Vector thrust device of aircraft

Abstract

The invention relates to the technical field of aircraft thrust devices, in particular to an aircraft vector thrust device which comprises a vector motion platform which can be arranged at the head or the tail of an aircraft, and an engine is arranged on the face, away from the aircraft, of the vector motion platform; the three linear motion actuating mechanisms are arranged between the vector motion platform and the aircraft, and the linear motion actuating mechanisms are universally connected with the vector motion platform; wherein one ends of the three linear motion actuating mechanisms are distributed at the vertex angles of an equilateral triangle, the three linear motion actuating mechanisms are arranged in parallel at equal intervals, and through the structural design, the thrust direction of the engine can be rapidly adjusted, the structural complexity is reduced, and the flight stability is improved.

Description

Technical Field

[0001] The present application relates generally to the technical field of aircraft thrust devices, and in particular to aircraft vector thrust devices. Background Art

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

[0003] At present, the existing aircraft vector thrust devices are mostly used in large fighters. After long-term development and a lot of practical verification, such devices can better meet the high maneuverability requirements of large fighters in complex air combat environments.

[0004] However, suitable vector thrust devices for small UAVs are extremely scarce, and the few existing vector thrust devices used for small UAVs have many disadvantages.

[0005] Its structural design is complex and contains a large number of precise and cumbersome parts, which not only leads to a significant increase in production costs, limiting the large-scale application of small drones in cost-sensitive fields, but also significantly increases the overall weight of the aircraft.

[0006] The increase in weight will further reduce the endurance and flight maneuverability of small drones.

[0007] In addition, the adjustment mechanisms of these devices are complex, with low stability during actual operation and prone to failure. They cannot provide stable and reliable vector thrust control for small UAVs, which seriously affects the flight safety and mission execution of small UAVs.

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

[0009] In order to solve the problems of complex structure, high manufacturing cost and low stability of existing vector thrust devices, the present application provides an aircraft vector thrust device, which achieves the purpose of adjusting engine thrust in multiple directions, has a simple structure and high stability.

[0010] According to one aspect of the present application, there is provided an aircraft vector thrust device, the vector thrust device comprising: a vector motion platform, the vector motion platform may be arranged at the head or tail of the aircraft, an engine is arranged on a side of the vector motion platform away from the aircraft; There are three linear motion actuators, which are arranged between the vector motion platform and the aircraft. The linear motion actuators are universally connected to the vector motion platform. One end of the three linear motion actuating mechanisms is distributed at each vertex of an equilateral triangle, and the three linear motion actuating mechanisms are equidistant and parallel.

[0011] In some embodiments, a mounting plate is provided at one end of the three linear motion actuating mechanisms away from the vector motion platform, and one end of the three linear motion actuating mechanisms close to the mounting plate is hinged to the mounting plate; and The swing directions of the three linear motion actuating mechanisms all point to the center of the equilateral triangle where the hinge is located; A rotation drive mechanism is provided on a side of the mounting plate close to the aircraft, and the rotation drive mechanism is used to drive the mounting plate to rotate around its central axis.

[0012] In some embodiments, the vector motion platform is an equilateral triangle structure; The equilateral triangle structure of the vector motion platform is provided with mounting holes near each vertex, and the three linear motion actuating mechanisms are respectively installed in the mounting holes. In some embodiments, the linear motion actuating mechanism comprises: A ball joint bearing, wherein one end of the fixed end of the ball joint bearing is bolted to the mounting hole, and one end of the movable end of the ball joint bearing is universally connected to the fixed end; It also includes a linear motion actuating mechanism body, one end of which is connected to the movable end of the ball joint bearing, and the other end is hinged to the mounting plate.

[0013] In some embodiments, the rotation drive mechanism comprises: The chassis is arranged on the side of the mounting plate away from the linear motion actuating mechanism; wherein The mounting plate is rotatably connected to the inner wall of the chassis via a rotating shaft; A driving motor is mounted on an inner wall of the chassis away from the mounting plate; A swing arm assembly is disposed in the chassis and is drivingly connected to the driving motor; A gear set is provided at one end of the rocker assembly away from the driving motor, and the gear set is rotatably connected to the mounting plate.

