公开(公告)号：US3799700A

公开(公告)日：1974-03-26

申请号：US14397071

申请日：1971-05-17

Applicant: TEXTRON INC

Inventor： BROEKHUIZEN W ,  COVINGTON C

IPC: B64C27/46 ,  B64C29/00

CPC classification number: B64C29/0033 ,  B64C27/46

Abstract: An aircraft proprotor blade having a leading edge spar with upper and lower after body skins secured at their leading edges to the upper and lower trailing edges, respectively, of the spar and coupled together along the trailing edges thereof. Honeycomb body halves are secured to and are substantially coextensive with each skin. The honeycomb cells are oriented substantially perpendicular to the blade chord plane with confronting ends of the cells intercised and adhesively bonded at the blade chord plane.

Abstract translation: 一种具有前缘翼梁的飞机推进器叶片，其在身体皮肤分别在其前缘固定到翼梁的上和下后缘并且沿着其后缘连接在一起，具有上部和下部。 蜂窝体半部固定在每个皮肤上并基本上与每个皮肤共同延伸。 蜂窝单元取向为基本上垂直于叶片弦平面，其中细胞的相对端在叶片翼平面处被间隔并粘合。

公开(公告)号：US3804552A

公开(公告)日：1974-04-16

申请号：US26911472

申请日：1972-07-05

Applicant: TEXTRON INC

Inventor： COVINGTON C

IPC: B64C27/35 ,  B64C27/41 ,  B64C27/52

CPC classification number: B64C27/35 ,  B64C27/41

Abstract: Helicopters traveling in level flight are considered to be operating in a one ''''g'''' condition; that is, the rotor is producing lift equal to the vehicle weight. In a helicopter equipped with a gimbaled, teetering rotor, which cannot transmit a rotor moment into the mast head, a control moment about the aircraft center of gravity, a requirement to command a change in aircraft attitude, is obtained by tilting the rotor and hence its thrust vector. Thus, the control moment is a function of rotor thrust and tilt angle. When such an aircraft is subjected to a sudden descending maneuver, the rotor thrust will be reduced toward a zero or negative ''''g'''' condition. Consequently, the control moment capability will be reduced to zero and the aircraft becomes uncontrollable. However, the rotor is capable of producing a moment, if cyclic pitch is introduced to the rotor through a normal helicopter control system. This moment may be transmitted across a gimbal, down the supporting rotor mast to exert a controlling moment about the helicopter center of gravity by means of an elastomeric hub spring, connecting the gimbaled rotor hub to the rotor mast. This spring attaches to a first flange as part of the rotor hub yoke, and a second flange bolted to the supporting mast.

Abstract translation: 在水平飞行中行驶的直升机被认为在一个“g”条件下运行; 也就是说，转子正在产生等于车辆重量的升力。 在配备有不能将转子力矩传递到桅杆头部的万向节，转向转子的直升机中，关于飞机重心的控制力矩，通过倾斜转子获得飞行器姿态变化的要求，因此 其推力矢量。 因此，控制力矩是转子推力和倾角的函数。 当这种飞机遭受突然下降的机动时，转子推力将朝向零或负“g”状态减小。 因此，控制力能力将降至零，飞机变得不可控制。 然而，如果通过正常的直升机控制系统将循环螺距引入转子，则转子能够产生力矩。 这一时刻可以穿过支撑转子桅杆上的万向架，通过弹性轮毂弹簧，将平衡的转子轮毂连接到转子桅杆上，围绕直升机重心施加控制力矩。 该弹簧附接到作为转子毂轭的一部分的第一凸缘，以及螺栓连接到支撑杆的第二凸缘。