A test simulation device for aircraft lateral reciprocating motion

Abstract

The present invention discloses a lateral reciprocating motion test simulation device for aircraft, which belongs to the field of aircraft wind tunnel test. The device comprises an aircraft model, a force balance, a pitch angle adjustment unit, an upper support rod, a lower support rod, a lateral motion unit and a turntable base, wherein the lateral motion unit can move in the horizontal direction, the upper end of the upper support rod is provided with a pitch angle adjustment unit, the aircraft model is connected to the pitch angle adjustment unit through the force balance, the pitch angle adjustment unit can adjust the angle in the Y direction to achieve the change of the pitch angle of the aircraft model, the lower end of the upper support rod is meshed with the upper end of the lower support rod and can adjust the angle in the Z direction to achieve the change of the aircraft side slip angle, and the lower end of the lower support rod is fixedly connected to the lateral drive motion unit to achieve the reciprocating oscillating motion of the aircraft model in the horizontal direction. The device has the advantages of simplicity, symmetry and high rigidity, and can realize the measurement test of the differential derivative of the lateral and heading wash flow of models within a large size range.

Description

Technical Field

[0001] The invention belongs to the field of aircraft wind tunnel tests, and in particular relates to an aircraft lateral reciprocating motion test simulation device. Background Art

[0002] The differential dynamic derivative of the lateral and yaw flow is the derivative of the aerodynamic coefficient of the aircraft to the side slip angle rate of the aircraft. It is one of the necessary aerodynamic parameters in the process of aircraft development and is used for aircraft stability analysis and control law design. At present, the main means to obtain the differential dynamic derivative of the lateral and yaw flow include wind tunnel test, numerical simulation, simulation flight or test flight parameter identification, etc. The calculation time required for numerical simulation is long, which is not suitable for the acquisition of a large amount of data, and the calculation method and accuracy in the medium and large angle of attack range still need further research. Simulation flight or test flight means have the disadvantages of high cost, long implementation cycle, safety risks, poor repeatability and low parameter identification accuracy. In addition, in the absence of dynamic derivatives, simulation flight and test flight cannot be carried out safely, so it is not suitable as the main means to obtain dynamic derivatives of the model. Wind tunnel test is the most reliable means to obtain dynamic derivative data, but most wind tunnels currently only have the ability to test angular oscillation dynamic derivatives, and can only obtain composite dynamic derivatives, and lack test methods and test equipment for differential dynamic derivatives of lateral and yaw flow. This is mainly due to technical problems such as insufficient accuracy of the model's lateral translation and greater interference of the support system on the model. Therefore, in response to the demand for differential derivative data of the lateral and heading flow in aircraft development, it is necessary to develop a test simulation device for aircraft lateral reciprocating motion. Summary of the invention

[0003] In view of the above shortcomings, the purpose of the present invention is to provide an aircraft lateral reciprocating motion test simulation device, which is used to carry out aerodynamic characteristics influence research of aircraft lateral heading flow differential derivative test in a wind tunnel, which can reduce the risk of new aircraft flight test and shorten the development cycle of new aircraft.

[0004] The technical solution of the present invention is: a lateral reciprocating motion test simulation device for an aircraft, comprising an aircraft model, a force balance, a pitch angle adjustment unit, an upper support rod, a lower support rod, a lateral motion unit and a turntable base, wherein the lateral motion unit is installed inside the turntable base, and the lateral motion unit can move in a horizontal direction, which is an X direction; the upper end of the upper support rod is installed with a pitch angle adjustment unit; the aircraft model is connected to the pitch angle adjustment unit through the force balance; the pitch angle adjustment unit can adjust the angle in the Y direction to achieve a change in the pitch angle of the aircraft model; the lower end of the upper support rod is meshed with the upper end of the lower support rod and can be relatively fixed after adjusting the angle in the Z direction to achieve a change in the sideslip angle of the aircraft; the lower end of the lower support rod is fixedly connected to the lateral drive motion unit to achieve a reciprocating oscillating motion of the aircraft model in the horizontal direction.

