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序号	专利名	申请号	申请日	公开（公告）号	公开（公告）日	发明人
221	JPS63501787A -	JP50401286	1986-06-20	JPS63501787A	1988-07-21
In a design and construction method, for a graduated series of aircraft of various sizes, development costs are minimized by maintaining a consistent scale configuration from model to model, and production costs are minimized through the use of a universal tooling concept for the manufacturing of detail parts, subassemblies and components of the airframes. Each model (M11, M12...M1n) of a series size-graduated elements such as the main wing airfoils (31, 32, 33) is designed with similar characteristics and overlapping dimensions. A common set of tools for constructing these elements is built to accommodate the largest dimensions, such as the root chord (34) of the largest airfoil (31), down to the smallest dimension, such as the tip chord (35) of the smallest airfoil (33). The maintaining of a consistent geometric-scaled relationship between the wing, horizontal and vertical airfoils of the various models for specific manufacturer's size-graduated series of aircraft and the maintenance of the structural bending and torsional stiffness coefficients consistent from model to model provides for consistent flying qualities and performance characteristics assuming that the thrust to weight ratios are also maintained constant from one model to another throughout a specific manufacturer's size-graduated series of aircraft. The universal tooling concept provides for a set of tooling to be used by a specific manufacturer for the making of all of the detail parts and the assembly of these parts, materials and components into completed airframes for each model in a specific manufacturer's size-graduated series of aircraft.
222	JPS62501408A -	JP50021185	1985-11-22	JPS62501408A	1987-06-11
A design and construction method for a graduated series of aircraft of various sizes of which development costs are minimized by maintaining a consistant scale configuration from model to model, and production costs are minimized through maximum reuse of molds, jigs, templates or other tooling for the manufacturing of detail parts, subassemblies and components of the airframes. Full implementation of the design and construction method is made possible through the use of "state-of-the-art" composite materials, which have sufficient bending and torsional stifness to permit the construction of a aft-mounted forward-swept wing (12) of high aspect ratio without a severe weight penalty. The forward-swept, high-aspect-ratio wing, in turn, allows the construction of an airframe configuration having, in addition to the forward-swept main wing airfoil (12), a canard airfoil (11), a aft-fuselage-mounted vertical airfoil (13) and propulsion system (6A-6H). Elimination of main-wing attachment points from the center fuselage section facilitates the design and manufacture of that section and allows the use of fuselage nose (81A-81H) and tail sections (82A-82D and 83E-83H) having a high degree of commonality between models. Main wing, canard and vertical airfoild for all models in the series are produced from a subset of molds, jigs, templates or other tooling which are shared to a significant degree by all models in the series.
223	JPS6244800U -	JP8032786	1986-05-29	JPS6244800U	1987-03-18

224	JPS5917647B2 -	JP14008475	1975-11-20	JPS5917647B2	1984-04-23	PIEERU BAANOWAN
1512276 Moulded inserts SOC NATIONALE INDUSTRIELLE AEROSPATIALE 24 Nov 1975 [26 Nov 1974] 48241/75 Heading B5A A thin-walled, hollow, composite structure such as a helicopter fuselage 26 is made by locating a plurality of rigid, heat-conducting, reinforcing elements forming two or more independent sub-frames 20 and 23 &c. adjacent internal walls of a rotatable mould (Fig. 1, not shown), said elements following substantially the contours of the internal walls of the mould, introducing a synthetic, plastics, moulding material into the mould and heating and rotating the mould to cause the material to form a relatively thin shell extending between and interconnecting the sub-frames formed by the reinforcing elements.
225	SYSTEM FOR ALIGNING A PROPELLER	PCT/US2012051213	2012-08-16	WO2013066477A3	2013-06-27	FIRANSKI JASON; MCALLISTER JUSTIN BATES; OLCH RONALD H; DALAN LANE DENNIS; GHAPGHARAN EMIL
A motor assembly that includes a motor (102) having a rotatable shaft (100), a hub (106) coupled to the rotatable shaft (100), the hub (106) having a propeller indexer (118) to receive a propeller (104), when the propeller (104) is present, a sensor trigger (108) rotatable with the shaft (100) and positioned at a propeller offset angle thetaPROP from the propeller indexer (118), and a sensor (110) coupled to the motor and positioned to detect the sensor trigger (108) so that the propeller indexer (118) may be positioned at the propeller offset angle thetaPROP from the sensor (110) through rotation of the shaft (100) so that said sensor (110) is proximate to the sensor trigger (108).
