CN115165292A - Aircraft transverse reciprocating motion test simulation device - Google Patents

Aircraft transverse reciprocating motion test simulation device Download PDF

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Publication number
CN115165292A
CN115165292A CN202210756734.7A CN202210756734A CN115165292A CN 115165292 A CN115165292 A CN 115165292A CN 202210756734 A CN202210756734 A CN 202210756734A CN 115165292 A CN115165292 A CN 115165292A
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CN
China
Prior art keywords
aircraft
shaped
transverse
strut
fixedly connected
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Pending
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CN202210756734.7A
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Chinese (zh)
Inventor
牟伟强
卜忱
陈昊
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AVIC Aerodynamics Research Institute
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AVIC Aerodynamics Research Institute
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Priority to CN202210756734.7A priority Critical patent/CN115165292A/en
Publication of CN115165292A publication Critical patent/CN115165292A/en
Pending legal-status Critical Current

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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/02—Wind tunnels
    • G01M9/04—Details
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
    • G01M9/062—Wind tunnel balances; Holding devices combined with measuring arrangements

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • General Physics & Mathematics (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Abstract

The invention discloses a device for simulating a transverse reciprocating motion test of an aircraft, and belongs to the field of wind tunnel tests of aircraft. Including aircraft model, dynamometry balance, pitch angle regulating unit, upper strut, lower strut, transverse movement unit and carousel base, the transverse movement unit can follow the horizontal direction motion, the upper end of upper strut install pitch angle regulating unit, the aircraft model passes through the dynamometry balance and is connected with pitch angle regulating unit, pitch angle regulating unit can follow Y direction angle regulation, realizes the change of aircraft model angle of pitch, the lower extreme of upper strut meshes with the upper end of lower strut and can follow Z direction angle regulation, realizes the change of aircraft sideslip angle, the lower extreme and the transverse driving motion unit fixed connection of lower strut realize the reciprocating oscillation motion of aircraft model along the horizontal direction. The device has the advantages of simplicity, symmetry and high rigidity and strength, and can realize the measurement test of the differential derivative during the transverse direction washing of the model in a larger size range.

