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Aircraft carrier carrier-borne aircraft electromagnetic launch device with inclining function

A tilting function and electromagnetic ejection technology, which is applied in the direction of launching/dragging transmissions, etc., can solve the problems of high equipment power requirements and no tilting function

Inactive Publication Date: 2018-01-09
荆门思安机械设备有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] At present, the electromagnetic ejection devices for carrier-based aircraft that have been applied for or authorized are all set horizontally and have no tilt function. If you want to eject large-tonnage carrier-based aircraft such as fighter jets, you need greater ejection force and faster take-off speed. High requirements on equipment power

Method used

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  • Aircraft carrier carrier-borne aircraft electromagnetic launch device with inclining function
  • Aircraft carrier carrier-borne aircraft electromagnetic launch device with inclining function
  • Aircraft carrier carrier-borne aircraft electromagnetic launch device with inclining function

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Embodiment Construction

[0011] Summary of the Invention The specific implementation of the present invention has been described in detail, and will not be repeated here. It needs to be explained: the linear motor of the present invention adopts a tubular linear motor with a long stator and a short mover. The working principle of this linear motor is a known technology. , will not be repeated here, certainly the linear motor of the present invention needs necessary control equipment; If the carrier-based aircraft of small tonnage such as ejection fighter is to be launched, the movable ejector is in a horizontal state.

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PUM

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Abstract

The invention provides an aircraft carrier carrier-borne aircraft electromagnetic launch device with an inclining function. The aircraft carrier carrier-borne aircraft electromagnetic launch device ismainly used for aircraft carrier carrier-borne aircraft flying assistance, has the inclining function and is low in requirement for equipment power. The aircraft carrier carrier-borne aircraft electromagnetic launch device is composed of a platform, a static ejector and a movable ejector. According to the work principle of the aircraft carrier carrier-borne aircraft electromagnetic launch device,a carrier-borne aircraft is parked on the platform and clamped, at the moment, the platform is located at the left end of the static ejector, and a power source of a suspension electromagnet A is started to enable the platform to be suspended; then forward power sources of two linear motor movers are started, and the linear motor movers drive the platform to move forwards on the static ejector inan acceleration mode; when the platform moves to the left end of the movable ejector, a jacking hydraulic system jacks up the right end of the movable ejector, and the platform and the carrier-borneaircraft upwards incline by a certain angle to enable the carrier-borne aircraft to take off; and after the carrier-borne aircraft takes off, reverse power sources of the two linear motor movers are started, and the linear motor movers move backwards along linear motor stators to drive the platform to move backwards to enable the platform to be reset to wait taking-off of a next carrier-borne aircraft.

Description

technical field [0001] The invention is mainly used for the flight aid of the carrier-based aircraft of an aircraft carrier. Background technique [0002] At present, the electromagnetic ejection devices for carrier-based aircraft that have been applied for or authorized are all set horizontally and have no tilt function. If you want to eject large-tonnage carrier-based aircraft such as fighter jets, you need greater ejection force and faster take-off speed. High requirements on equipment power. Contents of the invention [0003] The present invention solves the above problems. It has a tilting function and requires low equipment power; it consists of a platform (1), a stationary catapult (11), and a movable catapult (12); the stationary catapult (11) mainly includes two A symmetrically arranged linear motor stator (2) and corresponding linear motor mover (3), central shaft (4), base (8), connecting plate (9); the movable ejector (12) mainly includes two symmetrical Arra...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F1/06
Inventor 彭宝安
Owner 荆门思安机械设备有限公司
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