Small aircraft wing static test tool

Abstract

The utility model discloses a small aircraft wing static test tool which comprises a support frame, two sides of the support frame are respectively provided with a load station and an angle control station, the horizontal height of the load station is higher than that of the angle control station, the angle control station is provided with an angle control frame, the angle control frame is connected with a wing, and the wing is connected with the support frame. According to the invention, the adjustment of the horizontal angle of the wing is realized through the angle control frame, and the simulation of the actual state of the wing in flight is realized, so that the static force measurement precision is improved.

Description

Technical Field

[0001] The utility model relates to the field of general aircraft test tooling, in particular to a static test tooling for the wing of a small aircraft. Background Technique

[0002] The aircraft wing is one of the important components of the aircraft. Its stiffness plays a crucial role in the flight performance, stability and safety of the aircraft. The wing static test is an important method to evaluate the stiffness performance of the wing. The purpose is to measure the deformation amount and deformation shape of the wing when it is subjected to a certain load, and analyze the stiffness performance of the wing by means of numerical analysis, etc. Since the wing will have an amplitude during actual flight, resulting in a deflection between the angle of the wing and the horizontal plane, how to simulate whether the static force borne by the wing at different angles meets the standard requirements is a problem that the manufacturer needs to solve. In response to this need, this application proposes a solution. Summary of the Invention

[0003] Purpose of the utility model: The purpose of the utility model is to provide a static test tooling for the wing of a small aircraft, which is used to measure the value of the static force that the wing can withstand at different angles, and improve the measurement accuracy at the same time.

[0004] Technical solution: A static test tooling for the wing of a small aircraft described in the utility model includes a support frame. Load stations and angle control stations are respectively arranged on both sides of the support frame. The horizontal height of the load station is higher than that of the angle control station. An angle control frame is arranged on the angle control station. The angle control frame is connected to the wing to adjust the angle between the wing and the horizontal plane.

[0005] Preferably, a load steel plate is arranged on the load station, and a weight for balancing the wing load is arranged on the load steel plate.

[0006] The setting of the load station is used for the wing to be loaded with load when the load is applied. The load station is also loaded with load to balance the gravity on both sides of the support frame and prevent the entire tooling from tipping over during the measurement process.

[0007] Preferably, the angle control frame includes a tension positioning structure and a compression positioning structure arranged opposite to each other on both sides of the angle control station. The compression positioning structure is located on one side of the edge of the support frame, and the tension positioning structure is located on one side close to the load station. A wing beam of the wing passes through the compression U-shaped clamping plate in the compression positioning structure and the tension U-shaped clamping plate in the tension positioning structure, and the wing beam is fixed on the compression U-shaped clamping plate and the tension U-shaped clamping plate through positioning pins.

[0008] The wing beam of the wing is fixed by a compression U-shaped splint and a tension U-shaped splint, so that the angle between the wing beam and the horizontal plane is completely controlled by the compression U-shaped splint and the tension U-shaped splint, and thus the angle between the entire wing and the horizontal plane is controlled by the compression U-shaped splint and the tension U-shaped splint.

[0009] Preferably, the compression positioning structure includes a bottom plate 1 and a compression U-shaped splint. The bottom plate 1 is fixed on the support frame by bolts, and the compression U-shaped splint is fixed on the bottom plate 1 by bolts. The wing beam passes through the U-shaped opening of the compression U-shaped splint and is fixed in the U-shaped opening of the compression U-shaped splint by a positioning pin.

[0010] Preferably, the tension positioning structure includes a bottom plate 2 and a tension U-shaped splint. The bottom plate 2 is fixed on the support frame by bolts, and the tension U-shaped splint is fixed on the bottom plate 2 by bolts. The wing beam passes through the U-shaped opening of the tension U-shaped splint and is fixed in the U-shaped opening of the tension U-shaped splint by a positioning pin.

[0011] Preferably, the angle between the U-shaped opening of the compression U-shaped splint and the tension U-shaped splint and the horizontal plane is customized according to the measurement requirements and kept consistent, and the range of the angle is between 90° and 103.31°.

[0012] The setting of the angle between the U-shaped opening and the horizontal plane between 90° and 103.31° ensures that the entire tooling can simulate all the angles formed between the wing and the horizontal plane during actual flight.

[0013] Preferably, a torsion receiving mechanism is further provided at the angle control station. The torsion receiving mechanism includes a bracket, a fixing plate and a torsion receiving joint. The bracket is fixedly arranged on the support frame, the fixing plate is fixedly connected to the bracket by bolts, and the torsion receiving joint is fixedly connected to the fixing plate by bolts. The torsion receiving joint is fixedly connected to the connecting head in the wing.

