| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | 空运货物的燃料高效性的运输方法 | CN200880114513.8 | 2008-10-07 | CN101848837B | 2013-07-17 | E·小埃洛 |
| 一种由飞机运输货物到达期望地点的燃料高效性的方法。该方法包括确定能够以单个集装箱运输的货物的重量；基于所确定货物的重量，选择具有足够载重容量的集装箱来支撑该货物；并且用该货物填充所选择的集装箱。基于被填充集装箱的重量将被填充集装箱相对于该飞机的CG加载到飞机梁架上的一个位置，以保持处于该飞机的可接受CG范围内。具有较大重量的被填充集装箱被放置在该飞机的CG处或CG附近的梁架上，而具有较小重量的被填充集装箱被放置在远离该飞机的CG处。这些集装箱对于该梁架提供了强度以及刚度，以便在飞行中承受弯曲载荷以及扭转载荷。 | ||||||
| 2 | 空运货物的燃料高效性的运输方法 | CN200880114513.8 | 2008-10-07 | CN101848837A | 2010-09-29 | E·小埃洛 |
| 一种由飞机运输货物到达期望地点的燃料高效性的方法。该方法包括确定能够以单个集装箱运输的货物的重量；基于所确定货物的重量，选择具有足够载重容量的集装箱来支撑该货物；并且用该货物填充所选择的集装箱。基于被填充集装箱的重量将被填充集装箱相对于该飞机的CG加载到飞机梁架上的一个位置，以保持处于该飞机的可接受CG范围内。具有较大重量的被填充集装箱被放置在该飞机的CG处或CG附近的梁架上，而具有较小重量的被填充集装箱被放置在远离该飞机的CG处。这些集装箱对于该梁架提供了强度以及刚度，以便在飞行中承受弯曲载荷以及扭转载荷。 | ||||||
| 3 | 一种多旋翼武装直升机 | CN201610074594.X | 2016-01-29 | CN105730684A | 2016-07-06 | 梁广俊 |
| 本发明公开了一种多旋翼武装直升机，包括机身、顶部主旋翼、尾部旋翼、侧旋翼进出装置、装甲弹出装置以及控制器等组成。其中装甲弹射装置包括绳索收缩装置固定台、绳索收缩装置、绳索、拉动端、连接轴、弹射装置工作台、伸缩弹簧、装甲重物、重物存放台与冲击端。侧旋翼运动装置包括伸缩杆、回转臂、侧旋翼、侧旋翼运动装置工作台、伸缩臂与伸缩臂固定凸台。本发明的一种多旋翼武装直升机通过控制器控制侧旋翼进出装置、装甲弹出装置的配合工作，以保证一种多旋翼武装直升机在被袭击造成机体损伤时仍能够平稳飞行并安全降落，将遭受袭击造成的伤害降成最低。 | ||||||
| 4 | Ballast control mechanisms for aerial vehicles | US14497136 | 2014-09-25 | US09908619B1 | 2018-03-06 | Brian C. Beckman; Gur Kimchi; Amir Navot; Daniel Buchmueller |
| An automated aerial vehicle (“AAV”) and systems, devices, and techniques pertaining to moveable ballast that is movable onboard the AAV during operation and/or flight. The AAV may include a frame or support structure that includes the movable ballast. A ballast controller may be used to cause movement of the ballast based on one or more factors, such as a type of flight, a type of operation of the AAV, a speed of the AAV, a triggering event, and/or other factors. The ballast may be moved using mechanical, electrical, electromagnetic, pneumatic, hydraulic and/or other devices/techniques described herein. In some embodiments, the ballast may be moved or located in or toward a centralized position in the AAV to enable more agile control of the AAV. The ballast may be moved outward from the centralized location of the AAV to enable more stable control of the AAV. | ||||||
| 5 | Attitude control of an aircraft in a ditching condition | US13921012 | 2013-06-18 | US09248913B2 | 2016-02-02 | Kelly L. Boren; Sergey D. Barmichev |
| Configurations provide rapid adjustment to an aircraft attitude in the water upon an emergency water landing. In one configuration, an aircraft fuselage has a forward compartment that includes a water intake and an air vent. The water intake is located below an expected waterline upon ditching the aircraft in water and transports a flow of water to the forward compartment at a designed flow rate. The air vent is positioned at a height in the forward compartment and allows a desired volume of water to fill the forward compartment and adjust an attitude of the aircraft within a time period. | ||||||
| 6 | ATTITUDE CONTROL OF AN AIRCRAFT IN A DITCHING CONDITION | US13921012 | 2013-06-18 | US20140367520A1 | 2014-12-18 | Kelly L. Boren; Sergey D. Barmichev |
| Configurations provide rapid adjustment to an aircraft attitude in the water upon an emergency water landing. In one configuration, an aircraft fuselage has a forward compartment that includes a water intake and an air vent. The water intake is located below an expected waterline upon ditching the aircraft in water and transports a flow of water to the forward compartment at a designed flow rate. The air vent is positioned at a height in the forward compartment and allows a desired volume of water to fill the forward compartment and adjust an attitude of the aircraft within a time period. | ||||||
| 7 | Emergency balancing means | US12656837 | 1937-02-19 | US2117234A | 1938-05-10 | AUSTIN JONATHAN R; BERLIN DONOVAN R |
| 8 | MODULAR AIRCRAFT ASSEMBLY FOR AIRBORNE AND GROUND TRANSPORT | US16052938 | 2018-08-02 | US20180354617A1 | 2018-12-13 | SERGEY V. FROLOV; MICHAEL CYRUS; JOHN PETER MOUSSOURIS |
