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公开(公告)号:US20190241262A1
公开(公告)日:2019-08-08
申请号:US16269515
申请日:2019-02-06
摘要: A hypersonic vehicle includes a body; a first engine secured to the body, the first engine is configured to create forward thrust at a first flight regime; a second engine secured to the body, the second engine is configured to create forward thrust at a second flight regime; and the hypersonic vehicle transitions between the first engine and the second engine during the first flight regime and the second flight regime.
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公开(公告)号:US20180370651A1
公开(公告)日:2018-12-27
申请号:US15629952
申请日:2017-06-22
CPC分类号: B64D45/00 , B60L3/12 , B60L2200/10 , B64D27/12 , B64D27/16 , B64D27/24 , B64D2027/026 , B64D2045/0085 , B64D2221/00 , F01D21/003 , F05D2220/323 , F05D2220/76 , F05D2260/80 , F05D2260/821 , F05D2270/309 , F05D2270/335 , G01M15/14 , G05B23/0283 , G07C5/0808
摘要: Systems and methods for estimating engine and electrical machine health are provided. The systems and methods therefore include features that provide for improved health estimates of one or more engines and/or electrical machines of one or more engines having an electrical machine embedded therein or coupled thereto. In particular, the systems and methods therefore include features for utilizing sensed or measured operating parameters of the electrical machines and/or operating parameters of the prime mover to estimate the health of the prime mover and/or the electrical machines embedded therein or coupled thereto.
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公开(公告)号:US20180354632A1
公开(公告)日:2018-12-13
申请号:US15619673
申请日:2017-06-12
CPC分类号: B64D27/24 , B64D27/02 , B64D27/10 , B64D31/02 , B64D31/06 , B64D35/08 , B64D2027/026 , F01D15/10 , F02C6/00 , F02C6/14 , F02C7/262 , F02C7/268 , F02C7/36 , F02K5/00 , F05D2220/76
摘要: A hybrid-electric propulsion system for an aircraft includes a propulsor and a turbomachine. The turbomachine includes a high pressure turbine drivingly coupled to a high pressure compressor through a high pressure spool. The hybrid electric propulsion system further includes an electrical system including a first electric machine, a second electric machine, and an electric energy storage unit electrically connectable to the first and second electric machines. The first electric machine is coupled to the high pressure spool of the turbomachine and the second electric machine is coupled to the propulsor for driving the propulsor to provide a propulsive benefit for the aircraft. The hybrid electric propulsion system also includes a controller configured to provide electrical power from an electric power source to the first electric machine to drive the first electric machine to start, or assist with starting, the turbomachine.
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公开(公告)号:US20180327104A1
公开(公告)日:2018-11-15
申请号:US15919970
申请日:2018-03-13
CPC分类号: B64D35/08 , B64D27/10 , B64D27/14 , B64D27/20 , B64D35/02 , B64D2027/026 , F01D13/003 , F02C6/02 , F02C6/206 , F02K3/04 , F02K3/12 , F05D2220/323 , F05D2260/40311 , F05D2260/84
摘要: An aircraft propulsion assembly including a fan. It include a first engine and a second engine which are not coaxial and a mechanical energy transmission device configured to enable the fan to be conjointly rotated by the first engine and the second engine. This allows an aircraft propulsion assembly to be produced of which the fan may be positioned so as to ingest the boundary layer formed at the surface of a member of the aircraft equipped with the propulsion assembly, while allowing operating modes in the case of certain failures, and certification for commercial use of an aircraft equipped with such a propulsion assembly, to which the invention also relates.
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公开(公告)号:US20180319477A1
公开(公告)日:2018-11-08
申请号:US15972087
申请日:2018-05-04
申请人: Andrew X. Yakub
发明人: Andrew X. Yakub
CPC分类号: B64B1/58 , B64B1/70 , B64C39/001 , B64C2201/022 , B64C2201/042 , B64C2201/066 , B64D27/24 , B64D2027/026 , B64D2041/005 , B64D2211/00 , H01M8/186 , H01M2250/20
摘要: The zero carbon emission vehicle as disclosed herein may include a condenser for extracting fluid water from the atmosphere, an electrolyzer for generating hydrogen from the fluid water, and one or more deformable fluid-retaining chambers that couple thereto for selectively adjusting the buoyancy and altitude of the zero carbon emission vehicle in real-time, to maintain the air vehicle in flight substantially without needing to land and refuel the air vehicle. Solar panels provide the energy for the described systems, and the energy from the solar panels can be stored in the form of hydrogen gas which gives buoyancy to the air vehicle.
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公开(公告)号:US20180283292A1
公开(公告)日:2018-10-04
申请号:US15953209
申请日:2018-04-13
CPC分类号: F02D29/02 , B64C39/024 , B64C2201/024 , B64C2201/042 , B64C2201/044 , B64C2201/066 , B64C2201/086 , B64C2201/088 , B64C2201/104 , B64C2201/108 , B64C2201/16 , B64D27/02 , B64D27/24 , B64D31/00 , B64D41/00 , B64D2027/026 , Y02T50/44 , Y02T50/64
摘要: An unmanned aircraft includes a propulsion system having a diesel or kerosene internal combustion engine and a charger device for engine charging. The propulsion system can be a hybrid propulsion system or a parallel hybrid propulsion system.
