| 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 | 针对无人驾驶飞行器的地面站 | CN202180034021.3 | 2021-03-08 | CN115552500A | 2022-12-30 | A·拉普托波洛斯; P·雷斯米尼; I·巴鲁钦; L·鲁伊兹; D·韦尔登; J·拜尔斯; J·奥沙利文; A·吴; D·蔡; M·诺瓦克 |
| 本公开描述了一种被配置为使用无人驾驶飞行器(UAV)来促进递送有效负载的地面站。地面站包括多个传感器，该多个传感器允许作为较大有效负载运输系统的一部分的地面站的自主操作。传感器被配置为确认将有效负载装载到UAV上、检查无人机的状态和安全性、以及在UAV的起飞和/或着陆操作之前清理地面站周围的区域。 | ||||||
| 2 | 用于收割和稀释的无人机群管理的系统和方法 | CN201780050626.5 | 2017-08-17 | CN109862778B | 2022-03-01 | Y·马奥尔 |
| 本发明提供了一种用于收割或稀释果实的自主无人驾驶飞行器(UAV)群管理的管理系统，以及使用UAV群进行最佳收割的计算机化方法。 | ||||||
| 3 | 用于收割和稀释的无人机群管理的系统和方法 | CN201780050626.5 | 2017-08-17 | CN109862778A | 2019-06-07 | Y·马奥尔 |
| 本发明提供了一种用于收割或稀释果实的自主无人驾驶飞行器(UAV)群管理的管理系统，以及使用UAV群进行最佳收割的计算机化方法。 | ||||||
| 4 | 音響泳動により、ガスからエアロゾルと固形物粒子および繊維と、流体からの固形物粒子および繊維とを分離および／または清浄化するための方法および機器 | JP2021191784 | 2021-11-26 | JP7351886B2 | 2023-09-27 | グレゴア ルーテ; ルートガー ガウスリング; ニールス テン テイエ |
| 5 | Drone control system, method, and program | US16345796 | 2016-10-31 | US10589861B2 | 2020-03-17 | Shunji Sugaya |
| A drone control system in which a drone can move to a position where a purpose can be achieved and performs an action according to the purpose is provided. The drone control system 1 controls a drone 10 capable of performing a predetermined action on a predetermined object, and includes a state data acquiring module 201 that acquires state data indicating a state of the object, a purpose data acquiring module 202 that acquires purpose data which is a purpose of moving the drone, and a detecting module 203 that detects an action point, which is position information at which an action for the purpose is executed, based on the acquired state data and purpose data. | ||||||
| 6 | COVERING DEVICE FOR AN INTERIOR OF AN AIRCRAFT AND A METHOD FOR COVERING AN INTERIOR OF AN AIRCRAFT | US13419496 | 2012-03-14 | US20120175071A1 | 2012-07-12 | Ingo WUGGETZER; Stefan LIST; Nicolas TSCHECHNE; Tobias MAYER |
| A cladding apparatus is provided for the interior of an aircraft that includes, but is not limited to at least one two-dimensional fabric sheet, at least one guide device, and at least one tensioning element. The guide device is configured to be attached in the interior along a direction of extension of the interior, and slidably guide the fabric sheet at least in a first section of the interior along the direction of extension. The tensioning element is, furthermore, configured to be attached in the interior, and by producing a tensile force that acts on the front edge and/or the rear edge of the fabric sheet to stretch taut the fabric sheet along the direction of extension of the interior. | ||||||
| 7 | Flying body | US18331960 | 2023-06-09 | US12116129B2 | 2024-10-15 | Noritomo Yanagimoto |
| There is provided a flight vehicle including: a wing unit; a battery that is arranged in the wing unit; an air intake unit that is formed at a position corresponding to the battery on a front side of the wing unit; a heat sink unit that is arranged for the battery and cools the battery by air which flows in from the air intake unit and that includes a ventilation unit having a shape widening from the front side toward a rear side; and an exhaust unit that is formed at a position corresponding to the battery on the rear side of the wing unit and that exhausts air which flows out from the heat sink unit. | ||||||
| 8 | FLYING BODY | US18331960 | 2023-06-09 | US20230322383A1 | 2023-10-12 | Noritomo YANAGIMOTO |
| There is provided a flight vehicle including: a wing unit; a battery that is arranged in the wing unit; an air intake unit that is formed at a position corresponding to the battery on a front side of the wing unit; a heat sink unit that is arranged for the battery and cools the battery by air which flows in from the air intake unit and that includes a ventilation unit having a shape widening from the front side toward a rear side; and an exhaust unit that is formed at a position corresponding to the battery on the rear side of the wing unit and that exhausts air which flows out from the heat sink unit. | ||||||
| 9 | Angled airfoil extension for fan blade | US12038873 | 2008-02-28 | US08162613B2 | 2012-04-24 | Richard A. Oleson; Richard M. Aynsley; Dale R. Jury |
| An angled fan blade extension includes an attachment portion and an angled portion. The attachment portion is configured to facilitate securing the angled fan blade extension to the distal end of a fan blade. The angled portion is configured to extend from the distal end of the attachment portion, creating an angled extension relative to the fan blade. Adding angular fan blade extensions to fan blades may improve the airflow control, and thereby increase the utility and efficiencies of a fan. | ||||||
