An aircraft vector thrust device

Abstract

This application relates to the technical field of aircraft thrust devices, and specifically relates to an aircraft vector thrust device. The vector thrust device includes: a vector motion platform, which can be arranged at the head or tail of the aircraft, and an engine is arranged on the side of the vector motion platform away from the aircraft; three linear motion actuating mechanisms are arranged between the vector motion platform and the aircraft, and the linear motion actuating mechanisms are universally connected to the vector motion platform; one end of each of the three linear motion actuating mechanisms is distributed at the vertices of an equilateral triangle, and the three linear motion actuating mechanisms are equidistant and parallel. Through the above structural design, this application can quickly adjust the engine thrust direction, reduce the structural complexity, and improve the flight stability.

Description

Technical Field

[0001] This application generally relates to the technical field of aircraft thrust devices, and particularly to aircraft vector thrust devices. Background Art

[0002] In the field of aviation, the vector thrust technology of aircraft can significantly improve their maneuverability and flight performance.

[0003] Currently, most existing aircraft vector thrust devices are applied to large fighter jets. After long-term development and a large number of practical verifications, such devices can better meet the high maneuverability requirements of large fighter jets in complex air combat environments.

[0004] However, for small unmanned aerial vehicles (UAVs), applicable vector thrust devices are extremely scarce. There are many drawbacks in the few existing vector thrust devices applied to small UAVs.

[0005] Their structural design is complex, including a large number of precise and cumbersome components. This not only leads to a significant increase in production costs, limits the large-scale application of small UAVs in cost-sensitive fields, but also significantly increases the overall weight of the aircraft.

[0006] And the increase in weight will further reduce the endurance and flight flexibility of small UAVs.

[0007] In addition, the adjustment mechanisms of these devices are complex, with low stability during actual operation, prone to failures, and unable to provide stable and reliable vector thrust control for small UAVs, seriously affecting the flight safety and mission execution effect of small UAVs.

[0008] Therefore, there is an urgent need to develop a vector thrust device for small UAVs with a simple structure, low cost, and high stability. Summary of the Invention

[0009] To address the problems of the existing vector thrust devices with complex structures, high manufacturing costs, and low stability, this application provides an aircraft vector thrust device, which achieves the purpose of adjusting the engine thrust in multiple directions, with a simple structure and high stability.

[0010] According to one aspect of this application, there is provided an aircraft vector thrust device, which includes: a vector motion platform that can be arranged at the head or tail of the aircraft, and an engine is provided on one side of the vector motion platform away from the aircraft;

[0011] Three linear motion actuating mechanisms are provided between the vector motion platform and the aircraft, and the linear motion actuating mechanisms are universally connected to the vector motion platform; wherein

[0012] One end of each of the three linear motion actuating mechanisms is distributed at the apexes of an equilateral triangle, and the three linear motion actuating mechanisms are arranged equidistantly and parallel to each other.

[0013] In some embodiments, mounting plates are provided at the ends of the three linear motion actuating mechanisms away from the vector motion platform, and one end of each of the three linear motion actuating mechanisms close to the mounting plate is hinged to the mounting plate; and

[0014] The swinging directions of the three linear motion actuating mechanisms all point to the center of the equilateral triangle where the hinge is located;

[0015] A rotational drive mechanism is provided on the side of the mounting plate close to the aircraft, and the rotational drive mechanism is used to drive the mounting plate to rotate about its central axis.

[0016] In some embodiments, the vector motion platform is of an equilateral triangle structure;

[0017] Mounting holes are provided at positions close to each apex of the equilateral triangle structure of the vector motion platform, and the three linear motion actuating mechanisms are respectively installed in the mounting holes.

[0018] In some embodiments, the linear motion actuating mechanism includes:

[0019] A spherical joint bearing, one end of the fixed end of the spherical joint bearing is bolted to the mounting hole, and one end of the movable end of the spherical joint bearing is connected to the fixed end in a universal joint manner;

[0020] It further includes a linear motion actuating mechanism body, one end of the linear motion actuating mechanism body is connected to the movable end of the spherical joint bearing, and the other end is hinged to the mounting plate.

