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公开(公告)号：US5944282A
公开(公告)日：1999-08-31
申请号：US913292
申请日：1997-09-15
Applicant: Hans-Juergen Clausnitzer , Johann Schweren
Inventor： Hans-Juergen Clausnitzer , Johann Schweren
CPC classification number: F16F9/049 , B64D1/14 , B64G1/22 , B64G1/62 , B64D2201/00
Abstract: A landing shock absorber for aircraft including brake parachutes and comprising a landing cushion for creating damping upon impact of the aircraft, the landing cushion having an inflatable inner bag including a pressure-tight, plastically deformable sheet. The inner bag defines a plurality of inflatable air chambers, and at least one opening between the chambers for establishing communication between the chambers. The landing cushion further includes an outer bag enclosing the inner bag and having a greater internal volume that an internal volume of the inflatable air chambers of the inner bag when the chambers are inflated, the outer bag including a tear-resistant fabric defining a plurality of throttle openings therein.
Abstract translation: PCT No.PCT / EP96 / 00906 Sec。 371日期：1997年9月15日 102（e）1997年9月15日PCT PCT 1996年3月4日PCT公布。 公开号WO96 / 28344 日期1996年9月19日一种用于包括制动降落伞在内的飞机的着陆减震器，包括用于在飞机撞击时产生阻尼的着陆垫，该着陆垫具有一个包括压力密封的可塑性变形的片材的可充气内袋。 内袋限定多个可充气空气室，以及在室之间的至少一个开口，用于建立室之间的连通。 着陆垫还包括封闭内袋并具有较大的内部体积的外袋，当内腔膨胀时，内袋的可膨胀空气室的内部容积，外袋包括限定多个 节气门开口。
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公开(公告)号：US5921507A
公开(公告)日：1999-07-13
申请号：US242796
申请日：1994-05-16
Applicant: Robert Curtis Kalberer , Dan Goor
Inventor： Robert Curtis Kalberer , Dan Goor
CPC classification number: B64D25/00 , B64C13/04 , B64D2201/00
Abstract: An airbag module is positioned relative to an aircraft control yoke or shaft, the airbag being actuated by majority voting sensors that are responsive to acceleration forces upon the aircraft. The aircraft control yoke or control yoke post is constructed to telescope, extend, or move a limited distance toward the pilot as the airbag inflates. The yoke carries telescoping, extendable, or movable handle portions that allow left and right hand pilot grip handles to move, if necessary, under the force of the expanding airbag. Hand sleeves may be provided to help maintain the pilot's hands on the grip handles during airbag expansion. The movable yoke and handle portions may be manually or automatically restored to normal operative positions after airbag deflation. The yoke may be formed so as to provide a U shaped section that accommodates a horizontal support or table for holding the airbag module, a map, or a like device. The U shaped yoke and table support members are structured such that the table remains horizontal during pivoting movement of the yoke to control aircraft roll, and during generally horizontal movement of the yoke to control aircraft pitch.
