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1. 发明授权

US5005548A Fuel injection pump 失效
标题翻译：燃油喷射泵
公开(公告)号：US5005548A
公开(公告)日：1991-04-09
申请号：US542125
申请日：1990-06-22
申请人： Helmut Rembold , Hannes Pflug , Wilhelm Christ , Hans-Joachim Siebert , Ewald Eblen , Rodriguez-Amaya , Helmut Laufer , Alfred Schmitt , Werner Pape , Dominique Buisson , Pierre Lauvin , Detlev Potz , Nikolaus Simon , Jean Pigeroulet , Anton Karle
发明人： Helmut Rembold , Hannes Pflug , Wilhelm Christ , Hans-Joachim Siebert , Ewald Eblen , Rodriguez-Amaya , Helmut Laufer , Alfred Schmitt , Werner Pape , Dominique Buisson , Pierre Lauvin , Detlev Potz , Nikolaus Simon , Jean Pigeroulet , Anton Karle
IPC分类号： F02M41/14 , F02D1/18 , F02M41/06 , F02M45/06 , F02M59/36
CPC分类号： F02M41/063 , F02D1/183 , F02M41/06 , F02M45/066 , F02M59/366 , F02M2200/24
摘要： A fuel injection pump is proposed in which over a first portion of the supply stroke of the pump piston fuel for the main injection is pumped via a distributor line and a distributor groove into one at a time of a plurality of fuel injection lines. In a second, remaining portion of the pump piston supply stroke, on the same cam flank, fuel is then pre-stored in a reservoir, controlled by a first electrically controlled valve and a second electrically controlled valve and by one of a plurality of longitudinal control grooves, which fuel subsequently, before the beginning of the next main injection determined by the closure of the first electrically controlled valve, is pumped via a second distributor line into the next succeeding injection line.
摘要翻译：提出了一种燃料喷射泵，其中用于主喷射的泵活塞燃料的供给冲程的第一部分在多个燃料喷射管线处经由分配器管线和分配器槽泵入一个。在另一个中，泵活塞供应冲程的剩余部分在相同的凸轮侧面上，然后将燃料预先存储在储存器中，由第一电控阀和第二电控阀以及多个纵向在通过第一电控阀的关闭确定的下一次主要喷射开始之前，随后燃料的控制槽经由第二分配管线泵送到下一个后续喷射管线中。

2. 发明授权

US5245501A Process and apparatus for controlling and measuring the movement of an armature of an electromagnetic switching member 失效
标题翻译：用于控制和测量电磁开关构件的臂的运动的过程和装置
公开(公告)号：US5245501A
公开(公告)日：1993-09-14
申请号：US689769
申请日：1991-06-26
申请人： Johannes Locher , Hans-Joachim Siebert , Herbert Graf , Nestor Rodriguez-Amaya , Anton Karle , Alfred Schmitt , Joachim Tauscher , Werner Zimmermann , Dominique Buisson , Lucien Hehn , Pierre Lauvin , Henri Paganon
发明人： Johannes Locher , Hans-Joachim Siebert , Herbert Graf , Nestor Rodriguez-Amaya , Anton Karle , Alfred Schmitt , Joachim Tauscher , Werner Zimmermann , Dominique Buisson , Lucien Hehn , Pierre Lauvin , Henri Paganon
IPC分类号： B60T8/36 , B60T8/90 , F02D41/20 , H01F7/18
CPC分类号： B60T8/90 , B60T8/36 , F02D41/20 , H01F7/1844 , F02D2041/2017 , F02D2041/2051 , F02D2041/2055 , F02D2041/2058
摘要： A process for controlling and measuring the movement of an armature of an electromagnetic switching member with an excitation coil is proposed, which has the following steps: a current (i) or a voltage (u1) is applied to the excitation winding (3) in order to move the armature into a first actuatable position; before the start of the movement of the armature, the current or the voltage is raised above a value at which the armature remains in the actuated position, and before termination of the movement of the armature the current or the voltage is reduced to a defined value, which suffices to hold the armature in the actuated position; finally, the temporal variations in the current or the voltage are measured after setting of the defined value, for the purpose of recognizing the termination of the armature movement. With the aid of this process, it is possible for the movement of the armature, for example of a solenoid valve for a fuel injection device of an internal combustion engine, to be very precisely monitored, so that the injection instant and injection period can be optimally set.
摘要翻译： PCT No.PCT / DE89 / 00758 Sec。 371日期1991年6月26日 102（e）日期1991年6月26日PCT提交1989年12月7日PCT公布。出版物WO88 / 02544 日期：1988年4月7日。提出了一种用于控制和测量具有励磁线圈的电磁开关元件的电枢的运动的过程，其具有以下步骤：将电流（i）或电压（u1）施加到激励绕组（3），以便将电枢移动到第一致动位置; 在电枢运动开始之前，电流或电压升高到电枢保持在致动位置的值以上，并且在电枢移动终止之前，电流或电压降低到限定值，足以将电枢保持在致动位置; 最后，为了识别电枢运动的终止，在设定定义值之后测量电流或电压的时间变化。借助于该过程，可以非常精确地监视电枢的运动，例如用于内燃机的燃料喷射装置的电磁阀，使得喷射瞬间和喷射周期可以是最佳设定。

