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Erecting device and erecting method

A carrier and launcher technology, which is applied in the field of aircraft launch, can solve the problems of large load mass, etc., and achieve the effects of short working cycle, small system pressure and driving force, and fast response speed

Active Publication Date: 2021-06-22
AIR FORCE UNIV PLA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In order to improve the erection effect, at present, most of the actuators are improved, such as mechanical, hydraulic, electric transmission and other driving methods, mainly focusing on how to eliminate factors such as large load mass, diverse working environments, viscosity and external interference. Influences, such as the use of multi-stage oil cylinder control to improve the stability of the erection, there are few improvements to the structure of the erection device

Method used

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  • Erecting device and erecting method
  • Erecting device and erecting method

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Embodiment Construction

[0022] The present invention will be described in detail below in conjunction with the accompanying drawings. When describing the embodiments of the present invention in detail, for the convenience of explanation, the accompanying drawings showing the structure of the device will not be partially enlarged according to the general scale, and the schematic diagram is only an example, and it should not be limited here. The protection scope of the present invention. It should be noted that the drawings are in simplified form and use inaccurate scales, which are only used to facilitate and clearly assist the purpose of illustrating the embodiments of the present invention.

[0023] Such as figure 1 As shown, the erecting device of this embodiment includes a carrier 1 , an erecting cylinder 2 , a launching frame 3 and a booster cylinder 4 . Launcher 3 is arranged on carrier 1, and one end is hinged with carrier 1, and the rear portion of launcher 3 of the present embodiment is hing...

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Abstract

The invention discloses an erecting device and an erecting method. The erecting device comprises a carrier, a launcher arranged on the carrier and an erecting cylinder connected with the launcher, the launcher is hinged to the carrier, the erecting device further comprises a power-assisted cylinder arranged on the carrier, the power-assisted cylinder is located below the launcher, one end of the erecting cylinder is hinged to a free end of the power-assisted cylinder, and the other end of the erecting cylinder is hinged to the launcher. According to the erecting device, the erecting cylinder and the power-assisted cylinder are used in a dual-drive matched mode, stable conversion of a front-mounted direct-push type and a rear-mounted direct-push type of an erecting structure can be achieved, and the erecting device has the advantages of being high in response speed, short in work period, small in piston stroke, small in tilt angle of the inclined erecting cylinder, and small in system pressure and driving force, and the system stably realizes rapid erection and fall-back of the launcher.

Description

technical field [0001] The invention belongs to the technical field of aircraft launching, and in particular relates to an erecting device and an erecting method of a launching platform. Background technique [0002] The launch platform is a special device that completes the launch preparation, starts the launch, and completes the withdrawal of equipment after launch. Its design needs to meet two requirements: one is that the erection process is required to be stable without violent vibration, so as to avoid damage to the equipment on the launch platform. A large impact is generated to ensure that the accuracy of the erection angle meets the requirements; the second is to shorten the erection time as much as possible to reduce the launch preparation time. [0003] The currently widely used erecting mechanisms mainly include erecting arms, vehicle frames and erecting cylinders. For the structure of such erecting mechanisms, please refer to the Chinese invention patent applica...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B66F3/24B66F19/00B64F1/04
CPCB66F3/24B66F19/00B64F1/04
Inventor 史春娟程永强冯刚孙智勇舒涛时建明刘强
Owner AIR FORCE UNIV PLA
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