[0014] After the torsion receiving joint is fixedly connected to the connecting head, it is ensured that when the wing bears a load, the wing is prevented from being further twisted by the force, resulting in the inconsistency between the actual angle of the wing and the angle controlled by the compression U-shaped splint and the tension U-shaped splint.

[0015] Beneficial effects: Compared with the prior art, the present invention has the following advantages:

[0016] (1). In this application, the adjustment of the horizontal angle of the wing is realized through the adjustable tension U-shaped splint and compression U-shaped splint, and the simulation of the actual state of the wing during flight is realized.

[0017] (2) By setting the torsion-resistant mechanism in this application, the further torsional deformation of the wing after loading is prevented, ensuring that the angle between the wing and the horizontal plane is only controlled by the tension U-shaped splint and the compression U-shaped splint, thereby improving the measurement accuracy. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a three-dimensional view of one angle of the present utility model.

[0019] Figure 2 It is a front view of the present utility model.

[0020] Figure 3 It is a left view of the present utility model.

[0021] Figure 4 It is a three-dimensional structure diagram of the present utility model when the wing is installed.

[0022] Figure 5 It is a three-dimensional mechanism diagram of the wing.

[0023] Wherein: 100, support frame; 200, angle control frame; 300, wing; 400, load steel plate; 210, tension positioning structure; 211, tension U-shaped splint; 212, bottom plate two; 220, compression positioning structure; 221, compression U-shaped splint; 222, bottom plate one; 230, torsion-resistant mechanism; 231, support; 232, fixing plate; 233, torsion-resistant joint; 301, wing beam; 302, connecting head. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0024] The technical solution of the present utility model will be further described below with reference to the drawings.

[0025] Referring to the attached Figures 1 to 5 figure, the small aircraft wing static test tooling shown in the present utility model includes a support frame 100. A load station and an angle control station are respectively arranged on both sides of the support frame 100. The horizontal height of the load station is higher than that of the angle control station. An angle control frame 200 is arranged at the angle control station. The angle control frame 200 is connected to the wing 300 to adjust the angle between the wing 300 and the horizontal plane.

[0026] In this embodiment, a load steel plate 400 is arranged at the load station, and a load for balancing the load of the wing 300 is arranged on the load steel plate 400. Such a setting is used to load the load on the load station when the wing 300 is loaded, balance the gravity on both sides of the support frame 100, and prevent the entire tooling from tipping over during the measurement process.

[0027] In this embodiment, the angle control frame 200 includes a tension positioning structure 210 and a compression positioning structure 220 which are opposed to each other on both sides of the angle control station. The compression positioning structure 220 is located on one side of the edge of the support frame 100, and the tension positioning structure 210 is located on the side close to the load station. A wing beam 301 of the wing 300 passes through the compression U-shaped clamping plate 221 in the compression positioning structure 220 and the tension U-shaped clamping plate 211 in the tension positioning structure 210, and the wing beam 301 is fixed on the compression U-shaped clamping plate 221 and the tension U-shaped clamping plate 211 by positioning pins.

[0028] The wing beam 301 of the wing 300 is fixed by the compression U-shaped clamping plate 221 and the tension U-shaped clamping plate 211, so that the angle between the wing beam 301 and the horizontal plane is completely controlled by the compression U-shaped clamping plate 221 and the tension U-shaped clamping plate 211, and thus the angle between the entire wing 300 and the horizontal plane is controlled by the compression U-shaped clamping plate 221 and the tension U-shaped clamping plate 211.

[0029] In this embodiment, the compression positioning structure 220 includes a bottom plate one 222 and a compression U-shaped clamping plate 221. The bottom plate one 222 is fixed on the support frame 100 by bolts, and the compression U-shaped clamping plate 221 is fixed on the bottom plate one 222 by bolts. The wing beam 301 passes through the U-shaped opening of the compression U-shaped clamping plate 221 and is fixed in the U-shaped opening of the compression U-shaped clamping plate 221 by a positioning pin.

[0030] In this embodiment, the tension positioning structure 210 includes a bottom plate two 212 and a tension U-shaped clamping plate 211. The bottom plate two 212 is fixed on the support frame 100 by bolts, and the tension U-shaped clamping plate 211 is fixed on the bottom plate two 212 by bolts. The wing beam 301 passes through the U-shaped opening of the tension U-shaped clamping plate 211 and is fixed in the U-shaped opening of the tension U-shaped clamping plate 211 by a positioning pin.

