A lifting flight test fixture for a compound wing configuration aircraft

Abstract

The utility model discloses a kind of hoisting test flight tooling of composite wing configuration aircraft, including main frame, base, lifting eye and lifting eye limiting assembly, main frame is the rectangular frame structure formed by the butt joint of two longitudinal beams and two cross beams. Base has main frame connecting portion and aircraft connecting portion. Lifting eye has perforation and the lifting eye is set on the lifting hole and locking hole above perforation, and lifting eye is movably set on the cross beam of main frame by its perforation. Lifting eye limiting assembly includes limiting rod and locking piece, limiting rod is arranged on the side of the cross beam of main frame, and a plurality of limiting teeth are arranged on limiting rod along its length direction, and locking piece is used to fix lifting eye and limiting rod together. The lifting appliance of the tooling of the utility model can be quickly disassembled and assembled, and the lifting point position can be flexibly adjusted, so that the test requirements of different configuration or gravity center change aircraft can be adapted.

Description

Technical Field

[0001] This utility model relates to the field of test tooling technology, specifically to a lifting test flight tooling for a compound wing configuration aircraft. Background Technology

[0002] Suspension-based flight testing refers to suspending (or partially restraining) an aircraft using a pylon, crane, or ground tethering device before it achieves full free flight, and conducting tests on the multirotor system's functionality, control laws, and attitude stability under safe and controllable conditions. In the research and testing of compound-wing electric aircraft (i.e., aircraft possessing both fixed-wing and multirotor capabilities), suspension-based flight testing (or "tethered hovering flight testing") in a multirotor configuration is a crucial and common testing method. Its main considerations are as follows:

[0003] 1. By hoisting the aircraft for test flights, it is securely fixed (e.g., by suspending it with ropes), and only the multi-rotor power system is activated for hovering or minor attitude adjustments. This ensures that even if a problem occurs, it will not lead to a free fall.

[0004] 2. In multi-rotor mode, the fixed wings of the aircraft generate almost no lift; all lift and attitude control come from the rotors. This is one of the most unique and complex flight phases for compound wing aircraft. The lift-up test flight is the first step in verifying the design goals for this phase.

[0005] The purpose of hoisting test flights is to verify the stability, controllability, and propulsion of the compound-wing electric aircraft under conditions that prevent it from crashing. Only after confirming safety and reliability through hoisting (or tethering) test flights will it proceed to free hovering flight, then transitional flight, and finally full-mode conversion flight. Therefore, the tooling for hoisting test flights is crucial.

[0006] Reference 1: Chinese patent document with publication number CN223132380U.

[0007] Reference 1 discloses a UAV hoisting test device, including two clamps for fixing the UAV, upper and lower clamps connected to a boom, the upper end of the boom connected to the front end of a safety rope with a safety length, the safety rope passing through a pulley installed on a crossbeam, the rear end of the safety rope connected to a take-up and release reel on a motor, the motor rotating to control the take-up and release of the safety rope, a linear displacement sensor connected to the upper end of the boom, the linear displacement sensor monitoring the distance and speed of the boom's movement, and controlling the motor to take up and release the safety rope, the length and speed of the safety rope taken up and released by the motor being the same as the distance and speed of the boom's movement monitored by the linear displacement sensor, the device is equipped with an emergency button, when the emergency button is pressed, the UAV ground control station receives a signal to control the UAV to stop propellers, the motor quickly retracts the safety rope to the safety length, and the safety rope slowly lifts the UAV to the initial test position.

[0008] However, the aforementioned flight test device has only one lifting point, and the position of the lifting point cannot be adjusted, which cannot meet the testing requirements of aircraft with different configurations or changes in center of gravity. Utility Model Content

[0009] The purpose of this invention is to solve the aforementioned technical problems in the prior art and to provide a lifting and test flight fixture for a compound wing configuration aircraft.