Description

Aircraft transverse reciprocating motion test simulation device
Technical Field
The invention belongs to the field of wind tunnel tests of aircrafts, and particularly relates to a horizontal reciprocating motion test simulation device of an aircraft.
Background
The differential derivative of the horizontal directional wash flow is the derivative of the aerodynamic coefficient of the aircraft to the sideslip angular rate of the aircraft, is one of the necessary aerodynamic parameters in the process of developing the aircraft, and is used for the stability analysis and control law design of the aircraft. At present, the main means for obtaining the differential coefficient of lateral direction wash-flow includes wind tunnel test, numerical simulation, and identification of model flight or test flight parameters. The numerical simulation method needs longer calculation time, is not suitable for acquiring a large amount of data, and still needs further research on a calculation method and accuracy in a medium and large attack angle range. The model flight or test flight method has the defects of high cost, long implementation period, safety risk, poor repeatability, low parameter identification accuracy and the like, and the model flight and test flight cannot be safely carried out without a dynamic derivative, so the method is not suitable to be used as a main method for obtaining the dynamic derivative by models. Wind tunnel test is the most reliable means for obtaining dynamic derivative data, but most wind tunnels only have angular oscillation dynamic derivative test capability, only can obtain composite dynamic derivatives, and lack a test method and test equipment for differential derivatives during cross-directional wash flow. The method is mainly caused by the technical problem test technology that the precision of the transverse translational motion of the model is insufficient, the interference of a supporting system to the model is large, and the like. Therefore, aiming at the requirement of aircraft development on the dynamic derivative data during cross-directional wash flow, a simulation device for the aircraft transverse reciprocating motion test needs to be developed.
Disclosure of Invention
Based on the defects, the invention aims to provide the aircraft transverse reciprocating motion test simulation device which is used for researching the aerodynamic characteristic influence of the differential coefficient test when the aircraft transverse directional wash flow is developed in the wind tunnel, the test flight risk of a new aircraft can be reduced, and the development cycle of the new aircraft is shortened.
The technical scheme of the invention is as follows: the utility model provides an aircraft lateral reciprocating motion test analogue means, includes aircraft model, dynamometry balance, pitch angle regulating unit, upper strut, lower strut, transverse motion unit and carousel base, the transverse motion unit install inside the carousel base, the transverse motion unit can be followed the horizontal direction and moved, this direction is the X direction, the upper end of upper strut install pitch angle regulating unit, the aircraft model passes through the dynamometry balance and is connected with pitch angle regulating unit, pitch angle regulating unit can follow Y direction angle regulation, realizes the change of aircraft model pitch angle, the lower extreme of upper strut meshes with the upper end of lower strut and can carry out relatively fixed after following Z direction angle regulation, realizes the change of aircraft sideslip angle, the lower extreme and the transverse driving motion unit fixed connection of lower strut realize the reciprocating oscillation motion of aircraft model along the horizontal direction.
The aircraft model further comprises sealing units, wherein the sealing units are positioned on two sides of the lower support rod close to the lower end and are horizontally and fixedly connected with the side wall of the lower support rod, and when the aircraft model performs transverse reciprocating motion in the wind tunnel along the horizontal direction, the sealing units perform reciprocating following motion along with the lower support rod so as to prevent the air flow from moving up and down.
Furthermore, the pitching angle adjusting unit comprises 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 mounted on the sleeve through a force measuring balance, the middle part of the sleeve is hinged with the U-shaped frame, one end of the sleeve is hinged with the upper end of the rocker, the top end of the upper support rod is fixedly connected with the U-shaped frame, the vertical guide assembly is fixedly connected with the side wall of the upper support rod, the ear-shaped connecting seat is fixedly connected with a sliding unit on the vertical guide assembly, the upper end of the ear-shaped connecting seat is hinged with the lower end of the rocker, and the lower end of the ear-shaped connecting seat is connected with an actuating rod of the actuating cylinder; the actuating cylinder is fixedly connected with the side wall of the upper supporting rod and is positioned at the lower end of the vertical guide assembly.
Furthermore, the transverse motion unit comprises a lower base, two groups of V-shaped seats, two groups of V-shaped sliding blocks, two V-shaped guide rails, a box-shaped support, a traction frame, a transverse drive cylinder body assembly and a cylinder base, wherein the transverse drive cylinder body assembly is fixedly connected with the cylinder base, the cylinder base is fixed on the upper bottom surface inside the lower base, the lower base is fixedly connected inside the turntable base, the motion end of the transverse drive cylinder body assembly is connected with the traction frame through a hinged joint, one end of the box-shaped support is fixedly connected with the traction frame, the two V-shaped guide rails are respectively fixed on the inner side walls of the two sides of the lower base and are parallel to the driving direction of the transverse drive cylinder body assembly, the two groups of V-shaped seats are symmetrically and 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 sliding blocks are arranged between the V-shaped seats and the V-shaped guide rails, and the lower end of the lower support is fixedly connected with the box-shaped support.
Furthermore, the other end of the box-shaped support is fixedly provided with a vertical plate.
Furthermore, the shearing-resistant cylinder also comprises a shearing-resistant body which is fixedly arranged between the lower base and the cylinder seat.
