CN118088343A - Hypersonic thrust vectoring nozzle and translation adjustment and flow control method thereof - Google Patents

Abstract

The invention discloses a hypersonic thrust vectoring nozzle and a translation adjusting and flow controlling method thereof. The hypersonic thrust vectoring nozzle comprises an inner sleeve ring, a middle sleeve ring and an outer sleeve ring, wherein the three sleeve rings are divided into four quarter sleeve rings, and can independently translate along the axial direction. The translational adjustment method can not only adjust the outlet area of the spray pipe, but also adjust the thrust vector by adjusting the positions of the middle lantern ring and the outer lantern ring. The thrust performance of the hypersonic thrust vectoring nozzle can be improved by a flow control method that the flow channels of the middle ring and the outer ring are led into the outside high-speed atmosphere. The hypersonic thrust vectoring nozzle is suitable for hypersonic flight conditions and wide-speed domain operation, has excellent thrust performance, can generate vector angles in four directions in pitching and yawing directions, can still generate a small vector angle in hypersonic flight conditions, has excellent vectoring performance, is favorable for controlling the flight attitude of a hypersonic aircraft, and improves the maneuverability of the hypersonic aircraft.

Description

A hypersonic thrust vector nozzle and its translational regulation and flow control method

Technical Field

The present invention relates to the technical field of tail nozzles of aerospace engines, and in particular to a hypersonic thrust vector nozzle and a translational adjustment and flow control method thereof.

Background technique

Hypersonic technology refers to the technology involved in aircraft with a flight Mach number greater than 5, with air-breathing engines or their combination engines as the main power, and capable of long-distance flight in the atmosphere and across the atmosphere. In the military field, hypersonic technology has great strategic significance and is a hot field for the development of national defense science and technology and equipment in countries around the world. Hypersonic aircraft can be mainly divided into two categories: hypersonic cruise aircraft and hypersonic gliding aircraft. The former usually uses a scramjet engine as a power source, while the latter usually uses a solid rocket engine for boosting. Whether it is an air-breathing ramjet engine or a solid/liquid rocket engine as a power source, the tail nozzle is an important thrust component. The engine tail nozzle can be divided into fixed and adjustable nozzles according to the adjustment method. Adjustable nozzles are widely used in aviation gas turbine engines, ramjet engines, rocket engines and combined cycle engines. For rocket ramjet engines, adjustable nozzles can ensure excellent thrust performance within a wide Mach number working range and give full play to their power performance advantages of high-speed cruise. Combined cycle engines need to maintain high performance in a wide range of flight envelopes and meet engine flow, thrust and other requirements in a wide range of Mach numbers, so it is necessary to adjust the nozzle. Adjustable nozzles are mainly divided into two categories: mechanical and pneumatic adjustment nozzles, and the adjustment objects are mainly outlet area adjustment and throat area adjustment.

Thrust vector nozzle is one of the key equipment of future aircraft. With the continuous improvement of modern aviation military technology, in order to gain advantages in various air battles and improve survivability, higher requirements are put forward for the maneuverability of fighters. Thrust vector nozzle has become an indispensable key technology. In addition to providing flight thrust, thrust vector nozzle can also provide the force or torque required to control the aircraft in pitch, yaw, roll and other directions alone or simultaneously, so as to achieve better control quality and control performance of the aircraft. At present, in hypersonic aircraft, thrust vector nozzle is still less used. The aerodynamic thrust vector nozzle studied at home and abroad is mainly concentrated in subsonic and low supersonic conditions. The vector performance is general under hypersonic conditions. For example, the ejection effect type vector nozzle has a good effect on low-speed vector deflection control, but the vector control effect is poor in supersonic airflow. Wang Haoliang et al. modeled and analyzed an air-breathing hypersonic vehicle with both a vector nozzle and aerodynamic control surfaces, proposed three different tracking control modes, and achieved smooth switching between the three control modes, highlighting the advantages of vector nozzles in the control of hypersonic vehicles, and pointed out that the coordination of multiple control methods is of great significance to the attitude control of hypersonic vehicles. Therefore, the use of thrust vector nozzles in hypersonic vehicles has an important impact on the performance improvement and attitude control of the aircraft.

Therefore, in order to meet the requirements of the tail nozzle of the hypersonic aircraft for outlet area adjustment and good thrust vectoring capability, a hypersonic thrust vectoring nozzle with translational adjustment and a flow control method were designed, providing a thrust vectoring nozzle and an adjustment method for the hypersonic aircraft to achieve outlet area adjustment and thrust vectoring capability.

Summary of the invention

Technical purpose: The purpose of the present invention is to provide a hypersonic thrust vector nozzle and its translation adjustment and flow control method, which uses axial translation adjustment as the actuation mode, can not only adjust the nozzle outlet area, but also generate thrust vector through adjustment, and adopts the flow control method of secondary flow intake to improve the thrust performance of the nozzle. The present invention is used to meet the demand for excellent thrust performance of the tail nozzle of a hypersonic aircraft within a wide flight envelope, meet the demand for generating a certain vector angle under hypersonic flight conditions and wide flight envelopes, and provide a solution to the problem that it is difficult for the thrust vector nozzle to generate a vector angle under hypersonic flight conditions. At the same time, it simplifies the mechanical adjustment actuation system, which is beneficial to the control of the attitude of the hypersonic aircraft and improves the maneuverability of the hypersonic aircraft. The adjustment method has strong applicability and multiple functions.

