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1. 发明授权

EP0641425B1 HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING AZIMUTH AND PITCH CONTROL 失效
标题翻译：综合火力和飞行控制与方位角和俯仰控制直升机
公开(公告)号：EP0641425B1
公开(公告)日：1996-09-18
申请号：EP93911145.6
申请日：1993-05-07
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： FOWLER, Donald, W. , LAPPOS, Nicholas, D. , DRYFOOS, James, B. , KELLER, James, F.
IPC分类号： F41G3/22 , G05D1/08
CPC分类号： F41G3/22 , G05D1/085 , G05D1/0858
摘要： 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.

2. 发明公开

EP0736166A1 HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING A PRE-LAUNCH AND POST-LAUNCH MANEUVER DIRECTOR 失效
标题翻译：综合火力和飞行控制FOR之前，控制系统，直升机在发射后
公开(公告)号：EP0736166A1
公开(公告)日：1996-10-09
申请号：EP95904907.0
申请日：1994-12-02
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： FOWLER, Donald, W. , LAPPOS, Nicolas, D. , EDWARDS, Joan, A.
IPC分类号： B64C13 , B64C27 , B64D7 , F41G5 , F41G9 , G05D1
CPC分类号： F41G7/007 , F41G5/18 , F41G9/002 , G05D1/085
摘要： An integrated fire and flight control (IFFC) system determines a ballistic firing solution based on the position of targets relative to a helicopter and also based on the type of weapons to be fired. An elevation command is determined based on the required change in helicopter attitude to achieve the ballistic firing solutin that, combined with the estimated time required to perform the aim and release of weapons, provides an estimate of deceleration and velocity loss that will occur. A forward acceleration and velocity profile is determined based on the desire to make a symmetrical maneuver sequence involving a nose down acceleration to achieve the acceleration and velocity profile that will be canceled by the subsequent deceleration and velocity loss during the pitch up maneuver to the ballistic firing solution. The forward acceleration and velocity profile is used to provide a pilot with a forward acceleration command that directs the pilot to fly a nose down attitude until the required forward acceleration and velocity profile is achieved. Alternatively, the acceleration profile is coupled to a flight control wherein a pre-launch maneuver feedforward command signal is summed with a side arm controller control command signal as the primary input to a rotor mixing function and a pre-launch commanded rate signal is summed with a side arm controller commanded rate signal to provide the primary input to an automatic flight control system, to thereby automatically control the aircraft to assume an attitude necessary to achieve the desired forward acceleration and velocity profile. A terminal phase maneuver is calculated to thereby return the aircraft to the previous attitude, velocity hold, hover hold or position hold condition prior to commencement of the pre-launch maneuver.

3. 发明公开

EP0641426A1 HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL SYSTEM HAVING TURN COORDINATION CONTROL 失效
标题翻译： HUBSCHRAUBER MIT INTEGRIERTEM FEUERLEIT- UND FLUGKONTROLLSYSTEMMIT KOORDINIERTER KURSABWEICHUNGSTEUERUNG。
公开(公告)号：EP0641426A1
公开(公告)日：1995-03-08
申请号：EP93911165.0
申请日：1993-05-06
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： FOWLER, Donald, W. , LAPPOS, Nicholas, D.
IPC分类号： F41G3 , G05D1
CPC分类号： F41G3/22 , G05D1/085 , G05D1/0858

4. 发明授权

EP0641426B1 HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL SYSTEM HAVING TURN COORDINATION CONTROL 失效
标题翻译：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
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： FOWLER, Donald, W. , LAPPOS, Nicholas, D.
IPC分类号： F41G3/22 , G05D1/08
CPC分类号： F41G3/22 , G05D1/085 , G05D1/0858
摘要： 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.
摘要翻译：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。

