Pneumatic deformation device for jet pipe of aircraft

Abstract

An aircraft nozzle pneumatic deformation device belongs to the field of jet engine design. An existing spray pipe generally adopts a fixed structure and cannot be changed timely and autonomously according to factors such as flight task requirements, flight speed and flight environment, so that different task requirements cannot be met. The device comprises an outer spray pipe and a deformation driving mechanism, the outer spray pipe is of a deformable annular structure, and the outer spray pipe is arranged on an engine spray pipe in a sleeving mode and serves as an airflow outlet of the engine spray pipe; the deformation driving mechanism is provided with a plurality of power output ends arranged in the circumferential direction, and each power output end is connected with the side wall of the outer spraying pipe so that the outer spraying pipe can be driven by multiple points in the circumferential direction. The outer spray pipe can expand, contract, pitch around the x axis, roll around the y axis, perform expansion-pitch motion, expansion-roll motion, contract-pitch motion and contract-roll motion under coupling driving of the multiple power output ends. The invention is mainly used for changing the pneumatic action area and action direction of the aircraft nozzle.

Description

Technical Field

[0001] The invention belongs to the field of jet engine design, and in particular relates to an aircraft nozzle aerodynamic deformation device. Background Art

[0002] A jet engine is a component that converts high-pressure gas (or air) into kinetic energy, causing the airflow to expand and accelerate and eject outward at high speed to generate a reaction thrust. It is also called an exhaust nozzle, thrust nozzle or tail nozzle. There are many types of nozzles, which are generally selected based on the performance of the aircraft and the working characteristics of the engine. Existing nozzles generally adopt a fixed structure, which cannot be changed in a timely and autonomous manner according to factors such as flight mission requirements, flight speed and flight environment, and thus cannot meet different mission requirements. Summary of the invention

[0003] In view of this, the present invention provides an aircraft nozzle aerodynamic deformation device, which can change the outlet area and action direction of the nozzle jet airflow to meet the flight mission requirements.

[0004] In order to solve the above technical problems, the technical solution adopted by the present invention is:

[0005] 1. An aircraft nozzle aerodynamic deformation device comprises an outer nozzle and a deformation drive mechanism, wherein the outer nozzle is a deformable annular structure, the outer nozzle is sleeved on an engine nozzle and serves as an airflow outlet of the engine nozzle; the deformation drive mechanism is provided with a plurality of circumferentially arranged power output ends, each power output end is connected to a side wall of the outer nozzle, so that the outer nozzle can be driven at multiple points in a circumferential direction, and the outer nozzle can expand, contract, pitch, roll, expand-pitch motion, expand-roll motion, contract-pitch motion and contract-roll motion under the coupled drive of the plurality of power output ends.

[0006] 2. On the basis of technical solution 1, the outer nozzle includes an outer blade, an inner blade and a cooperative connecting rod assembly. The outer blade and the inner blade are each provided with multiple pieces. The outer blades and the inner blades are alternately arranged inside and outside and enclose a ring structure. A movable gap is left between two adjacent outer blades and is blocked by the inner blade. The power output end of the deformation drive mechanism is arranged one by one in correspondence with the outer blades. Each power output end is connected to the side wall of the corresponding outer blade and can drive the outer blade to swing. There are multiple cooperative connecting rod assemblies, each of which is connected to an inner blade and two outer blades adjacent to the inner blade, so as to drive the middle inner blade to swing synchronously when the two adjacent outer blades swing.

[0007] 3. On the basis of Technical Solution 2, it also includes an annular fixed cover, which is provided with an opening and is sleeved on the outside of the engine nozzle, and the outer blades and the inner blades are hingedly connected to the opening of the annular fixed cover; when the magnitude and direction of the driving force output at each power output end are the same, the two adjacent outer blades swing inward or outward with the same swing amplitude, and drive the inner blade to swing inward or outward through the cooperative connecting rod assembly to fill the gap between the two adjacent outer blades; when the magnitude and / or direction of the driving force output at each power output end are different, the two adjacent outer blades swing inward or outward with different swing amplitudes, and an oblique gap is formed between the two adjacent outer blades. The two adjacent outer blades drive the inner blade to swing inward or outward through the cooperative connecting rod assembly, and also drive it to swing sideways to fill the oblique gap between the two adjacent outer blades.

[0008] 4. Based on technical solution 2, the outer blade and the inner blade are both trapezoidal, the root width of the outer blade is greater than the tip width, and the root width of the inner blade is less than the tip width.

[0009] 5. On the basis of Technical Solution 2, the cooperative connecting rod assembly includes a transmission rail, a transmission slider and a transmission connecting rod. The transmission rail is installed on the side wall of the inner blade and is located at the symmetry axis of the inner blade. The transmission slider is sleeved on the transmission rail and can move along the axis of the transmission rail. There are two transmission connecting rods, which correspond one to one with the two adjacent outer blades. The two transmission connecting rods are symmetrically arranged on both sides of the transmission rail. One end of each transmission connecting rod is connected to the transmission slider and can rotate, and the other end is connected to the corresponding outer blade side wall via a ball pair.

[0010] 6. Based on technical solution 1, the deformation drive mechanism includes a 3-RRS parallel drive assembly and a transmission connecting rod assembly. The transmission connecting rod assembly is provided with multiple and evenly arranged circumferentially. Each transmission connecting rod assembly connects the 3-RRS parallel drive assembly and the outer nozzle, so that the outer nozzle can be driven at multiple points in the circumferential direction.

[0011] 7. Based on technical solution 6, the redundant parallel drive assembly includes a linear drive and a drive ring. The linear drives are provided with N and are evenly arranged circumferentially, N ≥ 3. The actuating end of each linear drive is movably connected to the drive ring and generates driving force for the drive ring.

[0012] 8. Based on technical solution 7, each transmission connecting rod assembly includes a third connecting rod and a blade connecting frame, one end of the third connecting rod is hinged to the drive ring, and the other end is hinged to one end of the blade connecting frame, and the other end of the blade connecting frame is fixedly connected to the inner wall surface of the outer blade.