[0021] In some embodiments, the rotational drive mechanism includes:

[0022] A chassis, provided on the side of the mounting plate away from the linear motion actuating mechanism; wherein

[0023] The mounting plate is rotatably connected to the inner wall of the chassis through a rotating shaft;

[0024] A drive motor, installed on the inner wall of the chassis on the side away from the mounting plate;

[0025] A swing rod assembly, provided in the chassis and drivingly connected to the drive motor;

[0026] One end of the swing rod assembly away from the drive motor is provided with a gear set, and the gear set is rotatably connected to the mounting plate.

[0027] In some embodiments, a first pulley is provided on the output shaft of the drive motor, and a second pulley is provided at one end of the swing rod assembly close to the drive motor. One side of the second pulley is fixedly connected to the swing rod assembly, and the first pulley is connected to the second pulley by a belt;

[0028] The swing rod assembly includes:

[0029] A collar sleeved on the outer wall of the rotating shaft; and

[0030] A first connecting rod and a second connecting rod, one ends of the first connecting rod and the second connecting rod are respectively connected to the outer circumferential walls on both sides of the collar, and the other ends of the first connecting rod and the second connecting rod away from the collar are connected to the gear set.

[0031] In some embodiments, the gear set includes:

[0032] A first gear rotatably connected to one side of the first connecting rod close to the mounting plate;

[0033] A second gear meshing with the first gear and rotatably connected to one side of the second connecting rod close to the mounting plate; and

[0034] A third gear sleeved on the outer wall of the rotating shaft and provided between the swing rod assembly and the mounting plate; wherein

[0035] The first gear meshes with the third gear, and the second gear and the third gear are arranged at intervals;

[0036] A driving rod is provided on one side of the first gear close to the mounting plate. One end of the driving rod is fixedly connected to the axis of the first gear, and the other end is rotatably connected to the mounting plate;

[0037] A sleeve is provided at the axis of the third gear. The sleeve is sleeved on the outer wall of the rotating shaft, and the collar and the first pulley are sleeved on the outer wall of the sleeve;

[0038] A plurality of mounting rods are further provided on the outer wall of the sleeve. One ends of the plurality of mounting rods are connected to the sleeve, and the other ends are connected to the inner wall of the chassis. One ends of the plurality of mounting rods diverge with the sleeve as the center, and each mounting rod is respectively provided on the side of the first pulley away from the swing rod assembly.

[0039] In some embodiments, a lubrication assembly is further provided at one end of the swing rod assembly close to the gear set, and the lubrication assembly is provided on the side of the swing rod assembly away from the gear set;

[0040] The lubrication assembly includes:

[0041] The first limiting rod and the second limiting rod, the first limiting rod and the second limiting rod are respectively arranged on one side of the first connecting rod and the second connecting rod away from the gear set; wherein

[0042] An extension rod is provided at one end of the second limiting rod close to the second connecting rod, a mating rod is provided at one end of the extension rod away from the second limiting rod, and the mating rod passes through the second connecting rod and is fixedly connected to the center of the second gear;

[0043] A piston cylinder is provided between the first limiting rod and the second limiting rod, lubricating grease is provided in the piston cylinder, both ends of the piston cylinder are rotatably connected to the first limiting rod and the second limiting rod respectively, a one-way air inlet valve and a one-way grease discharge valve are provided on the cylinder body of the piston cylinder, and the one-way grease discharge valve is connected to each of the linear motion actuating mechanisms through a pipe.

[0044] The embodiments of the present application have the following advantages.

