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1. 发明申请

WO2013121139A3 DEVICE FOR SUPPLYING AIR TO AN AUXILIARY POWER UNIT OF AN AIRCRAFT AND ASSOCIATED AIRCRAFT 审中-公开
标题翻译：向飞机和相关飞机的辅助动力装置供应空气的装置
公开(公告)号：WO2013121139A3
公开(公告)日：2014-03-20
申请号：PCT/FR2013050283
申请日：2013-02-12
申请人： MOTORISATIONS AERONAUTIQUES
发明人： JOUBERT HUGUES DENIS , FERRARI SEBASTIEN
IPC分类号： B64D41/00 , B64D13/06 , B64D33/02
CPC分类号： B64D33/02 , B64D13/00 , B64D27/08 , B64D41/00 , B64D2013/0611 , B64D2033/0213 , B64D2041/002 , F05D2220/50 , Y02T50/44 , Y02T50/54
摘要： The device for supplying air to an auxiliary power unit (GAP) of an aircraft, said auxiliary power unit comprising a diesel engine (M) coupled to a turbocharger (TC), the said turbocharger comprising at least one first air inlet (AIR_CAB_1) for admitting air to a combustion chamber (CC) of the diesel engine (M) and a first outlet (AIR_T) carrying the burnt air to the turbocharger (TC), the diesel engine (M) delivering a power that is able to power an electric alternator (ALT) and a compressor (CP) known as the pressurizing compressor, intended to heat a second air inlet (AIR_EXT_32). The first air inlet (AIR_CAB_1) is fed with a fraction of pressurized air from the cabin (CAB) of the aircraft.
摘要翻译：用于向飞机的辅助动力单元（GAP）供应空气的装置，所述辅助动力单元包括联接到涡轮增压器（TC）的柴油发动机（M），所述涡轮增压器包括至少一个第一空气入口（AIR_CAB_1），用于将空气进入柴油发动机（M）的燃烧室（CC）和将燃烧空气携带到涡轮增压器（TC）的第一出口（AIR_T），柴油发动机（M）输送能够向电动机交流发电机（ALT）和称为加压压缩机的压缩机（CP），用于加热第二个空气入口（AIR_EXT_32）。第一个空气入口（AIR_CAB_1）从飞机的舱室（CAB）供给一部分加压空气。

2. 发明申请

WO2011142859A1 TWO-STROKE, FUEL INJECTED INTERNAL COMBUSTION ENGINES FOR UNMANNED AIRCRAFT AND ASSOCIATED SYSTEMS AND METHODS 审中-公开
标题翻译：两用燃油喷射内燃机，用于不定型飞机及相关系统及方法
公开(公告)号：WO2011142859A1
公开(公告)日：2011-11-17
申请号：PCT/US2011/023815
申请日：2011-02-04
申请人： INSITU, INC. , FFIELD, Paul , SIMMONS, Chuck , STEBBINS, Glen
发明人： FFIELD, Paul , SIMMONS, Chuck , STEBBINS, Glen
IPC分类号： F02B25/14 , F02B25/20 , F02B33/04 , F02D41/30
CPC分类号： F02M39/00 , B64D27/08 , F02B25/14 , F02B25/20 , F02B33/04 , F02B2075/025 , F02B2075/125 , F02D35/023 , F02D41/0087 , F02D41/123 , F02D41/1439 , F02D41/1444 , F02D41/222 , F02D41/3058 , F02D2200/0404 , F02D2400/04 , F02M69/10 , Y02T10/123
摘要： Two-stroke, fuel injected internal combustion engines for unmanned aircraft and associated systems and methods are disclosed herein. Engines configured in accordance with embodiments of the disclosure can include, for example, (a) an electronic fuel injection system configured to provide a desired low fuel rate by injecting fuel every nth compression cycle rather than every cycle (so-called "skip-cycle" operation), (b) one or more pressure sensors configured to measure fluctuations in peak crankcase pressure and use such fluctuations to control fuel injection delivery, and (c) a multi-cylinder configuration having a common crankcase with a fuel injection arrangement configured to mitigate or eliminate problems with mixed redistribution.
摘要翻译：本文公开了用于无人驾驶飞行器的二冲程燃料喷射内燃机及相关系统和方法。根据本公开的实施例构造的发动机可以包括例如（a）电子燃料喷射系统，该电子燃料喷射系统被配置为通过每第n个压缩循环而不是每个周期喷射燃料来提供期望的低燃料速率（所谓的“跳过循环 “操作”），（b）一个或多个压力传感器，被配置为测量曲轴箱顶部压力的波动并使用这种波动来控制燃料喷射输送;以及（c）具有共同的曲轴箱的多气缸构造，燃料喷射装置配置成减轻或消除混合再分配的问题。