| An aircraft for vertical take-off and landing includes an aircraft frame having an open frame portion, at least one vertical thruster, a pod, separable from the aircraft and including a cabin to contain at least one of cargo and passengers, where the pod, when mounted to the aircraft, defines at least a portion of the aircraft frame, and a mounting system including at least one attachment member configured to attach the pod to the open frame portion. Such aircraft is capable of flight with and without the pod. | ||||||
| 9 | Fluid-based orientation control system | US14058486 | 2013-10-21 | US08965674B1 | 2015-02-24 | Stephen D. Russell |
| A system includes a fluid reservoir containing a first fluid, a pair of fluidic channels in fluidic connection with the fluid reservoir, a counter-fluid reservoir having a second fluid that is non-miscible with the first fluid, and a pump connected to the fluid reservoir. The pump is configured to pump the first fluid from the fluid reservoir into the pair of fluidic channels. When contained in a vehicle, the system allows for control of the vehicle's orientation. The system may use sensor input to determine when to actuate the pump. Each fluidic channel may have a cross-section that varies along its length. The fluidic channels may be geometrically symmetric about the fluid reservoir. The system may be incorporated into a vehicle to control the vehicle's orientation. | ||||||
| 10 | METHODS FOR FUEL-EFFICIENT TRANSPORTATION OF CARGO BY AIRCRAFT | US11935328 | 2007-11-05 | US20090114773A1 | 2009-05-07 | Elie Helou, JR. |
| A fuel-efficient method for transporting cargo to a desired location via an aircraft. The method comprises determining the weight of the cargo capable of being transported in a single container, selecting a container having a sufficient weight capacity to support the cargo based on the determined weight of the cargo, and filling the selected container with the cargo. The filled container is loaded onto a location on the aircraft beam relative to the aircraft's CG based on the weight of the filled container to stay within the acceptable CG range for the aircraft. The filled containers having the greater weight are positioned on the beam at or adjacent to the aircraft's CG and the filled containers having lower weight are positioned farther from the aircraft's CG. The containers provide strength and rigidity to the beam to sustain the bending and torsional loads in flight. | ||||||
| 11 | Passive step trimmer for a maneuvering re-entry body (U) | US22125 | 1979-02-12 | US4784350A | 1988-11-15 | Ralph M. Darden |
| A passive step trimmer for a maneuvering re-entry body (MRB) which uses existing inertial forces acting on the MRB to deploy a free flowing mass from the rear of the MRB to trim the MRB altitude. The mass deployment from the MRB causes a forward shift in the center of gravity (CG) which in turn creates a more stable body which flies at a reduced angle-of-attack (.alpha.). | ||||||
| 12 | Attitude control of an aircraft in a ditching condition | EP14165640.5 | 2014-04-23 | EP2815962B1 | 2017-06-07 | Boren, Kelly L.; Barmichev, Sergey D. |
| 13 | METHODS FOR FUEL-EFFICIENT TRANSPORTATION OF CARGO BY AIRCRAFT | EP08848221 | 2008-10-07 | EP2205484A4 | 2011-11-16 | HELOU ELIE JR |
| 14 | 공중차 | KR1020150027824 | 2015-02-27 | KR1020160104925A | 2016-09-06 | 박영식 |
| 본발명은고층건물에서비상상황발생시공중차를현장근방에서로켓발사체로이륙시켜공중부양하여구조활동을할 수있는공중차에관한것이며, 이와같은공중차는, 차체(100)와, 차체(100)에구비된앞범퍼(110)의양측에각각설치되어, 운전자의제어에따라차체(100)를일측방향으로소정각도범위내에서경사지도록만든상태에서차체(100)를상기경사각방향으로발사하는제1 및제2 발사추진부(200a,200b)와, 차체(100)의전방좌측, 전방우측, 후방좌측, 후방우측에설치되며, 운전자의제어에따라액체질소의온도를조절하여차체(100)의상승, 하강, 회전동작을선택적으로제어하는제1 내지제4 공중부양회전부(300:300a,300b,300c,300d)와, 차체(100)의내부에설치되며, 운전자의제어에따라차체(100)의이륙, 착륙, 상승, 하강, 우회전, 좌회전의동작을선택적으로제어하는방향조절부(400)와, 차체(100)의내부에설치되어, 운전자의제어에따라차체(100) 중량의압력에의해발생된압축공기를이용하여지면에서의차량(100)을주행하도록제어하는운전제어부(500)로구성된다. | ||||||
| 15 | 탈 수 있는 로봇새 | KR1020140117337 | 2014-09-03 | KR1020160028324A | 2016-03-11 | 이정용 |
| 본발명은로봇새의원리와구조를그대로적용하되크기를사람이탈 수있는정도의크기로크게만들고그 큰로봇새의프레임내에공기주머니를형성하고그 공기주머니내에헬륨이나수소개스를채우는것이다. | ||||||
| 16 | VERTICAL TAKE OFF AND LANDING CLOSED WING AIRCRAFT | EP17170907.4 | 2017-05-12 | EP3243747A1 | 2017-11-15 | FENNY, Carlos Alexander; OLSON, Rohn Lee; ZAHASKY, Andrew James |