5. 发明授权

EP0667005B1 HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING COORDINATED AREA BOMBING CONTROL 失效
标题翻译：综合飞行控制，并用火炸弹袭击CONTROL协调
公开(公告)号：EP0667005B1
公开(公告)日：1997-01-15
申请号：EP93924913.2
申请日：1993-10-05
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： FOWLER, Donald, W. , LAPPOS, Nicholos, D.
IPC分类号： G05D1/08 , F41G9/00 , B64C13/50
CPC分类号： B64C13/503 , F41G3/22 , F41G5/18 , F41G9/002 , G05D1/0858
摘要： During operation of a flight control system in a coordinated area bombing mode, one pair in a group of pairs of fire control azimuth coordinate error signal and elevation coordinate error signals (145) are faded-in as the aircraft yaw attitude reference and pitch attitude reference, respectively. Each pair is respectively indicative of the change in aircraft yaw attitude and pitch attitude for an aircraft reference axis to be aligned with an aiming line of sight. The aiming line of sight corresponds to a target location within a selected target area. A firing signal (685) is provided in response to both the azimuth and elevation coordinate error signals being below respective threshold magnitudes, and the next pair in the group of pairs of azimuth and elevation coordinate error signals provide the aircraft attitude reference. A selected weapon is fired in response to the firing signal.

6. 发明公开

EP0641464A1 HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING CONSTRAINT LIMITING CONTROL 失效
标题翻译：综合火控和控制系统，具有功能限制的直升机。
公开(公告)号：EP0641464A1
公开(公告)日：1995-03-08
申请号：EP93909621.0
申请日：1993-04-26
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： FOWLER, Donald, W. , LAPPOS, Nicholas, D.
IPC分类号： B64C13 , F41G3 , G05D1
CPC分类号： G05D1/0858 , B64C13/503 , F41G3/12 , G05D1/0833

7. 发明授权

EP0736166B1 HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING A PRE-LAUNCH AND POST-LAUNCH MANEUVER DIRECTOR 失效
标题翻译：综合火力和飞行控制FOR之前，控制系统，直升机在发射后
公开(公告)号：EP0736166B1
公开(公告)日：1998-07-01
申请号：EP95904907.3
申请日：1994-12-02
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： FOWLER, Donald, W. , LAPPOS, Nicolas, D. , EDWARDS, Joan, A.
IPC分类号： F41G9/00 , F41G5/18 , G05D1/08
CPC分类号： F41G7/007 , F41G5/18 , F41G9/002 , G05D1/085

8. 发明授权

EP0641464B1 HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING CONSTRAINT LIMITING CONTROL 失效
标题翻译：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
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： FOWLER, Donald, W. , LAPPOS, Nicholas, D.
IPC分类号： G05D1/08 , B64C13/50
CPC分类号： G05D1/0858 , B64C13/503 , F41G3/12 , G05D1/0833
摘要： 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.
摘要翻译：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。

9. 发明公开

EP0667005A1 HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING COORDINATED AREA BOMBING CONTROL 失效
标题翻译：综合飞行控制，并用火炸弹袭击CONTROL协调。
公开(公告)号：EP0667005A1
公开(公告)日：1995-08-16
申请号：EP93924913.0
申请日：1993-10-05
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： FOWLER, Donald, W. , LAPPOS, Nicholos, D.
IPC分类号： B64C13 , F41G3 , F41G5 , F41G9 , G05D1
CPC分类号： B64C13/503 , F41G3/22 , F41G5/18 , F41G9/002 , G05D1/0858
摘要： During operation of a flight control system in a coordinated area bombing mode, one pair in a group of pairs of fire control azimuth coordinate error signal and elevation coordinate error signals (145) are faded-in as the aircraft yaw attitude reference and pitch attitude reference, respectively. Each pair is respectively indicative of the change in aircraft yaw attitude and pitch attitude for an aircraft reference axis to be aligned with an aiming line of sight. The aiming line of sight corresponds to a target location within a selected target area. A firing signal (685) is provided in response to both the azimuth and elevation coordinate error signals being below respective threshold magnitudes, and the next pair in the group of pairs of azimuth and elevation coordinate error signals provide the aircraft attitude reference. A selected weapon is fired in response to the firing signal.

10. 发明公开

EP0641425A1 HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING AZIMUTH AND PITCH CONTROL 失效
标题翻译：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
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： FOWLER, Donald, W. , LAPPOS, Nicholas, D. , DRYFOOS, James, B. , KELLER, James, F.
IPC分类号： B64C13 , B64C27 , F41G3 , G05D1
CPC分类号： F41G3/22 , G05D1/085 , G05D1/0858
摘要： 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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