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1.发明授权Process for preventing turning over during the landing of an aircraft or spacecraft 失效防止在飞机或航天器着陆期间翻转的过程
公开(公告)号：US6158691A
公开(公告)日：2000-12-12
申请号：US32280
申请日：1998-02-27
申请人： Stefan Menne , Yasar Ovadya , Bernhard Schmidt , Adalbert Wagner
发明人： Stefan Menne , Yasar Ovadya , Bernhard Schmidt , Adalbert Wagner
CPC分类号： B64D1/14
摘要： A process for preventing overturning during the landing of an aircraft or spacecraft using an air bag type landing impact-damping system, which is inflated with gas before the landing and from which gas is discharged via discharge valves during the landing. The process includes using as the air bag type landing impact-damping system a system that is divided into a plurality of chambers that can be inflated with gas and from which gas is released independently from one another, and that a pressure difference is generated during landing in the individual chambers of the air bag type landing impact-damping system.
摘要翻译： 一种防止在飞机或航天器着陆期间使用气囊式着陆冲击阻尼系统进行倒塌的过程，该系统在着陆之前被气体充气，并且在着陆期间通过排出阀排出气体。 该方法包括作为气囊式着陆冲击阻尼系统使用一种系统，该系统被分成多个可以被气体充气并且气体彼此独立地释放的室，并且在着陆期间产生压力差 在气囊式着陆冲击阻尼系统的各个室中。
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2.发明授权Airbag payload landing system for damping landing impact forces on a flying payload 失效安全气囊有效载荷着陆系统用于阻尼着陆冲击力对飞行有效载荷公开(公告)号：US06237875B1
公开(公告)日：2001-05-29
申请号：US09376746
申请日：1999-08-17
申请人： Stefan Menne , Peter Nikolaus Keerl
发明人： Stefan Menne , Peter Nikolaus Keerl
IPC分类号： B64D114
CPC分类号： B64D1/14 , B64D2201/00
摘要： An airbag configuration for braking the landing impact of flying payloads has a central airbag (17) and at least one torus ring (11, 12, 13) surrounding the central airbag. A payload (L) is attachable on the central airbag (17). A stabilizing device (19) is provided which extends from the lowermost portion of the at least one torus ring (11, 12, 13) to the central airbag (17). The central airbag provides primarily vertical braking of the landing impact while the torus ring provides primarily horizontal braking of the landing impact.
摘要翻译： 用于制动飞行有效载荷的着陆冲击的气囊构造具有中央气囊（17）和围绕中央气囊的至少一个环面环（11,12,13）。 有效载荷（L）可附接在中央气囊（17）上。 提供了一种稳定装置（19），其从所述至少一个环形环（11,12,13）的最下部延伸到所述中央气囊（17）。 中央安全气囊主要提供着陆冲击的垂直制动，而环形环主要提供着陆冲击的水平制动。
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3.发明授权Heat shield for mounting on a heat-radiating object, particularly on a rocket engine 有权用于安装在散热物体上，特别是火箭发动机上的隔热罩公开(公告)号：US07845175B2
公开(公告)日：2010-12-07
申请号：US11642857
申请日：2006-12-21
IPC分类号： F02K1/00
CPC分类号： F02K9/97 , B64G1/58 , F02K1/822 , F02K9/60 , F05D2250/141 , F05D2250/232 , F05D2260/221
摘要： A heat shield for mounting on a heat-radiating object, particularly on a rocket engine comprises a first planar element having a front side and a back side. In its mounted state, the first planar element extending from the heat-radiating object toward the outside, with its front side being exposed to the heat radiation at least of a section of the heat-radiating object. A second insulating element having a front side and a back side is arranged on the back side of the first planar element in such a manner that a gap is formed between the back side of the first planar element and the front side of the second element. In the mounted state of the heat shield, the gap widens in the direction from the heat-radiating object toward the outside.
摘要翻译： 用于安装在散热物体上，特别是在火箭发动机上的隔热罩包括具有前侧和后侧的第一平面元件。 在其安装状态下，第一平面元件从散热物体朝向外部延伸，其前侧至少暴露于散热物体的一部分的热辐射。 具有前侧和后侧的第二绝缘元件被布置在第一平面元件的背面上，使得在第一平面元件的背面和第二元件的前侧之间形成间隙。 在隔热罩的安装状态下，间隙从散热物体朝向外部的方向变宽。
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4.发明申请Heat shield for mounting on a heat-radiating object, particularly on a rocket engine 有权用于安装在散热物体上，特别是火箭发动机上的隔热罩公开(公告)号：US20070146972A1
公开(公告)日：2007-06-28
申请号：US11642857
申请日：2006-12-21
IPC分类号： H02B1/00
CPC分类号： F02K9/97 , B64G1/58 , F02K1/822 , F02K9/60 , F05D2250/141 , F05D2250/232 , F05D2260/221
摘要： A heat shield for mounting on a heat-radiating object, particularly on a rocket engine comprises a first planar element having a front side and a back side. In its mounted state, the first planar element extending from the heat-radiating object toward the outside, with its front side being exposed to the heat radiation at least of a section of the heat-radiating object. A second insulating element having a front side and a back side is arranged on the back side of the first planar element in such a manner that a gap is formed between the back side of the first planar element and the front side of the second element. In the mounted state of the heat shield, the gap widens in the direction from the heat-radiating object toward the outside.
摘要翻译： 用于安装在散热物体上，特别是在火箭发动机上的隔热罩包括具有前侧和后侧的第一平面元件。 在其安装状态下，第一平面元件从散热物体朝向外部延伸，其前侧至少暴露于散热物体的一部分的热辐射。 具有前侧和后侧的第二绝缘元件被布置在第一平面元件的背面上，使得在第一平面元件的背面和第二元件的前侧之间形成间隙。 在隔热罩的安装状态下，间隙从散热体朝向外部的方向变宽。
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