A REDUCTION DEVICE OF THE INITIAL ACCELERATION FOR AN AIRCRAFT

摘要

An initial acceleration reducing system for pilotless airplane launcher reduces vibration caused by excessive acceleration on launching by way of controlling the initial oil flow of the oil-hydraulic mechanism of a launcher. The launcher comprises a main body(10), a carrier(12) on which an separable airplane mounted, a locking unit(14) and an accelerator(18). The one side of the accelerator is connected to a power cylinder(20) for draft. A drain line(21) is placed on the power cylinder head. A head block(28) controls drain flow of the power cylinder on launching. An oil flow control bar(30) which is tapered corresponding to a hole(28a) serves to control the excessive speed of a piston rod(23) by closing the drain line(21). The pressure compensated flow control valve(32) controls the speed of the oil flow control bar when the oil flow control bar is pushed by oil hydraulic pressure and opens the drain line. The damping cylinder(34) which is initialized by a control solenoid valve(36) controls the oil flow control bar. The rests are a pilot check valve(38) and a pressure compensated flow control valve(40).