Formulation module of active concave mechanical conditions in vibration control system

Abstract

The invention discloses an active recessed mechanical condition making module in a vibration control system. The module includes six sub-modules: (1) a low-level test condition input sub-module; (2) a response amplitude limit point low-level measurement data import sub-module; (3) a high-level test condition input sub-module; (4) a response amplitude limit condition input sub-module; (5) a high-level active recessed condition making sub-module; and (6) a recessed condition display and storage sub-module; wherein the response amplitude limit condition of each response amplitude limit point is input, and the test conditions include amplitude limit frequency range and amplitude limit test magnitude; and the high-level active recessed condition making sub-module successively predicts the response of each response test point under the high-level test condition based on the input information of the (1) to (4) modules according to the linear relation. The making of the active recessed mechanic conditions is fused into a vibration control system, the independent modules of the vibration control system can complete the work to get rid of the defects that the previous condition making excessively depends on the experience of test personnel and massive calculation can be carried out; and meanwhile, the vibration control system can conveniently perform automatic calling of the made recessed conditions, so that the spacecraft mechanical environment testing efficiency can be greatly improved.

Description

technical field [0001] The invention belongs to the field of spacecraft mechanical environment tests, and in particular relates to a module for formulating active concave mechanical conditions in a vibration control system. Background technique [0002] The vibration control system is a very important part of the spacecraft mechanical environment test. It measures the response at the input interface of the spacecraft product and compares it with the reference test conditions to correct the drive signal input to the power amplifier in real time to ensure that the spacecraft The response of the input interface control points is consistent with the reference test conditions. [0003] Vibration control systems generally have a passive response limiter control function. This function is to set the limit level of a certain monitoring point on the spacecraft product in the control system in advance. Test; if the response of the limit point exceeds the set limit level, the control...

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Problems solved by technology

[0004] For some local measurement points on the spacecraft with small damping and peak response peaks, the passive response limiter control function cannot achieve ideal results, and it is generally carried out in combination with mechanical conditions and active concave.

At present, the formulation of active concave mechanical conditions is usually completed by experienced technicians through manual calculation, and then the formulated active concave mechanical conditions are input to the vibration control system; or according to the high-level test conditions of spacecraft sinusoidal vibration test The method described in the patent "Prediction System" (authorization number ZL201110406703.0) uses external independent software that is not related to the vibration control system to calculate the high-level concave condition, and then the test personnel input it to the vibration control system according to the condition. test, but the patent is limited to sinusoidal tests

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