[0005] Furthermore, it also includes a sealing unit, which is located on both sides of the lower support rod near the lower end and is horizontally fixedly connected to the side wall of the lower support rod. When the aircraft model performs horizontal reciprocating motion in the wind tunnel, the sealing unit performs reciprocating motion with the lower support rod to prevent the airflow from moving up and down.

[0006] Furthermore, the pitch angle adjustment unit includes a sleeve, a U-shaped frame, a rocker, an ear-shaped connecting seat, a vertical guide assembly and a vertical actuating cylinder. The aircraft model is installed on the sleeve through a force measuring balance. The middle part of the sleeve is hinged to the U-shaped frame, one end of the sleeve is hinged to the upper end of the rocker, the top end of the upper support rod is fixedly connected to the U-shaped frame, the vertical guide assembly is fixedly connected to the side wall of the upper support rod, the ear-shaped connecting seat is fixedly connected to the sliding unit on the vertical guide assembly, the upper end of the ear-shaped connecting seat is hinged to the lower end of the rocker, and the lower end of the ear-shaped connecting seat is connected to the actuating rod of the actuating cylinder; the actuating cylinder is fixedly connected to the lower end of the vertical guide assembly and to the side wall of the upper support rod.

[0007] Furthermore, the lateral motion unit includes a lower base, two groups of V-shaped seats, two groups of V-shaped sliders, two V-shaped guide rails, a box-shaped support, a traction frame, a lateral drive cylinder assembly and a cylinder seat. The lateral drive cylinder assembly is fixedly connected to the cylinder seat, and the cylinder seat is fixed to the upper bottom surface inside the lower base. The lower base is fixedly connected to the inside of the turntable base. The moving end of the lateral drive cylinder assembly is connected to the traction frame through a hinge joint, and one end of the box-shaped support is fixedly connected to the traction frame. The two V-shaped guide rails are respectively fixed on the inner side walls on both sides of the lower base and are parallel to the driving direction of the lateral drive cylinder assembly. The two groups of V-shaped seats are symmetrically fixedly arranged on the two side walls of the box-shaped support and correspond to the positions of the two V-shaped guide rails. The V-shaped slider is installed between the V-shaped seat and the V-shaped guide rail, and the lower end of the lower support rod is fixedly connected to the box-shaped support.

[0008] Furthermore, a vertical plate is fixedly mounted on the other end of the box-shaped support.

[0009] Furthermore, it also includes an anti-shear body, which is fixedly installed between the lower base and the cylinder seat.

[0010] The present invention has the advantages and beneficial effects. The device can be used to study the influence of differential derivatives of the lateral and yaw flow on the aerodynamic characteristics of the aircraft in the wind tunnel, measure the dynamic performance response parameters of the aircraft, grasp the movement law of the aircraft, and provide necessary technical guarantees for the safe flight of the aircraft. The lateral motion unit produces a continuous, controllable, and precise forced translational motion, which provides the basic conditions for obtaining the differential derivatives of the lateral and yaw flow. It has the characteristics of simplicity, symmetry, and high rigidity. It can effectively control the interference of the supporting equipment on the aerodynamic characteristics of the model, and can realize the measurement test of the differential derivatives of the lateral and yaw flow of models within a large size range, providing more real and stable data for the development of aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 It is a front view of the device of the present invention;

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

[0013] Figure 3 A top view of the device of the present invention; DETAILED DESCRIPTION

[0014] The present invention is further described below with reference to the accompanying drawings:

