公开(公告)号：US4003532A

公开(公告)日：1977-01-18

申请号：US666590

申请日：1976-03-15

申请人： Don L. Adams, Sr. ,  Raymond G. Johnson, Jr.

发明人： Don L. Adams, Sr. ,  Raymond G. Johnson, Jr.

IPC分类号： G05D1/00 ,  B64C11/34 ,  G05D1/08

CPC分类号： G05D1/0061

摘要： The automatic heading retention mode of operation of an automatic flight control system for a rotary wing aircraft is discontinued and reestablished through the use of a logic circuitry responsive to the yaw rate, bank angle and airspeed of the aircraft and to the force applied to the cyclic pitch control member by the pilot. The logic circuitry provides for the isolation of information commensurate with left and right turns and summation of the yaw rate and bank angle in each direction to determine if automatic disengagement of the heading hold is warranted.

摘要翻译： 通过使用响应于飞行器的横摆角速度，倾斜角度和空速以及施加到循环的力的逻辑电路来停止并重新建立用于旋翼飞机的自动飞行控制系统的自动航向保持操作模式 调速员由飞行员。 逻辑电路提供与左右匝相当的信息的隔离以及每个方向上的横摆角速度和倾斜角的总和，以确定是否有必要自动分离航向。

公开(公告)号：US4103848A

公开(公告)日：1978-08-01

申请号：US775670

申请日：1977-03-08

申请人： Raymond G. Johnson, Jr. ,  Lou S. Cotton ,  David J. Verzella

发明人： Raymond G. Johnson, Jr. ,  Lou S. Cotton ,  David J. Verzella

IPC分类号： B64C27/06 ,  G05D1/08 ,  B64C11/44

CPC分类号： G05D1/0858

摘要： A helicopter stabilator, combining the functions of tail stabilizer and aircraft elevator, has its angle of incidence with respect to the helicopter controlled by means of a pair of reversible actuators acting in series, controlled in a closed-loop fashion by electronic hardware, the controls being disconnected when the actuators fail to track within a threshold disparity of either position or rate of change of position of each other. A test switch introduces an imbalance to test the fault circuitry. The stabilator is biased to assume a maximum incidence position at low speeds, including hover; and inputs from airspeed and collective pitch position cause it to assume a substantially level position at higher, cruise speeds. A pitch rate gyro input controls the stabilator for stable flight against pitch-inducing flight commands and external effects, such as gusts. In one embodiment a canted tail rotor which provides tail lift; to overcome tail-up and tail-down effects of the downward component of the tail rotor due to more or less thrust and real or apparent lateral accelerations, a lateral accelerometer is used. To avoid main rotor downwash against the stabilator at hover, the lateral accelerometer and collective pitch inputs are washed-out at low speeds. The bias allows final adjustment for high speed flight.

摘要翻译： 结合尾翼稳定器和飞机升降机的功能的直升机稳定器具有相对于直升机的入射角，该直升机通过一对串联的可逆致动器控制，以电子硬件以闭环方式控制，控制 当执行器在任一位置的阈值差异或彼此的位置变化率之间不能跟踪时，断开连接。 测试开关引入不平衡来测试故障电路。 稳定器被偏置以在低速下呈现最大入射位置，包括悬停; 并且来自空速和总体俯仰位置的输入使其在较高的巡航速度下呈现基本水平的位置。 俯仰率陀螺仪输入控制稳定飞行器对于俯仰引导飞行命令和外部效应（如阵风）的稳定飞行。 在一个实施例中，提供尾部提升的倾斜尾部转子; 为了克服由于或多或少的推力和实际或明显的侧向加速度引起的尾部转子的向下部件的尾随和尾随效应，使用横向加速度计。 为了避免主转子在悬停时对稳定器进行下冲洗，侧向加速度计和集体倾斜输入以低速冲洗掉。 偏差允许最终调整高速飞行。

公开(公告)号：US4534702A

公开(公告)日：1985-08-13

申请号：US565668

申请日：1983-12-27

申请人： Raymond G. Johnson, Jr. ,  Bill L. Trustee ,  William C. Fischer

发明人： Raymond G. Johnson, Jr. ,  Bill L. Trustee ,  William C. Fischer

IPC分类号： B64C27/32 ,  F01D17/00 ,  B64C11/18 ,  B64C19/00 ,  B64C27/06

CPC分类号： B64C27/325

摘要： Quad-redundant signal processors in a flight control computer control valves to modulate airflow in a circulation control rotor system. The valves are arranged in a series and each valve is responsive to two signal processors. Loss of a valve occurs when both signal processors for that valve fail. A first valve, and every fourth valve in the series thereafter is responsive to a first signal processor and a third signal processor. The next valve in the series, and every fourth valve in the series thereafter is responsive to a second signal processor and a fourth signal processor. The third valve in the series, and every fourth valve in the series thereafter is responsive to the first signal processor and the fourth signal processor. The next valve in the series, and every fourth valve in the series thereafter is responsive to the second signal processor and the third signal processor. Predetermined pairs of adjacent valves define fixed rotor locations and the pair of valves at a fixed rotor location are controlled each by two and aggregately by all four signal processors. The first and second processors are in a separate chassis from the third and fourth processors.

摘要翻译： 飞行控制计算机中的四冗余信号处理器控制阀来调节循环控制转子系统中的气流。 阀被串联布置，并且每个阀响应于两个信号处理器。 当该阀门的两个信号处理器都失效时，会发生阀门的损失。 第一阀门，并且其后的每一个第四阀门响应于第一信号处理器和第三信号处理器。 该系列中的下一个阀，并且此后的系列中的每个第四阀响应于第二信号处理器和第四信号处理器。 该系列中的第三个阀，其后的每一个第四个阀都响应于第一个信号处理器和第四个信号处理器。 该系列中的下一个阀，其后的每一个第四个阀响应于第二信号处理器和第三信号处理器。 预定的相邻阀对限定了固定的转子位置，并且固定转子位置处的这对阀门被所有四个信号处理器分别控制两个并且被所有四个信号处理器聚集。 第一和第二处理器与第三和第四处理器在独立的机架中。

公开(公告)号：US4078749A

公开(公告)日：1978-03-14

申请号：US800117

申请日：1977-05-24

申请人： Raymond G. Johnson, Jr.

发明人： Raymond G. Johnson, Jr.

IPC分类号： G05D1/00 ,  G05D1/10

CPC分类号： G05D1/0061

摘要： In the cyclic pitch stick controls of a helicopter of the type in which feel is provided to the pilot by inducing a force which is proportional but opposite to the motion of the cyclic stick from an adjustable trim position, null offset errors which may be due, inter alia, to temperature variation of the hydraulic fluid in the system, are periodically overcome by means of sensing the pressure differential across the force augmentation hydraulic servo actuator at times when the differential pressure thereacross should be nearly zero, during trim release with small stick motion, and providing a countermanding bias in response thereto; the pressure differential is measured by a differential pressure transducer having a full scale which is only sufficient to measure the expected null errors, which may be about an order of magnitude lower than the full scale, operative pressure differentials which may occur.

摘要翻译： 在通过诱导与循环棒的运动成比例但相反的力从可调整的装饰位置提供感觉的直升机的循环俯仰杆控制中，可能导致的零偏移误差， 特别是对于系统中的液压流体的温度变化，通过感测力增大液压伺服致动器两端的压力差定期克服，当压力差在几乎为零时，在微小的运动中调整释放期间 并且提供响应于此的反向偏置; 通过具有满量程的压差传感器来测量压力差，该压差传感器仅足以测量预期的无效误差，其可能比可能出现的满量程操作压差低约一个数量级。