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 |
|---|---|---|---|---|---|---|
| 161 | Debris detector for non-ferrous bearings | US13863126 | 2013-04-15 | US09879824B2 | 2018-01-30 | James M. McCollough; Ryan T. Ehinger; Troy Bunch |
| A system and method to detect non-ferrous debris from a non-ferrous roller bearing element. The system includes a trap in fluid communication with a lubrication fluid of the non-ferrous bearing and a sensor operably associate with the trap. The method includes trapping the non-ferrous material debris in the lubrication fluid with the trap and triggering the sensor upon detection of the non-ferrous material debris trapped within the trap. | ||||||
| 162 | Redundant component and intelligent computerized control system for multi-rotor VTOL aircraft | US14835567 | 2015-08-25 | US09828107B1 | 2017-11-28 | Arnold Peter Ruymgaart; Lydia Tapia; Aleksandra Faust; Rafael Fierro |
| The present invention provides a vehicle with redundant systems to increase the overall safety of the vehicle. In other aspects, the present invention provides a method for learning control of non-linear motion systems through combined learning of state value and action-value functions. | ||||||
| 163 | Hybrid composite-metal shaft | US14662406 | 2015-03-19 | US09821520B2 | 2017-11-21 | Phillip A. Kendrick |
| A method for making a composite-metal hybrid shaft for a rotorcraft includes providing a tubular metal member that has an internal surface defining a space therein, preparing a composite member using a curing tool, curing the composite member, creating a cured composite member, expanding the metal member with heat, placing the cured composite member into the space defined by the internal surface of the expanded metal member, and allowing the expanded metal member to cool. | ||||||
| 164 | Supervisory control of an unmanned aerial vehicle | US14587091 | 2014-12-31 | US09817396B1 | 2017-11-14 | Leila Takayama; Brandon Alexander; Roger William Graves; Justin Sadowski; Abraham Bachrach |
| An unmanned aerial vehicle (UAV) is disclosed that may allow for supervisory control interaction by a remote operator to assist with navigation to a target location. The UAV may navigate to a target area and capture and send an image of the target area to the remote operator. The remote operator can then provide a user input that indicates a target location within the target area. Upon receiving an indication of the target area, the UAV can then autonomously navigate to the target location. In some examples, after reaching the target location, the UAV may initiate delivery of a payload at the target location using a retractable delivery system while the UAV hovers above. | ||||||
| 165 | Power Safety Instrument System | US15608696 | 2017-05-30 | US20170307401A1 | 2017-10-26 | 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. | ||||||
| 166 | Tapered Sockets for Aircraft Engine Mount Assemblies | US15410036 | 2017-01-19 | US20170217598A1 | 2017-08-03 | Bruce Bennett Bacon; John Elton Brunken, Jr.; Tyler Wayne Baldwin |
| An engine mount assembly for coupling an engine to an airframe. The engine mount assembly includes a torsion bar coupled between the engine and the airframe. The torsion bar has upper and lower tapered bosses. Upper and lower arm assemblies couple the engine to the torsion bar. Each arm assembly has an end bell crank with a tapered socket that is adapted to receive a respective tapered boss therein to secure the end bell cranks to the torsion bar such that the end bell cranks rotate with the torsion bar responsive to movements of the engine. | ||||||
| 167 | Beam Springs for Aircraft Engine Mount Assemblies | US15410015 | 2017-01-19 | US20170217597A1 | 2017-08-03 | Bruce Bennett Bacon; John Elton Brunken, JR.; Michael Edwin Rinehart; Nick Pravanh |
| An engine mount assembly for coupling an engine to an airframe. The engine mount assembly includes a torsion bar coupled to the engine and a lateral movement control assembly coupled between the torsion bar and the airframe. The lateral movement control assembly includes a spring having a lateral stiffness. The torsion bar rotates in response to lateral movement of the engine such that the lateral movement of the engine is controllable based on the lateral stiffness of the spring. | ||||||
| 168 | Launching unmanned aerial copter from mid-air | US15053592 | 2016-02-25 | US09612599B2 | 2017-04-04 | Henry W. Bradlow; Antoine Balaresque |
