| 摘要 |
military equipment, guided missiles and projectiles. SUBSTANCE: interrupted pneumatic actuator of the control system of a spin-stabilized missile, having a power amplifier and an actuator linked with the control surfaces, uses also an adder, whose one input serves as an input of the actuator and is connected to the output of the missile control equipment, two-step relay with a negative hysteresis loop of a variable width, whose output is connected to the input of the power amplifier. The actuator is also provided with a linearizing oscillator, whose output is connected to the second input of the adder, and a device for setting the phase lead of the actuator during the missile flight, whose output is connected to the hysteresis loop width control inputs of the two-step relay. The dynamics is monitored during equivalent lag at a supply pressure corresponding to the selected missile flight conditions, for example, the maximum and minimum flight speeds, and readout of information on angular position of the control surfaces from the output of the control surface angle sensor, applied to the input of the two-step relay with a negative hysteresis loop of a variable width from the output of the signal generator is a periodic square- wave signal at a frequency equal, for example, to the maximum spin rate of the missile with an amplitude corresponding to the maximum travel of the control surfaces (according to the limits), the angle of the control surfaces and the preset signal are fixed on the registering device, the time of start-up, movement and actuation of the actuator at a travel of the control surfaces from one extreme position (limit) to the other and back is determined, time taue of the equivalent lag of the actuator according to a definite mathematical dependence is determined. EFFECT: simplified design of the actuator, enhanced accuracy and reliability of its operation, simplified monitoring of the actuator dynamics. 2 cl, 4 dwg
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