[0013] 9. On the basis of Technical Solution 1, it also includes a movable base for steering the engine nozzle. While the movable base drives the engine nozzle to deflect, the deformation drive mechanism drives the outer nozzle to deflect in the same direction to ensure that the outer nozzle is coaxial with the engine nozzle.

[0014] 10. On the basis of technical solution 9, the movable base includes a bottom connecting base, a nozzle base, a pitch motor, a pitch drive shaft, a roll motor and a roll drive shaft. The pitch motor is installed on the bottom connecting base, and the pitch drive shaft is connected to the motor shaft of the pitch motor and can rotate with the motor shaft; the engine nozzle is installed on the nozzle base, the roll motor is installed on the nozzle base, the roll drive shaft is connected to the motor shaft of the roll motor and can rotate with the motor shaft, and the roll drive shaft is vertically fixedly connected to the pitch drive shaft.

[0015] Compared with the prior art, the present invention has the following beneficial effects:

[0016] 1. The deformation drive mechanism of the present invention is composed of a 3-RRS parallel drive assembly and a plurality of transmission connecting rod assemblies. The plurality of transmission connecting rod assemblies connect the 3-RRS parallel drive assembly and the outer nozzle so that the outer nozzle is driven at multiple points. The 3-RRS parallel drive assembly can generate a variety of coupling forces, so that the outer nozzle can expand, contract, pitch around the x-axis, roll around the y-axis, expand-pitch motion, expand-roll motion, contract-pitch motion and contract-roll motion under the coupling action of multiple driving forces, thereby being able to adjust the outlet area and / or injection direction of the jet airflow of the engine nozzle 5 to meet the mission requirements of the aircraft.

[0017] 2. The outer blade and the inner blade of the present invention are both designed to be trapezoidal, the root width of the outer blade is greater than the tip width, and the root width of the inner blade is less than the tip width. This design will not affect the contraction of the outer nozzle, and can also achieve gap filling to avoid leaks.

[0018] 3. The design of the cooperative connecting rod assembly and the second rotating pair in the present invention enables the inner blade to swing both inward and outward and sideways, so as to fill the gap between two adjacent outer blades without distinction.

[0019] 4. The movable base in the present invention can drive the engine nozzle to swing so as to change the direction of the nozzle jet airflow. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The accompanying drawings are incorporated as part of this application and are used to provide a further understanding of the present invention.

[0021] Figure 1 The present invention is a schematic structural diagram of an aircraft nozzle aerodynamic deformation device.

[0022] Figure 2The structure of the present invention after removing part of the outer shell and part of the outer nozzle is schematically shown. Figure 1 .

[0023] Figure 3 for Figure 2 A partial enlarged view of point A in the middle.

[0024] Figure 4 The structure of the present invention after removing part of the outer shell and part of the outer nozzle is schematically shown. Figure 2 .

[0025] Figure 5 for Figure 4 A partial enlarged view of point B in the middle.

[0026] Figure 6 It is a schematic diagram of the structure of the connection between the nozzle and the movable base.

[0027] Description of reference numerals: 1-frame; 2-shell wrap; 3-external nozzle; 31-outer blade; 32-inner blade; 33-cooperative connecting rod assembly; 331-slide rail mounting seat; 332-transmission slide rail; 333-transmission slider; 334-transmission connecting rod; 335-connecting rod mounting seat; 34-first rotating pair; 35-second rotating pair; 351-first rotating shaft; 352-first shaft sleeve; 353-second rotating shaft; 354-second Bushing; 36-movable gap; 4-deformation drive mechanism; 41-crank rocker drive unit; 411-blade drive motor; 412-first connecting rod; 413-second connecting rod; 42-third connecting rod; 43-blade connecting frame; 44-drive ring; 5-engine nozzle; 6-movable base; 61-bottom connecting base; 62-nozzle base; 63-pitch motor; 64-pitch drive shaft; 65-roll motor; 66-roll drive shaft. DETAILED DESCRIPTION

[0028] The present invention is described in detail below in conjunction with specific embodiments.

[0029] Figure 1 FIG. 4 shows a schematic structural diagram of an aircraft nozzle aerodynamic deformation device according to the present embodiment. Figure 1 As shown, an aircraft nozzle aerodynamic deformation device of this embodiment includes a frame 1, a shell wrap 2, an outer nozzle 3 and a deformation drive mechanism 4. The frame 1 is an annular frame body, and the shell wrap 2 is provided with multiple pieces. The multiple shell wraps 2 are evenly installed on the frame 1 in the circumferential direction and form an annular fixed cover with an opening on one side. The annular fixed cover is coaxially sleeved outside the engine nozzle 5, and the jet outlet of the engine nozzle 5 faces the opening of the annular fixed cover. Figure 1 As shown, the outer nozzle 3 is a deformable annular structure, and the outer nozzle 3 is coaxially installed at the opening of the annular fixed cover to serve as the air flow outlet of the engine nozzle 5. Figure 2As shown, the deformation drive mechanism 4 is installed in the annular fixed cover, and the deformation drive mechanism 4 is provided with a plurality of power output ends uniformly arranged in the circumferential direction, and each power output end can generate a driving force on the side wall of the outer nozzle 3, that is, the outer nozzle 3 is driven at multiple points in the circumferential direction, and the outer nozzle 3 can generate deformations of expansion, contraction, pitching around the x-axis, rolling around the y-axis, expansion-pitch motion, expansion-roll motion, contraction-pitch motion and contraction-roll motion under the coupling action of multiple driving forces, wherein the pitching around the x-axis and the rolling around the y-axis are collectively referred to as vector yaw below, and the expansion-pitch motion, expansion-roll motion, contraction-pitch motion and contraction-roll motion are collectively referred to as coupling motion below. The deformation of the outer nozzle 3 can adjust the outlet area and / or injection direction of the jet airflow of the engine nozzle 5 to meet the mission requirements of the aircraft. In addition, in this embodiment, the outer nozzle 3 is arranged outside the original engine nozzle 5, and there is no need to improve the original structure, so as to avoid the occurrence of problems affecting aerodynamics caused by directly improving the engine nozzle.