[0010] To solve the above-mentioned technical problems, the technical solution adopted by this utility model is: a lifting and test flight fixture for a compound wing configuration aircraft, comprising:

[0011] The main frame is a rectangular frame structure formed by the joining of two longitudinal beams and two transverse beams; and

[0012] The base has a main frame connecting part and an aircraft connecting part, as well as

[0013] The lifting ring has a through hole and a lifting hole and a locking hole above the through hole, and the lifting ring is movably fitted onto the crossbeam of the main frame through the through hole; and

[0014] The lifting ring limiting assembly includes a limiting rod and a locking component. The limiting rod is located on one side of the crossbeam of the main frame, and several limiting teeth are provided on the limiting rod along its length. The locking component is used to fix the lifting ring and the limiting rod together.

[0015] As a further optimization of the lifting and test flight fixture for a compound wing configuration aircraft of this utility model: the two ends of the crossbeam of the main frame are respectively provided with connecting plates for connecting the base, and the connecting plates are provided with four elongated holes.

[0016] As a further optimization of the lifting and test flight fixture for a compound wing configuration aircraft of this utility model: the base includes an aircraft connecting plate and a main frame connecting plate that are perpendicular to each other. The main frame connecting plate is provided with four elongated holes, and the aircraft connecting plate is provided with four round holes.

[0017] As a further optimization of the lifting and test flight fixture for a compound wing configuration aircraft of this utility model: the base also includes two side plates, the side edges and bottom edges of which are fixedly connected to the main frame connecting plate and the aircraft connecting plate, respectively.

[0018] As a further optimization of the lifting and test flight fixture for a composite wing configuration aircraft of this utility model: a damping pad is also provided on the lower end face of the aircraft connecting plate.

[0019] As a further optimization of the lifting and test flight fixture for a compound wing configuration aircraft of this utility model: two lifting rings are fitted on each crossbeam of the main frame.

[0020] As a further optimization of the lifting and test flight fixture for a compound wing configuration aircraft according to this utility model: the lifting ring is provided with two locking holes.

[0021] As a further optimization of the lifting and test flight fixture for a compound wing configuration aircraft of this utility model: the limiting rod is mounted between two longitudinal beams, and the limiting teeth are set on the upper end face of the limiting rod.

[0022] As a further optimization of the lifting and test flight fixture for a compound wing configuration aircraft according to this utility model: the locking component is a steel cable.

[0023] As a further optimization of the lifting and test flight fixture for a composite wing configuration aircraft of this utility model: the main frame is made of steel profile, and the longitudinal beams and the transverse beams are welded together.

[0024] This utility model has the following beneficial effects:

[0025] 1. The tooling of this utility model can withstand the total weight of the aircraft plus dynamic load, ensuring that it will not break, deform or fall off accidentally;

[0026] 2. The lifting point design of this utility model tooling is reasonable, simulating the center of gravity of the aircraft, avoiding excessive tilting torque after lifting, which would affect the balance and control of the multi-rotor system;

[0027] 3. The lifting device of this utility model can be quickly disassembled and assembled, and the position of the lifting point can be flexibly adjusted, so as to adapt to the testing needs of aircraft with different configurations or changes in center of gravity. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the structure of the lifting test flight fixture of this utility model in the working state;

[0029] Figure 2 This is a schematic diagram of the structure of the lifting test flight fixture of this utility model;

[0030] Figure 3 This is a structural schematic diagram of the main frame of the lifting test flight fixture of this utility model;

[0031] Figure 4 This is a schematic diagram of the base structure in the lifting test flight fixture of this utility model;

[0032] Figure 5 This is a schematic diagram of the lifting ring in the lifting test flight tool of this utility model;

[0033] Figure 6 This is a schematic diagram of the lifting ring in the locked state of the lifting test flight tool of this utility model;

[0034] The following are the labeling elements in the diagram: 1. Main frame; 101. Longitudinal beam; 102. Crossbeam; 103. Connecting plate; 2. Base; 201. Aircraft connecting plate; 202. Main frame connecting plate; 203. Side plate; 204. Damping pad; 3. Lifting ring; 301. Drill hole; 302. Lifting hole; 303. Locking hole; 4. Lifting ring limiting assembly; 401. Limiting rod; 402. Locking component. Detailed Implementation

[0035] To better understand this utility model, the following embodiments further illustrate the content of this utility model, but the content of this utility model is not limited to the following embodiments.