Abstract translation: 安全气囊模块相对于飞行器控制轭或轴定位，所述安全气囊由响应于飞机上的加速力的多数投票传感器致动。 飞机控制轭或控制轭架被构造成在安全气囊膨胀时向导向器伸出，延伸或移动有限的距离。 轭架承载伸缩的，可延伸的或可移动的手柄部分，其允许左右驾驶员把手在必要时在膨胀的气囊的作用下移动。 可以提供手袖以帮助在气囊膨胀期间将驾驶员的手保持在把手上。 可移动轭和手柄部分可以手动或自动恢复到气囊放气后的正常操作位置。 轭可以形成为提供容纳用于保持气囊模块，地图等装置的水平支撑件或工作台的U形部分。 U形轭和台支撑构件被构造成使得在轭的枢转运动期间桌子保持水平以控制飞行器辊，并且在轭的大体水平运动期间保持水平以控制飞行器俯仰。
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公开(公告)号：US5915663A
公开(公告)日：1999-06-29
申请号：US33979
申请日：1993-03-19
Applicant: Ken-Chee Lee
Inventor： Ken-Chee Lee
IPC: B60R19/20 , B60R21/02 , B60R21/04 , B60V3/08 , B63H21/30 , B64D25/00 , E01D19/02 , E01D19/04 , E01F15/14 , E04H9/02 , F16F9/04 , F16F15/023 , F16M13/00
CPC classification number: F16F15/023 , B60R19/20 , B60V3/08 , B63H21/302 , B64D25/00 , E01D19/02 , E01D19/04 , E04H9/021 , F16F9/0472 , B60R2021/0293 , B60R2021/0407 , B64D2201/00
Abstract: An object protection system protects properties and lives from collision, vibration or earthquake. The system comprises an energy body, a forcing system, and energy force releasing means. According to the theory of the present invention, the reacting force responding to the forcing system in the direction opposite to the striking force is significantly less than the striking force by the principle of energy force released from the forcing system into a space. This novel concept of the present invention is leaping from the classical science with much significance and many distinctive applications to protect the properties and lives. Further application of this principle in consecutively and continuously to reduce the reacting force from the forcing system, theoretically, the reacting force may approach zero, practically, the reacting force cannot reach zero. In practical applications, the present invention achieves a degree of significance by further reducing the reacting force to an amount less than fifty (50) percent of the striking force to protect the properties and lives in case of collision, vibration or earthquake. The system further comprises and combines means for inflating and refilling medium into cell structure, moveable panel and fixed panel, a number of cell structures in cell structure, a number of cell structures in series, parallel, or loop arrangements, means for decelerating and balancing a moving object, and means for measuring the reacting force. The system can be disposed onto land, air and water vehicles, building structures, building grounds, river banks, river beds, piers, highway barriers, airport runways, car raceways, train railways, guided rails, rail end stops, nuclear reactor blow out stops, vibrating machines, sensitive equipment, instruments, dangerous goods, and supporting structures for the protection of properties and lives to enhance our quality of life and preserve a safe living environment.
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公开(公告)号：US5836544A
公开(公告)日：1998-11-17
申请号：US645283
申请日：1996-05-13
Applicant: Dino M. Gentile
Inventor： Dino M. Gentile
IPC: B64D25/00
CPC classification number: B64D17/80 , B64C27/006 , B64D25/00 , B64D2201/00
Abstract: An emergency soft-landing system (10) for use on a rotor-type aircraft such as a helicopter (70). The system (10) includes at least one parachute-containing structure (12) that houses at least one parachute (50). The structure (12) is designed to be selectivelly attached to various locations on the helicopter's lower surface (76), the sides (82), and to the landing gear struts (85). The parachute (50) is deployed from the structure (12) when an out-of-control landing is unavoidable or an extreme emergency exists. The system (10) can be designed so that the parachute-containing structure (12) operates in combination with an airbag (60). An airbag can be attached to the helicopter's lower surface (76) near the rear end (78), and front end (80), and to the center of the helicopter between the landing gear (84). The parachute(s) (50) and airbag(s) (60) are designed to be manually deployed by a helicopter crew member or automatically by a dynamic responsive switch (34). The switch (34) is enabled when the helicopter reaches a specified altitude or an abnormal rate of descent.
Abstract translation: 一种用于诸如直升机（70）的转子式飞机上的紧急软着陆系统（10）。 系统（10）包括容纳至少一个降落伞（50）的至少一个具有降落伞的结构（12）。 结构（12）被设计成选择性地附接到直升机的下表面（76），侧面（82）和起落架支柱（85）上的各种位置。 当失控着陆不可避免或存在极端紧急情况时，降落伞（50）从结构（12）部署。 系统（10）可以被设计成使得降落伞结构（12）与气囊（60）组合地操作。 安全气囊可以附接到靠近后端（78）和前端（80）的直升机的下表面（76），并且连接到起落架（84）之间的直升机的中心。 降落伞（50）和安全气囊（60）被设计成由直升机机组人员手动部署或由动态响应开关（34）自动地部署。 当直升机达到指定的高度或异常的下降速度时，开关（34）被使能。
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公开(公告)号：US5765778A
公开(公告)日：1998-06-16
申请号：US632599
申请日：1996-04-15
Applicant: Ayako Otsuka
Inventor： Ayako Otsuka
CPC classification number: B64D25/00 , B64C25/56 , B64D1/14 , B64D2201/00
Abstract: An aircraft which is capable of safely landing during an emergency landing is disclosed. The aircraft has a safety device which includes a plurality of auxiliary engines. Each auxiliary engine is movable so as to vary the thrust axis in a range between a substantially horizontal direction and a substantially vertical direction. The safety device also includes a plurality of gas bags contracted and disposed at a lower portion of the aircraft body so as to be instantly expandable at a necessary time, such as during an emergency landing.