Technical solution: To achieve the above technical objectives, the present invention adopts the following technical solution:

A hypersonic thrust vector nozzle comprises an inner sleeve ring, a middle sleeve ring and an outer sleeve ring which are connected in series in sequence;

The inner sleeve ring is located at the innermost ring of the hypersonic thrust vector nozzle, and includes an inner sleeve straight section and an inner sleeve expansion section formed integrally; the front end of the inner sleeve straight section is the nozzle gas inlet, through which the high-temperature and high-pressure gas in the combustion chamber is introduced, and the rear end of the inner sleeve expansion section is the inner sleeve outlet, and the inner sleeve ring is formed by four quarter and half inner sleeve rings connected in series;

The middle ring is located in the middle ring of the hypersonic thrust vector nozzle, and includes an integrally formed middle ring straight section and a middle ring expansion section. The front end of the middle ring expansion section is the middle ring expansion section inlet, and the rear end is the middle ring outlet. The middle ring is formed by connecting four quarter and half middle rings in series.

The outer ring is located at the outermost ring of the hypersonic thrust vector nozzle, and includes an outer ring straight section and an outer ring expansion section formed in one piece. The front end of the outer ring expansion section is the outer ring expansion section inlet, and the rear end is the outer ring outlet. The outer ring is formed by four quarter and half outer rings connected in series.

The four quarter and a half inner rings, the four quarter and a half middle rings, and the four quarter and a half outer rings can all independently translate along the axial direction of the hypersonic thrust vector nozzle under the drive of the driving device; at the same time, the four quarter and a half middle rings are defined as the upper half middle ring, the lower half middle ring, the left half middle ring, and the right half middle ring; the four quarter and a half middle outer rings are the upper middle outer ring, the lower middle outer ring, the left middle outer ring, and the right middle outer ring.

Preferably, the axial length of the inner ring expansion section is defined as _L1 , the axial length of the middle ring expansion section is defined as _L2 , and the axial length of the outer ring expansion section is defined as _L3 , satisfying _L1 = (0.2-0.25)*( _L1 + _L2 + _L3 ), _L2 = (2-4) _L1 , _L3 = (1-1.2) _L2 ; the length of the inner ring equal straight section is defined as _Lx1 , the length of the middle ring equal straight section is defined as _Lx2 , and the length of the outer ring equal straight section is defined as _Lx3 , satisfying _Lx2 = ( _Lx1 + _L1 ) _≥L3 , _Lx3 = _Lx2 + _L2 .

Preferably, the inner wall cutting angle of the inner ring outlet is defined as α, and the inner wall cutting angle of the middle ring expansion section inlet is defined as β, satisfying α=β, and α≤15°; the inner wall surface of the middle ring outlet is tangent to the inner wall surface of the outer ring expansion section inlet.

Preferably, the non-vector large outlet area state of the hypersonic thrust vector nozzle is: the inlet of the middle ring expansion section is flush with the inner ring outlet position, and the inlet of the outer ring expansion section is flush with the middle ring outlet position; the inner wall surfaces of the middle ring expansion section and the outer ring expansion section are combined into a continuous inner wall surface, which together with the inner wall surface of the inner sleeve ring constitute the axisymmetric expansion type flow channel of the hypersonic thrust vector nozzle.

Preferably, the axisymmetric expansion flow channel is provided with a step at the inner ring outlet, and the step is the wall thickness at the inner sleeve ring outlet. The step staggers the middle sleeve ring and the inner sleeve ring so that the middle sleeve ring can translate freely along the axial direction. At the same time, the step raises the height of the middle ring flow channel, allowing more air to enter, thereby improving the performance of the hypersonic thrust vector nozzle.

Preferably, the inner ring outlet diameter is defined as _De1 , the middle ring expansion section inlet diameter is defined as _Di2 , the step height is h, and _Di2 = _De1 +2h, h = (0.04-0.05) _De1 ; the middle ring outlet diameter is defined as _De2 , the outer ring outlet (9) diameter is defined as _De3, and _De3 = (1.15-1.2) _De2 .

Preferably, a translational adjustment method for a hypersonic thrust vectoring nozzle includes an outlet area translational adjustment method and a thrust vector translational adjustment method: the outlet area translational adjustment method includes two types: translational adjustment of a large outlet area to a small outlet area, and translational adjustment of a small outlet area to a large outlet area; the thrust vector translational adjustment method includes two types: translational adjustment for generating a pitch direction vector angle and translational adjustment for generating a yaw direction vector angle.

Preferably, the translation adjustment from the large outlet area to the small outlet area is realized in the following process: the inner ring remains in a fixed position, the middle ring translates upstream by a distance _X1 , satisfying _X1 = (0.25-1)* _L2 , and the outer ring translates upstream until the outer ring outlet is flush with the middle ring outlet. At this time, the hypersonic thrust vector nozzle is in a non-vector small outlet area state. The outlet area of the hypersonic thrust vector nozzle is small, and it is suitable for low Mach number flight conditions.

The translational adjustment of the small outlet area to the large outlet area is that the position of the inner ring remains unchanged, the middle ring translates downstream until the inlet of the middle ring expansion section is flush with the inner ring outlet, and the outer ring translates downstream until the inlet of the outer ring expansion section is flush with the middle ring outlet. At this time, the inner wall surfaces and steps of the inner ring expansion section, the middle ring expansion section, and the outer ring expansion section are combined into a continuous inner wall surface, and the hypersonic thrust vector nozzle has a large outlet area, which is suitable for high Mach number flight conditions.

