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1. 发明申请

US20210300541A1 TILTING MECHANISM WITH TELESCOPING ACTUATOR 有权
公开(公告)号：US20210300541A1
公开(公告)日：2021-09-30
申请号：US17211225
申请日：2021-03-24
申请人： Kitty Hawk Corporation
发明人： Pranay Sinha , Damon Vander Lind
IPC分类号： B64C29/00 , G05D1/10 , B64C13/48 , B64C39/12 , B64D27/24 , B64D27/26 , B60L53/00 , B60L50/64 , B64C27/82 , B64D27/02 , B64D31/06
摘要： A tiltrotor has a range of motion between a forward flight position and a hovering position, where a pylon and the tiltrotor are coupled via a telescoping actuator, a rigid bottom bar, and a fixed hinge that is attached between the rigid bottom bar and the tiltrotor. The tiltrotor moves from the forward flight position to the hovering position includes extending the telescoping actuator so that the tilt rotor rotates about the fixed hinge.

2. 发明授权

US10040541B2 Dynamic activation of pumps of a fluid power system 有权
公开(公告)号：US10040541B2
公开(公告)日：2018-08-07
申请号：US14626676
申请日：2015-02-19
申请人： The Boeing Company
发明人： Thomas M. Wilson , Edmond C. Chin , Mark W. Lesyna , Thomas R. Hasenoehrl
IPC分类号： B64C13/42 , B64C13/40 , B64C13/48 , B64C25/22 , B64C25/26 , B64C25/28 , F04B23/04 , F04B49/06 , F15B18/00 , F04B49/20
摘要： A method includes receiving pump cycle location data associated with a fluid power system. The fluid power system includes a plurality of pumps (including at least a first pump, a second pump, and a third pump). Based on the pump cycle location data having a first value, the method includes activating the first pump as a primary pump. Based on the pump cycle having a second value, the method includes activating the second pump as the primary pump. The method also includes activating the third pump as a secondary pump when the fluid power system is in a multiple-pump operating mode.

3. 发明授权

US4804520A Warm gas accumulator 失效
标题翻译：暖气蓄能器
公开(公告)号：US4804520A
公开(公告)日：1989-02-14
申请号：US548526
申请日：1983-11-03
申请人： William J. Richtenburg , Donald S. Jenkins
发明人： William J. Richtenburg , Donald S. Jenkins
IPC分类号： F15B1/02 , B01J7/00 , B64C13/48 , F42B10/64 , B01J8/02
CPC分类号： F42B10/64 , B01J7/00
摘要： A warm gas accumulator system 10 suitable for use in guidance vane-actuator systems of missiles comprising a tank 12 containing a supply of Tridyne gas, which tank 12 includes an internally mounted catalytic bed 26 and an internally mounted heat exchanger 18. A portion of the flow of Tridyne gas being discharged from the tank is first directed through the catalytic bed 26 and heat exchanger 18 for purposes of generating and transferring heat to the remainder of the contained Tridyne gas. Upon completing its circuit, the diverted portion of the flow is then mixed with the undiverted portion of the flow prior to discharge from the tank for pusposes of improving the volumetric flow rate of warm gas accumulator system 10.
摘要翻译：一种适合用于导弹的导向叶片 - 致动器系统的暖气蓄能器系统10，其包括含有供应Tridyne气体的罐12，该罐12包括内部安装的催化床26和内部安装的热交换器18.一部分首先通过催化床26和热交换器18引导从罐排出的Tridyne气体的流动，以便产生热量并传递给剩余的Tridyne气体。在完成其回路之后，流体的转向部分然后在从罐排出之前与流动的未流出部分混合，以提高暖气蓄能器系统10的体积流量。

4. 发明授权

US12071234B2 Hybrid power systems for different modes of flight 有权
公开(公告)号：US12071234B2
公开(公告)日：2024-08-27
申请号：US18244785
申请日：2023-09-11
申请人： Kitty Hawk Corporation
发明人： Pranay Sinha , Damon Vander Lind
IPC分类号： B64C29/00 , B60L50/64 , B60L53/00 , B64C13/48 , B64C27/82 , B64C39/12 , B64D27/02 , B64D27/24 , B64D27/40 , B64D31/06 , G05D1/00
CPC分类号： B64C29/0033 , B60L50/64 , B60L53/00 , B64C13/48 , B64C27/82 , B64C39/12 , B64D27/02 , B64D27/24 , B64D27/40 , B64D31/06 , G05D1/101 , B60L2200/10 , B64C2027/8209 , B64D27/026 , B64D27/402
摘要： During a cruise mode, a cruise-only propeller provides thrust using power from a first power source. During a hovering mode and a transitional mode, the propeller provides no thrust. The first power source includes an internal combustion engine; a second power source includes a high discharge rate battery and a high energy battery. The propeller is electrically connected to the first power source and is electrically disconnected from the second power source. During the hovering mode and the transitional mode, a hover-and-transition-only tiltrotor provides thrust using power from the second power source. During a vertical landing, the tiltrotor switches power sources from the high energy battery to the high discharge rate battery, independent of current draw. The tiltrotor is electrically disconnected from the first power source and is electrically connected to the second power source. During the cruise mode, the tiltrotor provides no thrust.