Abstract translation: 公开了能够在紧急着陆期间安全着陆的飞机。 飞机具有包括多个辅助发动机的安全装置。 每个辅助发动机是可移动的，以便在大致水平方向和基本垂直方向之间的范围内改变推力轴。 安全装置还包括收缩并设置在飞行器主体的下部的多个气囊，以便在必要的时间（例如在紧急着陆期间）立即展开。
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Patent Agency Ranking
公开(公告)号：US5558300A
公开(公告)日：1996-09-24
申请号：US383424
申请日：1995-02-02
Applicant: Robert C. Kalberer , Dan Goor
Inventor： Robert C. Kalberer , Dan Goor
CPC classification number: B60R21/09 , B60R21/16 , B64D25/00 , B60R2021/0093 , B64D2201/00
Abstract: An aircraft airbag module and an energy or impact absorbing and shock reducing control yoke are disclosed, the airbag module using non toxic compressed gas to provide either pyrotechnic or non-pyrotechnic inflation of an airbag independent of other aircraft operational systems. An airbag with one or more sections, when inflated, provides pilot protection without physically engaging the aircraft's control yoke, thus affording the possibility of continued aircraft control by the pilot. The aircraft control yoke includes a mechanically keyed and physically compressible section, as well as padding, thus providing the pilot with additional impact protection with or without airbag deployment. The airbag is retractable or releasable mounted so as to allow the airbag to be manually or automatically removed from the airbag module after an airbag inflation/deflation cycle.
Abstract translation: 公开了一种飞行器安全气囊模块和能量或冲击吸收和减震控制轭，所述安全气囊模块使用无毒压缩气体，以独立于其他飞行器操作系统提供安全气囊的烟火或非烟火充气。 具有一个或多个部分的气囊在充气时提供飞行员保护，而不会实际接触飞机的控制叉，从而提供飞行员继续飞行器控制的可能性。 飞机控制轭包括机械键合和物理可压缩部分以及填充，从而为飞行员提供具有或不具有气囊展开的额外的冲击保护。 安全气囊可伸缩或可拆卸地安装，以便在气囊充气/放气循环之后允许气囊从气囊模块手动或自动地移除。
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公开(公告)号：US5395073A
公开(公告)日：1995-03-07
申请号：US7130
申请日：1993-01-22
Applicant: Elbert L. Rutan , Hugh J. Schmittle
Inventor： Elbert L. Rutan , Hugh J. Schmittle
CPC classification number: B64C29/02 , B64C29/0033 , B64C3/385 , B64C39/024 , B64C39/04 , B64C2201/044 , B64C2201/046 , B64C2201/084 , B64C2201/086 , B64C2201/088 , B64C2201/104 , B64C2201/146 , B64C2201/165 , B64C2201/182 , B64C2201/187 , B64D2201/00 , Y10S446/901
Abstract: A VTOL/STOL free wing aircraft includes a free wing having wings on opposite sides of a fuselage connected to one another respectively adjacent fixed wing inboard or center root sections fixedly attached to the fuselage for free rotation about a spanwise access. Horizontal and vertical tail surfaces are located at the rear end of a boom assembly rotatably connected to the fuselage. A gearing or screw rod arrangement controlled by the pilot or remote control operator selectively relatively pivots the fuselage in relation to the tail boom assembly to enable the fuselage to assume a tilted or nose up configuration to enable VTOL/STOL flight.
