| 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 | SELF-CONTAINED AERIAL CARGO VEHICLE | US15365414 | 2016-11-30 | US20180148168A1 | 2018-05-31 | Daniel I. Newman |
| An aerial vehicle includes one or more rotors and a cargo container. The one or more rotors are configured to propel the aerial vehicle. The cargo container defines a cargo volume and is configured to travel with the aerial vehicle during propulsion by the one or more rotors. The cargo container is further configured to contain, at least, the one or more rotors, when the aerial vehicle is not configured for moving cargo. | ||||||
| 142 | Multi-Configuration Autonomous Platform With Mounted Camera | US15386344 | 2016-12-21 | US20170259914A1 | 2017-09-14 | JoeBen Bevirt; Andy Clark |
| A system for video imaging and photographing using an autonomous aerial platform. The system may be a quad rotor system using electrically powered propellers. The aerial platform may be commanded by the user to follow an object of interest. The aerial platform may have multiple configurations for its thrust units such that they are clear of the field of view of the imaging device in a first configuration, such that they protect the imaging device during landing in a second configuration, and that allows for efficient storage in a stowed configuration. | ||||||
| 143 | STOWABLE UNMANNED AERIAL VEHICLES AND ASSOCIATED SYSTEMS AND METHODS | US15268225 | 2016-09-16 | US20170225782A1 | 2017-08-10 | Christoph Kohstall; Jelena Jovanovic; Dylan Owens; Nathan Leefer; Ben Sampson |
| Stowable and deployable unmanned aerial vehicles (UAVs), and associated systems and methods are disclosed. A UAV in accordance with a particular embodiment includes a main body, frames carried by the main body, and motors carried by the frames. At least two frames are positioned to move relative to each other between a stowed configuration in which the frames are generally aligned proximate to each other and a deployed configuration different from the stowed configuration. The main body can include a first body portion pivotably connected to a second body portion. In a stowed configuration, the body portions can generally overlap each other. A UAV in accordance with particular embodiments includes a modular electronics unit carried by the UAV and including a camera, a battery, and a vehicle controller. Modular electronics units can be configured to be removably connected to and disconnected from the UAV and other vehicles. | ||||||
| 144 | SPHERICAL VTOL AERIAL VEHICLE | US15129555 | 2015-03-27 | US20170210468A1 | 2017-07-27 | JAMEY D. JACOB; WENG KHEONG LOH |
| An embodiment of the present disclosure relates to an unmanned flying robotic object that contains a wheeled mechanism that encircles its spherical exoskeleton. This feature allows the flying spherical vehicle to readily transform into a ground maneuverable vehicle. A robotic motor with differential speed capability is used to operate each wheel to provide effective ground maneuverability. There are examples provided herein of wheel configurations suitable for use with an embodiment. One is the straight-(or parallel) wheel design, and another is tilted-wheel design as are illustrated and discussed hereinafter. One embodiment of an unmanned flying robotic object taught herein is foldable. | ||||||
| 145 | IN-FLIGHT RECONFIGURABLE AIRCRAFT TAIL | US14717778 | 2015-05-20 | US20170190412A1 | 2017-07-06 | Colin Kemater Bunting; Michael Peter Strauss |
| A system and method for a reconfigurable aircraft having a fuselage with one or more propellers, at least one tail assembly, a processor, and a memory having instructions stored thereon that, when executed by the processor, cause the system to: determine a safety clearance for the at least one tail assembly; and selectively move the at least one tail assembly upon a determination that the safety clearance is achieved. | ||||||
| 146 | AERIAL VEHICLE | US15379554 | 2016-12-15 | US20170174336A1 | 2017-06-22 | Hiroyasu BABA; Koji KAWASAKI; Takenori MATSUE |
| An aerial vehicle is provided which includes first thrusters with first propellers and second thrusters with second propellers. Each of the first propellers has a first rotating region in which blades thereof rotate. Similarly, each of the second propellers has a second rotating region in which blades thereof rotate. Each of the first rotating regions is located to overlap one of the second rotating regions, as viewed in a direction of a yaw axis of the aerial vehicle. The first rotating regions are located away from the second rotating regions in the direction of the yaw axis. Such layout of the first and second propellers eliminates physical interference therebetween. The overlap between the first and second propellers results in a decreased cross-sectional area of projection of the aerial vehicle from the front view in a flight direction thereof. | ||||||
| 147 | MULTICOPTER-ASSISTED SYSTEM AND METHOD FOR LAUNCHING AND RETRIEVING A FIXED-WING AIRCRAFT | US15434735 | 2017-02-16 | US20170158319A1 | 2017-06-08 | Andreas H. von Flotow; Corydon C. Roeseler; Caleb Andrew Woodruff; Daniel Pepin Reiss |
