| 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 | 一种固定翼飞行器控制装置 | CN201610864440.0 | 2016-09-29 | CN106394871A | 2017-02-15 | 邱铁; 刘一玮; 王鑫; 刘西泽; 李军 |
| 本发明公开了一种固定翼飞行器控制装置。本发明通过卡尔曼滤波算法多次获取飞行器状态参数，并进行调整得到相对准确参数，据此进行动力性建模，姿态数据的获取相对较为明确难度在于PID各参数的调整上，其参数调整主要依靠设计人员的自身经验必须经过多次实验调整才能确定，使飞机飞行处于相对稳定状态。 | ||||||
| 2 | 一种飞行器实时监控及可视化展示系统 | CN201610913302.7 | 2016-10-19 | CN106657886A | 2017-05-10 | 王日光; 叶茂林; 陈建伟 |
| 本发明公开了一种飞行器实时监控及可视化展示系统，涉及无人机技术领域，包括无人机、可视化展示系统和可视化显示控制模块，其特征在于：所述无人机上设有图传模块Ⅰ、数传模块Ⅰ和定位模块，所述图传模块、数传模块和定位模块连接有设在无人机内的微处理器，所述可视化展示系统包括图传模块Ⅱ和数传模块Ⅱ，所述可视化显示控制模块连接有可视化展示系统，本发明不仅可以实时显示无人机的各种参数信息图像信息，还可以实现简单操作即可转动相机方位，让操作者有身临其境的感觉，视觉效果极佳，拥有完美的可视化界面，操作简单，控制实时准确，极大的方便无人机实时监控。 | ||||||
| 3 | 用于管理飞行器系统的方法、系统及计算机可读介质 | CN201510050334.4 | 2015-01-30 | CN104820426A | 2015-08-05 | 蒂博·普; 弗朗索瓦·比龙; 马埃尔·梅斯冈 |
| 公开了用于通过专用界面管理飞行器系统的方法、系统及计算机可读介质。用于实现本文所描述的主题的方法的一个方面包括：在被配置成用于管理飞行器系统的至少一个交互式界面处，显示表示至少一个或更多个系统部件的至少一个或更多个图形对象，显示表示能量流的循环方向的至少一个或更多个能量流图标，以及通过对所述至少一个或更多个图形对象的用户动作来与所述至少一个或更多个系统部件进行交互。 | ||||||
| 4 | GROUND-PROJECTILE GUIDANCE SYSTEM | US15244431 | 2016-08-23 | US20170191809A1 | 2017-07-06 | Gordon L. Harris; Stephen L. Harris |
| A range extension unit extends the range of a guided mortar bomb. The range extension unit includes a housing interface defining an internal cup that receives a rear portion of a guided mortar bomb, wherein the housing interface covers a rear portion of the mortar bomb. The housing interface, when coupled to the mortar bomb, collectively forms an aerodynamically shaped body with the mortar bomb. At least two deployable wings are attached to the housing interface, wherein the wings transition between a retracted state and a deployed state. | ||||||
| 5 | Procedure and device for improving the maneuverability of an aircraft during the approach to landing and flare-out phases | US11182864 | 2005-07-18 | US20070057114A1 | 2007-03-15 | Stéphane Boissenin; Jacques Rosay |
| The process improves the maneuverability of an aircraft during the approach to landing and then flare-out phases, the aircraft being equipped with air brakes. According to the process, the air brakes are put in a first deployed position during the approach phase, and as a function of a representative parameter of a given altitude and in case of a steep angle approach, they are actuated to transition to a second more retracted position than the first position so as to achieve a flare-out allowing to essentially maintain the same angle of incidence, corresponding in case of a steep angle approach to achieve a flare-out with habitual exterior piloting references during the flare-out phase. | ||||||
| 6 | Method and apparatus for improving the maneuverability of the aircraft at the time of the cause approach phase and subsequent nose before landing | JP2007520864 | 2005-07-13 | JP2008506577A | 2008-03-06 | ボワスナン，ステファヌ; ローゼイ，ジャック |
| 本発明の方法により、着陸前の進入段階とその後の機首引き起こしの際に、エアブレーキを備えた航空機の操縦性が改善される。 この方法によると、着陸前の進入段階ではエアブレーキを広げられた第１の状態（曲線ＣＦＡＡ）にし、急角度で進入する場合には、所定の高度を表わすパラメータを考慮してそのエアブレーキを第１の状態よりも引っ込んだ第２の状態（曲線ＣＦＳＡ）に移行させる操作を行なうことで、急角度で進入する場合には、機首引き起こし段階を通じて通常の操縦の際の外部参照物を利用した機首引き起こしとほぼ同じ迎え角を維持することを可能にする機首引き起こしがなされる。 | ||||||
| 7 | 有線式ドローン群 | JP2016217345 | 2016-11-07 | JP2018075869A | 2018-05-17 | 能見 基彦; 関野 夕美子 |
| 【課題】複数のドローンを有線ケーブルで連結したドローン群であって、有線ケーブルが天然の物体や人工の物体に引っ掛かることなく、また絡まることがない有線式ドローン群および有線式ドローン群の制御方法を提供する。 【解決手段】複数のドローン1を有線ケーブル2によって直列に連結してドローン群を形成し、有線ケーブル2は、各ドローン1への給電および/または各ドローン1との通信を行う機能を有し、ドローン群の一端側のドローン1に、ドローン群の移動を制御する制御装置3を接続した。 【選択図】図1 |
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| 8 | 航空機管理装置、航空機、及び航空機の軌道算出方法 | JP2015143183 | 2015-07-17 | JP2017026190A | 2017-02-02 | 山崎 光一 |
