公开(公告)号：US3754727A

公开(公告)日：1973-08-28

申请号：US3754727D

申请日：1971-04-28

Applicant: MC DONNELL DOUGLAS CORP

Inventor： DONOVAN B

IPC: B64C13/30 ,  B64C9/00

CPC classification number: B64C13/30 ,  Y10T74/18568 ,  Y10T74/18856 ,  Y10T74/20

Abstract: A flap or slat extension controlled mechanism for engaging outboard ailerons of an aircraft during the initial part of the extension, with a capability of absorbing additional flap or slat extension input. This structure consists of a latch dwell mechanism which comprises a rotary input member, a rotary output member, a pitman of the overcenter linkage type, and a fixed abutment whereby upon rotation of the input member up to a certain angle of rotation, the output member rotates in proportion thereto but beyond that point dwells as a result of the pitman overcenter linkage coming into contact with the abutment member.

Abstract translation: 在延伸的初始部分期间用于接合飞行器的外侧副翼的翼片或板条延伸控制机构，具有吸收附加的翼片或板条延伸输入的能力。 该结构包括一个闩锁停留机构，它包括一个旋转输入部件，一个旋转输出部件，一个超中心连杆式的凹槽，一个固定的支座，当输入部件旋转到一定的旋转角度时，输出部件 由于pitman超中心联动与抵接构件接触，与其成比例地旋转但超出该点。

公开(公告)号：US3738594A

公开(公告)日：1973-06-12

申请号：US3738594D

申请日：1971-08-16

Applicant: MC DONNELL DOUGLAS CORP

Inventor： DONOVAN B ,  WOOD L

IPC: B64C13/00 ,  B64C13/18 ,  B64C13/30

CPC classification number: B64C13/00

Abstract: A controlling mechanism for a direct lift control system which is utilized primarily during the landing phase of aircraft flight to reduce the response time of the aircraft to longitudinal or pitch commands. The system incorporates modulated spoilers to affectuate augmented vertical control of the flight path of the aircraft without necessarily changing the pitch attitude thereof. When the aircraft is preparing to land and the flaps are placed at the desired landing flap angle, the mechanism raises the spoilers on each wing symmetrically to a predetermined bias position. The mechanism thereafter causes the spoilers to operate up and down from this bias position in response to elevator commands generated either manually by the pilot or automatically by the autopilot. The mechanism also includes means to disengage the system automatically during stalls, go-arounds, landing rollout, or manually whenever the pilot desires.

Abstract translation: 一种用于直升机控制系统的控制机构，主要用于飞机飞行着陆阶段，以减少飞机对纵向或俯仰指令的响应时间。 该系统包括调节的扰流板，以影响飞行器的飞行路径的增强垂直控制，而不必改变其俯仰姿态。 当飞机准备着陆并且襟翼被放置在期望的襟翼角度时，该机构将每个翼上的扰流板对称地提升到预定的偏置位置。 此后的机构使得扰流板响应于由驾驶员手动产生的电梯命令或通过自动驾驶仪自动地从该偏置位置上下运行。 该机构还包括在停机，复飞，着陆推出期间或者当飞行员期望时手动断开系统的手段。