| 10 | Gap Covering Device | US12532343 | 2008-03-25 | US20100176242A1 | 2010-07-15 | Thomas Bock; Michael Auburger; Patrique Doemeland; Brigitte Gerner; Florian Schuephaus; Silvan Fiedler |
| A gap covering device (10) for covering a gap (16) between two mutually adjacent first aircraft interior components (12, 14) comprises a visible portion (18) as well as a retaining portion (20) connected to the visible portion (18) and extending opposite the visible portion (18). A receiving structure is fastened to an inner surface of the visible portion (18) and/or of the retaining portion (20) and has a receiving contour adapted to an edge contour of the first aircraft interior components (12, 14). | ||||||
| 11 | SYSTEM FOR ACCOMMODATING AT LEAST ONE OBJECT IN A CABIN OF A VEHICLE | US12618964 | 2009-11-16 | US20100140409A1 | 2010-06-10 | Nils Poerner |
| A system for accommodating at least one object in a cabin of a vehicle exhibits at least one first connecting means, at least one second connecting means and at least one latching device, wherein the first connecting means is positioned in the cabin of the vehicle, and the second connecting means is positioned on the object, the first connecting means and the second connecting means establish a connection in an accommodating position of the object, and the latching device latches the object in the accommodating position. This makes it possible to replace conventional stowage compartments with a weight-saving system, which may accommodate correspondingly prepared luggage items or other objects in a vehicle cabin. | ||||||
| 12 | GROUND STATION FOR UNMANNED AERIAL VEHICLES | EP21767999.2 | 2021-03-08 | EP4100936A1 | 2022-12-14 | RAPTOPOULOS, Andreas; RESMINI, Paolo; BARUCHIN, Ido; RUIZ, Lalo; WELDON, David; BYARS, Jon; O'SULLIVAN, Jim; WU, Alex; TSAI, David; NOVAK, Martin |
| This disclosure describes a ground station configured to facilitate the delivery of payloads using unmanned aerial vehicle (UAV). The ground station includes multiple sensors that allow for autonomous operation of the ground station as part of a larger payload transportation system. The sensors are configured to confirm loading of payloads onto a UAV, checking a status and safety of the drone and clearing an area surrounding the ground station prior to takeoff and/or landing operations of the UAV. | ||||||
| 13 | SYSTEM AND METHOD FOR DRONE FLEET MANAGEMENT FOR HARVESTING AND DILUTION | EP17841224.3 | 2017-08-17 | EP3500086A1 | 2019-06-26 | MAOR, Yaniv |
| The present invention provides a computerized system for mapping an orchard, and a method for producing precise map and database with high resolution and accuracy of all trees in an orchard. | ||||||
| 14 | Gas propulsion thrust device | US17888871 | 2022-08-16 | US12049315B2 | 2024-07-30 | Igor Morozov |
| A novel gas propulsion device comprises one or more high-frequency linear actuators (such as a voice coil linear actuator or a piezoelectric linear actuator) attached to one or more gas propulsion elements having a concave internal surface facing a first side thereof. Linear actuators operate to cause reciprocal movements of each gas propulsion element at a sufficient speed, such as a subsonic or supersonic speed, and suitable amplitude to form a high gas pressure zone on the first side of the gas propulsion element and a low gas pressure zone on the second side thereof. The gas pressure differential in turn causes propulsion of gas away from the device along the longitudinal axis or to the side of it if the gas propulsion element is tilted. The invention may be used as a main or secondary thrust engine for an aircraft. | ||||||
| 15 | Method And Device For Aiding The Localization Of An Aircraft Wreck Submerged In A Sea | US13310873 | 2011-12-05 | US20120138741A1 | 2012-06-07 | Christian Fabre; Alain Bignolais |
| Method and device for aiding the localization of an aircraft wreck submerged in a sea.The device includes at least a beacon (2a, 2b) which is automatically ejected out of the fuselage of the aircraft (AC), when this latter is submerged in a sea (M). | ||||||
| 16 | DEVICE FOR HOLDING AN INSULATING BLANKET AND FOR FASTENING SYSTEMS ADAPTED TO BE MOUNTED IN AN AIRCRAFT | US13165461 | 2011-06-21 | US20110309197A1 | 2011-12-22 | Julie Holvoet; Matthieu De Kergommeaux; Jean-Claude Briois; Luc Michelet |
| This device is intended for an aircraft comprising frames, a skin and connecting pieces between the skin and the frames, referred to as clips.It comprises: two brackets (30), each bracket having a first branch (32) intended to be fastened to a clip of the aircraft and a second branch (34) provided with a slot (36), a stirrup-shaped clip (1) comprising a base (2) and two arms (4, 6), each arm (4, 6) having at its free end a securing lug (17) adapted for being able to be inserted in the slot (36) of one of the said brackets with a flange (19) that forms a stop countering displacement of the securing lug once the latter is inserted into the said slot, each arm (4, 6) further comprising at least one support (14, 22) for accommodating a system. | ||||||