[0014] In some embodiments, the output shaft of the driving motor is provided with a first pulley, and the end of the swing arm assembly close to the driving motor is provided with a second pulley, one side of the second pulley is fixedly connected to the swing arm assembly, and the first pulley is connected to the second pulley by a belt; The swing rod assembly comprises: A collar, sleeved on the outer wall of the rotating shaft; and A first connecting rod and a second connecting rod, wherein one end of the first connecting rod and the second connecting rod are respectively connected to the circumferential outer walls on both sides of the collar, and one end of the first connecting rod and the second connecting rod away from the collar is connected to the gear set.

[0015] In some embodiments, the gear set includes: A first gear, rotatably connected to a first connecting rod close to a side of the mounting plate; A second gear meshing with the first gear and rotatably connected to a second connecting rod close to the mounting plate; and The third gear is sleeved on the circumferential outer wall of the rotating shaft and is arranged between the swing arm assembly and the mounting plate; wherein The first gear is meshed with the third gear, and the second gear is spaced apart from the third gear; 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; A sleeve is provided at the axis of the third gear, the sleeve is sleeved on the circumferential outer wall of the rotating shaft, and the sleeve ring and the first pulley are sleeved on the circumferential outer wall of the sleeve; The circumferential outer wall of the sleeve is also provided with a plurality of mounting rods, one end of each of the mounting rods is connected to the sleeve, and the other end is connected to the inner wall of the chassis, one end of each of the mounting rods is divergently arranged with the sleeve as the center, and each of the mounting rods is respectively arranged on a side of the first pulley away from the rocker assembly.

[0016] In some embodiments, a lubrication assembly is further provided at one end of the swing arm assembly close to the gear set, and the lubrication assembly is provided at a side of the swing arm assembly away from the gear set; The lubrication assembly comprises: A first limiting rod and a second limiting rod, wherein the first limiting rod and the second limiting rod are respectively arranged on a side of the first connecting rod and the second connecting rod away from the gear set; wherein An extension rod is provided at one end of the second limiting rod close to the second connecting rod, and a matching rod is provided at one end of the extension rod away from the second limiting rod, and the matching rod passes through the second connecting rod and is fixedly connected to the axis of the second gear; A piston cylinder is provided between the first limiting rod and the second limiting rod, and grease is provided in the piston cylinder. The two ends of the piston cylinder are rotatably connected to the first limiting rod and the second limiting rod respectively. The cylinder body of the piston cylinder is provided with a one-way air intake valve and a one-way grease discharge valve, and the one-way grease discharge valve is connected to each of the linear motion actuating mechanism pipes.

[0017] The embodiments of the present application have the following advantages.

[0018] The vector thrust device is used to adjust the tilt direction of the engine propeller, so that the propulsion direction of the propeller changes, thereby controlling the fuselage to maneuver by changing the propulsion direction. When the vector thrust device is working, the linear motion actuator is controlled to extend and retract, 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 propeller changes. Regardless of whether the engine and the vector motion platform are located at the head or tail of the aircraft, the tilt direction of the engine is the same as the movement direction of the aircraft, so that the thrust or pulling force generated by the engine is the same as the flight direction required by the aircraft. When multiple linear motion actuators are controlled to extend and retract at the same time, the vector motion platform can be controlled to tilt in all directions. The engine thrust direction has a wide adjustment range and high adjustment efficiency.

[0019] Other features and advantages of the present invention will be described in the following description, and partly become apparent from the description, or understood by practicing the present invention. The purpose and other advantages of the present invention can be realized and obtained by the structures particularly pointed out in the written description and the accompanying drawings.

[0020] The technical solution of the present invention is further described in detail below through the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The accompanying 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 of the present invention. In the accompanying drawings: Figure 1 A schematic diagram of the installation of a vector thrust device according to an embodiment of the present application is shown.

[0022] Figure 2 A schematic structural diagram of a vector thrust device according to an embodiment of the present application is shown.

[0023] Figure 3 A schematic diagram of the structure of a rotation drive mechanism according to an embodiment of the present application is shown.

[0024] Figure 4 Show Figure 3 Magnified view of area A.

