CN102141493B - Test loading device of airplane joystick type control system - Google Patents
Test loading device of airplane joystick type control system Download PDFInfo
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- CN102141493B CN102141493B CN2010105864740A CN201010586474A CN102141493B CN 102141493 B CN102141493 B CN 102141493B CN 2010105864740 A CN2010105864740 A CN 2010105864740A CN 201010586474 A CN201010586474 A CN 201010586474A CN 102141493 B CN102141493 B CN 102141493B
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- slide rail
- control system
- slipping plane
- frame
- loading device
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Abstract
The invention relates to a loading device, in particular relating to a test loading device of an airplane joystick type control system. The test loading device of the airplane joystick type control system provided by the invention comprises a slide rail, slide surfaces, double acting balls, a false joystick and frames comprising the slide surfaces, wherein the slide rail is a horizontal slide rail and comprises a heading slide rail and a lateral slide rail; the heading slide rail and the lateral slide rail are respectively arranged on upper and lower layers, and the heading slide rail and the lateral slide rail are connected end to end; the slide surfaces are elongated slot slide surfaces which are arranged in the frames; the number of the frames is two, and the two ends of each frame are arranged in the slide rail; and the double acting balls are arranged in the slide surfaces, and the centers of the double acting balls pass through the false joystick. The test loading device provided by the invention can be used for finishing the tests of displacement follow-up loading and composite operation loads, thereby more truly simulating the service condition of a joystick, and having greater actual application value.
Description
Technical field
The utility model relates to a kind of charger, especially a kind of experiment loading unit about aircraft handling rod-type control system.
Background technology
Usually, for flight control system static(al), torture test, being one basically independently, also is the ground intensity demonstration test content of very important direct relation flight safety with respect to aircraft body structure.
Control system test in the past generally is single independent operation test, i.e. the test separately of the control loop of control systems such as elevating rudder (or flying tail), aileron, yaw rudder.And the operation that the maneuvering flight of aircraft (special fighter plane) is reflected in control system composition operation often.Therefore, have the test of accomplishing single operation load and composition operation load simultaneously and can reflect manipulation of physical, need a device and accomplish this task.And control system in the past test generally is to be controlled quentity controlled variable with the masterpiece, and the displacement of operating rod is very little, is difficult to the actual operating position of real simulation operating rod.
The utility model content
The purpose of the utility model: a kind of big displacement servo-actuated loading and the composition operation load test that can accomplish control stick system is provided, the good aircraft handling rod-type control system experiment loading unit of operating rod simulation authenticity.
The technical scheme of the utility model is: a kind of aircraft control stick control system experiment loading unit, and it comprises slip rail, slipping plane, two moving ball, false jociey stick and frame, wherein; Said slip rail is a horizontally-sliding guide, comprises course slide rail and side direction slide rail, and said course slide rail and direction finding slide rail are arranged in two aspects up and down respectively; And it is end to end; Said slipping plane is the elongated slot slipping plane of offering in the frame, and frame is two up and down, and its two ends are arranged in the slip rail; Two moving balls are arranged in the slipping plane, and false jociey stick has been passed at its center.
Contact or sliding contact for rolling between said two moving ball and the slipping plane.
Said frame is connected with the hydraulic actuator that drives its push-and-pull.
The beneficial effect of the utility model is: the utility model aircraft handling rod-type control system experiment loading unit contains frame the moving in the slip rail of slipping plane through control; With displacement as controlled quentity controlled variable; The big displacement servo-actuated that has realized operating rod loads; Be that operating rod can servo-actuated in two dimensional surface, can realize the test of composition operation load, thereby can simulate the operating position of operating rod more realistically; Open a more approach of real simulated, demonstration test for static(al), the torture test of similar shape control system structure simultaneously, therefore had bigger actual application value.
Description of drawings
The structural representation of Fig. 1 the utility model aircraft control stick control system experiment loading unit one preferred embodiments;
Fig. 2 is the schematic diagram of the utility model aircraft control stick control system experiment loading unit one preferred embodiments;
Fig. 3 is the structural representation of slip rail among Fig. 1;
Fig. 4 is the structural representation of slipping plane among Fig. 1;
Fig. 5 is the structural representation of two moving balls among Fig. 1;
Fig. 6 is the structural representation of false jociey stick among Fig. 1,
Wherein, 1-slip rail, 2-slipping plane, the two moving balls of 3-, the false jociey stick of 4-, 5-hydraulic actuator, 6-frame.
