子分类：
- B64C27/001： .{减振装置}
- B64C27/006： .{保护装置}
- B64C27/008： .{旋翼跟踪或平衡装置}
- B64C27/02： .旋翼飞机
- B64C27/04： .直升飞机
- B64C27/20： .以具有带罩旋翼,例如飞行平台为特点的旋翼机
- B64C27/22： .混合式旋翼机,即飞行中利用飞机和旋翼机两者特征的飞行器
- B64C27/32： .旋翼(旋翼和螺旋桨共有的特征入B64C11/00)
- B64C27/51： .{叶片运动的减震}
- B64C27/52： .整个旋翼相对机身的倾斜(翘翘板型结构入B64C27/43)
- B64C27/54： .用于控制叶片相对于旋翼毂的调节或运动,例如滞后提前运动的机构
- B64C27/82： .以装有用于平衡升力旋翼扭矩或改变旋翼机方向的辅助旋翼或流体喷射装置为特点的
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 141 | Aircraft with counterrotating members | US244570 | 1981-03-17 | US4386748A | 1983-06-07 | Heinz Jordan |
| A rotationally symmetrical supporting member provides lift in response to movement of air over its upper surface, and such air movement is produced by the impeller of a coaxially arranged drive unit, the base of which is connected to the supporting member so that counter torque from the drive unit imparts rotational movement to the supporting member. A carrier which may hold a load or supporting steering flaps is rotatably mounted in relation to the supporting member and to the driving unit. | ||||||
| 142 | Helicopter with stabilator detuned in antisymmetric vibration modes from main rotor wake excitation frequency | US923834 | 1978-07-12 | US4247061A | 1981-01-27 | William A. Kuczynski; John Marshall, II, deceased |
| A helicopter stabilator having naturally high response to the main rotor wake excitation frequency in roll and yaw stabilator vibratory modes is selectively mounted so as to be detuned therefrom in antisymmetric stabilator vibratory modes without adversely affecting symmetric stabilator vibratory modes, stabilator vertical stiffness, or stabilator pitch stiffness. | ||||||
| 143 | Rotary wing aircraft | US941802 | 1978-09-11 | US4208025A | 1980-06-17 | Raymond Jefferson |
| An aircraft rotary wing aerofoil assembly comprising a generally planar annular frame supporting radially inner and outer sets of aerofoil blades, each set being disposed to form an annulus and supported on the frame for rotation about a common axis, and first and second sets of panels are mounted on the frame for movement to shroud portions of the inner and outer sets of aerofoil blades respectively. | ||||||
| 144 | Helicopter muffler system | US45646374 | 1974-04-01 | US3905564A | 1975-09-16 | FURLANO ROLAND V |
| This invention relates to a system for providing a single muffler for helicopters which normally require two mufflers, comprising a Y shaped tubing adapted to receive the exhaust from each of the existing exhaust tailpipes and combining the exhaust into a single entry into a centrally mounted muffler system.
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| 145 | Helicopter step and cargo carrier assembly | US46929174 | 1974-05-13 | US3904155A | 1975-09-09 | CHAVIS GENE |
| A helicopter step and cargo assembly comprising a tubular frame adapted to be connected directly to the skid tube supports or other undercarriage of a helicopter which provides an elongated horizontal surface of substantial length, having an offset portion extending between the supports. The tubular frame is designed to allow maximum load carrying area with a minimum drag on the aircraft. The tubular frame includes side rails for securing cargo with the outboard side rail being hinged or swingably attached to the frame so as to be swung downwardly when the frame is used as a step for boarding or leaving the helicopter.
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| 146 | Helicopter lighting | US3723722D | 1970-09-14 | US3723722A | 1973-03-27 | VAN IDERSTINE T; BONNELL L |
| Relatively rotatable elements coupled for light transmission by fiber optic devices analogous to electrical commutators. A rotary wing aircraft embodiment employing fiber optics in the rotor blade for navigational lights has a flexible light pipe extension from the blade with an end fixed to move with the driving assembly in a set circular path, to sweep by and pick up light from a light source on the body. Other portions of the extension flex to follow cyclic pivoting of the blade relative to its driving assembly. Fibers in the blade are arranged to bend with the blade during operation by use of a flexible light pipe within which the fibers adjust relative to one another during blade bending. Heat-curing of plastic about a heat resistant flexible light pipe and bonding the fibers directly into the blade matrix as bendable strength element using a thin, wide and long ribbon of optical fibers are shown. Light sources on the body of the aircraft are shown as fiber light pipes with ends fixed to be swept by the pickup pipes. Four source light pipes provide light in accordance with navigational rules, a rotor blade receiving alternately white, green, white, red light as it rotates through various sectors. A Maxwellian lens at the end of a source light pipe defines an extended lighted arc along the pickup path, to provide extended duration of light transmission in each sector, the lens also enabling variation in the physical position of the blade assembly as occurs in the field.
