子分类：
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 81 | AUTOMOTIVE DRONE DEPLOYMENT SYSTEM | US15419814 | 2017-01-30 | US20170139421A1 | 2017-05-18 | John A. Lockwood; Joseph F. Stanek |
| This disclosure generally relates to an automotive drone deployment system that includes at least a vehicle and a deployable drone that is configured to attach and detach from the vehicle. More specifically, the disclosure describes the vehicle and drone remaining in communication with each other to exchange information while the vehicle is being operated in an autonomous driving mode so that the vehicle's performance under the autonomous driving mode is enhanced. | ||||||
| 82 | REDUNDANCY IN UAV ENGINE TIMING POSITION SYSTEMS | US15319948 | 2015-06-23 | US20170138281A1 | 2017-05-18 | Tyron Dean UTLEY; Nicolass Harry BUTERS; Jayesh NARAYAN |
| Redundancy in engine timing position sensing maintains a UAV operational in the event of failure of a primary engine timing position sub-system. The redundancy avoids duplication of the primary crankshaft timing position sensing components, and avoids adding weight, cost and component complexity. Conditioned (square) waveform(s) (102) is/are created from respective sinusoidal waveform(s). Each consecutive leading edge (103a) and trailing edge (103b) of the pulses of the square waveform (102) is derived from the crossing of the zero voltage value by consecutive sinusoidal waveforms A,B,C (e.g. Voltage (V) vs Time (t) or angular degrees). The square pulse waveform (102) is output (104) to a microcontroller (106) to create and output a pseudo crankshaft timing position signal (108) to be used by an ECU to determine ignition and fuel injection events in the event that the primary timing signal from the crankshaft position sensor (CPS) has failed. The signal (108) output to the ECU can have a missing pulse (116) (i.e. indicative of a TDC position of the engine crankshaft) as well as multiple square pulses (114) corresponding to the pulses of the initial square pulse waveform (102). The waveform signal (108) is therefore derived from the alternator waveform signal(s) and provides a pseudo crankshaft timing position signal in the event of failure of the primary or initial CPS signal. | ||||||
| 83 | SYSTEM AND METHOD FOR ULTRASOUND DISTANCE DETECTION | US15169449 | 2016-05-31 | US20170059704A1 | 2017-03-02 | Jiebin XIE; Litian ZHANG; Wei REN |
| A system for using ultrasound to detect distance on mobile platform and methods for making and using same. The system includes an ultrasound transceiver that can transmit and/or receive ultrasound waves and determine distance from an object of interest using a time-of-flight of the ultrasound wave. The system is adapted to reduce noise by using a dynamic model of the mobile platform to set constraints on the possible location of a received ultrasound echo. A linear, constant-speed dynamic model can be used to set constraints. The system can further reduce noise by packetizing a received ultrasound waveform and filtering out noise according to height and width of the packets. The system likewise can remove dead zones in the ultrasound transceiver by subtracting an aftershock waveform from the received waveform. The systems and methods are suitable for ultrasound distance detection on any type of mobile platform, including unmanned aerial vehicles. | ||||||
| 84 | Automotive drone deployment system | US15231579 | 2016-08-08 | US09555885B2 | 2017-01-31 | Joseph F. Stanek; John A. Lockwood |
| This disclosure generally relates to an automotive drone deployment system that includes at least a vehicle and a deployable drone that is configured to attach and detach from the vehicle. More specifically, the disclosure describes the vehicle and drone remaining in communication with each other to exchange information while the vehicle is being operated in an autonomous driving mode so that the vehicle's performance under the autonomous driving mode is enhanced. | ||||||
| 85 | WIRELESS AIRCRAFT AND METHODS FOR OUTPUTTING LOCATION INFORMATION OF THE SAME | US15185094 | 2016-06-17 | US20160379369A1 | 2016-12-29 | Shunji SUGAYA |
| The present invention is to provide a wireless aircraft and a method for outputting location information to reduce a cost, simplify the process, and output the necessary information. The wireless aircraft 10 flying in the air takes an live image, detects the location information on which the wireless aircraft is located, stores a specific image of an extracted object, compares the taken live image with the specific image to recognize an object to be extracted from the live image, and outputs the detected location information when the object is recognized. | ||||||
| 86 | IMPACT ABSORPTION APPARATUS FOR UNMANNED AERIAL VEHICLE | US14713343 | 2015-05-15 | US20160332739A1 | 2016-11-17 | Clifford Wong |
| An unmanned aerial vehicle apparatus comprises a frame. Further, the unmanned aerial vehicle apparatus comprises a propulsion mechanism coupled to the frame that propels the frame through the air. In addition, the unmanned aerial vehicle apparatus comprises a storage device that stores one or more airbags and is coupled to the frame. The unmanned aerial vehicle apparatus also comprises an inflation device coupled to the frame that receives an activation signal and inflates the one or more airbags based upon receipt of the activation signal to deploy the one or more airbags from the storage device prior to an impact of the frame with an object. | ||||||
| 87 | System and method for placement of sensors through use of unmanned aerial vehicles | US14716850 | 2015-05-19 | US09454907B2 | 2016-09-27 | Usman Hafeez; David Mauer |