Preferably, the translation adjustment method for generating the pitch direction vector angle includes:

(1) The inner ring remains in a fixed position, and the upper half-middle ring and the upper half-outer ring move downstream to a position in a non-vector large outlet area state, wherein the position in the non-vector large outlet area state is specifically: the inlet of the middle ring expansion section is flush with the inner ring outlet, and the inlet of the outer ring expansion section is flush with the middle ring outlet; the lower half-middle ring moves upstream to a position where the middle ring outlet is flush with the inner ring outlet, and the lower half-outer ring also moves upstream to a position where the outer ring outlet is flush with the inner ring outlet; at this time, the hypersonic thrust vector nozzle is an asymmetric configuration staggered up and down, generating a nose-down vector angle in a high Mach number flight condition, and generating a nose-up vector angle in a low Mach number flight condition;

(2) The inner ring remains in a fixed position, the lower half-middle ring and the lower half-outer ring move downstream to a position in a non-vector large outlet area state, the upper half-middle ring moves upstream to a position where the middle ring outlet is flush with the inner ring outlet, and the upper half-outer ring also moves upstream to a position where the outer ring outlet is flush with the inner ring outlet; at this time, the hypersonic thrust vector nozzle is an asymmetric configuration that is staggered up and down, and generates a nose-up vector angle in a high Mach number flight condition, and generates a nose-down vector angle in a low Mach number flight condition;

The translation adjustment method for generating the yaw direction vector angle comprises:

(a) The inner ring remains stationary, the left half-middle ring and the left half-outer ring move downstream to a position in a non-vector large outlet area state, the right half-middle ring moves upstream to a position where the middle ring outlet is flush with the inner ring outlet, and the right half-outer ring also moves upstream to a position where the outer ring outlet is flush with the inner ring outlet. At this time, the hypersonic thrust vector nozzle is an asymmetric configuration that is staggered left and right, and generates a right yaw vector angle in a high Mach number flight condition and a left yaw vector angle in a low Mach number flight condition.

(b) The inner ring remains in a fixed position, the right half-middle ring and the right half-outer ring move downstream to a position in a non-vector large outlet area state, the left half-middle ring moves upstream to a position where the middle ring outlet is flush with the inner ring outlet, and the left half-outer ring also moves upstream to a position where the outer ring outlet is flush with the inner ring outlet. At this time, the hypersonic thrust vector nozzle has an asymmetric configuration that is staggered left and right, and generates a left yaw vector angle in a high Mach number flight condition and a right yaw vector angle in a low Mach number flight condition.

Preferably, the flow control method is secondary flow intake, that is, introducing external high-speed atmosphere into the middle ring flow channel and the outer ring flow channel to improve the thrust performance of the hypersonic thrust vector nozzle in a non-vector small exit area state and a low Mach number flight condition;

The middle ring flow channel is a flow channel formed between the inner ring and the middle ring when the hypersonic thrust vector nozzle is in a non-vector small outlet area state or under a low Mach number flight condition, and the outer ring flow channel is a flow channel formed between the middle ring and the outer ring when the hypersonic thrust vector nozzle is in a non-vector small outlet area state or under a low Mach number flight condition.

It should be noted that if flow control means are not adopted, the middle ring flow channel and the outer ring flow channel are both in a closed state, and are not connected to the outside atmosphere. Only the nozzle gas inlet of the inner sleeve ring is connected to the high-temperature and high-pressure gas.

Beneficial effects: Compared with the prior art, the present invention has the following technical effects:

(1) A hypersonic thrust vectoring nozzle, which is an axisymmetric expansion nozzle in a non-vector state. The nozzle outlet area can be adjusted by adjusting the positions of the middle ring and the outer ring in translation. It is suitable for operation in a wide speed range and can maintain good working performance in a wide flight envelope. Compared with a geometrically fixed nozzle that cannot adjust the outlet area, it has better thrust performance. It can meet the requirement of maintaining high working performance in a wide flight envelope of the combined engine tail nozzle.

(2) The hypersonic thrust vector nozzle of the present invention can form different asymmetric configurations by adjusting the positions of the inner and outer rings in translation, and can generate vector angles in four directions, namely, the pitch direction and the yaw direction. It has excellent vector performance and a variety of vector directions. It can still generate a considerable vector angle under hypersonic flight conditions, which is beneficial to the control of the flight attitude of the hypersonic aircraft and improves the maneuverability of the hypersonic aircraft.

(3) The translational adjustment method adopted by the present invention can adjust the nozzle outlet area and perform thrust vector adjustment, realizing two adjustment functions through one adjustment method. It has strong applicability and multiple functions, can simplify the types of adjustment mechanisms and methods, and simplify the mechanical adjustment actuation system.

(4) The flow control method of the present invention can improve the thrust performance of the thrust vectoring nozzle under low Mach number conditions by means of secondary flow intake.

(5) The present invention provides a solution for realizing area adjustment and thrust vector adjustment of an axisymmetric hypersonic nozzle. The same translation adjustment concept and flow control method can be applied to nozzles of other axisymmetric structures, and has strong universality.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG1 is a schematic diagram of the central meridian plane of the hypersonic thrust vector nozzle in a non-vector large outlet state used in the present invention;

FIG2 is a schematic diagram of the central meridian plane of the hypersonic thrust vector nozzle in a non-vectored small outlet state used in the present invention;

FIG3 is a schematic diagram of the central meridian plane of the pitch direction vector state of the hypersonic thrust vector nozzle used in the present invention;

4 is a schematic diagram of the structure of the hypersonic thrust vectoring nozzle in the non-vectored large outlet state, the non-vectored small outlet state, the head-up vector, the head-down vector, the left yaw vector, and the right yaw vector of the present invention;

FIG5 is a schematic diagram of geometric constraints of a hypersonic thrust vectoring nozzle according to the present invention;

FIG6 is a Mach number cloud diagram of the hypersonic thrust vector nozzle of the present invention under different working conditions and states;

FIG7 is a thrust coefficient curve diagram of a typical working condition of a hypersonic thrust vectoring nozzle of the present invention;

FIG8 is a vector angle curve diagram of a typical working condition of the hypersonic thrust vector nozzle of the present invention.