3. 发明申请

WO1998025821A1 AIRCRAFT EQUIPPED WITH ROTARY PISTON AND CONTRA-ROTATING PROPELLER PISTON JET ENGINES 审中-公开
标题翻译：装有旋转活塞和旋转螺旋桨活塞喷气发动机的飞机
公开(公告)号：WO1998025821A1
公开(公告)日：1998-06-18
申请号：PCT/FR1996001987
申请日：1996-12-12
申请人： DELMOTTE, Didier
IPC分类号： B64D27/02
CPC分类号： B64D27/08 , B64D27/06
摘要： Aircraft equipped with pod-mounted rotary piston and contra-rotating propeller jet engines. One aspect of the invention consists in the adaptation of the rotary piston and contra-rotating propeller piston jet engines (3) to any aircraft cell by replacing the currently installed traction systems: the reciprocating engines (1), an example of which is shown in figure 1; the rotary piston and ducted propeller piston jet engines (2) shown in figure 2. A second aspect of the invention consists in moving the engine masses of the two pod-mounted rotary piston and contra-rotating propeller piston jet engines (3) forwards and backwards with respect to a point of reference on either side of the aircraft body, as shown in figures 3 and 4, thereby aligning the aircraft centering.
摘要翻译：飞机装有荚式旋转活塞和反转螺旋桨喷气发动机。本发明的一个方面在于通过更换当前安装的牵引系统来将旋转活塞和反转螺旋桨活塞喷射发动机（3）适应于任何飞行器单元：往复式发动机（1），其示例如图1; 旋转活塞和管道螺旋桨活塞喷气发动机（2），如图2所示。本发明的第二方面在于将两个荚果安装的旋转活塞和反转螺旋桨活塞喷射发动机（3）的发动机质量向前移动，如图3和图4所示，相对于飞行器主体的任一侧上的参考点向后，从而使飞行器居中对准。

4. 发明申请

WO2015022711A1 CONVERTIPLANE WITH NEW AERODYNAMIC AND TECHNICAL SOLUTIONS WHICH MAKE THE AIRCRAFT SAFE AND USABLE 审中-公开
标题翻译：具有使航空器安全可用的新的航空和技术解决方案的CONVERTIPLANE
公开(公告)号：WO2015022711A1
公开(公告)日：2015-02-19
申请号：PCT/IT2014/000212
申请日：2014-08-07
申请人： UNIT 1SRL
发明人： GIOVENGA PIETRO
IPC分类号： B64C29/00 , B64D27/08 , B64C3/38 , B64C3/54
CPC分类号： B64C29/0033 , B64C3/385 , B64C3/54 , B64C39/024 , B64C2201/021 , B64C2201/104 , B64C2201/108 , B64C2201/162 , B64D27/08 , Y02T50/14
摘要： The proposed convertiplane has the ability to take off like a helicopter and then fly horizontally like a conventional aircraft. The aircraft comprises : - a variable incidence front wing of variable span located below the fuselage and mounted on a structure in the form of a venturi tube - a rear wing having two propellers for controlling the stability of the vehicle in pitch and roll installed therein - two counter-rotating, pivotally mounted ducted propellers equipped with four flaps orthogonal to each other provided on the sides of the cockpit - engines placed behind the cockpit close to the center of gravity - a static balancing system for controlling the center of gravity of the aircraft consisting of a weight placed in the lower part of the fuselage, self-propelled on the track rack longitudinally to the fuselage - Digital flight control system
摘要翻译：提出的转换飞机具有像直升机一样起飞的能力，然后象常规飞机一样水平飞行。飞机包括： - 位于机身下方的可变跨度的可变入射前翼，并安装在文丘里管形式的结构上 - 后翼具有两个螺旋桨，用于控制安装在其中的俯仰和滚动中的车辆的稳定性 - 两个反向旋转的枢转安装的管道式推进器，其配备有四个彼此正交的翼片，其设置在驾驶舱的侧面 - 放置在靠近重心的驾驶舱后面的发动机 - 用于控制飞行器的重心的静态平衡系统由放置在机身下部的重量组成，在轨道架上纵向自动推进到机身 - 数字飞行控制系统