VERTICAL TAKE OFF AND LANDING CLOSED WING AIRCRAFT An aircraft (100) capable of vertical takeoff and landing, stationary flight and forward flight includes a closed wing (102) that provides lift whenever the aircraft (100) is in forward flight, a fuselage (104) at least partially disposed within a perimeter of the closed wing (102), and one or more spokes (106) coupling the closed wing (102) to the fuselage (104). The fuselage (104) can have a rear module substantially disposed within a perimeter of the distributed airframe (1002, Figure 11), and a front module removably connected to the rear module and substantially aligned with the longitudinal axis. One or more engines or motors (132) are disposed within or attached to the closed wing (102), fuselage (104) or spokes (106). Three or more propellers (120) are proximate to a leading edge of the closed wing (102) or the one or more spokes (106), distributed along the closed wing (102) or the one or more spokes (106), and operably connected to the one or more engines or motors (132). The propellers (120) provide lift whenever the aircraft (100) is in vertical takeoff and landing and stationary flight, and provide thrust whenever the aircraft (100) is in forward flight.
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| 17 | Attitude control of an aircraft in a ditching condition | EP14165640.5 | 2014-04-23 | EP2815962A1 | 2014-12-24 | Boren, Kelly L.; Barmichev, Sergey D. |
Configurations provide rapid adjustment to an aircraft attitude in the water upon an emergency water landing. In one configuration, an aircraft fuselage (202; 402) has a forward compartment (204; 404) that includes a water intake (206; 406) and an air vent (208; 410). The water intake (206; 406) is located below an expected waterline (102) upon ditching the aircraft (100) in water and transports a flow of water to the forward compartment (204; 404) at a designed flow rate. The air vent (208; 410) is positioned at a height in the forward compartment (204; 404) and allows a desired volume of water to fill the forward compartment (204; 404) and adjust an attitude of the aircraft (100) within a time period. (Fig. 2)
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| 18 | METHODS FOR FUEL-EFFICIENT TRANSPORTATION OF CARGO BY AIRCRAFT | EP08848221.1 | 2008-10-07 | EP2205484B1 | 2013-01-09 | Helou, Elie Jr. |
| 19 | METHODS FOR FUEL-EFFICIENT TRANSPORTATION OF CARGO BY AIRCRAFT | EP08848221.1 | 2008-10-07 | EP2205484A2 | 2010-07-14 | Helou, Elie Jr. |
| A fuel-efficient method for transporting cargo to a desired location via an aircraft. The method comprises determining the weight of the cargo capable of being transported in a single container, selecting a container having a sufficient weight capacity to support the cargo based on the determined weight of the cargo, and filing the selected container with the cargo. The filled container is loaded onto a location on the aircraft beam relative to the aircraft's CG based on the weight of the filled container to stay within the acceptable CG range for the aircraft. The filled containers having the greater weight are positioned on the beam at or adjacent to the aircraft's CG and the filled containers having lower weight are positioned farther from the aircraft's CG. The containers provide strength and rigidity to the beam to sustain the bending and torsional loads in flight. | ||||||
| 20 | 압축공기 추진식 비행체. | KR1020170101655 | 2017-08-10 | KR101839130B1 | 2018-04-27 | 유재원 |
| 본발명은압축공기추진식비행체에관한것으로서, 보다상세하게는공중또는수중에서이동하는물체즉, 비행체를구성함에있어터빈또는프로펠러의구성대신압축탱크와압축공기를이용하여상기압축공기를일정압력으로제어하며상기비행체의수직방향과수평방향으로다방향분사하여상기비행체의비행방향과비행속도를결정하는것을특징으로하는압축공기추진식비행체에관한것이다. 본발명은터빈또는프로펠러없이비행체를부양하고이를제어하여공중또는수중에서이동시킬수 있어, 소음과안전사고의염려가극히줄어들며, 오염물질의배출이없고, 비행체의이동방향을전방위로상기변경하여효율적인비행을운용할수 있는효과가있다. 또한, 본발명은프로펠러없이압축공기로채워지는에어탱크와에어노즐을구비하여형성된구조이기때문에, 압축공기의충전이간편하며, 터빈과프로펠러등의사용이없어이산화탄소및 질소등의오염물질의배출이없고, 정제후 압축기술이요구되는수소또는연료를사용하지않고, 일반공기의압축공정을통한압축에어를수용하는에어탱크를구비함으로써수소또는연료의순간적인연소로인한 2차폭발위험이종래기술에비해절감되며, 비행체의유지보수등 관리가용이하고고장발생시모듈구성을포함하는비행체의특성상수리하기가편리한효과가있다. | ||||||
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