Among them, 1-inner sleeve ring, 2-nozzle gas inlet, 3-inner ring straight section, 4-middle ring straight section, 5-inner ring outlet, 6-outer ring straight section, 7-middle sleeve ring, 8-middle ring outlet; 9-outer ring outlet, 10-inner ring expansion section, 11-step, 12-middle ring expansion section, 13-outer ring expansion section, 14-outer sleeve ring;

15-middle ring flow channel, 16-outer ring flow channel, 17-outer ring expansion section inlet, 18-middle ring expansion section inlet.

19-lower half half outer ring, 20-lower half half middle ring, 21-upper half half outer ring, 22-upper half middle ring. 23-right half half middle ring, 24-right half half outer ring, 25-left half half outer ring. 26-left half half middle ring.

Detailed ways

The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

As shown in Figure 1, it is a schematic diagram of the central meridian plane of the non-vector large outlet state of the hypersonic thrust vector nozzle of the present invention, including an inner ring 1, a middle ring 7, and an outer ring 14. The inner ring 1, the middle ring 7, and the outer ring 14 are all divided into four quarter-and-a-half rings separated from each other up and down and left and right. In the non-vector state, the inner ring 1, the middle ring, and the outer ring are of an axisymmetric configuration as a whole. The inner ring 1 is located at the innermost ring of the thrust vector nozzle, and is composed of four quarter-and-a-half inner rings, including an inner ring straight section 3 and an inner ring expansion section 10. The front end of the inner ring straight section 3 is the nozzle gas inlet 2, which is passed into the high-temperature and high-pressure gas in the combustion chamber, and the rear end of the inner ring expansion section 10 is the inner ring outlet 5.

The middle ring is located in the middle ring of the thrust vector nozzle and is composed of four quarter and half middle rings, including a middle ring straight section 4 and a middle ring expansion section 12. The front end of the middle ring expansion section is the middle ring expansion section inlet 18, and the rear end is the middle ring outlet 8.

The outer ring is located at the outermost ring of the thrust vector nozzle and is composed of four quarter and half outer rings, including an outer ring straight section 6 and an outer ring expansion section 13. The front end of the outer ring expansion section is the outer ring expansion section inlet 17, and the rear end is the outer ring outlet 9.

Further, the axial length of the inner ring expansion section 10 is defined as _L1 , the axial length of the middle ring expansion section is defined as _L2 , and the axial length of the outer ring expansion section is defined as _L3 . The three lengths satisfy: _L1 = (0.2-0.25)* ( _L1 + _L2 + _L3 ), _L2 = (2-4) _L1 , _{and L3} = (1-1.2) _L2 .

Define the length of the inner ring straight segment 3 as Lx ₁ , the length of the middle ring straight segment 4 as Lx ₂ , and the length of the outer ring straight segment 6 as Lx ₃ . The three lengths satisfy Lx ₂ =Lx ₁ +L ₁ ≥L ₃ , Lx ₃ =Lx ₂ +L ₂ .

The inner wall cut angle of the inner ring outlet 5 is defined as α, and the inner wall cut angle of the middle ring expansion section inlet is defined as β, which must satisfy α＝β, and α≤15°. The inner wall of the middle ring outlet is tangent to the inner wall of the outer ring expansion section inlet.

Further, the four quarter-and-a-half inner rings, the four quarter-and-a-half middle rings, and the four quarter-and-a-half outer rings can all independently translate in the axial direction and are driven by a screw stepper motor as a driving device. The four quarter-and-a-half middle rings are combined in pairs to form an upper half middle ring 22, a lower half middle ring 20, a left half middle ring 26, and a right half middle ring 23. The four quarter-and-a-half outer rings are combined in pairs to form an upper half outer ring 21, a lower half outer ring 19, a left half outer ring 25, and a right half outer ring 24, as shown in FIG. 4 .

Further, as shown in FIG1 , the figure shows that the upstream is the left side and the downstream is the right side. In the non-vector large outlet area state of the thrust vector nozzle, the inner ring 1, the middle ring 7, and the outer ring 14 are all at their respective closest downstream positions, the middle ring expansion section inlet 18 is flush with the inner ring outlet 5, and the outer ring expansion section inlet 17 is flush with the middle ring outlet 8. The inner wall surfaces of the middle ring expansion section 12 and the outer ring expansion section 13 are combined into a continuous inner wall surface, which together with the inner wall surface of the inner ring 1 constitute the axisymmetric expansion flow channel of the hypersonic thrust vector nozzle. In this case, the thrust vector nozzle has the largest outlet area and is suitable for high Mach number flight conditions.

Furthermore, the axisymmetric expansion flow channel includes a step 11 at the inner ring outlet 5. The step 11 is the wall thickness at the outlet of the inner sleeve ring 1. The step 11 makes the middle sleeve ring staggered with the inner sleeve ring 1 so that the middle sleeve ring can freely translate along the axial direction. At the same time, the step 11 can raise the height of the middle ring flow channel 15 to allow more air to enter.

Define the inner ring outlet 5 diameter as _De1 , the middle ring expansion section inlet diameter as _Di2 , the step 11 height as h, satisfying _Di2 = _De1 +2h, h = (0.04-0.05) _De1 . Define the middle ring outlet diameter as _De2 , the outer ring outlet 9 diameter as _De3 satisfying _De3 = (1.15-1.2) _De2 .

