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    HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL SYSTEM HAVING TURN COORDINATION CONTROL
    1.
    发明申请
    HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL SYSTEM HAVING TURN COORDINATION CONTROL 审中-公开
    具有协调控制的直升机综合火力和飞行控制系统

    公开(公告)号：WO1993023716A1

    公开(公告)日：1993-11-25

    申请号：PCT/US1993004359

    申请日：1993-05-06

    Applicant: UNITED TECHNOLOGIES CORPORATION.

    Inventor： UNITED TECHNOLOGIES CORPORATION. ,  FOWLER, Donald, W. ,  LAPPOS, Nicholas, D.

    IPC: F41G03/22

    CPC classification number: F41G3/22 ,  G05D1/085 ,  G05D1/0858

    Abstract: During operation of a flight control system in a coupled aiming mode, wherein a fire control system (55) azimuth command and elevation command provide an aircraft attitude reference, a bank angle calculation function (1077) provides a bank angle signal to place the aircraft in a roll angle which results in a substantially coordinated turn. The bank angle signal is determined primarily as a function of an aiming line of sight heading rate for small azimuth commands, and is determined primarily as a function of aircraft heading rate for large azimuth commands. Additionally, the bank angle initially comprises a component as a function of aircraft lateral acceleration for driving aircraft lateral acceleration to zero, and after the aircraft assumes a roll attitude for turn coordination, the bank angle comprises a component as a function of aircraft side slip for driving aircraft side slip to zero. Automatic turn coordination is disabled if the pilot maneuvers the aircraft to avoid a coordinated turn, and is re-enabled if the pilot maneuvers the aircraft into a coordinated turn attitude. A rate feedback path (143) is provided during operation in the coupled aiming mode wherein aircraft yaw and pitch rate error signals are respectively replaced by the rate of change of the azimuth command and the elevation command. During operation in the coupled aiming mode, intended pilot commanded maneuvers maintain full authority at all times.

    Abstract translation: 在联合瞄准模式下的飞行控制系统的操作期间，其中消防控制系统（55）的方位指令和仰角命令提供飞机姿态参考，倾斜角计算功能（1077）提供倾斜角度信号以将飞机放置在 滚动角度导致基本上协调的转弯。 主角角信号主要根据小方位指令的目标航向速度的函数来确定，并且主要被确定为大方位指令的飞机航向速率的函数。 另外，岸角最初包括作为飞行器侧向加速度的函数的一个部件，用于将飞机横向加速度推到零，并且在飞行器采用卷轴姿态进行转向协调之后，该倾斜角度包括作为飞行器侧滑的函数的分量 驾驶飞机侧滑到零。 如果飞行员操纵飞机避免协调转弯，则自动转向协调被禁用，如果飞行员操纵飞行员进行协调的转弯姿态，则重新启用。 在耦合的对准模式中，在操作期间提供速率反馈路径（143），其中飞行器偏航和俯仰速率误差信号分别被方位指令和仰角指令的变化率所代替。 在联合瞄准模式下运行期间，飞行员指挥的飞行任务始终保持着全面的权威。

    HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING CONSTRAINT LIMITING CONTROL
    2.
    发明申请
    HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING CONSTRAINT LIMITING CONTROL 审中-公开
    直升机综合火灾和飞行控制具有约束限制控制

    公开(公告)号：WO1993023797A1

    公开(公告)日：1993-11-25

    申请号：PCT/US1993003911

    申请日：1993-04-26

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： UNITED TECHNOLOGIES CORPORATION ,  FOWLER, Donald, W. ,  LAPPOS, Nicholas, D.

    IPC: G05D01/08

    CPC classification number: G05D1/0858 ,  B64C13/503 ,  F41G3/12 ,  G05D1/0833

    Abstract: During operation of an integrated fire and flight control (IFFC) system in a coupled aiming mode, the occurrence of a weapon (172), weapon mount (145) or sensor (146) reaching a constraint limit (210) induces a fade-in of a constraint limiting axis command signal (140) for a respective attitude axis as the aircraft attitude reference, replacing the flight control system attitude feedback error signal (111) for the respective attitude axis. The constraint limiting axis command signals provide the aircraft attitude reference only while the pilot manually depresses and holds an enable switch (920). The pilot command stick input (90) remains the primary input to the IFFC system to thereby provide override capability for pilot command maneuvers.

    HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING AZIMUTH AND PITCH CONTROL
    3.
    发明申请
    HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING AZIMUTH AND PITCH CONTROL 审中-公开
    直升机综合火灾和飞行控制具有控制和控制

    公开(公告)号：WO1993023715A1

    公开(公告)日：1993-11-25

    申请号：PCT/US1993004336

    申请日：1993-05-07

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： UNITED TECHNOLOGIES CORPORATION ,  FOWLER, Donald, W. ,  LAPPOS, Nicholas, D. ,  DRYFOOS, James, B. ,  KELLER, James, F.

    IPC: F41G03/22

    CPC classification number: F41G3/22 ,  G05D1/085 ,  G05D1/0858

    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。 响应于先导开关（920）的连续操作，方位指令和仰角指令低于相应的阈值大小（940,941）以及消防控制系统（55）的操作而被耦合的瞄准模式。 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。

    HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL SYSTEM HAVING TURN COORDINATION CONTROL
    5.
    发明授权
    HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL SYSTEM HAVING TURN COORDINATION CONTROL 失效
    利用内置的火灾和飞行控制系统协调当然是不同的遥控直升机

    公开(公告)号：EP0641426B1

    公开(公告)日：1997-09-24

    申请号：EP93911165.4

    申请日：1993-05-06

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： FOWLER, Donald, W. ,  LAPPOS, Nicholas, D.