5. 发明申请

WO2010010293A3 AIRCRAFT INCLUDING ENGINE CONTROLLED BY SYNCHROPHASING 审中-公开
标题翻译：飞机包括通过同步控制的发动机
公开(公告)号：WO2010010293A3
公开(公告)日：2010-03-18
申请号：PCT/FR2009051464
申请日：2009-07-21
申请人： AIRBUS OPERATIONS SAS , SAUCRAY JEAN-MICHEL , CHAREYRE PHILIPPE
发明人： SAUCRAY JEAN-MICHEL , CHAREYRE PHILIPPE
IPC分类号： B64D31/12
CPC分类号： B64D31/12 , B64C11/008 , B64C11/48 , B64C11/50 , B64D27/08 , B64D2027/026 , Y02T50/66
摘要： The aircraft (50) of the invention includes at least one engine (56) having counter-rotating rotors (58a, 58b), the engine or at least one of the engines having imbalances associated with at least one ellipse (70). The aircraft includes at least one vibration damper (64, 66) attached in an arrangement such that, at a given engine speed and for at least one given common direction of a large axis (68) of the ellipse or at least one of the ellipses, a speed related to the two ends of the damper is higher than for any other arrangement of the damper.
摘要翻译：本发明的飞机（50）包括至少一个具有反向旋转转子（58a，58b）的发动机（56），发动机或至少一个发动机具有与至少一个椭圆（70）相关联的不平衡。该飞行器包括至少一个减振器（64,66），该振动阻尼器（64,66）以一种布置的方式附接，使得在给定的发动机转速和至少一个给定的椭圆的大轴（68）的给定的共同方向或椭圆的至少一个与阻尼器的两端相关的速度高于阻尼器的任何其它布置。

6. 发明申请

WO2010020199A1 AIRCRAFT HYBRID PROPULSION 审中-公开
标题翻译：飞机混合推进
公开(公告)号：WO2010020199A1
公开(公告)日：2010-02-25
申请号：PCT/CZ2009/000102
申请日：2009-08-19
申请人： VYCITAL, Jiri , MORAVEC, Tomas
发明人： VYCITAL, Jiri , MORAVEC, Tomas
IPC分类号： B64D27/08 , B64D27/14 , B64D27/24
CPC分类号： B64D27/08 , B64D27/24 , B64D2027/026 , Y02T50/64
摘要： The invention relates to the aircraft hybrid propulsion, consisting of two propeller propulsion units, one of which is based on the principle of an internal combustion engine (1). with a propeller and the second one on the principle of an electric motor (2) with a propeller characterized in that the propulsion units are installed without an interdependent mechanical coupling in the push-pull configuration in the direction of flight on the aircraft fuselage, so that one of the propulsion units (1, 2) is located in the forward fuselage and generates a propulsion effect using a tractor propeller and the second one of the propulsion units (1, 2) is located in the rear fuselage and generates a propulsion effect using a pusher propeller and the batteries supplying the energy to the electric motor are rechargeable by recuperation during flight. From the electric motor with a propeller (2) and/or from a generator installed on the internal combustion engine (1).
摘要翻译：本发明涉及由两个螺旋桨推进装置组成的飞机混合动力推进装置，其中之一是基于内燃机（1）的原理。具有推进器，第二个是具有螺旋桨的电动机（2）的原理，其特征在于，推进装置在飞行器机身上的飞行方向上的推拉构造中没有相互依赖的机械联接而安装，因此推进单元（1,2）中的一个位于前机身中并且使用拖拉机螺旋桨产生推进效果，并且第二推进单元（1,2）位于后机身中并且产生推进效应使用推动螺旋桨，并且向电动机供应能量的电池可以通过在飞行期间的恢复来充电。从具有螺旋桨（2）的电动机和/或来自安装在内燃机（1）上的发电机。

7. 发明申请

WO2017118082A1 减震结构、云台及飞行器审中-公开
公开(公告)号：WO2017118082A1
公开(公告)日：2017-07-13
申请号：PCT/CN2016/098881
申请日：2016-09-13
申请人：深圳市大疆创新科技有限公司
发明人：张永生 , 王佳迪 , 陈星元
IPC分类号： B64D27/08
CPC分类号： B64D27/08
摘要：一种减震结构（100），云台（200）及飞行器（300），减震结构（100）包括可变形的减震件（30），减震件（30）开设有收容腔（331），收容腔（331）内填充有阻尼减震材料（34），减震件（30）与阻尼减震材料（34）能够进行复合式减震。

