-
公开(公告)号：TW201718064A
公开(公告)日：2017-06-01
申请号：TW104138131
申请日：2015-11-18
Applicant: 朝陽科技大學
Inventor： 鄭安欽
IPC: A63H27/20
CPC classification number: B64C39/024 , B64C2201/027 , B64C2201/12 , B64C2201/14 , B64D47/08 , G05D1/0016 , G05D1/101 , G06F3/0414 , G06F3/044
Abstract: 一種無人飛行器的其控制系統，包含控制該無人飛行器進入定位飄浮狀態的一驅動單元、偵測該無人飛行器1目前所在的位置座標，並輸出包括該位置座標的一位址訊號的一空間感測單元、一接觸開關，及與該驅動單元、該空間感測單元、該接觸開關電連接的一控制器。主要是在該無人飛行器以一第一位址進入定位飄浮狀態時，使用者只需直接碰觸該無人飛行器上的該接觸開關，就可以解除該無人飛行器的定位飄浮狀態，使該無人飛行器可以在任意移動後，以一第二位址為飄浮狀態時的定位位置。藉此，本發明可以在不需要搖控器的情形下，直覺的以手動的方式移動及控制該無人飛行器的定位位置，不但能夠簡化控制程序，提升用途及適用範圍，且使用操作相當簡便。
Abstract in simplified Chinese: 一种无人飞行器的其控制系统，包含控制该无人飞行器进入定位飘浮状态的一驱动单元、侦测该无人飞行器1目前所在的位置座标，并输出包括该位置座标的一位址信号的一空间传感单元、一接触开关，及与该驱动单元、该空间传感单元、该接触开关电连接的一控制器。主要是在该无人飞行器以一第一位址进入定位飘浮状态时，用户只需直接碰触该无人飞行器上的该接触开关，就可以解除该无人飞行器的定位飘浮状态，使该无人飞行器可以在任意移动后，以一第二位址为飘浮状态时的定位位置。借此，本发明可以在不需要摇控器的情形下，直觉的以手动的方式移动及控制该无人飞行器的定位位置，不但能够简化控制进程，提升用途及适用范围，且使用操作相当简便。
-
公开(公告)号：TWI535478B
公开(公告)日：2016-06-01
申请号：TW104138131
申请日：2015-11-18
Applicant: 朝陽科技大學
Inventor： 鄭安欽
IPC: A63H27/20
CPC classification number: B64C39/024 , B64C2201/027 , B64C2201/12 , B64C2201/14 , B64D47/08 , G05D1/0016 , G05D1/101 , G06F3/0414 , G06F3/044
-
公开(公告)号：KR20210029518A
公开(公告)日：2021-03-16
申请号：KR1020190110856A
申请日：2019-09-06
Applicant: 삼성전자주식회사
CPC classification number: G05D1/101 , B64C39/024 , B64D45/00 , B64D47/00 , B64D47/08 , G05D1/0094 , G05D1/042 , G05D1/0808 , G06K7/10009 , G06K7/1408 , G06K7/1413 , B64C2201/027 , B64C2201/127 , B64C2201/14 , B64C2201/141
Abstract: 본 개시는 멀티 센서 기반의 무인 비행체 및 그 제어 방법에 관한 것으로, 본 개시의 일 실시예에 따른 무인 비행체는, 상기 무인 비행체의 관성 정보 또는 위치 정보를 획득하는 센서부 및 상기 센서부에서 획득된 정보를 확장 칼만 필터(extended kalman filter)에 적용하여 상기 무인 비행체의 위치를 추정하고, 상기 추정된 무인 비행체의 위치에 기초하여 상기 무인 비행체의 주행을 제어하는 제어부를 포함하며, 상기 센서부는, 상기 무인 비행체의 관성 정보를 획득하는 관성 센서, 랙(rack)에 부착된 태그(tag)를 인식하여, 상기 무인 비행체의 절대 위치 정보를 획득하는 태그 인식 센서, 및 상기 무인 비행체에 부착되어, 상기 무인 비행체의 주행 환경 영상을 획득하는 영상 센서를 포함할 수 있다.
