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1. 发明授权

US11577818B2 Elevon control system 有权
公开(公告)号：US11577818B2
公开(公告)日：2023-02-14
申请号：US17174571
申请日：2021-02-12
申请人： AeroVironment, Inc.
发明人： Tony Shuo Tao , Nathan Olson , Carlos Thomas Miralles , Robert Nickerson Plumb
IPC分类号： B64C13/34 , B64C5/12 , B64C13/18 , B64C9/36 , B64C9/02 , B64C3/56 , B64C3/44 , B64C3/50 , B64C9/18 , B64C39/02 , B64C9/08 , B64C11/00 , B64C9/00
摘要： A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

2. 发明授权

US11220324B2 Apparatus for a vehicle 有权
公开(公告)号：US11220324B2
公开(公告)日：2022-01-11
申请号：US16478221
申请日：2018-02-01
申请人： ISRAEL AEROSPACE INDUSTRIES LTD.
发明人： Shahar Bar Hillel , Saar Shragai
IPC分类号： B64C5/12 , F42B10/06 , F42B10/50 , F42B10/20 , F42B10/28 , F42B10/12
摘要： Apparatuses for a projectile are provided, the projectile configured for weapons band launching, examples of the apparatus comprising a body, an inflation system and external walls. The body is inflatable by the inflation system, from a deflated configuration having a first volume to an inflated configuration having a second volume, greater than the first volume. The external walls are deployable from an undeployed configuration to a deployed configuration responsive to the body being inflated. In the undeployed configuration and at an operating airspeed, the center of pressure is located at a first position with respect to the projectile. In the deployed configuration the external walls provide a deployed external surface geometry exposed to an airflow corresponding to the operating airspeed, such that the center of pressure is located at a second position with respect to the projectile, different from the first position.

3. 发明授权

US11040766B2 Elevon control system 有权
公开(公告)号：US11040766B2
公开(公告)日：2021-06-22
申请号：US16747815
申请日：2020-01-21
申请人： AeroVironment, Inc.
发明人： Tony Shuo Tao , Nathan Olson , Carlos Thomas Miralles , Robert Nickerson Plumb
IPC分类号： B64C3/56 , B64C5/12 , B64C9/36 , B64C9/02 , B64C9/00 , B64C13/34 , B64C3/44 , B64C3/50 , B64C13/18 , B64C39/02 , B64C9/08 , B64C9/18 , B64C11/00
摘要： A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

4. 发明授权

US10974812B1 Hierarchical closed-loop flow control system for aircraft missiles and munitions 有权
公开(公告)号：US10974812B1
公开(公告)日：2021-04-13
申请号：US16166230
申请日：2018-10-22
申请人： Troy S Prince , Richard Kolacinski , Mehul Patel
发明人： Troy S Prince , Richard Kolacinski , Mehul Patel
IPC分类号： B64C5/12 , F42B15/01 , B64C23/06 , F42B10/64 , G05D1/00 , F41G7/00 , B64C21/00 , G05D1/08 , F42B10/62 , F42B10/02 , F42B10/14 , F42B10/60 , F42B10/00
摘要： The present invention relates to a missile or aircraft with a hierarchical, modular, closed-loop flow control system and more particularly to aircraft or missile with a flow control system for enhanced aerodynamic control, maneuverability and stabilization. The present invention further relates to flow control system involving different elements including flow sensors, active flow control device or activatable flow effectors and logic devices with closed loop control architecture. The active flow control device or activatable flow effectors of these various embodiments are adapted to be activated, controlled, and deactivated based on signals from the sensors to achieve a desired stabilization or maneuverability effect. The logic devices are embedded with a hierarchical control structure allowing for rapid, real-time control at the flow surface.

5. 发明授权

US10953976B2 Air vehicle system having deployable airfoils and rudder 有权
公开(公告)号：US10953976B2
公开(公告)日：2021-03-23
申请号：US14636019
申请日：2015-03-02
申请人： AEROVIRONMENT, INC.
发明人： Tony Shuo Tao , Nathan Olson , Carlos Thomas Miralles , Robert Nickerson Plumb
IPC分类号： B64C5/12 , B64C3/56 , B64C13/34 , B64C3/44 , B64C3/50 , B64C13/18 , B64C9/36 , B64C39/02 , B64C9/02 , B64C9/08 , B64C9/18 , B64C11/00 , B64C9/00
摘要： A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) including: a fuselage; a first pair of airfoils rotatable between a retracted position and a deployed position, the deployed position extending out from the fuselage and the retracted position extending substantially along a first portion on an exterior of the fuselage; a second pair of airfoils rotatable between a second retracted position and a second deployed position, the second deployed position extending out from the fuselage and the second retracted position extending substantially along the first portion on the exterior of the fuselage; and a rudder foldable against the fuselage in a pre-deployment position.

6. 发明申请

US20190351994A1 Retractable aircraft control surface 审中-公开
公开(公告)号：US20190351994A1
公开(公告)日：2019-11-21
申请号：US15932881
申请日：2018-05-16
申请人： Richard Michael Truhill
发明人： Richard Michael Truhill
IPC分类号： B64C5/12 , B64C5/02 , B64C9/36
摘要： A modification to conventional aircraft empennage design, which is also adaptable to all-wing aircraft. Vertical stabilizer/rudder assemblies are hinged such that actuator and lock mechanisms are able to vary the aircraft empennage configuration from one with fully functional conventional vertical stabilizer(s)/rudder(s) to one with no vertical stabilizer/rudder.

