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公开(公告)号：US09483058B2
公开(公告)日：2016-11-01
申请号：US14733228
申请日：2015-06-08
Applicant: ROLLS-ROYCE PLC
Inventor： Matthew Moxon
CPC classification number: G05D1/042 , B64D43/02 , G01C23/005 , G05D1/0005 , G05D1/0055 , G05D1/0607
Abstract: A computer-implemented method of controlling an aircraft including, determining whether a change in altitude at a predetermined thrust-setting can be performed, the determination including: determining a climb-requirement including initial and final altitudes and a required range of airspeeds at the final altitude; determining aircraft performance data including a thrust at the final altitude at the thrust-setting, an initial airspeed at the initial altitude and an aircraft total mass at the initial altitude; using the aircraft performance data to determine a final airspeed and drag at the final altitude if a change in altitude at the predetermined setting were performed; determining whether thrust at the final altitude at the thrust-settings and airspeed is greater than drag; and providing a signal indicating whether the calculated final airspeed falls within the required range of airspeeds, and whether the thrust at the final altitude and airspeed at the cruise thrust-setting is greater than drag.
Abstract translation: 一种控制飞行器的计算机实现方法，包括：确定是否可以执行预定推力设定处的高度变化，所述确定包括：确定包括初始和最终高度的爬升要求以及最终的空速所需的空速范围 高度; 确定飞机性能数据，包括在推力设定下的最终高度处的推力，初始高度处的初始空速和初始高度处的飞行器总质量; 如果执行了预定设置的高度变化，则使用飞机性能数据来确定最终空速并在最终高度拖动; 确定在推力设定和空速下的最终高度的推力是否大于阻力; 并且提供指示所计算的最终空速是否落在空速的所需范围内的信号，以及在巡航推力设定处的最终高度和空速的推力是否大于阻力。
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公开(公告)号：US11113979B2
公开(公告)日：2021-09-07
申请号：US16429156
申请日：2019-06-03
Applicant: ROLLS-ROYCE plc
Inventor： Matthew Moxon
Abstract: An aerodrome system for an aerodrome is provided. The aerodrome system comprises a plurality of light emitting elements configured to emit light from a surface of the aerodrome upon which aircraft may take-off, land and manoeuvre; and a controller operatively coupled to each of the light emitting elements so as to selectively control the light emitting elements, wherein the light emitting elements form pixels of a display and the controller is configured to control an image displayed by the display so as to display and demarcate at least one runway for aircraft to take-off or land, wherein the light emitting elements are spaced such that the controller may display the runway with a variable orientation and the controller is further configured to change the image displayed by the display so as to change the orientation of the runway.
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公开(公告)号：US10737759B2
公开(公告)日：2020-08-11
申请号：US16658432
申请日：2019-10-21
Applicant: ROLLS-ROYCE plc
Inventor： Matthew Moxon
Abstract: An aircraft has an internal combustion engine and a wing including a hollow structural member. The aircraft has an electrical network including: an electrical motor configured to drive an aircraft propulsor; at least one conductor configured to electrically couple the electrical motor and an electrical storage device; wherein the electrical conductor is formed of the hollow structural member of the aircraft wing.
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公开(公告)号：US10584616B2
公开(公告)日：2020-03-10
申请号：US15649800
申请日：2017-07-14
Applicant: ROLLS-ROYCE PLC
Inventor： Matthew Moxon
IPC: F01K25/04 , F02C1/10 , F01K25/00 , F01K7/00 , F02C9/00 , F02C6/18 , G01N21/53 , F01K25/10 , F02C9/24 , G01N21/84 , G01N21/03
Abstract: A turbomachinery control system for controlling supercritical working fluid turbomachinery. The control system includes a light emitter to project light through working fluid of the turbomachinery toward a primary light detector provided within a line of sight to the emitter. The system further includes one or more secondary light detectors spaced from the line of sight, and a controller determining one or both of an intensity of light detected by the primary detector relative to the detected light intensity by the secondary detector, and wavelength of light detected by the primary detector relative to wavelength of light detected by the secondary detector. The controller determines the working fluid proximity of the critical point based on one or both of the determined relative intensity and determined relative wavelength, and controlling an actuator to control turbomachinery inlet or outlet conditions in accordance with the working fluid determined proximity of the critical point.
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公开(公告)号：US10518863B2
公开(公告)日：2019-12-31
申请号：US15483721
申请日：2017-04-10
Applicant: ROLLS-ROYCE plc
Inventor： Matthew Moxon
Abstract: An aircraft has an internal combustion engine and a wing including a hollow structural member. The aircraft has an electrical network including: at least one alternating current electrical generator configured to be driven by the internal combustion engine; an electrical motor configured to drive an aircraft propulsor; at least one conductor configured to electrically couple the electrical motor and the electrical generator; wherein the electrical conductor is formed of the hollow structural member of the aircraft wing.