-
公开(公告)号：JP2016117485A
公开(公告)日：2016-06-30
申请号：JP2015255989
申请日：2015-12-28
Applicant: 深▲せん▼市大▲じゃん▼創新科技有限公司
CPC classification number: G01P1/003 , B64D45/00 , F16F15/00 , G01C19/16 , G01C19/56 , G01C19/5628 , G01C19/5663 , G01C19/5769 , G01C19/5783 , G01C21/16 , G01C25/00 , G01P15/08 , G01P15/0802 , B64C2201/14
Abstract: 【課題】防振効果が好ましい無人航空機慣性計測モジュールを提供する。 【解決手段】慣性センサーなど振動性能への要求が高いデバイスを第2回路板6に集成し、ダンパーを設置することによって慣性計測モジュールの振動特性を改善し、慣性計測モジュールの固有機械振動周波数を、航空機が発生する各種の運動に関連しない振動周波数よりはるかに低いものとする。第1防振パッド3を設置することによって、無人航空機による慣性センサーへの振動を迅速に減衰させ、無人航空機が50HZ以上の周波数を生じたとき、ダンパー使用後に慣性センサーが受ける振動を、防振パッド未使用時の振動の30%以下まで減衰させ、無人航空機の動作振動周波数による慣性センサーへの影響を極大に減少し、慣性センサーによる計測の安定性を向上させる。 【選択図】図4
Abstract translation: 要解决的问题：提供一种有利于隔振效果的无人飞行器惯性测量模块。解决方案：对振动性能要求高的惯性传感器等装置聚集到第二电路板6上，振动特性 通过安装阻尼器来改善惯性测量模块，惯性测量模块的自然机械振动频率被设定为比飞行器产生的各种运动不相关的振动频率更低的值 。 通过安装第一防振垫3，由无人驾驶飞机对惯性传感器造成的振动迅速衰减，使用阻尼器后惯性传感器接收到的振动被衰减到不高于非惯性传感器振动30％的值 - 当无人驾驶飞机产生不低于50HZ的频率时，使用防振垫，将由无人驾驶飞机的运动振动频率引起的惯性传感器的影响降至最低，惯性传感器测量的稳定性 改进。图4
-
公开(公告)号：JP5886201B2
公开(公告)日：2016-03-16
申请号：JP2012528910
申请日：2010-09-09
Applicant: エアロバイロメント,インコーポレイテッド , AEROVIRONMENT,INC.
Inventor： ミラジェス,カルロス トーマス , プラム,ニック , タオ,シュオ トニー , オルソン,ネイサン
CPC classification number: B64C3/56 , B64C13/18 , B64C13/28 , B64C3/44 , B64C3/50 , B64C39/024 , B64C5/12 , B64C9/02 , B64C9/08 , B64C9/18 , B64C2009/005 , B64C2201/021 , B64C2201/08 , B64C2201/102 , B64C2201/121 , B64C2201/14 , B64C2201/145 , B64C2201/146
-
Patent Agency Ranking
公开(公告)号：EP3391163A1
公开(公告)日：2018-10-24
申请号：EP16828716.7
申请日：2016-12-19
Applicant: Pfoertzsch, Antony
Inventor： PFOERTZSCH, Antony
IPC: G05D1/00
CPC classification number: B64C39/024 , B64C39/02 , B64C2201/024 , B64C2201/127 , B64C2201/14 , B64D47/08 , G05D1/0094 , G05D1/101 , G05D1/12 , G06F3/017 , G06K9/00 , G06K9/0063
Abstract: The invention relates to a device and a method for an unmanned flying object, in particular for a drone. According to the invention, sensor data (21) of at least one imaging sensor (16A - 16D) and at least one distance-detecting sensor (12A - 12D) is received by a sensor interface (18) and supplied to a signal processing unit (20) which is designed to detect at least one specified object and/or differentiate said at least one specified object from other objects and to determine the parameters of the detected or differentiated object by comparing the sensor data (21) with reference data (25). The parameters of the specified object are then output by an output interface (29).
-
公开(公告)号：EP3390224A1
公开(公告)日：2018-10-24
申请号：EP16831647.9
申请日：2016-12-16
Applicant: IOSIF, Taposu , RAZVAN, Sabie
Inventor： RAZVAN, Sabie
IPC: B64C39/00
CPC classification number: B64C39/001 , B64C2201/027 , B64C2201/14 , B64C2201/162 , B64C2201/167 , B64C2201/185
Abstract: The invention relates to an aircraft with vertical takeoff and landing and its operation method. Aircraft with vertical takeoff and landing of aerodyne type according to the invention comprises a circular symmetrical aerodynamic body (1) having an internal stiffening platform (2) located on the chord of the aerodynamic profile and which supports the components of the aircraft, at least four vertical ducted propellers (3a), (3b), (3c), (3d) arranged symmetrically to the central vertical axis of the carrier body (1), but also to the predetemined flight axis and to the transverse axis of the carrier body (1), propellers (3a) and (3c) having the same rotational direction opposite to that of propellers (3b) and (3d) at least two horizontal ducted propellers (4) with opposite rotation directions located inside the carrier body or outside of it, placed parallel symmetrical with the predetermined flight axis and on both sides of it, vector nozzles (5), one for each horizontal propeller (4), which provides vector orientation to jets of the horizontal ducted propellers (4), the means of power supply (6), which are designed to provide electricity necessary to operate all engines and all electrical and electronic devices on board, an electronic control and management flight module (7) and a landing gear (9), which aims to promote contact between the aircraft and the ground.
