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    • 1. 发明申请
    • De-iced total air temperature sensor
    • 除冰的总空气温度传感器
    • US20060056489A1
    • 2006-03-16
    • US10517796
    • 2003-06-13
    • Marc BernardCyril BarreDavid Lapeyronnie
    • Marc BernardCyril BarreDavid Lapeyronnie
    • G01K1/00G01K1/14
    • G01K13/028G01K13/02
    • A sensor for measuring a physical parameter of a fluid, in particular for measuring total air temperature, the sensor comprising: a fluid intake (1) fitted to a streamlined body (2); a duct provided in said streamlined body (2) to enable fluid flow, said duct communicating with said fluid intake; and a sensing element disposed inside said duct. The sensor is characterized in that it includes elements that give it improved measurement performance. In particular, the proposed air intake presents an inlet section which extends so as to define a sliding surface suitable for eliminating ice. The invention also provides an improved system for sucking in the boundary layer by using slots, and it also provides a ceramic sensing element that provides better thermal decoupling relative to the de-iced body.
    • 一种用于测量流体的物理参数,特别是用于测量总体空气温度的传感器,所述传感器包括:装配到流线型体(2)上的流体入口(1); 设置在所述流线型体(2)中以使流体流动的管道,所述管道与所述流体入口连通; 以及设置在所述管道内的传感元件。 传感器的特征在于它包括提供改进的测量性能的元件。 特别地,所提出的进气口具有延伸以限定适于消除冰的滑动表面的入口部分。 本发明还提供了一种用于通过使用狭缝吸附边界层的改进系统,并且还提供了相对于除冰体提供更好的热去耦的陶瓷感测元件。
    • 2. 发明授权
    • De-iced total air temperature sensor
    • 除冰的总空气温度传感器
    • US07441948B2
    • 2008-10-28
    • US10517796
    • 2003-06-13
    • Marc BernardCyril BarreDavid Lapeyronnie
    • Marc BernardCyril BarreDavid Lapeyronnie
    • G01K13/00G01K1/00
    • G01K13/028G01K13/02
    • A sensor for measuring a physical parameter of a fluid, in particular for measuring total air temperature, the sensor comprising: a fluid intake (1) fitted to a streamlined body (2); a duct provided in said streamlined body (2) to enable fluid flow, said duct communicating with said fluid intake; and a sensing element disposed inside said duct. The sensor is characterized in that it includes elements that give it improved measurement performance. In particular, the proposed air intake presents an inlet section which extends so as to define a sliding surface suitable for eliminating ice. The invention also provides an improved system for sucking in the boundary layer by using slots, and it also provides a ceramic sensing element that provides better thermal decoupling relative to the de-iced body.
    • 一种用于测量流体的物理参数,特别是用于测量总体空气温度的传感器,所述传感器包括:装配到流线型体(2)上的流体入口(1); 设置在所述流线型体(2)中以使流体流动的管道,所述管道与所述流体入口连通; 以及设置在所述管道内的传感元件。 传感器的特征在于它包括提供改进的测量性能的元件。 特别地,所提出的进气口具有延伸以限定适于消除冰的滑动表面的入口部分。 本发明还提供了一种用于通过使用狭缝吸附边界层的改进系统,并且还提供了相对于除冰体提供更好的热去耦的陶瓷感测元件。
    • 6. 发明授权
    • System for carrier guidance by laser beam and pyrotechnic thrusters
    • 激光束和烟火推进器的载体引导系统
    • US4901946A
    • 1990-02-20
    • US307341
    • 1989-02-06
    • Philippe ArnaudMarc Bernard
    • Philippe ArnaudMarc Bernard
    • F41G7/26
    • F41G7/266F42B10/661
    • A system is provided for guidance, by laser beam and pyrotechnic thrusters, of one or a number of carriers such as missiles which are intended to intercept maneuvering targets such as aircraft, helicopters or tanks. Guidance of the carrier is performed partly from the ground by means of a laser beam (beam-rider guidance) which tracks the target and partly by means of pyrotechnic thrusters placed on board the carrier. At each instant, the carrier thus "knows" its position with respect to the ideal flight path provided by the laser beam. The carrier corrects its flight path by triggering a pyrotechnic thruster when its distance with respect to the ideal flight path is greater than a predefined threshold value and when its radial velocity to the ideal path is lower than a predefined threshold.
    • 提供一种系统,用于通过激光束和烟火推进器来引导一个或多个载体,例如旨在拦截机动目标如飞机,直升机或坦克的导弹。 载体的引导部分地通过利用放置在载体上的烟火推进器的跟踪目标的激光束(射束驾驶员引导)从地面进行。 在每个瞬间,载体因此“知道”其相对于由激光束提供的理想飞行路径的位置。 当其相对于理想飞行路径的距离大于预定义的阈值并且当其到理想路径的径向速度低于预定阈值时,载体通过触发烟火推进器来校正其飞行路径。
    • 10. 发明授权
    • Peripheral casing for a guided munition fired with a cannon effect
    • 用于具有CANNON效应的引导式飞行器的外围壳体
    • US5103734A
    • 1992-04-14
    • US631098
    • 1990-12-19
    • Philippe ArnaudMarc BernardHerve BoubaultRene Thouron
    • Philippe ArnaudMarc BernardHerve BoubaultRene Thouron
    • F42B12/62
    • F42B12/62
    • The invention concerns a guided munition, fired from a launching system with a cannon effect. This munition comprising sub-assemblies is supported, during acceleration in the cannon, by a peripheral casing which rests on the first sub-assembly of the munition placed at the front of the munition and is fixed to an ejectable sub-assembly placed at the rear of the munition. The weight of this casing is necessary to withstand the forces due to acceleration and it enables the range of the munition to be increased during the ballistic phase. During the transition from the ballistic phase to the guided phase, the ejectable sub-assembly is ejected, taking with it the casing which thus frees the airfoil surfaces to open out. The casing thus positioned also provides sealing and protection of the sensitive parts and rigidity of the whole of the munition.
    • 本发明涉及从具有大炮效应的发射系统发射的导弹。 包括子组件的这种弹药在加油加油的过程中被一个外围的外壳支撑,该外围的外壳放置在弹药前面的弹药的第一个子组件上,并被固定到放置在后部的可弹出的子组件 的弹药。 这种套管的重量是必要的,以承受由于加速的力,并且使弹道的范围能够增加。 在从弹道阶段到引导阶段的过渡期间,弹出的子组件被排出,从而将壳体取下,从而使翼型表面释放出来。 因此定位的外壳还提供了敏感部件的密封和保护以及整个弹药的刚性。