[0036] like Figure 1 and 2 As shown, a lifting and flight test fixture for a compound wing configuration aircraft, through modular design and adjustable structure, meets the safe lifting and flight test requirements of aircraft with different configurations and changing centers of gravity. The lifting and flight test fixture includes a main frame 1, four bases 2, four lifting rings 3, and four lifting ring limiting components 4.

[0037] like Figure 3 As shown, the main frame 1 is welded from high-strength steel profiles and is formed by connecting two longitudinal beams 101 and two transverse beams 102 to form a rectangular frame. The steel profiles are made of Q355B material, and the welding joints adopt a full welding process to ensure that the tooling can withstand the total weight of the aircraft and dynamic loads, and to avoid breakage and deformation during flight testing.

[0038] The two ends of the crossbeam 102 are symmetrically welded with connecting plates 103. Each connecting plate 103 has four elongated holes. The design of the elongated holes allows the base 2 to adjust its installation position within a certain range along the length of the crossbeam 102, adapting to the fuselage size of different aircraft.

[0039] like Figure 4 As shown, the base 2 is an integrated welded structure, including mutually perpendicular aircraft connecting plates 201 and main frame connecting plates 202, as well as two triangular side plates 203. The four elongated holes on the main frame connecting plate 202 correspond to the elongated holes on the crossbeam 102 connecting plate 103, and are locked with high-strength bolts to achieve a detachable connection between the base 2 and the main frame 1, and the front and rear positions of the base can be finely adjusted.

[0040] The four round holes on the aircraft connecting plate 201 are used for bolt fixing to the pre-set connection points on the aircraft fuselage to ensure a stable connection. The side of the side plate 203 is fully welded to the main frame connecting plate 202 and the bottom edge is fully welded to the aircraft connecting plate 201 to form a stable triangular structure, which improves the overall rigidity of the base and prevents deformation under stress.

[0041] A silicone damping pad 204 is attached to the lower end face of the aircraft connecting plate 201. During test flights, it can buffer aircraft vibrations and prevent damage caused by hard contact between the fuselage and the tooling. At the same time, the damping is made of a flexible material, which can ensure a good fit between the flat surface (connector) and the curved surface (wing surface), reducing the impact of gaps on connection strength and damage to the wing surface.

[0042] Two lifting rings 3 are movably fitted onto each crossbeam 102. A through hole 301 (2mm larger in diameter than the crossbeam's cross-section) is formed in the center of each lifting ring 3 to ensure smooth sliding along the crossbeam 102. A lifting hole 302 is formed at the top of each lifting ring 3 for connecting a hook or cable to the lifting equipment. The inner wall of the lifting hole is chamfered to reduce stress concentration during lifting.

[0043] like Figure 5 As shown, two locking holes 303 are provided on the side of the lifting ring 3, symmetrically distributed on both sides of the through hole 301, for use with the locking component 402 to fix and limit the lifting ring. The double lifting ring design can be used in combination to precisely match the aircraft's center of gravity position and avoid tilting torque after lifting.

[0044] like Figure 6 As shown, the lifting ring limiting assembly 4 includes a limiting rod 401 and a locking element 402. The limiting rod 401 is mounted between two longitudinal beams 101 and parallel to the transverse beam 102. Its upper end face is evenly provided with several limiting teeth along its length, forming a precise positioning scale. The locking element 402 is made of high-strength steel cable. After passing through the locking hole 303 of the lifting ring 3, the cable is wound and locked onto the limiting teeth of the limiting rod 401. The preload of the cable fixes the lifting ring 3 to the limiting rod 401, preventing displacement of the lifting ring during flight testing. Combined with the sliding of the lifting ring along the transverse beam 102, the lifting point can be flexibly adjusted within the main frame 1, meeting the flight testing requirements of aircraft with different configurations and changing centers of gravity.

