Design method for vertical constant force system

Abstract

The invention provides a design method for a vertical constant force system. The vertical constant force system comprises a balance point constant force spring module, a gear and rack compensation module and a data acquisition and control module and is used for compensating the gravity generated in the process of ground validation of a spacecraft. The balance point constant force spring module comprises a compressed spring, a linear guide rail, linear bearings, rolling bearings, a spring jacket and connecting parts and is used for providing constant force at a balance point. The gear and rack compensation module comprises a gear and rack set, a motor and a fixing plate. When the spacecraft deviates from the balance point, the gear and rack compensation module can drive the balance point constant force spring module arranged at the lower end of the gear and rack compensation module to do acceleration and deceleration motion or uniform motion in the vertical direction to adjust force on the compressed spring, so constant force output is guaranteed. The data acquisition and control module comprises a motor driver, a control card, a high-precision tension sensor, a displacement sensor, a data acquisition card and an upper computer PC. The vertical constant force system can be used for providing the constant force in the vertical direction and compensating the gravity of the spacecraft and has the advantages being stable in operation, not prone to external interference, high in constant force accuracy and the like.

Description

Technical field [0001] The invention belongs to the technical field of ground verification of spacecraft navigation, guidance and control systems, and in particular relates to a method for realizing a vertical constant force system. Background technique [0002] Aerospace engineering is a high-risk, high-investment, high-reward, highly complex and high-precision system engineering. Its development level determines whether it can seize the high-tech commanding heights and maximize the use of space resources. There is no doubt that it is imminent to actively carry out aerospace technology research in our country. However, the space environment is extremely harsh. In order to successfully complete space missions, sufficient experiments must be carried out on the ground. Therefore, various space agencies at home and abroad attach great importance to the experimental verification of spacecraft on the ground. [0003] One of the most important features of the space environment is ...

AI Technical Summary

Problems solved by technology

The patent application number is CN201220400797 "Semi-active gravity compensation structure air bearing six degrees of freedom analog satellite device" announced a "parallel connection" scheme through the integration of motor ball screw and cylinder suspension to compensate the gravity of the spacecraft and Provides the freedom of movement in the vertical direction, which solves the problem that the air flotation method can only perform five-degree-of-freedom movement simulation, but its structure is relatively complicated, the air compression processing equipment occupies a large area, and the cost of marble is expensive; the patent application number is CN201310466806 "A Design Method for Unconstrained Suspension Active Gravity Compensation System" published a method to compensate the gravity of the spacecraft through hanging wire tension suspension to provide the freedom of movement in the vertical direction, but when the momentary force on the spacecraft exceeds the gravity of the spacecraft, The tension on the hanging wire changes suddenly, which puts forward extremely high requirements on the performance of the compensation system; therefore, it is necessary to find a simple and effective method to provide constant force for the suspension compensation system

[0004] In the existing constant force system of this kind, steel wire ropes are used to provide constant force. When the force on the steel wire rope changes, it will actively compensate, but the force on the steel wire rope changes instantaneously. When the external force on the spacecraft is greater than the gravity of the spacecraft, the steel wire rope Relaxation, there is a risk of instantaneous failure in compensation; the components designed by the spring combination satisfy the spacecraft within a certain range of motion, and the force provided by the spring system is constant, but this method requires high accuracy of the spring coefficient, the range of motion is small, and the structure is complex ; The design method of dual motors and torsion springs, the control is complex, and the vertical direction is easily disturbed

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