[0030] like Figure 2 As shown, the outer nozzle 3 of this embodiment includes an outer blade 31, an inner blade 32 and a coordinated connecting rod assembly 33. The outer blade 31 and the inner blade 32 are provided with multiple pieces and the number of the two pieces is the same. The outer blade 31 and the inner blade 32 are alternately arranged inside and outside and connected to form a deformable annular structure via the coordinated connecting rod assembly 33. Specifically, as Figure 2 and Figure 3 As shown, multiple outer blades 31 are evenly arranged circumferentially, and each outer blade 31 is connected to the opening of the annular fixed cover through a first rotation pair 34. A movable gap 36 is left between two adjacent outer blades 31 to leave room for movement when the outer blades 31 swing inward. Multiple inner blades 32 are also evenly arranged circumferentially, and each inner blade 32 is connected to the opening of the annular fixed cover through a second rotation pair 35. The inner blade 32 is located on the inner side of the outer blade 31 and is staggered with the outer blade 31, so that the inner blade 32 can block the movable gap 36 between two adjacent outer blades 31. Figure 4As shown, the power output end of the deformation driving mechanism 4 is arranged in one-to-one correspondence with the outer blade 31, and each power output end is connected to the inner wall of the outer blade 31, and can drive the corresponding outer blade 31 to swing inward or outward around the first rotation pair 34. There are multiple cooperative link assemblies 33, and each inner blade 32 corresponds to a cooperative link assembly 33. The cooperative link assembly 33 connects the corresponding inner blade 32 and the two outer blades 31 adjacent to the inner blade 32, so that when the two outer blades 31 swing, the inner blade 32 in the middle can be driven to swing through the cooperative link assembly 33. It can be seen that the outer nozzle 3 in this embodiment uses the swing of the outer blade 31 and the inner blade 32 to achieve multiple deformations. When the driving force output by each power output end of the deformation driving mechanism 4 is the same in size and direction, all the outer blades 31 and all the inner blades 32 are subjected to the same force, and the contraction or expansion movement of the outer nozzle 3 can be achieved. When the magnitude and / or direction of the driving force outputted by the power output end of the deformation driving mechanism 4 are different, the magnitude and direction of the driving force received by the outer blade 31 are different, and the magnitude and direction of the driving force received by the inner blade 32 are also different, so that the vector yaw motion or coupling motion of the outer nozzle 3 can be realized. The specific deformation process is as follows:

[0031] When each power output end of the deformation drive mechanism 4 pulls the outer blades 31 inward with the same force, all the outer blades 31 swing inward with the same swing amplitude, and the inner blades 32 swing inward with the outer blades 31 driven by the coordinated connecting rod assembly 33, and the outer nozzle 3 is evenly stressed as a whole and shrinks inward to reduce the outlet area of ​​the engine nozzle 5 jet airflow. When each power output end of the deformation drive mechanism 4 pushes the outer blades 31 outward with the same thrust, all the outer blades 31 swing outward with the same swing amplitude, and the inner blades 32 swing outward with the outer blades 31 driven by the coordinated connecting rod assembly 33, and the outer nozzle 3 is evenly stressed as a whole and expands outward to increase the outlet area of ​​the engine nozzle 5 jet airflow. The driving force output by each power output end of the deformation drive mechanism 4 is different in magnitude and / or direction. The driving force received by the outer nozzle 3 as a whole is a gradual force along its diameter direction (a force that increases or decreases according to a certain rule). That is to say, the force received between the two adjacent outer blades 31 is a gradual force, so that the swing amplitude between the two adjacent outer blades 31 is gradual. The inner blades 32 swing together with the outer blades 31 driven by the cooperative connecting rod assembly 33, and the outer nozzle 3 as a whole deflects to one side, thereby generating a vector yaw or coupled motion, thereby changing the direction and / or effective area of ​​the jet airflow of the engine nozzle 5.

[0032] When the outer nozzle 3 is contracting or expanding, the outer blade 31 and the inner blade 32 need to swing inward or outward accordingly. When swinging inward, two adjacent outer blades 31 may interfere with each other and affect the contraction amplitude of the outer nozzle 3. This embodiment solves this problem by specially designing the shapes of the outer blade 31 and the inner blade 32. Specifically:

[0033] like Figure 1 As shown, the outer blade 31 in this embodiment is designed to be trapezoidal, and the root width of the outer blade 31 is greater than the tip width. With this design, the movable gap 36 between two adjacent outer blades 31 gradually increases from the root to the tip, which can avoid the problem of interference between the two adjacent outer blades 31 when they swing inward. However, when the outer blade 31 swings outward, as the swing amplitude of the outer blade 31 increases, the movable gap 36 between the two adjacent outer blades 31 also gradually increases, especially near the tip, which may cause a gap in the outer nozzle, thereby affecting the aerodynamic force on the aircraft. Figure 4 As shown, the inner blade 32 in this embodiment is also designed to be trapezoidal, and the root width of the inner blade 32 is smaller than the tip width. In this way, the wider tip of the inner blade 32 can fill the larger active gap 36 between the two adjacent outer blades 31 near the tip, avoiding the generation of gaps. It can be seen that the outer blades 31 and the inner blades 32 of this embodiment are designed in a trapezoidal shape, which can not only avoid the interference of the outer blades 31 when the outer nozzle contracts, but also avoid the generation of gaps when the outer nozzle expands.

