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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	Aft engine for an aircraft	US14859514	2015-09-21	US09821917B2	2017-11-21	Thomas Lee Becker; Kurt David Murrow; Patrick Michael Marrinan; Brandon Wayne Miller
A propulsion system for an aircraft is provided having an aft engine configured to be mounted to the aircraft at an aft end of the aircraft. The aft engine includes a fan rotatable about a central axis of the aft engine having a plurality of fan blades. The aft engine also includes a nacelle encircling the plurality of fan blades with one or more structural members extending between the nacelle and the mean line of the aircraft at a location forward of the plurality of fan blades when the aft engine is mounted to the aircraft. The aft engine may increase a net thrust of the aircraft when mounted to the aircraft.
2	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.
3	Aircraft having an aft engine	US14859549	2015-09-21	US09637217B2	2017-05-02	Patrick Michael Marrinan; Thomas Lee Becker; Kurt David Murrow; Jixian Yao
An aircraft is provided including a fuselage and an aft engine. The fuselage defines a top side, a bottom side, and a frustum located proximate an aft end of the aircraft. The frustum defines a top reference line extending along the frustum at a top side of the fuselage, and a bottom reference line extending along the frustum at a bottom side of the fuselage. The top and bottom reference lines meet at a reference point aft of the frustum. The fuselage further defines a recessed portion located aft of the frustum and indented inwardly from the bottom reference line. The aft engine includes a nacelle extending adjacent to the recessed portion of the fuselage such that the aft engine may be included with the aircraft without interfering with, e.g., a takeoff angle of the aircraft.
4	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.
5	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.
6	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.
7	航空機用後部エンジン	JP2016178125	2016-09-13	JP6401759B2	2018-10-10	トーマス・リー・ベッカー; カート・デーヴィッド・マロー; パトリック・マイケル・マリナン; ブランドン・ウェイン・ミラー

8	航空機用後部エンジン	JP2016178125	2016-09-13	JP2017061303A	2017-03-30	トーマス・リー・ベッカー; カート・デーヴィッド・マロー; パトリック・マイケル・マリナン; ブランドン・ウェイン・ミラー
【課題】胴体を有する航空機のための推進システムを提供する。【解決手段】推進システムは、航空機10の後端において航空機10に取り付けられるように構成された後部エンジンを有する。後部エンジンは、中心軸の周りで回転可能で複数のファンブレードを有するファンを含む。また、後部エンジンは、複数のファンブレードを取り囲むナセルを含み、後部エンジンが航空機10に取り付けられた場合に複数のファンブレードの前方の位置で、ナセルと航空機10の中点線との間に延びる1又は2以上の構造部材を備える。後部エンジンは、航空機10に取り付けられた場合に航空機10の正味出力を増加させることができる。【選択図】図1
9	非軸対称後部エンジン	JP2016178124	2016-09-13	JP6313829B2	2018-04-18	パトリック・マイケル・マリナン; トーマス・リー・ベッカー; カート・デイヴィッド・マロー; チーシアン・ヤオ

