An aircraft take-off and landing simulation test device based on a horizontal opening wind tunnel

Abstract

The invention discloses an aircraft take-off and landing simulation test device based on a horizontal open wind tunnel, comprising a driving unit, an angle-changing mechanism, a base, a side-mounted floor, a strain balance and an aircraft model. The base is placed on the ground of the open wind tunnel, the side-mounted floor is opposite to the base and is placed relatively, the driving unit is installed on the base, the action mechanism of the driving unit can move along a translation direction according to a given setting, the angle-changing mechanism is connected to the action mechanism of the driving unit, the angle-changing mechanism can change the pitch angle along the incoming flow direction of the open wind tunnel, and the aircraft model is connected to the angle-changing mechanism through a strain balance; the aircraft model realizes the change of the angle of attack as the angle-changing mechanism moves, and at the same time moves with the action mechanism of the driving unit, so as to simulate the step-like change of speed during the take-off and landing process. The invention can simulate the influence of the dynamic ground effect on the aerodynamic characteristics of the aircraft during the take-off and landing process, provide the necessary technical guarantee for the safe flight of the aircraft, and improve the authenticity of the aerodynamic test.

Description

Technical Field

[0001] The invention relates to wind tunnel test equipment, in particular to an aircraft take-off and landing simulation test device based on a horizontal opening wind tunnel. Background Art

[0002] From the perspective of flight safety, the takeoff, landing and go-around of an aircraft are usually the most accident-prone stages. For different aircraft types, the takeoff and landing conditions are different, and the aerodynamic characteristics are also different. The dynamic ground effect has the greatest impact on the aerodynamic characteristics. The dynamic ground effect has a significant impact on the angle of attack, lift, drag and wash flow field during close-to-ground flight. With the advancement of technology, the take-off and landing methods of modern aircraft are different from those of old aircraft. For example, the heave and sink speed of aircraft using thrust vectoring to assist take-off and landing is much greater than that of old aircraft. Existing research results show that the heave and sink speed during take-off and landing is greatly affected by the dynamic ground effect, which directly affects the strength of the landing gear and the load design of the entire aircraft. The dynamic ground effect causes the aircraft's lift, drag, pitch moment and other aerodynamic forces and flow field structures to change dramatically, and presents strong nonlinear characteristics. Since the aircraft is generally at the edge of the stall angle of attack or stall speed during take-off and landing, if the nonlinear aerodynamic changes during take-off and landing cannot be accurately measured, the flight control system may issue a counter-effect command, which may cause the aircraft to enter the stall speed or stall angle of attack, causing flight accidents and affecting the safety of aircraft take-off and landing. Therefore, there is a need for an aircraft take-off and landing simulation test device based on a horizontal opening wind tunnel to study the influence of dynamic ground effect on the aerodynamic characteristics of the aircraft during take-off and landing. Summary of the invention

[0003] In view of the above shortcomings, the purpose of the present invention is to provide an aircraft take-off and landing simulation test device based on a horizontal opening wind tunnel, which is used to simulate the influence of dynamic ground effect on the aerodynamic characteristics of the aircraft during take-off and landing.

[0004] The technical solution of the present invention is: an aircraft take-off and landing simulation test device based on a horizontal open wind tunnel, comprising a driving unit, an angle-changing mechanism, a base, a side-mounted floor, a strain balance and an aircraft model, wherein the aircraft model is fixedly connected to the model end of the strain balance, the base is placed on the ground of the open wind tunnel, the side-mounted floor is used to simulate the ground, and is located opposite to the base and placed relatively, the driving unit is installed on the base, the driving unit can set the oscillation frequency, amplitude and motion mode, and then the action mechanism of the driving unit can move along the translation direction according to the given setting, the angle-changing mechanism is connected to the action mechanism of the driving unit, the angle-changing mechanism can change the pitch angle along the incoming flow direction of the open wind tunnel, and the support rod end of the stress balance is fixedly connected to the angle-changing mechanism; the aircraft model realizes the change of angle of attack as the angle-changing mechanism moves, and at the same time moves with the action mechanism of the driving unit, simulating the step-like change of speed during take-off and landing.

[0005] Furthermore, the driving unit includes a driving base, a hydraulic cylinder assembly, a hydraulic cylinder assembly mounting seat, an ear seat, a heavy-load parallel guide rail assembly, a box-type moving part and four groups of box-type mounting seats. The driving base is fixedly connected to the base, the heavy-load parallel guide rail assembly is mounted on the driving base, the box-type moving part is clamped and fixed in the middle of the four groups of box-type mounting seats, and the four groups of box-type mounting seats are divided into two groups at the front and two groups at the back, which are symmetrically arranged along the central axis of the box-type moving part. The four groups of box-type mounting seats are respectively slidably connected to the heavy-load parallel guide rail assemblies, the hydraulic cylinder assembly mounting seat is fixedly connected to the heavy-load parallel guide rail assembly, the fixed end of the hydraulic cylinder assembly is fixedly connected to the hydraulic cylinder assembly mounting seat, the action end of the hydraulic cylinder assembly is located on one side of the side-mounted floor, the action end of the hydraulic cylinder assembly is hinged to the ear seat, and the ear seat is fixedly mounted on the box-type moving part.

