-
公开(公告)号：US11897601B2
公开(公告)日：2024-02-13
申请号：US17672860
申请日：2022-02-16
Applicant: JETZERO, Inc.
Inventor： Mark Allan Page , Blaine Knight Rawdon
CPC classification number: B64C23/076 , B64C9/06 , B64C39/10 , B64C13/24 , B64C2039/105
Abstract: Aspects relate to aircraft and methods of use for aerodynamic control with winglet surfaces. In an aspect an exemplary aircraft includes a first wing having a first winglet at a distal end of the wing, wherein the first winglet comprises at least a first control surface at a first trailing edge of the first winglet and a second wing having a second winglet at a distal end of the wing, wherein the second winglet comprises at least a second control surface at a second trailing edge of the second winglet.
-
公开(公告)号：US20230382515A1
公开(公告)日：2023-11-30
申请号：US17829249
申请日：2022-05-31
Applicant: The Boeing Company
Inventor： Kevin Raylin Tsai
Abstract: Flaperon actuation systems for aircraft are disclosed herein. An example aircraft includes a wing including, a fixed wing portion, a flaperon, and an actuation system. The actuation system includes a first actuator coupled to the fixed wing portion. The first actuator is operable to move the flaperon along a first degree of freedom between a stowed position in which the flaperon is aligned with the fixed wing portion and a deployed position in which the flaperon is moved downward relative to the fixed wing portion. The actuation system also includes a linkage assembly coupled between the fixed wing portion and the flaperon. The linkage assembly includes a second actuator operable to move the flaperon along a second degree of freedom to pitch the flaperon between an upward position and a downward position.
-
13.发明授权公开(公告)号：US11820490B1
公开(公告)日：2023-11-21
申请号：US17751209
申请日：2022-05-23
Applicant: The Boeing Company
Inventor： Kevin Tsai , Mark S. Good
CPC classification number: B64C13/50 , B64C1/0009 , B64C1/38 , B64C9/02 , B64C9/06
Abstract: Methods, apparatus, and articles of manufacture for actuating control surfaces of an aircraft are disclosed. An example apparatus to control a control surface of an aerodynamic body includes a track rotatable about a pivot of a support structure of the aerodynamic body, the control surface slidably coupled to the track, a first actuator operatively coupled to the track, the first actuator to cause rotation of the track and the flaperon about the pivot, and a second actuator operatively coupled to the control surface, the second actuator to cause translation of the control surface along the track.
-
14.发明公开公开(公告)号：US20230221733A1
公开(公告)日：2023-07-13
申请号：US18187337
申请日：2023-03-21
Applicant: The Regents of the University of California
Inventor： Ilya M. Anishchenko , Stephen K. Robinson
IPC: B64U30/296 , B64U50/13 , B64C9/06 , B64C29/00
CPC classification number: B64U30/296 , B64U50/13 , B64C9/06 , B64C29/0033 , B64U10/20
Abstract: We describe an aircraft design, which is capable of vertical takeoff and landing and also high-speed cruise on a fixed wing. The aircraft comprises a fuselage with a probe-deployment mechanism, which deploys a sample-gathering probe, located at a front end of the fuselage. A main wing is coupled to a middle section of the fuselage, wherein a right motor and right propeller are coupled to a right side of the main wing, and a left motor and left propeller are coupled to a left side of the main wing. The right and left propellers are angled with respect to the fuselage enabling the aircraft to pitch up to a vertical-takeoff mode and pitch down a horizontal-cruising mode. A pitch motor and pitch propeller are located at the rear end of the fuselage, wherein the pitch propeller is angled to provide substantially vertical thrust to control a pitch of the fuselage.
-
公开(公告)号：US20230143989A1
公开(公告)日：2023-05-11
申请号：US17922015
申请日：2020-08-17
Applicant: EnExSys Research Inc.
Inventor： James Henke
CPC classification number: B64C27/82 , B64C27/06 , B64C9/06 , B64C9/18 , B64C2027/8272
Abstract: A simple, safe, and inexpensive flight control system in an aircraft. An anti-torque system for a rotary-wing aircraft has an airfoil with a first surface extending from a first trailing edge and a leading edge, and a second surface extending from a second trailing edge to join the first surface at the leading edge. The airfoil has a first moveable deflector panel pivotally coupled to the first trailing edge, and a second moveable deflector panel pivotally coupled to the second trailing edge. Means are provided to pivot the deflector panels in unison about their respective pivot axes to alter the direction of travel of the airflow downstream of the pivot axes over the surfaces of the deflector panels, thereby producing a lift in a direction perpendicular to the airflow to counteract the torque applied on the aircraft. The flight control system may be arranged within a fixed-wing aircraft.
-
Patent Agency Ranking
公开(公告)号：US09731813B2
公开(公告)日：2017-08-15
申请号：US14539789
申请日：2014-11-12
Applicant: The Boeing Company
Inventor： Jonathan Kyle Moore , Brian Charles Bock , Edward E. Coleman
Abstract: Methods and apparatus to control aircraft horizontal stabilizers are described herein. One described method includes calculating, using a processor, a desired movement of a horizontal stabilizer of an aircraft to counteract a pitching moment of the aircraft, and controlling the horizontal stabilizer based on the desired movement.
