Novel small hydrogen-oxygen engine head

Abstract

The invention relates to a novel small hydrogen-oxygen engine head which belongs to the field of rocket engines. The novel small hydrogen-oxygen engine head comprises an igniting oxygen nozzle (1), a hydrogen welding tip (2), a hydrogen nozzle (3), a niobium sheet (4), a resonant cavity (5), a resonant tube (6), a resonant head (7), an insulating sleeve (8), a jacket (9), a main oxygen welding tip (10), a main oxygen nozzle (11) and an end enclosure (12). The engine is ignited by utilizing a resonant heating phenomenon which is caused when engine propellant is jetted into the resonant tube. A novel pneumatic resonant ignition technique which has the advantages of simple structure and high reliability is adopted; in terms of the structure design, an igniter is organically integrated with the small engine head; and the size of the coaxial hydrogen-oxygen resonant igniter is reduced.

Description

【Technical field】 [0001] The invention relates to a structural device of a novel small hydrogen-oxygen engine head. 【Background technique】 [0002] When an aircraft executes a flight procedure, some control operations need to be completed: such as orbit change, orientation and stabilization in space, rendezvous and docking with other aircraft, deceleration, descent, and landing. These operations are generally realized by controlling the reaction force control system of the aircraft, and its actuator is a small-thrust rocket engine. In addition to being used in the control system, the small-thrust rocket engine is also used in the starting guarantee system of the main engine, which is used to generate overload to ensure that the liquid components enter the liquid storage device, the separation system of the aircraft components, and the protection of the spacecraft in the event of an accident during rocket take-off system and soft landing system, etc., the performance of the ...

AI Technical Summary

Problems solved by technology

If the electric ignition device system is used for a small thrust engine, the volume and weight of the entire small thrust engine head will be greatly increased

In addition, the electric ignition system is susceptible to space radio frequency and static interference, the reliability of the high-voltage circuit system in space is poor, and the electric spark plug often fails due to pollution.

The traditional electric ignition device system does not match the small-thrust engine in terms of weight and reliability, and has become a bottleneck restricting the research and development of small hydrogen-oxygen engines. Therefore, new ignition principles have been explored and researched for small-thrust engines with non-self-igniting propellants with the program

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