Freedom degree platform for aircraft

Abstract

The utility model belongs to the technical field of degree-of-freedom platforms, and particularly relates to a degree-of-freedom platform for an aircraft, which comprises a bottom plate, a lifting plate and a mounting plate, the lifting plate is arranged at the top of the bottom plate, the mounting plate is arranged at the top of the lifting plate, and a plurality of groups of electric push rods are arranged between the lifting plate and the mounting plate. A second driving motor in the quick release assembly drives a worm to rotate, a worm gear and a rotating rod are driven to be in linkage with a sliding block to move along an arc-shaped sliding groove, an L-shaped clamping block automatically clamps or loosens a first fixing plate, manual operation is not needed, tool-free quick installation and release of an aircraft are achieved, and the work efficiency is improved. A limiting rod between the first fixing plate and the second fixing plate is matched with a limiting groove, rapid positioning of the aircraft in the installation process is achieved, the lifting assembly drives a two-way screw to rotate, a sliding rod and a connecting rod are driven to accurately adjust the height of a lifting plate, stable lifting is guaranteed through sliding fit of a fixing column and a positioning pipe, and impact force generated in the descending process is buffered through a spring.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of degree of freedom platform, concretely is a kind of degree of freedom platform for aircraft. BACKGROUND

[0002] The degree of freedom platform for aircraft is a highly integrated multi-degree-of-freedom motion simulation system that can accurately simulate the complex motion state of an aircraft in three-dimensional space. This platform is widely used for pilot simulation training, aircraft control system testing, flight simulation research, and multi-task scenario simulation (such as emergency landing, complex weather response, etc.). Its high simulation and scalability make it a key device for aerospace research and development, training, and virtual reality experience. By combining real-time data feedback and intelligent algorithms, this platform can also reproduce subtle dynamics such as vibration and jitter in real flight, significantly improving the accuracy of training immersion and technical verification.

[0003] Existing degree of freedom platforms for aircraft mostly use bolts or complex buckle structures to fix the aircraft, which takes a long time to disassemble and assemble, affecting the flexibility and efficiency of the equipment. Moreover, some platforms lack lifting functionality, making it difficult to adapt to different height requirements. To address this issue, we propose a degree of freedom platform for aircraft that can be adjusted in height and quickly disassembled and replaced as needed. SUMMARY

[0004] To address the shortcomings of existing technology, the utility model provides a degree of freedom platform for aircraft, which realizes the tool-free quick installation and release of the aircraft through a quick-release assembly and accurately adjusts the height of the lifting plate through a lifting assembly, solving the aforementioned problems.

[0005] To achieve the above objectives, the utility model realizes the following technical solutions: a degree of freedom platform for aircraft, comprising a bottom plate, a lifting plate, and a mounting plate. The lifting plate is arranged on the top of the bottom plate, and the mounting plate is arranged on the top of the lifting plate. A plurality of electric push rods are arranged between the lifting plate and the mounting plate. The bottom end and the output end of the electric push rod are hingedly connected to the top side of the lifting plate and the bottom side of the mounting plate, respectively. An aircraft is arranged on the top side of the mounting plate. A quick-release assembly is installed between the mounting plate and the aircraft. A lifting assembly is installed between the bottom plate and the lifting plate.

[0006] Preferably, the quick release assembly comprises a mounting box fixedly installed at the middle portion of the mounting plate, an inner wall of the mounting box is fixedly connected with a second fixing plate, the bottom of the aircraft is fixedly connected with a fixing rod, the bottom end of the fixing rod is fixedly connected with a first fixing plate, the bottom side of the first fixing plate abuts against the top side of the second fixing plate, a plurality of first sliding grooves are formed through the second fixing plate, a sliding block is slidably connected with the first sliding grooves, the top side of the sliding block is fixedly connected with an L-shaped clamping block, the top and bottom sides of the L-shaped clamping block abut against the top side of the first fixing plate, and a driving mechanism for driving the sliding block to slide in the first sliding grooves is installed at the inner bottom side of the mounting box.

