Propeller power three-dimensional space attitude test platform

Abstract

The invention discloses a propeller power three-dimensional space attitude test platform, which belongs to the technical field of engine performance detection and comprises a first rotating part, a second rotating part and a third rotating part. A first supporting platform matched with the third rotating part is arranged on the first rotating part, and a second supporting platform matched with the second rotating part is arranged on the third rotating part; the first supporting platform can drive the second rotating part and the third rotating part to rotate around a first direction, the second supporting platform can drive the second rotating part to rotate around a second direction, a to-be-tested piece is arranged on the second rotating part, and the second rotating part can drive the to-be-tested piece to rotate around a third direction; the X / Y / Z axis rotation motion of the rack can be independent motion or three-axis linkage operation, the long-time test work of one space posture can be met, and a user can set the position state of a tested piece in the space according to the test requirement. The multi-dimensional test state simulates all attitude actions as much as possible when the aircraft flies in the air.

Description

Technical Field

[0001] This invention relates to the field of engine performance testing technology, and in particular to a propeller-driven three-dimensional spatial attitude test platform. Background Technology

[0002] The performance and reliability assessment of aero-engines, especially propeller engines, is highly dependent on testing methods capable of simulating their real, complex operating environments. Currently, while some advancements have been made in single-performance testing technologies for propeller engines—such as test benches focused on static or single-axis thrust / pull measurements, and test systems capable of circular moving airflow to assess the effects of different incoming flow directions—these platforms have significant limitations in terms of testing dimensions and the realism of environmental simulation. Most of these existing test platforms are designed to be fixed or capable of only a single degree of freedom of motion, unable to simulate the complex three-dimensional continuous combinations of attitudes that aircraft may experience in actual flight, such as dives, climbs, rolls, and stall rotations. This limitation makes it difficult for existing testing methods to comprehensively and realistically reflect the integrated performance of the engine and its related systems (such as intake and exhaust systems, fuel supply systems, lubrication systems, and rotating shaft systems) under dynamic flight attitudes.

[0003] Furthermore, the shortcomings of existing technologies are specifically reflected in the following aspects: First, in power output performance testing, traditional tensile testing platforms (such as platforms using cantilever mounting frames) can measure static thrust, but cannot reproduce the changes in engine power output characteristics and propeller aerodynamic efficiency under multi-dimensional acceleration coupling. Second, regarding intake and exhaust performance, even if some technologies attempt to simulate airflow from different directions by arranging movable fans, this simulation is local and non-integrated, making it difficult to accurately construct all-round, dynamically changing intake conditions that are completely consistent with the specific maneuvers of the aircraft. Third, the fuel supply performance of the engine and the lubrication performance of the power system are particularly critical under complex attitudes. When the aircraft rolls around the Y-axis or stalls around the Z-axis, the fuel and lubricating oil will be subjected to complex inertial forces and centrifugal forces, which can easily lead to problems such as fuel supply interruption and poor lubrication. Existing static or single-degree-of-freedom testing platforms cannot effectively simulate and evaluate the system state under these extreme conditions. Fourth, regarding the load-bearing capacity of rotating shaft systems and bearings, under continuous multidimensional rotation conditions, bearings need to withstand complex alternating loads from different directions and constantly changing. Existing testing equipment lacks an integrated platform that can simultaneously apply multidimensional loads and monitor their response, resulting in insufficient assessment of the life and reliability of this critical component under actual flight conditions.

[0004] In summary, current technologies lack an efficient, integrated three-dimensional testing platform. This platform should be able to simulate the continuous multi-dimensional maneuvers of an aircraft in the air, thereby enabling comprehensive and accurate testing and evaluation of key performance aspects of the propeller engine power system, such as power output, intake and exhaust, fuel supply, lubrication, and shaft load-bearing capacity, under near-real service conditions. This deficiency restricts the in-depth optimization of engine performance and the verification of its reliability. Summary of the Invention

[0005] The purpose of this invention is to provide a three-dimensional spatial attitude test platform for propeller power, addressing the aforementioned shortcomings. This solves the problem of the lack of an efficient and integrated three-dimensional test platform in the existing technology, enabling comprehensive and accurate testing and evaluation of key performance aspects of propeller engine power systems, such as power output, intake and exhaust, oil supply, lubrication, and shaft load-bearing capacity, under near-real service conditions.

