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：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：EP0736166B1

公开(公告)日：1998-07-01

申请号：EP95904907.3

申请日：1994-12-02

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F41G9/00 ,  F41G5/18 ,  G05D1/08

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