Abstract translation: VTOL / STOL自由翼飞机包括一个自由翼，机身相对两侧分别相邻的固定翼或固定在机身上的固定翼部分的机翼相对两侧的翅膀，用于围绕翼展向的自由旋转。 水平和垂直的尾部表面位于可旋转地连接到机身的悬臂组件的后端。 由飞行员或遥控操作员控制的传动装置或螺杆杆装置选择性地使机身相对于尾臂组件枢转，以使机身能够呈现倾斜或鼻部向上的构型，以使得垂直起落架/高空作业飞行。
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公开(公告)号：US5259574A
公开(公告)日：1993-11-09
申请号：US838426
申请日：1992-03-06
Applicant: Louis Carrot
Inventor： Louis Carrot
CPC classification number: B64C27/006 , B64C25/56 , B64D2201/00
Abstract: A device for protecting a helicopter and its occupants from damage during a crash or difficult landing. The device includes an inflatable bag attached to the bottom fuselage which covers a totality of the surface of the helicopter's bottom fuselage. The bag is inflatable into a trapezoidal shape having a very large volume, exceeding the helicopter's internal volume, for substantially cushioning the helicopter upon impact with the ground during a crash. The bag is equipped with distortion-control reinforcements for preventing toppling of the helicopter after a landing and bag air-pressure controlling and limiting devices.
Abstract translation: PCT No.PCT / FR91 / 00399 Sec。 371日期：1992年3月6日 102（e）1992年3月6日PCT PCT 1991年5月17日PCT公布。 出版物WO92 / 00876 日期：1992年1月23日。一种用于保护直升机及其乘客在碰撞或难以着陆时不受损伤的装置。 该装置包括附接到底部机身的充气袋，其覆盖直升机底部机身的整个表面。 该袋子充气成具有非常大体积的梯形形状，超过直升机的内部体积，用于在碰撞期间与地面撞击时基本上缓冲直升机。 该袋配有变形控制增强件，用于防止直升机在着陆和袋气压控制和限制装置之后倒塌。
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公开(公告)号：US4520975A
公开(公告)日：1985-06-04
申请号：US447223
申请日：1982-12-06
Applicant: William R. Blackhurst
Inventor： William R. Blackhurst
CPC classification number: B64D1/02 , B64D2201/00
Abstract: For use in an aircraft having a store retaining cavity from which a loaded store may protrude beyond the envelope of the aircraft, a dual condition air bag system for substantially eliminating air turbulence about the store-cavity interface when the store is loaded, and reducing relative movement of the store during taxiing and flight of the aircraft; and for substantially eliminating air turbulence about the cavity-aircraft interface following release of the store by expansion of the air-bag to a dimension to substantially conform the exterior thereof to the envelope of the aircraft, the expanded shape of the air-bag system being controlled by a plurality of ties bonded to the inner surfaces of the air-bag to limit the displacement of the exterior surface of the air-bag when air pressure is applied to the interior thereof.
Abstract translation: 用于具有商店保持空腔的飞机中，加载的商店可以从该商店保持空腔突出超过飞行器的信封，双重状态气囊系统，用于当储存装载时基本消除关于储存腔界面的空气湍流，并且减少相对 飞机滑行和飞行期间商店的运动; 并且为了基本上消除通过将气囊膨胀到使其外部基本上符合飞行器的外壳的尺寸释放存储器之后的空腔 - 飞机界面的空气湍流，气囊系统的扩展形状为 由连接到安全气囊的内表面的多个束带控制，以限制当气压被施加到其内部时气囊的外表面的位移。
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公开(公告)号：US1331359A
公开(公告)日：1920-02-17
申请号：US34006819
申请日：1919-11-22
Applicant: ROBERT HENRY DAVIS
Inventor： HUGHES PARROTT ARTHUR , HAROLD ROUND
CPC classification number: B64D25/00 , B60R2021/0407 , B64D2201/00
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