| The invention is directed toward a system and method for placing, activating, and testing sensors. The system comprises one or more server computers, one or more communication hubs, one or more unmanned aerial vehicles, and one or more sensors. The method comprises the steps of receiving geographic sensor placement locations, receiving sensor parameters, determining the geographic location of sensors, respectively sending location query signals to the unmanned aerial vehicles, respectively receiving location reply signals from the unmanned aerial vehicles, and calculating a geographic flight path for the unmanned aerial vehicles. The method also comprises calculating mission objectives and the energy needs of the unmanned aerial vehicles to complete the mission objectives. The method then determines the most efficient combination of unmanned aerial vehicles to complete the mission objectives and assigns the tasks to the unmanned aerial vehicles. The unmanned aerial vehicles place, activate, and test the sensors. | ||||||
| 88 | ULTRALIGHT AIRCRAFT | US15041424 | 2016-02-11 | US20160236789A1 | 2016-08-18 | Simon BURNS |
| An aircraft which has a supporting structure which has at least one fuselage, a wing structure and at least one drive apparatus. The drive apparatus has at least one propeller and a drive motor. The aircraft has at least one energy store for providing energy for operation of the drive apparatus. The at least one drive apparatus and the at least one energy store are mechanically connected to the supporting structure and/or the wing structure of the aircraft by a securing device. | ||||||
| 89 | Projection assemblies for use with unmanned aerial vehicles | US14448777 | 2014-07-31 | US09405181B2 | 2016-08-02 | Clifford W. Wong; Michael J. Ilardi |
| A projection assembly for use with an unmanned aerial vehicle (UAV) such as quadrotors. The projection assembly includes a projection screen with a rear surface and a front surface, and the projection screen has a level of opacity and/or other physical qualities that enables it to function as a rear-projection surface. The projection assembly includes a vehicle attachment member adapted for coupling with a frame of the UAV, and the projection screen is supported at a first end by the vehicle attachment member. The apparatus includes a projector projecting light, and the projected light is directed onto the rear surface of the projection surface to generate a displayed image visible on the front surface. The projection screen can be formed from a mesh sheet with a porosity allowing air to flow through the projection screen. The mesh sheet may be formed of plastic threads that provide the rear-projection surface function. | ||||||
| 90 | Micro unmanned aerial vehicle and method of control therefor | US14738467 | 2015-06-12 | US09352834B2 | 2016-05-31 | Barry Davies |
| A micro unmanned aerial vehicle or drone (“UAV”) 10 is remotely controlled through an HMI, although this remote control is supplemented by and selectively suppressed by an on-board controller. The controller operates to control the generation of a sonar bubble that generally encapsulates the UAV. The sonar bubble, which may be ultrasonic in nature, is produced by a multiplicity of sonar lobes generated by specific sonar emitters associated with each axis of movement for the UAV. The emitters produce individual and beamformed sonar lobes that partially overlap to provide stereo or bioptic data in the form of individual echo responses detected by axis-specific sonar detectors. In this way, the on-board controller is able to interpret and then generate 3-D spatial imaging of the physical environment in which the UAV is currently moving or positioned. The controller is therefore able to plot relative and absolute movement of the UAV through the 3-D space by recording measurements from on-board gyroscopes, magnetometers and accelerometers. Data from the sonar bubble can therefore both proactively prevent collisions with objects by imposing a corrective instruction to rotors and other flight control system and can also assess and compensate for sensor drift. | ||||||
| 91 | Method and system for estimating information related to a vehicle pitch and/or roll angle | US14362767 | 2014-04-14 | US09285460B2 | 2016-03-15 | Leif Haglund; Folke Isaksson; Michael Felsberg; Bertil Grelsson |
| The present disclosure relates to a method (200) for estimating information related to a vehicle pitch and/or roll angle. The method comprises a step of obtaining (220) a first estimate of the information related to the pitch and/or roll angle. The method is characterized by the steps of capturing (210) an image of an area covering at least a part of the horizon using a camera mounted on the airborne vehicle, and determining (240) an improved estimate of the information related to the pitch and/or roll angle based on the first estimate of the information related to the pitch and/or roll angle, and a digital elevation model. | ||||||
| 92 | PROPELLER SAFETY FOR AUTOMATED AERIAL VEHICLES | US14491215 | 2014-09-19 | US20160039529A1 | 2016-02-11 | Daniel Buchmueller; Brian C. Beckman; Amir Navot; Brandon William Porter; Gur Kimchi; Jeffrey P. Bezos; Frederik Schaffalitzky |
| The disclosure describes an automated aerial vehicle (AAV) and system for automatically detecting a contact or an imminent contact between a propeller of the AAV and an object (e.g., human, pet, or other animal). When a contact or an imminent contact is detected, a safety profile may be executed to reduce or avoid any potential harm to the object and/or the AAV. For example, if a contact with a propeller of the AAV by an object is detected, the rotation of the propeller may be stopped to avoid harming the object. Likewise, an object detection component may be used to detect an object that is nearing a propeller, stop the rotation of the propeller, and/or navigate the AAV away from the detected object. | ||||||
