公开(公告)号：US08074925B2

公开(公告)日：2011-12-13

申请号：US12507573

申请日：2009-07-22

Applicant: Brian Herman Morgan ,  David LeRoy Hagen

Inventor： Brian Herman Morgan ,  David LeRoy Hagen

IPC: B64C5/10

CPC classification number: B64C9/06 ,  B64C5/02 ,  B64C5/06 ,  B64C9/12 ,  Y02T50/32

Abstract: An aircraft attitude control configuration enables control surfaces to provide attitude control for an aircraft at hover or low air speed conditions. The aircraft attitude control configuration includes a plurality of thrusters mounted to an aircraft for thrusting air, a first control surface kinematically coupled to the aircraft at a position downstream of a first thruster to enable a first vector force to be generated by a portion of the thrusted air from the first thruster on the first control surface, and a second control surface kinematically coupled to the aircraft at a position downstream of a second thruster, the first and the second control surfaces being displaced symmetrically on opposite sides of a longitudinal axis of the aircraft, the second control surface being configured to be independently and differentially movable with respect to the first control surface to enable a second vector force to be generated by a portion of the thrusted air from the second thruster on the second control surface.

Abstract translation: 飞机姿态控制配置使得控制面能够在悬停或低空气速度条件下为飞行器提供姿态控制。 飞行器姿态控制结构包括安装在飞行器上用于推动空气的多个推进器，第一控制表面，其在第一推进器下游的位置处运动学地联接到飞行器，以使第一矢量力由推动的一部分产生 来自第一控制表面上的第一推进器的空气和在第二推进器下游的位置处运动学地联接到飞行器的第二控制表面，第一和第二控制表面在飞行器的纵向轴线的相对侧对称移位 所述第二控制表面被配置为相对于所述第一控制表面独立且可差分移动，以使第二向量力由所述第二控制表面上的来自所述第二推进器的被推动空气的一部分产生。

公开(公告)号：US20100001117A1

公开(公告)日：2010-01-07

申请号：US11601804

申请日：2006-11-20

Applicant: Tom Kusic

Inventor： Tom Kusic

IPC: F42B15/00 ,  B64C3/00

CPC classification number: B64C5/04 ,  B64C9/06

Abstract: An aircraft 1 with a spiral inducing assembly 2 which is capable of inducing the aircraft to travel in a continuous spiraling motion without the aircraft rolling. A ramjet 6b is attached to a tube 3a that is able to rotate around the encircled part of the fuselage. The ramjet 6b is able to rotate in a pivoting manner on the rotate-able tube 3a with respect to the rotate-able tube 3a, thereby changing their pitch relative to the longitudinal axis of the rotate-able tube 3a. Ramjet 6b is rotated as is another ramjet on the right side of the tube 3a. The rotate-able tube 3a is rotated by means of an electric motor 3b rotating a wheel 3c. The difference in degree of rotation between the ramjets makes the ramjet 6b exert a greater force on the rotate-able tube 3a than the ramjet on the right side when the ramjets are rotated in the same direction. The imbalance between the rotational forces thus causes the rotate-able tube 3a to rotate. When rotated, the ramjets would exert a lateral force on the rotate-able tube 3a. Thus, the ramjets would push the rotate-able tube sideways. But as the rotate-able tube is pushed sideways, it rotates, and hence the lateral direction of push constantly revolves, causing a spiraling motion of the aircraft when in flight.

Abstract translation: 具有螺旋诱导组件2的飞机1，其能够使飞机以不间断的旋转运动而飞行，而不会飞行。 冲压喷枪6b连接到能够围绕机身的环绕部分旋转的管3a。 冲压喷枪6b能够相对于可旋转管3a以可枢转的方式旋转在可旋转管3a上，从而相对于可旋转管3a的纵向轴线改变它们的俯仰。 Ramjet 6b与管3a右侧的另一冲头喷射一样旋转。 旋转管3a通过旋转轮3c的电动马达3b旋转。 当冲击器沿相同方向旋转时，冲压喷嘴6b之间的旋转差异使得冲压喷嘴6b在可旋转管3a上施加比右侧的冲压式喷射器更大的力。 因此，旋转力之间的不平衡使得可旋转管3a旋转。 当旋转时，冲击器将在可旋转管3a上施加横向力。 因此，冲击将横向推动可旋转管。 但是当可旋转管被侧向推动时，其旋转，因此推动的横向方向不断旋转，导致飞行器在飞行中的螺旋运动。

