External circulation energy system for semi-physical simulation test and test method of external circulation energy system

Abstract

The invention discloses an external circulation energy system for a semi-physical simulation test and a test method of the external circulation energy system. The method comprises the steps that aviation hydraulic oil with low ignition temperature is used, the pressure of the hydraulic oil in an oil tank is adjusted to work pressure needed for a servo mechanism through a hydraulic pump, an oil outlet loop and an oil return loop in the external circulation energy system and the servo mechanism form a closed-loop system, the pressure is controlled through an overflow valve, an energy accumulator accumulates energy to compensate for instantaneous high pressure, a high and low pressure circulation system is formed, the servo mechanism is driven to work, and the swing angle of an engine of a carrier rocket is controlled. Under the conditions that rocket fuel is not injected and the engine does not guide flow, the external circulation energy system is adopted, the functions of a servo energy system in the true flying state of the carrier rocket are completely simulated, the problem concerning servo mechanism energy of the simulation carrier rocket is solved, flight attitude control is participated in truthfully, it is ensured that an attitude control system simulation test is carried out, the simulation confidence is improved, economic cost is saved, the safety risk of personnel is lowered, energy conservation and environmental protection are achieved, and there is no special requirement for a site.

Description

technical field [0001] The invention relates to the technical field of launch vehicle attitude control systems, in particular to an external cycle energy system and a semi-physical simulation test method for launch vehicle attitude control semi-physical simulation tests. Background technique [0002] The task of the attitude control system is to ensure the stability of the rocket’s flight attitude. At present, the design of the attitude control system is based on the design of the dynamic response of the system. It is closely related to the dynamic characteristics and nonlinear relationship of the control object, measurement, and control actuators. Accurate measurement and analysis of these properties are very difficult. In the semi-physical simulation test, the rocket motor and servo mechanism used are real products. Therefore, only semi-physical simulation tests can be used for more realistic assessment and verification. [0003] The servo energy system on the launch veh...

AI Technical Summary

Problems solved by technology

[0005] The invention provides an external cycle energy system and a test method thereof for semi-physical simulation tests. Under the condition that rocket fuel is not poured and the engine is not drained, the external cycle energy system is used to completely simulate the servo drive in the real flight state of the launch vehicle. The function of the energy system solves the problem of simulating the energy of the launch vehicle servo mechanism, truly participates in the flight attitude control, ensures the development of the simulation test of the attitude control system, improves the confidence of the simulation, saves economic costs, and reduces personnel safety. risk, realize energy conservation and environmental protection, and have no special requirements for the site

Images