| The present disclosure provides various embodiments of a multicopter-assisted launch and retrieval system generally including: (1) a multi-rotor modular multicopter attachable to (and detachable from) a fixed-wing aircraft to facilitate launch of the fixed-wing aircraft into wing-borne flight; (2) a storage and launch system usable to store the modular multicopter and to facilitate launch of the fixed-wing aircraft into wing-borne flight; and (3) an anchor system usable (along with the multicopter and a flexible capture member) to retrieve the fixed-wing aircraft from wing-borne flight. | ||||||
| 148 | MULTICOPTER-ASSISTED SYSTEM AND METHOD FOR LAUNCHING AND RETRIEVING A FIXED-WING AIRCRAFT | US15434703 | 2017-02-16 | US20170158318A1 | 2017-06-08 | Andreas H. von Flotow; Corydon C. Roeseler |
| The present disclosure provides various embodiments of a multicopter-assisted launch and retrieval system generally including: (1) a multi-rotor modular multicopter attachable to (and detachable from) a fixed-wing aircraft to facilitate launch of the fixed-wing aircraft into wing-borne flight; (2) a storage and launch system usable to store the modular multicopter and to facilitate launch of the fixed-wing aircraft into wing-borne flight; and (3) an anchor system usable (along with the multicopter and a flexible capture member) to retrieve the fixed-wing aircraft from wing-borne flight. | ||||||
| 149 | In-flight reconfigurable hybrid unmanned aerial vehicle | US14524956 | 2014-10-27 | US09550567B1 | 2017-01-24 | Jack Erdozain, Jr.; Berk Ozturk; Nicholas Hampel Roberts; Brian C. Beckman |
| This disclosure is directed to an unmanned aerial vehicle (“UAV”) that transitions in-flight between vertical flight configuration and horizontal flight configuration by changing an orientation of the UAV by approximately ninety degrees. The UAV may include propulsion units that are coupled to a wing. The wing may include wing segments rotatably coupled together by pivots that rotate to position the propulsion units around a center of mass of the UAV when the fuselage is oriented perpendicular with the horizon. In this vertical flight configuration, the UAV may perform vertical flight or hover. During the vertical flight, the UAV may cause the wing to extend outward via the pivots such that the wing segments become positioned substantially parallel to one another and the wing resembles a conventional fixed wing. With the wing extended, the UAV assumes a horizontal flight configuration that provides upward lift generated from the wing. | ||||||
| 150 | UNMANNED AERIAL VEHICLE ARM ADJUSTMENT DEVICE AND UNMANNED AERIAL VEHICLE | US15210521 | 2016-07-14 | US20170015403A1 | 2017-01-19 | Yucheng LIANG; Fuhua AI |
| An unmanned aerial vehicle arm adjustment device for adjusting an unmanned aerial vehicle arm into a folding state or an extracting state with respect to a fuselage of the aerial vehicle includes: left and right curb plates connected to the fuselage; a rocking arm connected to the unmanned aerial vehicle arm, wherein one end of the rocking arm is articulated with the left and right curb plates, and a first engaging part is provided on the rocking arm; and a locking member articulated with the left and right curb plates, wherein the locking member is provided with a second engaging part for engaging with the first engaging part; wherein the locking member is adapted to rotate in a first direction to force the second engaging part to engage with the first engaging part so as to hold the rocking arm such that the unmanned aerial vehicle arm is in the extracting state; and wherein the locking member is adapted to rotate in a second direction opposite to the first direction to force the second engaging part to disengage with the first engaging part so as to release the rocking arm such that the unmanned aerial vehicle arm is able to be rotated into the folding state. | ||||||
| 151 | UNMANNED AERIAL VEHICLE WITH DETACHABLE COMPUTING DEVICE | US14658689 | 2015-03-16 | US20160376004A1 | 2016-12-29 | Jerry Daniel Claridge; Charles Fischer Manning |
| This disclosure is generally directed to an Unmanned Aerial Device (UAV) that uses a removable computing device for command and control. The UAV may include an airframe with rotors and an adjustable cradle to attach a computing device. The computing device, such as a smart phone, tablet, MP3 player, or the like, may provide the necessary avionics and computing equipment to control the UAV autonomously. For example, the adjustable cradle may be extended to fit a tablet or other large computing device, or retracted to fit a smart phone or other small computing device. Thus, the adjustable cradle may provide for the attachment and use of a plurality of different computing devices in conjunction with a single airframe. Additionally the UAV may comprise adjustable arms to assist in balancing the load of the different computing devices and/or additional equipment attached to the airframe. | ||||||
| 152 | DEVICE FOR FOLDING/UNFOLDING A TAIL BOOM OF A ROTORCRAFT, AN ASSOCIATED ROTORCRAFT, AND A CORRESPONDING FOLDING/UNFOLDING METHOD | US15083568 | 2016-03-29 | US20160332719A1 | 2016-11-17 | Maxime MALTINTI; Florian POGGIOLI |