[0025] Figure 5 Show Figure 3 Magnified view of area B.

[0026] Figure 6 A schematic structural diagram of a rocker arm assembly according to an embodiment of the present application is shown.

[0027] Reference numerals 1- vector motion platform; 11- mounting hole; 2- linear motion actuator; 21- linear motion actuator body; 22- ball joint bearing; 3-engine; 4-aircraft; 5-mounting plate; 6-Rotation drive mechanism; 61-chassis; 62-driving motor; 621-first pulley; 622-second pulley; 623-belt; 63-swing rod assembly; 631-ring; 632-first connecting rod; 633-second connecting rod; 64-rotating shaft; 65-gear set; 651-first gear; 652-second gear; 653-third gear; 654-driving rod; 655-sleeve; 656-mounting rod; 7-lubrication assembly; 71-first limiting rod; 72-second limiting rod; 73-extension rod; 74-matching rod; 75-piston cylinder. DETAILED DESCRIPTION

[0028] In order to make the purpose, scheme and advantages of the technical solution of the present application clearer, the technical solution of the embodiment of the present application will be clearly and completely described in conjunction with the drawings of the specific embodiments of the present application. Unless otherwise specified, the terms used herein have the usual meanings in the art. The same reference numerals in the drawings represent the same components.

[0029] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" 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 a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0030] As described above, in the traditional flight process of an aircraft, complex driving mechanisms need to cooperate with each other to adjust the flight state of the aircraft. The existing vector thrust device has the problem of complex structure and high manufacturing cost.

[0031] In order to at least partially solve one or more of the above-mentioned problems and other potential problems, an example embodiment of the present application provides an aircraft vector thrust device, which includes: a vector motion platform 1, which can be arranged at the head or tail of an aircraft 4, and 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, which are arranged between the vector motion platform 1 and the aircraft 4, and the linear motion actuating mechanisms 2 are universally connected to the vector motion platform 1; wherein one end 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 parallel.

[0032] In the above embodiment, the vector thrust device is used to adjust the tilt direction of the propeller of the engine 3, so that the propulsion direction of the propeller changes, thereby controlling the fuselage to maneuver by changing the propulsion direction. When the vector thrust device is working, the linear motion actuator 2 is controlled to extend and retract, 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 changes. Regardless of whether the engine 3 and the vector motion platform 1 are located at the head or tail of the aircraft 4, the tilt direction of the engine 3 is the same as the movement direction of the aircraft 4, so that the thrust or pulling force generated by the engine 3 is the same as the flight direction required by the aircraft 4. When multiple linear motion actuators 2 are controlled to extend and retract at the same time, the vector motion platform 1 can be controlled to tilt in all directions. The thrust direction of the engine 3 has a wide adjustment range and high adjustment efficiency.

[0033] See also Figure 1-Figure 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 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 drive mechanism 6 is provided on the side of the mounting plate 5 close to the aircraft 4, and the rotation drive mechanism 6 is used to drive the mounting plate 5 to rotate around its central axis.

[0034] In the above embodiment, the mounting plate 5 is connected to the rotation drive mechanism 6, and the rotation drive mechanism 6 can drive the mounting plate 5 to rotate. When one or two of the three linear motion actuator mechanisms 2 fail, one of the linear motion actuator mechanisms 2 is driven to extend or retract, so that the side of the vector motion platform 1 close to the linear motion actuator mechanism 2 moves away from or close to the mounting plate 5, so that the engine 3 tilts to that side. When the tilt direction of the engine 3 needs to be adjusted, the mounting plate 5 is first driven by the rotation drive mechanism 6 to drive a normally retractable linear motion actuator mechanism 2 to rotate to the side of the required rotation direction of the fuselage, and then the linear motion actuator mechanism 2 is extended or retracted, so that the engine 3 tilts to the rotation direction of the fuselage.

[0035] See also Figure 1-Figure 6 In some embodiments, 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 actuator mechanisms 2 are respectively installed in the mounting holes 11. In the above embodiment, the vector motion platform 1 is an equilateral triangle structure, and three linear motion actuators 2 are respectively installed at the vertices of the equilateral triangle structure, so that when one or more of the linear motion actuators 2 are extended or retracted, the vertices of the equilateral triangle structure are pulled to tilt, and the engine 3 is installed at the center of the equilateral triangle.