8. 发明申请

WO2009068638A1 IMPACT RESISTANT AIRCRAFT FUSELAGE 审中-公开
标题翻译：防撞飞机熔接
公开(公告)号：WO2009068638A1
公开(公告)日：2009-06-04
申请号：PCT/EP2008/066400
申请日：2008-11-28
申请人： AIRBUS ESPAÑA S.L. , VERDE PRECKLER, Jorge Pablo
发明人： VERDE PRECKLER, Jorge Pablo
IPC分类号： B64C1/00 , B64D27/02 , B64D29/04 , B64D27/14
CPC分类号： B64C1/12 , B64C1/068 , B64C2001/0072 , B64D27/08 , B64D27/14 , Y02T50/43
摘要： The invention relates to a structural configuration of the rear fuselage (4) of an aircraft with propeller engines (1) comprising propellers (23) formed in turn by blades (3), the mentioned propeller engines (1) being located at the rear part of the aircraft and the empennage (5) of the aircraft in turn being located behind the plane of the propellers (23), characterized in that the structural configuration of the rear fuselage (4) comprises an outer skin (6) and an inner skin (7), both skins (6, 7) being joined by means of radial elements (13) configuring cells (14), such that the obtained structural configuration maximizes the torsional strength of the rear fuselage (4) of the aircraft in the event of damage of the mentioned rear fuselage (4) due to the detachment of one of the blades (3) of the propeller engines (1).
摘要翻译：本发明涉及具有螺旋桨发动机（1）的飞行器的后机身（4）的结构构造，所述螺旋桨发动机（1）包括由叶片（3）依次形成的螺旋桨（23），所述螺旋桨发动机（1）位于后部的飞机和后轮（5）又位于螺旋桨（23）的平面之后，其特征在于后机身（4）的结构构造包括外皮（6）和内皮（7）中，两个外壳（6,7）通过配置电池（14）的径向元件（13）连接，使得所获得的结构构造在事件中使飞行器的后机身（4）的扭转强度最大化由于螺旋桨发动机（1）的一个叶片（3）的分离，所述后部机身（4）的损坏。

9. 发明申请

WO01054978A1 IMPROVED AEROBATIC AIRCRAFT 审中-公开
标题翻译：改进的AEROBATIC AIRCRAFT
公开(公告)号：WO01054978A1
公开(公告)日：2001-08-02
申请号：PCT/US2001/003119
申请日：2001-01-31
IPC分类号： B64C39/04 , B64D27/08 , B64D27/10 , B64D33/00 , F01M11/06
CPC分类号： B64D33/00 , B64C39/04 , B64D27/08 , B64D27/10 , F01M11/067
摘要： An improved aerobatic aircraft design having a first engine (18) located in the nose portion (14) of the fuselage (12) and a second engine (22) located in the tail portion (16) of the fuselage (12). The thrust components of both the first (18) and second (22) engines are coaxial along the long axis (70) of the fuselage (12). Both engines can individually provide sufficient power for the aircraft to takeoff, maintain altitude, and/or land.
摘要翻译：一种改进的特技飞行器设计，其具有位于机身（12）的鼻部（14）中的第一发动机（18）和位于机身（12）的尾部（16）中的第二发动机（22）。第一（18）和第二（22）发动机的推力部件沿机身（12）的长轴（70）同轴。这两种发动机可以单独提供足够的动力使飞机起飞，保持高度和/或降落。

10. 发明申请

WO9505974A3 MULTI-PURPOSE AIRCRAFT 审中-公开
标题翻译：多用途飞机
公开(公告)号：WO9505974A3
公开(公告)日：1995-06-08
申请号：PCT/US9409474
申请日：1994-08-24
申请人： GEVERS DAVID E
发明人： GEVERS DAVID E
IPC分类号： B64C1/00 , B64C3/38 , B64C3/54 , B64C3/56 , B64C25/52 , B64C25/54 , B64C25/66 , B64C35/00 , B64C35/02 , B64D27/00 , B64D27/02 , B64D27/08 , B64D29/04 , B64D35/04 , B64D25/08
CPC分类号： B64D35/04 , B64C1/00 , B64C3/38 , B64C3/54 , B64C3/56 , B64C25/52 , B64C25/54 , B64C25/66 , B64C35/00 , B64C35/002 , B64C35/008 , B64C2001/0045 , B64D27/00 , B64D27/08 , B64D29/04 , Y02T50/12 , Y02T50/145 , Y02T50/44
摘要： 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.
摘要翻译：披露了一些飞机的创新系统，以及包含它们的飞机。特征包括内置式发动机（24,25），带有用于转动机翼定位螺旋桨（8,9）的皮带传动系统（84,99）; 复合起落架整合滑雪（29,114），浮桥和轮（18,19,21）子部件; 用于起落架和/或螺旋桨的枢转安装衔铁（6,7），其提供多个可能的起落架和/或螺旋桨结构; 以及具有可延伸的翼板（4,5）的复合翼结构（14,15），其允许飞行器的机翼跨度在飞行中几乎翻倍。结合这种特征的飞机将比常规多引擎飞机享有几个安全优势，并且能够在飞行期间进行修改，这些飞行器可以在雪，硬表面（跑道）和水中任何一个上升降。

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