-
公开(公告)号：EP3384361A1
公开(公告)日：2018-10-10
申请号：EP16801681.4
申请日：2016-11-14
Applicant: Cloud Cap Technology, Inc.
Inventor： ALLEN, Michael, J.
CPC classification number: B64C27/57 , B64C39/024 , B64C2201/027 , B64C2201/108 , B64C2201/14 , B64D31/02 , G05D1/0072 , G05D1/0858
Abstract: A method for controlling each rotor on a multirotor aircraft includes receiving one or more sensed states of the multirotor aircraft, and determining a control scheme dynamically using the sensed one or more states of the multirotor aircraft. Receiving one or more sensed states can include receiving one or more of a rotational rate or acceleration of the aircraft, or any other suitable aircraft state.
-
公开(公告)号：EP2752643B1
公开(公告)日：2018-08-08
申请号：EP11871565.5
申请日：2011-09-15
Applicant: SZ DJI Technology Co., Ltd.
IPC: G01C21/18 , G01C19/16 , G01C19/5628 , G01C19/5663 , G01C19/5769 , G01C19/5783 , B64D45/00 , G01C21/16 , F16F15/00 , G01C19/56 , G01C25/00 , G01P15/08 , G01P1/00 , G01P1/02 , F16F7/104
CPC classification number: G01P1/003 , B64C2201/14 , B64D45/00 , F16F7/104 , F16F15/00 , G01C19/16 , G01C19/56 , G01C19/5628 , G01C19/5663 , G01C19/5769 , G01C19/5783 , G01C21/16 , G01C25/00 , G01P1/023 , G01P15/08 , G01P15/0802
Abstract: The present disclosure relates to an inertia measurement unit for an unmanned aircraft, which comprises a housing assembly, a sensing assembly and a vibration damper. The vibration damper comprises a first vibration-attenuation cushion; and the sensing assembly comprises a first circuit board, a second circuit board and a flexible signal line for connecting the first circuit board and the second circuit board. An inertia sensor is fixed on the second circuit board, and the first circuit board is fixed on the housing assembly. The inertia measurement unit further comprises a weight block, and the second circuit board, the weight block, the first vibration-attenuation cushion and the first circuit board are bonded together in sequence into one piece and then fitted into the housing assembly. In the present disclosure, components including the inertia sensor and so on that require a high vibration performance are integrated on the second circuit board, and by disposing the first vibration-attenuation cushion, vibrations suffered by the inertia sensor are attenuated to below 30% of those suffered before the vibration-attenuation cushion is disposed. This greatly reduces the influence of the operational vibration frequency of the unmanned aircraft on the inertia sensor and improves the measurement stability of the inertia sensor.
-
公开(公告)号：EP3353054A1
公开(公告)日：2018-08-01
申请号：EP16777858.8
申请日：2016-09-22
Applicant: Amazon Technologies, Inc.
Inventor： BECKMAN, Brian C. , SKEELS, Matthew Lee
CPC classification number: B64D27/26 , B64C39/024 , B64C2201/024 , B64C2201/042 , B64C2201/14 , B64C2220/00
Abstract: A motor mount assembly is provided for coupling a propeller motor to a body of an unmanned aerial vehicle (UAV). The motor mount assembly includes a floating portion and acts to attenuate frequencies of vibration from the propeller motor during operation, which modifies the corresponding noise that is produced and reduces stresses on the various components. The floating portion is surrounded on all sides by isolation portions (e.g., made of elastomers or other materials) that are held within a casing that attaches to the body of the UAV. In one implementation, the motor mount assembly is modular such that one or more of the isolation portions may be replaced with different isolation portions (e.g., having different attenuation properties), depending on the direction and nature of the vibrations from the propeller motor that are to be attenuated for a particular application.
-
-
-
-
-
-
-
-
-
Search Results
588
records
(took 0.024 seconds)