[0006] This invention is achieved through the following scheme: A propeller-powered three-dimensional spatial attitude test platform includes a first rotating part, a second rotating part, and a third rotating part; a first support platform cooperating with the third rotating part is provided on the first rotating part, and a second support platform cooperating with the second rotating part is provided on the third rotating part; the first support platform can drive the second rotating part and the third rotating part to rotate around a first direction, the second support platform can drive the second rotating part to rotate around a second direction, the test piece is placed on the second rotating part, and the second rotating part can drive the test piece to rotate around a third direction.

[0007] Based on the structure of the above-mentioned propeller-powered three-dimensional spatial attitude test platform, the first rotating part specifically includes a bench base, a first braking part, a first support platform, and a first rotary motor; the bench base is provided with a support frame that cooperates with the first support platform; the support frame is provided with a rotary bearing, the bottom of the first support platform is provided with a first rotating shaft that cooperates with the rotary bearing, and the first rotating shaft is also provided with a gear disk that cooperates with the first rotary motor, and the output end of the first rotary motor meshes with the gear disk through an output gear.

[0008] Based on the structure of the above-mentioned propeller-powered three-dimensional spatial attitude test platform, the bottom of the first support platform is provided with a support crossbeam, a support vertical frame, and a reinforcing rib; the support crossbeam is set at a predetermined distance from the bottom position of the first support platform through the support vertical frame, and the reinforcing rib is obliquely set between the first support platform and the support crossbeam.

[0009] Based on the structure of the above-mentioned propeller-powered three-dimensional spatial attitude test platform, the first braking unit includes a first brake disc, a first brake, and a brake support column; the support column is mounted on the platform base, the first brake is mounted on the brake support seat, and the first brake disc is connected to the support crossbeam; the first brake disc is embedded in the brake end of the first brake.

[0010] Based on the structure of the above-mentioned propeller-powered three-dimensional spatial attitude test platform, a limit block is also provided on the inner side of the support frame. The limit block is symmetrically arranged on both sides of the support frame along the center position of the platform base. An tilt sensor is provided on the first support platform.

[0011] Based on the structure of the aforementioned propeller-powered three-dimensional spatial attitude test platform, a counterweight assembly is further provided at the end of the first support platform. The counterweight assembly includes a first pulley, a second pulley, a third pulley, a pulley support frame, and a counterweight. The first pulley is located at the end of the first support platform, and the pulley support frame is located on a wall near the first support platform. The second and third pulleys are located on the pulley support frame, with the second and first pulleys at the same horizontal position. The pulley support frame is provided with a support slope that cooperates with the third pulley, and the third pulley is located on the support slope. The projections of the second and third pulleys on the horizontal plane do not coincide. The counterweight is connected to the first, second, and third pulleys via steel wire ropes.

[0012] Based on the structure of the aforementioned propeller-powered three-dimensional spatial attitude test platform, the third rotating part includes a second support platform, a support bearing, a second rotating motor, and a second braking part. The first support platform has a through hole that mates with the second rotating motor and the second braking part. The second rotating motor and the second braking part are embedded within the first support platform. The outer ring of the support bearing is connected to the first support platform, and the inner ring of the support bearing has a gear ring. The output end of the second rotating motor meshes with the gear ring via a gear. The inner ring of the support bearing is connected to the second support platform, and the second braking part is coaxially disposed on the outer ring of the support bearing.

[0013] Based on the structure of the above-mentioned propeller-powered three-dimensional spatial attitude test platform, the second braking part includes a brake ring and a second brake. The brake ring is coaxially disposed on the outer ring of the support bearing. The brake ring is connected to the bottom of the second support platform. The brake ring is inserted into the second brake. At least two second brakes are provided.