[0007] Preferably, the driving mechanism comprises a rotating plate arranged at the inner bottom side of the mounting box, a plurality of arc-shaped sliding grooves are formed through the rotating plate, a plurality of movable rods are movably connected with the arc-shaped sliding grooves, the sliding block is fixedly connected with the top end of the movable rod, the bottom end of the movable rod is fixedly connected with a limiting plate, the top side of the limiting plate abuts against the bottom side of the rotating plate, the bottom side of the rotating plate is fixedly connected with a rotating rod, the rotating rod rotates to extend out of the bottom of the mounting box, and a rotating mechanism for driving the rotating rod to rotate is installed at the bottom side of the mounting plate.

[0008] Preferably, the rotating mechanism comprises a second driving motor fixedly installed at the bottom of the mounting plate, a worm is rotatably installed at the bottom of the mounting box, the output shaft end of the second driving motor is fixedly connected with the left end of the worm, and a worm wheel is fixedly sleeved with the bottom end of the rotating rod and engaged with the worm.

[0009] Preferably, the lifting assembly comprises a bidirectional screw rod, a first mounting plate is fixedly connected with the top left and right sides of the bottom plate, the bidirectional screw rod is rotatably arranged between the two first mounting plates, a sliding rod is threadedly sleeved with the left and right sides of the bidirectional screw rod, a rotating shaft is fixedly connected with the front and rear ends of the sliding rod, a connecting rod is rotatably sleeved with the rotating shaft, the top end of the connecting rod is hingedly connected with the bottom side of the lifting plate, a first driving motor is fixedly installed at the top middle portion of the bottom plate, a bevel gear is fixedly sleeved with the output shaft of the first driving motor, a second bevel gear is fixedly sleeved with the middle portion of the bidirectional screw rod, and the first bevel gear is engaged with the second bevel gear.

[0010] Preferably, a plurality of limiting grooves are formed through the first fixing plate, and a plurality of limiting rods are fixedly connected with the top side of the second fixing plate, and the outer surface of the limiting rod abuts against the inner surface of the limiting groove.

[0011] Preferably, a positioning tube is fixedly connected with the top corners of the lifting plate, a bump pad is fixedly connected with the top of the positioning tube, a fixing column is fixedly connected with the top corners of the bottom plate, and the top of the fixing column is slidably connected with the inner wall of the positioning tube.

[0012] Preferably, the outer surface of the fixed column is fixedly sleeved with a limiting plate two, and a spring is sleeved on the fixed column, and the top and bottom of the spring abut with the bottom side of the lifting plate and the top side of the limiting plate two respectively.

[0013] Preferably, the bottom outer surface of the fixed column is fixedly connected with a plurality of reinforcing rib plates.

[0014] Preferably, the four edges of the bottom plate are fixedly connected with mounting plates two, and bolt mounting holes are formed in the mounting plates two.

[0015] The utility model provides a degree of freedom platform for aircraft, has the following beneficial effects compared with prior art:

[0016] 1、This degree of freedom platform for aircraft, through drive motor no. 2 in quick release assembly drives the rotation of worm, drives the linkage of worm wheel and rotating rod sliding block along the arc sliding slot, makes L shaped clamping block automatic clamping or loosening fixed plate one, need not manual operation, has remarkably shortened the dismounting time, has realized the toolless quick installation and release of aircraft, and the limiting rod between fixed plate one and fixed plate two cooperates with limiting groove, realizes the quick positioning of aircraft in installation.

