Recovery system of helicopter

A recovery system and helicopter technology, applied in aircraft parts, aircraft landers, parachutes, etc., can solve the problems of safety devices without alarm devices, threatening the safety of ground personnel, etc., to increase the success rate, increase landing time, and reduce damage. Effect

Active Publication Date: 2014-04-02
BEIJING RES INST OF SPATIAL MECHANICAL & ELECTRICAL TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] (3) The safety device does not have an alarm device. Once the helicopter falls unexpectedly, it will threaten the safety of the ground personnel

Method used

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  • Recovery system of helicopter
  • Recovery system of helicopter
  • Recovery system of helicopter

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Embodiment Construction

[0023] figure 1 It is a schematic diagram of the position of the patented system of the present invention, and the recovery system device of the helicopter is installed above the rotor head of the helicopter.

[0024] figure 2 It is a schematic diagram of the composition and position of the umbrella cabin of the patent of the present invention. The helicopter recovery system of the present invention comprises an umbrella cabin, an adapter device 5 and a control module, the umbrella cabin and the helicopter propeller main shaft 6 are fixedly connected through an adapter device, and are positioned above the rotor; wherein the umbrella cabin includes an umbrella cabin cover 1, a parachute bag 2 , catapult 3, umbrella cabin floor 4; umbrella cabin cover 1 is circular or streamlined; Inside the umbrella cabin cavity formed by the umbrella cabin cover 1 and the umbrella cabin bottom plate 4; the catapult 3 is placed inside the umbrella cabin cavity and fixedly installed at the ce...

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PUM

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Abstract

The invention relates to a recovery system of a helicopter. The recovery system comprises a parachute bay, a switching device and a control module; the parachute bay is fixedly connected with a propeller spindle of the helicopter through a switching device, and is arranged above a rotor wing, wherein the parachute bay comprises a parachute bay cover, a parachute bag, an ejector and a bottom plate of the parachute bay; the parachute bay cover is in a circular or streamline shape; the parachute bay cover is provided with a semi-circular or streamline-shaped spherical shell, and is buckled on the bottom plate of the parachute bay; the parachute bag is stacked in a parachute bay cavity which is formed by the parachute bay cover and the bottom plate of the parachute bay; the ejector is arranged inside the parachute bay cavity, and is fixedly arranged in the center of the bottom plate of the parachute bay; a separation part of the ejector is fixedly connected onto the parachute bay cover; the control module is loaded on the helicopter, and is used for starting the recovery system of the helicopter. The system is used for reducing the landing speed of the helicopter when the helicopter has an accident, so that the landing time is prolonged, personnel on the ground can evacuate conveniently, and the damage of the helicopter when the helicopter hits the ground is reduced.

Description

technical field [0001] The invention belongs to the technical field of recovery and landing of space optical remote sensors, and relates to a recovery system for a helicopter that can provide a safe landing function for the helicopter. Background technique [0002] Under normal control conditions, the helicopter can achieve a safe landing by adjusting its own attitude and propeller speed. The important information stored on the aircraft and the optical remote sensor crashed, which not only caused a huge loss of money, but also lost the valuable monitoring data of the optical remote sensor, and would cause serious danger to the safety of ground personnel. [0003] In view of the above situation, the current existing protection measures adopt the addition of parachute devices on the helicopter to achieve the purpose of safe and slow landing, but its design has the following deficiencies: [0004] (1) The parachute is ejected after blasting with a rocket launcher. The rocket l...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D45/04B64D17/80
Inventor 滕海山张卫卫赵曙光刘涛姚毅刚李鑫谢冰林招荣唐明章
Owner BEIJING RES INST OF SPATIAL MECHANICAL & ELECTRICAL TECH
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