[0045] During assembly, first adjust the mounting position of base 2 on the main frame 1 according to the aircraft's fuselage size and center of gravity, and then lock base 2 to the main frame 1 with bolts. Next, fix the aircraft fuselage to the aircraft connecting plate 201 with bolts, and ensure the damping pad 204 fits against the fuselage surface. Then, slide the lifting ring 3 to the preset lifting point position, pass a steel cable through the locking hole 303 and wrap it around the corresponding limiting tooth of the limiting rod 401, and tighten the steel cable to complete the lifting ring positioning. Finally, connect the hook of the lifting equipment to the lifting hole 302 of the lifting ring 3, and the lifting test flight can begin.

[0046] This utility model's lifting test flight fixture, through structural optimization and functional coordination of its components, ensures both the strength and stability of the fixture, while also enabling rapid adjustment and precise positioning of the lifting point. It effectively simulates the aircraft's center of gravity, avoids the influence of tilting torque on the balance control of the multi-rotor system, and fully meets the safety and functional verification requirements for lifting test flights of compound wing configuration aircraft.

[0047] The specific embodiments of this utility model have been described above. It should be understood that this utility model is not limited to the specific embodiments described above, and those skilled in the art can make various modifications or variations within the scope of the claims, which do not affect the substantive content of this utility model.

Claims

1. A lifting and test flight fixture for a compound wing configuration aircraft, characterized in that, include: The main frame (1) is a rectangular frame structure formed by the joint of two longitudinal beams (101) and two transverse beams (102); as well as The base (2) has a main frame connecting part and an aircraft connecting part, and The lifting ring (3) has a through hole (301) and a lifting hole (302) and a locking hole (303) provided above the through hole (301). The lifting ring (3) is movably fitted onto the crossbeam (102) of the main frame (1) through its through hole (301); and The lifting ring limiting assembly (4) includes a limiting rod (401) and a locking member (402). The limiting rod (401) is located on one side of the crossbeam (102) of the main frame (1). Several limiting teeth are provided on the limiting rod (401) along its length direction. The locking member (402) is used to fix the lifting ring (3) and the limiting rod (401) together.

2. The lifting and test flight fixture for a compound wing configuration aircraft as described in claim 1, characterized in that: The main frame (1) has connecting plates (103) at both ends of the crossbeam (102) for connecting the base (2), and the connecting plates (103) have four elongated holes.

3. The lifting and test flight fixture for a compound wing configuration aircraft as described in claim 2, characterized in that: The base (2) includes an aircraft connecting plate (201) and a main frame connecting plate (202) that are perpendicular to each other. The main frame connecting plate (202) is provided with four elongated holes, and the aircraft connecting plate (201) is provided with four round holes.

4. The lifting and test flight fixture for a compound wing configuration aircraft as described in claim 3, characterized in that: The base (2) also includes two side plates (203), the side and bottom edges of which are fixedly connected to the main frame connecting plate (202) and the aircraft connecting plate (201), respectively.

5. The lifting and test flight fixture for a compound wing configuration aircraft as described in claim 3, characterized in that: The lower end face of the aircraft connecting plate (201) is also provided with a damping pad (204).

6. The lifting and test flight fixture for a compound wing configuration aircraft as described in claim 1, characterized in that: Two lifting rings (3) are fitted on each crossbeam (102) of the main frame (1).

7. The lifting and test flight fixture for a compound wing configuration aircraft as described in claim 1, characterized in that: The lifting ring (3) is provided with two locking holes (303).

8. The lifting and test flight fixture for a compound wing configuration aircraft as described in claim 1, characterized in that: The limiting rod (401) is mounted between two longitudinal beams (101), and the limiting teeth are located on the upper end face of the limiting rod (401).

9. The lifting and test flight fixture for a compound wing configuration aircraft as described in claim 1, characterized in that: The locking element (402) is a steel cable.

10. The lifting and test flight fixture for a compound wing configuration aircraft as described in claim 1, characterized in that: The main frame (1) is made of steel profiles, and the longitudinal beams (101) and the transverse beams (102) are welded together.

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