Embodiment
Through embodiment the utility model is done further to specify below:
Please consult Fig. 1 and Fig. 2 simultaneously, wherein, Fig. 1 is the structural representation of the utility model aircraft control stick control system experiment loading unit, and Fig. 2 is its principle schematic.In this embodiment, said aircraft control stick control system experiment loading unit comprises slip rail 1, slipping plane 2, two moving ball 3, false jociey stick 4, hydraulic actuator 5 and contains the frame 6 of slipping plane 2.
Wherein, said slip rail 1 is a horizontally-sliding guide, comprises course slide rail and side direction slide rail, and said course slide rail and direction finding slide rail are arranged in two aspects up and down, not in same plane, and rectangle frame of the two end to end formation.Please consult Fig. 3 simultaneously, it is the structural representation of slip rail 1, and one section of slipping plane can moving in its corresponding slip rail 1, and the gap between the frame 6 of slip rail 1 and horizontal slip within it should not be excessive, to avoid loosening.
The camber elongated slot slipping plane of said slipping plane 2 for making two moving balls be free to slide or roll within it comprises course slipping plane and lateral slip face, wherein, supply the slip or the rolling of two moving balls, and the two is not in same plane.See also Fig. 4, it is the structural representation of slipping plane 2, and the radian that can be free to slide (or rolling) according to two moving balls within it requires processing camber elongated slot slipping plane.Said slipping plane processes comprising on the frame inwall of slipping plane, and slipping plane has (or rolling) requirement of sliding of fitting with two moving balls on the one hand, and the frame and the slip rail that contain slipping plane on the other hand have applying horizontal slip requirement.The frame that contains slipping plane needs according to two up and down of dimensional requirement processing, and corresponding with bilevel slip rail 1 respectively, can in slip rail 1, move.
See also Fig. 5, it is the structural representation of two moving balls, and said two moving balls 3 are arranged in the elongated slot of course slide rail and side direction slide rail, and its center passed false jociey stick 4, and the gap can not be excessive between itself and the false jociey stick 4, to avoid becoming flexible cunning.The moving ball 3 of this pair has applying slip requirement with false jociey stick 4 on the one hand, with slipping plane 2 (or rolling) requirement of sliding of fitting is arranged on the other hand.Two moving balls 1 need to be placed in respectively in the frame 6 that contains slipping plane according to two up and down of dimensional requirement processing, fit with slipping plane 2.Therefore two moving balls can slide up and down and in slipping plane 2, be free to slide or roll at false jociey stick 4.
See also Fig. 6, it is the structural representation of false jociey stick.Said false jociey stick 4 is for testing the circular uniform cross section rod member that is used for replacing true jociey stick, and its rod member thickness size needs and two moving ball endoporus are coordinated, and the gap is unsuitable excessive.
And hydraulic actuator 5 links to each other with the frame that contains slipping plane 26, through the traction control frame, it is moved on slip rail 1, thereby drives moving of slipping plane 2.
The above-mentioned part of the utility model aircraft handling rod-type control system experiment loading unit in the cabin, forms an integral body with frame fixation.During actual the use; Through the folding and unfolding campaign of two controlled hydraulic pressurized struts 5, drive moving of slipping plane 2, make two moving balls 3 in slipping plane 2, move with false jociey stick 4; Through controlling the displacement of false jociey stick 4; The false jociey stick 4 of push-and-pull to XOY plane more arbitrarily, thereby realize the control simulation of aircraft control stick, realize the purpose of imposed load.
The utility model aircraft handling rod-type control system experiment loading unit is a kind of load testing machine of two dimensional surface; Be applied in the torture test of the full machine primary control circuit of certain type aircraft, be applied in especially in the test of aileron, horizontal tail, can reach the displacement of any direction of jociey stick; The each point that is the XOY plane coordinate of trial stretch can both be met; Thereby constitute the two dimensional surface of test, comprise the composition operation of accomplishing test, i.e. aileron--the composition operation of horizontal tail.
The utility model aircraft handling rod-type control system experiment loading unit has solved the problem that rod-type control system in the past can only be done the single operation test; And carry out the jociey stick simulation through the control displacement and handle; Its displacement is big, for a more approach of real simulated, demonstration test has been opened in static(al), the torture test of similar shape control system structure.