[0014] Based on the structure of the above-mentioned propeller-powered three-dimensional spatial attitude test platform, the second rotating part includes a second support frame, a third brake part, a third rotating motor, and a swing frame; the second support frame is symmetrically arranged along the center position of the second support platform, the swing frame is arranged between the two second support frames, the swing frame is rotatably connected to the second support frame through a first rotating shaft, a rotating gear ring is provided at the end of the first rotating shaft, the third rotating motor is arranged on the second support frame, the output part of the third rotating motor meshes with the rotating gear ring through a gear, and the third brake part is arranged close to the rotating shaft gear ring.

[0015] Based on the structure of the above-mentioned propeller-powered three-dimensional spatial attitude test platform, the rotating gear ring includes a first gear ring connected to a first rotating shaft, and the third braking part includes a second brake disc and a third brake, wherein the second brake disc is coaxially arranged with the first gear ring and the second brake disc is inserted into the third brake.

[0016] In summary, due to the adoption of the above technical solution, the beneficial effects of the present invention are: 1. The test component in this scheme is an engine. The engine is mounted on a dynamometer motor and finally assembled on a second rotating part to achieve performance testing in three-dimensional space. The first rotating part simulates the aircraft's dive and vertical climb conditions; the second rotating part simulates the aircraft's roll conditions; and the third rotating part simulates the aircraft's stall rotation conditions. This simulates various rolling movements of a propeller-driven aircraft during flight. Furthermore, it can be connected to external components to verify the power output performance of the aircraft's power system under in-flight roll conditions, the engine's intake and exhaust performance, the engine's fuel supply performance, the power system's lubrication performance, and the bearing capacity of the rotating shaft system, thus achieving efficient testing of engine performance. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the overall installation structure of the present invention; Figure 2 This is a three-dimensional structural diagram of the entire invention; Figure 3 This is a schematic diagram of the structure of the first rotating part in this invention; Figure 4 This is a schematic diagram of the structure of the second rotating part in this invention; Figure 5 This is a schematic cross-sectional view of the second rotating part in this invention; Figure 6 This is a schematic diagram of the structure of the third rotating part in this invention; Reference numerals: 1. First rotating part; 2. Second rotating part; 3. Third rotating part; 6. Dynamometer motor; 11. Stand base; 12. First brake part; 13. First support platform; 14. First rotary motor; 15. Support frame; 16. Rotary bearing; 17. First rotating shaft; 18. Gear disk; 19. Limit block; 110. Tilt sensor; 21. Second support frame; 22. Third brake part; 23. Third rotary motor; 24. Swing frame; 25. First rotating shaft; 26. Rotary gear ring; 27. Second brake disc; 28. 31. Third brake; 32. Second support platform; 33. Support bearing; 34. Second rotating motor; 35. Second brake unit; 36. Inner ring; 37. Outer ring; 38. Brake ring; 39. Second brake; 40. Support crossbeam; 41. Support vertical beam; 42. Reinforcing rib; 121. First brake disc; 122. First brake; 123. Brake support column; 61. First pulley; 62. Second pulley; 63. Third pulley; 64. Pulley support frame; 65. Counterweight; 66. Supporting inclined plane; 67. Steel wire rope. Detailed Implementation

[0018] All features disclosed in this specification, or all steps in all disclosed methods or processes, may be combined in any way, except for mutually exclusive features and / or steps.

[0019] Any feature disclosed in this specification (including any appended claims and abstract) may be replaced by other equivalent or similar features, unless specifically stated otherwise. That is, unless specifically stated otherwise, each feature is merely one example of a series of equivalent or similar features.

[0020] In the description of this invention, it should be understood that the terms "upper," "lower," "left," "right," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a predetermined orientation, or be constructed and operated in a predetermined orientation. Therefore, they should not be construed as limitations on this invention.

[0021] Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the quantity indicated. Therefore, a feature defined with "first," "second," etc., may explicitly or implicitly include one or more of that feature.