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| 147 | Propulsive means for vertical rising aircraft | US13102849 | 1949-12-03 | US2610005A | 1952-09-09 | PRICE NATHAN C |
| 148 | Aeroplane wing construction | US48887630 | 1930-10-15 | US1822179A | 1931-09-08 | THOMAS ARTHUR E C |
| 149 | Helicopter | US19213127 | 1927-05-17 | US1668052A | 1928-05-01 | CLAUD DAVIS |
| 150 | Aircraft | US61704723 | 1923-02-05 | US1497789A | 1924-06-17 | MARTIN PEARSON |
| 151 | Flying-machine | US41552620 | 1920-10-08 | US1388642A | 1921-08-23 | WENZEL HAUPT |
| 152 | Flying-machine | US25496518 | 1918-09-20 | US1372498A | 1921-03-22 | PETTER FROVARP OLE |
| 153 | 无人飞行器的桨叶保护装置及无人机系统 | CN201720566645.0 | 2017-05-19 | CN206954500U | 2018-02-02 | 张蕾; 唐尹; 金时润 |
| 本实用新型公开了一种无人飞行器的桨叶保护装置及无人机系统。桨叶保护装置包括第一桨叶保护罩组件、第二桨叶保护罩组件以及锁扣组件，其中第一桨叶保护罩组件和第二桨叶保护罩组件设置于无人飞行器的相对两侧，且分别与无人飞行器的机臂卡合，锁扣组件用于锁定第一桨叶保护罩组件与第二桨叶保护罩组件，以保持第一桨叶保护罩组件及第二桨叶保护罩组件与无人飞行器的卡合状态。因此，本实用新型增强了桨叶保护罩组件的稳定性，从而提高了桨叶保护罩组件的抗冲击性能。 | ||||||
| 154 | AUTOMATED LANDING SOLUTION SYSTEMS AND METHODS | US15621992 | 2017-06-13 | US20180357910A1 | 2018-12-13 | RONALD HOBBS; JAMES LUECKE |
| A UAV landing system can include a landing pad defining a landing area including a target point; a plurality of positioning radio transmitters positioned in a spaced apart relation and equidistant from the target point, each radio transmitter transmitting a ranging signal; and a position determination and aircraft navigation system at the incoming UAV to receive the ranging signals; determine a range to each positioning radio using the received ranging signals; compute a position of the UAV relative to the target point; determine a course for the UAV to a point above the target point of the landing pad; fly the UAV to the point above the target point of the landing pad, and cause the aircraft to descend vertically toward the target point when the UAV reaches the point above the target point. | ||||||
| 155 | Power safety instrument system | US15608696 | 2017-05-30 | US10145708B2 | 2018-12-04 | James M. McCollough; Erik Oltheten; Nicholas Lappos |
| A power safety system is configured to provide power information in an aircraft. The power safety system includes a power safety instrument having a power required indicator and a power available indicator, each being located on a display. A position of the power required indicator and the power available indicator represent the power available and power required to perform a hover flight maneuver. The power safety system may be operated in a flight planning mode or in a current flight mode. The power safety system uses at least one sensor to measure variables having an effect on the power required and the power available. | ||||||
| 156 | Seat Assembly Using J-Track Seats | US15484724 | 2017-04-11 | US20180290751A1 | 2018-10-11 | Joshua Andrew Emrich; Guillaume Noiseux Boucher |
| The present invention includes a movable seat assembly for a vehicle, comprising: first and second predetermined paths located on the floor of the vehicle, each path having an operational location at a first end and an ingress/egress location at a second end, the paths having a substantially straight portion and a curved portion; a seat slidably connected to the paths and capable of translation between the first and the second position; two or more openings on the floor of the vehicle on or about the first and second predetermined paths that provide a locking position for the seat, wherein the two or more opening are connected via a conduit below the surface of the floor; and at least one locking pin/plunger connected to the seat and capable of engaging the two or more openings to lock the seat in place along the first and second predetermined paths. | ||||||
| 157 | UNMANNED AERIAL VEHICLE AND OPERATIONS THEREOF | US15947650 | 2018-04-06 | US20180229834A1 | 2018-08-16 | Tao Wang; Tao Zhao; Shaojie Chen; Zhigang Ou |
| The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors. | ||||||
| 158 | Exploiting or avoiding air drag for an aerial vehicle | US14991846 | 2016-01-08 | US10012999B2 | 2018-07-03 | Ranveer Chandra; Ashish Kapoor; Jongho Won |
| Methods and apparatus for avoiding or exploiting air drag on an aerial vehicle are disclosed. In embodiments, the methods and apparatus may be implemented in a controller and used to increase the energy efficiency of an aerial vehicle. In the embodiments, at least one parameter associated with a force on an aerial vehicle is determined. A yaw setting for the aerial vehicle is then determined that exploits or avoids air drag on the aerial vehicle for energy efficiency. The yaw setting may be referenced to a yaw based on directionality in the shape of the aerial vehicle. In other embodiments, a drag associated with a force on an aerial vehicle is determined. It is then determined if there is a selected component in the drag based on a desired maneuver of the aerial vehicle. A yaw setting is then determined based on whether the selected component is in the drag. | ||||||
| 159 | ROTORCRAFT FALL RESTRAINT PROTECTION ATTACH POINTS AND MECHANISM SYSTEMS | US15343678 | 2016-11-04 | US20180126199A1 | 2018-05-10 | Bob Thornton; Chyau Tzeng; Brian Mesing; Kevin Knott; Mark Wiinikka; Edith Richard; David Platz; Joshua Edler; Sarah Villanueva; Thomas Mast; Joseph Leachman; Daniel John Burns |
| The present invention includes a safety apparatus and method for protecting users during maintenance operations for a rotorcraft comprising: at least one permanent, semi-permanent, or detachable safety bar, strap, fastener, hook, or loop that is attached or attachable to a rotorcraft, wherein the safety bar, strap, fastener, hook, or loop is positioned in an area or surface between a windshield of the rotorcraft and a tail boom of the rotorcraft and is connectable to a user safety device to provide fall protection from the area or surface. | ||||||
| 160 | Adjustable unmanned aerial vehicles with multiple lifting motors and propellers | US15592948 | 2017-05-11 | US09908632B1 | 2018-03-06 | Gur Kimchi; Daniel Buchmueller; Brian C. Beckman; Amir Navot |
| This disclosure describes an unmanned aerial vehicle that may be configured during flight to optimize for agility or efficiency. | ||||||
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