[0017] 2、This degree of freedom platform for aircraft, lifting assembly drives the rotation of bidirectional screw rod, drives the accurate regulation of sliding rod and connecting rod height of lifting plate, and the sliding cooperation of fixed column and positioning pipe guarantees stable lifting, and the impact force when descending is buffered through spring. ACCURACY OF DRAWINGS

[0018] Figure 1 It is the front view structural schematic diagram of the main body of the utility model;

[0019] Figure 2 It is the bottom view structural schematic diagram of the main body of the utility model;

[0020] Figure 3 It is the installation plate and aircraft split structure schematic diagram of the utility model;

[0021] Figure 4 It is the installation box cross section structural schematic diagram of the utility model;

[0022] Figure 5 It is the internal structure schematic diagram of the drive mechanism of the utility model;

[0023] Figure 6 It is the utility model Figure 1 It is the structure enlarged schematic diagram of place A in the utility model;

[0024] Figure 7 It is the structure enlarged schematic diagram of place B in the utility model Figure 2

[0025] ​In the figure: 1, the base plate; 2, the lifting plate; 3, the mounting plate; 4, the fixed column; 5, the positioning tube; 6, the anti-collision pad; 7, the reinforcing rib plate; 8, the electric push rod; 9, the mounting plate one; 10, the mounting plate two; 11, the bolt mounting hole; 12, the connecting rod; 13, the aircraft; 14, the mounting box; 15, the fixed rod; 16, the fixed plate one; 17, the limiting rod; 18, the limiting groove; 19, the rotating plate; 20, the fixed plate two; 21, the sliding groove one; 22, the sliding block; 23, the rotating rod; 24, the arc-shaped sliding groove; 25, the movable rod; 26, the L-shaped clamping block; 27, the limiting plate one; 28, the bidirectional screw rod; 29, the driving motor one; 30, the bevel gear one; 31, the bevel gear two; 32, the sliding rod; 33, the rotating shaft; 34, the driving motor two; 35, the limiting plate two; 36, the spring; 37, the worm wheel; 38, the worm. DETAILED DESCRIPTION

[0026] The technical solutions in the embodiments of the utility model will be clearly and completely described below with reference to the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the protection scope of the utility model.

[0027] Please refer to Figures 1-7 The utility model provides a kind of technical scheme: a freedom platform for aircraft, including base plate 1, lifting plate 2 and mounting plate 3, lifting plate 2 is set on the top of base plate 1, mounting plate 3 is set on the top of lifting plate 2, be provided with several groups of electric push rod 8 between lifting plate 2 and mounting plate 3, the bottom end and output end of electric push rod 8 are respectively hinged in the top side of lifting plate 2 and the bottom side of mounting plate 3, the top side of mounting plate 3 is provided with aircraft 13, quick release assembly is installed between mounting plate 3 and aircraft 13, lifting assembly is installed between base plate 1 and lifting plate 2;

[0028] The freedom platform for aircraft uses, lifting plate 2 is vertically lifted by lifting assembly between base plate 1 and lifting plate 2, the overall height of platform is adjusted, the mounting plate 3 of the top of lifting plate 2 is hinged with lifting plate 2 by several groups of electric push rod 8, the bottom end of electric push rod 8 is fixed to the top side of lifting plate 2, the output end is hinged to the bottom side of mounting plate 3, the attitude angle of mounting plate 3 is adjusted by push rod telescopic, simulate the multiple freedom movement such as pitch, roll of aircraft 13, aircraft 13 on the top of mounting plate 3 is quickly fixed or released by quick release assembly, realize tool-free quick installation and replacement.

[0029] The quick release assembly comprises a mounting box 14 fixedly installed at the middle portion of the mounting plate 3, the inner wall of the mounting box 14 is fixedly connected with a second fixing plate 20, the bottom of the aircraft 13 is fixedly connected with a fixing rod 15, the bottom end of the fixing rod 15 is fixedly connected with a first fixing plate 16, the bottom side of the first fixing plate 16 abuts against the top side of the second fixing plate 20, a plurality of sliding grooves 21 are formed through the second fixing plate 20, a sliding block 22 is slidably connected with the sliding grooves 21, the top side of the sliding block 22 is fixedly connected with an L-shaped clamping block 26, the top and bottom sides of the L-shaped clamping block 26 abut against the top side of the first fixing plate 16, and a driving mechanism for driving the sliding block 22 to slide in the sliding grooves 21 is installed at the inner bottom side of the mounting box 14.