公开(公告)号：US07581696B2

公开(公告)日：2009-09-01

申请号：US11595525

申请日：2006-11-09

Applicant: Brian Herman Morgan ,  David LeRoy Hagen

Inventor： Brian Herman Morgan ,  David LeRoy Hagen

IPC: B64C5/10

CPC classification number: B64C9/06 ,  B64C5/02 ,  B64C5/06 ,  B64C9/12 ,  Y02T50/32

Abstract: An aircraft attitude control configuration enables control surfaces to provide attitude control for an aircraft at hover or low air speed conditions. The aircraft attitude control configuration includes a thruster mounted to an aircraft for thrusting air, a first control surface kinematically coupled to the aircraft at a position downstream of the thruster, and a second control surface kinematically coupled to the aircraft at a position downstream of the thruster, the second control surface being differentially movable with respect to the first control surface such that a portion of the thrusted air from the thruster generates a first vector force on the first control surface and another portion of the thrusted air generates a second vector force on the second control surface, so that the first and the second vector forces provide a net roll moment about the Y-Roll axis.

Abstract translation: 飞机姿态控制配置使得控制面能够在悬停或低空气速度条件下为飞行器提供姿态控制。 飞行器姿态控制构型包括安装在飞行器上用于推动空气的推进器，在推进器下游的位置运动地联接到飞行器的第一控制表面，以及在推进器下游的位置运动地联接到飞行器的第二控制表面 所述第二控制表面可相对于所述第一控制表面差异移动，使得来自所述推进器的所述推动空气的一部分在所述第一控制表面上产生第一向量力，并且所述推动空气的另一部分在所述第二控制表面上产生第二向量力 第二控制表面，使得第一和第二向量力围绕Y-辊轴提供净滚动力矩。

公开(公告)号：US20070102575A1

公开(公告)日：2007-05-10

申请号：US11595525

申请日：2006-11-09

Applicant: Brian Morgan ,  David Hagen

Inventor： Brian Morgan ,  David Hagen

IPC: B64C9/06

CPC classification number: B64C9/06 ,  B64C5/02 ,  B64C5/06 ,  B64C9/12 ,  Y02T50/32

Abstract: An aircraft attitude control configuration enables control surfaces to provide attitude control for an aircraft at hover or low air speed conditions. The aircraft attitude control configuration includes a thruster mounted to an aircraft for thrusting air, a first control surface kinematically coupled to the aircraft at a position downstream of the thruster, and a second control surface kinematically coupled to the aircraft at a position downstream of the thruster, the second control surface being differentially movable with respect to the first control surface such that a portion of the thrusted air from the thruster generates a first vector force on the first control surface and another portion of the thrusted air generates a second vector force on the second control surface, so that the first and the second vector forces provide a net roll moment about the Y-Roll axis.

Abstract translation: 飞机姿态控制配置使得控制面能够在悬停或低空气速度条件下为飞行器提供姿态控制。 飞行器姿态控制构型包括安装在飞行器上用于推动空气的推进器，在推进器下游的位置运动地联接到飞行器的第一控制表面，以及在推进器下游的位置运动地联接到飞行器的第二控制表面 所述第二控制表面可相对于所述第一控制表面差异移动，使得来自所述推进器的所述推动空气的一部分在所述第一控制表面上产生第一向量力，并且所述推动空气的另一部分在所述第二控制表面上产生第二向量力 第二控制表面，使得第一和第二向量力围绕Y-辊轴提供净滚动力矩。

公开(公告)号：US06708923B2

公开(公告)日：2004-03-23

申请号：US09886639

申请日：2001-06-22

Applicant: Tom Kusic

Inventor： Tom Kusic

IPC: B64C908

CPC classification number: B64C9/06 ,  B64C5/04

Abstract: An aircraft 1 in the form of an airplane with a spiral inducing assembly 2 which is capable of inducing the airplane to travel in a continuous spiralling motion without rolling. Two fins 3 and 4 are attached to a tube 5 that is able to rotate around the encircled part of the fuselage. The fins 3, 4 are able to rotate in a pivoting manner on the rotatable tube 5 with respect to the rotatable tube 5, thereby changing their pitch relative to the longitudinal axis of the rotatable tube 5. Fin 3 is larger than fin 4. The diferene in sizes between the fins makes the larger fin 3 exert a greater force on the rotatable tube 4 than the smaller fin 4 when the fins are pitched in unison. The aerodynamic imbalance between the fins thus casues the rotatable tube 5 to rotate. When pitched at an angle to the longitudinal axis in unison, both fins 3, 4 would exert a lateral force on the rotatable tube 5. Thus, as well as forcing the rotatable tube 5 to rotate, the fins 3, 4 would also push the rotatable tube sideways. But as the rotatable tube is pushed sideways, it rotates, and hence the lateral direction of push constantly revolves, causing a spiralling motion when in flight.

