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1. 发明申请

US20090072087A1 Aircraft ejection seat system 有权
标题翻译：飞机弹射座椅系统
公开(公告)号：US20090072087A1
公开(公告)日：2009-03-19
申请号：US11445881
申请日：2006-06-02
申请人： Brad Mastrolia
发明人： Brad Mastrolia
IPC分类号： B64D25/108
CPC分类号： B64D25/10
摘要： An ejection seat having pitch, roll, and yaw control provided by three separate rocket motors where each rocket motor has a fixed nozzle and the entire rocket motor is rotated about a single axis corresponding to the minimum principal moment of inertia of the rocket. Actuation for each rocket motor is by means of a hydraulic rack and pinion actuator. Power for the hydraulic actuators is provided by a unique hydro-pneumatic amplifier that converts stored gas energy into pressurized hydraulic fluid. The high pressure hydraulic fluid is directed through conventional servo valves into the appropriate actuators to provide main, roll, pitch, and yaw thrust as required to achieve upright orientation and vertical flight.
摘要翻译：具有由三个独立的火箭发动机提供的俯仰，滚转和偏航控制的弹射座椅，其中每个火箭发动机具有固定喷嘴，并且整个火箭发动机围绕与火箭的最小主要转动惯量相对应的单个轴线旋转。每个火箭发动机的致动是通过液压齿条和小齿轮致动器。用于液压执行器的功率由独特的液压气动放大器提供，其将储存的气体能量转换成加压的液压流体。高压液压流体通过常规的伺服阀被引导到适当的致动器中，以根据需要提供主要的，滚动的，俯仰的和偏航的推力，以实现垂直方向和垂直飞行。

2. 发明申请

US20120132099A1 NONTOXIC, NONCORROSIVE PHOSPHORUS-BASED PRIMER COMPOSITIONS AND AN ORDNANCE ELEMENT INCLUDING THE SAME 有权
标题翻译：非特异性，基于非腐蚀性磷酸盐的母体组合物和包括它们的元素元素
公开(公告)号：US20120132099A1
公开(公告)日：2012-05-31
申请号：US12194437
申请日：2008-08-19
申请人： Randall T. Busky , Tod R. Botcher , Joel L. Sandstrom , Jack A. Erickson
发明人： Randall T. Busky , Tod R. Botcher , Joel L. Sandstrom , Jack A. Erickson
IPC分类号： F42B4/26 , C06B45/34 , C06B45/10 , C06B39/06 , F42C19/08 , F42B5/02 , C06C5/00 , F42B12/20 , F42B27/00 , F42B7/04 , F42B10/02 , F42B15/00 , B64D25/108 , F16B35/00 , F02K9/00 , B26D5/08 , C06B39/00
CPC分类号： C06B39/00 , C06C7/00 , Y10T83/869
摘要： A primer composition that includes red phosphorus having an acid scavenger and a polymer thereon. The primer composition includes at least one other component that is substantially free of lead. The other component is at least one oxidizer, or at least one oxidizer and at least one of at least one secondary explosive composition and at least one energetic binder. The primer composition optionally includes at least one element having an ionic charge to ionic radius ratio of 4 or of 8, such as magnesium, zirconium, aluminum, silicon, titanium, tungsten, alloys thereof, and combinations thereof. The red phosphorus and the at least one oxidizer are present in the primer composition at approximately stoichiometric amounts. An ordnance element including the primer composition is also disclosed.
摘要翻译：一种底漆组合物，其包含具有酸清除剂的红磷和其上的聚合物。底漆组合物包括基本上不含铅的至少一种其它组分。另一组分是至少一种氧化剂，或至少一种氧化剂和至少一种二级炸药组合物和至少一种能量粘合剂中的至少一种。底漆组合物任选地包括至少一种离子电荷对离子半径比为4或8的元素，例如镁，锆，铝，硅，钛，钨，它们的合金，及其组合。红磷和至少一种氧化剂以约化学计量的量存在于底漆组合物中。还公开了包含底漆组合物的弹性元素。

3. 发明申请

US20090212160A1 Method for producing lateral ejection apparattii for helicopter or plane 审中-公开
公开(公告)号：US20090212160A1
公开(公告)日：2009-08-27
申请号：US11827146
申请日：2007-09-17
申请人： Michael Lawrence Beauchamp
发明人： Michael Lawrence Beauchamp
IPC分类号： B64D25/108
CPC分类号： B64D25/10 , B64D2201/00
摘要： An aircraft fuselage, with a seat chassis mounted on a set of track and guide rails. Any ejection seat chassis with an occupant attached to a guide track is ejectable along a lateral trajectory, perpendicular to the horizontal longitudinal axis of an aircraft fuselage interior, and can be guided out of the field of an imperiled aircraft during ejection by a rocket catapult system. A seat, framework, bed or chassis is enabled to eject laterally from an aircraft fuselage since a conventional hinged door is operational within a greater sliding emergency door panel which pneumatic rockets at the top and bottom of the emergency sliding door transverse the greater emergency sliding door panel including an interior fixed conventional hinge operational door along a set of tracks attached to the frame and outer fuselage of said aircraft, out of the path of the lateral ejection seat chassis or chassis', towards the rear of an aircraft where the sliding greater panel is prevented from recoiling by spring loaded latch catches; and which emergency door can also drop-slide down by pneumatic rocket assist for some aircraft where the weight, time and spatial difference between a drop-down and a slide-back emergency door or exit opening can in many instances is a benefit to use a drop-down emergency door or exit, pneumatically propelled; so that an aircraft has less nascent drag from rocket weight, and can result in a fractionally quicker or faster rate of acceleration and removal of the door, panel or canopy from the lateral ejection pathway when feasible. Wing struts can also be removed from the emergency lateral ejection exit pathway by pneumatic or other explosive charge means. Additional supporting fuselage struts and slender tempered glass panes are constructed into the fuselage for increased rigidity for the enlarged fuselage structure incorporating a same near relative number of aircraft seats for pilots and passengers, equipped with lateral ejection apparattii, and has an improved field of view. Dual airbags for positioning the legs and torso of an occupant for a safe emergency exit lateral ejection are embedded or attached to a structure directly in front of a seat chassis. A second set of pressure sensitive airbags, head, neck, spine and organ concave-convex protector are attached on both sides of a seat chassis. Three compartments for altitude appropriate parachutes and a sensor fuse box for opening said desired chute are located inside an ejection seats rigid framework back section. The invention includes an interior side mounted blast shield which a rocket catapult systems rocket nozzles face, and which rocket or rockets are locked by collar seal(s) to a said blast shields, alloy or metallic, ceramic tile backing. A track support launcher platform, column, columns or center console support the lateral ejection apparattii at a functional and comfortable level and height for the occupant or occupants. Otherwise, the tracks or guide rails can be attached directly on an aircraft fuselage floor frame or attached to a wall frame structure in an aircraft fuselage, and can be constructed within rows with aisles on a chain motor reloading laterally aligned guide track for lateral rotor positioning lateral ejection apparattii.

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