[0015] Example 1

[0016] like Figure 1-3 As shown, a lateral reciprocating motion test simulation device for an aircraft comprises an aircraft model, a force balance, a pitch angle adjustment unit, an upper support rod 4, a lower support rod 5, a lateral motion unit and a turntable base 19, wherein the lateral motion unit is installed inside the turntable base 19, and the lateral motion unit can move in a horizontal direction, which is the X direction. The upper end of the upper support rod 4 is installed with a pitch angle adjustment unit, and the aircraft model is connected to the pitch angle adjustment unit through the force balance, and the pitch angle adjustment unit can adjust the angle in the Y direction to achieve the change of the pitch angle of the aircraft model. The lower end of the upper support rod 4 is meshed with the upper end of the lower support rod 5 and can be relatively fixed after adjusting the angle in the Z direction to achieve the change of the sideslip angle of the aircraft, and the lower end of the lower support rod 5 is fixedly connected to the lateral drive motion unit to achieve the reciprocating oscillating motion of the aircraft model in the horizontal direction. Among them, the upper end face teeth 6 are embedded in the bottom surface groove of the upper support rod 4, and the lower end face teeth 7 are embedded in the top surface groove of the lower support rod 5. When the sideslip angle needs to be adjusted, the connecting screws of the upper support rod 4 and the lower support rod 5 are disengaged, rotated to the angle required by the test, and locked using the tooth meshing principle to achieve the change of the sideslip angle of the mechanism.

[0017] The pitch angle adjustment unit includes a sleeve, a U-shaped frame 3, a rocker 21, an ear-shaped connection seat 22, a vertical guide assembly 23 and a vertical actuating cylinder 24. The top of the upper support rod 4 is fixedly connected to the U-shaped frame 3. The aircraft model is installed on the sleeve 1 through a force measuring balance. The middle part of the sleeve 1 is connected to the U-shaped frame 3 through a rotating shaft 2. One end of the sleeve 1 is connected to the upper end of the rocker 21 through a rocker shaft 20. The vertical guide assembly 23 is fixedly installed on the side wall of the upper support rod 4 by screws. The sliding unit of the vertical guide assembly 23 is fixedly connected to the ear-shaped connection seat 22. The upper end of the ear-shaped connection seat 22 is hinged to the lower end of the rocker 21. The lower end of the ear-shaped connection seat 22 is connected to the actuating end of the actuating cylinder 24. The actuating cylinder 24 is located at the lower end of the vertical guide assembly 23. The actuating cylinder 24 is fixedly connected to the side wall of the upper support rod 4 through an actuating cylinder mounting seat 25. Under the control of the actuator 24 , the ear-shaped connecting seat 22 performs repeated linear motion under the guidance of the vertical guide assembly 23 , thereby driving the rocker 21 to drag the sleeve 1 around the rotating shaft 2 to change the pitch angle.

[0018] The lateral motion unit includes a lower base 28, two groups of V-shaped seats 29, two groups of V-shaped sliders 33, two V-shaped guide rails 34, a box-shaped support 32, a traction frame 16, a lateral drive cylinder assembly 17 and a cylinder seat 31. The fixed end of the lateral drive cylinder assembly 17 is fixedly connected to the cylinder seat 31, the moving end of the lateral drive cylinder assembly 17 is connected to the hinge head 15, the hinge head 15 is connected to the traction frame 16, one end of the box-shaped support 32 is connected to the traction frame 16, the V-shaped guide rail 34 is arranged on the inner side of the lower base 28, the V-shaped slider 33 made of high-strength and wear-resistant alloy material is installed between the V-shaped seat 29 and the V-shaped guide rail 34, the front and rear two groups of V-shaped seats 29 are symmetrically arranged on the box-shaped support 32, and the vertical plate 18 is installed at the other end of the box-shaped support 32. The cylinder seat 31 is fixed to the upper bottom surface inside the lower base 28, and the lower base 28 is installed inside the turntable base 19. The shear-resistant body 30 is installed between the lower base 28 and the cylinder seat 31 to withstand the lateral shear force generated during the reciprocating operation and switching process of the mechanism.