[0045] The vector thrust device is used to adjust the tilting direction of the engine blade, so that the propulsion direction of the blade changes, thereby controlling the maneuver of the fuselage through the change of the propulsion direction. When the vector thrust device works, the linear motion actuating mechanism is controlled to stretch and contract, so that one side of the vector motion platform is pulled and tilted. At this time, the vector motion platform drives the engine to tilt, so that the thrust direction of the blade changes. Whether the engine and the vector motion platform are arranged at the head or the tail of the aircraft, the tilting direction of the engine is the same as the moving direction of the aircraft, so that the thrust or pull force generated by the engine is the same as the required flight direction of the aircraft. At the same time, when controlling the stretching and contraction of multiple linear motion actuating mechanisms, the vector motion platform can be controlled to tilt in various directions, and the adjustment range of the engine thrust direction is wide and the adjustment efficiency is high.

[0046] Other features and advantages of the present invention will be described in the following specification, and, in part, will become apparent from the specification, or will be understood by practicing the present invention. The objectives and other advantages of the present invention can be realized and obtained by the structures specifically pointed out in the written specification and the drawings.

[0047] The technical solutions of the present invention will be further described in detail below through the drawings and embodiments. Description of the Drawings

[0048] The drawings are used to provide a further understanding of the present invention, and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention, and do not constitute a limitation to the present invention. In the drawings:

[0049] Figure 1 The installation schematic diagram of the vector thrust device according to an embodiment of the present application is shown.

[0050] Figure 2Shows a schematic structural diagram of a vector thrust device according to an embodiment of the present application.

[0051] Figure 3 Shows a schematic structural diagram of a rotational drive mechanism according to an embodiment of the present application.

[0052] Figure 4 Shows Figure 3 An enlarged view of area A therein.

[0053] Figure 5 Shows Figure 3 An enlarged view of area B therein.

[0054] Figure 6 Shows a schematic structural diagram of a swing rod assembly according to an embodiment of the present application.

[0055] Reference numerals

[0056] 1 - Vector motion platform; 11 - Mounting hole;

[0057] 2 - Linear motion actuator mechanism; 21 - Linear motion actuator mechanism body; 22 - Ball joint bearing;

[0058] 3 - Engine; 4 - Aircraft; 5 - Mounting plate;

[0059] 6 - Rotational drive mechanism;

[0060] 61 - Chassis; 62 - Drive motor; 621 - First pulley; 622 - Second pulley; 623 - Belt;

[0061] 63 - Swing rod assembly; 631 - Collar; 632 - First connecting rod; 633 - Second connecting rod;

[0062] 64 - Rotating shaft;

[0063] 65 - Gear set; 651 - First gear; 652 - Second gear; 653 - Third gear; 654 - Drive rod; 655 - Sleeve; 656 - Mounting rod;

[0064] 7 - Lubrication assembly; 71 - First limiting rod; 72 - Second limiting rod; 73 - Extension rod; 74 - Fitting rod; 75 - Piston cylinder. Detailed implementation manners

[0065] In order to make the objectives, solutions, and advantages of the technical solutions of the present application clearer, the technical solutions of the embodiments of the present application will be clearly and completely described below with reference to the drawings of the specific embodiments of the present application. Unless otherwise specified, the terms used herein have the ordinary meanings in the art. The same reference numerals in the drawings represent the same components.

[0066] In the description of the present application, it should be noted that unless otherwise clearly specified and defined, the terms "installed", "connected", and "coupled" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0067] As described above, during the flight of a traditional aircraft, complex drive mechanisms need to cooperate with each other to adjust the flight state of the aircraft. There are problems with the complex structure and high manufacturing cost of existing vector thrust devices.

[0068] To at least partially solve one or more of the above problems and other potential problems, an exemplary embodiment of the present application provides an aircraft vector thrust device. The vector thrust device includes: a vector motion platform 1, which can be arranged at the head or tail of the aircraft 4. An engine 3 is provided on the side of the vector motion platform 1 away from the aircraft 4; three linear motion actuating mechanisms 2 are provided between the vector motion platform 1 and the aircraft 4. The linear motion actuating mechanisms 2 are universally connected to the vector motion platform 1; one end of each of the three linear motion actuating mechanisms 2 is distributed at the vertices of an equilateral triangle, and the three linear motion actuating mechanisms 2 are equidistant and parallel to each other.

