CN103048151A - Aircraft large overload loading environmental simulation testing system - Google Patents

Abstract

The invention discloses an aircraft large overload loading environmental simulation testing system, which comprises a main shaft speed regulating system (2), a two-dimensional acceleration vector distribution system (3) and a main rotating arm (4). The technical scheme of the invention has the beneficial effects that the large overload loading environment of an aircraft is stimulated at an experimental room environment; performances of some critical components of the aircraft are tested and inspected, so that accordance is provided for development and detection and the like of the aircraft. The system is actually debugged, so that the requirements of ground simulation tests can be completely satisfied.

Description

The large overload loading environment of a kind of aircraft simulation experiment system

Technical field

The present invention relates to aircraft test and check system, in particular the large overload loading environment of a kind of aircraft simulation experiment system.

Background technology

Some critical component of the aircraft such as rocket, guided missile, aircraft must carry out test and check by large overload fault secure test before application.Because Hardware-in-loop Simulation Experimentation can repeatedly repeat in the laboratory, its economy and practicality are more and more outstanding, and the effect of bringing into play in the aircraft development process is also more and more important.Advanced emulation technology is the aircraft development and improves one of important means of design, carries out and the research of improving simulation model credibility improves accelerating its development typing, performance, shortens the lead time, saves manpower, reduction of expenditure has great importance.

Summary of the invention

Technical matters to be solved by this invention is to provide the large overload loading environment of a kind of aircraft simulation experiment system for the deficiencies in the prior art.

Technical scheme of the present invention is as follows:

The large overload loading environment of a kind of aircraft simulation experiment system comprises main shaft governing system (2), two dimension acceleration vector assignment system (3), main pivoted arm (4);

Main shaft governing system (2) comprises buncher (21), speed reduction unit (23), electromagnetic clutch (22), main shaft (24), main pivoted arm (4) is fixed on the main shaft (24), main shaft governing system (2) is finished the rotating speed control of main pivoted arm (4), in the ground simulation test of the large overload loading environment of aircraft, provide stable rotating speed;

Two dimension acceleration vector assignment system (3) comprises control motor (33), flexible belt (34), worktable (31), test specimen (32) is fixed on the worktable (31), control motor (33) drives worktable (31) by flexible belt (34) and test specimen (32) rotates together, angular displacement with control motor (33) control test specimen (32), movement locus and speed, according to predefined control law, during the large overload of simulation loading environment, make the normal acceleration direction of axially in 0.2 second, pointing to main pivoted arm (4) of test specimen (32), reach the acceleration requirement of loading environment; When the large overload of simulation is shut down environment, make the tangential or traditional method of indicating the pronunciation of a Chinese character of axially pointing to main pivoted arm (4) in 0.2 second of test specimen (32) to the acceleration direction, making its axial acceleration is 0, reaches the acceleration requirement that large overload is shut down environment.

The beneficial effect of technical solution of the present invention is exactly the large overload loading environment at laboratory environment Imitating aircraft, and some critical component of aircraft is carried out performance test and check, for the development of aircraft, detection etc. provide foundation.System can satisfy the requirement of ground simulation test fully through actual debugging.

Description of drawings

The general structure of the large overload loading environment of Fig. 1 simulation experiment system;

The principle of work of the large overload loading environment of Fig. 2 simulation experiment system, x to be test specimen axially, y to be test specimen radially;

The structure of the large overload loading environment of Fig. 3 two dimension acceleration vector assignment system;

The large overload axial acceleration of Fig. 4 test specimen curve;

2 main shaft governing systems, 3 two dimension acceleration vector assignment systems, 4 main pivoted arms, 21 bunchers, 22 electromagnetic clutchs, 23 speed reduction units, 24 main shafts (containing slip ring), 31 worktable, 32 test specimens, 33 control motors, 34 flexible belts; The H-vector axle, the P normal direction, Q is tangential;

Embodiment

Below in conjunction with specific embodiment, the present invention is described in detail.

With reference to figure 1, this pilot system comprises main shaft governing system 2, two dimension acceleration vector assignment system 3, main pivoted arm 4.

Main shaft governing system 2 comprises buncher 21, speed reduction unit 23, electromagnetic clutch 22, main shaft 24, main pivoted arm 4 is fixed on the main shaft 24, main shaft governing system 2 is mainly finished the rotating speed control of main pivoted arm 4, in the ground simulation test of the large overload loading environment of aircraft, provide stable rotating speed;

Two dimension acceleration vector assignment system 3 structures as shown in Figure 3, two dimension acceleration vector assignment system 3 comprises control motor 33, flexible belt 34, worktable 31, test specimen 32 is fixed on the worktable 31, control motor 33 drives worktable 31 by flexible belt 34 and test specimen 32 rotates together, therefore can control with control motor 33 angular displacement of test specimens 32, movement locus and speed, according to predefined control law, during the large overload of simulation loading environment, make the normal acceleration direction of axially in 0.2 second, pointing to main pivoted arm 4 of test specimen 32, reach the acceleration requirement of loading environment; When the large overload of simulation is shut down environment, make the tangential or traditional method of indicating the pronunciation of a Chinese character of axially pointing to main pivoted arm 4 in 0.2 second of test specimen 32 to the acceleration direction, making its axial acceleration is 0, reaches the acceleration requirement that large overload is shut down environment.