| 【課題】航空機の役割に応じたより最適な軌道をより短時間で算出する航空機管理装置を提供する。 【解決手段】CPU12は予めHDD18に記憶されているプログラムを実行することにより、役割決定部50、軌道決定部52、及び最適解判定部54の機能を有する。役割決定部50は、航空機の役割を決定する。具体的には、役割決定部50は、統合目的関数、統合等式制約条件、及び統合不等式制約条件をHDD18から読み出し、航空機に設定した役割に応じて、統合目的関数、統合等式制約条件、及び統合不等式制約条件のインディケータ変数を1又は0とする。軌道決定部52は、役割決定部50によってインディケータ変数が1又は0とされた後の統合目的関数、統合等式制約条件、及び統合不等式制約条件に基づいて、最適軌道算出を行うことによって航空機の役割に応じた最適な軌道を算出する。 【選択図】図13 |
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| 9 | Method and apparatus for improving the maneuverability of the aircraft at the time of the cause approach phase and subsequent nose before landing | JP2007520864 | 2005-07-13 | JP5184884B2 | 2013-04-17 | ボワスナン，ステファヌ; ローゼイ，ジャック |
| 10 | Flight Control Augmentation System And Method For High Aspect Ratio Aircraft Including Motorglider Aircraft, Optionally Piloted Vehicles (OPVs) and Unpiloted Air Vehicles (UAVs) | US14677512 | 2015-04-02 | US20160318601A1 | 2016-11-03 | Marc Arnold |
| A control augmentation system for high aspect ratio aircraft has aileron/flaperon and throttle position sensors; spoiler and flap controls; a mode switch with manual, and landing modes; and a controller driving left and right spoiler and flap servos, the controller including at least one processor with memory containing firmware configured to: when the mode switch is in manual mode, drive both spoiler servos to a symmetrical position according to the spoiler control; when the mode switch is in landing mode, drive the left spoiler to a position dependent on aileron and throttle position, and the right spoiler to a position dependent on aileron and throttle position, the left and right spoiler positions differing whenever ailerons are not centered, and an average of spoiler positions is more fully deployed when the throttle position is at a low-power setting than when the throttle position is at a high-power setting. | ||||||
| 11 | AIRCRAFT PILOTING ASSISTANCE SYSTEM AND METHOD | US15063940 | 2016-03-08 | US20160272336A1 | 2016-09-22 | Sébastien LEPAGE |
| A piloting assistance system for an aircraft during manual piloting is provided. The piloting assistance system includes a monitoring module, configured to compare an acceleration of the aircraft to an authorized acceleration that depends on a speed of the aircraft, an acceleration control module, able to be switched between an activated state and a deactivated state, and configured so as, in the activated state, excluding the deactivated state, to generate a control signal of at least one control device of the acceleration of the aircraft to push the acceleration of the aircraft toward the authorized acceleration range, in order to keep or push the speed of the aircraft in a predefined usage speed range, the monitoring module being configured to activate the acceleration control module when the acceleration of the aircraft is not comprised in the authorized acceleration range. | ||||||
| 12 | Method, device, and computer redable media for automatic management of configuration and reconfiguration of a plurality of systems of an aircraft | US13905907 | 2013-05-30 | US09002541B2 | 2015-04-07 | Samir Fezzazi; Stephane Porez |
| Methods, devices, and computer readable media are disclosed for automatic management of configuration and reconfiguration procedures of a plurality of systems of an aircraft, for example and without limitation, for aircraft operational and maintenance uses. In some aspects, a centralized device for automatic management of configuration and reconfiguration procedures of a plurality of systems of an aircraft includes a central unit for automatically generation control commands for automatic control of at least one action to be executed for one or both of the configuration or reconfiguration procedure, data links for automatic dispatch of control commands to corresponding systems for automatic execution. | ||||||