[0022] Example 1 like Figures 1-6 As shown, the present invention provides a technical solution: A propeller-driven three-dimensional spatial attitude test platform includes a first rotating part 1, a second rotating part 2, and a third rotating part 3; the first rotating part 1 is provided with a first support platform 13 that cooperates with the third rotating part 3, and the third rotating part 3 is provided with a second support platform 31 that cooperates with the second rotating part 2; the first support platform 13 can drive the second rotating part 2 and the third rotating part 3 to rotate around a first direction, and the second support platform 31 can drive the second rotating part 2 to rotate around a second direction; the test piece is placed on the second rotating part 2, and the second rotating part 2 can drive the test piece to rotate around a third direction.

[0023] Based on the above structure, the test component in this scheme is an engine. The engine is mounted on the dynamometer motor 6 and finally assembled on the second rotating part 2 to achieve performance testing in three-dimensional space. The first rotating part 1 simulates the aircraft's dive and vertical climb conditions; the second rotating part 2 simulates the aircraft's roll conditions; and the third rotating part 3 simulates the aircraft's stall rotation conditions to simulate various roll movements of a propeller aircraft during flight. In addition, it can be connected to external components to verify the power output performance of the aircraft's power system under roll conditions, the engine's intake and exhaust performance, the engine's fuel supply performance, the power system's lubrication performance, and the bearing capacity of the rotating shaft system, thus achieving efficient testing of engine performance.

[0024] As an example, the first direction is horizontal and is defined as the X-axis direction; the second direction is perpendicular to the first direction in the same plane and is defined as the Y-axis direction; the second direction is vertical and is defined as the Z-axis direction. The first rotating part 1 may specifically include a platform base 11, a first brake part 12, a first support platform 13, and a first rotary motor 14; the platform base 11 is provided with a support frame 15 that cooperates with the first support platform 13; the support frame 15 is provided with a rotary bearing 16; the bottom of the first support platform 13 is provided with a first rotating shaft 17 that cooperates with the rotary bearing 16; a gear disk 18 that cooperates with the first rotary motor 14 is also provided on the first rotating shaft 17; the output end of the first rotary motor 14 meshes with the gear disk 18 through an output gear.

[0025] Based on the above structure, the platform base 11 is connected to the first rotating shaft 17 through the support frame 15 and the rotating bearing 16. Under the action of the first rotating motor 14, the first support platform 13 rotates around the rotating shaft, and the deflection angle of the first support platform 13 is controlled by the first brake part 12.

[0026] As an example, the bottom of the first support platform 13 is provided with a support crossbeam 41, a support vertical beam 42 and a reinforcing rib 43; the support crossbeam 41 is set at a predetermined distance from the bottom position of the first support platform 13 through the support vertical beam 42, and the reinforcing rib 43 is obliquely set between the first support platform 13 and the support crossbeam 41.

[0027] Based on the above structure, the support crossbeam 41 is spaced apart from the bottom of the first support platform 13. On the one hand, this can avoid interference with the first rotating shaft 17, allowing the first rotating shaft 17 to rotate more smoothly. On the other hand, it can provide a support base for the first brake unit 12, achieving efficient braking.

[0028] As an example, the first brake unit 12 may include a first brake disc 121, a first brake 122 and a brake support column 123; the support column is disposed on the platform base 11, the first brake 122 is disposed on the brake support seat, and the first brake disc is connected to the support crossbeam 41; the first brake disc 121 is embedded in the brake end of the first brake 122.

[0029] Based on the above structure, the first brake disc 121 can be braked by the first brake 122, so as to achieve precise control of the first support platform 13. The brake support column 123 is set on the platform base 11, so that the reaction force generated during braking can be transmitted to the ground, making the overall braking performance more stable. Through the first brake part 12 and the first rotary motor 14, the X-axis rotation can be efficiently realized to simulate the diving and vertical climbing conditions of the aircraft.

[0030] As an example, a limit block 19 is also provided on the inner side of the support frame 15. The limit block 19 is symmetrically arranged on both sides of the support frame 15 along the center position of the platform base 11. An tilt sensor 110 is provided on the first support platform 13. Based on the above structure, the limit block 19 can provide extreme position restrictions for the high-speed rotating first support platform 13, allowing it to rotate within a safe range. At the same time, an tilt sensor 110 is provided on the first support platform 13, which can control the angle of the first support platform 13 more efficiently.