    IPC: F41G3/22 ,  G05D1/08

    CPC classification number: F41G3/22 ,  G05D1/085 ,  G05D1/0858

    Abstract: During operation of a flight control system in a coupled aiming mode, wherein a fire control system (55) azimuth command and elevation command provide an aircraft attitude reference, a bank angle calculation function (1077) provides a bank angle signal to place the aircraft in a roll angle which results in a substantially coordinated turn. The bank angle signal is determined primarily as a function of an aiming line of sight heading rate for small azimuth commands, and is determined primarily as a function of aircraft heading rate for large azimuth commands. Additionally, the bank angle initially comprises a component as a function of aircraft lateral acceleration for driving aircraft lateral acceleration to zero, and after the aircraft assumes a roll attitude for turn coordination, the bank angle comprises a component as a function of aircraft side slip for driving aircraft side slip to zero. Automatic turn coordination is disabled if the pilot maneuvers the aircraft to avoid a coordinated turn, and is re-enabled if the pilot maneuvers the aircraft into a coordinated turn attitude. A rate feedback path (143) is provided during operation in the coupled aiming mode wherein aircraft yaw and pitch rate error signals are respectively replaced by the rate of change of the azimuth command and the elevation command. During operation in the coupled aiming mode, intended pilot commanded maneuvers maintain full authority at all times.

    Abstract translation: 期间以耦合瞄准模式中的飞行控制系统的外科手术，worin火控制系统（55）方位命令和仰角命令飞行器姿态基准提供，一个倾斜角计算功能（1077）提供了一个坡度角信号以将飞机在 侧倾角导致实质上协调转弯。 倾斜角信号确定性开采主要作为视线驶向小方位角指令速率的瞄准线的功能，并且是确定性的主要开采飞机航向率大方位命令的功能。 另外，倾斜角最初包括一个成分作为飞机的横向加速度的用于驱动飞机的横向加速度为零的功能，并且在飞机übernimmt为转弯协调一个滚转姿态后，倾斜角包含组分作为用于飞机侧滑的函数 驾驶飞机侧滑为零。 如果飞行员操纵自动转弯协调被禁用的飞机，以避免协调转弯，并重新启用如果飞行员操纵飞机到协调转弯的态度。 一种速率反馈通路（143）在手术飞机worin偏航和俯仰速率误差信号分别由方位角指令的变化率和仰角命令代替耦合瞄准模式期间提供。 在手术过程中加上瞄准模式，嘱咐拟试点演习时刻保持充分的权力。

    HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING CONSTRAINT LIMITING CONTROL
    9.
    发明授权
    HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING CONSTRAINT LIMITING CONTROL 失效
    集成火灾及控制装置与直升机的限制的功能

    公开(公告)号：EP0641464B1

    公开(公告)日：1996-12-04

    申请号：EP93909621.0

    申请日：1993-04-26

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： FOWLER, Donald, W. ,  LAPPOS, Nicholas, D.

    IPC: G05D1/08 ,  B64C13/50

    CPC classification number: G05D1/0858 ,  B64C13/503 ,  F41G3/12 ,  G05D1/0833

    Abstract: During operation of an integrated fire and flight control (IFFC) system in a coupled aiming mode, the occurrence of a weapon (172), weapon mount (145) or sensor (146) reaching a constraint limit (210) induces a fade-in of a constraint limiting axis command signal (140) for a respective attitude axis as the aircraft attitude reference, replacing the flight control system attitude feedback error signal (111) for the respective attitude axis. The constraint limiting axis command signals provide the aircraft attitude reference only while the pilot manually depresses and holds an enable switch (920). The pilot command stick input (90) remains the primary input to the IFFC system to thereby provide override capability for pilot command maneuvers.

    Abstract translation: 期间以耦合瞄准模式集成火灾和飞行控制（IFFC）系统的外科手术中，武器（172），武器支架（145）或传感器（146）到达一个约束限制（210）的发生指数淡入 的约束限制了一个respectivement姿态轴作为飞行器姿态基准轴的指令信号（140），取代了飞行控制系统姿态反馈误差信号（111），用于将respectivement姿态轴。 约束限制轴命令信号提供飞行器姿态基准仅在导频手动按下和保持，以使开关（920）。 导向器命令棒输入（90）仍然是主要的输入到IFFC系统，从而提供覆盖能力飞行员命令演习。

    HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING AZIMUTH AND PITCH CONTROL
    10.
    发明公开
    HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING AZIMUTH AND PITCH CONTROL 失效
    集成火灾与方位角和俯仰控制直升机飞行控制。

    公开(公告)号：EP0641425A1

    公开(公告)日：1995-03-08

    申请号：EP93911145.0

    申请日：1993-05-07

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： FOWLER, Donald, W. ,  LAPPOS, Nicholas, D. ,  DRYFOOS, James, B. ,  KELLER, James, F.

    IPC: B64C13 ,  B64C27 ,  F41G3 ,  G05D1

    CPC classification number: F41G3/22 ,  G05D1/085 ,  G05D1/0858

    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.

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