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11. 发明申请

WO2010104601A1 HEAT ENGINE WITH REGENERATOR AND TIMED GAS EXCHANGE 审中-公开
标题翻译：具有再生器和定时气体交换的热发动机
公开(公告)号：WO2010104601A1
公开(公告)日：2010-09-16
申请号：PCT/US2010/000758
申请日：2010-03-12
申请人： SEALE, Joseph, B. , BERGSTROM, Gary
发明人： SEALE, Joseph, B. , BERGSTROM, Gary
IPC分类号： F02K5/00
CPC分类号： F02G1/0435 , F01K17/06 , F01K19/10
摘要： A Stirling-like system incorporating a heater, a displacer and a regenerator is intermittently coupled to an external system via valves, providing pneumatic power while ridding waste heat. The external system is commonly a Rankine cycle, sharing the working fluid of the Stirling-like system, and can be used for heat pumping, distillation and drying. The Stirling working fluid and the Rankine working fluid are the same material and are exchanged between the two systems. A dual Stirling-like system mates a heat engine with a heat pump, sharing the same pressure-containment, with the dual system intermittently coupled to external environments for convective exchange of heat and cold.
摘要翻译：包含加热器，置换器和再生器的斯特林式系统通过阀间歇地耦合到外部系统，在消除废热的同时提供气动功率。外部系统通常是兰金循环，共享斯特林式系统的工作流体，可用于热泵，蒸馏和干燥。斯特林工作流体和兰金工作流体是相同的材料，并在两个系统之间交换。双重斯特林式系统将热力发动机与热泵相配合，共享相同的压力容纳，双重系统间歇地耦合到外部环境，用于对流换热和冷热。

12. 发明申请

WO2016109408A4 ROTARY WING VTOL WITH FIXED WING FORWARD FLIGHT MODE 审中-公开
标题翻译：带固定翼向前飞行模式的旋转翼垂直
公开(公告)号：WO2016109408A4
公开(公告)日：2016-08-18
申请号：PCT/US2015067630
申请日：2015-12-28
申请人： SEALE JOSEPH B , SLOAN WALKER M
发明人： SEALE JOSEPH B , SLOAN WALKER M
IPC分类号： B64C27/24
CPC分类号： B64C27/24 , B64C27/16 , B64C27/18 , B64C29/0033
摘要： An aircraft's two wings and joined thruster propellers or turbines serve as rotary wings in helicopter mode and as fixed wings in airplane mode. The thrusters along the wingspans or at the wing tips drive both rotary wing rotation and airplane flight. Large-angle controlled feathering about the pitch change axes of the left and right wings and thrusters allows them to rotate, relative to each other, between facing and thrusting forward in the same direction for airplane flight or facing and thrusting oppositely for helicopter flight. Optional controls include: helicopter cyclic and collective pitch; airplane roll by differential wing pitch; yaw by differential prop thrust; fuselage pitch by wing pitch change and prop thrust change interacting with an underslung craft e.g.; and fuselage yaw control independent of rotor rotation via a powered rotary mast coupling or a tail responsive to rotor downwash. A teetering rotor hub is a further option.
摘要翻译：飞机的两个机翼和连接的推进器螺旋桨或涡轮机在直升机模式下用作旋翼，在飞机模式下用作固定翼。沿着翼展或翼尖的推进器驱动旋翼旋转和飞机飞行。左右翼和推进器的俯仰变化轴线的大角度控制羽化使得它们能够相对于彼此在面向之间旋转，并且以相同的方向向前推动用于飞机飞行或面向并且相反地用于直升机飞行的推进。可选控制包括：直升机循环和集体俯仰; 飞机按不同的机翼间距滚动; 通过差动推力推力偏航; 机翼俯仰变化和支撑推力变化引起的机身俯仰变化与下垂飞行器相互作用。机身偏航控制与转子旋转无关，通过动力旋转式桅杆联轴器或尾翼响应转子下冲。蹒跚的转子轮毂是另一种选择。