The translational adjustment method used in the hypersonic thrust vector nozzle of the present invention includes an outlet area translational adjustment method and a thrust vector translational adjustment method.

Further, the outlet area translation adjustment method includes: translation adjustment of the large outlet area to a small outlet area and translation adjustment of the small outlet area to a large outlet area. The adjustment method of the large outlet area translation adjustment to the small outlet area is that the inner ring 1 keeps its position unchanged, the middle ring translates upstream by a distance _X1 , satisfying _X1 = (0.25-1)* _L2 , and the outer ring translates upstream until the outer ring outlet 9 is flush with the middle ring outlet 8, as shown in Figure 2. At this time, the hypersonic thrust vector nozzle has a small outlet area, which is suitable for low Mach number flight conditions. Figure 2 is a schematic diagram of the central meridian plane of the non-vector small outlet state of the hypersonic thrust vector nozzle. In the figure, the middle ring equal straight section 4 and the outer ring equal straight section 6 of the middle ring and the outer ring are partially cut off for the convenience of schematic display. The defined non-vector small outlet area state refers to the small outlet area of the channel through which the gas flows. When _X1 = 1* _L2 , the outlet area is the smallest (that is, 8 is flush with 5). FIG2 shows the small outlet area state when _X1 = _0.25L2. Both are small outlet area states. According to different actual working conditions, different _X1 distances can be selected for movement. It is not necessary to move all to the minimum outlet area. After 9 is translated to be flush with 8, it is meaningless to continue to translate to the left, because the gas cannot flow through the outer ring afterwards. The adjustment method of adjusting the small outlet area to a large outlet area is that the position of the inner ring 1 remains unchanged, the middle ring is translated downstream until the inlet 18 of the middle ring expansion section is flush with the position of the inner ring outlet 5, and the outer ring is translated downstream until the inlet 17 of the outer ring expansion section is flush with the position of the middle ring outlet 8, as shown in FIG1. At this time, the inner ring expansion section 10, the middle ring expansion section, the inner wall surface of the outer ring expansion section and the step 11 are combined into a continuous inner wall surface, and the nozzle outlet area is large, which is suitable for high Mach number flight conditions.

The thrust vector translation adjustment method includes translation adjustment for generating a pitch direction vector angle and translation adjustment for generating a yaw direction vector angle.

Furthermore, the translation adjustment method for generating the pitch direction vector angle includes two adjustment methods.

(1) The inner sleeve 1 remains in place, the upper half middle sleeve 22 and the upper half outer sleeve 21 move downstream to the position of the non-vector large outlet area state, the lower half middle sleeve 20 moves upstream to the position where the middle sleeve outlet 8 is flush with the inner sleeve outlet 5, and the lower half outer sleeve 19 also moves upstream to the position where the outer sleeve outlet 9 is flush with the inner sleeve outlet 5, as shown in Figure 3. At this time, the hypersonic thrust vector nozzle is an asymmetric configuration that is staggered up and down, which can generate a nose-down vector angle in high Mach number flight conditions and a nose-up vector angle in low Mach number flight conditions. In Figures 3 and 4, the middle sleeve and outer sleeve straight sections 4 and the outer sleeve straight sections 6 of the middle sleeve and outer sleeve are partially cut off for the convenience of schematic diagram display. The schematic diagram of the hypersonic thrust vector nozzle structure after such adjustment is shown in the third figure in the first row of Figure 4.

(2) The inner ring 1 remains in position, the lower half-middle ring 20 and the lower half-outer ring 19 move downstream to the position of the non-vector large outlet area state, the upper half-middle ring 22 moves upstream to the position where the middle ring outlet is flush with the inner ring outlet 5, and the upper half-outer ring 21 also moves upstream to the position where the outer ring outlet 9 is flush with the inner ring outlet 5, as shown in the first figure of the second row in FIG. 4. At this time, the hypersonic thrust vector nozzle is an overall asymmetric configuration of staggered upper and lower parts, which can generate a nose-up vector angle in high Mach number flight conditions and a nose-down vector angle in low Mach number flight conditions.

Furthermore, the translational adjustment method for generating the yaw direction vector angle includes two adjustment methods.

(1) The inner ring 1 remains in position, the left half-middle ring 26 and the left half-outer ring 25 move downstream to the position of the non-vector large outlet area state, the right half-middle ring 23 moves upstream to the position where the middle ring outlet is flush with the inner ring outlet 5, and the right half-outer ring 24 also moves upstream to the position where the outer ring outlet 9 is flush with the inner ring outlet 5, as shown in the second picture of the second row in FIG. 4. At this time, the hypersonic thrust vector nozzle is an asymmetric configuration of left and right staggered, which can generate a right yaw vector angle in high Mach number flight conditions and a left yaw vector angle in low Mach number flight conditions.

(2) The inner ring 1 remains in position, the right half middle ring 23 and the right half outer ring 24 move downstream to the position of the non-vector large outlet area state, the left half middle ring 26 moves upstream to the position where the middle ring outlet is flush with the inner ring outlet 5, and the left half outer ring 25 also moves upstream to the position where the outer ring outlet 9 is flush with the inner ring outlet 5, as shown in the third figure of the second row in FIG. 4. At this time, the hypersonic thrust vector nozzle is an overall asymmetric configuration of left and right staggered, which can generate a left yaw vector angle in high Mach number flight conditions and a right yaw vector angle in low Mach number flight conditions.

A flow control method that can be used for a hypersonic thrust vector nozzle includes a middle ring flow channel 15 and an outer ring flow channel 16.