[0069] In the above embodiment, the vector thrust device is used to adjust the tilt direction of the propeller blades of the engine 3, so that the propulsion direction of the propeller blades changes, and thus the maneuver of the fuselage is controlled by the change of the propulsion direction. When the vector thrust device works, the linear motion actuating mechanisms 2 are controlled to expand and contract, so that one side of the vector motion platform 1 is pulled and tilted. At this time, the vector motion platform 1 drives the engine 3 to tilt, so that the thrust direction of the propeller blades changes. Whether the engine 3 and the vector motion platform 1 are arranged at the head or tail of the aircraft 4, the tilt direction of the engine 3 is the same as the motion direction of the aircraft 4, so that the thrust or pull generated by the engine 3 is the same as the required flight direction of the aircraft 4. At the same time, when controlling the expansion and contraction of multiple linear motion actuating mechanisms 2, the vector motion platform 1 can be controlled to tilt in various directions, and the adjustment range of the engine 3 thrust direction is wide and the adjustment efficiency is high.

[0070] Please refer to Figures 1 - 6, in some embodiments, a mounting plate 5 is provided at one end of the three linear motion actuating mechanisms 2 away from the vector motion platform 1, and one end of each of the three linear motion actuating mechanisms 2 close to the mounting plate 5 is hinged to the mounting plate 5; and the swinging directions of the three linear motion actuating mechanisms 2 all point to the center of the equilateral triangle where the hinge is located; a rotation driving mechanism 6 is provided on one side of the mounting plate 5 close to the aircraft 4, and the rotation driving mechanism 6 is used to drive the mounting plate 5 to rotate around its central axis.

[0071] In the above embodiment, the mounting plate 5 is connected to the rotation driving mechanism 6, and the rotation driving mechanism 6 can drive the mounting plate 5 to rotate. When one or two of the three linear motion actuating mechanisms 2 fail, one of the linear motion actuating mechanisms 2 is driven to extend and retract, so that one side of the vector motion platform 1 close to this linear motion actuating mechanism 2 moves away from or close to the mounting plate 5, causing the engine 3 to tilt to this side. When the tilt direction of the engine 3 needs to be adjusted, first, the rotation driving mechanism 6 is used to drive the mounting plate 5 to drive a linearly movable and normally extendable linear motion actuating mechanism 2 to rotate to one side in the required rotation direction of the fuselage, and then this linear motion actuating mechanism 2 is extended and retracted to tilt the engine 3 to the rotation direction of the fuselage.

[0072] Please refer to Figures 1 - 6 , in some embodiments, the vector motion platform 1 has an equilateral triangle structure; mounting holes 11 are provided near each vertex of the equilateral triangle structure of the vector motion platform 1, and the three linear motion actuating mechanisms 2 are respectively installed in the mounting holes 11.

[0073] In the above embodiment, the vector motion platform 1 has an equilateral triangle structure, and the three linear motion actuating mechanisms 2 are respectively installed at the vertices of the equilateral triangle structure. When one or more of the linear motion actuating mechanisms 2 extend and retract, the vertices of the equilateral triangle structure are pulled to tilt, and the engine 3 is installed at the center of the equilateral triangle.

[0074] Please refer to Figures 1 - 6 , in some embodiments, the linear motion actuating mechanism 2 includes: a spherical joint bearing 22, one end of the fixed end of the spherical joint bearing 22 is bolted to the mounting hole 11, and one end of the movable end of the spherical joint bearing 22 is connected to the fixed end in a universal manner; it further includes a linear motion actuating mechanism 2 body, one end of the linear motion actuating mechanism 2 body is connected to the movable end of the spherical joint bearing 22, and the other end is hinged to the mounting plate 5.

