space vehicle force measuring device

Abstract

The invention provides a spacecraft force exertion measuring device, which comprises an upper protection cover, a first output shaft, an angle position sensor, a second output shaft, a volute spiral spring, a deep groove ball bearing, an end cover and a lower protection cover, wherein the upper protection cover and the lower protection cover are connected, the end cover is connected with the lower protection cover, the first output shaft is connected with the upper protection cover, the angle position sensor is respectively connected with the first output shaft and the lower protection cover, one end of the second output shaft is connected with the first output shaft, the other end of the second output shaft passes through the end cover, the deep groove ball bearing is sheathed and connected onto the outer side of the second output shaft and is connected with the end cover, and the volute spiral spring is sheathed and connected onto the outer side of the second output shaft and is connected with the lower protection cover. The spacecraft force exertion measuring device solves the problem that the precise force and moment measurement is needed on partial spacecrafts, meanwhile, the device also has the characteristics that the weight is light, the initial moment is adjustable, the size is small, the compatibility is good, and the like, the accuracy and the reliability of the force measurement are effectively ensured, and wide application prospects are realized.

Description

technical field [0001] The invention relates to a force measuring device, in particular to a space vehicle force measuring device. Background technique [0002] With the development of spacecraft technology, the moving parts used in spacecraft are becoming more and more extensive, and the mechanisms that require precise control of force or torque are also produced. However, general commercial force sensors at home and abroad mainly have the following problems: [0003] 1) Most of the force sensors require more complex conditioning circuits, with large weight and volume; [0004] 2) Generally, it is used as the ground, and the reliability of space use and the influence of the environment on it need special test verification. [0005] The above technical problems limit the use of force measurement technology on space vehicles such as space vehicles, and even limit the use of related moving parts on space vehicles and spacecraft. With the development trend of lightweight spa...

AI Technical Summary

Problems solved by technology

[0003] 1) Most of the force sensors require more complex conditioning circuits, with large weight and volume;

[0004] 2) It is generally used as the ground, and the reliability of space use and the impact of the environment on it need special test verification

[0005] The above technical problems limit the use of force measurement technology on spacecraft such as space vehicles, and even limit the use of related moving parts on space vehicles and spacecraft

With the development trend of lightweight spacecraft, the weight of each load on the spacecraft is required to be smaller and smaller, and the method used by the general force measurement technology cannot meet the needs of the spacecraft due to its large weight and resources.

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