CN102141493A - 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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- CN102141493A CN102141493A CN 201010586474 CN201010586474A CN102141493A CN 102141493 A CN102141493 A CN 102141493A CN 201010586474 CN201010586474 CN 201010586474 CN 201010586474 A CN201010586474 A CN 201010586474A CN 102141493 A CN102141493 A CN 102141493A
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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 present invention 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 finishing single operation load and composition operation load simultaneously and can reflect manipulation of physical, need a device and finish 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.
Summary of the invention
Purpose of the present invention: provide a kind of big displacement servo-actuated loading and the composition operation load test that can finish control stick system, the good aircraft handling rod-type control system experiment loading unit of operating rod simulation authenticity.
Technical scheme of the present invention is: a kind of aircraft control stick control system experiment loading unit, it comprises slip rail, slipping plane, two moving ball, false jociey stick and frame, wherein, described slip rail is a horizontally-sliding guide, comprise course slide rail and side direction slide rail, described course slide rail and direction finding slide rail are arranged in two aspects up and down respectively, and it is end to end, described slipping plane is the elongated slot slipping plane of offering in the frame, frame is two up and down, its two ends are arranged in the slip rail, and 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 described two moving ball and the slipping plane.
Described frame is connected with the hydraulic actuator that drives its push-and-pull.
The invention has the beneficial effects as follows: aircraft handling rod-type control system experiment loading unit of the present invention contains frame the moving in the slip rail of slipping plane by 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 aircraft control stick control system of the present invention experiment loading unit one better embodiment;
Fig. 2 is the schematic diagram of aircraft control stick control system experiment loading unit one better embodiment of the present invention;
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
The present invention is described in further detail below by embodiment:
Please consult Fig. 1 and Fig. 2 simultaneously, wherein, Fig. 1 is the structural representation of aircraft control stick control system experiment loading unit of the present invention, and Fig. 2 is its principle schematic.In the present embodiment, described 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, described slip rail 1 is a horizontally-sliding guide, comprises course slide rail and side direction slide rail, and described 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 the slip rail 1 of its correspondence, 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 described slipping plane 2 for making two moving balls be free to slide or roll within it comprises course slipping plane and lateral slip face, and wherein, for 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.Described 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 move in slip rail 1.
See also Fig. 5, it is the structural representation of two moving balls, and described 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 be free to slide in slipping plane 2 or roll at false jociey stick 4.
See also Fig. 6, it is the structural representation of false jociey stick.Described 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 6 that contains slipping plane 2, by the traction control frame, it is moved on slip rail 1, thereby drives moving of slipping plane 2.
The above-mentioned part of aircraft handling rod-type control system experiment loading unit of the present invention in the cabin, forms an integral body with frame fixation.During actual the use, folding and unfolding campaign by two controlled hydraulic pressurized struts 5, drive moving of slipping plane 2, make two moving balls 3 and false jociey stick 4 in slipping plane 2, move, by 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.
Aircraft handling rod-type control system experiment loading unit of the present invention 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 finishing test, i.e. aileron--the composition operation of horizontal tail.
Aircraft handling rod-type control system experiment loading unit of the present invention 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 by 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. aircraft control stick control system experiment loading unit, it is characterized in that: comprise slip rail (1), slipping plane (2), two moving balls (3), false jociey stick (4) and frame (6), wherein, described slip rail (1) is a horizontally-sliding guide, comprise course slide rail and side direction slide rail, described course slide rail and direction finding slide rail are arranged in two aspects up and down respectively, and it is end to end, described (2) slipping plane is the elongated slot slipping plane of offering in the frame (6), frame (6) is two up and down, its two ends are arranged in the slip rail, and two moving balls (3) are arranged in the 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 described 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: described 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 true CN102141493A (en) | 2011-08-03 |
| CN102141493B CN102141493B (en) | 2012-07-25 |
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| 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 |
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| CN (1) | CN102141493B (en) |
Cited By (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 |
| CN103994878A (en) * | 2014-04-17 | 2014-08-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Integration test verification method of airplane movable wing surface |
| CN105571839A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Continuous variable-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 |
| CN106737861A (en) * | 2016-12-05 | 2017-05-31 | 重庆华数机器人有限公司 | A kind of Robot compliance test device |
Citations (5)
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|---|---|---|---|---|
| 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 |
|---|
| 《中国民航飞行学院学报》 20100131 白穆等 飞机操纵装置优化布局 28-31 1-3 第21卷, 第1期 * |
Cited By (7)
| 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 |
| CN103994878A (en) * | 2014-04-17 | 2014-08-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Integration test verification method of airplane movable wing surface |
| CN105571839A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Continuous variable-angle cyclic loading method |
| 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 |
| CN106737861A (en) * | 2016-12-05 | 2017-05-31 | 重庆华数机器人有限公司 | A kind of Robot compliance test device |
| CN106737861B (en) * | 2016-12-05 | 2023-06-06 | 重庆华数机器人有限公司 | Robot flexibility testing device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102141493B (en) | 2012-07-25 |
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Granted publication date: 20120725 Termination date: 20161214 |