[0075] In the above embodiment, the spherical joint bearing 22 is used for the universal connection between the linear motion actuating mechanism 2 and the vector motion platform 1. The linear motion actuating mechanism body 21 can optionally be an electric telescopic rod, a linear motor platform, a hydraulic cylinder, etc.

[0076] Please refer to Figures 1 - 6, in some embodiments, the rotational drive mechanism 6 includes: a chassis 61 disposed on a side of the mounting plate 5 away from the linear motion actuator 2; wherein the mounting plate 5 is rotatably connected to the inner wall of the chassis 61 through a rotating shaft 64; a drive motor 62 mounted on the inner wall of the chassis 61 on a side away from the mounting plate 5; a swing rod assembly 63 disposed inside the chassis 61 and drivingly connected to the drive motor 62; a gear set 65 is provided at an end of the swing rod assembly 63 away from the drive motor 62, and the gear set 65 is rotatably connected to the mounting plate 5.

[0077] In the above embodiments, the mounting plate 5 is rotatably connected to the inner wall of the chassis 61 through the rotating shaft 64. When the mounting plate 5 is driven to rotate, the mounting plate 5 rotates around the rotating shaft 64 and drives the linear motion actuator 2 and the vector motion platform 1 to rotate. The drive motor 62 drives the swing rod assembly 63, causing the swing rod assembly 63 to rotate around the rotating shaft 64. The gear set 65 at the end of the swing rod assembly 63 is rotatably connected to the mounting plate 5. When the swing rod assembly 63 rotates around the rotating shaft 64, it can drive the end to drive the mounting plate 5 to rotate around the rotating shaft 64.

[0078] Please refer to Figures 1 - 6 , in some embodiments, a first pulley 621 is provided on the output shaft of the drive motor 62, a second pulley 622 is provided at an end of the swing rod assembly 63 close to the drive motor 62, one side of the second pulley 622 is fixedly connected to the swing rod assembly 63, and the first pulley 621 and the second pulley 622 are connected by a belt 623; the swing rod assembly 63 includes: a collar 631 sleeved on the outer wall of the rotating shaft 64; and a first connecting rod 632 and a second connecting rod 633, one ends of the first connecting rod 632 and the second connecting rod 633 are respectively connected to the outer circumferential walls on both sides of the collar 631, and the ends of the first connecting rod 632 and the second connecting rod 633 away from the collar 631 are connected to the gear set 65.

[0079] In the above embodiments, when the output shaft of the drive motor 62 rotates, it drives the first pulley 621 to rotate. Since the first pulley 621 and the second pulley 622 are connected by the belt 623, the second pulley 622 is driven to rotate. When the second pulley 622 makes a circular motion on the outer circumferential wall of the rotating shaft 64, the second pulley 622 drives the collar 631 fixedly connected to it to rotate. The first connecting rod 632 and the second connecting rod 633 on both sides of the collar 631 rotate around the collar 631 at the same time, causing the gear set 65 at the ends of the first connecting rod 632 and the second connecting rod 633 to make a circular motion around the collar 631. Since the gear set 65 is rotatably disposed on the mounting plate 5, when the gear set 65 is driven to rotate around the collar 631, the mounting plate 5 will also be driven to rotate around the collar 631. The mounting plate 5 and the gear set 65 can be regarded as eccentrically connected.

[0080] Please refer to Figures 1 - 6 In some embodiments, the gear set 65 includes: a first gear 651 rotatably connected to one side of the first link 632 close to the mounting plate 5; a second gear 652 meshing with the first gear 651 and rotatably connected to one side of the second link 633 close to the mounting plate 5; and a third gear 653 sleeved on the outer wall of the rotating shaft 64 and disposed between the swing rod assembly 63 and the mounting plate 5. The first gear 651 meshes with the third gear 653, and the second gear 652 is spaced from the third gear 653. A driving rod 654 is provided on one side of the first gear 651 close to the mounting plate 5. One end of the driving rod 654 is fixedly connected to the axis of the first gear 651, and the other end is rotatably connected to the mounting plate 5. A sleeve 655 is provided at the axis of the third gear 653. The sleeve 655 is sleeved on the outer wall of the rotating shaft 64. The collar 631 and the first pulley 621 are sleeved on the outer wall of the sleeve 655. A plurality of mounting rods 656 are further provided on the outer wall of the sleeve 655. One end of each of the plurality of mounting rods 656 is connected to the sleeve 655, and the other end is connected to the inner wall of the chassis 61. One ends of the plurality of mounting rods 656 are divergently arranged with the sleeve 655 as the center, and each of the mounting rods 656 is disposed on one side of the first pulley 621 away from the swing rod assembly 63.