[0030] The driving mechanism comprises a rotating plate 19 arranged at the inner bottom side of the mounting box 14, a plurality of arc-shaped sliding grooves 24 are formed through the rotating plate 19, a plurality of movable rods 25 are movably connected with the arc-shaped sliding grooves 24, the sliding block 22 is fixedly connected with the top end of the movable rod 25, the bottom end of the movable rod 25 is fixedly connected with a limiting plate 27, the top side of the limiting plate 27 abuts against the bottom side of the rotating plate 19, the bottom side of the rotating plate 19 is fixedly connected with a rotating rod 23, the rotating rod 23 rotates and extends out of the bottom of the mounting box 14, and a rotating mechanism for driving the rotating rod 23 to rotate is installed at the bottom side of the mounting plate 3.

[0031] The rotating mechanism comprises a driving motor 34 fixedly installed at the bottom of the mounting plate 3, a worm 38 rotatably installed at the bottom of the mounting box 14, the output shaft end of the driving motor 34 is fixedly connected with the left end of the worm 38, and the bottom end of the rotating rod 23 is fixedly sleeved with a worm wheel 37 in mesh with the worm 38.

[0032] When the quick release assembly is used, the worm 38 is driven to rotate by the driving motor 34, the worm 38 is in mesh with the worm wheel 37 fixedly connected with the bottom end of the rotating rod 23, so that the rotating rod 23 and the rotating plate 19 are synchronously rotated, the arc-shaped sliding grooves 24 on the rotating plate 19 guide the movable rod 25 to move along the sliding groove track, the sliding block 22 fixedly connected with the top end of the movable rod 25 slides in the sliding grooves 21 of the second fixing plate 20, the L-shaped clamping block 26 connected with the top of the sliding block 22 moves close to or away from the first fixing plate 16, when the L-shaped clamping block 26 moves close to the first fixing plate 16, the bottom side of the top long side of the L-shaped clamping block 26 abuts against the top side of the first fixing plate 16, the bottom of the aircraft 13 is fixedly connected with the first fixing plate 16 through the fixing rod 15, and the first fixing plate 16 is quickly fixed with the mounting box 14, on the contrary, when the L-shaped clamping block 26 moves away from the first fixing plate 16, the first fixing plate 16 is released, the aircraft 13 is quickly separated from the mounting plate 3, the limiting plate 27 at the bottom end of the movable rod 25 abuts against the bottom side of the rotating plate 19, the moving track of the sliding block 22 is stable, and the tool-free quick disassembly and assembly process is completed.

[0033] The lifting assembly comprises a bidirectional screw rod 28, the top of the bottom plate 1 is fixedly connected with two installation plates 9, the bidirectional screw rod 28 is rotatably arranged between the two installation plates 9, the left and right sides of the bidirectional screw rod 28 are threadedly sleeved with sliding rods 32, the front and rear ends of the sliding rods 32 are fixedly connected with rotating shafts 33, the rotating shafts 33 are rotatably sleeved with connecting rods 12, the top end of the connecting rod 12 is hingedly connected to the bottom side of the lifting plate 2, the top side of the bottom plate 1 is fixedly connected with a driving motor 29, the output shaft of the driving motor 29 is fixedly sleeved with a bevel gear 30, the middle part of the bidirectional screw rod 28 is fixedly sleeved with a bevel gear 31, and the bevel gear 30 is engaged with the bevel gear 31.

