-
公开(公告)号：US20200277082A1
公开(公告)日：2020-09-03
申请号：US16802967
申请日：2020-02-27
摘要： A haptic alert mechanism. The mechanism includes an actuator. At least one arm of a movable stopping piece is connected to the actuator. A spring box is provided with an enclosure containing a pre-stressed torsion spring, said spring box being mounted to be movable in rotation about the axis of rotation. The enclosure includes at least one lug that is mounted to be movable in rotation about said axis of rotation. A finger of the torsion spring passes through an elongate orifice in a front flank of the enclosure to form a movable, resilient stop that is overridable.
-
公开(公告)号：US20200247557A1
公开(公告)日：2020-08-06
申请号：US16708942
申请日：2019-12-10
申请人： AIRBUS HELICOPTERS
摘要： A directional lighting system fitted to an aircraft and comprising firstly a light source mounted on a motor-driven support and secondly a control device serving to control the motor-driven support. According to the invention, such a directional lighting system comprises a selector member for selecting a pointing target that is to be pointed to, a camera for acquiring a plurality of images of the surroundings outside the aircraft, image processor means for identifying the selected pointing target, a calculation unit configured to calculate the current coordinates of the pointing target, and a servocontrol member of the control device for servocontrolling the position of the motor-driven support to occupy an angular orientation as determined by the calculation unit.
-
公开(公告)号：US20190088146A1
公开(公告)日：2019-03-21
申请号：US16117807
申请日：2018-08-30
申请人： Airbus Helicopters
摘要： A method and a device for avoiding an object by detecting its approach to an aircraft. After detecting an object in the vicinity of an aircraft and detecting its approach, a first track for the object and a second track for the aircraft are estimated from successive first states for the object and successive second states for the aircraft. Thereafter, a minimum distance (dm) between the first track and the second track is estimated and a warning is triggered as soon as the minimum distance is less than a first threshold so as to warn a crew of the aircraft of a risk of collision. Finally, if the minimum distance is less than a second threshold, an avoidance maneuver is performed automatically by the aircraft in order to move away from the first track, and thereby avoid any risk of collision with the object.
-
4.发明申请公开(公告)号：US20180009546A1
公开(公告)日：2018-01-11
申请号：US15644439
申请日：2017-07-07
申请人： AIRBUS HELICOPTERS
CPC分类号： B64D45/08 , B64C13/18 , B64C27/57 , B64D47/08 , G06K9/0063 , G08G5/0021 , G08G5/025 , H04N5/2252 , H04N5/23296 , H04N5/247
摘要： A device for assisting the piloting of a rotorcraft in order to pilot a rotorcraft during an approach stage preceding a stage of landing on a rotorcraft landing area. Such a device includes in particular a camera for taking a plurality of images of the environment of the rotorcraft along a line of sight, looking at least along a forward direction Dx of the rotorcraft, and processor means for identifying in at least one image from among said plurality of images at least one looked-for landing area.
-
5.发明申请FLIGHT CONTROL SYSTEM AND METHOD FOR A ROTARY WING AIRCRAFT, ENABLING IT TO MAINTAIN EITHER TRACK OR HEADING DEPENDING ON ITS FORWARD SPEED 有权飞行控制系统和旋转飞行器的方法，使其能够依靠其前进速度维持跟踪或起始公开(公告)号：US20150375850A1
公开(公告)日：2015-12-31
申请号：US14750731
申请日：2015-06-25
申请人： AIRBUS HELICOPTERS
CPC分类号： B64C13/18 , B64C27/04 , B64C27/57 , G05D1/0858
摘要： A flight control method and system for a rotary wing aircraft. When the longitudinal speed UX of the aircraft is greater than a first threshold speed Vthresh1, a first mode of operation of the method enables flight to be performed while maintaining track relative to the ground, the flight setpoints of an autopilot being a ground course angle TKsol, a forward speed Va, a pitch angle P, and a heading Ψ. When the longitudinal speed UX is less than a second threshold speed Vthresh2, a second mode of operation enables flight to be performed while maintaining heading, the flight setpoints being the longitudinal speed UX, a lateral speed VY, a vertical speed WZ, and the heading Ψ.
摘要翻译： 旋翼飞机的飞行控制方法和系统。 当飞行器的纵向速度UX大于第一阈值Vthresh1时，该方法的第一操作模式能够在维持相对于地面的轨道的同时进行飞行，自动驾驶仪的飞行设定点为地面航向角度TKsol ，前进速度Va，俯仰角P和航向Ψ。 当纵向速度UX小于第二阈值Vthresh2时，第二操作模式能够在保持航向的同时进行飞行，飞行设定点为纵向速度UX，横向速度VY，垂直速度WZ和航向 Ψ。
-
6.发明申请FLIGHT CONTROL SYSTEM AND METHOD WITH TRACK MAINTENANCE FOR A ROTARY WING AIRCRAFT 有权飞行控制系统和方法与轨道维护为旋转式飞机公开(公告)号：US20150375849A1
公开(公告)日：2015-12-31
申请号：US14750726
申请日：2015-06-25
申请人： AIRBUS HELICOPTERS
CPC分类号： B64C13/18 , B64C27/04 , G05D1/0858
摘要： A flight control system for a rotary wing aircraft, the aircraft following a track Tsol relative to the ground with a ground course angle TKsol, a forward speed Va, a pitch angle P, and a heading Ψ, the aircraft having one or more rotary wings provided with blades of collective pitch and of cyclic pitch that are variable about respective pitch axes and that are capable of performing movements in rotation and in translation. The flight control system has two control members each provided respectively with at least one movement axis A, B, C, D, and an autopilot for generating control signals. An action on one of the control members relative to one of the movement axes A, B, C, D gives rise independently to a modification to the forward speed Va, to the ground course angle TKsol, or indeed to the pitch angle P by means of the autopilot.