13. 发明申请

WO1986004801A1 NON-INVASIVE DETERMINATION OF MECHANICAL CHARACTERISTICS IN THE BODY 审中-公开
标题翻译：机构机械特性的非入侵性确定
公开(公告)号：WO1986004801A1
公开(公告)日：1986-08-28
申请号：PCT/US1986000351
申请日：1986-02-19
申请人： SEALE, Joseph, B.
IPC分类号： A61B05/02
CPC分类号： A61B8/04 , A61B3/16 , A61B5/02133 , A61B5/02216 , A61B5/02233 , A61B5/205
摘要： A non-invasive system and method for inducing vibrations in a selected element of the human body and detecting the nature of responses for determining mechanical characteristics of the element. The method includes the steps of: inducing multiple-frequency vibrations, including below 20 KHz, in a selected element e.g., in one embodiment, the carotid artery (40, Fig. 1), of the body by use of a driver (1); determining parameters of the vibrations exerted on the body by the driver; sensing variations of a dimension of the element of the body over time, including in response to the driver; correlating the variations with frequency components of operation of the driver below 20 KHz to determine corresponding frequency components of the variations; resolving the frequency components into components of vibrations mode shape; and determining the mechanical characteristics of the element on the basis of the parameters of vibrations exerted by the driver and of the components of vibration mode shape.

14. 发明专利

CA2972784A1 ROTARY WING VTOL WITH FIXED WING FORWARD FLIGHT MODE 未知
公开(公告)号：CA2972784A1
公开(公告)日：2016-07-07
申请号：CA2972784
申请日：2015-12-28
申请人： SEALE JOSEPH B , SLOAN WALKER M
发明人： SEALE JOSEPH B , SLOAN WALKER M
IPC分类号： B64C27/24
摘要： An aircraft's two wings and joined thruster propellers or turbines serve as rotary wings in helicopter mode and as fixed wings in airplane mode. The thrusters along the wingspans or at the wing tips drive both rotary wing rotation and airplane flight. Large-angle controlled feathering about the pitch change axes of the left and right wings and thrusters allows them to rotate, relative to each other, between facing and thrusting forward in the same direction for airplane flight or facing and thrusting oppositely for helicopter flight. Optional controls include: helicopter cyclic and collective pitch; airplane roll by differential wing pitch; yaw by differential prop thrust; fuselage pitch by wing pitch change and prop thrust change interacting with an underslung craft e.g.; and fuselage yaw control independent of rotor rotation via a powered rotary mast coupling or a tail responsive to rotor downwash. A teetering rotor hub is a further option.

15. 发明专利

AU3980601A A solenoid for efficient pull-in and quick landing 未知
公开(公告)号：AU3980601A
公开(公告)日：2001-09-03
申请号：AU3980601
申请日：2001-02-21
申请人： SEALE JOSEPH B , BERGSTROM GARY E
发明人： SEALE JOSEPH B , BERGSTROM GARY E
IPC分类号： F16K31/06 , H01F7/08 , H01F7/16 , H01F7/18 , F16K11/00 , H01F7/00
摘要： A solenoid with improved pull-in and landing characteristics. As a solenoid armature closes toward contact with the pole faces of a yoke, a geometric redistribution of a constant total flux causes the force to increase with decreasing gap. Latching force at saturation is maximized when the latching contact area matches the tightest bottleneck in the flux path. The addition of ferromagnetic area not making latching contact preserves the maximum latching force, increases power efficiency for pulling at a distance, and increases the flux redistribution effect of increasing force with decreasing gap at constant flux. The extra constant-flux force change at small gaps may be abrupt, for a high deceleration followed by a quick passive force increase to latch with low impact, or gradual, for tight servo control and very low impact. Conductive material can provide selective inductive damping near latching. Armature mass can be kept low despite the extra ferromagnetic area.