[0006] Furthermore, the box-shaped moving part adopts a hollow structure.

[0007] Furthermore, the angle-changing mechanism includes a support rod, a fork-shaped ear piece, an inner arc tooth, a fan-shaped outer arc tooth, a balance sleeve, a two-way nut and a rotating shaft, one end of the support rod is fixedly connected to the box-shaped moving part, one end of the inner arc tooth is inserted into the other end of the support rod and fixedly connected by a pin shaft, a part of the two-way nut is sleeved on the outer wall surface near the middle section of the inner arc tooth and is threadedly connected to it, and the other part of the two-way nut is sleeved on the outer wall surface of one end of the fork-shaped ear piece and is threadedly fastened to it, one end of the balance sleeve is hinged to the other end of the fork-shaped ear piece through the rotating shaft, the fan-shaped outer arc tooth is fixedly connected to the axial outer wall surface of the balance sleeve, the support rod end of the strain balance is fixedly connected to the balance sleeve, the model end of the strain balance is fixedly connected to the aircraft model, the other end of the inner arc tooth is located inside the fork-shaped ear piece and meshes with the fan-shaped outer arc tooth, and the meshing degree between the inner arc tooth and the fan-shaped outer arc tooth can be adjusted by rotating the two-way nut, thereby adjusting the pitch angle of the balance sleeve along the incoming flow direction of the wind tunnel.

[0008] Furthermore, the angle-changing mechanism also includes a joint and a locking nut, one end of the support rod is connected to the joint by a conical surface and fastened by a locking nut, and the joint is fixedly connected to the box-shaped moving part by a flange.

[0009] Furthermore, the side-mounted floor includes a panel surface and a panel surface mounting seat. The panel surface is made of multiple pieces of lightweight alloy and is used to simulate the ground during aircraft take-off and landing. The panel surface is vertically fixedly connected to the panel surface mounting seat. The panel surface is also fixedly connected to the panel surface mounting seat through a diagonal rod.

[0010] The invention has advantages and beneficial effects. The device can be used in a horizontal open wind tunnel to study the influence of dynamic ground effects on the aerodynamic characteristics of an aircraft during take-off and landing. At the same time, the device can realize the harmonic oscillation motion of translation and pitch coupling or the motion of a given function. Through the device, the parameters of the dynamic ground effect response of the aircraft model during take-off and landing can be measured, and its motion law can be mastered, providing the necessary technical guarantee for the safe flight of the aircraft, and improving the authenticity of the aerodynamic test. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 is a schematic diagram of the device of the present invention;

[0012] Figure 2 It is a front view of the device of the present invention;

[0013] Figure 3 is a side view of the device of the present invention;

[0014] Figure 4 A top view of the device of the present invention;

[0015] Figure 5 A three-dimensional diagram of a driving unit of the present invention;

[0016] Figure 6 A side view of the drive unit of the present invention

[0017] Figure 7 It is a structural diagram of the angle-changing mechanism of the present invention;

[0018] Figure 8 is a cross-sectional view of the angle-changing mechanism of the present invention;

[0019] Example 1

[0020] like Figure 1-4As shown, an aircraft take-off and landing simulation test device based on a horizontal open wind tunnel comprises a driving unit, an angle-changing mechanism, a base 1, a side-mounted floor, a strain balance and an aircraft model. The aircraft model is fixedly connected to the model end of the strain balance. The base 1 is placed on the ground of the open wind tunnel. The base 1 is the installation foundation of the whole device and is welded with steel sections to ensure the stability of the device during movement. In order to facilitate the transportation of the equipment, the base 1 is moved by air flotation. The side-mounted floor is used to simulate the ground and is located opposite to the base. The driving unit is installed on the base. The driving unit can set the oscillation frequency, amplitude and motion mode, and then the action mechanism of the driving unit can move along the translation direction according to the given setting. The angle-changing mechanism is connected to the action mechanism of the driving unit. The angle-changing mechanism can change the pitch angle along the incoming flow direction of the open wind tunnel. The support rod end of the stress balance is fixedly connected to the angle-changing mechanism. The aircraft model changes the angle of attack as the angle-changing mechanism moves and moves as the action mechanism of the driving unit to simulate the step-like change of speed during take-off and landing. The motion indicators of the test device are: model oscillation frequency f = 2.4 Hz; model oscillation amplitude A = ±500 mm.