226	PLANETARY DE-ROTATION SYSTEM FOR A SHAFT FAIRING SYSTEM	PCT/US2008050010	2008-01-02	WO2009088491A2	2009-07-16	LAUDER TIMOTHY FRED
A de-rotation system includes a planetary gear set, and a fairing support structure mounted for rotation with a first ring gear.
227	TWIN ENGINE AIRCRAFT	PCT/US9917316	1999-07-29	WO0009392A8	2000-07-13	WILLIAMS SAMUEL BARLOW
A jet aircraft (10) has a generally conical front fuselage section (14), a cylindrical intermediate fuselage section (16) defining a passenger compartment, a generally conical aft fuselage section (18), and a single vertical stabilizer (20). The aircraft's propulsion engines (30 and 32) are mounted on pylons (33) on the conical aft fuselage section (18) with the air inlets (34 and 36) thereof disposed entirely within a rearward projection (37) of the lateral cross section of the intermediate fuselage section (16) thereby to preclude the ingestion of foreign objects into the engines (30 and 32) while minimizing the effect of boundary layer airflow. The exhaust nozzles (50 and 52) extend rearwardly past the vertical stabilizer (20) to minimize side line noise.
228	MULTI-PURPOSE AIRCRAFT	PCT/US9409474	1994-08-24	WO9505974A3	1995-06-08	GEVERS DAVID E
Several innovative systems for an aircraft, and aircraft incorporating them, are disclosed. Features include inboard-mounted engine(s) (24, 25) with a belt drive system (84, 99) for turning wing-situated propellers (8, 9); compound landing gear integrating ski (29, 114), pontoon and wheel (18, 19, 21) subcomponents; pivotal mounting armatures (6, 7) for landing gear and/or propellers which provide a plurality of possible landing gear and/or propeller configurations; and a compound wing structure (14, 15) featuring extendable wing panels (4, 5) that permit the wing span of the aircraft to be nearly doubled while in flight. Aircraft incorporating such features will enjoy several safety advantages over conventional multi-engine aircraft and will be capable of modifications during flight which permit landings on any of snow, hard surfaces (runways) and water.
229	COMPOSITE MATERIALS	PCT/US2013036555	2013-04-15	WO2014011293A2	2014-01-16	RESTUCCIO CARMELO LUCA; FRULLONI EMILIANO; LENZI FIORENZO
A composite material that includes a layer of reinforcing fibres impregnated with a curable resin matrix and a plurality of electrically conductive composite particles positioned adjacent or in proximity to the reinforcing fibres. Each of the electrically conductive composite particles is composed of a conductive component and a polymeric component, wherein the polymeric component includes one or more polymers that are initially in a solid phase and are substantially insoluble in the curable resin, but is able to undergo at least partial phase transition to a fluid phase during a curing cycle of the composite material.
230	STRUCTURAL COMPONENT OF AN AIRCRAFT OR SPACECRAFT AND A FUSELAGE COMPONENT ARRANGEMENT OF AN AIRCRAFT OR SPACECRAFT	PCT/EP2009065227	2009-11-16	WO2010060824A4	2010-07-22	GROSS CLAUS-PETER
The invention relates to a structural component (2) of an aircraft or spacecraft comprising a fuselage section connection area (10) for connecting to an associated fuselage section (5) having a thermal expansion coefficient that is approximately aligned with the associated fuselage section (5); an inner connection area (11) for connecting to an associated installation element having a thermal expansion coefficient that is approximately aligned with the associated installation element; and a separating area (12) for connecting the fuselage section connection area (10) and the inner connection area (11), wherein at least one of the areas (10, 11, 12) has a high thermal resistance (R13, R14, R15).