[0031] As an example, a counterweight 65 assembly may also be provided at the end of the first support platform 13. The counterweight 65 assembly may include a first pulley 61, a second pulley 62, a third pulley 63, a pulley support frame 64, and the counterweight 65. The first pulley 61 is provided at the end of the first support platform 13, the pulley support frame 64 is provided on the wall near the first support platform 13, the second pulley 62 and the third pulley 63 are provided on the pulley support frame 64, the second pulley 62 and the first pulley 61 are at the same horizontal position, the pulley support frame 64 is provided with a support slope 66 that cooperates with the third pulley 63, the third pulley 63 is provided on the support slope 66, and the projections of the second pulley 62 and the third pulley 63 on the horizontal plane do not coincide. The counterweight 65 is connected to the first pulley 61, the second pulley 62, and the third pulley 63 by a steel wire rope 67.

[0032] Based on the above structure, the counterweight 65 component can ensure that the first support platform 13 is level when it is not working. The projections of the second pulley 62 and the third pulley 63 on the horizontal plane do not overlap, so that when the wire rope 67 passes around the third pulley 63, the counterweight 65 is set at a certain distance from the wall, so that the counterweight 65 will not contact the wall.

[0033] As an example, the third rotating part 3 may include a second support platform 31, a support bearing 32, a second rotating motor 33, and a second brake part 34; a through hole is provided on the first support platform 13 to cooperate with the second rotating motor 33 and the second brake part 34; the second rotating motor 33 and the second brake part 34 are embedded in the first support platform 13; the outer ring 322 of the support bearing 32 is connected to the first support platform 13; the inner ring 321 of the support bearing 32 is provided with a gear ring; the output end of the second rotating motor 33 meshes with the gear ring through a gear; the inner ring 321 of the support bearing 32 is connected to the second support platform 31; and the second brake part 34 is coaxially disposed on the outer ring 322 of the support bearing 32.

[0034] Based on the above structure, when the second rotating motor 33 rotates, it will drive the second support platform 31 to rotate along the center position of the support bearing 32. The second brake part 34 is embedded on the outside of the support bearing 32, which can effectively limit the rotation angle of the second support platform 31.

[0035] As an example, the second brake part 34 may include a brake ring 341 and a second brake 342. The brake ring 341 is coaxially disposed on the outer ring 322 of the support bearing 32. The brake ring 341 is connected to the bottom of the second support platform 31. The brake ring 341 is inserted into the second brake 342. At least two second brakes 342 are provided.

[0036] Based on the above structure, efficient braking can be achieved through the cooperation of the second brake 342 and the brake ring 341. With the cooperation of the second rotating motor 33, the entire second support platform 31 can rotate on the Z-axis to simulate the aircraft stall rotation condition.

[0037] As an example, the second rotating part 2 may include a second support frame 21, a third brake part 22, a third rotating motor 23, and a swing frame 24; the second support frame 21 is symmetrically arranged along the center position of the second support platform 31, the swing frame 24 is arranged between the two second support frames 21, the swing frame 24 is rotatably connected to the second support frame 21 through a first rotating shaft 25, a rotating gear ring 26 is provided at the end of the first rotating shaft 25, the third rotating motor 23 is arranged on the second support frame 21, the output part of the third rotating motor 23 meshes with the rotating gear ring 26 through gears, and the third brake part 22 is arranged close to the rotating shaft gear ring.

[0038] Based on the above structure, the swing frame 24 is connected to the second support parts on both sides through the first rotating shaft 25. Under the action of the third rotating motor 23, the swing frame 24 can be rotated, and the third brake part 22 brakes the swing frame 24.

[0039] As an example, the rotating gear ring 26 may include a first gear ring connected to a first rotating shaft 25, and the third brake part 22 may include a second brake disc 27 and a third brake 28. The second brake disc 27 is coaxially arranged with the first gear ring and is inserted into the third brake 28.