[0081] In the above embodiments, when the first link 632 and the second link 633 rotate around the collar 631, the third gear 653 is fixed to the inner wall of the chassis 61. The first link 632 drives the first gear 651 to perform a circular motion around the axis of the third gear 653. At this time, the first gear 651 and the third gear 653 are meshed. When the first gear 651 performs a circular motion, it will rotate on its own axis. Since the relative position between the first gear 651 and the chassis 61 changes, the mounting plate 5 connected to the first gear 651 is driven by the driving rod 654 on the surface of the third gear 653, so that the driving rod 654 drives the mounting plate 5 to rotate around the rotating shaft 64. At this time, the purpose of driving the linear motion actuator 2 to rotate around the rotating shaft 64 can be achieved. The plurality of mounting rods 656 are used to fix the sleeve 655 fixedly connected to the third gear 653 to the inner wall of the chassis 61, so that when the first gear 651 and the second gear 652 rotate around the third gear 653, the third gear 653 remains stationary.

[0082] Please refer to Figures 1 - 6, in some embodiments, a lubrication assembly 7 is further provided at one end of the swing rod assembly 63 close to the gear set 65, and the lubrication assembly 7 is arranged on the side of the swing rod assembly 63 away from the gear set 65; the lubrication assembly 7 includes: a first limiting rod 71 and a second limiting rod 72, and the first limiting rod 71 and the second limiting rod 72 are respectively arranged on the sides of the first connecting rod 632 and the second connecting rod 633 away from the gear set 65; wherein an extension rod 73 is provided at one end of the second limiting rod 72 close to the second connecting rod 633, and a mating rod 74 is provided at one end of the extension rod 73 away from the second limiting rod 72, and the mating rod 74 penetrates through the second connecting rod 633 and is fixedly connected to the axis of the second gear 652; a piston cylinder 75 is arranged between the first limiting rod 71 and the second limiting rod 72, lubricating grease is arranged in the piston cylinder 75, two ends of the piston cylinder 75 are respectively rotatably connected to the first limiting rod 71 and the second limiting rod 72, and a one-way air inlet valve and a one-way grease discharge valve are arranged on the cylinder body of the piston cylinder 75, and the one-way grease discharge valve is connected to each linear motion actuator 2 through a pipe.

[0083] In the above embodiments, when the fuselage is flying normally, only three linear motion actuators 2 need to be contracted to realize the vector adjustment of the engine 3. If one or two of the linear motion actuators 2 fail, the rotation drive mechanism 6 needs to be cooperated to realize the vector adjustment of the engine 3. When the rotation drive mechanism 6 works, it can drive the lubrication assembly 7 to lubricate the linear motion actuators 2, so as to improve the problem that the linear motion actuators 2 cannot work normally due to lubrication reasons. It can also intermittently lubricate the linear motion actuators 2 that have worked for a period of time by starting the rotation drive mechanism 6 to extend the service life of the linear motion actuators 2. When the lubrication assembly 7 works, since the first gear 651 meshes with the second gear 652, when the first gear 651 makes a circular motion around the second gear 652, the first gear 651 rotates itself to drive the second gear 652 to rotate itself. Since an extension rod 73 is further provided on the side of the second gear 652 passing through the second connecting rod 633, and one end of the extension rod 73 is connected to the second gear 652 through a mating rod 74, when the second gear 652 rotates, it can drive the extension rod 73 to make a circular motion around the mating rod 74 through the mating rod 74, so that the distance between the second limiting rod 72 at one end of the extension rod 73 and the first limiting rod 71 intermittently increases and decreases. When a piston cylinder 75 is arranged between the first limiting rod 71 and the second limiting rod 72, the distance between the installation end and the telescopic end of the piston cylinder 75 changes intermittently. When the piston rod of the piston cylinder 75 is pulled by the second limiting rod 72, the one-way air inlet valve opens and the one-way grease discharge valve closes. At this time, air is filled into the piston cylinder 75. When the piston cylinder 75 is compressed, the one-way air inlet valve closes and the one-way grease discharge valve opens. The one-way grease discharge valve is connected to the grease filling port of each linear motion actuator 2 through a hose, so that the lubricating grease in the piston cylinder 75 enters the linear motion actuator 2 to lubricate its moving parts.