16. 发明专利

AU2015374294B2 Rotary wing VTOL with fixed wing forward flight mode 未知
公开(公告)号：AU2015374294B2
公开(公告)日：2020-03-12
申请号：AU2015374294
申请日：2015-12-28
申请人： SEALE JOSEPH B , SLOAN WALKER M
发明人： SEALE JOSEPH B , SLOAN WALKER M
IPC分类号： B64C27/24
摘要： An aircraft's two wings and joined thruster propellers or turbines serve as rotary wings in helicopter mode and as fixed wings in airplane mode. The thrusters along the wingspans or at the wing tips drive both rotary wing rotation and airplane flight. Large-angle controlled feathering about the pitch change axes of the left and right wings and thrusters allows them to rotate, relative to each other, between facing and thrusting forward in the same direction for airplane flight or facing and thrusting oppositely for helicopter flight. Optional controls include: helicopter cyclic and collective pitch; airplane roll by differential wing pitch; yaw by differential prop thrust; fuselage pitch by wing pitch change and prop thrust change interacting with an underslung craft e.g.; and fuselage yaw control independent of rotor rotation via a powered rotary mast coupling or a tail responsive to rotor downwash. A teetering rotor hub is a further option.

17. 发明专利

AU2583201A Flat lamination solenoid 未知
公开(公告)号：AU2583201A
公开(公告)日：2001-07-03
申请号：AU2583201
申请日：2000-12-19
申请人： BERGSTROM GARY E , SEALE JOSEPH B
发明人： BERGSTROM GARY E , SEALE JOSEPH B
IPC分类号： H01F7/08 , H01F7/16 , H01F3/00 , H01F5/00 , H02K33/04
摘要： A variable reluctance solenoid includes an armature and a yoke located axially beyond one end of the armature. Magnetic attraction across an axial gap between the armature and yoke causes the armature to move axially and close the gap. The armature includes ferromagnetic laminations lying in a plane perpendicular to the axial direction. These laminations may include slots, proportioned and directed to combat eddy currents and reduce moving mass while avoiding creation of flux bottlenecks. The solenoid may have two yokes on opposite sides of the armature, providing reciprocating armature motion.

18. 发明专利

AU6056000A A spring for valve control in engines 未知
公开(公告)号：AU6056000A
公开(公告)日：2001-01-31
申请号：AU6056000
申请日：2000-06-23
申请人： BERGSTROM GARY E , SEALE JOSEPH B
发明人： SEALE JOSEPH B , BERGSTROM GARY E
IPC分类号： C07D263/18 , F16F1/06
摘要： An improved process for making chiral, alpha -methylated, alpha -substituted amino acids of the formula I wherein Y is a hydrogen atom and R2 is the residue of a natural or unnatural amino acid, in which process an oxazolidinone of the formula II is formed by reacting a protected amino acid of the formula IA wherein Y is a protecting group, with an aldehyde of the formula RCHO, or an equivalent thereof, in the presence of a chlorinating agent and a Lewis acid. The group R2 is introduced into the oxazolidinone intermediate of formula II in a conventional manner, and subsequent hydrolysis and deprotection, both carried out in a conventional manner, yield the chiral, alpha -methylated, alpha -substituted amino acid.

19. 发明专利

AU2015374294A1 Rotary wing VTOL with fixed wing forward flight mode 未知
公开(公告)号：AU2015374294A1
公开(公告)日：2017-08-17
申请号：AU2015374294
申请日：2015-12-28
申请人： SEALE JOSEPH B , SLOAN WALKER M
发明人： SEALE JOSEPH B , SLOAN WALKER M
IPC分类号： B64C27/24
摘要： An aircraft's two wings and joined thruster propellers or turbines serve as rotary wings in helicopter mode and as fixed wings in airplane mode. The thrusters along the wingspans or at the wing tips drive both rotary wing rotation and airplane flight. Large-angle controlled feathering about the pitch change axes of the left and right wings and thrusters allows them to rotate, relative to each other, between facing and thrusting forward in the same direction for airplane flight or facing and thrusting oppositely for helicopter flight. Optional controls include: helicopter cyclic and collective pitch; airplane roll by differential wing pitch; yaw by differential prop thrust; fuselage pitch by wing pitch change and prop thrust change interacting with an underslung craft e.g.; and fuselage yaw control independent of rotor rotation via a powered rotary mast coupling or a tail responsive to rotor downwash. A teetering rotor hub is a further option.

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