The middle ring flow channel 15 is a flow channel formed between the inner ring 1 and the middle ring when the hypersonic thrust vector nozzle is in a small outlet area state and a thrust vector state, and the outer ring flow channel 16 is a flow channel formed between the middle ring and the outer ring.

Furthermore, the flow control method is secondary flow intake, that is, introducing external high-speed atmosphere into the middle ring flow channel 15 and the outer ring flow channel 16, which can improve the thrust performance of the hypersonic thrust vector nozzle in the thrust vector state under the non-vector small outlet area state and low Mach number conditions.

It should be noted that if flow control means are not adopted, the middle ring flow channel and the outer ring flow channel are both in a closed state, and the outside atmosphere is not allowed to enter. Only the nozzle gas inlet 2 of the inner sleeve ring 1 allows high-temperature and high-pressure gas to enter.

The present invention essentially invents an axisymmetric expansion type hypersonic thrust vector nozzle, a translational adjustment method and a flow control method for the nozzle to achieve outlet area adjustment and thrust vector capability, uses the axial translation of the inner, middle and outer three rings as the translational adjustment method to adjust the nozzle outlet area, and forms an asymmetric configuration of the nozzle through translational adjustment, thereby generating a thrust vector, and adopts a secondary flow intake flow control method to improve the thrust performance of the nozzle.

The innovation of the present invention is as follows: the hypersonic thrust vector nozzle of the present invention is suitable for hypersonic flight conditions and wide speed range, and can maintain good working performance in a wide flight envelope. Compared with the geometrically fixed nozzle that cannot adjust the outlet area, the thrust performance is better. It can generate vector angles in four directions in the pitch direction and the yaw direction, with excellent vector performance and many types of vector directions. It can still generate a large vector angle in the hypersonic flight condition, which is beneficial to the control of the flight attitude of the hypersonic aircraft and improves the maneuverability of the hypersonic aircraft. The translation adjustment method of the present invention can adjust the nozzle outlet area and perform thrust vector adjustment. Two adjustment functions are achieved through one adjustment method, which has strong applicability and multiple functions, and can simplify the types of adjustment mechanisms and methods and simplify the mechanical adjustment actuation system. The flow control method of the present invention adopts the secondary flow intake method to improve the thrust performance of the thrust vector nozzle under low Mach number conditions. The present invention provides a solution for realizing area adjustment and thrust vector adjustment for an axisymmetric hypersonic nozzle. The same translation adjustment idea and flow control means can be applied to nozzles of other axisymmetric structures, and has strong universality.

Example:

For a certain combination engine Ma2 to Ma7 working conditions, the hypersonic thrust vector nozzle described in the present invention is applied, and the translational adjustment method of the present invention is used for adjustment and the flow control method is used for control. The non-vector state and vector state of the hypersonic thrust vector nozzle are subjected to three-dimensional numerical simulation calculations, and the relevant performance parameters are summarized. In the Ma2 flight condition, the nozzle has a small ideal expansion outlet area due to the low pressure drop ratio. Therefore, the nozzle is placed in a small outlet area state through translational adjustment. In the Ma7 flight condition, the pressure drop ratio is high and the ideal expansion outlet area of the nozzle is large. Therefore, the nozzle is placed in a large outlet area state through translational adjustment. The vector state takes the translational adjustment of the nose-down vector generated in the hypersonic flight condition as an example.

Figure 6 shows the Mach number cloud diagram of the hypersonic thrust vectoring nozzle in the small outlet non-vector state of Ma2 working condition, the Mach number cloud diagram of the small outlet non-vector state using flow control means, the Mach number cloud diagram of the large outlet non-vector state of Ma7 working condition, and the Mach number cloud diagram of the vector state of Ma7 working condition. It can be seen from the figure that in the small outlet non-vector state of Ma2 working condition, the secondary flow is closed and there is no air intake. Because the step 11 causes the airflow to reattach to the wall to produce a reattached shock wave, there is a trailing edge shock wave at the nozzle outlet. It can be seen from the figure that in the small outlet non-vector state of Ma2 working condition, after the flow control means of secondary flow intake are adopted, high-speed atmosphere is introduced into the middle ring flow channel and the outer ring flow channel, and there are reflections and intersections of shock wave expansion waves in the middle ring flow channel and the outer ring flow channel, and the over-expansion phenomenon of the nozzle is effectively alleviated. In the large outlet non-vector state of Ma7 working condition, because the step 11 causes the airflow to reattach to the wall to produce a reattached shock wave, the internal expansion of the nozzle is good, and the nozzle is in a slightly under-expansion state. In the thrust vector state of Ma7 working condition, because the step 11 causes the airflow to reattach to the wall of the middle ring in the upper half to produce a reattachment shock wave, the nozzle has an asymmetric configuration that is staggered up and down. There are expansion wave fans and trailing edge shock waves at the outlet of the inner ring 1, and the airflow is deflected downward to produce a nose-down vector.

As shown in Figure 7, this is the thrust coefficient of the hypersonic thrust vector nozzle of the present invention in the non-vector state within the flight envelope. It can be seen from the figure that the thrust coefficient of the hypersonic thrust vector nozzle in the hypersonic flight condition of Ma7 is greater than 0.96. In the Ma2 non-design point under-expansion condition, the thrust coefficient is also greater than 0.92 by reducing the area and flow control means. The thrust coefficient of the hypersonic thrust vector nozzle of the present invention in the wide flight envelope is maintained at a high level, and the thrust performance is excellent.

