An actuator with mechanical logic control capability
A technology of control ability and mechanical logic, applied in the chassis and other directions, can solve the problems of increasing the complexity of the electrical control system of the landing gear system, increasing the complexity of the hydraulic (air-conditioning) system, etc., to reduce the number, complexity, and oil The effect of the flow path
Active Publication Date: 2018-11-27
JIANGXI HONGDU AVIATION IND GRP
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Problems solved by technology
That is, the logic control relationship between retracting the position locking actuator and the landing gear retracting actuator logic control is completely dependent on electrical signals to achieve logic control, which increases the complexity of the electrical control system of the landing gear system. In addition, the two processes are connected through parallel hydraulic ( Air-conditioning) pipeline independent pressure supply, which increases the complexity of the hydraulic (air-conditioning) system
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Embodiment Construction
[0014] The embodiment of the present invention is: an actuator with mechanical logic control capability, such as figure 1 As shown, it mainly includes hydraulic oil return pipe 1, hydraulic logic outlet pipe 2, hydraulic inlet pipe 3, air-conditioning logic outlet pipe 4, outer cylinder 5, air-conditioning inlet pipe 6, emergency actuating lever 7, conventional actuating lever 8, etc. .
[0015] On the outer cylinder 5 along the extension direction of the actuator cylinder, as shown in the direction A, five nozzles are arranged, which are cold air inlet pipe 6, cold air logic outlet pipe 4, hydraulic inlet pipe 3, hydraulic logic outlet pipe 2, and Hydraulic oil return port pipe 1. Each nozzle is threadedly connected to the outer cylinder 5, and is respectively connected to external auxiliary equipment, such as figure 2 As shown, it includes an emergency system pressure supply port 12 , a hydraulic system pressure supply port 13 , a hydraulic system oil return port 14 and a...
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The invention relates to an actuating cylinder with mechanical logic control capability, which comprises an outer cylinder (5), and the outer cylinder (5) is respectively arranged with a hydraulic oil return pipe (1), a hydraulic logic outlet pipe (2), a hydraulic Inlet pipe (3), air-conditioning logic outlet pipe (4), air-conditioning inlet pipe (6) and other 5 nozzles, emergency actuating lever (7) and conventional actuating lever (8) are respectively installed inside the outer cylinder (5) , through sealing to form a conventional extension cavity (10) and a conventional retraction cavity (11); the conventional actuating rod (8) runs in the extending direction of the actuating cylinder, and is executed and realized by controlling the hydraulic logic stroke or the emergency logic stroke Logical control of actuators. The invention simplifies the logical control relationship between the retractable position locking actuator of the aircraft landing gear and the retractable actuator of the landing gear, reduces the complexity of the electro-hydraulic control of the landing gear system, and improves the reliability of the entire logic control system.
Description
technical field [0001] The invention relates to the technical field of aircraft hydraulic system structure design, in particular to an actuator structure with mechanical logic control capability. Background technique [0002] Before the aircraft lands, in order to lower the landing gear normally, the hydraulic system should supply the actuating cylinder for retracting the landing gear to ensure that the retracting position lock of the landing gear is normally unlocked, and then supply the actuating cylinder for retracting and retracting the landing gear to ensure that the landing gear is retracted. The drop frame is lowered normally. When the hydraulic system fails, the emergency air-conditioning system shall be able to ensure the emergency unlocking of the retracted position lock of the landing gear and supply pressure to the actuating cylinder for retracting and extending the landing gear in an emergency. [0003] In the process of lowering the landing gear, it mainly inc...
Claims
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IPC IPC(8): B64C25/22B64C25/30
CPCB64C25/22B64C25/30
Inventor 鲁胜陈红裴华平敖文伟张改华钟小宏朱波黄志军周恒黄勋李琼李妍
Owner JIANGXI HONGDU AVIATION IND GRP