[0021] like Figure 5 As shown, the driving unit includes a driving base 2, a hydraulic cylinder assembly 4, a hydraulic cylinder assembly mounting seat 5, an ear seat 8, a heavy-load parallel guide rail assembly 16, a box-shaped moving part 3 and four groups of box-shaped mounting seats 17. The driving base 2 is fixedly connected to the base 1, and the heavy-load parallel guide rail assembly 16 is mounted on the driving base 2. The box-shaped moving part 3 is clamped and fixed in the middle of the four groups of box-shaped mounting seats 17. The box-shaped moving part 3 adopts a hollow structure to ensure the rigidity requirements of the moving parts and meet the requirements of light weight of the moving parts. In order to ensure the stability of the moving parts during the test, the four groups of box-shaped mounting seats 17 are divided into two groups at the front and rear and are symmetrically arranged along the central axis of the box-shaped moving part 3, so as to truly simulate the take-off and landing process of the aircraft. The state changes during the process, the device needs to realize the rapid change of the aircraft model at a large speed in a very short time, and at the same time, it needs to have the ability to withstand strong impact loads. Therefore, a heavy-duty guide rail assembly 16 that can realize rapid movement and withstand large impact loads is selected, and the four groups of box-shaped mounting seats 17 are respectively slidably connected to the heavy-duty parallel guide rail assembly 16, and the two sides of the hydraulic cylinder assembly mounting seat 5 are respectively fixedly connected to the heavy-duty parallel guide rail assembly 16 by hexagon socket bolts 6. The fixed end of the hydraulic cylinder assembly 4 is fixedly connected to the hydraulic cylinder assembly mounting seat 5, and the action end of the hydraulic cylinder assembly 4 is located on the side of the side mounting floor. The action end of the hydraulic cylinder assembly 4 is hinged with the ear seat 8 with adjustable angle deviation through the pin shaft 7, and the ear seat 8 is fixedly mounted on the box-shaped moving part 3. The hydraulic cylinder assembly 4 can realize the harmonic oscillation motion or given function motion of the aircraft model along the translation direction, and at the same time has the characteristics of large output and no gap.

[0022] like Figure 6-7 As shown, the angle-changing mechanism includes a support rod 11, a fork-shaped ear piece 20, an inner arc tooth 13, a fan-shaped outer arc tooth 21, a balance sleeve 23, a two-way nut 19, a rotating shaft 22, a joint 9 and a locking nut 10. One end of the support rod 11 is connected to the joint 9 by a conical surface and is fastened by the locking nut 10. The joint 9 is fixedly connected to the box-shaped moving part 3 by a flange. One end of the inner arc tooth 13 is inserted into the other end of the support rod 11 and is fixedly connected by a pin 12. A part of the two-way nut 19 is sleeved on the outer wall surface near the middle section of the inner arc tooth 13 and is threadedly connected thereto. Another part of the two-way nut 19 is sleeved on the outer wall surface of one end of the fork-shaped ear piece 20 and is threadedly fastened thereto. The inner arc tooth 1 The threads on the outer wall surface near the middle section 3 are in opposite directions to the threads on the outer wall surface at one end of the fork-shaped ear piece 20. One end of the balance sleeve 23 is hinged to the other end of the fork-shaped ear piece 20 through the rotating shaft 22. The fan-shaped outer arc tooth 21 is fixedly connected to the axial outer wall surface of the balance sleeve 23. The support rod end of the strain balance is fixedly connected to the balance sleeve 23. The model end of the strain balance is fixedly connected to the aircraft model. The other end of the inner arc tooth is located inside the fork-shaped ear piece 20 and meshes with the fan-shaped outer arc tooth 21. The meshing degree between the inner arc tooth 13 and the fan-shaped outer arc tooth 21 can be adjusted by rotating the two-way nut 19, thereby adjusting the pitch angle of the balance sleeve 23 along the incoming flow direction of the wind tunnel to achieve the change of the angle of attack of the aircraft model.

[0023] like Figure 1-4 As shown, the side-mounted floor comprises a panel and a panel mounting seat. The panel 15 is made of multiple pieces of light alloy and is used to simulate the ground during the take-off and landing of the aircraft. The panel 15 is vertically mounted on the panel mounting seat 18. The panel mounting seat 18 is made of channel steel welded horizontally and vertically. In order to prevent the panel 15 from tilting during the wind tunnel blowing test, it is reinforced and supported by the inclined rod 14. One end of the inclined rod 14 is connected to the panel 15, and the other end is connected to the panel mounting seat 18. In order to facilitate test preparation and on-site transportation, the panel mounting seat 18 is moved by air flotation.

