公开(公告)号：US4980835A

公开(公告)日：1990-12-25

申请号：US256937

申请日：1988-10-13

申请人： Thomas H. Lawrence ,  Phillip J. Gold

发明人： Thomas H. Lawrence ,  Phillip J. Gold

IPC分类号： B64C27/32

CPC分类号： B64C27/325

摘要： Control law system for the collective axis, as well as pitch and roll axes, of an X-Wing aircraft and for the pneumatic valving controlling circulation control blowing for the rotor. As to the collective axis, the system gives the pilot single-lever direct lift control and insures that maximum cyclic blowing control power is available in transition. Angle-of-attach de-coupling is provided in rotary wing flight, and mechanical collective is used to augment pneumatic roll control when appropriate. Automatic gain variations with airspeed and rotor speed are provided, so a unitary set of control laws works in all three X-Wing flight modes. As to pitch and roll axes, the system produces essentially the same aircraft response regardless of flight mode or condition. Undesirable cross-couplings are compensated for in a manner unnoticeable to the pilot without requiring pilot action, as flight mode or condition is changed. A hub moment feedback scheme is implemented, utilizing a P+I controller, significantly improving bandwidth. Limits protect aircraft structure from inadvertent damage. As to pneumatic valving, the system automatically provides the pressure required at each valve azimuth location, as dictated by collective, cyclic and higher harmonic blowing commands. Variations in the required control phase angle are automatically introduced, and variations in plenum pressure are compensated for. The required switching for leading, trailing and dual edge blowing is automated, using a simple table look-up procedure. Non-linearities due to valve characteristics of circulation control lift are linearized by map look-ups.

摘要翻译： 用于X翼飞机的集体轴以及俯仰轴的控制律系统，以及用于转子的气动阀控制循环控制。 对于集体轴线，该系统给出了先导单杆直升机控制，并确保了最大的循环吹风控制功率在转换中可用。 在旋转翼飞行中提供了附着角度的脱耦合，并且在适当的情况下使用机械集合来增加气动辊控制。 提供了空速和转子速度的自动增益变化，因此，所有三种X翼飞行模式中都有一套统一的控制规律。 对于俯仰和滚动轴，系统产生与飞行模式或条件无关的基本相同的飞机响应。 当飞行模式或状况发生变化时，不需要先导操作，不合需要的交叉联轴器以对飞行员不明显的方式进行补偿。 利用P + I控制器实现了一个中枢时刻反馈方案，显着提高了带宽。 限制保护飞机结构免受意外损坏。 对于气动阀门，系统根据集体，循环和高次谐波吹制命令自动提供每个阀方位位置所需的压力。 自动引入所需控制相位角的变化，补偿气室压力的变化。 使用简单的表查找程序，可以自动进行前，后和双边吹风所需的切换。 由循环控制电梯的阀门特性引起的非线性由地图查找线性化。

公开(公告)号：US5465925A

公开(公告)日：1995-11-14

申请号：US250988

申请日：1994-05-27

申请人： Christopher J. Connolly ,  Thomas H. Lawrence ,  Joseph J. Mankaukas ,  John J. Pawlowski ,  Matthew T. Smith

发明人： Christopher J. Connolly ,  Thomas H. Lawrence ,  Joseph J. Mankaukas ,  John J. Pawlowski ,  Matthew T. Smith

IPC分类号： B64D1/12

CPC分类号： B64D1/12 ,  Y10S706/90

摘要： A helicopter external cargo suspension system (12) has load sensors (19,20) at each suspension point for sensing the magnitude of a load (32) at each suspension point. A delay period (FIG. 6) is determined based on the magnitude of the load, and a load is released if one of the following failure modes occurs for a period which exceed the delay period: one of the suspension points is unloaded, the magnitude of the load exceeds a maximum threshold magnitude, or if the distribution of the load, as indicated by the difference in magnitude at each suspension point, exceeds a difference threshold magnitude. If the magnitude of the load is below a minimum threshold magnitude, the load will be carried by one of the suspension points in response to a failure of the other suspension points.Alternatively, the load information is converted from crisp values to fuzzy inputs (700) wherein the detected values are fuzzified by assigning a membership weight at discrete points or segments on a normalized scale; a new mode fuzzy output (707) is provided by applying a compositional rule of inference (705) across each fuzzy input (702) and a composite mode selection rule base (710), the new mode fuzzy output (707) is converted into a crisp output by taking the weighted sum of the membership weight at each point on the normalized scale in excess of a threshold value (712), and new mode is determined by comparing the new mode crisp output to a set of new mode membership ranges (FIGS. 8e and 9e).

摘要翻译： 直升机外部货物悬挂系统（12）在每个悬挂点处具有负载传感器（19,20），用于感测每个悬挂点处的负载（32）的大小。 延迟时段（图6）是根据负载的大小确定的，如果下列故障模式中的一个发生超过延迟周期的时间段，则释放负载：暂停点中的一个被卸载， 或者如果由每个悬挂点处的幅度差表示的负载分布超过差值阈值， 如果负载的大小低于最小阈值大小，则负载将由其他悬挂点的一个承载，以响应其他悬挂点的故障。 或者，将负载信息从脆性值转换为模糊输入（700），其中通过在归一化尺度上的离散点或分段处分配成员权重来对所检测值进行模糊化; 通过在每个模糊输入（702）和复合模式选择规则库（710）中应用推理组合规则（705）来提供新模式模糊输出（707），将新模式模糊输出（707）转换为 通过将归一化标度上的每个点处的成员权重的加权和采用超过阈值（712）的清晰输出，并且通过将新模式清晰输出与一组新模式成员范围进行比较来确定新模式（图6 8e和9e）。

公开(公告)号：US4507050A

公开(公告)日：1985-03-26

申请号：US559995

申请日：1983-12-09

申请人： Philip A. E. Jeffery ,  Thomas H. Lawrence

发明人： Philip A. E. Jeffery ,  Thomas H. Lawrence

IPC分类号： B64C27/32 ,  B64C11/24 ,  F01D5/18

CPC分类号： B64C27/325

摘要： A circulation control rotor system in which butterfly valves (44, 46) control the flow of compressed air from a plenum chamber (40) to the rotor blades (14). Each has an actuator (48, 52) positioning the valve in accordance with a control input and in which a spring loaded averaging linkage (120) between adjacent valves around a plenum chamber circumference acts to position the valve at an average position of the two adjacent valves if a fault in the actuator or within its control or power system should develop. Should such a fault develop, as determined by a comparison of actual valve position with command position, the faulty valve's actuator is shut down.

摘要翻译： 一种循环控制转子系统，其中蝶阀（44,46）控制从压力室（40）到转子叶片（14）的压缩空气流。 每个都具有致动器（48,52），该致动器根据控制输入定位阀，并且其中围绕增压室周围的相邻阀之间的弹簧加载的平均连杆机构（120）用于将阀定位在两个相邻的平均位置 如果执行器中的故障或其控制或电源系统中出现故障，阀门应发展。 如果通过实际阀位与指令位置的比较来确定这种故障，故障阀的执行器被关闭。