5. 发明公开

US20230234704A1 SHORT TAKEOFF AND LANDING VEHICLE WITH FORWARD SWEPT WINGS 审中-公开
公开(公告)号：US20230234704A1
公开(公告)日：2023-07-27
申请号：US18122502
申请日：2023-03-16
申请人： Kitty Hawk Corporation
发明人： Pranay Sinha , Damon Vander Lind
IPC分类号： B64C29/00 , G05D1/10 , B64C13/48 , B64C39/12 , B64D27/24 , B64D27/26 , B60L53/00 , B60L50/64 , B64C27/82 , B64D27/02 , B64D31/06
CPC分类号： B64C29/0033 , B60L50/64 , B60L53/00 , B64C13/48 , B64C27/82 , B64C39/12 , B64D27/02 , B64D27/24 , B64D27/26 , B64D31/06 , G05D1/101 , B60L2200/10 , B64C2027/8209 , B64D2027/026 , B64D2027/264
摘要： A vehicle includes a tilt rotor that is aft of a fixed wing and that is attached to the fixed wing via a pylon. A flight computer configured to instruct the tilt rotor to produce a maximum downward angle including by updating an actuator authority database associated with the flight computer to reflect the maximum downward angle, and generating a rotor control signal for the tilt rotor using the updated actuator authority database that reflects the maximum downward angle, wherein the maximum downward angle is adjustable.

6. 发明授权

US11634218B2 Redundant drive train for pylon mounted rotors 有权
公开(公告)号：US11634218B2
公开(公告)日：2023-04-25
申请号：US17362683
申请日：2021-06-29
申请人： Kitty Hawk Corporation
发明人： Pranay Sinha , Damon Vander Lind
IPC分类号： B64C29/00 , B64C13/48 , B64C39/12 , B64C27/82 , G05D1/10 , B64D27/24 , B64D27/26 , B60L53/00 , B60L50/64 , B64D27/02 , B64D31/06
摘要： A system includes an inboard tiltrotor subsystem and an outboard tiltrotor subsystem. The inboard tiltrotor subsystem includes an inboard pylon, an inboard tiltrotor, and a single and non-redundant drivetrain. The outboard tiltrotor subsystem includes an outboard pylon that is coupled to a wing and an outboard tiltrotor. The outboard tiltrotor has a range of motion and is coupled to the wing via the outboard pylon, such that the outboard tiltrotor is aft of the wing. The outboard tiltrotor subsystem further includes a redundant drivetrain (which has a plurality of motors and a plurality of motor controllers) that drives one or more blades and the one or more blades.

7. 发明授权

US09586676B2 Pneumatic positioning system 有权
标题翻译：气动定位系统
公开(公告)号：US09586676B2
公开(公告)日：2017-03-07
申请号：US14242817
申请日：2014-04-01
申请人： The Boeing Company
发明人： Jeffrey C. Coffman , David E. Blanding
IPC分类号： B64C13/00 , B64C13/36 , F15B15/19 , F15B15/14 , B64C13/42 , F15B11/064 , F15B15/08 , F15B20/00 , B64C13/48 , B64C13/50 , F15B11/12
CPC分类号： B64C13/36 , B64C13/42 , B64C13/48 , B64C13/50 , F15B11/064 , F15B11/123 , F15B15/088 , F15B15/149 , F15B15/19 , F15B20/002 , F15B2211/21 , F15B2211/8752 , F15B2211/8757 , F15B2211/8855 , Y02T50/44
摘要： Provided are mechanisms and processes for a pneumatic shaft positioning system. According to various examples, the pneumatic shaft positioning system includes a pyrotechnic valve that is configured to control the flow of gas from a pressurized gas source into a pressure chamber. The pressure chamber includes a first piston that is slidably coupled to the pressure chamber. When gas from the pressurized gas source fills the pressure chamber, the piston is configured to slide through the pressure chamber and force a shaft into a predetermined position.
摘要翻译：提供了用于气动轴定位系统的机构和过程。根据各种示例，气动轴定位系统包括烟火阀，其构造成控制从加压气体源进入压力室的气体流。压力室包括可滑动地联接到压力室的第一活塞。当来自加压气体源的气体填充压力室时，活塞构造成通过压力室滑动并迫使轴进入预定位置。