10	非軸対称後部エンジン	JP2016178124	2016-09-13	JP2017061302A	2017-03-30	パトリック・マイケル・マリナン; トーマス・リー・ベッカー; カート・デイヴィッド・マロー; チーシアン・ヤオ
【課題】表面摩擦抗力、形状抗力、および誘導抗力を含む航空機への抗力の影響を相殺し、エンジンの効率を改善するためのシステムを提案する。【解決手段】胴体(20)および後部エンジン(200)を含む航空機(10)が提供される。胴体は、航空機の前方端(14)から航空機の後方端(16)に向かって延在する。後部エンジンは、航空機の後方端に近接して胴体に取り付けられる。後部エンジンは、後部エンジンの中心軸の周りに回転可能で複数のファンブレードを含むファンを含む。後部エンジンはまた、複数のファンブレードを取り囲み、入口を定めるナセルを含む。入口は、後部エンジンの中心軸に対して非軸対称形を定めて、例えば、後部エンジンに最大限の空気流量が入ることを可能にする。【選択図】図1
11	後部エンジンを有する航空機	JP2016176048	2016-09-09	JP2017061300A	2017-03-30	パトリック・マイケル・マリナン; トーマス・リー・ベッカー,ジュニア; カート・デイヴィッド・マロー; チーシアン・ヤオ
【課題】胴体および後部エンジンを含む航空機が提供する。【解決手段】胴体20は上側202、下側204、および航空機10の後方端16に近接して配置された切頭体206を定める。切頭体は胴体の上側において切頭体に沿って延在する上基準線212、および胴体の下側において切頭体に沿って延在する下基準線214を定める。上基準線と下基準線は切頭体の後方の基準点215で交わる。切頭体の後方に位置し、下基準線から内向きに窪んでいる凹陥部216を胴体はさらに定める。後部エンジンは胴体の凹陥部に隣接して延在するナセル224を含み、その結果、航空機は、例えば、航空機の離陸角度と干渉することなく後部エンジンを含むことができる。【選択図】図4
12	Automotive drone deployment system	US15419804	2017-01-30	US09977431B2	2018-05-22	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.
13	Non-axis symmetric aft engine	US14859556	2015-09-21	US09884687B2	2018-02-06	Patrick Michael Marrinan; Thomas Lee Becker; Kurt David Murrow; Jixian Yao
An aircraft including a fuselage and an aft engine is provided. The fuselage extends from a forward end of the aircraft towards an aft end of the aircraft. The aft engine is mounted to the fuselage proximate the aft end of the aircraft. The aft engine includes a fan rotatable about a central axis of the aft engine, the fan including a plurality of fan blades. The aft engine also includes a nacelle surrounding the plurality of fan blades and defining an inlet. The inlet defines a non-axis symmetric shape with respect to the central axis of the aft engine to, e.g., allow for a maximum amount of airflow into the aft engine.
14	SYSTEM FOR THE DUAL MANAGEMENT OF ANTI-ICING AND BOUNDARY-LAYER SUCTION ON AN AEROFOIL OF AN AIRCRAFT	US15519038	2015-10-19	US20170217569A1	2017-08-03	Dimitri GUEUNING; Stephane DEBAISIEUX
For dual management of anti-icing and boundary-layer suction, a system for an aerofoil of an aircraft, including: a channel having a double function of anti-icing and boundary-layer suction; a double-function main pipe to which a device for monitoring the boundary-layer suction and a device for monitoring anti-icing are connected; an anti-icing air-intake pipe connecting the main pipe and the channel; a non-return valve enabling anti-icing air to go from the main pipe to the pipe; at least one suction-air collection pipe connecting the channel and the main pipe; and a non-return valve enabling suction air to pass from the pipe toward the main pipe.
15	AFT ENGINE FOR AN AIRCRAFT	US14859514	2015-09-21	US20170081035A1	2017-03-23	Thomas Lee Becker; Kurt David Murrow; Patrick Michael Marrinan; Brandon Wayne Miller
A propulsion system for an aircraft is provided having an aft engine configured to be mounted to the aircraft at an aft end of the aircraft. The aft engine includes a fan rotatable about a central axis of the aft engine having a plurality of fan blades. The aft engine also includes a nacelle encircling the plurality of fan blades with one or more structural members extending between the nacelle and the mean line of the aircraft at a location forward of the plurality of fan blades when the aft engine is mounted to the aircraft. The aft engine may increase a net thrust of the aircraft when mounted to the aircraft.
16	AIRCRAFT HAVING AN AFT ENGINE	US14859549	2015-09-21	US20170081013A1	2017-03-23	Patrick Michael Marrinan; Thomas Lee Becker; Kurt David Murrow; Jixian Yao
An aircraft is provided including a fuselage and an aft engine. The fuselage defines a top side, a bottom side, and a frustum located proximate an aft end of the aircraft. The frustum defines a top reference line extending along the frustum at a top side of the fuselage, and a bottom reference line extending along the frustum at a bottom side of the fuselage. The top and bottom reference lines meet at a reference point aft of the frustum. The fuselage further defines a recessed portion located aft of the frustum and indented inwardly from the bottom reference line. The aft engine includes a nacelle extending adjacent to the recessed portion of the fuselage such that the aft engine may be included with the aircraft without interfering with, e.g., a takeoff angle of the aircraft.
17	Automotive drone deployment system	US14333462	2014-07-16	US09409644B2	2016-08-09	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.
18	MICRO UNMANNED AERIAL VEHICLE AND METHOD OF CONTROL THEREFOR	US14738467	2015-06-12	US20150314870A1	2015-11-05	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.
19	MICRO UNMANNED AERIAL VEHICLE AND METHOD OF CONTROL THEREFOR	US14310307	2014-06-20	US20150160658A1	2015-06-11	Ivan Reedman; 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.
20	AFT ENGINE FOR AN AIRCRAFT	EP16188786.4	2016-09-14	EP3144226B1	2018-11-21	BECKER, Thomas Lee; MURROW, Kurt David; MARRINAN, Patrick Michael; MILLER, Brandon Wayne
A propulsion system for an aircraft (10) is provided having an aft engine configured to be mounted to the aircraft (10) at an aft end of the aircraft (10). The aft engine includes a fan (304) rotatable about a central axis of the aft engine having a plurality of fan blades (310). The aft engine also includes a nacelle (306) encircling the plurality of fan blades (310) with one or more structural members (308) extending between the nacelle (306) and the mean line (15) of the aircraft (10) at a location forward of the plurality of fan blades (310) when the aft engine is mounted to the aircraft (10). The aft engine may increase a net thrust of the aircraft (10) when mounted to the aircraft (10).

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