Abstract translation: 具有螺旋形诱导组件2的飞机形式的飞机1，其能够引导飞机以连续的螺旋运动而不滚动。 两个翅片3和4连接到能够围绕机身的环绕部分旋转的管5。 翅片3,4能够相对于可旋转管5以可枢转的方式旋转在可旋转管5上，从而相对于可旋转管5的纵向轴线改变它们的间距。翅片3大于翅片4。 散热片之间的尺寸差异使得较大的翅片3在翅片一致地倾斜时，在可旋转管4上施加比较小翅片4更大的力。 因此，翅片之间的空气动力学不平衡使可旋转管5旋转。 当与纵向轴线一致地倾斜时，两个翅片3,4将在可旋转的管5上施加横向力。因此，以及迫使可旋转管5旋转，翅片3,4还将推动 侧向旋转管。 但是当可旋转管被侧向推动时，其旋转，因此推动的横向方向恒定地旋转，在飞行中引起螺旋运动。

公开(公告)号：US06648433B2

公开(公告)日：2003-11-18

申请号：US10067964

申请日：2002-02-08

Applicant: Tom Kusic

Inventor： Tom Kusic

IPC: F42B1006

CPC classification number: B64C9/06 ,  B64C5/04

Abstract: A cross-section of a missile 1 with the missile attachment 2. The missile attachment consists of a cylindrical tube 3 which encircles part of the missile 1, and a protruding section 4 with a concave forward facing surface area 5. Shown also is a friction inducing movable component in the form of a lever 11 pivotly attached to the missile by a bracket 12, such that the lever 11 can be pivotly moved an actuating mechanism which is in the form of an electric motor 13 using a rotor arm 14. When the lever is pivoted by the electric motor 13, using the rotor arm 14, a part of the lever is pressed through a hole 15 in the missile 1 so that the part of the lever that is pressed through the hole can reach the cylindrical tube. As the rotor arm 14 presses harder against the lever, the lever is pressed harder against the cylindrical tube. With the friction that occurs between the lever and the cylindrical tube, the rotation of the cylindrical tube relative to the missile can be controlled, so that the spiralling motion of the missile can be controlled. A computer 16 controls the action of the electric motor 13, and a battery 17 provides electrical power for the computer and the electrical motor.

Abstract translation: 具有导弹附件2的导弹1的横截面。导弹附件包括环绕导弹1的一部分的圆柱形管3和具有凹入的前向表面区域5的突出部分4.还示出了摩擦 引导以支架12枢转地附接到导弹的杠杆11形式的可移动部件，使得杠杆11能够使用转子臂14使电动机13形式的致动机构枢转运动。当 杠杆由电动马达13枢转，使用转子臂14，杆的一部分通过导弹1中的孔15被按压，使得通过孔按压的杆的部分可以到达圆柱形管。 当转子臂14更加压靠杠杆时，杆被更加压紧在圆柱形管上。 由于杠杆和圆柱形管之间发生摩擦，可以控制圆柱形管相对于导弹的旋转，从而可以控制导弹的螺旋运动。 计算机16控制电动机13的作用，并且电池17为计算机和电动机提供电力。

公开(公告)号：US20010054668A1

公开(公告)日：2001-12-27

申请号：US09886639

申请日：2001-06-22

Inventor： Tom Kusic

IPC: B64C003/00

CPC classification number: B64C9/06 ,  B64C5/04

Abstract: An aircraft 1 in the form of an aeroplane with a spiral inducing assembly 2 which is capable of inducing the aeroplane to travel in a continuous spiralling motion without rolling. Two fins 3 and 4 are attached to a tube 5 that is able to rotate around the encircled part of the fuselage. The fins 3, 4 are able to rotate in a pivoting manner on the rotatable tube 5 with respect to the rotatable tube 5, thereby changing their pitch relative to the longitudinal axis of the rotatable tube 5. Fin 3 is larger than fin 4. The diferene in sizes between the fins makes the larger fin 3 exert a greater force on the rotatable tube 4 than the smaller fin 4 when the fins are pitched in unison. The aerodynamic imbalance between the fins thus casues the rotatable tube 5 to rotate. When pitched at an angle to the longitudinal axis in unison, both fins 3, 4 would exert a lateral force on the rotatable tube 5. Thus, as well as forcing the rotatable tube 5 to rotate, the fins 3, 4 would also push the rotatable tube sideways. But as the rotatable tube is pushed sideways, it rotates, and hence the lateral direction of push constantly revolves, causing a spiralling motion when in flight.