[0040] Based on the above structure, the rotation of the third rotary motor 23 can drive the first gear ring to rotate, which in turn drives the swing frame 24 to rotate along the center position of the first rotating shaft 25 through transmission. The third brake 28 brakes the second brake disc 27. The dynamometer motor 6 and the engine under test are installed on the swing frame 24. This test bench uses the X / Y / Z three-axis rotation of the test bench (X-axis rotation simulates the aircraft's dive and vertical climb conditions; Y-axis rotation simulates the aircraft's roll conditions; Z-axis rotation simulates the aircraft's stall rotation conditions) to simulate various rolling actions of a propeller aircraft during flight, thereby verifying the power output performance of the aircraft's power system under air roll conditions, the engine's intake and exhaust performance, the engine's fuel supply performance, the lubrication performance of the power system, and the bearing capacity of the rotating shaft system, etc.

[0041] The base 11 is constructed from 200×8 square tubing welded together to form a frame structure, serving as the load-bearing base for the entire equipment. It houses components such as the brake system mounting bracket, dead gear limit seat, and X-axis rotary bearing seat.

[0042] The X-axis swing frame is constructed from 100×6 square tubing welded together. The top is designed with a rotating bearing mounting bracket, an inclination sensor 110 mounting base, and a rotating drive motor mounting base, while the remaining parts are covered with 5mm patterned steel plates.

[0043] The Z-axis rotary platform uses an 80×5 square tube frame structure welded together. The bottom is designed with a rotary bearing mounting base, and the top beam ends are welded with 25mm steel plates to serve as the Y-axis support mounting platform. The Y-axis support has a drive motor mounting bracket. The remaining non-equipment installation space on the platform is covered with 5mm checkered steel plates.

[0044] The Y-axis swing platform uses an 80mm steel plate as the dynamometer mounting platform. T-slots are machined into the platform to accommodate the dynamometer and the engine under test. An inclination sensor 110 is also mounted on the platform. Rotary swing brackets are designed at both ends of the platform, which are fixed to the Z-axis rotating platform via rotating shafts / bearings, connecting to the Y-axis bracket on the Z-axis rotating platform.

[0045] The X / Y / Z axis rotation of the test bench can move independently or operate in three-axis linkage, thus satisfying long-term testing of a single spatial posture. Users can set the position and state of the test specimen in space according to experimental requirements. The position and state can be continuous and periodic or random. This multi-dimensional testing state aims to simulate all attitude and movement of an aircraft in flight as closely as possible.

[0046] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A propeller-powered three-dimensional spatial attitude test platform, characterized in that: It includes a first rotating part (1), a second rotating part (2) and a third rotating part (3); the first rotating part (1) is provided with a first support platform (13) that cooperates with the third rotating part (3), and the third rotating part (3) is provided with a second support platform (31) that cooperates with the second rotating part (2); the first support platform (13) can drive the second rotating part (2) and the third rotating part (3) to rotate around a first direction, the second support platform (31) can drive the second rotating part (2) to rotate around a second direction, the test piece is placed on the second rotating part (2), and the second rotating part (2) can drive the test piece to rotate around a third direction.

2. The propeller-powered three-dimensional spatial attitude test platform as described in claim 1, characterized in that: The first rotating part (1) specifically includes a platform base (11), a first brake part (12), a first support platform (13), and a first rotary motor (14); the platform base (11) is provided with a support frame (15) that cooperates with the first support platform (13); the support frame (15) is provided with a rotating bearing (16), the bottom of the first support platform (13) is provided with a first rotating shaft (17) that cooperates with the rotating bearing (16), the first rotating shaft (17) is also provided with a gear disk (18) that cooperates with the first rotary motor (14), and the output end of the first rotary motor (14) meshes with the gear disk (18) through an output gear.

3. The propeller-powered three-dimensional spatial attitude test platform as described in claim 2, characterized in that: The first support platform (13) is provided with a support crossbeam (41), a support vertical frame (42) and a reinforcing rib (43) at the bottom; the support crossbeam (41) is set at a predetermined distance from the bottom position of the first support platform (13) through the support vertical frame (42), and the reinforcing rib (43) is obliquely set between the first support platform (13) and the support crossbeam (41).