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公开(公告)号:US20180281931A1
公开(公告)日:2018-10-04
申请号:US15475401
申请日:2017-03-31
发明人: Brandon Wayne Miller , Randy M. Vondrell , Patrick Michael Marrinan , Paul Robert Gemin , Nicholas Taylor Moore
CPC分类号: B64C21/06 , B64C2230/04 , B64D27/18 , B64D27/24 , B64D2027/026 , B64D2221/00 , F01D15/10 , F02K5/00 , F05D2220/36
摘要: An aeronautical propulsion system includes a fan having a plurality of fan blades rotatable about a central axis and defining a fan pressure ratio, FPR. The propulsion system also includes an electric motor mechanically coupled to the fan for driving the fan, the electric motor including a number of poles, npoles, and defining a maximum power, P. The relationship between the fan pressure ratio, FPR, of the fan, the number of poles, npoles, of the electric motor, and the maximum power, P, of the electric motor is defined by an equation: n pole P = C 1 · e - 9.062 · FPR + C 2 · e - 1.2604 · FPR ; wherein C1 is a constant having a value between 22,000 and 52,000, wherein C2 is a constant having a value between 4.0 and 9.8, and wherein e is Euler's number.
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8.
公开(公告)号:US10071801B2
公开(公告)日:2018-09-11
申请号:US15080167
申请日:2016-03-24
发明人: David D. North , Mark J. Aull , William J. Fredericks , Mark D. Moore , Paul M. Rothhaar , William T. Hodges , Zachary R. Johns
CPC分类号: B64C29/0033 , B64C5/02 , B64C25/52 , B64C29/0025 , B64C39/024 , B64C2201/042 , B64C2201/044 , B64D27/24 , B64D2027/026 , Y02T50/44 , Y02T50/64
摘要: Systems, methods, and devices provide a vehicle, such as an aircraft, with rotors configured to function as a tri-copter for vertical takeoff and landing (“VTOL”) and a fixed-wing vehicle for forward flight. One rotor may be mounted at a front of the vehicle fuselage on a hinged structure controlled by an actuator to tilt from horizontal to vertical positions. Two additional rotors may be mounted on the horizontal surface of the vehicle tail structure with rotor axes oriented vertically to the fuselage. For forward flight of the vehicle, the front rotor may be rotated down such that the front rotor axis may be oriented horizontally along the fuselage and the front rotor may act as a propeller. For vertical flight, the front rotor may be rotated up such that the front rotor axis may be oriented vertically to the fuselage, while the tail rotors may be activated.
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公开(公告)号:US20180251228A1
公开(公告)日:2018-09-06
申请号:US15450990
申请日:2017-03-06
发明人: Jonathan S. Sands , Ryan C. Humes
IPC分类号: B64D31/00 , F02B63/04 , F01D15/10 , F01D15/12 , F01D21/00 , B64D27/24 , B64D35/04 , B64D35/08
CPC分类号: B64D35/08 , B63H23/12 , B64D27/02 , B64D27/24 , B64D31/00 , B64D31/06 , B64D31/14 , B64D35/04 , B64D2027/026 , F01D15/10 , F01D15/12 , F01D21/003 , F02B63/04 , F02D25/04 , F05D2220/32 , Y02T50/62
摘要: A propulsion system that includes a plurality of power units, a plurality of propulsors, where respective power units of the plurality of power units are controllably coupled to the plurality of propulsors, and a controller configured to receive a desired throttle value corresponding to a desired propulsive force, determine a number of power units of the plurality of power units to be coupled to the plurality of propulsors to achieve the desired propulsive force based on a respective power value associated with each respective power unit of the plurality of power units, and cause the number of power units of the plurality of power units to be coupled to the plurality of propulsors.
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公开(公告)号:US20180230845A1
公开(公告)日:2018-08-16
申请号:US15430052
申请日:2017-02-10
CPC分类号: F01D15/10 , B64C11/30 , B64D27/18 , B64D27/24 , B64D2027/026 , F02C6/00 , F02C6/14 , F02C7/32 , F02C7/36 , F02K3/06 , F02K5/00 , F05D2220/323 , F05D2220/36 , F05D2220/76
摘要: A propulsion system for an aircraft includes a turbomachine, a primary fan, and an electric machine. The turbomachine includes a first turbine and a second turbine, with at least one of the first turbine or second turbine operably connected to the electric machine and the second turbine driving the primary fan. The propulsion system additionally includes an auxiliary propulsor assembly configured to be mounted at a location away from the turbomachine and the primary fan. The electric machine is in electrical communication with the auxiliary propulsor assembly for transferring power with the auxiliary propulsor assembly during operation of the propulsion system.
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