[0034] Before the outer nozzle 3 is deformed, the active gap 36 between the two adjacent outer blades 31 is blocked by the blade surface of the inner blade 32, so the active gap 36 and the inner blade 32 can be regarded as being on the same circumferential surface. When the outer nozzle 3 is vector-deflected, the swing amplitude of each outer blade 31 is different. From the direction of the nozzle, a shape similar to a step is formed between the two adjacent outer blades 31, which causes the active gap 36 between the two adjacent outer blades 31 to no longer be on the same circumferential surface, that is, the active gap 36 is deflected. If the inner blade 32 can only swing inward and outward, the active gap 36 cannot be completely blocked, resulting in a gap in the outer nozzle 3, affecting the aerodynamic force on the aircraft. At the same time, the inner surface of the outer nozzle 3 will not be smooth enough, the airflow force is turbulent, and the flight trajectory of the aircraft is disturbed. In addition, when the inner blade 32 swings with the outer blade 31, it may also interfere with the outer blade 31, affecting the swing of the outer blade 31. This embodiment solves the problem by coordinating the transmission of the connecting rod assembly 33 and increasing the freedom of the inner blade 32 to swing. Specifically:

[0035] Figure 5 The schematic diagram of the structure of the cooperative connecting rod assembly is shown in FIG. Figure 5As shown, the cooperative connecting rod assembly 33 of this embodiment includes a slide rail mounting seat 331, a transmission slide rail 332, a transmission slider 333, a transmission connecting rod 334 and a connecting rod mounting seat 335. The transmission slide rail 332 is mounted on the inner wall surface of the inner blade 32 via the slide rail mounting seat 331. The transmission slide rail 332 is located at the symmetry axis of the inner blade 32, and the direction of the axis of the transmission slide rail 332 is in the same direction as the extension direction of the symmetry axis of the inner blade 32. The transmission slider 333 is sleeved on the transmission slide rail 332 and can move along the direction of the axis of the transmission slide rail 332. There are two transmission connecting rods 334, and the two transmission connecting rods 334 are symmetrically arranged on both sides of the transmission slide rail 332. There are two connecting rod mounting seats 335, which correspond to the transmission connecting rods 334 one by one. The two connecting rod mounting seats 335 are respectively mounted on the inner wall surfaces of the two adjacent outer blades 31 (such as Figure 5 As shown, the connecting rod mounting seat 335 on the same outer blade 31 can be set as an integral body), one end of each transmission connecting rod 334 is connected to the transmission slider 333 and can rotate, and the other end is connected to the corresponding connecting rod mounting seat 335 via a ball pair, thereby realizing the connection between the inner blade 32 and the outer blades 31 on both sides. Each outer blade 3 can transmit driving force to the inner blade 32 through the transmission connecting rod 334, that is, each inner blade 32 is subjected to two driving forces and can swing under the two driving forces.

[0036] Figure 3 The schematic diagram of the structure of the second rotating pair is shown. Figure 3 It can be seen that the second rotating pair 35 of this embodiment is a universal joint structure, which is provided with a first rotating shaft 351, a first sleeve 352, a second rotating shaft 353 and a second sleeve 354. The first sleeve 352 is installed in the annular fixed cover, the first rotating shaft 351 is arranged in the first sleeve 352 and can rotate, the second sleeve 354 is installed at the root of the inner blade 32, one end of the second rotating shaft 353 is arranged in the second sleeve 354 and can rotate, and the other end is inserted into the first rotating shaft 351 along the diameter direction of the first rotating shaft 351. It can be seen that the inner blade 32 has two degrees of freedom, namely the degree of freedom of rotation around the first rotating shaft 351 and the degree of freedom of rotation around the second rotating shaft 353. The inner blade 32 can produce different swings under the coupling action of the above two driving forces.

[0037] Specifically, when the outer nozzle 3 is preparing to perform a contraction movement or an expansion movement, the driving force output by each power output end of the deformation driving mechanism 4 is the same in magnitude and direction, and all the outer blades 31 are subjected to the same force and swing inward or outward with the same swing amplitude. At this time, the movable gap 36 between each two adjacent outer blades 31 is on the same circumferential surface, and the two adjacent outer blades 31 generate the same magnitude of pulling force on the two transmission connecting rods 334 connected thereto, so the two driving forces received by the inner blade 32 are also the same in magnitude. Under the coupling force of the two driving forces, the inner blade 32 only swings inward or outward around the first rotating axis 351, and the inner blade 32 can block the movable gap 36. When the outer nozzle 3 performs vector yaw motion or coupling motion in advance, the deformation drive mechanism 4 applies symmetrical forces to both sides of the outer nozzle 3 with the diameter of the outer nozzle 3 as the symmetry axis, and the power output end on one side of the symmetry axis applies a gradual force to the two adjacent outer blades 31. At this time, the adjacent two outer blades 31 are subjected to different forces and swing amplitudes, and the adjacent two outer blades 31 produce different pulling forces on the two transmission connecting rods 334 connected thereto, and the two driving forces on the inner blade 32 are also different in magnitude. The coupling force of the two driving forces drives the inner blade 32 to swing inward or outward while also driving it to deflect, that is, the inner blade 32 swings around the first rotation axis 351 and also swings around the second rotation axis 353, so as to achieve the blocking of the active gap 36 by the inner blade 32. It can be seen that no matter whether the outer nozzle 3 performs expansion motion, contraction motion, vector yaw motion or coupling motion, the inner blade 32 in this embodiment can fill the active gap 36 indiscriminately to avoid affecting the flight of the aircraft.

