CN111977029B - A multi-purpose transmission system and construction method thereof - Google Patents

Abstract

The present invention discloses a multi-purpose transmission system and a construction method thereof, which belongs to the field of aerospace technology. It includes an ultra-giant near-space aerostat and a space launch platform and a control platform in the upper part, a giant near-space aerostat and a transfer station platform that intersects the upper and lower parts in the middle part, an anchor station in the lower part, and cables and self-propelled cable cars between these three parts. Its unique feature is that the aerostat is equipped with sufficient air bags so that the load capacity of the aerostat will not decrease due to the increase in altitude. The main purpose of the present invention is to serve as an efficient and energy-saving space launch platform system set in an ultra-high airspace of 30 to 50 kilometers above sea level, and it also has multiple important uses. The present invention can use a large cable car to transport personnel, materials, space equipment, etc. to the ultra-giant aerostat through cables, and then the space launch platform will launch the space equipment into space. Compared with traditional, under-development and future aerospace methods, it has many advantages.

Description

A multi-purpose transmission system and construction method thereof

Technical Field

The present invention discloses an unprecedented multi-purpose transmission system and its construction method. It is a technology belonging to the field of aerospace. Its main purpose is to be a highly efficient and energy-saving ultra-high altitude space launch platform system set at an altitude of 30 to 50 kilometers. It can transport personnel, cargo, equipment, space vehicles, spacecraft and space materials to a super-giant near-space aerostat (super-floater) located at an ultra-high altitude by a large cable car through a cable, and then launch the spacecraft into space via the space launch platform and control platform thereon. Therefore, the present invention mainly belongs to the technology of the field of aerospace. The present invention also has multiple important uses.

Background Art

The present invention relates to a large number of technical fields. In order to illustrate that the present invention has a reliable technical basis and technical breakthroughs, the following main background technologies involved in the present invention are now necessary to explain.

1. New materials.

1. Ultra-high molecular weight polyethylene (UHMWPE) fiber.

UHMWPE is a thermoplastic engineering plastic with excellent cost performance. It almost concentrates the advantages of various plastics and its density is slightly lower than water. Its heat resistance, stiffness and hardness are relatively low, but its fiber strength is the highest among all commercialized fibers so far. It is also a super fiber material that my country can independently produce and manufacture on a large scale with high quality and will not be subject to foreign countries! UHMWPE fiber is used in the fields of navigation and aerospace such as ultra-long cables and near-space airships. It can reduce its own weight, increase effective load-bearing and load-carrying, improve the ceiling of airships and be durable. For example, the minimum breaking force of the current commercialized UHMWPE fiber rope with a diameter of 10mm is above 9.4t (tons). After optimizing the fiber twist and the type and content of fiber dipping, Chinese scientists have made the minimum breaking force of the same diameter UHMWPE fiber rope reach 12t! Assuming that this optimized fiber is woven into a ribbon cable with a thickness of 30mm and a width of 200mm, it is conservatively estimated that its minimum breaking force will reach 750--850t. If the cable is 15 km long from top to bottom, its deadweight is about 100 tons. If the passenger safety factor is set to 6 and the cargo safety factor is set to 4, its maximum effective load-bearing capacity for carrying passengers and cargo is 125 tons and 170 tons respectively, and the maximum effective net load-bearing capacity after deducting the deadweight of the cable is 25 tons and 70 tons respectively. If the cable is made thick at the top (54 mm) and thin at the bottom (30 mm), its deadweight is 140 tons, its minimum breaking force at the upper end is 1350-1440 tons, and its minimum breaking force at the lower end is still 750-800 tons, but its maximum effective net load-bearing capacity for carrying passengers and cargo will reach 125 tons and 170 tons or more respectively (the deadweight of the cable has been shared by the increased cable thickness)! Therefore, it is completely feasible to apply this fiber material to the cable system described in the present invention.

2. Poly(p-phenylene terephthalamide) (para-aramid) (PPTA) fiber.

The specific strength is 5 times that of steel. The biggest advantage is high temperature resistance, and it is widely used in the field of national defense and aerospace. The composite use of UHMWPE fiber and PPTA fiber will obtain excellent specific strength and high temperature resistance.

3. Poly(p-phenylene benzobisoxazole) (polybenzoxazole) (PBO) fiber.

High-end PBO fiber has the highest strength and modulus among existing chemical fibers; its heat resistance and flame retardancy are higher than any other organic fiber. A 1 mm diameter PBO filament can lift a weight of 450 kg, and its strength is more than 10 times that of steel fiber. It is a 21st century super fiber with a wide range of important uses.

4. Carbon nanotube fibers.

Carbon nanotube fibers have good mechanical properties, with a tensile strength of 50-200, which is 100 times that of steel, but only 1/6 of the density of steel; the elastic modulus is equivalent to that of diamond, about 5 times that of steel. The tensile strength of a single-walled carbon nanotube with an ideal structure is about 800GPa! Carbon nanotube fibers are revolutionary super fiber materials of the future, with extremely broad application prospects.

5. Polyvinyl fluoride (PVF.

)PVF film has excellent wear resistance and weather resistance, and can be used as the surface weathering layer of aerospace equipment.

6. Ethylene-vinyl alcohol copolymer (EVOH).

The most notable feature of EVOH resin is its gas barrier effect, making it most suitable as the helium barrier layer for the skin of airships and other aerostats.

7. Polyether polyurethane.

Polyether polyurethane is an excellent adhesive and welding agent for near-space airship skin materials.

(ii) Airship.

As one of the earliest aircraft, airships were once popular, but were gradually replaced by airplanes. In recent years, airships have regained attention, and countries have developed new airships. The main reason is that airships have a large effective load capacity and strong air transportation capacity, which can meet the needs of medium and long-distance air transportation. Modern advanced manufacturing control technology not only prevents the Hindenburg airship disaster from happening again, but also extends the use of airships. Countries are vigorously developing high-altitude and ultra-high-altitude airships for radar detection, early warning navigation, communication forwarding, emergency satellite function replacement, mobile communication services, astronomical observation, meteorological monitoring, ground exploration, surveying, mapping, ultra-high-precision observation and detection of the ground, emergency rescue, high-altitude and ultra-high-altitude tourism, etc. It can be seen that airships have very broad application prospects in the future.

Traditional airships, in order to increase their ceiling, must either reduce ballast or remove air from the airbags. However, as the altitude increases, the atmospheric pressure also drops sharply, and the pressure difference between the inside and outside of the airbags continues to increase, causing the expansion rate of the airbags and the bearing capacity of the skin to quickly reach their limits. Therefore, if you want the airship to fly higher, you should break the traditional and conventional layout of the airship and try to reserve enough large, lightweight, and high-strength airbags to accommodate the expanding gas in advance. In this way, even if the airship rises to an altitude of tens of kilometers and the buoyancy gas expands dozens or hundreds of times, there is no need to worry about the airbags bursting.

Summary of the invention

The main purpose of the present invention is to inherit and carry forward the advantages of various aircraft in the existing and under-development aerospace fields and to limit their respective disadvantages as much as possible, so as to build a ground-to-earth transmission system, specifically a space launch platform system established at an ultra-high altitude; therefore, the present invention is an unprecedented multi-purpose transmission system that mainly serves as an ultra-high altitude space launch platform.

To achieve the above-mentioned purpose, the technical solution adopted by the present invention is as follows: the main structure of the system includes a super-floating device and a space launch and control platform of the upper structure, a giant floater and a transfer station platform of the upper and lower intersections of the middle structure, an anchor station platform of the lower structure, and cables and cable cars connecting the upper, middle and lower parts; wherein the super-floating device of the upper structure is a new type of semi-rigid airship with a new concept V-shaped layout, the main part of which is a semi-rigid airship with a Zeppelin airship shape with a retracted tail, and the two sides of the main body are symmetrical spherical semi-rigid airships, the spherical semi-rigid airship includes an airbag that is unfolded into a nearly spherical shape after inflation and a shell-like outer cover that can accommodate the spherical airbag; the space launch platform is located at the main part of the super-floating device. The back surface includes a launch plaza with a runway and a space launch track, on which there is an orbital accelerator and a braking system, on which a carrier rocket is carried, a rope-pulling accelerator is installed at the bottom of the orbital accelerator, and the launch plaza is equipped with lifting equipment; the space control platform is located under the belly of the main body of the superfloater; at the center of gravity of the superfloater is a passageway connecting the space launch platform and the control platform from top to bottom, a gantry hanger is provided at the upper end of the passageway, the upper end of the moored transmission cable is fastened to the gantry hanger through the passageway, and an elevator for transporting personnel and materials up and down is installed on the inner wall of the passageway.

