Aircraft stage separation structure and method

Abstract

The invention provides an aircraft stage separation structure and method. The structure comprises an interstage cabin, a spring separation mechanism and a cutting rope assembly. The two ends of the interstage cabin are connected with a booster stage and an aircraft main stage. The spring separation mechanism comprises a bottom plate, an outer sleeve, an inner sleeve, a force bearing plate and a spring. The cutting rope assembly comprises a cutting rope, an electric ignition tube and a flame detonator. The bottom plate is connected with the outer sleeve, the force bearing plate is connected with the inner sleeve, the outer sleeve is mounted on the outer portion of the inner sleeve in a sleeving manner, and the spring is mounted in the inner sleeve. The bottom plate is connected with one endof the interstage cabin, and the force bearing plate is connected with the other end of the interstage cabin. The electric ignition tube and the flame detonator are arranged on the cutting rope, theelectric ignition tube is connected with the flame detonator, and the cutting rope is arranged on the interstage cabin. The structure is simple and reasonable, the connecting constraint between the booster stage and the aircraft main stage is relieved through the cutting rope assembly, meanwhile, the constraint of the spring separation mechanism is also relieved, spring force releases elastic force to push away the booster stage and the aircraft main stage, and the booster stage and the aircraft main stage are separated rapidly.

Description

technical field [0001] The invention relates to the technical field of aircraft separation, in particular to an aircraft inter-stage separation structure and method. Background technique [0002] At present, long-range air defense missiles are generally improved designs based on mature missile platforms, and mainly meet the requirements of long-range air defense by adding a new level of booster. Therefore, missiles generally adopt the overall plan of "main stage + booster". The booster engine is separated from the main-stage missile after its work is completed. Before the separation, the missile is statically stable; after separation, the main-stage body of the missile is statically unstable; when the separation occurs, the flight Mach number of the missile is around 2.3 to 2.6. The characteristics of the missile body change from static stability to static instability in a short period of time before and after separation, and the disturbance torque generated by the disturban...

AI Technical Summary

Problems solved by technology

Although this scheme has a simple structure, it cannot avoid the instability caused by the disturbing torque generated by the projectile disturbance during separation, and it does not have the characteristics of rapid separation.

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