[0038] Figure 2 and Figure 3 FIG. 4 shows a schematic diagram of the structure of the deformation driving mechanism. Figure 2 and Figure 3As shown, the deformation drive mechanism 4 of the present embodiment is composed of a redundant parallel drive assembly and a transmission connecting rod assembly. There are multiple transmission connecting rod assemblies. The redundant parallel drive assembly can generate multiple coupling forces and can be transmitted to the outer nozzle 3 through multiple transmission connecting rod assemblies to achieve multiple deformations of the outer nozzle 3. Specifically, the redundant parallel drive assembly of the present embodiment is preferably a 3-RRS parallel drive assembly. The 3-RRS parallel drive assembly includes a linear drive and a drive ring 44. There are three linear drives and they are evenly arranged circumferentially. The linear drive is preferably a crank rocker drive unit 41. Each crank rocker drive unit 41 includes a blade drive motor 411, a first connecting rod 412 and a second connecting rod 413. The blade drive motor 411 is installed on the frame 1. The drive ring 44 is coaxially arranged in the frame 1. One end of the first connecting rod 412 is connected to the blade drive motor 411. The motor shaft can rotate with the motor shaft, and the other end is hinged to one end of the second connecting rod 413, and the other end of the second connecting rod 413 is hinged to the drive ring 44. It can be seen that the drive ring 44 is driven by three points, and the three-point drive is evenly arranged. The drive ring 44 is the end output platform driven by the three crank rocker drive units 41. Under the coupled drive of the three crank rocker drive units 41, the drive ring 44 can move up horizontally, move down horizontally, pitch around the x-axis, roll around the y-axis, move up horizontally while also doing pitch or roll movement, and move down while also doing pitch or roll movement. The specific implementation process is as follows. It should be noted that the drive ring 44 remains horizontal in the initial state:

[0039] Horizontal upward movement: the three blade drive motors 411 drive their respective first connecting rods 412 to rotate counterclockwise, and the first connecting rod 412 drives the second connecting rod 413 to swing upward. At this time, the coupling force output by the three crank rocker drive units 41 is an upward thrust along the z-axis direction, and the drive ring 44 moves horizontally upward due to the upward thrust.

[0040] Horizontal downward movement: the three blade drive motors 411 drive their respective first connecting rods 412 to rotate clockwise, and the first connecting rod 412 drives the second connecting rod 413 to swing downward. At this time, the coupling force output by the three crank rocker drive units 41 is a downward pulling force along the z-axis direction, and the drive ring 44 moves horizontally downward due to the downward pulling force.

[0041] Pitch motion: The three blade drive motors 411 are driven synchronously. The blade drive motor 411 on one side of the x-axis drives the corresponding first connecting rod 412 to rotate clockwise. The first connecting rod 412 drives the second connecting rod 413 to swing downward, and a driving point of the drive ring 44 is subjected to a downward pulling force (upward thrust). The two blade drive motors 411 on the other side of the x-axis drive the corresponding first connecting rod 412 to rotate counterclockwise at the same angle. The first connecting rod 412 drives the corresponding second connecting rod 413 to swing upward, and the other two driving points of the drive ring 44 are subjected to an upward thrust (downward pulling force). The coupling force output by the three crank rocker drive units 41 is on one side of the x-axis and is a force rotating around the x-axis. The drive ring 44 performs a pitch motion around the x-axis under the coupling force.

[0042] Rolling motion: The three blade drive motors 411 are driven synchronously. The blade drive motor 411 on one side of the y-axis drives the corresponding first connecting rod 412 to rotate clockwise. The first connecting rod 412 drives the second connecting rod 413 to swing downward, and a driving point of the drive ring 44 is subjected to a downward pulling force (upward thrust). The two blade drive motors 411 on the other side of the y-axis drive the corresponding first connecting rod 412 to rotate counterclockwise at the same angle. The first connecting rod 412 drives the corresponding second connecting rod 413 to swing upward, and the other two driving points of the drive ring 44 are subjected to an upward thrust (downward pulling force). The coupling force output by the three crank rocker drive units 41 is on one side of the y-axis and is a force rotating around the y-axis. The drive ring 44 performs a rolling motion around the y-axis under the coupling force.

[0043] Upward + pitch coupling movement: the three blade drive motors 411 are driven synchronously, each blade drive motor 411 drives the corresponding first connecting rod 412 to rotate counterclockwise, the first connecting rod 412 drives the second connecting rod 413 to swing upward, and the drive ring 44 as a whole is subjected to an upward thrust, but the force on the driving point on one side of the x-axis on the drive ring 44 is less than / greater than the force on the two driving points on the other side of the x-axis, that is, the coupling force output by the three crank rocker drive units 41 is on one side of the x-axis, and the coupling force can be decomposed into an upward force along the z-axis and a rotational force around the x-axis. The drive ring 44 moves upward under the coupling force and also performs a pitch motion around the x-axis.

[0044] Upward + rolling coupling movement: the three blade drive motors 411 are driven synchronously, each blade drive motor 411 drives the corresponding first connecting rod 412 to rotate counterclockwise, the first connecting rod 412 drives the second connecting rod 413 to swing upward, and the drive ring 44 as a whole is subjected to an upward thrust, but the force on the driving point on one side of the y-axis on the drive ring 44 is less than / greater than the force on the two driving points on the other side of the y-axis, that is, the coupling force output by the three crank rocker drive units 41 is on one side of the y-axis, and the coupling force can be decomposed into an upward force along the z-axis and a rotational force around the y-axis. The drive ring 44 moves upward under the coupling force while also rolling around the y-axis.

[0045] Downward movement + pitch coupling movement: the three blade drive motors 411 are driven synchronously, each blade drive motor 411 drives the corresponding first connecting rod 412 to rotate clockwise, the first connecting rod 412 drives the second connecting rod 413 to swing downward, and the drive ring 44 as a whole is subjected to downward pulling force, but the force on the driving point on one side of the x-axis on the drive ring 44 is less than / greater than the force on the two driving points on the other side of the x-axis. That is to say, the coupling force output by the three crank rocker drive units 41 is on one side of the x-axis, and the coupling force can be decomposed into a downward force along the z-axis and a rotational force around the x-axis. The drive ring 44 moves downward under the coupling force and also performs a pitch motion around the x-axis.

[0046] Downward movement + rolling coupling movement: the three blade drive motors 411 are driven synchronously, each blade drive motor 411 drives the corresponding first connecting rod 412 to rotate clockwise, and the first connecting rod 412 drives the second connecting rod 413 to swing downward. The drive ring 44 is subjected to a downward pulling force as a whole, but the force on the driving point on one side of the y-axis on the drive ring 44 is less than / greater than the force on the two driving points on the other side of the y-axis. That is to say, the coupling force output by the three crank rocker drive units 41 is on one side of the y-axis, and the coupling force can be decomposed into a downward force along the z-axis and a rotational force around the y-axis. The drive ring 44 moves downward under the coupling force and also rolls around the y-axis.

