| 摘要 |
1,262,567. Controlling helicopters. UNITED AIRCRAFT CORP. 5 Dec., 1969 [28 April, 1969], No. 59402/69. Heading B7G. A pitch control linkage for a helicopter tail rotor incorporates a spring-loaded actuator 36, Fig. 3, operatively connected with a control rod 16 of the linkage for actuating the tail rotor blades to a preselected positive pitch setting upon failure of the control linkage. The actuator is mounted in parallel with rod 16 and adjustably bolted at one end to a fixed structure 50, and at the other end to a pendulum link which connects rod 16 and the servo input link 30. The actuator comprises a cylinder 38, Fig. 4, through which a control rod 68 is reciprocable; a spring 88 is disposed along an extension 76 of the rod between discs 82, 90 carrying O-ring seals 84, 94 and spring-centring bosses 86, 92. Initially, rod 16 is actuated to bring the tail rotor pitch to + 9 degrees and bolts 96, 44 are suitably adjusted (Fig. 4). In operation, right or left movement of rod 16 causes corresponding movement of rod 68 (Fig. 3), spring 88 being compressed by a snap ring 80 on rod 76 or by shoulder 78 of rod 68. Upon failure of some part of the pitch control linkage rod 16 becomes ineffective, whereupon spring 88 expands and the actuator reverts to the centred position (Fig. 4) to provide the optimum + 9 degrees pitch setting which ensures adequate anti-torque force and sufficient directional control in yaw for the emergency. |