Abstract translation: 具有螺旋形诱导组件2的飞机形式的飞机1，其能够引导飞机以连续的螺旋运动而不滚动。 两个翅片3和4连接到能够围绕机身的环绕部分旋转的管5。 翅片3,4能够相对于可旋转管5以可枢转的方式旋转在可旋转管5上，从而相对于可旋转管5的纵向轴线改变它们的间距。翅片3大于翅片4。 散热片之间的尺寸差异使得较大的翅片3在翅片一致地倾斜时，在可旋转管4上施加比较小翅片4更大的力。 因此，翅片之间的空气动力学不平衡使可旋转管5旋转。 当与纵向轴线一致地倾斜时，两个翅片3,4将在可旋转的管5上施加横向力。因此，以及迫使可旋转管5旋转，翅片3,4还将推动 侧向旋转管。 但是当可旋转管被侧向推动时，其旋转，因此推动的横向方向恒定地旋转，在飞行中引起螺旋运动。

公开(公告)号：US5322243A

公开(公告)日：1994-06-21

申请号：US12071

申请日：1993-02-01

Applicant: David R. Stoy

Inventor： David R. Stoy

IPC: B64C5/10 ,  B64C9/06 ,  F42B10/62

CPC classification number: F42B10/62 ,  B64C5/10 ,  B64C9/06

Abstract: A maneuvering system for a flight vehicle rotates a lifting aerodynamic surface of the flight vehicle about an axis parallel with a direction of flight of the vehicle in a rotational direction corresponding to the desired change of flight direction to which the vehicle is to be steered, while maintaining attitude stability of the flight vehicle by altering other aerodynamic surfaces of the vehicle.

Abstract translation: 用于飞行车辆的操纵系统使飞行器车辆的提升空气动力学表面围绕与车辆的飞行方向平行的轴线旋转，该旋转方向对应于车辆将被转向的飞行方向的期望变化， 通过改变车辆的其它空气动力学表面来维持飞行器的姿态稳定性。

公开(公告)号：US4544118A

公开(公告)日：1985-10-01

申请号：US431759

申请日：1982-09-30

Applicant: Curtiss W. Robinson

Inventor： Curtiss W. Robinson

IPC: B64C9/06 ,  B64C9/18

CPC classification number: B64C9/16 ,  B64C9/06 ,  B64C9/18

Abstract: A flap (22) carries a guide roller (24) at each of its ends. Each guide roller (24) travels within a fore and aft track (28) positioned immediately endwise outwardly of its end of the flap (22). The flap (22) is extended and retracted by means including a reaction link (36) and a two-way linear actuator (38). The actuator (38) and the reaction link (36) are pivotally connected at their forward ends to the outer end of a bell crank arm (34), for pivotal movement about a common axis (40). At its rearward end the actuator (38) is pivotally attached to the flap at a location (44) offset above the roller (24). The reaction link (36) is pivotally attached at its rearward end to the flap (22) at a location (42) offset below the roller (24). Rotation of the bell crank arm (34) alone will result in the flap (22) being translated rearwardly and rotated downwardly, i.e. Fowler flap movement. Extension or retraction of the actuator (38) will cause a rotation of the flap (22) about the axes (26) of the rollers (24).

Abstract translation: 翼片（22）在其每个端部处承载有导辊（24）。 每个引导辊（24）在前后轨道（28）内行进，该前后轨道（28）紧邻其翼片（22）的端部的内侧。 翼片（22）通过包括反作用连杆（36）和双向线性致动器（38）的装置而延伸和缩回。 致动器（38）和反作用连杆（36）在其前端枢转地连接到钟形曲柄臂（34）的外端，用于围绕公共轴线（40）枢转运动。 在其后端，致动器（38）在偏移在辊（24）上方的位置（44）处枢转地附接到翼片。 反作用连杆（36）在其后端处枢转地附接到位于辊（24）下方的位置（42）处的挡板（22）。 单独的曲拐臂（34）的旋转将导致翼片（22）向后平移并向下旋转，即福勒翼片运动。 致动器（38）的延伸或缩回将导致翼片（22）围绕辊（24）的轴线（26）旋转。