3. 发明授权

US4903666A Fuel injection device 失效
标题翻译：燃油喷射装置
公开(公告)号：US4903666A
公开(公告)日：1990-02-27
申请号：US281144
申请日：1988-12-06
申请人： Dominique Buisson , Francois Henry , Jean Leblanc , Helmut Pfeifle , Jean Pigeroulet
发明人： Dominique Buisson , Francois Henry , Jean Leblanc , Helmut Pfeifle , Jean Pigeroulet
IPC分类号： F02M61/00 , F02M55/04 , F02M57/02 , F02M59/36 , F02M59/46
CPC分类号： F02M57/02 , F02M55/04 , F02M59/366 , F02M59/462 , F02B2275/14 , Y02T10/123
摘要： A fuel injection device having a pump piston which during the supply stroke pumps fuel from a pump work chamber into an injection line which leads to a fuel injection valve. Directly adjacent to the branching off of the injection line from the pump work chamber, at the diameter of the injection line, a valve seat is provided, at which the injection line then merges with a chamber into which a pressure valve closing member plunges. The valve closing member is tightly guided in a guide bore, loaded by a valve spring, and in the chamber has a pressure shoulder adjoining the sealing surface that cooperates with the valve seat. The rear side of the pressure valve closing member communicates with a continuously open relief line. Because of this construction, the pressure valve closing member operates as an equal-pressure valve and simultaneously as a deflecting piston as well, with the aid of which a pressure rise in the pump work chamber is built up in a retarded manner until such time as the pressure valve closing member comes to rest on a stop. A pressure rise of this type is particularly advantageous in connection with control of the injection phase by means of a magnetic valve subjected to the high pressure.

4. 发明授权

US4805580A Fuel injection device 失效
标题翻译：燃油喷射装置
公开(公告)号：US4805580A
公开(公告)日：1989-02-21
申请号：US870468
申请日：1986-06-04
申请人： Dominique Buisson , Francois Henry , Jean Leblanc , Helmut Pfeifle , Jean Pigeroulet
发明人： Dominique Buisson , Francois Henry , Jean Leblanc , Helmut Pfeifle , Jean Pigeroulet
IPC分类号： F02M61/00 , F02M55/04 , F02M57/02 , F02M59/36 , F02M59/46 , F02M39/00
CPC分类号： F02M57/02 , F02M55/04 , F02M59/366 , F02M59/462 , F02B2275/14 , Y02T10/123
摘要： A fuel injection device having a pump piston which during the supply stroke pumps fuel from a pump work chamber into an injection line which leads to a fuel injection valve. Directly adjacent to the branching off of the injection line from the pump work chamber, at the diameter of the injection line, a valve seat is provided, at which the injection line then merges with a chamber into which a pressure valve closing member plunges. The valve closing member is tightly guided in a guide bore, loaded by a valve spring, and in the chamber has a pressure shoulder adjoining the sealing surface that cooperates with the valve seat. The rear side of the pressure valve closing member communicates with a continuously open relief line. Because of this construction, the pressure valve closing member operates as an equal-pressure valve and simultaneously as a deflecting piston as well, with the aid of which a pressure rise in the pump work chamber is built up in a retarded manner until such time as the pressure valve closing member comes to rest on a stop. A pressure rise of this type is particularly advantageous in connection with control of the injection phase by means of a magnetic valve subjected to the high pressure.
摘要翻译：具有泵活塞的燃料喷射装置，其在供给冲程期间将来自泵工作室的燃料泵送到通向燃料喷射阀的喷射管线。在喷射管直径处，直接与喷射管路分离出的离开泵入口管线的直径相同，设置有一个阀座，在该阀座处，注射管线与压力阀关闭件所在的腔室合并。阀关闭构件被紧密地引导在由阀弹簧加载的引导孔中，并且在腔室中具有邻接与阀座配合的密封表面的压力肩部。压力阀关闭构件的后侧与连续打开的浮雕线连通。由于这种结构，压力阀关闭部件作为等压阀工作，同时作为偏转活塞，借助于此，泵工作室中的压力上升以延迟的方式被建立，直到压力阀关闭件在停止时停止。这种类型的压力上升与通过经受高压的电磁阀控制喷射相相关是特别有利的。