-
公开(公告)号：US09180962B2
公开(公告)日：2015-11-10
申请号：US14034987
申请日：2013-09-24
Applicant: The Boeing Company
Inventor： Matthew A. Moser , Mark J. Gardner , Michael R. Finn , Mark S. Good , Adam P. Malachowski , Monica E. Thommen , Stephen R. Amorosi , Dan Onu
CPC classification number: B64C3/50 , B64C9/06 , B64C9/12 , B64C9/24 , B64C13/00 , B64C13/16 , B64C13/26 , B64C13/503 , Y02T50/32 , Y02T50/44
Abstract: A system for varying a wing camber of an aircraft wing may include a leading edge device coupled to the wing. The leading edge device may be configured to be actuated in an upward direction and a downward direction relative to a retracted position of the leading edge device.
Abstract translation: 用于改变飞机机翼的机翼弯曲的系统可以包括联接到机翼的前缘装置。 前缘装置可以被构造成相对于前缘装置的缩回位置沿向上的方向和向下的方向被致动。
-
公开(公告)号：US20150307182A1
公开(公告)日：2015-10-29
申请号：US14554142
申请日：2014-11-26
Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH
Inventor： Sebastian MORES , Alessandro D'ALASCIO , Uwe KIESEWETTER , Stefan PROBST , Christian WEHLE , Marius BEBESEL
CPC classification number: B64C5/10 , B64C9/06 , B64C27/82 , B64C2027/8254 , B64C2027/8272 , B64C2027/8281
Abstract: A pitch stabilizer with box configuration suitable for providing stability to a rotorcraft comprising a vertical mid-plane and a fuselage; the pitch stabilizer comprising one or two pitch stabilizing assemblies, with no more than one pitch stabilizing assembly on each side of the vertical mid-plane, wherein each pitch stabilizing assembly comprises upper pitch stabilizing means, lower pitch stabilizing means and a wing tip element.
Abstract translation: 一种具有箱形结构的桨距稳定器，其适于为包括垂直中平面和机身的旋翼飞机提供稳定性; 所述桨距稳定器包括一个或两个俯仰稳定组件，在垂直中平面的每一侧上不超过一个桨距稳定组件，其中每个俯仰稳定组件包括上桨距稳定装置，下桨距稳定装置和翼尖元件。
-
公开(公告)号：US07913949B2
公开(公告)日：2011-03-29
申请号：US11761023
申请日：2007-06-11
Applicant: Robert Hoffenberg
Inventor： Robert Hoffenberg
Abstract: A vertical tail for use with an aircraft or other form of mobile platform. The vertical tail includes a main element which is fixedly secured to the mobile platform, and a leading edge element that is movably secured to the main element. The cross section of the leading edge element is symmetric about the cruise chord line of the tail. The leading edge element can be pivoted and/or extended to create a gap with the main (fixed) element. The movable leading edge element is used to increase the maximum yawing moment provided by the vertical tail. The maximum yawing moment is increased when air flow is incident from either side of the vertical tail.
Abstract translation: 用于飞机或其他形式的移动平台的垂直尾巴。 垂直尾部包括固定地固定到移动平台的主要元件和可移动地固定到主元件的前缘元件。 前缘元素的横截面与尾巴的巡航弦线对称。 前缘元件可以枢转和/或延伸以与主（固定）元件产生间隙。 可移动前缘元件用于增加由垂直尾部提供的最大横摆力矩。 当空气流从垂直尾部的任一侧入射时，最大偏转力矩增加。
-
公开(公告)号：US20080302919A1
公开(公告)日：2008-12-11
申请号：US11761023
申请日：2007-06-11
Applicant: Robert Hoffenberg
Inventor： Robert Hoffenberg
IPC: B64C3/50
Abstract: A vertical tail for use with an aircraft or other form of mobile platform. The vertical tail includes a main element which is fixedly secured to the mobile platform, and a leading edge element that is movably secured to the main element. The cross section of the leading edge element is symmetric about the cruise chord line of the tail. The leading edge element can be pivoted and/or extended to create a gap with the main (fixed) element. The movable leading edge element is used to increase the maximum yawing moment provided by the vertical tail. The maximum yawing moment is increased when air flow is incident from either side of the vertical tail.
Abstract translation: 用于飞机或其他形式的移动平台的垂直尾巴。 垂直尾部包括固定地固定到移动平台的主要元件和可移动地固定到主元件的前缘元件。 前缘元素的横截面与尾巴的巡航弦线对称。 前缘元件可以枢转和/或延伸以与主（固定）元件产生间隙。 可移动前缘元件用于增加由垂直尾部提供的最大横摆力矩。 当空气流从垂直尾部的任一侧入射时，最大偏转力矩增加。
-
-
-
-
-
-
-
-
-
Search Results
69
records
(took 0.02 seconds)