8. 发明授权

US07007897B2 Flight control actuation system 失效
标题翻译：飞行控制驱动系统
公开(公告)号：US07007897B2
公开(公告)日：2006-03-07
申请号：US10874729
申请日：2004-06-22
申请人： Paul T. Wingett , Louie T. Gaines , Paul S. Evans , James I. Kern
发明人： Paul T. Wingett , Louie T. Gaines , Paul S. Evans , James I. Kern
IPC分类号： B64C13/40 , B64C13/48
CPC分类号： B64C13/50 , B64C13/42
摘要： A flight control actuation system comprises a controller, electromechanical actuator and a pneumatic actuator. During normal operation, only the electromechanical actuator is needed to operate a flight control surface. When the electromechanical actuator load level exceeds 40 amps positive, the controller activates the pneumatic actuator to offset electromechanical actuator loads to assist the manipulation of flight control surfaces. The assistance from the pneumatic load assist actuator enables the use of an electromechanical actuator that is smaller in size and mass, requires less power, needs less cooling processes, achieves high output forces and adapts to electrical current variations. The flight control actuation system is adapted for aircraft, spacecraft, missiles, and other flight vehicles, especially flight vehicles that are large in size and travel at high velocities.
摘要翻译：飞行控制致动系统包括控制器，机电致动器和气动致动器。在正常操作期间，仅需要机电致动器来操作飞行控制表面。当机电致动器负载水平超过40安培正时，控制器激活气动执行器以抵消机电执行器负载，以帮助操纵飞行控制表面。来自气动负载辅助致动器的帮助使得能够使用尺寸和质量更小的机电致动器，需要更少的功率，更少的冷却过程，实现高输出力并适应于电流变化。飞行控制致动系统适用于飞机，航天器，导弹和其他飞行器，特别是大型飞行器和高速行驶的飞行器。

9. 发明公开

US20230415886A1 HYBRID POWER SYSTEMS FOR DIFFERENT MODES OF FLIGHT 审中-公开
公开(公告)号：US20230415886A1
公开(公告)日：2023-12-28
申请号：US18244785
申请日：2023-09-11
申请人： Kitty Hawk Corporation
发明人： Pranay Sinha , Damon Vander Lind
IPC分类号： B64C29/00 , G05D1/10 , B64C13/48 , B64C39/12 , B64D27/24 , B64D27/26 , B60L53/00 , B60L50/64 , B64C27/82 , B64D27/02 , B64D31/06
CPC分类号： B64C29/0033 , B64D2027/026 , B64C13/48 , B64C39/12 , B64D27/24 , B64D27/26 , B60L53/00 , B60L50/64 , B64C27/82 , B64D27/02 , B64D31/06 , B64D2027/264 , B60L2200/10 , B64C2027/8209 , G05D1/101
摘要： During a cruise mode, a cruise-only propeller provides thrust using power from a first power source. During a hovering mode and a transitional mode, the propeller provides no thrust. The first power source includes an internal combustion engine; a second power source includes a high discharge rate battery and a high energy battery. The propeller is electrically connected to the first power source and is electrically disconnected from the second power source. During the hovering mode and the transitional mode, a hover-and-transition-only tiltrotor provides thrust using power from the second power source. During a vertical landing, the tiltrotor switches power sources from the high energy battery to the high discharge rate battery, independent of current draw. The tiltrotor is electrically disconnected from the first power source and is electrically connected to the second power source. During the cruise mode, the tiltrotor provides no thrust.

10. 发明授权

US11851172B1 Apparatus, system and method for a supplemental wing for a rotary wing aircraft 有权
公开(公告)号：US11851172B1
公开(公告)日：2023-12-26
申请号：US17334713
申请日：2021-05-29
申请人： Piasecki Aircraft Corporation
发明人： Luigi U. Ricci Moretti , Frederick W. Piasecki , Robert H. Lewis , Dinesh Barwey
IPC分类号： B64C27/26 , B64C13/16 , B64C9/30 , B64C13/48 , B64C9/10 , B64C3/38
CPC分类号： B64C27/26 , B64C3/385 , B64C9/10 , B64C9/30 , B64C13/16 , B64C13/48 , B64C2211/00
摘要： A supplemental wing for a rotary wing aircraft rotates about a pitch axis between a forward flight position and a hover position. The supplemental wing generates lift and generates both positive and negative pitching moments that balance and that may passively rotate the supplemental wing to an equilibrium position. The supplemental wing may use power assist to overcome friction to move to the equilibrium position. The lift generated by the supplemental wing reduces at high forward speeds to preserve main rotor control authority. The supplemental wing rotates to avoid aft translation when in the hover position. The supplemental wing may be retrofitted to existing helicopters and flown using existing helicopter controls without pilot re-training.

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