Furthermore, the giant float of the middle structure of the multi-purpose transmission system is an approximately reduced version of the super float, including a main body and a spherical semi-rigid airship, etc.; the upper and lower intersection transfer station platform includes a transfer cabin located under the belly of the main body of the giant float and a transfer plaza on the back; the upper and lower sections of the moored transmission cable are connected by a clutch device in the channel shaft of the giant float.

Furthermore, the anchor station platform of the lower structure of the multi-purpose transmission system includes a decomposable and autonomous central mooring anchor station and a triangular wind-resistant and tensile anchor station. The triangular wind-resistant and tensile anchor station is located at the vertex of an equilateral triangle centered on the central mooring anchor station. It can be moved according to meteorological conditions to adjust the angle and orientation of the triangular oblique wind-resistant cable to adapt to different wind speeds and directions to maintain the stability of the giant float. The bottom of the central mooring anchor station and the triangular wind-resistant and tensile anchor station have several roots drilled into the ground. Anchor piles of tens of meters; the lower half of the central mooring anchor station has the entrance and exit passage of the cable car, and the entrance and exit passage has a special gantry hanger for the cable car. From the gantry hanger to the inside of the passage is a cable car track lifted off the ground, and from the upper surface of the central mooring anchor station to the passage is the cable car channel shaft, and directly below the center of the cable car channel shaft is a cable rope retraction and release hinge device; the central mooring anchor station and the triangular wind-resistant and tensile-resistant anchor station are assembled from hollow combined units, and the cavity of the combined unit can be filled with water to increase weight.

Furthermore, the cable is divided into a moored transmission cable, a triangular obliquely-stayed wind-resistant and tensile-resistant cable and a lift overload protection cable; the cable retraction and release hinge device is provided in the super-floating device and the giant floater at the upper and lower ends of the triangular wind-resistant and tensile-resistant anchor station, the lift overload protection cable, and on the cable gantry hanger; the moored transmission cable is a high-strength fiber braided belt with a rectangular cross-section, which is thick on the top and thin on the bottom, and is divided into an upper and lower section, the lower section of which starts from the central mooring anchor station on the ground and ends at the transfer cabin, and the upper section starts from the transfer cabin, passes through the giant floater, the control platform, the super-floating device, and ends at the cable gantry hanger. The triangular obliquely-stayed wind-resistant and tensile-resistant cable is located between the triangular wind-resistant and tensile-resistant anchor station and the giant floater, the belly of the super-floating device and the back of the giant floater, and is used to prevent the buoyancy overload of the super-floating device after launch during large-scale space launches, causing the mooring cable to break. All of the above types of cables are equipped with damping oscillators that are wind-resistant and anti-vibration.

Furthermore, the cable car is a self-climbing powered cable car, which is divided into three functional parts, upper, middle and lower, by fireproof materials. The upper part is the power area, the middle part is the loading area, and the lower part is the safety emergency area; wherein, the upper end of the power area is a plurality of sets of strong magnetic clutch, opposite compression, synchronous wheel crawler travel devices, the travel device structure from outside to inside includes a cantilever, an outer cover, a strong magnetic clutch, a gear box, a gear mechanism, a synchronous crawler, a synchronous wheel and a synchronous wheel axle, the lower end of the travel device is connected to the oil drive and the electric drive respectively through a universal joint shaft, a transfer case, a transmission, and a coupling, the oil drive is connected to a fuel tank and an emergency landing shock absorbing air bag, the electric drive is connected to a large-capacity battery pack and a laser photoelectric panel or a fuel cell, the electric drive motor is a power generation and electric integrated machine, when the cable car runs downward, the electric drive motor can generate electricity by itself and store it in the battery pack, the power There is also an emergency fire station in the central area of the area, and large emergency deceleration parachutes are available on both sides of the power area; the cantilever of the traveling device is tightly connected to the loading area through the bracket, and the four sides of the rectangular bracket have a rotating surface that can be rotated and opened to facilitate the clutch of the cable car and the moored transmission cable; a number of clutch push-pull cylinders are installed from top to bottom on the outside of the rotating surface and the outside of the opposite bracket, and the piston of the cylinder passes through the bracket facade and is connected to the outer cover of the traveling device. The traveling device is clutched and engaged with the moored transmission cable through the piston movement of the cylinder; the loading area is an open space frame structure, which can be loaded with modular mission cabins that meet various transportation needs. The modular mission cabins are divided into personnel cabins, cargo cabins, space vehicle cabins, space fuel cabins, supply cabins, rescue cabins, etc. according to different carrying functions; the loading area is mainly composed of a frame and a concentric cylinder. The frame and the concentric cylinder are opened from top to bottom with a notch to facilitate the clutch of the cable car and the moored transmission cable; the aforementioned emergency shock-absorbing air bag is in the safety emergency area. The outer sides of the upper ends of the prisms around the safety emergency zone are emergency landing buffer rockets; the bottom of the through-cylinder is a guide wheel device with a principle structure similar to the crawler-type travel device; the cable car can run on the moored transmission cable at a speed of 15-30km/h.

Further, the launch plaza and the transfer plaza are equipped with self-balancing escape capsules, and the control platform and the bottom of the transfer capsule are equipped with emergency evacuation aircraft; multi-purpose modular functional areas are reserved inside the super-floating device and the giant floater, and inside and outside the space launch platform, the control platform and the upper and lower intersection transfer station platform. The multi-purpose modular functional area is selected to carry corresponding functional modules according to the needs of the current task of the earth-sky transmission system, such as: various types of radars, radar antenna modules, aerospace measurement and control modules, aerospace launch modules, emergency communication repeater modules, emergency satellite function replacement modules, mobile communication service modules, substitute synchronous satellite function modules, ground, sea, air and sky navigation modules, astronomical observation modules, meteorological monitoring modules, ground exploration, surveying and mapping modules, ground ultra-high precision observation and detection modules, emergency rescue modules, high altitude, ultra-high altitude tourism and sports modules, system self-defense and anti-destruction defense modules, etc.; rails are laid inside the super-floating device and the giant floater to facilitate the forward and backward movement of some of the functional modules to maintain the balance of the super-floating device and the giant floater.

Furthermore, the upper and lower outer surfaces of the shell-like outer cover, the control platform and the tail of the upper and lower intersection transfer cabins are each provided with a large electric propeller propeller, and the tail of the main body of the super-floating device and the giant floating device are each provided with an ultra-large electric propeller propeller; the head and tail upper surfaces of the main body of the super-floating device and the giant floating device, and the top surface of the spherical airbag are covered with a large area of thin-film solar cell arrays, and the thin-film solar cell arrays are connected to the battery packs inside the super- and giant floating devices.

Furthermore, when constructing this multi-purpose transmission system, all parts of the main structure of the system are installed with anti-static, lightning protection and lightning elimination devices; the manned airtight spaces such as the aerospace control platform, upper and lower transfer cabins, cable car personnel cabins and rescue cabins are equipped with oxygen production and supply systems, thermal insulation and pressure maintenance systems, cold-resistant and pressure-resistant shells, and ultraviolet and cosmic ray blocking coatings; the surfaces of other structural parts of the main structure of the system except the anchor station are covered with anti-aging and weather-resistant layers.

Furthermore, for the skin material of the super-floater and giant floater, the weather-resistant layer currently uses aluminum-plated + polyvinyl fluoride (PVF) film, the load-bearing layer currently uses ultra-high molecular weight polyethylene (UHMWPE fiber cloth or para-aramid (PPTA) and UHMWPE blended fiber cloth (suitable for the earth-to-sky transmission system at an altitude of 30km), and in the future, polybenzoxazole (PBO) fiber cloth (suitable for the earth-to-sky transmission system at an altitude of 30-50km) or carbon nanotube fiber cloth (suitable for the earth-to-sky transmission system at an altitude of more than 50km) may be used, the helium-barrier layer currently uses ethylene-vinyl alcohol copolymer (EVOH) coating, and the adhesive layer currently uses polyether polyurethane; the inner and outer surface protective layers currently use polyethylene (PE) or polyurethane (PU) coating; the cable manufacturing material, the load-bearing core material currently uses ultra-high molecular weight polyethylene fiber or (and) para-aramid fiber (suitable for the earth-to-sky transmission system at an altitude of 30km), and in the future, polybenzoxazole fiber (30-50km) or Carbon nanotube fiber (more than 50km), its weather-resistant and wear-resistant sheath layer currently uses polyvinyl fluoride fiber; the materials for building the internal skeleton of the super and giant floater, as well as the platform frame materials of the upper and lower intersection transfer station, the non-high-temperature resistant frame materials of the space launch, control platform and cable car, the mission cabin and functional module frame materials, the above component materials currently use ultra-high molecular weight polyethylene fiberboard laminated composite materials or (and) titanium steel, aluminum alloy, and will use PBO or carbon nanotube fiber materials in the future; the high-temperature resistant frame materials in the ground-to-earth transmission system currently use PPTA fiber materials or (and) titanium alloy, aluminum alloy, and will use PBO fiber or carbon nanotube fiber materials in the future; the construction of the ground-to-earth transmission system will use any known and future high-quality materials and their products to manufacture the system components, so as to achieve the positive goals of reducing weight and increasing buoyancy, reducing materials and strengthening, reducing consumption and increasing efficiency, safety and environmental protection.

