Hydrogen peroxide posture control system applied to solid-liquid hybrid power carrier rocket

Abstract

The invention relates to the field of carrier rocket posture control systems, in particular to a hydrogen peroxide posture control system applied to a solid-liquid hybrid power carrier rocket. The system includes four pitching rolling posture control engines and two yawing posture control engines; the two yawing posture control engines are arranged in the positive and negative directions of a Z axis of the outer side of a rocket three-sublevel main engine separately; the first pitching rolling posture control engine is installed on the surface of the main engine, and a 40-degree included angleis formed between the first pitching rolling posture control engine and the negative direction of the Z axis; the fourth pitching rolling posture control engine is installed on the surface of the main engine, and a 40-degree included angle is formed between the fourth pitching rolling posture control engine and the positive direction of the Z axis; the other two pitching rolling posture control engines are installed symmetrically on the surface of the main engine relatively to an XZ plane. According to the scheme, six posture control engines are adopted as propelling force, the number of thrusters is small, invalid loads can be reduced to a great extent, and the conveying capability of the whole carrier rocket is improved. Meanwhile, the failure rate of the posture control system is decreased, and the stability and safety of the system are improved.

Description

technical field [0001] The invention relates to the technical field of launch vehicle attitude control systems, in particular to a hydrogen peroxide attitude control system for solid-liquid hybrid launch vehicles. Background technique [0002] The attitude control system is an essential part of the third sub-stage of the launch vehicle. Its functions include the three-axis attitude control of pitch, yaw, and roll in the gliding section of the third sub-stage; the sinking of the liquid oxidant before the ignition of the main engine of the third sub-stage; the braking after the main engine of the third sub-stage stops working; Sub-level auxiliary power system. [0003] The existing medium and large launch vehicles mainly adopt the 12-thruster scheme (a total of three groups, respectively controlling the three axes of pitch, yaw, and roll, four in each group), or the 24-thruster scheme (a set of redundant design ). For solid-liquid small launch vehicles, the total mass and m...

AI Technical Summary

Problems solved by technology

For solid-liquid small launch vehicles, the total mass and moment of inertia of the third sub-stage are small, and the controllability is high. The conventional attitude control system contains too many attitude control engines, which will bring greater risk factors. Reduce safety and reliability; it will increase a large number of invalid loads and reduce the carrying capacity of solid-liquid small launch vehicles;

[0004] At present, attitude control engines used in launch vehicle power systems, spacecraft, space stations and other spacecraft at home and abroad are divided into three types: dual-component attitude control engines, single-component attitude control engines and air-cooled attitude control engines. The oxidant and fuel in the engine require two independent propellant supply systems, with complex structure, large dead load, high thrust, and high cost. Most of them are used in the final stage of large launch vehicles, and are not suitable for small solid-liquid launch vehicles.

Mono-component engines basically use toxic propellants such as hydrazine and dinitrogen tetroxide to propel the system. The production, storage, transportation and use of these propellants are relatively complicated, and the maintenance, replacement, inspection, and filling of the propulsion system require small Leakage may endanger the safety of personnel

The use of toxic propellant propulsion systems is increasingly restricted in the context of environmental protection and human health maintenance

Air-cooled attitude control engines mostly use inert gas as the working medium, with low temperature, low specific impulse, and low efficiency. They are mostly used for attitude control of satellites, and their ability to control the third sub-stage of launch vehicles is weak

In addition, the conventional single-component engine and the air-cooled attitude control engine require an independent extrusion propellant supply system, and the dead load is also relatively large

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