[0034] When the lifting assembly is used, the driving motor 29 drives the bevel gear 30 to rotate, the bevel gear 30 is engaged with the bevel gear 31 fixedly arranged on the middle part of the bidirectional screw rod 28, so that the bidirectional screw rod 28 is driven to rotate, the sliding rods 32 on the left and right sides of the bidirectional screw rod 28 move towards or away from each other due to opposite screw directions, the rotating shafts 33 fixedly arranged at the front and rear ends of the sliding rods 32 are rotatably sleeved with the connecting rods 12, the top end of the connecting rod 12 is hingedly connected to the bottom side of the lifting plate 2, so that the linear motion of the sliding rods 32 is converted into lifting power of the lifting plate 2, and the vertical movement of the lifting plate 2 along the top of the bottom plate 1 is realized.

[0035] A plurality of limiting grooves 18 are arranged through the fixing plate 16, the top side of the fixing plate 20 is fixedly connected with a plurality of limiting rods 17, the outer surface of the limiting rod 17 is abutted with the inner surface of the limiting groove 18, the limiting groove 18 on the fixing plate 16 is matched with the limiting rod 17 on the top side of the fixing plate 20 through surface abutment, the transverse deviation of the aircraft 13 during installation is limited, the accurate alignment of the fixing plate 16 and the fixing plate 20 is ensured, and the quick positioning and stable installation of the bottom fixing rod 15 of the aircraft 13 are realized.

[0036] The top side of the lifting plate 2 is fixedly connected with the positioning pipes 5, the top of the positioning pipe 5 is fixedly connected with the anti-collision pad 6, the top side of the bottom plate 1 is fixedly connected with the fixing columns 4, the top of the fixing column 4 is slidingly connected to the inner wall of the positioning pipe 5, the positioning pipe 5 at the four corners of the lifting plate 2 is slidingly matched with the fixing column 4 on the top side of the bottom plate 1, the transverse displacement of the lifting plate 2 during vertical lifting is constrained, the stable motion track is ensured, the anti-collision pad 6 on the top of the positioning pipe 5 absorbs impact when the lifting plate 2 moves to the limit position, and hard collision damage is prevented.

[0037] The outer surface of the fixing column 4 is fixedly sleeved with the limiting plate 35, the fixing column 4 is sleeved with the spring 36, the top and bottom of the spring 36 are respectively abutted with the bottom side of the lifting plate 2 and the top side of the limiting plate 35, the limiting plate 35 on the outer surface of the fixing column 4 is connected with the bottom side of the lifting plate 2 through the spring 36, the spring 36 buffers external impact force in real time during the lifting process of the lifting plate 2, vibration transmission is reduced, and the stability and durability of platform operation are improved.

[0038] The bottom outer surface of the fixed column 4 is fixedly connected with a plurality of reinforcing rib plates 7. The reinforcing rib plates 7 on the bottom outer surface of the fixed column 4 enhance the connection strength between the fixed column 4 and the bottom plate 1, prevent the fixed column 4 from bending or deforming when the lifting plate 2 is overloaded or quickly lifted, and ensure the structural reliability.

[0039] The four edges of the bottom plate 1 are fixedly connected with mounting plates two 10. Bolt mounting holes 11 are formed in the mounting plates two 10. The mounting plates two 10 on the four edges of the bottom plate 1 are fixed to the ground or base through the bolt mounting holes 11 thereon and external bolts, thereby achieving stable installation and positioning of the equipment.

[0040] Working principle: when the freedom platform for aircraft is in use, the driving motor one 29 drives the bevel gear one 30 to rotate. Since the bevel gear one 30 is engaged with the bevel gear two 31 fixed in the middle of the bidirectional screw rod 28, the bidirectional screw rod 28 is driven to rotate. The sliding rods 32 on the left and right sides of the bidirectional screw rod 28 move towards or away from each other when the bidirectional screw rod 28 rotates because the thread directions are opposite. The rotating shafts 33 fixed at the front and rear ends of the sliding rods 32 are rotatably connected with the connecting rods 12. The connecting rods 12 are hingedly connected to the bottom side of the lifting plate 2. Therefore, the linear motion of the sliding rods 32 is converted into lifting power for the lifting plate 2, realizing vertical motion of the lifting plate 2 along the top of the bottom plate 1, and adjusting the overall height of the platform.