Furthermore, when constructing the super-floater and giant floater, due to their extremely huge envelope volume, it is almost impossible to build a manufacturing plant that can accommodate them under existing technical conditions. Therefore, this construction plan abandons the traditional metal structure greenhouse plant and seeks concave geological structure points in nature that are surrounded by mountains on all sides and have low-lying and flat and open terrain in the middle, such as the Qinling high mountain canyons, the mountain valleys around the Sichuan Basin, or large tiankengs, craters, etc.; the selected construction site should be as close as possible to industrial cities and traffic arteries to facilitate the manufacture and transportation of construction materials and supplies. The low-lying terrain in the middle should be open enough, its length should be greater than 2.3km, its width should be greater than 0.9km, and the height of the mountains on all sides should be greater than 0.9k m; artificially close the narrow passes on the mountains on all sides as needed, build cable towers on the higher ground around, which can facilitate the construction of the roof and the installation of cable cars. The roof can be built with the ultra-high molecular weight polyethylene fiber cloth, and a large helium balloon can be used to hold up the middle of the roof; the super-floating device is manufactured in this semi-natural and semi-artificial super-large factory building. If the selected geological structure point has a ready-made access line, it will be directly transformed and utilized. If the terrain is steep and the transportation is inconvenient, several lifts will be built on the spot to solve the problem; if the transportation with the outside world is really inconvenient or even far away from the transportation line, one or several giant medium and low altitude airships will be built first, with a useful load capacity of tens to hundreds of tons, to solve the transportation problem with the outside world.

Beneficial effects of the present invention.

The present invention is an unprecedented, multi-purpose, energy-efficient, safe and environmentally friendly space-to-earth transmission system that combines the advantages of airships and rockets. It is also a space-to-earth transmission system that effectively avoids or limits the shortcomings and drawbacks of the above-mentioned aerospace technologies. Therefore, the present invention has many advantages and positive significance, which are described in detail below.

1. The present invention is compared with traditional airship technologies and those being developed by various countries. First, the space launch function of the present invention is unmatched by them; second, since the problem of the contradiction between the ceiling and the load caused by the expansion of the airbag has been solved, the perfect balance of the ceiling (30--50km) and the effective load (thousand tons) of the present invention is unmatched by them; third, since the air at high altitude and ultra-high altitude is thin and the resistance is small, the present invention is more convenient for long-distance and high-speed maneuvers; fourth, due to the multi-point distributed propeller thruster system of the present invention, the steering flight operation is more flexible, and the problem of slow steering action and difficult yaw correction of the airship has been solved to the greatest extent; fifth, since the present invention has mooring cables, mooring anchor stations, wind-resistant oblique cables, and wind-resistant oblique anchor stations, the ground-to-earth transmission system is easier to achieve static hovering and synchronous positioning, and the energy consumption is relatively lower.

2. Compared with the traditional ground-launched rocket technology, the present invention has greater advantages and significance. First, the research and development, manufacturing, and launch of rockets are very expensive, which will consume a huge amount of human wealth. The larger and heavier the rocket, the more expensive it is. The space-to-earth transmission system described in the present invention uses rockets at an ultra-high altitude of 30-50km, that is, the space launch starts in near space, avoiding the thick and heavy surface atmosphere. The thin atmosphere makes the resistance to the rocket very small, and at the same time greatly improves the efficiency of the rocket engine. Therefore, compared with the traditional ground rocket launch, the rocket shell size, engine size, and fuel consumption required for the same launch mission of the present invention are greatly reduced. Under ideal conditions, the launch cost can be saved by more than 50%, and the economic benefits are significant. Secondly, rocket launches require the use of a large amount of expensive aerospace fuel, which consumes a large amount of precious human energy. Most of the fuel consumed by traditional rocket launches is used for the rocket itself to break through the thick atmospheric troposphere. Compared with the mass of the spacecraft actually sent into space, it is really high consumption and low efficiency. The present invention avoids the troposphere and directly launches in the stratosphere where the air is thinner, which will greatly save fuel and enable humans to do more with limited resources. Third, the huge amount of rocket fuel burned in the atmosphere will cause serious pollution and damage to the atmospheric environment, and with the intensification of human space activities, this damage to the atmosphere will become more and more serious! The present invention greatly reduces fuel consumption, thus effectively reducing the pollution and damage to the atmosphere, which is beneficial to environmental protection. Fourth, the more heavy rocket launch projects involve, the longer the cycle of research and development, manufacturing, transportation, preparation, and launch, which is increasingly incompatible with future aerospace needs. Compared with the traditional aerospace launch method, the launch method of the present invention greatly reduces the size and weight of the rocket required for the same payload mission, so the launch cycle is greatly shortened, the efficiency is improved, and the launch frequency can be significantly increased. Fifth, because traditional rocket launches need to pass through the troposphere, they will be affected by the complex and changeable meteorological conditions in the troposphere. For safety reasons, they have to look for and wait for a suitable "window period". The launch process of the present invention skips the troposphere and launches in the stratosphere where the meteorological conditions are relatively stable. The launch process is more stable and safe, and the impact of the "window period" is greatly reduced. It can even transmit and launch non-stop day and night, which once again increases the launch frequency. Sixth, when traditional rockets are launched, friction with the air will generate high temperatures, so thick insulation tiles need to be laid on the surface of the rocket body. The present invention is launched in ultra-high altitudes where the air is thin, and frictional heat is less, which can greatly reduce the use of insulation tiles, which once again helps to reduce energy consumption and increase the launch load. Seventh, traditional rocket launches only serve to carry spacecraft. In addition to being able to complete space launch missions, the ground-to-air transmission system of the present invention itself has many important uses. The super-float and giant float can optionally carry and install numerous functional modules inside, which can accomplish various important tasks, such as radar detection, aerospace measurement and control, emergency communication forwarding, emergency satellite replacement, mobile communication services, earth exploration, deep space exploration, astronomical observation, meteorological monitoring, emergency rescue, ultra-high precision observation and detection of the earth, substitute synchronous satellites, all-round navigation of the land, sea, air and space, high-altitude and ultra-high-altitude tourism, system self-defense protection, emergency and safe evacuation of personnel, and other important uses.

BRIEF DESCRIPTION OF THE DRAWINGS

In order to more clearly illustrate the technical solutions of the present invention in the embodiments, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the following drawings are only for some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

FIG1 is a three-dimensional schematic diagram of the overall structure of the multi-purpose transmission system when viewed from the southwest axis.

Figure 1-1 is a three-dimensional schematic diagram of the overall structure of the multi-purpose transmission system viewed from the northwest axis.

Fig. 2 is a three-dimensional superimposed schematic diagram of the shell-like cover (of the spherical semi-rigid airship) in the opening and closing states at high, medium and low altitudes.

FIG3 is a three-dimensional schematic diagram of the anchor station platform structure (lower right figure) and the enlarged central mooring anchor station structure (upper left figure).

FIG. 4 is an enlarged three-dimensional schematic diagram of the cable and the channel shaft.

FIG5 is a three-dimensional schematic diagram of the cable car structure (left picture) and a three-dimensional schematic diagram of the cable car safety emergency zone turned upside down (right picture).

Figure 5-1 is a three-dimensional schematic diagram of the cable car bracket structure, rotating surface, and universal joint transmission shaft.

Figure 5-2 is a three-dimensional schematic diagram of the decomposed structure of the cable car traveling device.