| An unmanned aerial vehicle (UAV) copter for consumer photography or videography can be launched by a user throwing the UAV copter into mid-air. The UAV copter can detect that the UAV copter has been thrown upward while propeller drivers of the UAV copter are inert. In response to detecting that the UAV copter has been thrown upward, the UAV copter can compute power adjustments for propeller drivers of the UAV copter to have the UAV copter reach a predetermined elevation above an operator device. The UAV copter can then supply power to the propeller drivers in accordance with the computed power adjustments. | ||||||
| 169 | SYSTEM AND METHOD FOR DETECTING AND ALERTING THE USER OF AN AIRCRAFT OF AN IMPENDENT ADVERSE CONDITION | US14798459 | 2015-07-14 | US20170015434A1 | 2017-01-19 | David Edward MCKAY |
| A method detects an impendent situation of an operating aircraft. The method comprises receiving data corresponding to a plurality of parameters related to an operation of the aircraft. It is determined if any of the plurality of parameters is at or beyond at least a first respective threshold by comparing the plurality of parameters with the first respective thresholds. If at least one of the parameters is an outlier parameter at or beyond its first respective threshold, another or others of the plurality of parameters associated to the at least one outlier parameter is identified, the at least one other parameter being selected based on a predetermined combination of parameters representative of an adverse condition. The associated parameters are compared with a stored data combination threshold specific to the associated parameters. A signal indicative of an impending situation is output if the associated parameters are on or beyond the data combination threshold. A system and an aircraft detecting an impendent situation are also provided. | ||||||
| 170 | WIDE AREA SENSING SYSTEM, IN-FLIGHT DETECTION METHOD, AND NON-TRANSITORY COMPUTER READABLE MEDIUM STORING PROGRAM OF WIDE AREA SENSING SYSTEM | US14859974 | 2015-09-21 | US20170003690A1 | 2017-01-05 | Atsushi Tanahashi |
| A wide area sensor system includes an unmanned airplane being switchable between an airplane mode for high speed flight and a VTOL mode for low speed flight, a state detection sensor provided in the unmanned airplane, the state detection sensor being driven to detect a state of a detection target, and an external control apparatus that controls flight of the unmanned airplane and driving of the state detection sensor. The external control apparatus performs high speed sensing by driving the state detection sensor while performing the high speed flight of the unmanned airplane in the airplane mode. The control apparatus performs low speed sensing by driving the state detection sensor while performing the low speed flight of the unmanned airplane in the VTOL mode. | ||||||
| 171 | CONTROL AND STABILIZATION OF A FLIGHT VEHICLE FROM A DETECTED PERTURBATION BY TILT AND ROTATION | US15091566 | 2016-04-05 | US20160291598A1 | 2016-10-06 | THOMAS A. YOUMANS |
| A flight vehicle control and stabilization process detects and measures an orientation of a non-fixed portion relative to a fixed frame or portion of a flight vehicle, following a perturbation in the non-fixed portion from one or both of tilt and rotation thereof. A pilot or rider tilts or rotates the non-fixed portion, or both, to intentionally adjust the orientation and effect a change in the flight vehicle's direction. The flight vehicle control and stabilization process calculates a directional adjustment of the rest of the flight vehicle from this perturbation and induces the fixed portion to re-orient itself with the non-fixed portion to effect control and stability of the flight vehicle. The flight vehicle control and stabilization process also detects changes in speed and altitude, and includes stabilization components to adjust flight vehicle operation from unintentional payload movement on the non-fixed portion. | ||||||
| 172 | POWER SAFETY INSTRUMENT SYSTEM | US15168356 | 2016-05-31 | US20160272342A1 | 2016-09-22 | 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. | ||||||
| 173 | BUBBLE COLLECTOR FOR SUCTION FUEL SYSTEM | US14098587 | 2013-12-06 | US20160252051A1 | 2016-09-01 | David R. Smith; Daniel John Shields |
| A fuel feed system for a rotary-winged aircraft includes a fuel feed line extending from a fuel source to an engine and an engine fuel suction pump disposed at the fuel feed line to urge a flow of fuel through the fuel feed line to the engine. A collector is located along the fuel feed line between the fuel source and the engine to collect air-vapor bubbles which form in the flow of fuel. An air-vapor line extends from the top of the collector and merges with the fuel line section between the collector and the engine fuel pump. The air-vapor line is sized and configured to limit the flow of air-vapor from the collector to the engine fuel suction pump to a rate which the engine fuel suction pump can tolerate. | ||||||