231	MODULAR AEROSPACE PLANE	PCT/US2006015869	2006-04-28	WO2007133182A2	2007-11-22	TALMAGE ROBERT
A modular aerospace plane. In one embodiment the plane can include a forward fuselage section, a main wing section, a tail section and wing attachments. Various sections can be integrated to offer a variety of aircraft characteristics, performance and missions. The forward fuselage and tail sections may utilize a parachute device whereby these sections can separate in an emergency and safely lower the occupants to the ground.
232	ROTOR HUB FAIRING SYSTEM FOR A COUNTER-ROTATING, COAXIAL ROTOR SYSTEM	PCT/US2006016401	2006-04-28	WO2006130287A3	2007-10-04	BERTOLOTTI FABIO P
A rotor hub fairing system includes an upper hub fairing, a lower hub fairing and a shaft fairing therebetween. The rotor hub fairing system is sized and configured to reduce the overall drag on a dual, counter-rotating, coaxial rotor system. Preferably, the rotor hub fairing is fully integrated. The shaft fairing preferably includes a minimal thickness at the midsection to reduce drag with an increasing thickness adjacent the upper and lower hub fairings to reduce the flow separation on the hub fairing surfaces without overly excessive drag. Other aerodynamic structures, such as a horizontal splitter and/or a plurality of turning vanes may be mounted to the shaft fairing to facilitate flow around the upper and lower hub fairings to reduce flow separation and drag.
233	一种椭球形飞行器	CN201720047584.7	2017-01-16	CN206427265U	2017-08-22	蔡波
本实用新型提供一种椭球形飞行器，壳体的上端安装有上盖，壳体的下端装配有升降座，升降座为圆盘形结构，升降座的中轴线与壳体的中轴线处于同一直线上，上盖与壳体连接处的位置通过转轴安装有旋转臂，旋转臂下侧的中间位置装配有固定套筒，固定套筒为圆筒形结构，固定套筒的内部安装有电机，通过添加升降座来实现对本实用新型升降过程的稳定性控制，增加外壳与地面之间的接触面积，防止侧翻的情况出现，防止由于硬接触造成壳体内部电子元器件损坏的情况出现，而旋转臂通过卡扣与位于壳体凹槽内部的卡槽啮合在一起，该设计可以有效的防止旋转臂在运输的过程中由于松动造成叶片与电机损坏的情况出现，该设计解决了传统设备容易损坏的难题。
234	一种太阳能四旋翼飞行器	CN201621276046.7	2016-11-25	CN206187335U	2017-05-24	文锦伟; 苏俊鹏
本实用新型公开了一种太阳能四旋翼飞行器，其太阳能电池板输入端与电子开关输出端电连接，太阳能电池板输出端与DC/DC转换器、充电器和电压采集模块相连接，电子开关输入端与微控制器连接，电子开关输出端还与蓄电池连接，蓄电池输入端与充电器连接，蓄电池输出端与DC/DC转换器连接，微控制器输入端与DC/DC转换器、电压采集模块连接，微控制器和DC/DC转换器的输出端均与电机驱动器连接，电机驱动器与电机连接。本实用新型结构简单，利用立体分层采光，可以大大增强太阳能利用率，减小整机的体积，降低了设计成本；机身利用碳纤维或石墨烯气凝胶材料制作，减轻整体重量，飞行灵巧轻便；自带蓄电池和电源切换控制装置，保证了整机的可靠供电。
235	WINGS FOR FLYING OBJECTS (VARIANTS)	US16342541	2017-10-12	US20190241249A1	2019-08-08	Gevorg Serezhaevich NOROYAN
The group of inventions relates to the field of aircraft. In each variant, a flying object (FO) comprises a body and wings. In a first variant, an FO comprises wings mounted so as to be capable of rotating the FO. In a second variant, an FO comprises a body on which is mounted a rim with side wings. In a third variant, an FO comprises wings in the shape of a triangular prism, one side of which is fastened to the body, and the other two sides of which are spherical with arcs of different radii. In a fourth variant, the FO comprises tail wings fastened to the body such that the exhaust gases from the nozzle impinge on the wings and create a force which rotates the FO.