FIG6 is an enlarged three-dimensional schematic diagram of the space launch platform and its local structure.

FIG. 7 is a three-dimensional schematic diagram of the control platform structure.

FIG8 is a three-dimensional schematic diagram of the platform structure of the upper and lower intersection transfer station.

FIG9 is a three-dimensional schematic diagram of the positions of the solar battery pack, gas storage tank, ballast, and some functional modules.

In the figure: 1--super giant near-space aerostat (referred to as super aerostat) 2--space launch platform 3--control platform 4--giant near-space aerostat (referred to as giant aerostat) 5--upper and lower intersection transfer station platform 6--anchor station platform 7--cable 8--cable car 11--main part of super aerostat 12--spherical semi-rigid airship 13--channel shaft 131--cable gantry hanger 132--transfer elevator 14 (44)--super large electric propeller thruster 16 (46)--gas storage tank 17 (47)--solar battery pack 18 (48)--guide rail 19 (49)--ballast 121--spherical airbag 122--shell cover 21--launch plaza 22--space launch track 23 (521)--self-balancing escape capsule 25--lifting equipment 221--Orbital accelerator 222--Launch vehicle 223--Rope traction accelerator 224--Braking system 31(511)--Emergency evacuation vehicle 41--Main part of giant float 42--Spherical semi-rigid airship of giant float 43--Access shaft of giant float 51--Transfer cabin 52--Transfer plaza 61--Central mooring anchor station 62--Triangular wind-resistant and anti-tension anchor station 63 Anchor station platform hollow combination unit 64--Anchor pile 611--Cable retracting and releasing hinge device 612--Cable car access channel 613--Orbit gantry hanger 614--Cable car track 615--Cable car access shaft 71--Mooring transmission cable 72--Triangular inclined wind-resistant and anti-tension cable 73--Lift overload protection cable 74--Wind-resistant pendulum damping shock absorber 711--Lower section of moored transmission cable 712--Upper section of moored transmission cable 81--Cable car power area 82--Loading area 83--Safety emergency area 811--(Strong magnetic clutch, opposite pressure, synchronous wheel crawler type) travel device 8111--Cantilever 8112--Outer cover 8113--Strong magnetic clutch 8114--Gear box 8115--Gear mechanism 8116--Synchronous crawler 8117--Synchronous wheel 8118--Synchronous wheel shaft 8121--Universal drive shaft 8122--Transfer case 8123--Transmission 8124--Coupling 8131--Oil drive 8132--Fuel tank 8141--Electric drive 8142--Battery pack 8143--Laser photoelectric panel 8144--Fuel cell 815--Emergency fire station 816--Emergency deceleration parachute 817--Pendant 8171--Pendant rotating surface 8172--Clutch push-pull cylinder 821--Loading area frame 822--Through cylinder 823--Notch 831--Emergency landing shock absorbing air bag 832--Emergency landing buffer rocket 833--Guide wheel device 1221(33 513)--Large electric propeller thruster 15(45 12114211)--Thin-film solar cell array 24(32 512 522)--High-power multi-purpose laser.

DETAILED DESCRIPTION

The following further illustrates the structural features, working principles and advantages of the present invention by taking the multi-purpose transmission system leaving the factory, base assembly and launch, space launch, emergency rescue, ultra-high precision observation and detection of the ground, etc. as examples. Obviously, the embodiments described below are only a small part of the many implementation methods of the present invention, not all of them. The data ratio parameters that appear are only for better explanation of the structural features, working principles and advantages of the present invention, rather than for limitation of the present invention. All other embodiments or improvements and changes obtained without creative labor based on the spirit and principles of the present invention fall within the scope of the rights protection claimed by the present invention.

Embodiment 1. Factory delivery.

After all components of the multi-purpose transmission system are manufactured and tested, they will be moved from the manufacturing base to the space launch ground base (if the manufacturing base has superior conditions in all aspects, it can also be directly transformed into a space launch ground base). To facilitate aerial maneuvering, the system will be temporarily combined into two sets of autonomous maneuvering aerostats, one with the super-floating device (1) as the main body and the other with the giant floating device (4) as the main body. First, the functional modules, the mission cabin, the cable car (8), the upper section of the mooring transmission cable (712), the lift overload protection cable (73) and other components planned to be carried are temporarily installed, fixed and stored in the functional areas of the super-floating device (1), the space launch plaza (21) and the control platform (3); the central mooring anchor station (61) and the triangular wind-resistant and anti-tension anchor station (62) are disassembled into the hollow combined unit (63), and then stored and fixed together with the lower section of the mooring cable (711), the triangular wind-resistant and anti-tension cable (72) and the spare cable car (8) in the upper and lower intersection transfer station (5). (If the manufacturing base has good external traffic conditions, the central mooring anchor station (61) and the triangular anti-wind anchor station (62) can be disassembled and can be driven to the space launch ground base by land transportation by self-powered motorized equipment.) Then, the super-floating device main body (11) and the giant floater main body (41) are filled with buoyancy gas and loaded with ballast (which can store water or dry ice). After adjusting the buoyancy, the super-floating device (1) and the giant floater (4) are slowly lifted into the air one after another. At the same time, the thin-film solar cell array (15) (45) starts to generate electricity and charge the solar battery pack. The large and super-large electric propeller propulsion devices (1221) (4221) (513) (14) (44) powered by the solar battery pack are started, and the super-floating device (1) and the giant floater (4) rise to the medium and low altitude airspace and fly to the space launch ground base at medium or low speed. At this time, the spherical airbag (121)(421) of the spherical semi-rigid airship (12)(42) is in a state of being stored in the shell-shaped outer cover (122)(422).

Embodiment 2: Base assembly and launch.

After the multi-purpose transmission system leaves the factory, it flies at a medium or low altitude to the space launch ground base. The giant float (4) maneuvers at a low speed to the top of the predetermined installation position of the triangular wind-resistant and anti-tension anchor station (62) and remains in a hovering position. After the hollow combination unit (63) of the triangular wind-resistant and anti-tension anchor station (62) is loaded in the transfer cabin, the spare cable car (8) is moved into the channel shaft (43) through a special slideway facility. The strong magnetic clutch (8113) on the cable car travel device (811) is separated, and the pylon rotating surface (8171) is opened, driving the travel device (811) to deflect, and the guide wheel device (833) is opened in the same manner. The lower section (711) of the mooring cable enters the center position of the cable car through the notch (823) on the cable car frame (821) and the through-column (822). Then the pylon rotating surface (8171) is closed, and the strong magnetic clutch (8113) is closed. The guide wheel device (833) is similarly closed. At this point, the cable car (8) is coupled to the lower section (711) of the mooring cable. Then the cable car (8) starts the oil drive (8131) or the electric drive (8132), and the transmission (8123) is adjusted to the reverse gear, and through the transfer case (8122), the transmission shaft (8121), the gear mechanism (8115), the synchronous wheel (8117), and the synchronous crawler (8116), the cable car (8) is able to run downward at a low speed on the lower section (711) of the mooring cable. When the cable car (8) runs to the part of the mooring transmission cable where the anti-wind swing damping shock absorber (74) is located, the guide wheel device (833) and the synchronous wheel track travel device (811) are separated in turn in opposite directions under the action of the strong magnetic clutch (8113) and the clutch push-pull cylinder (8172). After the guide wheel device (833) and the synchronous wheel track travel device (811) pass over the anti-wind swing damping shock absorber (74), they are again closed and pressed in opposite directions under the action of the clutch push-pull cylinder (8172) and the strong magnetic clutch (8113). During this process, the cable car (8) only needs to slightly reduce the travel speed without stopping. When the cable car (8) runs to the ground, the hollow combination unit (63) is immediately removed and the triangular wind-resistant and anti-tension anchor station (62) and the anchor pile are assembled. (64) drilled into the ground. After the cable car (8) is loaded with a certain amount of ballast, the traveling device (811) is started, the gear is changed, and it starts to climb upward. At the same time, the super float (1) hovers above the giant float (4), and begins to release the upper section of the mooring cable (712) and the lift overload protection cable (73) downward to dock with the giant float (4). When the hollow combination unit (63) is continuously transported to the ground by the cable car (8) and the assembly of the triangular wind-resistant and tensile anchor station (62) is completed, the giant float (4) releases the wind-resistant and tensile cable (72) downward to dock with the triangular wind-resistant and tensile anchor station (62). Wait for the three triangular wind-resistant and tensile anchor stations to be connected. (62) After the transmission, assembly and docking are completed, the transmission, assembly and docking of the central mooring anchor station (61) are started. When the docking of the super-floating device (1) with the giant floating device (4) and the giant floating device (4) with the anchor station platform (6) is completed, the super-floating device (1) and the giant floating device (4) begin to rise at a uniform speed. As the height increases, the spherical airbag (121) of the spherical semi-rigid airship (12) (42) begins to absorb the buoyancy gas that expands and overflows from the main body of the super-floating device (11) and the main body of the giant floating device (41) and gradually inflates and unfolds until it rises to its respective rated height and fully unfolds into a spherical shape. Subsequently, the super-floating device (1) and the giant floating device (4) adjust their buoyancy, maintain hovering, and enter a mission standby state.