| 13 | METHOD, DEVICE, AND COMPUTER REDABLE MEDIA FOR AUTOMATIC MANAGEMENT OF CONFIGURATION AND RECONFIGURATION OF A PLURALITY OF SYSTEMS OF AN AIRCRAFT | US13905907 | 2013-05-30 | US20140200747A1 | 2014-07-17 | Samir FEZZAZI; Stephane POREZ |
| Methods, devices, and computer readable media are disclosed for automatic management of configuration and reconfiguration procedures of a plurality of systems of an aircraft, for example and without limitation, for aircraft operational and maintenance uses. In some aspects, a centralized device for automatic management of configuration and reconfiguration procedures of a plurality of systems of an aircraft includes a central unit for automatically generation control commands for automatic control of at least one action to be executed for one or both of the configuration or reconfiguration procedure, data links for automatic dispatch of control commands to corresponding systems for automatic execution. | ||||||
| 14 | Procedure and device for improving the maneuverability of an aircraft during the approach to landing and flare-out phases | US12136887 | 2008-06-11 | US07896293B2 | 2011-03-01 | Stéphane Boissenin; Jacques Rosay |
| The process improves the maneuverability of an aircraft during the approach to landing and then flare-out phases, the aircraft being equipped with air brakes. According to the process, the air brakes are put in a first deployed position during the approach phase, and as a function of a representative parameter of a given altitude and in case of a steep angle approach, they are actuated to transition to a second more retracted position than the first position so as to achieve a flare-out allowing to essentially maintain the same angle of incidence, corresponding in case of a steep angle approach to achieve a flare-out with habitual exterior piloting references during the flare-out phase. | ||||||
| 15 | Procedure and device for improving the maneuverability of an aircraft during the approach to landing and flare-out phases | US11182864 | 2005-07-18 | US07614587B2 | 2009-11-10 | Stéphane Boissenin; Jacques Rosay |
| The process improves the maneuverability of an aircraft during the approach to landing and then flare-out phases, the aircraft being equipped with air brakes. According to the process, the air brakes are put in a first deployed position during the approach phase, and as a function of a representative parameter of a given altitude and in case of a steep angle approach, they are actuated to transition to a second more retracted position than the first position so as to achieve a flare-out allowing to essentially maintain the same angle of incidence, corresponding in case of a steep angle approach to achieve a flare-out with habitual exterior piloting references during the flare-out phase. | ||||||
| 16 | Integrated propulsion/lift/control system for aircraft and ship applications | US140970 | 1998-08-27 | US5975462A | 1999-11-02 | Maximilian F. Platzer |