236	CONDUCTIVE DEVICE INTENDED TO BE MOUNTED ON THE SURFACE OF PARTS MADE OF COMPOSITE MATERIALS	US15527900	2015-11-19	US20180342332A1	2018-11-29	DIDIER MESNAGE; THIERRY PELEGRIN
A conductive device to form electrical connections on the surface of a structure made of composite material. The device includes a thin interface layer having a face via which the device is fixed to the surface of the structure made of composite material. A conductive metal element is placed on the face of the interface layer opposite the face making contact with the surface of the structure. The conductive element is configured to be able to undergo tensile and compressive stresses without damage. A protective layer is configured to protect the conductive element from attack from the environment surrounding the structure. These various elements are arranged relative to one another such that the length of the conductive element can vary as a function of temperature variations independently of the amplitude of the variations undergone by the structure on which the device is mounted.
237	Monument for a cabin of a vehicle, and fastening arrangement	US15099074	2016-04-14	US10137974B2	2018-11-27	Tim von Ahlen; Daniel Hiebing; Ansgar Josef Fennen; Falk Bajorat; Christian Lübbering
A monument for a cabin of a vehicle, in particular of an aircraft or spacecraft, having an outer housing side and a fastening rail for fastening connection elements in a longitudinal direction of the fastening rail in order to fix the monument in position inside the cabin, wherein the fastening rail has a receiving space extending in the longitudinal direction of the fastening rail, which space is designed to receive and fasten mounting feet of the connection elements to the fastening rail, and wherein the fastening rail is integrated in the outer housing side.
238	Self-righting aeronautical vehicle and method of use	US15672262	2017-08-08	US10112694B2	2018-10-30	Gaofei Yan; James Dees
A self-righting aeronautical vehicle comprising a hollowed frame and a lift mechanism. The exterior of the frame and center of gravity are adapted to self-right the vehicle. The frame can include sealed, hollowed sections for use in bodies of water. The frame can be spherical in shape enabling inspection of internal surface of partially or fully enclosed structures. Inspection equipment can be integrated into the vehicle and acquired data can be stored or wirelessly communicated to a server. A controlled or other mass can be pivotally assembled to a pivot axle spanning across the interior of the frame. The pivot axis can rotate about a vertical axis (an axis perpendicular to the elongated axis). The propulsion mechanisms can be adapted for use as a terrestrial vehicle when enclosed in a sealed spherical shell.
239	Aircraft fuselage and aircraft with same	US15562802	2016-04-08	US20180281919A1	2018-10-04	Yu Tian; Wenyan Jiang
The present invention provides an aircraft housing and an aircraft with the same. The aircraft housing includes an upper housing and a lower housing. The upper and lower housings are connected through ultrasonic welding or gluing. The aircraft housing has a cavity therein which is communicated with at least one opening of the lower housing. A power system is located within the cavity through the opening. In the present invention, the upper and lower housings of the aircraft are connected through ultrasonic welding, and the aircraft is formed by one step and is high in good product rate. Meanwhile, the aircraft housing is processed through welding, so that the upper and lower housing are in seamless connection with each other, the contact surface suffers from stress, and the strength is substantially increased.
240	METHOD AND APPARATUS FOR FABRICATION OF LATTICE COMPOSITE FUSELAGE FOR COMMERCIAL AIRCRAFT EMPLOYING STEERED FIBER LAY UP	US15467980	2017-03-23	US20180273206A1	2018-09-27	Boris B. Sokolov; Mostafa Rassaian; Marc J. Piehl
A system for fabrication of an aerospace structure incorporates a mold having a surface and at least one unidirectional SFL head adapted to lay down a plurality of collimated tows in a predetermined laminated pattern on the mold surface to produce a fuselage skin. At least one cross plied laminate SFL head is adapted to lay down a cross plied laminate base interface on the fuselage skin to establish a lattice rib shape for each of a plurality of lattice ribs. The cross plied laminate SFL head has a band placement head steerable to avoid structural design features and to maintain spacing from adjacent steered lattice ribs. The unidirectional SFL head is further adapted to lay down a plurality of collimated tows on the base interface of each of the plurality of lattice ribs for a first plurality of unidirectional tow plies in each lattice rib. The unidirectional SFL head has a fiber placement head steerable to match the lattice rib shape to avoid structural design features and to maintain spacing from adjacent steered lattice ribs.

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