Example 3. Space launch.

After receiving the space launch mission in the standby state, the multi-purpose transmission system will take corresponding operation steps depending on the mission type. Since the space launch involved in the present invention starts in the near space at an altitude of 30-50km or above, the thick and heavy surface atmosphere is avoided. The thin atmosphere makes the resistance to the rocket very small, and at the same time greatly improves the efficiency of the rocket engine. Therefore, compared with the traditional ground rocket launch, the rocket shell size, engine size, and fuel consumption required to complete the same load launch mission of the present invention are greatly reduced, and the use of rockets of the same specifications can bear a larger launch load.

When the launch mission is a medium- and low-orbit small-sized satellite, the total weight of the satellite and the carrier rocket (222) will be reduced from less than 100 tons of the traditional ground launch type to less than 60 tons. For this type of launch, three plans can be selected. One: The ground base completes the assembly of the satellite and the rocket, and directly uses the cable car (8) to transport the satellite and the rocket together to the space launch platform (2). Then launch into orbit as planned. The second: Various types of small and medium-sized rockets are first transported to the space launch platform (2) for inventory by the cable car, and at the same time, various modular emergency satellites are also transported to the space control platform (3) for standby. If an emergency satellite launch is required, it is only necessary to select a modular emergency satellite and a corresponding rocket for the required purpose, and after rapid assembly on the space launch platform (2), it can be immediately launched into space. The third: If it is a normal commercial satellite launch, the customized satellite must first be transported to the ground base, then transported to the space launch platform by the cable car, and then a matching rocket is selected for assembly, and then it can be launched.

When the launch mission is a large-scale space launch activity in a medium or high orbit, if the space launch platform (2) of the present invention is used for launch, the required rocket tonnage is much lower than that of a traditional ground-launched rocket, but the absolute value is still very high. A more complex solution is needed. Now, take the extreme mission project of manned lunar landing as an example to illustrate. Although there is no giant carrier rocket like Saturn V that can fly directly to the moon, we can use a heavy rocket of the Long March 5 level to launch several times in the form of the Earth orbit assembly method. Then rely on the "Tiangong" space station to dock and combine into a lunar landing spacecraft with a first-stage Earth-Moon orbit acceleration rocket. Since the take-off method of the space launch platform is compared with the ground take-off method, the resistance of the rocket is reduced, the efficiency of the rocket engine is improved, and the ascent path is shortened, so the payload of the same type and type of rocket is significantly increased. Conservative estimates can increase the near-Earth orbit payload of my country's Long March 5 rocket to more than 30 tons, and the synchronous orbit payload to more than 18 tons. The total weight of the lunar spacecraft is about 45 tons (excluding the weight of the Earth-Moon orbit acceleration rocket), of which the command module and service module weigh about 30 tons, and the lunar module weighs about 15 tons. In addition, the Earth-Moon orbit acceleration rocket engine and rocket weight about 10 tons, and the rocket fuel is more than 30 tons (this fuel is equivalent to the fuel required for the second ignition and orbit change of the third stage of the Saturn V rocket. And the altitude of China's Tiangong space station is 400 kilometers, and the fuel required for orbit change at this altitude will be less than the fuel required for the second ignition and orbit change of the third stage of the Saturn V rocket at an altitude of 300 kilometers). The total weight of the lunar spacecraft and the acceleration rocket is about 90 tons. Therefore, the lunar spacecraft can be divided into three sections and launched to the "Tiangong" space station in three times. They are about 30 tons of rocket fuel tank section, about 30 tons of command and service module section, about 15 tons of lunar module + about 10 tons of Earth-Moon orbit acceleration rocket engine and rocket body + about 5 tons of reserve rocket fuel section. The Long March 5 rocket is used to launch the various sections of the lunar landing spacecraft from the space launch platform (2) to the preset docking points of the Tiangong space station in three times, and then docked and assembled using the auxiliary facilities of the space station, and finally separated from the space station at an appropriate time, changed orbit and flew to the moon.

To prove the feasibility of the present embodiment, it is necessary to demonstrate the basic technical parameters of the minimum requirements required for the multi-purpose transmission system to complete the present embodiment. The super-floating device (1) reaches a ceiling of 30 km and performs a minimum technical parameter demonstration scheme for large-scale space launch under current material and technical conditions: the main body (11) of the super-floating device is 600 meters long, 150 meters at the maximum diameter, an envelope volume of about 7 million cubic meters, a maximum buoyancy of 7,150 tons, a designed empty weight of 3,400 tons, a useful load of 1,500 tons, a reserve load of 2,250 tons, and an ultimate load of 7,200 tons. The spherical body diameter of the spherical semi-rigid airship (12) on the left and right sides of the super-floating device main body (11) after being fully expanded after being inflated is 777 meters, and the envelope volume of the left and right spheres is a total of 490 million cubic meters, and the designed empty weight is a total of 2,000 tons. In summary, the total maximum envelope volume of the super-floating device is nearly 500 million cubic meters, the maximum buoyancy is 7150 tons, the maximum load is 7200 tons, the overall empty weight is 5400 tons, and the effective load is more than 1500 tons. The technical parameters of the main part (41) of the giant floater are roughly equivalent to or slightly smaller than those of the main part (11) of the super-floating device. Because the giant floater (4) is at an altitude of 15 km, the expansion rate of the buoyancy gas is much lower than the buoyancy gas in the super-floating device (1), therefore, the technical parameters of the giant floater spherical semi-rigid airship (42) will be much smaller than the technical parameters of the super-floating device spherical semi-rigid airship (12), so that the effective load of the main part (41) of the giant floater is greatly increased. The technical parameters of the various cables (8) have been demonstrated in the aforementioned "Technical Background", and only the parameters shown need to be adjusted or enlarged, and will not be repeated here. The cable car frame components can be telescopically adjusted to adapt to loading tasks of different shapes and sizes. The maximum size of the cable car (8) is not less than 10mx5mx30m. Its maximum load capacity matches the technical parameters of the mooring cable (71). The tensile strength of the central mooring anchor station (61) and each of the triangular wind-resistant and tensile anchor stations (62) is above the thousand-ton level. It should be stated that the above-mentioned technical parameter demonstration scheme is only to confirm the feasibility of the following embodiment description. The actual technical parameters of the super-floating device and the giant floating device will be determined according to the material technology development level in different periods and the scope of space launch missions and other use scopes. Any technical parameter scheme proposed based on the spirit and principle of the present invention falls within the scope of the rights protection claimed by the present invention.

The specific implementation process is as follows: first, the cable car (8) is used to transport the fuel at each level, the rocket body and the engine at each level of the Long March 5 rocket launched in a single launch, and the load of the first launch - the fuel tank of the about 30-ton orbit-changing accelerating rocket, to the space launch platform (2) in turn along the transmission cable, and the assembly is completed on the orbital accelerator using the special equipment such as the lifting equipment (25). In this process, when the cable car (8) moves upward to the giant floater channel well (43), it is first separated from the moored transmission cable lower section (711), and then combined with the moored transmission cable upper section (712), and then continues to climb upward. In other words, when the cable car (8) travels back and forth between the ground and the super floater (1), it is necessary to complete the relay handover of the upper and lower sections of the moored transmission cable (71) in the giant floater channel well (43). After the Long March 5 rocket is transferred and assembled, it can be launched on the space launch platform (2) as planned, so as to transport the payload to the Tiangong space station docking point. In this way, three consecutive launches can transport all components of the lunar landing spacecraft to the Tiangong space station docking point and then complete the docking assembly and fuel filling. The lunar landing astronauts can also arrive at the Tiangong space station with the command service module with the last launch and wait for orders.