Its principle of work schematic diagram as shown in Figure 2.

During main pivoted arm rotation, its acceleration is:

$\left\{\begin{array}{c}\stackrel{\→}{\mathrm{At}}=r\·\mathrm{d\ω}/\mathrm{dt}\\ \stackrel{\→}{\mathrm{Ar}}=r\·{\mathrm{\ω}}^2\end{array}\right.---\left(1\right)$

Its resultant acceleration is:

$\stackrel{\→}{A}=\stackrel{\→}{\mathrm{At}}+\stackrel{\→}{\mathrm{Ar}}---\left(2\right)$

In the formula

Be respectively tangential acceleration, normal acceleration and the resultant acceleration at place, vector axle axle center.

By above formula as can be known: in the main shaft accelerator, have normal direction and tangential acceleration, but work as stabilization of speed, when main shaft at the uniform velocity rotated with angular velocity omega, main pivoted arm only had normal acceleration, and tangential acceleration is 0.Therefore when main pivoted arm rotated with stable angular velocity, as long as the main pivoted arm of axial sensing of control test specimen is tangential, then the axial acceleration of test specimen was 0; The normal direction of the main pivoted arm of axial sensing of control test specimen, then the axial acceleration of test specimen is r ω ²Therefore as long as the rotating speed of controlling main pivoted arm by the main shaft governing system reaches the acceleration requirement when loading, by the axial location of two-dimensional vector acceleration distribution system control test specimen, just can realize the ground simulation test of the large overload loading environment of aircraft.

The course of work: (1) installs test specimen, make its primitive axis to the tangential coincidence of main pivoted arm; (2) the main shaft governing system begins rotation according to the acceleration of setting, and when main pivoted arm invariablenes turning speed, only have normal acceleration, and tangential acceleration is 0, so the axial acceleration of test specimen is 0; (3) two-dimensional vector acceleration distribution system control test specimen 90-degree rotation in 0.2 second, the normal direction of the main pivoted arm of axial sensing of test specimen, so the normal acceleration of the axial acceleration of test specimen and main pivoted arm is consistent the simulation of the large overload of realization loading environment; (4) the main shaft governing system keeps stabilized (steady-state) speed, two-dimensional vector acceleration distribution system locking test specimen position, whole system stable operation; (5) two-dimensional vector acceleration distribution system is controlled test specimen 90-degree rotation (or reverse rotation 90 degree) in 0.2S again, and the traditional method of indicating the pronunciation of a Chinese character of axially pointing to again main pivoted arm of test specimen is to (or tangential), and its acceleration is 0, and the large overload of realization is shut down the simulation of environment.

It axially transships greatly accelerating curve as shown in Figure 4.

Should be understood that, for those of ordinary skills, can be improved according to the above description or conversion, and all these improvement and conversion all should belong to the protection domain of claims of the present invention.

Claims (1)

1. the large overload loading environment of an aircraft simulation experiment system is characterized in that, comprises main shaft governing system (2), two dimension acceleration vector assignment system (3), main pivoted arm (4);

Main shaft governing system (2) comprises buncher (21), speed reduction unit (23), electromagnetic clutch (22), main shaft (24), main pivoted arm (4) is fixed on the main shaft (24), main shaft governing system (2) is finished the rotating speed control of main pivoted arm (4), in the ground simulation test of the large overload loading environment of aircraft, provide stable rotating speed;

Two dimension acceleration vector assignment system (3) comprises control motor (33), flexible belt (34), worktable (31), test specimen (32) is fixed on the worktable (31), control motor (33) drives worktable (31) by flexible belt (34) and test specimen (32) rotates together, angular displacement with control motor (33) control test specimen (32), movement locus and speed, according to predefined control law, during the large overload of simulation loading environment, make the normal acceleration direction of axially in 0.2 second, pointing to main pivoted arm (4) of test specimen (32), reach the acceleration requirement of loading environment; When the large overload of simulation is shut down environment, make the tangential or traditional method of indicating the pronunciation of a Chinese character of axially pointing to main pivoted arm (4) in 0.2 second of test specimen (32) to the acceleration direction, making its axial acceleration is 0, reaches the acceleration requirement that large overload is shut down environment.

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