公开(公告)号：US5617316A

公开(公告)日：1997-04-01

申请号：US404774

申请日：1995-03-15

Applicant: Donald L. Fogler, Jr. ,  James F. Keller

Inventor： Donald L. Fogler, Jr. ,  James F. Keller

IPC: G05D1/08 ,  B64C11/44

CPC classification number: G05D1/0816

Abstract: A model-following aircraft control system in which a roll rate command in Euler coordinates is integrated to provide a bank angle command, which has actual bank angle subtracted therefrom to provide a command error that is converted back to aircraft body coordinates for use, so long as the pitch attitude of the aircraft does not approach zenith or nadir. But, while the absolute value of the pitch attitude exceeds 85.degree. the last error generated before exceeding 85.degree. is converted to body coordinates for use by the aircraft, and the initial integrated value of attitude command, for use when the pitch angle reverts below 85.degree., is formed as the sum of said last error and the actual attitude angle of the aircraft.

Abstract translation: 一种模型跟随飞行器控制系统，其中欧拉坐标中的滚动速率命令被集成以提供从其中减去的实际斜角角度的斜角命令，以提供转换回飞行器身体坐标以使用的命令错误 因为飞机的俯仰姿态不接近天顶或最低点。 但是，当俯仰姿态的绝对值超过85°时，在超过85°之前产生的最后一个误差转换为飞机使用的身体坐标和姿态指令的初始积分值，当俯仰角回复到85°以下时使用 DEG形成为所述最后一个误差与飞行器的实际姿态角的总和。

公开(公告)号：US08302169B1

公开(公告)日：2012-10-30

申请号：US12399754

申请日：2009-03-06

Applicant: David Leo Presotto ,  Michal P. Szymaniak ,  James F. Keller ,  Mark Klenk

Inventor： David Leo Presotto ,  Michal P. Szymaniak ,  James F. Keller ,  Mark Klenk

IPC: G06F7/04

CPC classification number: G06F21/6209 ,  G06F21/602 ,  G06F21/6218 ,  H04L63/0428 ,  H04L63/102

Abstract: A server system receives requests from client systems and sends responses back to the client systems. For a subset of the requests, in addition to responding to a request from a client system, the method includes creating a cryptographic object at the server system. The cryptographic object is used to cryptographically protect information related to the request, and the cryptographically protected information associated with the cryptographic object is stored at the server system. The server system then sends the cryptographic object to the client system, and in conjunction with sending the cryptographic object to the client system, irreversibly modifies the cryptographic object on the server system. For example, in some embodiments the cryptographic object includes an cryptographic key, and the server system deletes or truncates the only instances of the cryptographic object on the server system when the server system finishes responding to the request from the client system.

Abstract translation: 服务器系统从客户端系统接收请求并将响应发送回客户端系统。 对于请求的子集，除了响应来自客户端系统的请求之外，该方法包括在服务器系统处创建加密对象。 密码对象用于加密地保护与请求相关的信息，并且与服务器系统相关联的密码保护的信息被存储在服务器系统中。 然后，服务器系统将密码对象发送到客户端系统，并且将密码对象发送到客户端系统，不可逆地修改服务器系统上的密码对象。 例如，在一些实施例中，加密对象包括加密密钥，并且当服务器系统完成对来自客户端系统的请求的响应时，服务器系统删除或截断服务器系统上的加密对象的唯一实例。

公开(公告)号：US5431084A

公开(公告)日：1995-07-11

申请号：US196936

申请日：1994-04-07

Applicant: Donald W. Fowler ,  Nicholas D. Lappos ,  James B. Dryfoos ,  James F. Keller

Inventor： Donald W. Fowler ,  Nicholas D. Lappos ,  James B. Dryfoos ,  James F. Keller

IPC: B64C13/18 ,  B64C27/04 ,  F41G3/22 ,  G05D1/08

CPC classification number: F41G3/22 ,  G05D1/085

Abstract: A fire control system (55) azimuth command and elevation command provides a flight control system attitude reference in response to operation of the flight control system in a coupled aiming mode. The coupled aiming mode is engaged in response to the continuous operation of a pilot switch (920) the azimuth command and elevation command being below respective threshold magnitudes (940, 941), and the operation of the fire control system (55). During operation in the coupled aiming mode, the azimuth command and elevation command replace the yaw attitude feedback error signal and pitch attitude error signal, respectively, as the aircraft attitude reference. During integration of the fire control system and the flight control system, the flight control system is made less sensitive to small pilot command stick inputs below a stick input threshold magnitude, so that small or inadvertent pilot commanded yaw and pitch maneuvers will not affect the yaw and pitch attitude reference commanded by the fire control system azimuth and elevation commands. However, intended pilot commanded yaw and pitch maneuvers (70) maintain full authority at all times.