[0084] The embodiments of the present application have been described above. The above description is exemplary and not exhaustive, and is also not limited to the disclosed embodiments. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments.

[0085] The selection of the terms used herein is intended to best explain the principles of the embodiments, the practical application, or the improvement of the technology in the market, or to enable other ordinary skilled persons in the art to understand the embodiments disclosed herein.

[0086] The above are only optional embodiments of the present application and are not used to limit the present application. For those skilled in the art, various changes and modifications can be made to the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included within the protection scope of the present application.

Claims

1. An aircraft vector thrust device, characterized in that: include: A vector motion platform (1), the vector motion platform (1) being arranged at the head or tail of the aircraft (4), and an engine (3) being arranged on a side of the vector motion platform (1) away from the aircraft (4); There are three linear motion actuating mechanisms (2) disposed between the vector motion platform (1) and the aircraft (4), and the linear motion actuating mechanisms (2) and the vector motion platform (1) are universally connected; One end of each of the three linear motion actuating mechanisms (2) is distributed at each vertex of an equilateral triangle, and the three linear motion actuating mechanisms (2) are equidistant and arranged in parallel; A mounting plate (5) is provided at one end of the three linear motion actuating mechanisms (2) away from the vector motion platform (1), and one end of the three linear motion actuating mechanisms (2) close to the mounting plate (5) is hinged to the mounting plate (5); and the swinging directions of the three linear motion actuating mechanisms (2) are all directed to the center of the equilateral triangle at the hinged position; A rotation drive mechanism (6) is provided on a side of the mounting plate (5) close to the aircraft (4), wherein the rotation drive mechanism (6) is used to drive the mounting plate (5) to rotate around its central axis; When one or two of the three linear motion actuators (2) fail and the tilt direction of the engine (3) needs to be adjusted, the rotating drive mechanism (6) drives the mounting plate (5) to drive a normally retractable linear motion actuator (2) to rotate to the side of the required rotation direction of the fuselage, and then the linear motion actuator (2) is retracted to achieve vector adjustment of the engine (3).

2. The aircraft vector thrust device according to claim 1, characterized in that: The vector motion platform (1) is an equilateral triangle structure; The equilateral triangle structure of the vector motion platform (1) is provided with mounting holes (11) near each vertex, and the three linear motion actuating mechanisms (2) are respectively mounted in the mounting holes (11).

3. The aircraft vector thrust device according to claim 2, characterized in that: The linear motion actuating mechanism (2) comprises: A ball joint bearing (22), wherein one end of the fixed end of the ball joint bearing (22) is bolted to the mounting hole (11), and one end of the movable end of the ball joint bearing (22) is universally connected to the fixed end; It also comprises a linear motion actuating mechanism body (21), one end of the linear motion actuating mechanism body (21) being connected to the movable end of the ball joint bearing (22), and the other end being hinged to the mounting plate (5).