Since it is impossible to ensure that the materials used in the components of the super-floating device (1) and the moored transmission cable (71) can withstand the burning of the ultra-high temperature flame heat wave when the rocket is ignited and taken off under the current material technology conditions, it is necessary to adopt a gliding acceleration-throwing method to take off. The purpose is to allow the rocket to officially ignite and take off after leaving the super-floating device at a certain horizontal safety distance. In specific implementation, the cable traction machine (222) tows the self-driven orbital accelerator (221) carrying the Long March 5 from the middle of the launch track (22) at a low speed to the highest point of the slope surface of the launch track (22) located above the head of the super-floating device (1). In this process, the gas tanks and ballast inside the super-floating device (1) are moved in an orderly manner on their respective guide rails to the tail of the super-floating device main body (11) under the control of the intelligent system to balance the changing center of gravity position and keep the space launch plaza (2) in a horizontal state as much as possible.

Since the Long March 5 rocket is a heavy rocket, in order to prevent the buoyancy overload of the super-floating device (1) from damaging the mooring transmission cable (71) and the like after launch, before launching, a plurality of lift overload protection cables (73) prepared on the super-floating device (1) are released and connected to the giant float (4). During launching, the super-floating device (1) takes the head against the wind, and the orbital accelerator (221) is continuously accelerated by the four forces of the traction force of the rope traction accelerator (223) in the middle of the launch track (22), the self-driving force of the orbital accelerator (221), the gravity sliding component of the inclined surface of the launch track (22) and the wind force, carrying the Long March 5 rocket, and finally reaching the other end of the launch track (22) at a higher speed. Under the control of the intelligent system, the orbital accelerator (221) releases the clamping device of the Long March 5 rocket in advance and in time, and immediately decelerates and stops under the action of the braking system (224). The Long March 5 rocket is ejected by virtue of its huge inertia. During this process, as the Long March 5 rocket moves on the launch track (22), the center of gravity of the super-floating device (1) moves again. Therefore, the ballast (15) and the gas tank (16) inside the super-floating device (1) move in the opposite direction relative to the Long March 5 rocket on their respective guide rails (18) under the control of the intelligent system to adjust the center of gravity of the super-floating device and prevent the super-floating device from being seriously tilted. At the same time, the cable retracting and releasing hinge device (616) continuously adjusts the retraction or release of each lift overload protection cable (73) under the control of the attitude sensing and cable force sensing intelligent control system of the super-floating device (1) to evenly offset the buoyancy of about 1,000 tons that suddenly increases after the Long March 5 rocket is ejected, and maintain the attitude of the super-floating device. At the same time, the gas tank inside the super-floating device is sucking and compressing the buoyancy gas at maximum power, further reducing the overall buoyancy of the earth-to-sky transmission system and alleviating the tension on the cable (7) system. Afterwards, when the Long March 5 rocket is thrown away from the tail of the super-floating device at high speed to a safe distance, the rocket attitude control system is activated, and the rocket vector nozzle intermittently sprays compressed gas to adjust the rocket attitude to maintain horizontal flight and horizontal speed. At the same time, a large amount of water mist or dry ice is quickly sprayed from various places at the tail of the super-floating device (1) for isolation and protection. When the rocket is thrown to a safe distance, the vector nozzle adjusts the rocket attitude to be perpendicular to the horizontal direction. Then it automatically ignites and takes off immediately. After obtaining sufficient initial velocity, the rocket enters the ascent phase and flies to the Tiangong space station, transporting about 30 tons of fuel required for the lunar landing spacecraft to accelerate the rocket to the space station for standby.

After two more launches, the remaining sections of the lunar spacecraft and astronauts will be transported to the Tiangong space station docking point. The docking assembly and fuel filling of the lunar spacecraft will be quickly completed using the special facilities at the docking point, and the spacecraft will be ready for launch. After entering the launch window, the lunar spacecraft accelerator rocket will ignite, and the spacecraft will begin to accelerate and change its orbit to fly to the moon. After entering the Earth-Moon transfer orbit, it will separate from the accelerator rocket. The subsequent lunar landing and return process is similar to that of the Apollo spacecraft. The difference is that Apollo discarded the service module before re-entering the atmosphere during the return. Now that we have the Tiangong space station, we can leave the service module in the space station, and it can be used again after maintenance, or it can continue to play a role as a module of the space station.

It can be seen that as long as the space-to-earth transmission system of the present invention is built, the existing aerospace technology and heavy-duty carrier rockets can complete the manned lunar mission. Its significance lies not only in energy saving and environmental protection, but also in greatly accelerating the pace of deep space exploration in my country.

Embodiment 4. Emergency relief.

As a multi-purpose transmission system, the present invention not only has the main purpose of being used for ultra-high altitude space launches, but also has other extensive and important uses. Some of its other uses are now further explained as examples. Every year, many serious natural disasters occur in the world, causing huge losses to mankind, such as earthquakes, forest fires, wind disasters, snow disasters, floods and droughts. Some disasters occur in remote and primitive areas, with inconvenient transportation and difficult rescue. Some disasters will also seriously damage roads and bridges, block transportation and communications, and aggravate the disaster. When such major disasters occur, the earth-to-sky transmission system can play a key role that is superior to ground transportation and aircraft-type air transportation, and make important contributions to disaster prevention and relief. The following is a demonstration using the disaster scenes of the Greater Khingan Range fire and the 5.12 earthquake level as examples.

When a forest fire occurs in a remote primeval forest, the fire area is far from modern transportation lines, and large-scale fire-fighting, felling equipment, and disaster relief forces cannot arrive quickly. The water source required for fire-fighting is even more scarce. Therefore, once a forest fire occurs, it often lasts for ten days, a half month, or even several months, causing huge losses to the country and causing huge damage to nature. Now, if a forest fire of this degree occurs, the earth-sky transmission system of the present invention immediately switches from the standby state to the emergency rescue-forest fire mission mode. The ground base immediately removes the stored related equipment and materials, and the super-floating device (1) and the giant floating device (4) quickly descend to a low altitude, shortening the length of the moored transmission cable (71) so that the irrelevant functional modules can be quickly unloaded by the cable car (8). Then the ground base transports the first batch of disaster relief equipment and materials including water, dry ice, etc. to the super-floating device (1) by the cable car, and finally loads them into the backup center mooring anchor station (61). After the super-floating device (1) is fully loaded, it immediately rises into the stratosphere and then flies to the fire area at high speed. Destinations within a radius of 5,000 kilometers of the country can be reached within 30 hours after receiving the order. During this period, disaster relief forces from all over the disaster area will also immediately gather from the ground to the disaster area. Then the giant float (4) will also carry the second batch of disaster relief equipment, materials, and disaster relief forces to the disaster area quickly. After the super float (1) arrives near the disaster area, it will immediately open a disaster relief command and dispatch base next to the traffic trunk line closest to the fire scene together with the local disaster relief forces to uniformly deploy the disaster relief forces and equipment and materials assembled by all parties. And use the advanced observation equipment on the super float to monitor and map the disaster situation 24 hours a day at high altitude, quickly formulate a disaster relief plan, and select a frontier disaster relief base. After the giant float (4) arrives at the disaster area, it will immediately go to the predetermined frontier disaster relief base (the frontier disaster relief base should be selected in the front direction of the fire spread, but it is safe enough from the fire scene, the terrain is flat and the vegetation is relatively sparse). After arriving at the location, the central mooring anchor station (61) and all equipment, materials and personnel will be unloaded by the cable car (8). The vanguard immediately clears the site, cuts down trees and vegetation, and creates a fireproof isolation zone. Then, while continuing to open up fireproof isolation zones on both sides of the fire scene, the central mooring cable (71) and lift overload protection cable (73) on the super-floating device (1) are combined with special grabs, hoisting equipment, etc. to move the cut trees away from the scene, or transport them back to the disaster relief command and dispatch base as ballast by air. After that, the super-floating device cooperates with the giant floating device and helicopters to fight back and forth. Subsequent firefighting and felling equipment, firefighting materials, disaster relief forces, etc. are transported to the firefighting site, and the strategy of "blocking the front and extinguishing the fire on both wings" is adopted. A large number of mechanized felling equipment are deployed at multiple points in the direction of the fire front, and the fire isolation belt is rapidly expanded and extended. At the same time, a large number of manpower, firefighting equipment, and firefighting materials are used to carry out firefighting work on both wings of the fire. At the same time, the people and materials in the disaster area are actively evacuated to safe areas, and the fire situation is closely monitored, weather changes are monitored, wind speed and direction are predicted, and atmospheric and environmental pollution conditions are detected and evaluated. During the disaster relief process, we should always be vigilant against the damage of the high temperature heat wave of the fire scene to the non-high temperature resistant material components currently used in the super float (1) and the giant float (4), and prevent them from appearing at close range in the downwind position of the fire front. When the fire approaches the front disaster relief base and the fire isolation belt, all personnel, materials, equipment, the super float (1) and the giant float (4) should be evacuated quickly in advance. After the fire is controlled and extinguished, the super-float and the giant float can recover relevant equipment, materials and personnel, return to the ground base and resume standby status.