摘要翻译： 一种用于旋转飞行器的飞行控制系统，该飞机遵循轨道Tsol相对于地面的地面，具有地面航向角度TKsol，前进速度Va，俯仰角P和航向Ψ，飞行器具有一个或多个旋翼 提供有关于相应俯仰轴线变化的并且能够执行旋转和平移的运动的具有共同俯仰和循环俯仰的叶片。 飞行控制系统具有两个控制构件，每个控制构件分别具有至少一个移动轴线A，B，C，D以及用于产生控制信号的自动驾驶仪。 一个控制构件相对于其中一个运动轴线A，B，C，D的动作独立于对前进速度Va，对地面坡度角度TKsol的改变，或者实际上与俯仰角度P 的自动驾驶仪。
-
公开(公告)号：US20180222602A1
公开(公告)日：2018-08-09
申请号：US15891837
申请日：2018-02-08
申请人： AIRBUS HELICOPTERS
CPC分类号： B64D45/08 , B64C27/57 , G01C21/165 , G01C23/005 , G05D1/0684 , G05D1/101 , G05D1/12 , G06K9/00637 , G06T7/74 , G06T2207/10032 , G06T2207/20221 , G08G5/0021 , G08G5/025 , H04N7/181
摘要： A method that recommends capturing a stream of images of the landing zone, using a first imaging system to calculate position information for the landing zone on the basis of at least one real image of the stream, using an autopilot system to determine a current position of the landing zone at the current calculation instant, using a second imaging system to verify the presence of a landing zone at the current position in the real image, and generating an alarm if the presence is not found.
-
公开(公告)号：US20180099739A1
公开(公告)日：2018-04-12
申请号：US15727826
申请日：2017-10-09
申请人： AIRBUS HELICOPTERS
CPC分类号： B64C13/0421 , B64C11/30 , B64C13/04 , B64C13/044 , B64C13/28 , B64C13/341 , B64C13/42 , B64C13/50 , B64C13/505 , B64C13/506 , B64C27/26 , B64C27/56 , B64C27/82 , B64D31/04
摘要： An electric control device having manipulation means. The electric control device has a first measurement system and a second measurement system respectively taking a first measurement and a second measurement of the current position of the manipulation means. A processor unit compares the first and second measurements in order to generate a control signal as a function of said current position, said processor unit considering that the manipulation means are in a neutral position when the first and second measurements do not correspond to the same position for the manipulation means.
-
9.发明申请公开(公告)号：US20160347467A1
公开(公告)日：2016-12-01
申请号：US15163834
申请日：2016-05-25
申请人： AIRBUS HELICOPTERS
CPC分类号： B64D43/02 , B64C13/04 , B64C13/18 , B64C13/22 , G05D1/0858
摘要： A method of determining the longitudinal air speed VairX and the longitudinal ground speed VsolX of a rotary wing aircraft depending on the exposure of the aircraft to the wind, the aircraft flying at a speed of advance Va. The method making it possible to determine characteristic speed curves for the aircraft depending on the longitudinal speed of the relative wind to which the aircraft is subjected, and then during a flight and depending on the actions of the pilot of the aircraft, to deduce the longitudinal ground speed VsolX and the longitudinal air speed VairX to be applied to the aircraft depending on variations in the longitudinal speed of the relative wind to which the aircraft is subjected.
摘要翻译： 一种确定旋翼机飞行器的纵向空气速度VairX和纵向地面速度VsolX的方法，该方法取决于飞机对风的暴露，飞行器以提前速度Va飞行。该方法使得可以确定特征速度 飞机的纵向速度取决于飞机所经受的相对风的纵向速度，然后在飞行期间并根据飞行员飞行员的动作，推断出纵向地面速度VsolX和纵向空气速度VairX 根据飞机所经受的相对风的纵向速度的变化而应用于飞行器。
-
10.发明申请公开(公告)号：US20160176522A1
公开(公告)日：2016-06-23
申请号：US14964796
申请日：2015-12-10
申请人： AIRBUS HELICOPTERS
CPC分类号： B64C27/57 , G01P3/00 , G01P5/00 , G05D1/0204 , G05D1/0808 , G05D1/0858
摘要： A method and a system for determining an angular velocity in turning for a rotary wing aircraft in order to make turns that are coordinated relative to the ground or else relative to the air and in order to manage the transition between ground coordination and air coordination while taking account of the wind to which said aircraft is subjected. Said method serving to determine an angular velocity in yaw by means of an anticipation value A and a correction value B on the basis in particular of speeds of advance of the aircraft relative to the ground Vasol and relative to the air Vaair, of its lateral acceleration GY and of its lateral load factor Ny.
摘要翻译： 一种用于确定旋转翼飞行器的转向角速度的方法和系统，以便使相对于地面或相对于空气协调的转弯，并且为了管理地面协调和空中协调之间的过渡，同时采取 说明飞机受到的风的描述。 所述方法用于通过预期值A和校正值B来确定偏航中的角速度，特别是基于飞行器相对于地面Vasol的前进速度和相对于空气Vaair的横向加速度 GY及其横向载荷系数Ny。
-
-
-
-
-
-
-
-
-
搜索结果
11 条记录 (耗时 0.029 秒)