4. The aircraft vector thrust device according to claim 3, characterized in that: The rotation drive mechanism (6) comprises: The chassis (61) is arranged on a side of the mounting plate (5) away from the linear motion actuating mechanism (2); wherein The mounting plate (5) is rotatably connected to the inner wall of the chassis (61) via a rotating shaft (64); A driving motor (62) is mounted on an inner wall of the chassis (61) away from the mounting plate (5); A swing arm assembly (63) is disposed in the chassis (61) and is drivingly connected to the driving motor (62); A gear set (65) is provided at one end of the swing arm assembly (63) away from the drive motor (62), and the gear set (65) is rotatably connected to the mounting plate (5).

5. The aircraft vector thrust device according to claim 4, characterized in that: The output shaft of the driving motor (62) is provided with a first pulley (621); an end of the swing arm assembly (63) close to the driving motor (62) is provided with a second pulley (622); one side of the second pulley (622) is fixedly connected to the swing arm assembly (63); and the first pulley (621) and the second pulley (622) are connected via a belt (623); The rocker assembly (63) comprises: A sleeve (631) sleeved on the outer wall of the rotating shaft (64); and A first connecting rod (632) and a second connecting rod (633), wherein one end of the first connecting rod (632) and one end of the second connecting rod (633) are respectively connected to the circumferential outer walls on both sides of the collar (631), and one end of the first connecting rod (632) and one end of the second connecting rod (633) away from the collar (631) are connected to the gear set (65).

6. The aircraft vector thrust device according to claim 5, characterized in that: The gear set (65) comprises: A first gear (651) rotatably connected to a first connecting rod (632) close to a side of the mounting plate (5); A second gear (652) meshes with the first gear (651) and is rotatably connected to a side of the second connecting rod (633) close to the mounting plate (5); and The third gear (653) is sleeved on the circumferential outer wall of the rotating shaft (64) and is disposed between the swing arm assembly (63) and the mounting plate (5); wherein The first gear (651) is meshed with the third gear (653), and the second gear (652) is spaced apart from the third gear (653); A driving rod (654) is provided on a surface of the first gear (651) close to the mounting plate (5); one end of the driving rod (654) is fixedly connected to the axis of the first gear (651), and the other end is rotatably connected to the mounting plate (5); A sleeve (655) is provided at the axis of the third gear (653), the sleeve (655) is sleeved on the circumferential outer wall of the rotating shaft (64), and the sleeve ring (631) and the first pulley (621) are sleeved on the circumferential outer wall of the sleeve (655); The circumferential outer wall of the sleeve (655) is further provided with a plurality of mounting rods (656), one end of each of the mounting rods (656) being connected to the sleeve (655) and the other end being connected to the inner wall of the chassis (61), one end of each of the mounting rods (656) being arranged divergently with the sleeve (655) as the center, and each of the mounting rods (656) being arranged on a side of the first pulley (621) away from the swing arm assembly (63).

7. The aircraft vector thrust device according to claim 6, characterized in that: A lubrication assembly (7) is further provided at one end of the rocker assembly (63) close to the gear set (65); the lubrication assembly (7) is provided on a side of the rocker assembly (63) away from the gear set (65); The lubrication assembly (7) comprises: A first limiting rod (71) and a second limiting rod (72), wherein the first limiting rod (71) and the second limiting rod (72) are respectively arranged on a side of the first connecting rod (632) and the second connecting rod (633) away from the gear set (65); wherein An extension rod (73) is provided at one end of the second limiting rod (72) close to the second connecting rod (633), and a matching rod (74) is provided at one end of the extension rod (73) away from the second limiting rod (72); the matching rod (74) passes through the second connecting rod (633) and is fixedly connected to the axis of the second gear (652); A piston cylinder (75) is provided between the first limiting rod (71) and the second limiting rod (72), and grease is provided in the piston cylinder (75). Two ends of the piston cylinder (75) are rotatably connected to the first limiting rod (71) and the second limiting rod (72), respectively. A one-way air intake valve and a one-way grease discharge valve are provided on the cylinder body of the piston cylinder (75), and the one-way grease discharge valve is connected to the pipe of each linear motion actuating mechanism (2).

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