[0036] See also Figure 1-Figure 6 In some embodiments, the linear motion actuating mechanism 2 includes: a ball joint bearing 22, 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; and also 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 ball joint bearing 22, and the other end is hinged to the mounting plate 5.

[0037] In the above embodiment, the ball joint bearing 22 is used for universal connection between the linear motion actuator 2 and the vector motion platform 1, and the linear motion actuator body 21 can optionally include an electric telescopic rod, a linear motor platform, a hydraulic cylinder, etc.

[0038] See also Figure 1-Figure 6 In some embodiments, the rotation drive mechanism 6 includes: a chassis 61, which is arranged on the side of the mounting plate 5 away from the linear motion actuator mechanism 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, which is installed on the inner wall of the chassis 61 away from the mounting plate 5; a rocker arm assembly 63, which is arranged in the chassis 61 and is drivingly connected to the drive motor 62; a gear set 65 is provided at one end of the rocker arm assembly 63 away from the drive motor 62, and the gear set 65 is rotatably connected to the mounting plate 5.

[0039] In the above embodiment, the mounting plate 5 is rotatably connected to the inner wall of the chassis 61 through the rotating shaft 64, so that 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, and the driving motor 62 drives the connected rocker assembly 63 to rotate around the rotating shaft 64. The gear set 65 at the end of the rocker assembly 63 is rotatably connected to the mounting plate 5, so that when the rocker assembly 63 rotates around the rotating shaft 64, it can drive the end driving mounting plate 5 to rotate around the rotating shaft 64.

[0040] See also Figure 1-Figure 6In some embodiments, the output shaft of the driving motor 62 is provided with a first pulley 621, and the end of the rocker 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 rocker assembly 63, and the first pulley 621 and the second pulley 622 are connected by a belt 623; the rocker assembly 63 includes: a ring 631, which is sleeved on the outer wall of the rotating shaft 64; and a first connecting rod 632 and a second connecting rod 633, one end of the first connecting rod 632 and the second connecting rod 633 are respectively connected to the circumferential outer walls on both sides of the ring 631, and the first connecting rod 632 and the second connecting rod 633 are connected to the gear set 65 at one end away from the ring 631.

[0041] In the above embodiment, when the output shaft of the driving motor 62 rotates, the first pulley 621 is driven 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 circumferential outer wall of the rotating shaft 64, the second pulley 622 drives the ring 631 fixedly connected thereto to rotate, and the first connecting rod 632 and the second connecting rod 633 on both sides of the ring 631 rotate around the ring 631 at the same time, so that the gear set 65 at the end of the first connecting rod 632 and the second connecting rod 633 makes a circular motion around the ring 631. Since the gear set 65 is rotatably arranged on the mounting plate 5, when the gear set 65 is driven to rotate around the ring 631, the mounting plate 5 is also driven to rotate around the ring 631. The mounting plate 5 and the gear set 65 can be regarded as eccentrically connected.

[0042] See also Figure 1-Figure 6In some embodiments, the gear set 65 includes: a first gear 651, which is rotatably connected to the first connecting rod 632 on a side close to the mounting plate 5; a second gear 652, which is meshed with the first gear 651 and is rotatably connected to the second connecting rod 633 on a side close to the mounting plate 5; and a third gear 653, which is sleeved on the circumferential outer wall of the rotating shaft 64 and is arranged between the rocker 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 from the third gear 653; a driving rod 654 is provided on a side of the first gear 651 close to the mounting plate 5, and one of the driving rods 654 One end 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, and the sleeve 655 is sleeved on the circumferential outer wall of the rotating shaft 64, and the 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 also provided with a plurality of mounting rods 656, one end 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 end of the plurality of mounting rods 656 is divergently arranged with the sleeve 655 as the center, and each of the mounting rods 656 is respectively arranged on the side of the first pulley 621 away from the rocker assembly 63.