Claims (3)
1. an aircraft control stick control system experiment loading unit is characterized in that: comprise slip rail (1), slipping plane (2), two moving ball (3), false jociey stick (4) and frame (6), wherein; Said slip rail (1) is a horizontally-sliding guide, comprises course slide rail and side direction slide rail, and said course slide rail and side direction slide rail are arranged in two aspects up and down respectively; And end to end, the elongated slot slipping plane of said slipping plane (2) for offering in the frame (6), frame (6) they are two up and down; Its two ends are arranged in the slip rail; And corresponding with bilevel slip rail respectively, two moving balls (3) have two up and down, are placed in respectively in the frame that contains slipping plane; Fit with slipping plane, and false jociey stick (4) has been passed at its center.
2. aircraft control stick control system experiment loading unit according to claim 1 is characterized in that: contact or sliding contact for rolling between said two moving balls (3) and the slipping plane (2).
3. aircraft control stick control system experiment loading unit according to claim 2 is characterized in that: said frame is connected with and drives its hydraulic actuator that moves (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010105864740A CN102141493B (en) | 2010-12-14 | 2010-12-14 | Test loading device of airplane joystick type control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010105864740A CN102141493B (en) | 2010-12-14 | 2010-12-14 | Test loading device of airplane joystick type control system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102141493A CN102141493A (en) | 2011-08-03 |
| CN102141493B true CN102141493B (en) | 2012-07-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010105864740A Expired - Fee Related CN102141493B (en) | 2010-12-14 | 2010-12-14 | Test loading device of airplane joystick type control system |
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| Country | Link |
|---|---|
| CN (1) | CN102141493B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103308295A (en) * | 2013-01-05 | 2013-09-18 | 中国航空工业集团公司西安飞机设计研究所 | Control and check test method for flight control mechanical control system |
| CN103994878B (en) * | 2014-04-17 | 2017-06-16 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of compbined test verification method of aircraft movable wing |
| CN105571839B (en) * | 2014-10-11 | 2018-03-02 | 中国航空工业集团公司西安飞机设计研究所 | A kind of continuous varied angle CYCLIC LOADING method |
| CN106767365A (en) * | 2016-11-29 | 2017-05-31 | 中国直升机设计研究所 | The method of testing and component of bar displacement in a kind of control system stick force attribute testing |
| CN106737861B (en) * | 2016-12-05 | 2023-06-06 | 重庆华数机器人有限公司 | Robot flexibility testing device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4907970A (en) * | 1988-03-30 | 1990-03-13 | Grumman Aerospace Corporation | Sidestick-type thrust control simulator |
| CN2173436Y (en) * | 1993-10-27 | 1994-08-03 | 福州开发区汽车驾驶模拟器制造厂 | Operating mechanism for driving imitator |
| US5823876A (en) * | 1996-05-03 | 1998-10-20 | Unbehand; Erick Michael | Steering wheel simulation assembly |
| CN201015064Y (en) * | 2006-09-26 | 2008-01-30 | 邹自正 | Automobile drive exercising machines |
| CN201653546U (en) * | 2010-01-06 | 2010-11-24 | 张弦 | Navaid light intensity automation measuring device |
-
2010
- 2010-12-14 CN CN2010105864740A patent/CN102141493B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4907970A (en) * | 1988-03-30 | 1990-03-13 | Grumman Aerospace Corporation | Sidestick-type thrust control simulator |
| CN2173436Y (en) * | 1993-10-27 | 1994-08-03 | 福州开发区汽车驾驶模拟器制造厂 | Operating mechanism for driving imitator |
| US5823876A (en) * | 1996-05-03 | 1998-10-20 | Unbehand; Erick Michael | Steering wheel simulation assembly |
| CN201015064Y (en) * | 2006-09-26 | 2008-01-30 | 邹自正 | Automobile drive exercising machines |
| CN201653546U (en) * | 2010-01-06 | 2010-11-24 | 张弦 | Navaid light intensity automation measuring device |
Non-Patent Citations (1)
| Title |
|---|
| 白穆等.飞机操纵装置优化布局.《中国民航飞行学院学报》.2010,第21卷(第1期),28-31. * |
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| Publication number | Publication date |
|---|---|
| CN102141493A (en) | 2011-08-03 |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20120725 Termination date: 20161214 |
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| CF01 | Termination of patent right due to non-payment of annual fee |