5. 发明授权

US4949269A Process and system for determining the longitudinal position of the center of gravity of an aircraft provided with an adjustable horizontal stabilizer 失效
标题翻译：用于确定具有可调节水平稳定器的飞行器的重心的纵向位置的过程和系统
公开(公告)号：US4949269A
公开(公告)日：1990-08-14
申请号：US251709
申请日：1988-08-12
申请人： Dominique Buisson , Joseph Irvoas
发明人： Dominique Buisson , Joseph Irvoas
IPC分类号： B64D45/00 , G01M1/12
CPC分类号： G01M1/127
摘要： Method and system for determining the longitudinal position of the gravity center of an aircraft having an adjustable stabilizer. At a flight point for which the aircraft is in equilibrium with its elevator in aerodynamic prolongation of the adjustable stabilizer, the gravity center position is calculated from the position (X.sub.F) of the focus (F) of the aircraft (1), the measurement of the deflection (iH) of the adjustable stabilizer, a first function K(M, N1) of the engine speed (N1) of the engines of the aircraft and the Mach number (M). The first function is representative of the deflection value (iHRef) of the adjustable stabilizer. In the case where the gravity center would be at the focus (F) of the aircraft, a second function H(Cz, M) of the lift coefficient (Cz) of the aircraft and of the Mach number (M) is used. The second function is representative of the stabilizer deflection variation for a variation of 1 percent of the gravity center position.
摘要翻译： PCT No.PCT / FR88 / 00003 Sec。 371日期1988年8月12日 102（e）日期1988年8月12日PCT提交1988年1月4日PCT公布。 WO88 / 05163 PCT出版物日期：1988年7月14日。用于确定具有可调稳定器的飞行器的重心的纵向位置的方法和系统。在可调稳定器的空气动力学延长期间飞行器与其升降机平衡的飞行点处，重心位置由飞行器（1）的焦点（F）的位置（XF）计算，测量可调节稳定器的偏转（iH），飞机发动机的发动机转速（N1）和马赫数（M）的第一函数K（M，N1）。第一个功能代表可调稳定器的偏转值（iHRef）。在重心处于飞机的焦点（F）的情况下，使用飞机的升力系数（Cz）和马赫数（M）的第二函数H（Cz，M）。第二个功能代表了1％的重心位置变化的稳定器偏转变化。

6. 发明授权

US4937754A Process and system for determining the longitudinal position of the center of gravity of an aircraft provided with an adjustable horizontal stabilizer and application to the monitoring of said center of gravity near the focus of the aircraft 失效
标题翻译：用于确定具有可调节的水平稳定器的飞行器的重心的纵向位置的处理和系统，并且用于监视靠近飞机焦点的所述重心的重心
公开(公告)号：US4937754A
公开(公告)日：1990-06-26
申请号：US251705
申请日：1988-08-12
申请人： Dominique Buisson , Augustin Moline
发明人： Dominique Buisson , Augustin Moline
IPC分类号： B64D45/00 , G01M1/12
CPC分类号： G01M1/127
摘要： Method and system for determining the longitudinal position of the gravity center of an aircraft provided with an adjustable stabilizer. At a point of flight for which the aircraft is in equilibrium with its elevator in aerodynamic prolongation of the adjustable stabilizer and when the gravity center is at the vicinity of the focus of the aircraft, the gravity center position is calculated from: the position (X.sub.F) of the focus (F) of the aircraft, the measurement of the deflection (iH) of the adjustable stabilizer, a first function K(M, N1) of the engine speed (N1) of the engines of the aircraft and the Mach number (M); and a second function of such Mach number. There is application to the monitoring of the gravity center of a flying aircraft.
摘要翻译： PCT No.PCT / FR88 / 00002 Sec。 371日期1988年8月12日 102（e）日期1988年8月12日PCT提交1988年1月4日PCT公布。出版物WO88 / 05162 日期：1988年7月14日。用于确定具有可调稳定器的飞行器的重心的纵向位置的方法和系统。在飞行器的飞行时，飞机与可升降机的空气动力学延长与升降机平衡，并且当重心处于飞机焦点附近时，重心位置由下式计算：位置（XF ），飞行器的发动机转速（N1）的第一函数K（M，N1）和马赫数（M）; 以及这种马赫数的第二功能。应用于飞行器重心的监测。