As shown in FIG8 , the vector angle of the hypersonic thrust vector nozzle of the present invention in the vector state within the flight envelope. It can be seen from the figure that the hypersonic thrust vector nozzle can produce a vector angle greater than 10° in the hypersonic flight conditions of Ma6 and Ma7, and the vector angle is a positive value, which is a nose-down vector angle. In the low Mach number condition of Ma2, a vector angle greater than 40° can be produced, and the vector angle is a negative value, which is a nose-up vector angle. It can be seen from FIG7 that the hypersonic thrust vector nozzle of the present invention can still produce a large vector angle in the hypersonic flight condition, and the vector performance is excellent.

The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principle of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims (10)

1. A hypersonic thrust vectoring nozzle, characterized in that it comprises an inner sleeve ring (1), a middle sleeve ring (7), and an outer sleeve ring (14) connected in series in sequence; The inner ring (1) is located at the innermost ring of the hypersonic thrust vectoring nozzle, and comprises an inner ring straight section (3) and an inner ring expansion section (10) which are integrally formed; the front end of the inner ring straight section (3) is a nozzle gas inlet (2), through which high-temperature and high-pressure gas in the combustion chamber is introduced; the rear end of the inner ring expansion section (10) is an inner ring outlet (5); the inner ring (1) is formed by four quarter and half inner rings connected in series; The middle ring (7) is located in the middle ring of the hypersonic thrust vector nozzle, and comprises an integrally formed middle ring straight section (4) and a middle ring expansion section (12); the front end of the middle ring expansion section (12) is a middle ring expansion section inlet (18), and the rear end is a middle ring outlet (8); the middle ring (7) is formed by connecting four quarter and half middle rings in series; The outer ring (14) is located at the outermost ring of the hypersonic thrust vector nozzle, and comprises an outer ring straight section (6) and an outer ring expansion section (13) formed in one piece, the front end of the outer ring expansion section (13) is an outer ring expansion section inlet (17), and the rear end is an outer ring outlet (9), and the outer ring (14) is formed by four quarter and half outer rings connected in series; The four quarter inner rings, the four quarter middle rings, and the four quarter outer rings can all independently translate along the axial direction of the hypersonic thrust vector nozzle under the drive of the driving device; at the same time, the middle ring (7) is divided into an upper half middle ring (22), a lower half middle ring (20), a left half middle ring (26), and a right half middle ring (23); the upper half middle ring (22), the lower half middle ring (20), the left half middle ring (26), and the right half middle ring (23). 6) The right half middle sleeve ring (23) is formed by connecting two adjacent quarter half middle sleeve rings in series; the outer sleeve ring (14) is divided into an upper middle outer sleeve ring (21), a lower middle outer sleeve ring (19), a left middle outer sleeve ring (25), and a right middle outer sleeve ring (24); the upper middle outer sleeve ring (21), the lower middle outer sleeve ring (19), the left middle outer sleeve ring (25), and the right middle outer sleeve ring (24) are all formed by connecting two adjacent quarter half outer sleeve rings in series. 2. A hypersonic thrust vectoring nozzle according to claim 1, characterized in that: the axial length of the inner ring expansion section (10) is defined as _L1 , the axial length of the middle ring expansion section (12) is defined as _L2 , and the axial length of the outer ring expansion section (13) is defined as _L3 , satisfying _L1 = (0.2-0.25)*( _L1 + _L2 + _L3 ), _L2 = (2-4) _L1 , _L3 = (1-1.2) _L2 ; the length of the inner ring equal straight section (3) is defined as _Lx1 , the length of the middle ring equal straight section (4) is defined as _Lx2 , and the length of the outer ring equal straight section (6) is defined as _Lx3 , satisfying _Lx2 = ( _Lx1 + _L1 ) ≥ _L3 , _Lx3 = _Lx2 + _L2 . 3. A hypersonic thrust vectoring nozzle according to claim 1, characterized in that: the inner wall tangent angle of the inner ring outlet (5) is defined as α, and the inner wall tangent angle of the middle ring expansion section inlet (18) is defined as β, satisfying α=β, and α≤15°; the inner wall surface of the middle ring outlet (8) is tangent to the inner wall surface of the outer ring expansion section inlet (17). 4. A hypersonic thrust vectoring nozzle according to claim 1, characterized in that: the non-vector large outlet area state of the hypersonic thrust vectoring nozzle is: the inlet (18) of the middle ring expansion section is flush with the inner ring outlet (5), and the inlet (17) of the outer ring expansion section is flush with the middle ring outlet (8); the inner wall surfaces of the middle ring expansion section (12) and the outer ring expansion section (13) are combined into a continuous inner wall surface, which together with the inner wall surface of the inner sleeve ring (1) constitute the axisymmetric expansion flow channel of the hypersonic thrust vectoring nozzle. 5. A hypersonic thrust vectoring nozzle according to claim 1, characterized in that: the axisymmetric expansion type flow channel is provided with a step at the inner ring outlet (5), the step being the wall thickness at the inner sleeve ring outlet (5), the step causing the middle sleeve ring (7) to be staggered with the inner sleeve ring (1), so that the middle sleeve ring (7) can freely translate in the axial direction, and at the same time the step raises the height of the middle ring flow channel (15), so that more air is taken in, thereby improving the performance of the hypersonic thrust vectoring nozzle. 6. A hypersonic thrust vectoring nozzle according to claim 1, characterized in that: the diameter of the inner ring outlet (5) is defined as _De1 , the diameter of the middle ring expansion section inlet (18) is defined as _Di2 , the step height is h, and _Di2 = _De1 +2h, h = (0.04-0.05) _De1 ; the diameter of the middle ring outlet (8) is defined as _De2 , the diameter of the outer ring outlet (9) is defined as _De3, and _De3 = (1.15-1.2) _De2 . 