[0047] like Figure 4As shown, multiple transmission link assemblies of this embodiment are evenly arranged along the circumferential direction of the driving ring 44, and each transmission link assembly corresponds to an outer blade 31; each transmission link assembly includes a third link 42 and a blade connecting frame 43, one end of the third link 42 is hinged to the driving ring 44, and the other end is hinged to one end of the blade connecting frame 43, and the other end of the blade connecting frame 43 is fixedly connected to the inner wall surface of the outer blade 31, wherein the blade connecting frame 43 is the power output end of the deformation driving mechanism 4. The driving ring 44 can generate different pulling forces on the transmission link assemblies at different positions under different motion states. Specifically, during the horizontal downward movement of the driving ring 44, all the third links 42 can be pulled downward synchronously, and the driving forces received by all the third links 42 are of the same magnitude and downward direction. The third links 42 drive the outer blades 31 to swing inwards via the blade connecting frame 43, and the swing amplitudes of all the outer blades 31 are the same, so as to achieve the contraction of the outer nozzle 3. During the horizontal upward movement of the driving ring 44, all the third links 42 can be pushed to move upward synchronously. The driving force on all the third links 42 is the same in magnitude and in an upward direction. The third links 42 drive the outer blades 31 to swing outwards via the blade connecting frame 43. The swing amplitudes of all the outer blades 31 are the same, thereby realizing the expansion of the outer nozzle 3. During the pitch or roll movement of the driving ring 44, the third links 42 on one side of the x-axis (y-axis) of the driving ring 44 are pulled downwards and move downwards, and the third links 42 on the other side of the x-axis (y-axis) are pushed upwards and move upwards. The third links 42 moving downwards drive the corresponding outer blades 31 to swing inwards via the blade connecting frame 43, and the third links 42 moving upwards drive the corresponding outer blades 31 to swing outwards via the blade connecting frame 43, thereby realizing the vector deflection of the outer nozzle 3. When the driving ring 44 moves upward as a whole and performs a coupled motion of pitch or roll, the driving ring 44 pushes all the third links 42 to move upward synchronously with different thrusts. The driving force on the third link 42 corresponding to the position where the driving ring 44 moves upward faster is greater than that at other positions. The driving force of the third link 42 at this position on the outer blade 31 is greater than that at other positions, resulting in different outward swinging amplitudes of the outer blade 31 at different positions, so that the outer nozzle 3 expands while performing a coupled motion of pitch or roll. When the driving ring 44 moves downward as a whole and performs a coupled motion of pitch or roll, the driving ring 44 pulls all the third links 42 to move downward synchronously with different pulling forces. The driving force on the third link 42 corresponding to the position where the driving ring 44 moves downward faster is greater than that at other positions. The driving force on the outer blade 31 at this position is greater than that at other positions, resulting in different inward swinging amplitudes of the outer blade 31 at different positions, so that the outer nozzle 3 contracts while performing a coupled motion of pitch or roll.

[0048] It can be seen that the outer nozzle 3 of this embodiment can achieve multiple deformations of expansion, contraction, vector deflection and coupled motion under the coupling driving force of the three crank rocker drive units 41, the cooperation of the drive ring 44 and multiple transmission connecting rod assemblies, and when the outer nozzle 3 transitions from the vector deflection on one side to the other side, it can be achieved without reversing (for example, it can directly transition from the left side to the right side, without transitioning from the left side to the upper side, and then from the upper side to the right side), achieving free deflection, and the entire movement process is simple. The number of driving sources of the deformation drive mechanism 4 is small, which reduces the solution process of the deformation drive mechanism 4. In addition, the deformation drive mechanism 4 adopts the form of a crank rocker, which can speed up the response speed of the outer nozzle 3, thereby speeding up the deformation of the outer nozzle 3.

[0049] After the outer nozzle 3 undergoes vector deflection or coupling motion, the airflow ejected by the engine nozzle 5 directly acts on the inner wall surface of the outer nozzle 3, and then the inner wall surface changes the direction of the airflow. Although this method can achieve the change of the direction of the ejected airflow, it will lose a part of the force of the airflow, and the outer blades 31 and the inner blades 32 are easily damaged after being subjected to the ejection force of the airflow for a long time. Figure 6 As shown, this embodiment is also provided with a movable base 6 for steering the engine nozzle 5. The engine nozzle 5 is mounted on the frame 1 via the movable base 6. When the direction of the airflow ejected from the engine nozzle 5 needs to be changed, the movable base 6 drives the engine nozzle 5 to deflect, and at the same time, the deformation drive mechanism 4 drives the outer nozzle 3 to make a vector deflection movement in the same direction as the engine nozzle 5, so as to ensure that the outer nozzle 3 and the engine nozzle 5 always remain coaxial. In other words, this embodiment directly changes the direction of the airflow ejected from the engine nozzle 5 via the movable base 6, and at the same time, in order to prevent the outer nozzle 3 from affecting the ejection direction of the airflow, the outer nozzle 3 makes a synchronous deflection. In this way, the loss of airflow force can be avoided, and damage to the outer blades 31 and the inner blades 32 can be avoided. Specifically, Figure 6 The structure diagram of the movable base is shown in FIG. Figure 6As shown, the movable base 6 of this embodiment includes a bottom connecting base 61, a nozzle base 62, a pitch motor 63, a pitch drive shaft 64, a roll motor 65 and a roll drive shaft 66. The bottom connecting base 61 is installed on the frame 1, the pitch motor 63 is installed on the bottom connecting base 61, the pitch drive shaft 64 is connected to the motor shaft of the pitch motor 63 and can rotate with the motor shaft; the engine nozzle 5 is installed on the nozzle base 62, the roll motor 65 is installed on the nozzle base 62, the roll drive shaft 66 is connected to the motor shaft of the roll motor 65 and can rotate with the motor shaft, and the roll drive shaft 66 is vertically fixedly connected to the pitch drive shaft 64; when the pitch motor 63 drives the pitch drive shaft 64 to rotate, the roll drive shaft 66 drives the engine nozzle 5 to rotate around the pitch drive shaft 64 via the nozzle base 62 to realize the pitch movement of the engine nozzle 5. When the roll motor 65 drives the roll drive shaft 66 to rotate, the roll drive shaft 66 remains stationary under the limit of the pitch drive shaft 64, and transmits the rotational driving force in reverse to the roll motor 65. The roll motor 65 drives the engine nozzle 5 to rotate around the roll drive shaft 66 via the nozzle base 62 to realize the rolling movement of the engine nozzle 5.