| 17 | Method for connecting a first material to a second material in aircraft construction | US12682455 | 2008-10-13 | US20110284691A1 | 2011-11-24 | Sabine Wlach (Metzech); Georg Wachinger; Thomas Meer; Christian Lammel |
| The invention concerns a method of connecting a first material to a second material by means of a heat-activatable adhesive material (8) in aircraft construction, wherein the adhesive material (8) is arranged between the first material and the second material and an induction heat which is adequate to activate the adhesive material (8) is generated. The first material and/or the second material and/or the adhesive material (8) have an induction heat-generating means. The induction heat-generating means is a non-woven metallic mesh and/or the induction heat-generating means (53) has an amount of carbon fibers for induction heat generation. The invention further concerns an apparatus comprising a first material and a second material, wherein the first material and the second material have a connection which can be produced by a heat-activatable adhesive material arranged between the first material and the second material, in accordance with the method in accordance with the invention. | ||||||
| 18 | CONNECTION ASSEMBLY FOR AT LEAST ONE ITEM OF ELECTRONIC EQUIPMENT IN AN AIRCRAFT | US13021432 | 2011-02-04 | US20110198445A1 | 2011-08-18 | Emile COLONGO; Salles PIERRE |
| The invention relates to an assembly for connection (1; 101) of an electronic equipment item (2) to wiring of an aircraft, in which the item of electronic equipment (2) is disposed in a support means (4) and comprises connection means (26) adapted for being connected to the wiring, a connection interface (6; 106) being disposed between the wiring and the connection means (26) to provide connection of the item of electronic equipment (2) to the said wiring, the said connection assembly (1; 101) being adapted for changing over from a connected state in which the connection means (26) are connected to the connection interface (6; 106) to a disconnected state in which the connection means (26) are free. The connection interface is fastened to the structure (28) of the aircraft; whether the connection assembly is in the connected or disconnected state. The support means (4) is movable and comprises an at least partially open face turned toward the connection interface (6; 106) and onto which the connection means (26) emerge. The connection of the connection assembly (1; 101) to the connection interface (6; 106) is made by moving the support means (4) between a first position where the connection assembly (1; 101) is in a disconnected state and a second position where it is in a connected state. | ||||||
| 19 | METHOD AND SYSTEM FOR LIMITING ENERGY TO A SENSOR | US13008938 | 2011-01-19 | US20110187182A1 | 2011-08-04 | Howard Austerlitz; Ron Bueter; John O'Brien |
| A method and system for limiting energy to a sensor and/or an environment in which the sensor is located. A high current sensor driver is powered through a resistance-capacitance (RC) circuit. In a failure mode, the RC circuit constrains output of a sensor driver to the sensor in order to limit average current applied to the sensor. In one embodiment, the capacitor is chosen so that it can provide adequate current to the sensor driver for a short period of time. The value of the resistor may be chosen to ensure that under short circuit conditions direct current (DC) is limited to a safe value. The combined values of the resistor and capacitor may be adjusted such that the capacitor can charge to a prescribed level during the interval between active pulses. | ||||||
| 20 | Aircraft with a Rear Fuselage Protection Shield | US11794487 | 2005-12-29 | US20100059627A1 | 2010-03-11 | Cesar Bautista De La Llave; Bernardo Lopez Romano; Angel Postigo Rodriguez; Jose Sanchez Gomez |
| The invention relates to an aircraft with a protection shield for the rear composite material, fuselage 25) for conducting tail impact tests, in addition to a tail absorber, the shield (11) being formed by a plurality of pieces (21) joined to supports (23) fixed to the rear fuselage (25) behind the tail absorber (1), said pieces (21) having a laminar structure with an outer steel sheet (13), an inner composite sheet (17) and an intermediate high resistance silicon sheet (15). | ||||||
QQ群二维码
意见反馈
意见反馈