[0043] In the above embodiment, when the first connecting rod 632 and the second connecting rod 633 rotate around the collar 631, the third gear 653 is fixed to the inner wall of the chassis 61, and the first connecting rod 632 drives the first gear 651 to make 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, and the first gear 651 will rotate when making a circular motion. Since the relative position of 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, and 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 is fixed.

[0044] See also Figure 1-Figure 6In some embodiments, a lubrication assembly 7 is further provided at one end of the swing arm assembly 63 close to the gear set 65, and the lubrication assembly 7 is arranged on the side of the swing arm assembly 63 away from the gear set 65; the lubrication assembly 7 comprises: 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 side of the first connecting rod 632 and the second connecting rod 633 away from the gear set 65; wherein the second limiting rod 72 is provided with an extension rod 73 at one end close to the second connecting rod 633, and the extension rod 7 A matching rod 74 is provided at one end away from the second limiting rod 72, and 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. The two ends of the piston cylinder 75 are rotatably connected to the first limiting rod 71 and the second limiting rod 72 respectively, and the cylinder body of the piston cylinder 75 is provided with a one-way air intake valve and a one-way grease discharge valve, and the one-way grease discharge valve is connected to each of the linear motion actuating mechanisms 2.

[0045] In the above embodiment, when the fuselage is flying normally, the vector adjustment of the engine 3 can be achieved by contracting the three linear motion actuators 2. If one or two of the linear motion actuators 2 fail, it is necessary to cooperate with the rotary drive mechanism 6 to achieve the vector adjustment of the engine 3. When the rotary drive mechanism 6 is working, the lubrication component 7 can be driven to lubricate the linear motion actuator 2 to improve the problem that the linear motion actuator 2 cannot work normally due to lubrication reasons. The linear motion actuator 2 can also be lubricated intermittently by starting the rotary drive mechanism 6 after working for a period of time to extend the service life of the linear motion actuator 2. When the lubrication component 7 is working, since the first gear 651 is meshed with the second gear 652, when the first gear 651 makes a circular motion around the second gear 652, the first gear 651 rotates to drive the second gear 652 to rotate. Since the second gear 652 passes through the second connecting rod 63 3 is also provided with an extension rod 73, and one end of the extension rod 73 is connected to the second gear 652 through a matching rod 74, so that when the second gear 652 rotates, the extension rod 73 can be driven by the matching rod 74 to make a circular motion around the matching 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 is intermittently increased and reduced. When a piston cylinder 75 is provided between the first limiting rod 71 and the second limiting rod 72, the distance between the mounting 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 intake valve opens and the one-way grease discharge valve closes. At this time, air is filled in the piston cylinder 75. When the piston cylinder 75 is compressed, the one-way air intake 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 grease in the piston cylinder 75 enters the linear motion actuator 2 to lubricate its moving parts.

[0046] The embodiments of the present application have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

[0047] The terms used in this document are selected to best explain the principles of the embodiments, practical applications or technical improvements in the marketplace, or to enable other ordinary technicians in this technical field to understand the embodiments disclosed herein.

[0048] The above are only optional embodiments of the present application and are not intended to limit the present application. For those skilled in the art, the present application may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. An aircraft vector thrust device, characterized in that: include: A vector motion platform (1), wherein the vector motion platform (1) can be arranged at the head or tail of the aircraft (4), and an engine (3) is 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; in 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 arranged equidistantly and in parallel.

2. The aircraft vector thrust device according to claim 1, characterized in that: An end of the three linear motion actuating mechanisms (2) away from the vector motion platform (1) is provided with a mounting plate (5), and an end of the three linear motion actuating mechanisms (2) close to the mounting plate (5) is hinged to the mounting plate (5); and The swing 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 drive mechanism (6) is provided on a side of the mounting plate (5) close to the aircraft (4), and the rotation drive mechanism (6) is used to drive the mounting plate (5) to rotate around its central axis.

3. The aircraft vector thrust device according to claim 2, 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).

4. The aircraft vector thrust device according to claim 3, 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).

5. The aircraft vector thrust device according to claim 4, 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).

6. The aircraft vector thrust device according to claim 5, 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).

7. The aircraft vector thrust device according to claim 6, 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).

8. The aircraft vector thrust device according to claim 7, 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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