7. 发明授权

US10295318B2 Fin retention and release mechanism 有权
公开(公告)号：US10295318B2
公开(公告)日：2019-05-21
申请号：US15123330
申请日：2015-03-12
申请人： Moog Inc.
发明人： Laurie Hammond , Jonathon Pickard
IPC分类号： F42B10/14 , F42B10/20 , F42B10/18 , B64C5/12 , F42B10/16
摘要： An improved fin retention and release mechanism (15) comprising an elongated body (16), at least one fin (18a) mounted to the body and capable of moving from a stowed position (30) to a deployed position (32), an actuator (20a) connected to the fin and arranged to rotate the fin about a first axis (33), a fin retention member (19a) connected to the body and configured and arranged to rotate about a second axis (34) from a locked position (36) to a release position (38), the fin and the fin retention member configured and arranged such that the fin is held in the stowed position by the fin retention member when being in the locked position and the fin is not held in the stowed position by the fin retention member when being in the release position, and wherein actuation of the fin about the first axis by the actuator rotates the fin about the first axis in a first direction (39) and correspondingly rotates the fin retention member about the second axis in a second direction (40) opposite to the first direction and from the locked position to the release position.

8. 发明授权

US09310166B2 Hierarchical closed-loop flow control system for aircraft, missiles and munitions 有权
公开(公告)号：US09310166B2
公开(公告)日：2016-04-12
申请号：US14010909
申请日：2013-08-27
申请人： Troy S Prince , Richard Kolacinski , Mehul Patel
发明人： Troy S Prince , Richard Kolacinski , Mehul Patel
IPC分类号： F42B10/02 , F42B10/14 , F42B10/60 , F42B10/62 , F42B15/01 , F41G7/00 , B64C5/12 , G05D1/00 , F42B10/00
CPC分类号： B64C21/00 , B64C5/12 , F41G7/00 , F42B10/14 , F42B10/60 , F42B10/62 , F42B15/01 , G05D1/0088
摘要： The present invention relates to a missile or aircraft with a hierarchical, modular, closed-loop flow control system and more particularly to aircraft or missile with a flow control system for enhanced aerodynamic control, maneuverability and stabilization. The present invention further relates to a method of operating the flow control system.Various embodiments of the flow control system of the present invention involve different elements including flow sensors, active flow control device or activatable flow effectors and logic devices with closed loop control architecture. The sensors of these various embodiments are used to estimate or determine flow conditions on the various surfaces of a missile or aircraft. The active flow control device or activatable flow effectors of these various embodiments create on-demand flow disturbances, preferably micro-disturbances, at different points along the various aerodynamic surfaces of the missile or aircraft to achieve a desired stabilization or maneuverability effect. The logic devices are embedded with a hierarchical control structure allowing for rapid, real-time control at the flow surface.

9. 发明授权

US07083141B2 Self-propelled projectile 失效
标题翻译：自走式射弹
公开(公告)号：US07083141B2
公开(公告)日：2006-08-01
申请号：US10725100
申请日：2003-12-02
申请人： Edward Nitenson , Robert Cumings
发明人： Edward Nitenson , Robert Cumings
IPC分类号： B64C5/12
CPC分类号： F02K9/00 , F42B10/14 , F42B15/00
摘要： A self-propelled projectile which will maintain a straight trajectory through air or water.
摘要翻译：一种能够通过空气或水保持直线轨迹的自走式射弹。

10. 发明授权

US07004425B2 Flying body for firing from a tube with over-caliber stabilizers 有权
标题翻译：飞行体从具有超大口径稳定器的管中点燃
公开(公告)号：US07004425B2
公开(公告)日：2006-02-28
申请号：US10504116
申请日：2003-02-06
申请人： Shinichi Okada , Sadao Okawa , Masato Shinomiya , Makoto Mochizuki
发明人： Shinichi Okada , Sadao Okawa , Masato Shinomiya , Makoto Mochizuki
IPC分类号： B64C5/12
CPC分类号： F42B10/20 , F42B10/16
摘要： A missile to be fired from a barrel contains a tail, a tail sleeve attached to the tail, a stop element fixed to the tail sleeve, and a movable structural part disposed at the tail. Fin assembly wings are provided and are to be released from a subcaliber launch position to an overcaliber functional position by the movable structural part moving toward the stop element through a given distance. A pressure area is disposed between the tail end surface and the movable structural part. A propellant gas enters the pressure area during the firing of the missile, for moving the movable structural part away from the tail end surface against the stop element after firing. Bearing shafts are supported by the tail sleeve, the fin assembly wings are configured as a wrap around tail fin assembly held about the bearing shafts.
摘要翻译：从枪管发射的导弹包含尾巴，尾巴附着在尾部，固定在尾部套筒上的止动元件和设在尾部的可移动结构部件。翅片组装翅膀被设置并且通过可移动结构部件朝着停止元件移动给定距离而从亚光子发射位置释放到超光纤功能位置。压力区域设置在尾端表面和可移动结构部件之间。在发射导弹期间，推进剂气体进入压力区域，用于将可动结构部件从射出后的尾端表面靠近止动元件移动。轴套由尾套支撑，翅片组件翼被构造成围绕轴承轴保持的尾翼组件的卷绕。

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