[0024] like Figure 1 As shown in the figure, the test process is as follows: first, the take-off and landing simulation test device is moved to the specified position in the horizontal open wind tunnel by air flotation, and then the aircraft model is installed. Then, the angle of attack of the aircraft model is adjusted by the variable angle mechanism, and the oscillation frequency, amplitude and motion mode are set by the drive unit. Finally, a dynamic take-off and landing model test of the aircraft model is carried out and the test data is obtained.

Claims

1. An aircraft take-off and landing simulation test device based on a horizontal open wind tunnel, comprising a drive unit, an angle-changing mechanism, a base, a side-mounted floor, a strain balance and an aircraft model, wherein the aircraft model is fixedly connected to the model end of the strain balance, the base is placed on the ground of the open wind tunnel, the side-mounted floor is used to simulate the ground, and is located opposite to the base and placed oppositely, the drive unit is installed on the base, the drive unit can set the oscillation frequency, amplitude and motion mode, and then the action mechanism of the drive unit can move along the translation direction according to the given setting, the angle-changing mechanism is connected to the action mechanism of the drive unit, the angle-changing mechanism can change the pitch angle along the incoming flow direction of the open wind tunnel, and the support rod end of the strain balance is fixedly connected to the angle-changing mechanism; the aircraft model realizes the change of the angle of attack as the angle-changing mechanism moves, and at the same time moves with the action mechanism of the drive unit, simulating the step-like change of speed during take-off and landing, characterized in that: The driving unit includes a driving base, a hydraulic cylinder assembly, a hydraulic cylinder assembly mounting seat, an ear seat, a heavy-load parallel guide rail assembly, a box-type moving part and four groups of box-type mounting seats. The driving base is fixedly connected to the base, the heavy-load parallel guide rail assembly is mounted on the driving base, the box-type moving part is clamped and fixed in the middle of the four groups of box-type mounting seats, and the four groups of box-type mounting seats are divided into two groups at the front and two groups at the back, and are symmetrically arranged along the central axis of the box-type moving part. The four groups of box-type mounting seats are respectively slidably connected to the heavy-load parallel guide rail assembly, the hydraulic cylinder assembly mounting seat is fixedly connected to the heavy-load parallel guide rail assembly, the fixed end of the hydraulic cylinder assembly is fixedly connected to the hydraulic cylinder assembly mounting seat, the action end of the hydraulic cylinder assembly is located on one side of the side-mounted floor, the action end of the hydraulic cylinder assembly is hinged to the ear seat, and the ear seat is fixedly mounted on the box-type moving part.

2. The aircraft take-off and landing simulation test device based on a horizontal opening wind tunnel according to claim 1, characterized in that: The box-shaped moving part adopts a hollow structure.

3. The aircraft take-off and landing simulation test device based on a horizontal opening wind tunnel according to claim 1 or 2, characterized in that: The angle-changing mechanism comprises a support rod, a fork-shaped ear piece, an inner arc tooth, a fan-shaped outer arc tooth, a balance sleeve, a two-way nut and a rotating shaft, one end of the support rod is fixedly connected to the box-shaped moving part, one end of the inner arc tooth is inserted into the other end of the support rod and fixedly connected by a pin shaft, a part of the two-way nut is sleeved on the outer wall surface near the middle section of the inner arc tooth and is threadedly connected thereto, the other part of the two-way nut is sleeved on the outer wall surface of one end of the fork-shaped ear piece and is threadedly fastened thereto, one end of the balance sleeve is hinged to the other end of the fork-shaped ear piece through the rotating shaft, the fan-shaped outer arc tooth is fixedly connected to the axial outer wall surface of the balance sleeve, the support rod end of the strain balance is fixedly connected to the balance sleeve, the model end of the strain balance is fixedly connected to the aircraft model, the other end of the inner arc tooth is located inside the fork-shaped ear piece and meshes with the fan-shaped outer arc tooth, and the meshing degree between the inner arc tooth and the fan-shaped outer arc tooth can be adjusted by rotating the two-way nut, thereby adjusting the pitch angle of the balance sleeve along the incoming flow direction of the wind tunnel.

4. The aircraft take-off and landing simulation test device based on a horizontal opening wind tunnel according to claim 3, characterized in that: It also includes a joint and a locking nut. One end of the support rod is connected to the joint by a conical surface and is fastened by the locking nut. The joint is fixedly connected to the box-shaped moving part by a flange.

5. The aircraft take-off and landing simulation test device based on a horizontal opening wind tunnel according to claim 1, characterized in that: The side-mounted floor includes a panel and a panel mounting seat. The panel is made of multiple pieces of lightweight alloy and is used to simulate the ground during the take-off and landing of an aircraft. The panel is vertically fixedly connected to the panel mounting seat. The panel is also fixedly connected to the panel mounting seat through a diagonal rod.

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