[0041] The mounting plate 3 on the top of the lifting plate 2 is hingedly connected with the lifting plate 2 through a plurality of groups of electric push rods 8. The bottom end of the electric push rod 8 is fixed to the top side of the lifting plate 2, and the output end is hingedly connected to the bottom side of the mounting plate 3. The attitude angle of the mounting plate 3 is adjusted through the extension and retraction of the push rod, simulating the pitch, roll and other multi-freedom motion of the aircraft 13. When the aircraft 13 on the top of the mounting plate 3 is disassembled, the driving motor two 34 drives the worm 38 to rotate. Since the worm 38 is engaged with the worm gear 37 fixed at the bottom end of the rotating rod 23, the rotating rod 23 and the rotating plate 19 are driven to rotate synchronously. The arc-shaped sliding groove 24 on the rotating plate 19 guides the movable rod 25 to move along the sliding groove track. The sliding block 22 fixed at the top end of the movable rod 25 slides in the sliding groove one 21 of the fixed plate two 20. The L-shaped clamping block 26 connected to the top of the sliding block 22 moves close to or away from the fixed plate one 16. When the L-shaped clamping block 26 moves close to the fixed plate one 16, the bottom side of the long edge on the top of the L-shaped clamping block 26 abuts against the top side of the fixed plate one 16, realizing quick fixing of the fixed plate one 16 and the mounting box 14 fixedly connected to the bottom of the aircraft 13. Conversely, when the L-shaped clamping block 26 moves away from the fixed plate one 16, the fixed plate one 16 is released, and the aircraft 13 and the mounting plate 3 are quickly separated. The limiting plate one 27 at the bottom end of the movable rod 25 abuts against the bottom side of the rotating plate 19, ensuring the stability of the moving track of the sliding block 22, and completing the tool-free quick disassembly process.

[0042] It is to be noted that, in the present document, relational terms such as first and second and the like can be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises", "comprising", or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can include other elements not expressly listed or inherent to such process, method, article, or apparatus.

[0043] While the embodiments of the present application have been illustrated and described, it will be understood by those skilled in the art that various changes, modifications, substitutions, and alterations can be made therein without departing from the spirit and scope of the application, which is defined by the appended claims and their equivalents.

Claims

1. A freedom platform for an aircraft, comprising a base plate (1), a lifting plate (2) and a mounting plate (3), characterized in that: The lifting plate (2) is arranged on the top of the bottom plate (1), the mounting plate (3) is arranged on the top of the lifting plate (2), a plurality of groups of electric push rods (8) are arranged between the lifting plate (2) and the mounting plate (3), the bottom end and the output end of the electric push rod (8) are hinged to the top side of the lifting plate (2) and the bottom side of the mounting plate (3) respectively, the top side of the mounting plate (3) is provided with an aircraft (13), a quick release assembly is installed between the mounting plate (3) and the aircraft (13), and a lifting assembly is installed between the bottom plate (1) and the lifting plate (2).

2. A degree of freedom platform for an aircraft as defined in claim 1, wherein: The quick release assembly comprises a mounting box (14), the mounting box (14) is fixedly installed in the middle of the mounting plate (3), the inner wall of the mounting box (14) is fixedly connected with a second fixed plate (20), the bottom of the aircraft (13) is fixedly connected with a fixed rod (15), the bottom end of the fixed rod (15) is fixedly connected with a first fixed plate (16), the bottom side of the first fixed plate (16) abuts against the top side of the second fixed plate (20), a plurality of first sliding grooves (21) are penetratingly formed in the second fixed plate (20), a sliding block (22) is slidably connected with the first sliding groove (21), the top side of the sliding block (22) is fixedly connected with an L-shaped clamping block (26), the top and bottom sides of the L-shaped clamping block (26) abut against the top side of the first fixed plate (16), and a driving mechanism for driving the sliding block (22) to slide in the first sliding groove (21) is installed at the inner bottom side of the mounting box (14).