[0050] Combine the following Figure 1 The working principle and working process of the aerodynamic deformation device of the aircraft engine nozzle 5 of this embodiment are described in detail.

[0051] Expansion of the outer nozzle: The three blade drive motors 411 drive the first connecting rods 412 corresponding to them to rotate counterclockwise, and the first connecting rod 412 drives the second connecting rod 413 to swing upward. At this time, the drive ring 44 is subjected to three identical upward thrusts and moves upward horizontally. During the horizontal upward movement of the drive ring 44, all the third connecting rods 42 are pushed to move upward synchronously. All the third connecting rods 42 are subjected to the same driving force. The third connecting rods 42 drive the outer blades 31 to swing outward with the same swing amplitude via the blade connecting frame 43. The two adjacent outer blades 31 drive the inner blades 3 to swing via the transmission connecting rod 334 and the transmission slider 333. The driving force of the two outer blades 31 on the inner blade 32 in the middle is the same in magnitude and direction, and the inner blade 32 swings outward around the first rotating shaft 351, thereby achieving the expansion of the outer nozzle 3.

[0052] The outer nozzle retracts: the three blade drive motors 411 drive the first connecting rods 412 corresponding to them to rotate clockwise, and the first connecting rod 412 drives the second connecting rod 413 to swing downward. At this time, the drive ring 44 is subjected to three identical downward pulling forces and moves downward horizontally. During the horizontal downward movement of the drive ring 44, all the third connecting rods 42 are pulled downward synchronously, and all the third connecting rods 42 are subjected to the same driving force. The third connecting rods 42 drive the outer blades 31 to swing inward with the same swing amplitude via the blade connecting frame 43. The two adjacent outer blades 31 drive the inner blades 3 to swing via the transmission connecting rod 334 and the transmission slider 333. The driving force of the two outer blades 31 on the inner blade 32 in the middle is the same in magnitude and direction, and the inner blade 32 swings inward around the first rotating shaft 351, thereby realizing the retraction of the outer nozzle 3.

[0053] Vector deflection of the outer nozzle: the three blade drive motors 411 are driven synchronously, the blade drive motor 411 on one side of the x-axis (y-axis) drives the corresponding first connecting rod 412 to rotate clockwise, the first connecting rod 412 drives the second connecting rod 413 to swing downward, and a driving point of the driving ring 44 is subjected to downward pulling force. The two blade drive motors 411 on the other side of the x-axis (y-axis) drive the corresponding first connecting rod 412 to rotate counterclockwise at the same angle, and the first connecting rod 412 drives the corresponding second connecting rod 413 to swing upward. The other two driving points of the driving ring 44 are subjected to an upward thrust, and the driving ring 44 performs a pitch or roll motion under the driving forces corresponding to the three driving points. When the driving ring 44 is performing a pitch or roll motion, the third connecting rod 42 on one side of the x-axis (y-axis) of the driving ring 44 is subjected to a downward pulling force and moves downward, and the third connecting rod 42 on the other side of the x-axis (y-axis) is subjected to an upward thrust and moves upward. The third connecting rod 42 moving downward drives the corresponding outer blade 31 to swing inward via the blade connecting frame 43, and the third connecting rod 42 moving upward drives the corresponding outer blade 31 to swing outward via the blade connecting frame 43, thereby realizing the vector deflection of the outer nozzle 3.

[0054] Expansion + pitch or roll coupling motion: The three blade drive motors 411 are driven synchronously and drive the corresponding first connecting rods 412 to rotate counterclockwise. The first connecting rods 412 drive the corresponding second connecting rods 413 to swing upward. The angle output by one blade drive motor 411 is smaller than the angle output by the other two blade drive motors 411, so that the upward thrust received by one driving point of the drive ring 44 is smaller than the upward thrust received by the other two driving points. At this time, the drive ring 44 moves upward as a whole and also performs pitch or roll motion. When the drive ring 44 moves upward as a whole and performs pitch or roll coupling motion, the drive ring 44 pushes all the third connecting rods 42 to move upward synchronously with different thrusts. The driving force received by the third connecting rod 42 corresponding to the position where the drive ring 44 moves upward quickly is greater than that of the other positions. The driving force of the third connecting rod 42 at this position on the outer blade 31 is greater than that of the other positions, resulting in different amplitudes of the outer blade 31 swinging outward at different positions, so that the outer nozzle 3 expands and performs pitch or roll coupling motion at the same time.

[0055] Contraction + pitch or roll coupling motion: The three blade drive motors 411 are driven synchronously and drive the corresponding first connecting rods 412 to rotate clockwise. The first connecting rods 412 drive the corresponding second connecting rods 413 to swing downward. The angle output by one blade drive motor 411 is smaller than the angle output by the other two blade drive motors 411, so that the downward pulling force received by one driving point of the drive ring 44 is smaller than the downward pulling force received by the other two driving points. At this time, the drive ring 44 moves downward as a whole and also performs pitch or roll motion. When the drive ring 44 moves downward as a whole and performs pitch or roll coupling motion, the drive ring 44 pulls all the third connecting rods 42 to move downward synchronously with different pulling forces. The driving force received by the third connecting rod 42 corresponding to the position where the drive ring 44 moves downward faster is greater than that of the other positions. The driving force of the third connecting rod 42 at this position on the outer blade 31 is greater than that of the other positions, resulting in different inward swinging amplitudes of the outer blade 31 at different positions, so that the outer nozzle 3 contracts and performs pitch or roll coupling motion at the same time.

