CN102645325A

CN102645325A - Airplane operation torque and operation angular displacement simulating method

Info

Publication number: CN102645325A
Application number: CN2011100427658A
Authority: CN
Inventors: 王慧; 牟瑾刚; 刘波
Original assignee: Xian Aircraft Design and Research Institute of AVIC
Current assignee: Xian Aircraft Design and Research Institute of AVIC
Priority date: 2011-02-22
Filing date: 2011-02-22
Publication date: 2012-08-22

Abstract

The invention belongs to the field of aviation test and particularly relates to the field of airplane operation system test, wherein a support frame assembly (1) is fixedly arranged on a test table frame or an airplane main structure, a rotary mechanical signal generator (2) is fixedly arranged on the support frame assembly (1), a torque sensor (3) is connected in series onto a mechanical signal generator output rod (10), an operation disc clamp (6) is clamped on an operation disc (7), the torque sensor (3) and the operation disc clamp (6) are connected through a mechanical transmission rod (5), an angular displacement sensor (4) is connected with the airplane operation disc (7) through a mechanical linkage rod (5), torque and angular displacement signals required by the operation system test are output through the rotary mechanical signal generator (2), the airplane operation disc (7) is driven to move, and the goal of simulating the airplane operation torque and the operation angular displacement is reached, the test of the airplane operation system is conveniently carried out, the work intensity of test operators is reduced, the test efficiency is improved, and the test result accuracy is improved.

Description

A kind of aircraft handling moment and manipulation angular displacement analogy method

Technical field

The invention belongs to field of aviation measurement and test, particularly the flight control system field tests.

Background technology

In airplane design; Control system performance test test is indispensable in the airplane design process; And in control system performance test process of the test, the most difficult is how operating torque and manipulation angular displacement to be imported, and promptly how accurately drive simulating person handles aircraft.In static test, can handle control wheel by the people, read through moment, angular displacement sensor, but, can increase the test result error because the people handles the influence of disturbing factors such as time individual's fitness, personal habits.And when the people handles, can not accurately import the operating torque of certain value or handle angular displacement, can't accurately test.In dynamic test, the people handles can't simulate step signal, sinusoidal signal and other high-frequency signals.

In addition; In application number is 201010119246.2 patent, a kind of airplane steering wheel multi-axis force measurement component and measuring method thereof have been proposed, be the measurement assembly of handle type; Promptly need the people to handle control wheel and measure its operating torque, can't satisfy accurate measurement and the dynamically simulation of manipulated variable.

Summary of the invention

The object of the invention: for solving the flight control system operating torque and handling the problem that angular displacement is difficult to simulate; Especially accurately the simulation of simulation and Dynamic Signal; The present invention proposes a kind of aircraft handling moment and handles the angular displacement analogy method; Can realize operating torque and handle angular displacement and accurately control; And accurately draw the static performance index value of flight control system through operating torque and the curve of handling angular displacement, simultaneously, can realize dynamic operating torque signal and the simulation of handling the parallactic angle shifting signal; Like step signal, high frequency sinusoidal signal, square-wave signal, triangular signal and sawtooth signal, to realize testing requirement to the dynamic and static performance of flight control system.

Technical scheme of the present invention: a kind of aircraft handling moment that the present invention proposes and manipulation angular displacement analogy method, former reason is shown in Figure 1, comprises bracket component 1; Rotary type mechanical signal generator 2; Torque sensor 3, angular displacement sensor 4, mechanical drive bar 5; Control handwheel anchor clamps 6, mechanical linkage bar 11 and aircraft handling dish 7.The practical implementation step is following:

(a) bracket component 1 is fixed on test-bed or the aircraft main structure;

(b) rotary type mechanical signal generator 2 is fixed on the bracket component 1;

(c) torque sensor 3 is series on the mechanical signal generator take-off lever 10;

(d) control handwheel anchor clamps 6 are held on the aircraft handling dish 7;

(e) through mechanical drive bar 5 torque sensor 3 is linked to each other with control handwheel anchor clamps 6;

(f) angular displacement sensor 4 is linked to each other with aircraft handling dish 7 through mechanical linkage bar 11;

(g) adjustment mounting assembly 1 makes aircraft handling dish 7 be in the neutral position, and torque sensor 3, angular displacement sensor 4 all are in zero-bit;

(h) through required moment, the angular displacement signal of rotary type mechanical signal generator 2 output control system tests; Drive 7 motions of aircraft handling dish; Thereby reach simulated aircraft operating torque and the purpose of handling angular displacement; Can gather through

torque sensor

3 and 4 pairs of operating torques of angular displacement sensor and manipulation angular displacement simultaneously, conveniently carry out the test of flight control system.

Bracket component 1 is to do three direction of principal axis position adjustments and the rigid support that axial rotation is regulated.

Rotary type mechanical signal generator 2 can produce the moment and the angular displacement control signal of steady state value, and can produce the waveform signal of various frequencies and amplitude as required.

The good effect that the present invention produces: a kind of aircraft handling moment proposed by the invention and manipulation angular displacement analogy method, can be adapted to the control system test of various maneuverability patterns, it is strong to have adaptability; Reliability is high, and the characteristics that accuracy is high are especially for the dynamic and static performance test of flight control system aspect; Greatly reduced and tested required manpower and materials; Reduce Test Operator's working strength, improved test efficiency, improved the test findings degree of accuracy.

