Parachute assembly suitable for rocket

Abstract

The invention relates to a parachute assembly applicable to rockets, which comprises a cylinder-shaped cabin body (1) the two ends of which are connected with other parts of a rocket; the side wall of the cabin body (1) is provided with a hatch where a hatchcover (2) and a hatchcover opening device are arranged; the hatchcover (2) is connected with a retarding parachute body through a hauling rope, the retarding parachute body is connected with a main parachute body through a retarding parachute connecting rope, and the main parachute body is connected with the cabin body (1) through a main parachute connecting belt. According to the appearance structure characteristic of a meteorocket (or a sounding rocket), in the parachute assembly, the hatch and the hatchcover thereof are arranged on the side wall of the cabin body and the parachute hatchcover is released in side direction of the cabin body, thus overcoming the defects in the prior art, without designing a rocket detaching mechanism and with simple structure and low cost; and the separated rocket body is avoided, thus causing no interference on the parachute, with good safety and reliability; and the interfaces among each part of the rocket are simple, thus improving the parachute assembly quality and reducing the using failure rate.

Description

technical field [0001] The invention relates to a parachute device, in particular to a parachute device used on a rocket used in fields such as meteorology and sounding. Background technique [0002] The process of pulling out the parachute from the rocket parachute to opening is a key technology that needs to be solved in the design of rocket parachutes used in meteorology, sounding and other fields. For meteorological rockets or sounding rockets with a cross-sectional diameter of the parachute less than 200mm, due to the high parachute opening speed (generally greater than 150m / s), the small parachute compartment and the complicated situation of the tail parachute opening channel, the separation mechanism is often used to separate the rocket The nose cone and the rocket body are pushed away at a speed of not less than 10m / s, and the parachute is opened along the rocket axis. There are following problems in this parachute technology: [0003] 1. The design of the separati...

AI Technical Summary

Problems solved by technology

[0003] 1. The design of the separation mechanism between the rocket nose cone and the rocket body is relatively complicated, and its development and equipment costs are relatively high

[0004] 2. After the rocket head body is separated, the parachute will quickly deploy and decelerate the rocket nose cone, while the rocket body is still moving forward at the same speed as when the parachute was opened. It is very small, so the high-speed moving arrow will catch up with the deployed parachute and interfere with it, which will cause the parachute to fail, and its safety and parachute opening reliability are low

[0005] 3. The interface relationship between parachute-nose-cone-capsule-rocket body is relatively complicated. The parachute is usually shipped in a loose state (unpacked state), and the parachute is packaged and assembled with the rocket by a non-professional parachute manufacturer. It is so easy to cause parachute damage. The technical status and assembly quality are not easy to control, which increases the accident rate of parachute opening

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