7. A method for translational adjustment of a hypersonic thrust vector nozzle as described in any one of claims 1 to 6, characterized in that it includes an outlet area translational adjustment method and a thrust vector translational adjustment method: the outlet area translational adjustment method includes two types: translational adjustment of a large outlet area to a small outlet area, and translational adjustment of a small outlet area to a large outlet area; the thrust vector translational adjustment method includes two types: translational adjustment for generating a pitch direction vector angle and translational adjustment for generating a yaw direction vector angle. 8. The translation adjustment method according to claim 7, characterized in that: the translation adjustment process of adjusting the large outlet area to the small outlet area is as follows: the inner ring (1) remains in a fixed position, the middle ring (7) translates upstream by a distance _X1 , satisfying _X1 = (0.25-1)* _L2 , the outer ring (14) translates upstream until the outer ring outlet (9) is flush with the middle ring outlet (8), at which time the hypersonic thrust vector nozzle is in a non-vector small outlet area state, and the outlet area of the hypersonic thrust vector nozzle is small, which is suitable for low Mach number flight conditions; The translation adjustment of the small outlet area to the large outlet area is that the position of the inner ring (1) remains unchanged, the middle ring (7) translates downstream until the middle ring expansion section inlet (18) is flush with the inner ring outlet (5), and the outer ring (14) translates downstream until the outer ring expansion section inlet (17) is flush with the middle ring outlet (8). At this time, the inner wall surface and the step of the inner ring expansion section (10), the middle ring expansion section (12), and the outer ring expansion section (13) are combined into a continuous inner wall surface, and the hypersonic thrust vector nozzle has a large outlet area, which is suitable for high Mach number flight conditions. 9. The translation adjustment method according to claim 8, characterized in that: the translation adjustment method for generating the pitch direction vector angle comprises: (1) The inner sleeve ring (1) remains in a fixed position, and the upper half middle sleeve ring (22) and the upper half outer sleeve ring (21) move downstream to a position in a non-vector large outlet area state, wherein the position in the non-vector large outlet area state is specifically: the inlet of the middle sleeve ring expansion section (18) is flush with the position of the inner sleeve ring outlet (5), and the inlet of the outer sleeve ring expansion section (17) is flush with the position of the middle sleeve ring outlet (8); the lower half middle sleeve ring (20) moves upstream to a position in which the middle sleeve ring outlet (8) is flush with the inner sleeve ring outlet (5), and the lower half outer sleeve ring (19) also moves upstream to a position in which the outer sleeve ring outlet (9) is flush with the inner sleeve ring outlet (5); at this time, the hypersonic thrust vector nozzle is an asymmetric configuration staggered up and down, generating a nose-down vector angle in a high Mach number flight condition, and generating a nose-up vector angle in a low Mach number flight condition; (2) The inner sleeve ring (1) remains in a fixed position, the lower half middle sleeve ring (20) and the lower half outer sleeve ring (19) move downstream to a position in a non-vector large outlet area state, the upper half middle sleeve ring (20) moves upstream to a position where the middle sleeve outlet (8) is flush with the inner sleeve outlet (5), and the upper half outer sleeve ring (21) also moves upstream to a position where the outer sleeve outlet (9) is flush with the inner sleeve outlet (5); at this time, the hypersonic thrust vector nozzle is an asymmetric configuration staggered up and down, generating a nose-up vector angle in a high Mach number flight condition and a nose-down vector angle in a low Mach number flight condition; The translation adjustment method for generating the yaw direction vector angle comprises: (a) The inner sleeve ring (1) remains stationary, the left half middle sleeve ring (26) and the left half outer sleeve ring (25) move downstream to a position in a non-vector large outlet area state, the right half middle sleeve ring (23) moves upstream to a position where the middle sleeve outlet (8) is flush with the inner sleeve outlet (5), and the right half outer sleeve ring (24) also moves upstream to a position where the outer sleeve outlet (9) is flush with the inner sleeve outlet (5). At this time, the hypersonic thrust vector nozzle is an asymmetric configuration with left and right staggered, generating a right yaw vector angle in a high Mach number flight condition and a left yaw vector angle in a low Mach number flight condition. (b) The inner ring (1) remains stationary, the right half middle ring (23) and the right half outer ring (24) move downstream to a position in a non-vector large outlet area state, the left half middle ring (26) moves upstream to a position where the middle ring outlet (8) is flush with the inner ring outlet (5), and the left half outer ring (25) also moves upstream to a position where the outer ring outlet (9) is flush with the inner ring outlet (5). At this time, the hypersonic thrust vector nozzle is an asymmetric configuration with left and right staggered, generating a left yaw vector angle in a high Mach number flight condition and a right yaw vector angle in a low Mach number flight condition. 10. A flow control method for a hypersonic thrust vector nozzle according to any one of claims 1 to 6, characterized in that: The flow control method is a secondary flow intake, that is, introducing external high-speed atmosphere into the middle ring flow channel (15) and the outer ring flow channel (16), so as to improve the thrust performance of the hypersonic thrust vector nozzle in a non-vector small exit area state and a low Mach number flight condition; The middle ring flow channel (15) is a flow channel formed between the inner ring (1) and the middle ring (7) when the hypersonic thrust vectoring nozzle is in a non-vector small outlet area state or under a low Mach number flight condition, and the outer ring flow channel (16) is a flow channel formed between the middle ring (7) and the outer ring (14) when the hypersonic thrust vectoring nozzle is in a non-vector small outlet area state or under a low Mach number flight condition.