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Patent Agency Ranking
公开(公告)号：US10960984B2
公开(公告)日：2021-03-30
申请号：US16458321
申请日：2019-07-01
Applicant: ROLLS-ROYCE plc
Inventor： Matthew Moxon
IPC: B64D27/24
Abstract: A modular energy storage system within a vehicle, wherein the energy storage system comprises a plurality of discrete energy storage units which are movable within the vehicle and selectively securable in a variety of positions.
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公开(公告)号：US10794617B2
公开(公告)日：2020-10-06
申请号：US16142362
申请日：2018-09-26
Applicant: ROLLS-ROYCE plc
Inventor： Matthew Moxon
IPC: F25B11/04 , B64D27/02 , B64D35/04 , H01M10/613 , H01M10/625 , H01M10/6556 , H01M10/6567 , H01M10/663 , B64D13/06 , B64D27/24 , F02C7/14 , H01M8/04029 , H02K9/19 , H02K11/00
Abstract: A thermal management system comprises a first heat exchanger configured to exchange heat between a first component and a first working fluid, a first working fluid compressor downstream in first working fluid flow of the first heat exchanger and configured to compress the first working fluid, a second heat exchanger downstream in first working fluid flow of the compressor and configured to exchange heat between the first working fluid and a second working fluid and an expander downstream in first working fluid flow of the second heat exchanger, and configured to expand and cool first working fluid and deliver cooled first working fluid to the first heat exchanger. The system further comprises a third heat exchanger upstream in second working fluid flow of the second heat exchanger, and configured to exchange heat between a second component and the second working fluid.
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公开(公告)号：US10246197B2
公开(公告)日：2019-04-02
申请号：US15280170
申请日：2016-09-29
Applicant: ROLLS-ROYCE plc
Inventor： Rory D Stieger , Matthew Moxon , Mikko Mattila
Abstract: An aircraft (10) comprising a fuselage (12), the fuselage (10) comprising at least first and second inwardly tapering portions (20, 22) extending in a generally rearward direction from an aft end of the fuselage (12), each inwardly tapering portion (20, 22) comprising a boundary layer ingesting propulsor (36) mounted thereon.
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公开(公告)号：US09815559B2
公开(公告)日：2017-11-14
申请号：US14976414
申请日：2015-12-21
Applicant: ROLLS-ROYCE plc
Inventor： Matthew Moxon
CPC classification number: B64D27/10 , B64C39/10 , B64C2039/105 , B64D27/02 , B64D27/14
Abstract: An aircraft (2) comprises at least first and second gas turbine engines (10a, 10b) arranged in a line extending generally normally to an aircraft longitudinal axis (A), each engine (10a, 10b) comprising at least one compressor or turbine rotor disc (32-42) defining a respective rotational plane (D32-D42). The rotational plane (D32-D42) of at least one of the rotors (32-42) of at least one of the engines (10a, 10b) is angled relative to the aircraft longitudinal line (A) such that a burst disc plane of the respective engine (10a, 10b) is nonintersecting with another engine (10a, 10b).
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公开(公告)号：US09096312B2
公开(公告)日：2015-08-04
申请号：US14537112
申请日：2014-11-10
Applicant: ROLLS-ROYCE PLC
Inventor： Matthew Moxon
CPC classification number: B64C23/005 , B64C3/00 , B64C3/28 , B64C9/18 , B64C11/00 , B64C39/00 , B64D27/10 , B64D27/12 , B64D27/24 , Y02T50/44 , Y02T50/64
Abstract: An aircraft (40). The aircraft (40) comprises a propulsion system comprising a pair of internal combustion engines (10) each driving an electrical power generator (56), each electrical power generator (56) being electrically coupled to a plurality of electrically driven propulsors (46). The propulsors (46) are located forward of a leading edge (45) of the wings (44) such that an airstream generated by the propulsors flows over the wings (44) in use. Each internal combustion engine (10) and electrical generator (56) is mounted on a respective wing (44) outboard of a center of thrust (70) of the propulsors (46) on that wing (44).
Abstract translation: 飞机（40）。 飞机（40）包括推进系统，其包括一对驱动发电机（56）的内燃机（10），每个发电机（56）电耦合到多个电驱动推进器（46）。 推进器（46）位于翼（44）的前缘（45）的前方，使得由推进器产生的气流在使用中在翼（44）上流动。 每个内燃机（10）和发电机（56）安装在该翼（44）上的推进器（46）的推力中心（70）外侧的相应翼（44）上。
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