| 93 | Automotive Drone Deployment System | US14333462 | 2014-07-16 | US20160016663A1 | 2016-01-21 | Joe F. Stanek; Tony A. Lockwood |
| This disclosure generally relates to an automotive drone deployment system that includes at least a vehicle and a deployable drone that is configured to attach and detach from the vehicle. More specifically, the disclosure describes the vehicle and drone remaining in communication with each other to exchange information while the vehicle is being operated in an autonomous driving mode so that the vehicle's performance under the autonomous driving mode is enhanced. | ||||||
| 94 | Systems and Methods for Illumination and Observation | US13776444 | 2013-02-25 | US20150358556A1 | 2015-12-10 | Abe Karem; Benjamin Tigner |
| An aerial surveillance and reconnaissance system includes a gimbal-stabilized ISR imaging sensor with 0.8-1.2 microradian optical resolution, using pulsed ultraviolet laser (0.330-0.380 micrometer wavelength) radiation to illuminate the observed target, and a narrow-band-pass filter at the focal plane detector to remove light at frequencies other than the illuminating frequency. Preferred sensors can be operated in a snapshot mode using intermittent illuminating pulses, with timing of the pulses selected for minimum detectability based on observations made with a lower-resolution sensor, or in a video-mode with illuminating pulses selected to generate full-motion video at operator-selectable frame rates. Some sensor embodiments may further combine the UV system described above with conventional daylight optical and sensor systems, though alternative arrangements could also include an IR sensor as well (either using a common aperture with the UV system or with a separate set of light-gathering optics). | ||||||
| 95 | Apparatus for use on unmanned vehicles | US14129195 | 2012-06-20 | US09156552B2 | 2015-10-13 | Isobel Louise Freeman; Keith Antony Rigby |
| An apparatus, and a method performed by the apparatus, are disclosed wherein the apparatus can be mounted on an unmanned vehicle and arranged to act upon a payload. The payload can be mounted on the unmanned vehicle and, under an action of the apparatus, is able to be activated. The method can include receiving an activation instruction from an entity remote from the unmanned vehicle; determining whether or not the received activation instruction is valid by performing a validation process; and in response to determining that the received activation instruction is valid, activating the payload. In response to determining that the received activation instruction is not valid, activation of the payload may be prevented or opposed. | ||||||
| 96 | Unmanned device utilization methods and systems | US13551334 | 2012-07-17 | US09044543B2 | 2015-06-02 | Royce A. Levien; Richard T. Lord; Robert W. Lord; Mark A. Malamud; John D. Rinaldo, Jr.; Lowell L. Wood, Jr. |
| Structures and protocols are presented for configuring an unmanned aerial device to perform a task, alone or in combination with other entities, or for using data resulting from such a configuration or performance. | ||||||
| 97 | UNMANNED DEVICE UTILIZATION METHODS AND SYSTEMS | US13551334 | 2012-07-17 | US20140025236A1 | 2014-01-23 | Royce A. Levien; Richard T. Lord; Robert W. Lord; Mark A. Malamud; John D. Rinaldo, JR.; Lowell L. Wood, JR. |
| Structures and protocols are presented for configuring an unmanned aerial device to perform a task, alone or in combination with other entities, or for using data resulting from such a configuration or performance. | ||||||
| 98 | UNMANNED DEVICE UTILIZATION METHODS AND SYSTEMS | US13551320 | 2012-07-17 | US20140025235A1 | 2014-01-23 | Royce A. Levien; Richard T. Lord; Robert W. Lord; Mark A. Malamud; John D. Rinaldo, JR.; Lowell L. Wood, JR. |
| Structures and protocols are presented for configuring an unmanned aerial device to perform a task, alone or in combination with other entities, or for using data resulting from such a configuration or performance. | ||||||
| 99 | UNMANNED DEVICE UTILIZATION METHODS AND SYSTEMS | US13551266 | 2012-07-17 | US20140025233A1 | 2014-01-23 | Royce A. Levien; Richard T. Lord; Robert W. Lord; Mark A. Malamud; John D. Rinaldo, JR.; Lowell L. Wood, JR. |
| Structures and protocols are presented for configuring an unmanned aerial device to perform a task, alone or in combination with other entities, or for using data resulting from such a configuration or performance. | ||||||
| 100 | Lenticular airship | US13342373 | 2012-01-03 | US08418952B2 | 2013-04-16 | Pierre Balaskovic |
| An airship may include a hull substantially shaped as an oblate spheroid, one or more frame members defining a support structure, wherein the support structure forms at least a partial support for the hull, at least one horizontal stabilizing member operably coupled to a lower surface of the airship, and at least one horizontal stabilizing member having a first end and a second end. The at least one horizontal stabilizing member may define an anhedral configuration. The airship may also include a vertical stabilizing member having a first end pivotally coupled to the airship and a second end oriented to remain below an upper surface of the airship. The vertical stabilizing member may be configured to pivot within a vertical plane, and the first end of the vertical stabilizing member and the first end of the at least one horizontal stabilizing member may be operably coupled to one another. | ||||||
QQ群二维码
意见反馈
意见反馈