| A folding/unfolding device for folding/unfolding a tail boom, the device being arranged in association with a rear power transmission shaft of a tail rotor of the rotorcraft, the folding/unfolding device comprising pivot means enabling a movable portion of the tail boom to move in pivoting relative to a stationary portion of the tail boom, the relative pivoting movement being performed between two distinct extreme positions, namely an unfolded, working position enabling the rear power transmission shaft to transmit driving torque to the tail rotor, and a folded, rest position enabling the overall length of the rotorcraft to be reduced. According to the invention, the folding/unfolding device includes motor-driven decoupling/coupling means for mechanically decoupling/coupling together two portions of a single rear power transmission shaft before/after the relative pivoting movement of the movable portion of the tail boom relative to the stationary portion. | ||||||
| 153 | Vehicle | US15132288 | 2016-04-19 | US20160229245A1 | 2016-08-11 | Michael Alwin William Stekelenburg; Christiaan Cornelis Klok; Louis Petrus Valentijn Marie Van Rijn; Wouter Adriaan Soethoudt; Robert Christiaan Wegerif |
| A vehicle capable of being converted between a flying condition and an automotive riding condition. The vehicle has a telescopically extendable tail having a first tubular tail segment and a second tail segment disposed axially slideable within the first tubular tail segment. The tail is provided with at least two form-closing coupling members located at an axial distance from each other for providing a force-transferring coupling between the second tail segment and the first tubular tail segment in the extended state of the second tail segment, each of the form-closing coupling members capable of transferring torque and transverse forces, and each of the form-closing coupling members coming into engagement by axial displacement of the second tail segment in the outward direction. | ||||||
| 154 | HOVERING UNMANNED AERIAL VEHICLE | US14436310 | 2013-10-17 | US20150259066A1 | 2015-09-17 | Glen Johannesson; David Kroetsch; Michael Peasgood; Stephen Marchetti |
| In an aspect, an apparatus includes a hovering unmanned aerial vehicle (HUAV). The HUAV includes an arm assembly configured to support a propeller in such a way that propeller drag of the propeller is decoupled from yaw torque requirements associated with the hovering unmanned aerial vehicle. In another aspect, an apparatus includes an HUAV that has an arm assembly that is field-foldable relative to the HUAV between a flight-ready state and a folded state. In another aspect, an apparatus includes an HUAV having an arm assembly that is keyed in such a way as to facilitate field-assembly relative to the HUAV. | ||||||
| 155 | Dismountable helicopter | US13513722 | 2009-12-02 | US09067677B2 | 2015-06-30 | Per-Erik Cardell; Kjell Stenbom; Robert Lidström |
| An unmanned aerial vehicle helicopter including a dismountable tail section including a torque compensating rotor. Power transmission from the motor to the torque compensating rotor is accomplished by pulley-and-belt drive arrangements. | ||||||
| 156 | Modular miniature unmanned aircraft with vectored-thrust control | US13954278 | 2013-07-30 | US08967527B2 | 2015-03-03 | Adam John Woodworth; James Peverill; Greg Vulikh; Jeremy Scott Hollman |
| An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds. | ||||||
| 157 | Modular miniature unmanned aircraft with vectored-thrust control | US13954218 | 2013-07-30 | US08951086B2 | 2015-02-10 | Adam John Woodworth; James Peverill; Greg Vulikh; Jeremy Scott Hollman |
| An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds. | ||||||
| 158 | VEHICLE | US14357075 | 2012-11-09 | US20140291440A1 | 2014-10-02 | Michael Alwin William Stekelenburg; Christiaan Cornelis Klok; Louis Petrus Valentijn Marie Van Rijn; Wouter Adriaan Soethoudt; Robert Christiaan Wegerif |
| The present invention discloses a vehicle (1) capable of being converted between a flying condition and an automotive riding condition. The vehicle has a telescopically extendable tail (10) comprising a first tubular tail segment (11) and a second tail segment (12) disposed axially slideable within the first tubular tail segment. The tail is provided with at least two form-closing coupling members (21, 35; 31, 36) located at an axial distance (LI) from each other for providing a force-transferring coupling between the second tail segment (12) and the first tubular tail segment (11) in the extended state of the second tail segment (12), each of said form-closing coupling members (21, 35; 31, 36) capable of transferring torque and transverse forces, and each of said form-closing coupling members (21, 35; 31, 36) coming into engagement by axial displacement of the second tail segment (12) in the outward direction. | ||||||
| 159 | MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED-THRUST CONTROL | US13954278 | 2013-07-30 | US20140061384A1 | 2014-03-06 | Adam John Woodworth; James Peverill; Greg Vulikh; Jeremy Scott Hollman |
| An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds. | ||||||
| 160 | Modular miniature unmanned aircraft with vectored-thrust control | US13567015 | 2012-08-04 | US08500067B2 | 2013-08-06 | Adam Woodworth; James Peverill; Greg Vulikh; Jeremy Scott Hollman |
| An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds. | ||||||
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