The device has the advantages and beneficial effects that the device can be used for researching the influence of the aerodynamic characteristics of the dynamic derivative when the aircraft washes the flow in the transverse direction in the wind tunnel, measuring the dynamic performance response parameters of the aircraft, mastering the motion rule of the aircraft and providing necessary technical guarantee for the safe flight of the aircraft. The transverse moving unit generates continuous controllable and accurate forced translational motion, and provides basic conditions for obtaining differential derivatives in transverse washing. The method has the characteristics of simplicity, symmetry, high rigidity and strength and the like, can effectively control the interference of the support equipment on the aerodynamic characteristics of the model, can realize the measurement test of the differential derivative during the transverse course washing of the model in a larger size range, and provides more real and stable data for the development of the aircraft.
Drawings
FIG. 1 is a front view of the apparatus of the present invention;
FIG. 2 is a side view of the apparatus of the present invention;
FIG. 3 is a top view of the apparatus of the present invention;
Detailed Description
The invention is further described by way of example in the following description with reference to the accompanying drawings:
example 1
As shown in fig. 1-3, an aircraft transverse reciprocating motion test simulation device comprises an aircraft model, a force measuring balance, a pitch angle adjusting unit, an upper support rod 4, a lower support rod 5, a transverse motion unit and a turntable base 19, wherein the transverse motion unit is installed inside the turntable base 19 and can move along the horizontal direction, the direction is the X direction, the pitch angle adjusting unit is installed at the upper end of the upper support rod 4, the aircraft model is connected with the pitch angle adjusting unit through the force measuring balance, the pitch angle adjusting unit can adjust the angle along the Y direction to realize 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 along the Z direction to realize the change of the sideslip angle of the aircraft, and the lower end of the lower support rod 5 is fixedly connected with the transverse driving motion unit to realize the reciprocating oscillating motion of the aircraft model along the horizontal direction. Wherein, pre-buried up end tooth 6 in the upper strut 4 bottom surface recess, pre-buried lower extreme tooth 7 in the lower strut 5 top surface recess, when needs adjustment sideslip angle, throw off the connecting screw of upper strut 4 and lower strut 5, rotate the angle that the experiment required, utilize the tooth meshing principle to lock, and then realize the change of mechanism sideslip angle.
The pitching angle adjusting unit comprises a sleeve, a U-shaped frame 3, a rocker 21, an ear-shaped connecting seat 22, a vertical guide assembly 23 and a vertical acting cylinder 24, the top end of an upper supporting rod 4 is fixedly connected with the U-shaped frame 3, an aircraft model is installed on the sleeve 1 through a force measuring balance, the middle of the sleeve 1 is connected with the U-shaped frame 3 through a rotating shaft 2, and one end of the sleeve 1 is connected with the upper end of the rocker 21 through a rocker shaft 20. The vertical guide component 23 is fixedly installed on the side wall of the upper support rod 4 through a screw, a sliding unit of the vertical guide component 23 is fixedly connected with the ear-shaped connecting seat 22, the upper end of the ear-shaped connecting seat 22 is hinged with the lower end of the rocker 21, the lower end of the ear-shaped connecting seat 22 is connected with the actuating end of the actuating cylinder 24, the actuating cylinder 24 is positioned at the lower end of the vertical guide component 23, and the actuating cylinder 24 is fixedly connected with the side wall of the upper support rod 4 through an actuating cylinder installing seat 25. Under the control of the actuating cylinder 24, the ear-shaped connecting seat 22 performs repeated linear motion under the guidance of the vertical guiding component 23, and then the rocker 21 is driven to drag the sleeve 1 to change the pitch angle around the rotating shaft 2.
The transverse movement unit comprises a lower base 28, two groups of V-shaped seats 29, two groups of V-shaped sliding blocks 33, two V-shaped guide rails 34, a box-shaped support 32, a traction frame 16, a transverse driving cylinder body assembly 17 and a cylinder seat 31, wherein the fixed end of the transverse driving cylinder body assembly 17 is fixedly connected with the cylinder seat 31, the moving end of the transverse driving cylinder body assembly 17 is connected with a hinged joint 15, the hinged joint 15 is connected with the traction frame 16, one end of the box-shaped support 32 is connected with the traction frame 16, the V-shaped guide rails 34 are arranged on the inner side of the lower base 28, the V-shaped sliding blocks 33 made of high-strength wear-resistant alloy materials are arranged between the V-shaped seats 29 and the V-shaped guide rails 34, the front and the rear groups of the V-shaped seats 29 are symmetrically arranged on the box-shaped support 32, and the vertical plates 18 are arranged at the other end of the box-shaped support 32. The cylinder seat 31 is fixed on the upper bottom surface inside the lower base 28, the lower base 28 is installed inside the turntable base 19, and the shear resistant body 30 is installed between the lower base 28 and the cylinder seat 31 and used for bearing the transverse shear force generated during the reversing process of the reciprocating operation of the mechanism.
The embodiment further comprises a sealing unit which comprises a positioning supporting plate 26, a thrust block 9, a protective sleeve 8, a side cover plate 27, a sealing plate 10 and a roller pair, wherein the positioning supporting plate 26 is fixed on two sides of the lower support rod 5, and the thrust block 9 is fixed on the lower support rod 5 through the positioning supporting plate 26. In order to reduce the impact generated in the process of transverse repeated movement of the mechanism, a protective sleeve 8 with a buffering function is arranged between the thrust block 9 and the lower support rod 5. The sealing plate 10 is fixed on the thrust block 9, the upper and lower sides of the sealing plate 10 are clamped by the rollers 14, the rollers 14 are installed on the roller seats 12 through the roller shafts 13, the upper and lower roller seats 12 are installed on the upper cover plate 11 and the turntable 19 respectively to prevent the sealing plate 10 from moving up and down in the movement process, and the side cover plate 27 covers the upper part of the sealing plate 10. When the mechanism does transverse reciprocating motion, the sealing unit follows the lower support rod 5, so that the air flow can be effectively prevented from moving up and down in the test process.

