公开(公告)号：WO1994010616A1

公开(公告)日：1994-05-11

申请号：PCT/US1993009500

申请日：1993-10-05

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: G05D01/08

CPC classification number: B64C13/503 ,  F41G3/22 ,  F41G5/18 ,  F41G9/002 ,  G05D1/0858

Abstract: 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.

Abstract translation: 在协调区域轰炸模式下的飞行控制系统的操作期间，一组火控方位坐标误差信号和仰角坐标误差信号（145）中的一对作为飞机偏航姿态参考和俯仰姿态参考 ， 分别。 每一对分别表示与瞄准视线对准的飞行器参考轴的飞行器偏航姿态和俯仰姿态的变化。 目标瞄准线对应于所选目标区域内的目标位置。 响应于方位角和仰角坐标误差信号两者都低于相应的阈值幅度而提供点火信号（685），并且该组方位角和仰角坐标误差信号组中的下一对提供飞机姿态参考。 选择的武器是响应发射信号而被触发的。

公开(公告)号：WO1995017641A1

公开(公告)日：1995-06-29

申请号：PCT/US1994014392

申请日：1994-12-02

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  FOWLER, Donald, W. ,  LAPPOS, Nicolas, D. ,  EDWARDS, Joan, A.

IPC: F41G09/00

CPC classification number: F41G7/007 ,  F41G5/18 ,  F41G9/002 ,  G05D1/085

Abstract: 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.

Abstract translation: 一个综合的火力和飞行控制系统（IFFC）系统根据目标相对于直升机的位置，并根据要被射击的武器的类型确定弹道射击解决方案。 根据直升机姿态所要求的改变来确定升高指令，以实现弹道射击解决方案，结合执行武器目标和释放所需的估计时间，提供将会发生的减速和速度损失的估计。 根据期望制作一个涉及下降加速度的对称机动序列来达到加速度和速度分布的要求，确定前进加速度和速度分布，该加速度和速度分布将在随后的减速和速度损失期间消除， 解。 前进加速度和速度分布用于为驾驶员提供前进加速指令，其指导飞行员飞行下降姿态，直到达到所需的前进加速度和速度曲线。 或者，加速度曲线被耦合到飞行控制，其中预发射机动前馈指令信号与侧臂控制器控制命令信号相加，作为转子混合功能的主要输入，并且预发射命令速率信号与 侧臂控制器命令速率信号以向主动输入提供自动飞行控制系统，从而自动控制飞机采取所需的姿态以达到所需的正向加速度和速度曲线。 计算终端阶段机动，从而使飞机返回到先前的姿态，速度保持，悬停保持或位置保持状态，然后再启动前的动作。

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。

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.

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。

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

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F41G3/22 ,  G05D1/08

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.

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

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： FOWLER, Donald, W. ,  LAPPOS, Nicolas, D. ,  EDWARDS, Joan, A.

IPC: B64C13 ,  B64C27 ,  B64D7 ,  F41G5 ,  F41G9 ,  G05D1

CPC classification number: F41G7/007 ,  F41G5/18 ,  F41G9/002 ,  G05D1/085

Abstract: 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.

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

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F41G3 ,  G05D1

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

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。

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

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: G05D1/08 ,  F41G9/00 ,  B64C13/50

CPC classification number: B64C13/503 ,  F41G3/22 ,  F41G5/18 ,  F41G9/002 ,  G05D1/0858

Abstract: 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.