Three-dimensional general force measuring platform for satellite force limit vibration test

Abstract

The invention discloses a three-dimensional general force measuring platform for a satellite force limit vibration test. The three-dimensional general force measuring platform comprises an upper auxiliary tool, a lower auxiliary tool and a three-dimensional force sensor arranged between the two auxiliary tools, wherein the three are in mechanical connection, and the pretightening force of the mechanical connection can ensure that the contact surface of the three are in close cooperation, the pretightening force between the three-dimensional force sensor and the auxiliary tools is greater than the maximum force born by force sensors and the multiple force sensors bear uniform forces when a force measuring device bears a vertical or horizontal force; and force combination and resultant moment calculation are performed on force signals obtained by the three-dimensional force sensor through a force signal adjusting system, and the force signals are in electric communication with a vibration test control system for force limit control. The three-dimensional force measuring platform provided by the invention can cooperate with vibration test clamps of different products for use, and has the advantages of high matching, good frequency transmission characteristics and saved test cost.

Description

technical field [0001] The invention belongs to the field of mechanical environment tests of spacecraft, and in particular relates to a force measuring device used for force limit control vibration tests of spacecraft. Background technique [0002] In domestic spacecraft vibration tests, traditional acceleration control methods have been widely used. However, this method has obvious defects in the resonance frequency band of spacecraft products. During the vibration test process, due to the difference in interface impedance, the spacecraft structure will experience an acceleration response much higher than the actual launch environment, that is, the problem of over-testing will occur. It will cause damage to the payload subsystems, components and even the main structure of the antenna, solar wing, power supply, and various sensors installed on the spacecraft, reducing the reliability and life of the spacecraft. [0003] The force limit control vibration test method is based...

AI Technical Summary

Problems solved by technology

However, this method has obvious defects in the resonance frequency band of spacecraft products. During the vibration test process, due to the difference in interface impedance, the spacecraft structure will experience an acceleration response much higher than the actual launch environment, that is, there will be problems in the over-test, and the over-test will Causes damage to the payload subsystems, components and even the main structure of the antenna, solar wing, power supply, and various sensors installed on the spacecraft, reducing the reliability and life of the spacecraft

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