Auxiliary opening device for rocket fairing

Abstract

The invention provides an auxiliary opening device for a rocket fairing. The auxiliary opening device comprises a wing plate, a wing plate opening servo control mechanism, a thrust spring set, a transverse explosive bolt and a longitudinal explosive bolt. The transverse explosive bolt is used for fixedly connecting the bottom of the fairing with the top of the rocket cabin section; the fairing comprises a first fairing and a second fairing; the first fairing and the second fairing are fixedly connected through a longitudinal explosive bolt, and a cavity for protecting the electronic equipment is formed in the first fairing and the second fairing; one end of the thrust spring group is connected with the bottom of the fairing, and the other end is connected with the top of the rocket cabin section; the bottom of the fairing is connected with the top of the rocket cabin section through a rotating mechanism; the fairing is provided with an air inlet, and the wing plate is connected to the air inlet through the wing plate opening servo control mechanism. The structure is simple, safe and reliable, it is guaranteed that pressure inside and outside the fairing is consistent, and the fairing is easier to open.

Description

technical field [0001] The present application relates to the technical field of rocket fairings, in particular to an auxiliary opening device for a rocket fairing. Background technique [0002] At present, in the field of rocket technology, the rocket fairing is made of materials with high strength, light weight, high temperature resistance, and strong radio wave permeability. Space size design. The fairing is used to reduce air resistance, which is conducive to the flight of the arrow body and protects its internal electronic equipment. Before the rocket lifts off, the fairing protects the spacecraft on the ground and ensures the spacecraft's requirements for temperature, humidity, and cleanliness. The fairing shields the spacecraft from aerodynamic forces and aerodynamic heat as the rocket lifts through the atmosphere. After the launch vehicle flies out of the atmosphere, the fairing will be split into two longitudinally along the rocket body and thrown away to complet...

AI Technical Summary

Problems solved by technology

The vacuum inside the cowl requires more thrust or changing the direction of the thrust to open the fairing, and even causes the thrust spring to fail to open the fairing, resulting in rocket launch failure

[0006] 3. Uncertainties in processes such as spring and explosive bolt connections reduce the safety factor of rocket fairing opening

[0007] 4. In terms of unlocking structure: after the spring releases force, the spring force is small, the unlocking mechanism is easy to get stuck, and cannot be controlled according to the requirements, so the system is complicated

[0008] 5. In terms of the number and complexity of spring installation: due to the change of thrust direction, the control requirements can only be fulfilled through system coordination control, so it is necessary to arrange springs in various directions (vertical, horizontal and other multi-directional arrangements), occupying structural space and increasing equipment weight. add insecurity

[0009] 6. In terms of process requirements: the number of spring installations is large, and the layout and installation process is complicated

The assembly efficiency is low, the utilization rate of the rocket is low, and it affects the follow-up installation process

And structural failures are highly random, and it is difficult to guarantee safety reasons

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