| A new method for boundary layer energization and boundary layer propulsionor use on vehicles moving through fluids, which comprises mounting small airfoils parallel or perpendicular to the vehicle's surface, said airfoils being embedded within the said vehicle's boundary layer and juxtaposed the surface of said vehicle, said airfoils being approximately the height of the boundary layer thickness and exciting said airfoils into flapping oscillation parallel to the chord plane of said airfoils, said oscillation at a frequency up to 100 cycles per second at an amplitude up to 20 percent of the chord length of said airfoil, whereby flow separation is delayed or suppressed which enables the redesign of said vehicle. | ||||||
| 17 | Airplane rudder and controls | US502057 | 1974-08-30 | US3931943A | 1976-01-13 | Don M. Westergren; Walter E. Mooney |
| In a small airplane, a combination nose wheel, shroud and rudder is provided. The shroud encloses all but a lower cord of the wheel. The shroud has an aerodynamic profile and is pivotable for inflight guidance by a pair of actuator pedals pivoted to the interior structure of the cabin. The shroud is directionally operatable by the pedals operating through a bellcrank and connecting rod. The shroud is returnable to a normal straight flight condition by airstream forces alone. An additional interconnection is provided from the shroud for simultaneously controlling a conventional rear rudder. | ||||||
| 18 | 항공기 종축 제어 모듈 및 그 모듈을 이용한 항공기 종축 제어 방법 | KR1020120036498 | 2012-04-09 | KR101273835B1 | 2013-06-11 | 김종섭 |
| PURPOSE: An aircraft longitudinal axis control module and an aircraft longitudinal axis control method using the module are provided to stably increase or decrease the altitude of the aircraft. CONSTITUTION: An aircraft longitudinal axis control module includes an altitude control module(100) and a speed control module(200). The altitude control module generates a thrust control signal according to an altitude control input and outputs the signal to an aircraft. The speed control module generates a pitch orientation angle control signal according to a speed control input and outputs the signal to the aircraft. The altitude control module controls an altitude increasing and decreasing an attack angle of the air craft according to the variation of thrust while controlling the longitudinal axis of the aircraft. The speed control module controls a speed by increasing and decreasing the drag of the aircraft according to the variation of a pitch orientation angle. [Reference numerals] (1) Altitude command; (100) Altitude control module; (101) Thrust command; (11) Altitude feedback; (2) Speed command; (200) Speed control module; (21) Speed feedback; (300) Pitch control module; (301) Horizontal profit command; (311) Pitch orientation angle feedback; (312) Pitch angular speed feedback; (400) Aircraft | ||||||
| 19 | FLIGHT CONTROL AUGMENTATION SYSTEM AND METHOD FOR HIGH ASPECT RATIO AIRCRAFT | EP15162566.2 | 2015-04-07 | EP2930102B1 | 2017-11-01 | Arnold, Marc |
| 20 | Methods, systems and computer readable media for managing aircraft systems | EP15153440.1 | 2015-02-02 | EP2902324A1 | 2015-08-05 | Poux, Thibaut; Mesguen, Maël; Buron, François |
Methods, systems, and computer readable media are disclosed for managing an aircraft's systems through a dedicated interface. One aspect of a method for implementing the subject matter described herein includes at least one interactive interface configured for managing an aircraft system, displaying at least one or more graphic object representing at least one or more system component, displaying at least one or more energy flow icon representing the direction of circulation of an energy flow, and interacting with the at least one or more system component through a user action on the at least one or more graphic object.
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