3. A degree of freedom platform for an aircraft as defined in claim 2, wherein: The driving mechanism comprises a rotating plate (19), the rotating plate (19) is arranged at the inner bottom side of the mounting box (14), a plurality of arc-shaped sliding grooves (24) are penetratingly formed in the rotating plate (19), a plurality of movable rods (25) are movably connected with the arc-shaped sliding grooves (24), the sliding block (22) is fixedly connected with the top end of the movable rod (25), the bottom end of the movable rod (25) is fixedly connected with a limiting plate (27), the top side of the limiting plate (27) abuts against the bottom side of the rotating plate (19), the bottom side of the rotating plate (19) is fixedly connected with a rotating rod (23) in the middle, the rotating rod (23) rotates and extends out of the bottom of the mounting box (14), and a rotating mechanism for driving the rotating rod (23) to rotate is installed at the bottom side of the mounting plate (3).

4. A degree of freedom platform for an aircraft as defined in claim 3, wherein: The rotating mechanism comprises a second driving motor (34), the second driving motor (34) is fixedly installed at the bottom of the mounting plate (3), the mounting box (14) is rotatably installed with a worm (38) at the bottom, the output shaft end of the second driving motor (34) is fixedly connected with the left end of the worm (38), the bottom end of the rotating rod (23) is fixedly sleeved with a worm wheel (37), and the worm wheel (37) is engaged with the worm (38).

5. A degree of freedom platform for an aircraft as defined in claim 1, wherein: The lifting assembly comprises a bidirectional screw rod (28), the top of the bottom plate (1) is fixedly connected with a mounting plate one (9) on the left and right sides, the bidirectional screw rod (28) is rotatably arranged between the two mounting plate ones (9), the left and right sides of the bidirectional screw rod (28) are threadedly sleeved with a sliding rod (32), the front end and the rear end of the sliding rod (32) are fixedly connected with a rotating shaft (33), the rotating shaft (33) is rotatably sleeved with a connecting rod (12), the top end of the connecting rod (12) is hingedly connected to the bottom side of the lifting plate (2), the top side of the bottom plate (1) is fixedly connected with a driving motor one (29), the output shaft of the driving motor one (29) is fixedly sleeved with a bevel gear one (30), the middle part of the bidirectional screw rod (28) is fixedly sleeved with a bevel gear two (31), and the bevel gear one (30) is engaged with the bevel gear two (31).

6. A degree of freedom platform for an aircraft as defined in claim 2, wherein: A plurality of limiting grooves (18) are formed through the fixing plate one (16), the top side of the fixing plate two (20) is fixedly connected with a plurality of limiting rods (17), and the outer surface of the limiting rod (17) abuts against the inner surface of the limiting groove (18).

7. A degree of freedom platform for an aircraft as defined in claim 1, wherein: The top side of the lifting plate (2) is fixedly connected with a positioning pipe (5) at the four corners, the top of the positioning pipe (5) is fixedly connected with a bump pad (6), the top side of the bottom plate (1) is fixedly connected with a fixed column (4) at the four corners, and the top of the fixed column (4) is slidingly connected to the inner wall of the positioning pipe (5).

8. A degree of freedom platform for an aircraft as defined in claim 7, wherein: The outer surface of the fixed column (4) is fixedly sleeved with a limiting plate two (35), the fixed column (4) is sleeved with a spring (36), and the top and the bottom of the spring (36) abut against the bottom side of the lifting plate (2) and the top side of the limiting plate two (35) respectively.

9. A degree of freedom platform for an aircraft as defined in claim 7, wherein: The bottom outer surface of the fixed column (4) is fixedly connected with a plurality of reinforcing rib plates (7).

10. The freedom platform for an aerial vehicle of claim 1, wherein: The four edges of the bottom plate (1) are fixedly connected with a mounting plate two (10), and the mounting plate two (10) is provided with a bolt mounting hole (11).

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