When a geological disaster with an earthquake intensity of 5.12 occurs, the multi-purpose transmission system switches from the standby state to the emergency rescue-earthquake disaster relief mission mode. After the giant floater (4) is quickly separated from the super floater (1), it immediately takes off lightly and flies to the disaster area at full speed. Destinations within a radius of 5,000 kilometers from the border should be reached within 20 hours. At the same time, the provinces and cities surrounding the disaster area immediately dispatch relevant geological experts, elite medical emergency teams, communication maintenance and support teams, field special teams, etc. to form a disaster relief advance team of about 300 people, and each of them will quickly assemble from their jurisdiction to the predetermined location in the cities surrounding the disaster area. The city where the assembly point is located should immediately dispatch relevant disaster relief equipment and materials such as communications, medical care, and engineering machinery from the local area to the assembly point. The super floater (1) completes the configuration of the earthquake disaster relief function module at the ground base, and then flies to the disaster area at full speed carrying the disaster relief team and equipment and materials urgently dispatched from the base and the surrounding areas of the base. When the giant float (4) arrives at the predetermined assembly point, it immediately carries 300 disaster relief advance teams and the first batch of disaster relief equipment and materials into the disaster area. In the epicenter area where the disaster is the most serious and transportation and communication are blocked and severely damaged, the giant float restores communication relay transmission from the air, surveys and assesses the disaster situation and reports to the command center, and selects a safe and favorable landing site. When the opportunity arises, the cable car (8) is used to safely transport the disaster relief advance team and disaster relief equipment and materials to the ground to carry out disaster relief operations. When the super float (1) arrives at the predetermined assembly point, it immediately carries the disaster relief teams and equipment and materials from all parties that arrive later, and establishes an aerial medical rescue center on the super float, and then immediately enters the disaster area. After receiving a certain number of wounded and elderly and young victims, the giant float (4) returns to the assembly point, and is then diverted to various treatment and relief points by other transportation forces. The communication relay and survey tasks of the giant float (4) in the disaster area are relayed by the super float (1). After that, the super-floating device and the giant floating device work together, alternately travel back and forth between the disaster area and the assembly point, and continuously transport the equipment and material resources of the subsequent rescue teams to the areas with severe traffic blockages, and then transport the injured and trapped victims in the disaster area out of the disaster area, forming a lifeline for emergency medical relay from the disaster site to the air and the surrounding ground. The giant floating device can carry hundreds of people and hundreds of tons of equipment and materials each time, and the super-floating device can carry up to thousands of people or thousands of tons of equipment and materials each time. The powerful mobility, transportation capacity, adaptability, and advanced and complete module functions win precious time for disaster relief, and promptly send rescue forces and equipment and materials to the disaster-stricken areas that were originally unable to be rescued due to communication interruptions and traffic blockages. The super-floating device and the giant floating device will become "magic weapons" in earthquake relief.

Example 5. Ultra-high precision observation and detection of the ground.

Since the multi-purpose transmission system can carry various most advanced and high-precision detection equipment and can hover at an ultra-high altitude of tens of kilometers for a long time, it has the ability to accurately and finely detect the ground, sea, air, and space, and the long, medium and short distances of various types of equipment. The super-floating device can hover at an ultra-high altitude of more than 30 kilometers for a long time, detect various types of aircraft within a range of thousands of kilometers, conduct high-resolution observation within a radius of more than 1,000 kilometers on the ground, and use the staring function to conduct long-term, uninterrupted, high-definition and high-resolution observation and monitoring of targets within a range of hundreds of kilometers.

Embodiment 6. Carrying other types of air and space flying objects.

The above content is to further illustrate the principle, structure, use and significance of the present invention by using the embodiments of the multi-purpose transmission system such as delivery, assembly, space launch, emergency rescue, etc. The above embodiments are described and recorded only as examples and are not intended to limit the disclosure, scope of application or mode of use of the present invention. Without departing from the spirit of the basic structure, principle and characteristic scope of the present invention, the present invention will also have various changes and improvements (for example, the V-shaped layout shape of the super floater and the giant floater will inevitably be continuously optimized and improved in the future for the dual considerations of drag reduction, energy saving and weight reduction and load increase, as well as the progress of new material technology). All these changes and improvements fall within the scope of the claims of the present invention to be protected. The scope of rights of the present invention will include any embodiment or (and) improvement and change that falls within the structure, principle and attached claims described in the previous description.

Claims (8)

1. The utility model provides a multipurpose transmission system as ultra-high space launching platform which characterized in that: the main body structure of the system comprises an upper huge near space aerostat (1), an aerospace launching platform (2), a control platform (3), a middle huge near space aerostat (4), an upper and lower intersection transfer station platform (5), a lower anchor station platform (6), and a cable (7) and a cable car (8) which are connected with the upper, middle and lower parts; the upper ultra-huge near space aerostat (1) is a semi-rigid airship with a V-shaped layout, a main body part (11) of the aerostat is a semi-rigid airship with a Ji Bailin airship shape with a contracted tail part, two sides of the main body part (11) are symmetrically arranged spherical semi-rigid airships (12), and the spherical semi-rigid airship (12) comprises an airbag (121) which is expanded into an approximate sphere after being inflated at high altitude and a shell type outer cover (122) which can store the spherical airbag (121) at a low altitude stage;

The space launching platform (2) is positioned on the back surface of the main body part (11) of the ultra-huge near space aerostat and comprises a space launching square (21) and a space launching orbit (22); during launching, the oversized near-space aerostat (1) takes a head upwind position, and the track accelerator (221) continuously accelerates under the combined action of four forces of a rope traction accelerator (223) traction force in the middle of the spaceflight launching track (22), self-driving force of the track accelerator (221), gravity sliding component force of an inclined plane of the launching track (22) and wind force, and finally reaches the end of the launching track (22) at a higher speed; under the control of an intelligent system, the track accelerator (221) releases the clamping device of the rocket in advance and immediately decelerates and stops under the action of the braking system (224); the rocket is thrown out by means of huge inertia; in the process, under the control of an intelligent system, ballast (15) and a gas storage tank (16) in the ultra-huge near-space aerostat (1) move in opposite directions relative to a rocket on respective guide rails so as to adjust the gravity center position of the ultra-huge near-space aerostat and prevent the ultra-huge near-space aerostat from being severely inclined; the control platform (3) is positioned below the abdomen of the oversized near-space aerostat main body part (11);

the middle point of the gravity center of the ultra-huge near-space aerostat (1) is a channel well penetrating the ultra-huge near-space aerostat (1) from top to bottom and communicating the aerospace launching platform (2) and the control platform (3); a cable gantry hanger (131) is arranged above the passage well, and the cable (7) is divided into a mooring transmission cable (71), a triangle cable-stayed wind-resistant tensile cable (72) and a lifting overload protection cable (73); the mooring transmission cable (71) is divided into an upper mooring transmission cable section (712) and a lower mooring transmission cable section (711), the upper mooring transmission cable section (712) passes through the passage well to be fixedly connected with the cable gantry crane (131), and an up-down transfer elevator (132) is arranged on the inner wall of the passage well; the handling platform (3) is an airtight space compartment.

2. The multipurpose transport system of claim 1, wherein: the giant adjacent space aerostat is a scaled down version of the giant adjacent space aerostat (1); the upper and lower intersection transfer station platform (5) comprises a transfer control cabin (51) positioned below the abdomen of the giant adjacent space aerostat main body part (41) and a transfer square (52) positioned on the back; the center of gravity of the huge near space aerostat (4) is provided with a passage well penetrating up and down, and the mooring transmission cable (71) can be fixedly connected with the huge near space aerostat (4); the transfer control cabin (51) is an airtight space cabin.