7. 发明授权

US4982713A Unit fuel injector including a fuel injection pump for internal combustion engines 失效
标题翻译：单元燃料喷射器，包括用于内燃机的燃油喷射泵
公开(公告)号：US4982713A
公开(公告)日：1991-01-08
申请号：US542136
申请日：1990-06-22
申请人： Dominique Buisson
发明人： Dominique Buisson
IPC分类号： F02M57/02 , F02B3/06 , F02M55/00 , F02M59/36
CPC分类号： F02M55/00 , F02M59/366 , F02B3/06 , F02M55/007
摘要： A fuel injection pump including a pump piston, which pumps fuel at injection pressure to an injection nozzle as long as a control valve blocks the flow of the fuel, which overflows from the pump work chamber via a flow conduit, to a low-pressure chamber. In this operating state, if the control valve jams and the supply of fuel to the pump work chamber is not completely prevented. A Venturi pump is provided to evacuate the fuel. By means of the Venturi pump with a permanent flow of fuel through it, the static pressure is partially dropped at a flow throttle and this negative pressure is utilized at bottom dead center (UT) of the pump piston to evacuate the pump work chamber by suction, thereby preventing an unintended injection. The apparatus is especially suitable for high-pressure injection in Diesel engines, to achieve redundantly safe operation.
摘要翻译：一种燃料喷射泵，其包括泵活塞，其将注射压力的燃料泵送到喷嘴，只要控制阀将经由流动管道从泵工作室溢出的燃料的流动阻塞到低压室。在该操作状态下，如果控制阀堵塞并且没有完全防止向泵工作室供应燃料。提供文丘里泵以排出燃料。通过文丘里泵具有通过其的永久性燃料流，静压在流动节流阀处部分地下降，并且该负压在泵活塞的下死点（UT）处被利用以通过抽吸抽空泵工作室，从而防止意外注射。该设备特别适用于柴油发动机的高压喷射，实现了冗余安全运行。

8. 发明授权

US07366592B2 System for automatically controlling lift-enhancing devices of an aircraft, in particular wing leading edge slats 有权
标题翻译：用于自动控制飞机升力增强装置，特别是机翼前缘板条的系统
公开(公告)号：US07366592B2
公开(公告)日：2008-04-29
申请号：US10890182
申请日：2004-07-14
申请人： Franck Delaplace , Dominique Buisson
发明人： Franck Delaplace , Dominique Buisson
IPC分类号： B64C1/00
CPC分类号： G05D1/0066
摘要： A control system for an aircraft includes an actuation section that moves lift-enhancing devices as a function of received control orders, a control member operable by a pilot of the aircraft, and a control unit that includes a control section that produces control orders, as a function of actuation of the control member, so as to control the actuation section to bring the lift-enhancing devices into a predetermined position. The control unit further includes a device that produces automatically auxiliary control orders which are transmitted to the actuation section to automatically retract the lift-enhancing devices when the aircraft is in a first flight condition and another device that automatically disables control orders produced by the control section following actuation of the control member to deploy the lift-enhancing devices when the aircraft is in a second flight condition.
摘要翻译：用于飞行器的控制系统包括：作为接收到的控制命令的函数来移动提升增强装置的致动部分，由飞行器的飞行员操作的控制部件和包括产生控制命令的控制部分的控制单元，如控制构件的致动功能，以便控制致动部分使提升增强装置进入预定位置。控制单元还包括一个装置，该装置产生自动的辅助控制命令，当飞行器处于第一飞行状态时，辅助控制命令被传送到致动部分以自动缩回提升增强装置，另一个装置自动地禁止由控制部分产生的控制命令随后在飞行器处于第二飞行状态时致动控制构件以展开提升增强装置。

9. 发明申请

US20070185628A1 System for automatically controlling lift-enhancing devices of an aircraft, in particular wing leading edge slats 有权
标题翻译：用于自动控制飞机升力增强装置，特别是机翼前缘板条的系统
公开(公告)号：US20070185628A1
公开(公告)日：2007-08-09
申请号：US10890182
申请日：2004-07-14
申请人： Franck Delaplace , Dominique Buisson
发明人： Franck Delaplace , Dominique Buisson
IPC分类号： G01C23/00 , G06F17/00
CPC分类号： G05D1/0066
摘要： A control system for an aircraft includes an actuation section that moves lift-enhancing devices as a function of received control orders, a control member operable by a pilot of the aircraft, and a control unit that includes a control section that produces control orders, as a function of actuation of the control member, so as to control the actuation section to bring the lift-enhancing devices into a predetermined position. The control unit further includes a device that produces automatically auxiliary control orders which are transmitted to the actuation section to automatically retract the lift-enhancing devices when the aircraft is in a first flight condition and another device that automatically disables control orders produced by the control section following actuation of the control member to deploy the lift-enhancing devices when the aircraft is in a second flight condition.
摘要翻译：用于飞行器的控制系统包括：作为接收到的控制命令的函数来移动提升增强装置的致动部分，由飞行器的飞行员操作的控制部件和包括产生控制命令的控制部分的控制单元，如控制构件的致动功能，以便控制致动部分使提升增强装置进入预定位置。控制单元还包括一个装置，该装置产生自动的辅助控制命令，当飞行器处于第一飞行状态时，辅助控制命令被传送到致动部分以自动缩回提升增强装置，另一个装置自动地禁止由控制部分产生的控制命令随后在飞行器处于第二飞行状态时致动控制构件以展开提升增强装置。

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