| 174 | Rotorcraft control laws for sea-based operations | US14245036 | 2014-04-04 | US09429952B2 | 2016-08-30 | Derek Geiger; James Rigsby; Aaron L. Greenfield; Vineet Sahasrabudhe; Jennifer D. Goss |
| A method and system of controlling a rotorcraft for sea-based operations includes receiving sensed information indicative of an operation of the rotorcraft; receiving operator commands, ship models and system constraints; and determining a solution to an optimization function that avoids violating the system constraints, the solution being representative of control command signals for augmenting a flight response of the rotorcraft to a ship. | ||||||
| 175 | VARIABLE SPEED AIRCRAFT TRANSMISSION | US14683218 | 2015-04-10 | US20160076629A1 | 2016-03-17 | Brian Stanley Modrzejewski; Russell Mueller; Doug Mueller; Ron Woods; Tim Cecil |
| A variable state planetary shifting transmission can include an input shaft, an output shaft; and a planetary system having a sun gear associated with the input shaft, a planetary carrier, and a ring gear associated with a ring housing. The transmission can include an overrunning clutch operably coupled to the planetary carrier. The transmission can include a clutch assembly coupled to the planetary carrier. The transmission is capable of changing the speed ratio between the input shaft and the output shaft by selective engagement of the clutch assembly against the ring gear which can cause either the freeing or locking of the planetary carrier by the overrunning clutch. | ||||||
| 176 | Dry lubricated linear actuator for in blade rotor control | US13599843 | 2012-08-30 | US09278756B2 | 2016-03-08 | Paul R. Brewer; Reg R. Raval; Suat Bekircan |
| A rotor blade assembly includes a rotor blade and a rotatable flap portion located along a span of the rotor blade. A linear actuator located inside the rotor blade is operably connected to the flap portion to rotate the flap portion about a flap axis and is absent oil, grease or other fluid lubricant. A rotary-winged aircraft includes an airframe and a main rotor assembly operably connected to the airframe. The main rotor assembly includes a plurality of rotor blade assemblies rotatable about a rotor assembly axis. At least one rotor blade assembly of the plurality of rotor blade assemblies includes a rotor blade and a rotatable flap portion located along a span of the rotor blade. A linear actuator positioned inside the rotor blade is operably connected to the flap portion to rotate the flap portion about a flap axis and is absent oil, grease or other fluid lubricant. | ||||||
| 177 | Rotorcraft, dynamic, CG management apparatus and method | US13623778 | 2012-09-20 | US09205913B2 | 2015-12-08 | Jacob J. van der Westhuizen |
| An aircraft is disclosed having an engine and a propeller mounted to a fuselage. An empennage mounts to the aircraft and includes first and second horizontal stabilizers separated by a distance greater than the diameter of a stream tube of the propeller at the horizontal stabilizers. A rudder extends between the horizontal stabilizers and is positioned within the stream tube of the propeller. A bulkhead is positioned rearward from the cockpit and oriented perpendicular to a longitudinal axis of the airframe. A tailboom and engine are mounted to the airframe by means of the bulkhead having the engine mounted between the tailboom and a lower edge of the bulkhead. Landing gear may mount to the bulkhead proximate a lower edge thereof. Systems and methods redistribute fuel among laterally, vertically, and longitudinally opposed fuel tanks to maintain a center of gravity in a dynamically stable position. | ||||||
| 178 | Power Safety Instrument System | US14715236 | 2015-05-18 | US20150321769A1 | 2015-11-12 | 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. | ||||||
| 179 | ASSISTED TAKEOFF | US14257955 | 2014-04-21 | US20150274309A1 | 2015-10-01 | Jun Shi; Xu Yang Pan |
| Systems, methods, and devices are provided for assisted takeoff of an aerial vehicle. The aerial vehicle may takeoff using a first control scheme and switch to a second control scheme for normal flight when a takeoff threshold is met. The first control scheme optionally does not use integral control while the second control scheme may use integral control. The aerial vehicle may determine that a takeoff threshold is met, based on an output to a motor of the aerial vehicle and/or an acceleration of the aerial vehicle. | ||||||
| 180 | Power safety instrument system | US13641325 | 2010-12-22 | US09035802B2 | 2015-05-19 | 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. | ||||||
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