Abstract translation: 消防控制系统（55）方位指令和仰角命令提供飞行控制系统姿态参考，以响应飞行控制系统在耦合瞄准模式下的操作。 响应于导频开关（920）的连续操作，方位指令和仰角指令低于相应阈值（940,941）和消防控制系统（55）的操作。 在联合瞄准模式下，方位指令和仰角指令分别代替飞行姿态反馈误差信号和俯仰姿态误差信号作为飞机姿态参考。 在消防控制系统和飞行控制系统的集成期间，使飞行控制系统对小型导向指令杆输入的敏感度低于杆输入阈值大小，从而小型或无意的飞行员指挥的偏航和俯仰机动不会影响偏航 以及由消防控制系统方位角和仰角指令指示的俯仰姿态参考。 然而，预期的飞行员指挥偏航和俯仰机动（70）始终保持完全的权威。

公开(公告)号：US5238203A

公开(公告)日：1993-08-24

申请号：US751431

申请日：1991-08-28

Applicant: Joseph P. Skonieczny ,  Donald L. Fogler, Jr. ,  Phillip J. Gold ,  James F. Keller ,  James B. Dryfoos

Inventor： Joseph P. Skonieczny ,  Donald L. Fogler, Jr. ,  Phillip J. Gold ,  James F. Keller ,  James B. Dryfoos

IPC: B64C13/18 ,  G05D1/08

CPC classification number: G05D1/085 ,  G05D1/0858

Abstract: A helicopter flight control system (21) includes a model following control system architecture which automatically provides a coordinating yaw command signal to the helicopter tail rotor to coordinate helicopter flight during a banked turn. The control system processes information from a variety of helicopter sensors (31) in order to provide the coordinating yaw command signal on an output line (72) to the tail rotor (20) of the helicopter.

Abstract translation: 直升机飞行控制系统（21）包括一个跟随控制系统架构的模型，它自动向直升机尾部转子提供协调偏航指令信号，以协调在转弯期间的直升机飞行。 控制系统处理来自各种直升机传感器（31）的信息，以便在直升机的尾部转子（20）的输出线（72）上提供协调偏航指令信号。

公开(公告)号：US5553817A

公开(公告)日：1996-09-10

申请号：US237540

申请日：1994-05-03

Applicant: Phillip J. Gold ,  Donald L. Fogler, Jr. ,  Joseph Skonieczny ,  James F. Keller

Inventor： Phillip J. Gold ,  Donald L. Fogler, Jr. ,  Joseph Skonieczny ,  James F. Keller

IPC: B64C27/57 ,  G05D1/08 ,  B64C13/16

CPC classification number: G05D1/0858

Abstract: A turn coordination inhibit system (150) inhibits a rotary winged aircraft control system from operating in an automatic turn coordination mode when a pilot desired to perform a sideslip maneuver, e.g., a flat turn. When automatic turn coordination is not engaged (132,212,215), e.g., the aircraft is not in a coordinated turn, and either aircraft bank angle (119) exceeds an inhibit threshold magnitude (210) or a pilot yaw command provided by a pilot sidearm controller (155) exceeds a minimum threshold value (243), e.g., the sidearm controller is out of detent in the yaw axis, automatic turn coordination is inhibited (152). Automatic turn coordination remains inhibited until both aircraft bank angle falls below a reset threshold magnitude (230) and the sidearm controller is back in the detent position for the yaw axis (243).

Abstract translation: 转向协调禁止系统（150）当驾驶员期望执行侧滑操纵（例如平转）时，禁止旋转飞行的飞行器控制系统以自动转向协调模式操作。 当没有进行自动转向协调（132,212,215）时，例如，飞机不处于协调的转弯，并且飞机倾斜角（119）超过禁止阈值幅值（210）或者由导频侧臂控制器提供的导频偏航指令 155）超过最小阈值（243），例如侧臂控制器偏离偏航轴的制动器，禁止自动转向协调（152）。 自动转向协调保持禁止，直到两个飞行器组角度低于复位阈值大小（230），并且侧臂控制器返回到用于偏航轴（243）的制动位置。

公开(公告)号：US5331881A

公开(公告)日：1994-07-26

申请号：US885702

申请日：1992-05-19

Applicant: Donald W. Fowler ,  Nicholas D. Lappos ,  James B. Dryfoos ,  James F. Keller

Inventor： Donald W. Fowler ,  Nicholas D. Lappos ,  James B. Dryfoos ,  James F. Keller

IPC: B64C13/18 ,  B64C27/04 ,  F41G3/22 ,  G05D1/08

CPC classification number: F41G3/22 ,  G05D1/085

Abstract: A fire control system (55) azimuth command and elevation command provides a flight control system attitude reference in response to operation of the flight control system in a coupled aiming mode. The coupled aiming mode is engaged in response to the continuous operation of a pilot switch (920) the azimuth command and elevation command being below respective threshold magnitudes (940, 941), and the operation of the fire control system (55). During operation in the coupled aiming mode, the azimuth command and elevation command replace the yaw attitude feedback error signal and pitch attitude error signal, respectively, as the aircraft attitude reference. During integration of the fire control system and the flight control system, the flight control system is made less sensitive to small pilot command stick inputs below a stick input threshold magnitude, so that small or inadvertent pilot commanded yaw and pitch maneuvers will not affect the yaw and pitch attitude reference commanded by the fire control system azimuth and elevation commands. However, intended pilot commanded yaw and pitch maneuvers (70) maintain full authority at all times.

Abstract translation: 消防控制系统（55）方位指令和仰角命令提供飞行控制系统姿态参考，以响应飞行控制系统在耦合瞄准模式下的操作。 响应于导频开关（920）的连续操作，方位指令和仰角指令低于相应阈值（940,941）和消防控制系统（55）的操作。 在联合瞄准模式下，方位指令和仰角指令分别代替飞行姿态反馈误差信号和俯仰姿态误差信号作为飞机姿态参考。 在消防控制系统和飞行控制系统的集成期间，使飞行控制系统对小型导向指令杆输入的敏感度低于杆输入阈值大小，从而小型或无意的飞行员指挥的偏航和俯仰机动不会影响偏航 以及由消防控制系统方位角和仰角指令指示的俯仰姿态参考。 然而，预期的飞行员指挥偏航和俯仰机动（70）始终保持完全的权威。