[0019] This embodiment also includes a sealing unit, including a positioning support plate 26, a thrust seat 9, a protective cover 8, a side cover plate 27, a sealing plate 10 and a roller pair. The positioning support plate 26 is fixed on both sides of the lower support rod 5, and the thrust seat 9 is fixed on the lower support rod 5 through the positioning support plate 26. In order to reduce the impact generated during the lateral reciprocating movement of the mechanism, the protective cover 8 with a buffering function is installed between the thrust seat 9 and the lower support rod 5. The sealing plate 10 is fixed on the thrust seat 9, and the upper and lower sides of the sealing plate 10 are clamped by rollers 14. The rollers 14 are installed on the roller seats 12 through the roller shafts 13. The upper and lower groups of roller seats 12 are respectively installed on the upper cover plate 11 and the turntable 19 to prevent the sealing plate 10 from moving up and down during the movement. The side cover plate 27 covers the sealing plate 10. When the mechanism performs lateral reciprocating movement, the sealing unit moves with the lower support rod 5, which can effectively prevent the airflow from moving up and down during the test.

Claims

1. A test simulation device for lateral reciprocating motion of an aircraft, comprising an aircraft model, a force measuring balance, a pitch angle adjustment unit, an upper support rod, a lower support rod, a lateral motion unit, a shear resistance body, a sealing unit and a turntable base, characterized in that: The lateral motion unit is installed inside the turntable base. The lateral motion unit can move in the horizontal direction, which is the X direction. The upper end of the upper support rod is installed with a pitch angle adjustment unit. The aircraft model is connected to the pitch angle adjustment unit through a force measuring balance. The pitch angle adjustment unit can adjust the angle in the Y direction to achieve the change of the pitch angle of the aircraft model. The lower end of the upper support rod is meshed with the upper end of the lower support rod and can be relatively fixed after adjusting the angle in the Z direction to achieve the change of the aircraft side slip angle. The lower end of the lower support rod is fixedly connected to the lateral drive motion unit to achieve the change of the aircraft model in the horizontal direction. The sealing unit is located on both sides of the lower support rod near the lower end and is fixedly connected to the lower support rod horizontally. When the aircraft model performs lateral reciprocating motion in the horizontal direction in the wind tunnel, the sealing unit performs reciprocating following motion with the lower support rod to prevent the airflow from moving up and down. The pitch angle adjustment unit includes a sleeve, a U-shaped frame, a rocker, an ear-shaped connecting seat, a vertical guide assembly and a vertical actuator cylinder. The aircraft model is installed on the sleeve through a force measuring balance. The middle part of the sleeve is hinged to the U-shaped frame, one end of the sleeve is hinged to the upper end of the rocker, the top end of the upper support rod is fixedly connected to the U-shaped frame, and the vertical guide The assembly is fixedly connected to the side wall of the upper support rod, the ear-shaped connecting seat is fixedly connected to the sliding unit on the vertical guide assembly, the upper end of the ear-shaped connecting seat is hinged to the lower end of the rocker, and the lower end of the ear-shaped connecting seat is connected to the actuating rod of the actuating cylinder; the actuating cylinder is located at the lower end of the vertical guide assembly and is fixedly connected to the side wall of the upper support rod; the lateral motion unit includes a lower base, two groups of V-shaped seats, two groups of V-shaped slide blocks, two V-shaped guide rails, a box-shaped support, a traction frame, a lateral drive cylinder assembly and a cylinder seat, the lateral drive cylinder assembly is fixedly connected to the cylinder seat, the cylinder seat is fixed to the upper bottom surface inside the lower base, and the lower base is fixedly connected Inside the turntable base, the moving end of the transverse drive cylinder assembly is connected to the traction frame through a hinge joint, one end of the box-shaped support is fixedly connected to the traction frame, two V-shaped guide rails are respectively fixed on the inner walls on both sides of the lower base and are parallel to the driving direction of the transverse drive cylinder assembly, two groups of V-shaped seats are symmetrically fixedly arranged on the two side walls of the box-shaped support and correspond to the positions of the two V-shaped guide rails, the V-shaped slider is installed between the V-shaped seat and the V-shaped guide rail, and the lower end of the lower support rod is fixedly connected to the box-shaped support; the other end of the box-shaped support is fixedly installed with a vertical plate; the shear-resistant body is fixedly installed between the lower base and the cylinder seat.

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