[0056] It can be seen from this that the outer nozzle 3 of this embodiment can be deformed in various ways, thereby changing the outlet area of ​​the airflow ejected by the engine nozzle 5 and the direction of action of the airflow.

[0057] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention, rather than to limit the scope of protection of the present invention. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that the technical solution of the present invention can be modified or replaced by equivalents without departing from the essence and scope of the technical solution of the present invention.

Claims

1. An aircraft nozzle aerodynamic deformation device, characterized in that: The invention comprises an outer nozzle and a deformation driving mechanism. The outer nozzle is a deformable annular structure. The outer nozzle is sleeved on the engine nozzle and serves as the airflow outlet of the engine nozzle. The deformation driving mechanism is provided with a plurality of circumferentially arranged power output ends. Each power output end is connected to the side wall of the outer nozzle so that the outer nozzle can be driven at multiple points in the circumferential direction. The outer nozzle can perform expansion, contraction, pitch, roll, expansion-pitch motion, expansion-roll motion, contraction-pitch motion and contraction-roll motion under the coupled drive of the plurality of power output ends.

2. The aerodynamic deformation device for an aircraft nozzle according to claim 1, characterized in that: The outer nozzle includes an outer blade, an inner blade and a cooperative connecting rod assembly. The outer blade and the inner blade are both provided with multiple pieces. The outer blades and the inner blades are alternately arranged inside and outside and enclose a ring structure. A movable gap is left between two adjacent outer blades and is blocked by the inner blade. The power output end of the deformation drive mechanism is arranged one by one corresponding to the outer blades. Each power output end is connected to the side wall of the corresponding outer blade and can drive the outer blade to swing. There are multiple cooperative connecting rod assemblies, each of which is connected to an inner blade and two outer blades adjacent to the inner blade, so as to drive the middle inner blade to swing synchronously when the two adjacent outer blades swing.

3. The aerodynamic deformation device for an aircraft nozzle according to claim 2, characterized in that: It also includes an annular fixed cover, which is provided with an opening and is sleeved on the outside of the engine nozzle, and the outer blades and the inner blades are hingedly connected to the opening of the annular fixed cover; when the magnitude and direction of the driving force output at each power output end are the same, the two adjacent outer blades swing inward or outward with the same swing amplitude, and drive the inner blade to swing inward or outward via a coordinated connecting rod assembly to fill the gap between the two adjacent outer blades; when the magnitude and / or direction of the driving force output at each power output end are different, the two adjacent outer blades swing inward or outward with different swing amplitudes, and a skewed gap is formed between the two adjacent outer blades. The two adjacent outer blades drive the inner blade to swing inward or outward via the coordinated connecting rod assembly, and at the same time, drive it to swing sideways to fill the skewed gap between the two adjacent outer blades.

4. The aerodynamic deformation device for an aircraft nozzle according to claim 2, characterized in that: The outer blade and the inner blade are both trapezoidal, the blade root width of the outer blade is greater than the blade tip width, and the blade root width of the inner blade is less than the blade tip width.

5. The aircraft nozzle aerodynamic deformation device according to claim 2, characterized in that: The cooperative connecting rod assembly includes a transmission slide rail, a transmission slider and a transmission connecting rod. The transmission slide rail is installed on the side wall of the inner blade and is located at the symmetry axis of the inner blade. The transmission slider is sleeved on the transmission slide rail and can move along the axis of the transmission slide rail. Two transmission connecting rods are provided and correspond one-to-one to the two adjacent outer blades. The two transmission connecting rods are symmetrically arranged on both sides of the transmission slide rail. One end of each transmission connecting rod is connected to the transmission slider and can rotate, and the other end is connected to the corresponding outer blade side wall via a ball pair.

6. The aircraft nozzle aerodynamic deformation device according to claim 1, characterized in that: The deformation drive mechanism includes a redundant parallel drive assembly and a transmission connecting rod assembly. The transmission connecting rod assembly is provided with multiple and evenly arranged circumferentially. Each transmission connecting rod assembly connects the redundant parallel drive assembly and the outer nozzle so that the outer nozzle can be driven at multiple points in the circumferential direction.

7. The aircraft nozzle aerodynamic deformation device according to claim 6, characterized in that: The redundant parallel drive assembly includes a linear drive and a drive ring. The linear drives are provided with N and are evenly arranged circumferentially, where N≥3. The actuating end of each linear drive is movably connected to the drive ring and generates a driving force for the drive ring.

8. The aircraft nozzle aerodynamic deformation device according to claim 7, characterized in that: Each transmission connecting rod assembly includes a third connecting rod and a blade connecting frame. One end of the third connecting rod is hinged to the driving ring, and the other end is hinged to one end of the blade connecting frame. The other end of the blade connecting frame is fixedly connected to the inner wall surface of the outer nozzle.

9. The aircraft nozzle aerodynamic deformation device according to claim 1, characterized in that: It also includes a movable base for steering the engine nozzle. While the movable base drives the engine nozzle to deflect, the deformation drive mechanism drives the outer nozzle to deflect in the same direction to ensure that the outer nozzle is coaxial with the engine nozzle.

10. The aircraft nozzle aerodynamic deformation device according to claim 9, characterized in that: The movable base includes a bottom connecting base, a nozzle base, a pitch motor, a pitch drive shaft, a roll motor and a roll drive shaft. The pitch motor is installed on the bottom connecting base, and the pitch drive shaft is connected to the motor shaft of the pitch motor and can rotate with the motor shaft; the engine nozzle is installed on the nozzle base, the roll motor is installed on the nozzle base, the roll drive shaft is connected to the motor shaft of the roll motor and can rotate with the motor shaft, and the roll drive shaft is vertically fixedly connected to the pitch drive shaft.

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