The shock-absorber for executive powers of system of stabilization of a spacecraft

Engines-flywheels are widely used in the systems of orientation and stabilization of a small-sized spacecrafts. Today the topical issue is reduction of harmful revolting influences on the engines-flywheels caused by errors of manufacturing and assemblage of ball-bearing support, a rotor-flywheel unbalance, electromagnetic influences. Minimization of negative mechanical influences of separate knots and engine-flywheel elements will allow to improve dynamic properties and spacecraft service life as a whole. In presented article principal causes of occurrence of harmful mechanical influences at engine-flywheel work are considered. The methods of their reduction are considered. The short review of existing types of shock-absorbers and principles of their work and described features of application of shock-absorbers for systems of orientation and stabilization on the base of engines-flywheels is regarded. The construction of the shock-absorber for the electric motor-flywheel is offered. The description of work of the developed shock-absorber is achieved. Under the developed drawings the development type of the shock-absorber is made. The technique of carrying out of measurement of vibrating characteristics is made. The conducted tests are consisted of measurement of vibrating characteristics of the engine-flywheel in normal conditions on free elastic pendant without external vibroprotective devices and also together with it. In the article the graphs of comparison of dependences vibrovelocity from frequency of rotation of a rotor-flywheel of the investigated engine on three orthogonal axes without the shock-absorber and together with it are presented. It is revealed, that a shock-absorber installation on a spacecraft a level of vibrovelocity decreases in comparison with level of vibrovelocity on a landing surface of the engine-flywheel. For definition of quantity of this amplitude peak coefficients effectiveness ratio of application of the shock-absorber from frequency of rotation of a rotor-flywheel are calculated. Corresponding graphs show that shock-absorber installation between the engine-flywheel and a spacecraft are reduced a level of vibrovelocity, transferred to a space vehicle to 3,5 - 4 times (on the average in 2 times) and reduces quantity of the harmful revolting moments transferred to a spacecraft. In conclusion, the detention about application of the developed shock-absorber is given.