4. The propeller-powered three-dimensional spatial attitude test platform as described in claim 3, characterized in that: The first brake unit (12) includes a first brake disc (121), a first brake (122) and a brake support column (123); the support column is mounted on the platform base (11), the first brake (122) is mounted on the brake support seat, and the first brake disc is connected to the support crossbeam (41); the first brake disc (121) is embedded in the brake end of the first brake (122).

5. The propeller-powered three-dimensional spatial attitude test platform as described in claim 4, characterized in that: The support frame (15) is also provided with a limit block (19) on the inner side. The limit block (19) is symmetrically arranged on both sides of the support frame (15) along the center position of the platform base (11). The first support platform (13) is provided with an tilt sensor (110).

6. The propeller-powered three-dimensional spatial attitude test platform as described in claim 5, characterized in that: The first support platform (13) is also provided with a counterweight (65) assembly at its end. The counterweight (65) assembly includes a first pulley (61), a second pulley (62), a third pulley (63), a pulley support frame (64), and the counterweight (65). The first pulley (61) is located at the end of the first support platform (13), the pulley support frame (64) is located on the wall near the first support platform (13), and the second pulley (62) and the third pulley (63) are located on the pulley support frame (64). On 64), the second pulley (62) and the first pulley (61) are at the same horizontal position. The pulley support frame (64) is provided with a support slope (66) that cooperates with the third pulley (63). The third pulley (63) is set on the support slope (66). The projections of the second pulley (62) and the third pulley (63) on the horizontal plane do not coincide. The counterweight (65) is connected to the first pulley (61), the second pulley (62), and the third pulley (63) through a steel wire rope (67).

7. The propeller-powered three-dimensional spatial attitude test platform as described in claim 6, characterized in that: The third rotating part (3) includes a second support platform (31), a support bearing (32), a second rotating motor (33), and a second brake part (34); the first support platform (13) is provided with a through hole that cooperates with the second rotating motor (33) and the second brake part (34); the second rotating motor (33) and the second brake part (34) are embedded in the first support platform (13); the outer ring (322) of the support bearing (32) is connected to the first support platform (13); the inner ring (321) of the support bearing (32) is provided with a gear ring; the output end of the second rotating motor (33) meshes with the gear ring through a gear; the inner ring (321) of the support bearing (32) is connected to the second support platform (31); and the second brake part (34) is coaxially arranged on the outer ring (322) of the support bearing (32).

8. The propeller-powered three-dimensional spatial attitude test platform as described in claim 7, characterized in that: The second brake part (34) includes a brake ring (341) and a second brake (342). The brake ring (341) is coaxially disposed on the outer ring (322) of the support bearing (32). The brake ring (341) is connected to the bottom of the second support platform (31). The brake ring (341) is inserted into the second brake (342). There are at least two second brakes (342).

9. The propeller-powered three-dimensional spatial attitude test platform as described in claim 8, characterized in that: The second rotating part (2) includes a second support frame (21), a third brake part (22), a third rotating motor (23), and a swing frame (24); the second support frame (21) is symmetrically arranged along the center position of the second support platform (31), the swing frame (24) is arranged between the two second support frames (21), the swing frame (24) is rotatably connected to the second support frame (21) through a first rotating shaft (25), the end of the first rotating shaft (25) is provided with a rotating gear ring (26), the third rotating motor (23) is arranged on the second support frame (21), the output part of the third rotating motor (23) meshes with the rotating gear ring (26) through gears, and the third brake part (22) is arranged close to the rotating shaft gear ring.

10. The propeller-powered three-dimensional spatial attitude test platform as described in claim 9, characterized in that: The rotating gear ring (26) includes a first gear ring, which is connected to a first rotating shaft (25). The third brake part (22) includes a second brake disc (27) and a third brake (28). The second brake disc (27) is coaxially arranged with the first gear ring, and the second brake disc (27) is inserted into the third brake (28).

Images