[0031] In this embodiment, the included angle between the U-shaped openings of the compression U-shaped clamping plate 221 and the tension U-shaped clamping plate 211 and the horizontal plane is customized according to the measurement requirements and kept consistent. The range of the included angle is between 90° and 103.31°. Setting the included angle in this interval can ensure that the entire tooling can simulate all the angles formed between the wing 300 and the horizontal plane during actual flight.

[0032] In this embodiment, a torsion-receiving mechanism 230 is further provided on the angle control station 200. The torsion-receiving mechanism 230 includes a bracket 231, a fixing plate 232, and a torsion-receiving joint 233. The bracket 231 is fixedly arranged on the support frame 100. The fixing plate 232 is fixedly connected to the bracket 231 by bolts. The torsion-receiving joint 233 is fixedly connected to the fixing plate 232 by bolts. The torsion-receiving joint 233 is fixedly connected to the connecting head 302 in the wing 300. After the torsion-receiving joint 233 is fixedly connected to the connecting head 302, when the wing 300 bears a load, it can prevent the wing 300 from being further twisted by the force, resulting in the actual angle of the wing 300 being inconsistent with the angle controlled by the compression U-shaped clamp 221 and the tension U-shaped clamp 211.

[0033] When this application is in operation, after the operator determines the angle at which the wing 300 needs to be inclined during this measurement, the compression U-shaped clamp 221 and the tension U-shaped clamp 211 that are consistent with the set angle are selected. The wing beam 301 of the wing 300 is placed into the U-shaped opening in the compression U-shaped clamp 221 and the tension U-shaped clamp 211. After positioning with the positioning pin, the connecting head 302 in the wing 300 is fixedly connected to the torsion-receiving joint 233. After the connection between the wing 300 and the tooling is completed, set loads are respectively applied to the load steel plate 400 and the wing 300. The operator records the state of the wing 300 at this time. After the recording is completed, the load is removed, and the wing 300 is removed from the tooling. The angle at which the wing 300 needs to be inclined for the next measurement is determined, and the corresponding compression U-shaped clamp 221 and tension U-shaped clamp 211 are replaced, and the above operations are repeated until all the different state data of the wing 300 under different inclination angles and loads are measured.

Claims

1. A small aircraft wing static test tool, including a support frame, characterized in that: A load station and an angle control station are respectively arranged on both sides of the support frame. The horizontal height of the load station is higher than that of the angle control station. An angle control frame is arranged on the angle control station. The angle control frame is connected to the wing to adjust the angle between the wing and the horizontal plane.

2. A small aircraft wing static test tool according to claim 1, characterized in that: A load steel plate is arranged on the load station, and a weight for balancing the wing load is arranged on the load steel plate.

3. The small aircraft wing static test tool according to claim 1, characterized in that: The angle control frame includes a tension positioning structure and a compression positioning structure which are opposite to each other on both sides of the angle control station. The compression positioning structure is located on one side of the edge of the support frame, and the tension positioning structure is located on the side close to the load station. The compression U-shaped clamp in the compression positioning structure and the tension U-shaped clamp in the tension positioning structure penetrate the wing beam of the wing, and the wing beam is fixed to the compression U-shaped clamp and the tension U-shaped clamp by positioning pins.

4. A small aircraft wing static test tool as claimed in claim 3, characterized in that: The pressure-bearing positioning structure includes a base plate 1 and a pressure-bearing U-shaped clamp. The base plate 1 is fixed to the support frame by bolts, and the pressure-bearing U-shaped clamp is fixed to the base plate 1 by bolts. The wing beam passes through the U-shaped opening of the pressure-bearing U-shaped clamp and is fixed in the U-shaped opening of the pressure-bearing U-shaped clamp by a positioning pin.

5. The small aircraft wing static test tool according to claim 3, characterized in that: The tension positioning structure includes a base plate 2 and a tension U-shaped clamp. The base plate 2 is fixed to the support frame by bolts, and the tension U-shaped clamp is fixed to the base plate 2 by bolts. The wing beam passes through the U-shaped opening of the tension U-shaped clamp and is fixed in the U-shaped opening of the tension U-shaped clamp by a positioning pin.

6. The small aircraft wing static test tool according to claim 3, characterized in that: The angles between the U-shaped openings in the compression U-shaped splint and the tension U-shaped splint and the horizontal plane are customized according to the measurement requirements and remain consistent, and the range of the angles is between 90° and 103.31°.

7. The small aircraft wing static test tool according to claim 1, characterized in that: The angle control station is also provided with a torsion mechanism, which includes a bracket, a fixing plate and a torsion joint. The bracket is fixedly arranged on the support frame, the bracket is fixedly connected with a fixing plate by bolts, the fixing plate is fixedly connected with a torsion joint by bolts, and the torsion joint is fixedly connected to a connecting head in the wing.

Images