3. The multipurpose transmission system of claim 2, wherein: the anchor station platform (6) of the multi-purpose transmission system substructure comprises a central mooring anchor station (61) and a triangular wind-resistant tensile anchor station (62); the triangular wind-resistant tensile anchor station (62) is positioned at the vertex position of an equilateral triangle taking the central mooring anchor station (61) as the center in a normal state; the bottoms of the central mooring anchor station (61) and the triangular wind-resistant tensile anchor station (62) are provided with a plurality of anchor piles which are drilled into the ground for tens of meters; an access passage (612) of the cable car (8) is arranged at the lower part of the central mooring anchor station (61), a special track-entering gantry crane (613) for the cable car is arranged at the port of the access passage (612), a cable car track (614) which is separated from the ground is arranged between the track-entering gantry crane (613) and the access passage (612), a cable car passage well (615) is arranged between the upper surface of the central mooring anchor station and the access passage (612), and a cable rope winding and unwinding hinge device is arranged right below the center of the cable car passage well (615); the central mooring anchor station (61) and the triangular wind-resistant tensile anchor station (62) are assembled by hollow combined units (63); the lower section (711) of the mooring transmission cable stands up from the central mooring anchor on the ground to the transfer control cabin (51), and the upper section (712) of the mooring transmission cable starts from the transfer control cabin (51) to the cable gantry crane (131) through the huge adjacent space aerostat (4), the control platform (3) and the ultra-huge adjacent space aerostat (1); the triangular cable-stayed wind-resistant tensile cable (72) is positioned between the triangular wind-resistant tensile anchor station (62) and the giant adjacent space aerostat (1); the lifting overload protection cable (73) is arranged between the ultra-huge near-space aerostat (1) and the huge near-space aerostat (4) according to the requirement; the triangular wind-resistant tensile anchor station (62), the ultra-huge near-space aerostat (1) at the upper end and the lower end of the lifting overload protection cable (73) and the huge near-space aerostat are respectively provided with a cable winding and unwinding hinge device on the cable gantry hanger.

4. The multipurpose transmission system of claim 2, wherein: the cable car (8) runs on the cable (7) and is a power cable car capable of climbing independently; the cable car (8) is divided into an upper functional area part, a middle functional area part and a lower functional area part by fireproof materials, wherein the upper part of the cable car is a power area (81), the middle part of the cable car is a loading area (82), and the lower part of the cable car is a safety emergency area (83); the upper end of the power area (81) is provided with a plurality of groups of strong magnetic clutch, opposite compaction and synchronous wheel crawler type travelling devices (811), the travelling devices (811) structurally comprise a cantilever (8111), an outer cover (8112), a strong magnetic clutch (8113), a box body (8114), a gear mechanism (8115), a synchronous crawler (8116), a synchronous wheel (8117) and a synchronous wheel shaft (8118), the lower end of the travelling devices (811) is respectively connected with an oil driver (8131) and an electric driver (8141) through a universal transmission shaft (8121), a transfer case (8122), a transmission (8123), a coupling (8124), the oil driver (8131) is connected with a fuel tank (8132) and an emergency Liu Jianzhen air bag (831), the electric driver (8141) is connected with a high-capacity storage battery pack (8142) and a laser photoelectric plate (8143) or a fuel cell (8144), a motor for electric driving is a power generation-electric all-in-one machine, and the motor for electric driving (8141) can be stored in a self-running mode and can be arranged in the power area (816) on two sides of the power area (816), and the power area (81) is provided with a power area (81) for emergency landing; the cantilever (8111) of the travelling device (811) is tightly connected with a loading area (82) in the middle of the cable car (8) through a hanging frame (817), a part of the four sides of the hanging frame (817) can be rotated to be opened, so that the cable car (8) is convenient to clutch with a cable (7), the loading area (82) is of a frame type structure with an open space, a modularized task cabin meeting various transportation requirements can be loaded, the loading area (82) mainly comprises a frame (821) and a through cylinder (822), and the frame (821) and the through cylinder (822) are provided with openings (823) from top to bottom, so that the cable car (8) is convenient to clutch with the cable (7); the lower part of the cable car is the safety emergency area (83), the inside of the cable car is the emergency landing shock-absorbing air bag (831), emergency landing buffer rockets (832) are arranged outside four corners of the safety emergency area, and a guide wheel device (833) is arranged at the bottom of the through cylinder (822).

5. The multipurpose transport system of claim 1, wherein: the multifunctional modular functional areas are reserved inside the ultra-huge near-space aerostat (1) and the ultra-huge near-space aerostat (4) and inside and outside the spaceflight launching platform (2), the control platform (3) and the upper and lower junction transfer station platform (5), and the multifunctional modular functional areas are used for selectively carrying corresponding functional modules according to the current task requirements of the multifunctional transmission system.

6. The multipurpose transport system of claim 4, wherein: the high-power multipurpose laser is arranged on the aerospace launching platform, the control platform and the upper and lower junction transfer station platform, and can supply energy to the laser photoelectric plate (8143) on the cable car (8) in a medium-low power state; the upper surface and the lower surface of a shell-shaped outer cover (122) of the spherical semi-rigid airship (12), the tail parts of the control platform (3) and the transfer control cabin (51) are respectively provided with a large-sized electric propeller, and the tail parts of the ultra-large near-space aerostat and the huge near-space aerostat are respectively provided with an ultra-large electric propeller; the upper surfaces of the ultra-huge near-space aerostat (1) and the huge near-space aerostat (4) are covered with large-area thin film solar cell arrays, and the thin film solar cell arrays are connected with storage battery packs in the ultra-huge near-space aerostat (1) and the huge near-space aerostat (4).

7. The multipurpose transmission system of claim 2, wherein: when the multipurpose transmission system is built, each part of the main body structure of the system is provided with a static electricity removing, lightning protecting and lightning eliminating device; the space launching platform (2), the control platform (3), the transfer control cabin (51) and the manned airtight space of the cable car (8) are respectively provided with an oxygen-making and oxygen-supplying system, a heat-preserving and pressure-maintaining system, a cold-resistant pressure-resistant shell, an ultraviolet-resistant and cosmic ray-resistant coating, and the surfaces of other structural parts except the anchor station platform (6) of the main body structure of the system are covered with an anti-aging and weather-resistant layer; the method comprises the steps of building skin materials of the ultra-huge near-space aerostat (1) and the huge near-space aerostat (4), wherein a weather-proof layer is an aluminized polyvinyl fluoride film, a bearing layer is an ultra-high molecular weight polyethylene fiber cloth or a para-aramid fiber and ultra-high molecular weight polyethylene blend fiber cloth, a helium blocking layer is an ethylene-vinyl alcohol copolymer coating, an adhesive layer is polyether polyurethane, and an inner surface protective layer and an outer surface protective layer are polyethylene or polyurethane coatings; the bearing core material of the cable material uses ultra-high molecular weight polyethylene fibers and/or para-aramid fibers; the inner frameworks of the ultra-large near space aerostat and the upper and lower intersection transfer station platform frameworks, and the non-high-resistant Wen Goujia of the aerospace launching platform, the control platform and the cable car are laminated by using ultra-high molecular weight polyethylene fiber boards; the high temperature resistant framework material in the multipurpose transmission system uses para-aramid fiber material.

8. The method of constructing a multipurpose transport system of claim 1, wherein: when the ultra-huge near space aerostat (1) and the huge near space aerostat (4) are built, concave geological structure points which are four sides surrounded by mountains, low in middle topography and flat and wide are found in the nature, and the selected structure points are as close to industrial cities and traffic trunks as possible so as to facilitate the manufacturing and transportation of construction material materials; the middle low-lying land pattern should be wide enough, the length is preferably greater than 2.3km, the width is preferably greater than 0.9km, and the four-side mountain pattern height is preferably greater than 0.9km; the method is characterized in that the choke on four mountain positions is manually closed according to the requirement, and a guy cable iron tower is built at the higher position of the four mountain positions, so that a guy cable passing cable car can be erected, and a ceiling can be conveniently built; the ceiling is built by using ultra-high molecular weight polyethylene fiber cloth, and a large helium balloon is used in the middle of the ceiling to be lifted upwards; the ultra-huge near space aerostat (1) and the huge near space aerostat (4) are manufactured in the semi-natural semi-artificial ultra-large factory building, the selected geological structure points are directly modified and utilized if existing in-out traffic lines exist, if the traffic is inconvenient in the ground, a plurality of lifting cable cars are built on site to solve the problem, if the traffic is inconvenient in the out-in traffic with the outside or even far away from the traffic lines, one or a plurality of huge middle-low-altitude airships are built at first, the effective load weight is tens to hundreds tons, and the method is used for solving the traffic and transportation problem with the outside.