Description of drawings

Fig. 1 is a kind of aircraft handling moment and manipulation angular displacement analogy method schematic diagram;

Fig. 2 is a double Hooke's joint torque arm structure principle chart;

Wherein 1 is bracket component, the 2nd, and rotary type mechanical signal generator, the 3rd, torque sensor, the 4th, angular displacement sensor; The 5th, mechanical drive bar, the 6th, control handwheel anchor clamps, the 7th, aircraft handling dish, the 8th, universal joint; The 9th, torque arm, the 10th, mechanical signal generator take-off lever, the 11st, mechanical linkage bar.

Embodiment

Present embodiment is control wheel operating torque and manipulation angular displacement analogy method, and former reason is shown in Figure 1, relates to bracket component 1; Rotary type mechanical signal generator 2, torque sensor 3, angular displacement sensor 4; Mechanical drive bar 5, control handwheel anchor clamps 6, aircraft handling dish 7.Wherein aircraft handling dish 7 is a control wheel.Bracket component 1 is the mounting bracket of rotary type mechanical signal generator 2, is a rigid support, and can do three axial position adjustments and regulate around an axial rotation, regulates with the installation site of realizing rotary type mechanical signal generator 2.Rotary type mechanical signal generator 2 can produce the moment or the angular displacement control signal of fixed value, and can produce the waveform signal of various frequencies as required.Mechanical drive bar 5 is the double Hooke's joint torque arm, is made up of the universal joint at two 8 and the torque arm 9 at middle part, is used for preventing that gear train from crossing constraint.Control handwheel anchor clamps 6 are unit clamp, are held on the control wheel pilot and hold a place, as control wheel operating torque and the input point of handling displacement.

This method is taked following steps:

(a) bracket component 1 is passed through bolt on test-bed or aircraft main structure;

(b) rotary type mechanical signal generator 2 is clamped be fixed on the bracket component 1;

(c) torque sensor 3 is linked to each other with mechanical signal generator take-off lever 10 and tighten up;

(d) control handwheel anchor clamps 6 being held on the control handwheel pilot holds and locates and tighten up;

(e) through mechanical drive bar 5 torque sensor 3 is connected with control handwheel anchor clamps 6, and when guaranteeing that mechanical signal generator take-off lever 10 rotates, control wheel, control handwheel anchor clamps 6, mechanical drive bar 5, torque sensor 3 are done and are followed rotation reliably;

(f) angular displacement sensor 4 is fixed on test-bed or the aircraft main structure, and coaxial with the control wheel rotating shaft, link to each other with control wheel through mechanical linkage bar 11, when control wheel rotated, angular displacement sensor 4 was done and is followed rotation;

(g) adjustment mounting assembly 1 makes control wheel be in the neutral position, and torque sensor 3, angular displacement sensor 4 all are in zero-bit;

(h) through required moment, the angular displacement signal of rotary type mechanical signal generator 2 output control system tests; The motion of drive control wheel; Thereby reach simulated aircraft operating torque and the purpose of handling angular displacement; Can gather through

torque sensor

Claims

An aircraft handling moment with handle the angular displacement analogy method, comprise bracket component (1), rotary type mechanical signal generator (2); Torque sensor (3), angular displacement sensor (4), mechanical drive bar (5); Control handwheel anchor clamps (7), mechanical linkage bar (11), and aircraft handling dish (7); It is characterized in that, this method take following steps:

(a) bracket component (1) is fixed on test-bed or the aircraft main structure;

(b) rotary type mechanical signal generator (2) is fixed on the bracket component;

(c) torque sensor (3) is series on the mechanical signal generator take-off lever (10);

(d) control handwheel anchor clamps (6) are held on the aircraft handling dish (7);

(e) through mechanical drive bar (5) torque sensor (3) is linked to each other with control handwheel anchor clamps (6);

(f) with angular displacement sensor (4) with link to each other with aircraft handling dish (7) through mechanical linkage bar (11);

(g) adjustment mounting assembly (1) makes aircraft handling dish (7) be in the neutral position, and torque sensor (3), angular displacement sensor (4) all are in zero-bit;

(h) drive aircraft handling dish (7) motion through required moment, the angular displacement signal of rotary type mechanical signal generator (2) output control system test; Simulated aircraft operating torque and manipulation angular displacement are gathered operating torque and manipulation angular displacement through force transducer and displacement transducer simultaneously.
2. a kind of aircraft handling power as claimed in claim 1 and manipulation shift simulation method is characterized in that, said bracket component (1) is to do three direction of principal axis position adjustments and the rigid support that axial rotation is regulated.
3. a kind of aircraft handling power as claimed in claim 1 and manipulation shift simulation method; It is characterized in that; Said rotary type mechanical signal generator (2) can produce the moment and the angular displacement control signal of steady state value, and can produce the waveform signal of various frequencies and amplitude as required.
4. a kind of aircraft handling power as claimed in claim 1 and manipulation shift simulation method is characterized in that said mechanical drive bar (5) is the double Hooke's joint torque arm, are formed by fixedly connecting in the universal joint (8) at two and the torque arm (9) at middle part.