Claims (6)

1. The utility model provides an aircraft lateral reciprocating motion test analogue means, includes aircraft model, dynamometry balance, pitch angle regulating unit, upper strut, lower strut, transverse movement unit and carousel base, its characterized in that, transverse movement unit install inside the carousel base, the transverse movement unit can be followed the horizontal direction motion, this direction is the X direction, the upper end of upper strut install pitch angle regulating unit, the aircraft model passes through the dynamometry balance and is connected with pitch angle regulating unit, pitch angle regulating unit can follow Y direction angle regulation, realizes the change of aircraft model angle of pitch, the lower extreme of upper strut meshes and the upper end of lower strut and can follow and carry out relatively fixed behind the Z direction angle regulation, realizes the change of aircraft sideslip angle, the lower extreme and the transverse driving motion unit fixed connection of lower strut realize the aircraft model along the reciprocating oscillation motion of horizontal direction.
2. The aircraft lateral reciprocating motion test simulation device of claim 1, wherein: the aircraft model is characterized by further comprising sealing units, wherein the sealing units are located on two sides, close to the lower end, of the lower support rod and are horizontally and fixedly connected with the lower support rod, and when the aircraft model performs transverse reciprocating motion in the wind tunnel along the horizontal direction, the sealing units perform reciprocating following motion along with the lower support rod so as to prevent air flow from moving up and down.
3. The aircraft transverse reciprocating motion test simulation device according to claim 2, wherein: the pitching angle adjusting unit comprises a sleeve, a U-shaped frame, a rocker, an ear-shaped connecting seat, a vertical guiding 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 with the U-shaped frame, one end of the sleeve is hinged with the upper end of the rocker, the top end of an upper supporting rod is fixedly connected with the U-shaped frame, the vertical guiding assembly is fixedly connected with the side wall of the upper supporting rod, the ear-shaped connecting seat is fixedly connected with a sliding unit on the vertical guiding assembly, the upper end of the ear-shaped connecting seat is hinged with the lower end of the rocker, and the lower end of the ear-shaped connecting seat is connected with the actuating rod of the actuating cylinder; the actuating cylinder is fixedly connected with the side wall of the upper supporting rod and is positioned at the lower end of the vertical guide assembly.
4. The aircraft lateral reciprocating motion test simulation device of claim 3, wherein: the transverse motion unit comprises a lower base, two groups of V-shaped seats, two groups of V-shaped sliding blocks, two V-shaped guide rails, a box-shaped support, a traction frame, a transverse drive cylinder body assembly and a cylinder base, wherein the transverse drive cylinder body assembly is fixedly connected with the cylinder base, the cylinder base is fixed on the upper bottom surface inside the lower base, the lower base is fixedly connected inside a turntable base, the motion end of the transverse drive cylinder body assembly is connected with the traction frame through a hinge joint, one end of the box-shaped support is fixedly connected with the traction frame, the two V-shaped guide rails are respectively fixed on the inner side walls of the two sides of the lower base and are parallel to the driving direction of the transverse drive cylinder body assembly, the two groups of V-shaped seats are symmetrically and 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 sliding blocks are installed between the V-shaped seats and the V-shaped guide rails, and the lower end of the lower support is fixedly connected with the box-shaped support.
5. The aircraft transverse reciprocating motion test simulation device of claim 4, wherein: the other end of the box-shaped support is fixedly provided with a vertical plate.
6. The aircraft transverse reciprocating motion test simulation device according to claim 4 or 5, wherein: the shearing-resistant cylinder also comprises a shearing-resistant body which is fixedly arranged between the lower base and the cylinder seat.
CN202210756734.7A 2022-06-29 2022-06-29 Aircraft transverse reciprocating motion test simulation device Pending CN115165292A (en)

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Application Number Priority Date Filing Date Title
CN202210756734.7A CN115165292A (en) 2022-06-29 2022-06-29 Aircraft transverse reciprocating motion test simulation device

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Application Number Priority Date Filing Date Title
CN202210756734.7A CN115165292A (en) 2022-06-29 2022-06-29 Aircraft transverse reciprocating motion test simulation device

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CN115165292A true CN115165292A (en) 2022-10-11

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115436007A (en) * 2022-11-08 2022-12-06 中国航空工业集团公司哈尔滨空气动力研究所 Single-strut active blow-by prevention mechanism with variable cross section and blow-by prevention method

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115436007A (en) * 2022-11-08 2022-12-06 中国航空工业集团公司哈尔滨空气动力研究所 Single-strut active blow-by prevention mechanism with variable cross section and blow-by prevention method

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