Aircraft ejection traction rod control system
A technology of control system and tow bar, which is applied in the direction of launch/tow transmission, etc., can solve the problems of lack of safety measures, unfavorable safe flight of aircraft, and low tolerance of operator's operation error.
Inactive Publication Date: 2019-12-13
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology
[0002] The aircraft relies on the ejection tow bar installed on the landing gear to achieve ejection take-off. Reliable control of the ejection tow bar so that it can be smoothly stowed or lowered under the required conditions is crucial to the safe flight of the aircraft. The current The control system cannot guarantee reliable control of the ejection tow bar, and lacks safety measures, and has a very low tolerance for operator errors, which is not conducive to the safe flight of the aircraft
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[0045] The application will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the related application, not to limit the application. In addition, it should be noted that, for ease of description, only parts relevant to the present application are shown in the drawings.
[0046] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and embodiments.
[0047] It should be noted that in the description of this application, the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. The terms of the indicated direction or positional relationship are based on the direction or positional ...
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The invention discloses an aircraft ejection traction rod control system. The aircraft ejection traction rod control system comprises a hydraulic actuation cylinder, an electromagnetic valve and a controller, wherein a piston rod of the hydraulic actuation cylinder is used for being connected with an aircraft ejection traction rod; the electromagnetic valve is connected with the actuation cylinderthrough an oil pipe; the controller is electrically connected with the electromagnetic valve to control the electromagnetic valve in an oil supply state; the electromagnetic valve supplies oil to thehydraulic actuation cylinder, and the piston rod of the hydraulic actuation cylinder extends out to place down the aircraft ejection traction rod; and when the electromagnetic valve is in an oil return state, the hydraulic actuation cylinder returns the oil to the electromagnetic valve, and the piston rod of the hydraulic actuation cylinder shrinks back to withdraw the aircraft ejection tractionrod.
Description
technical field [0001] The application belongs to the technical field of control of an aircraft ejection tow bar, and in particular relates to a control system of an aircraft ejection tow bar. Background technique [0002] The aircraft relies on the ejection tow bar installed on the landing gear to achieve ejection take-off. Reliable control of the ejection tow bar so that it can be smoothly stowed or lowered under the required conditions is crucial to the safe flight of the aircraft. The current The control system cannot guarantee reliable control of the ejection tow bar, and lacks safety measures, and has a very low tolerance for operator errors, which is not conducive to the safe flight of the aircraft. [0003] The present application is proposed in view of the above-mentioned defects of the prior art. Contents of the invention [0004] The purpose of the present application is to provide a control system for ejecting the tow bar of an aircraft, so as to overcome or a...
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IPC IPC(8): B64F1/06
CPCB64F1/06
Inventor 刘泽华任芳
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA