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1. 发明授权

US07732741B1 Folding articulating wing mechanism 有权
标题翻译：折叠式铰接机构
公开(公告)号：US07732741B1
公开(公告)日：2010-06-08
申请号：US11518734
申请日：2006-08-31
申请人： Kent G. Whitham
发明人： Kent G. Whitham
IPC分类号： F42B13/32
CPC分类号： F42B10/14 , F42B10/64
摘要： A locking mechanism for securing an articulated folding wing assembly in a fully extended position by means of a tapered locking plunger urged by a coiled compression spring to contact a complementary mating surface formed on the wing assembly. The spring urged locking plunger is released from a retracted position by rotation of the wing assembly from the folded position to the extended position. A folding mechanism for rotating the wing assembly through a compound angle from the folded position to a rigid and positively locked fully extended position is provided wherein the extended wing may be rotated about its longitudinal axis to provide directional control to the vehicle.
摘要翻译：一种锁定机构，用于通过由螺旋压缩弹簧推动的锥形锁定柱塞将铰接的折叠翼组件固定在完全伸出的位置，以接触形成在翼组件上的互补配合表面。弹簧推动的锁定柱塞通过翼组件从折叠位置旋转到延伸位置而从缩回位置释放。提供了一种折叠机构，用于将翼组件从折叠位置旋转到刚性并且正向锁定的完全伸出位置的复合角度，其中延伸机翼可围绕其纵向轴线旋转以向车辆提供方向控制。

2. 发明授权

US4798143A Gas dispensing projectile 失效
标题翻译：燃气喷射弹
公开(公告)号：US4798143A
公开(公告)日：1989-01-17
申请号：US46921
申请日：1987-05-06
申请人： Douglas Graham
发明人： Douglas Graham
IPC分类号： F42B12/54 , F42B13/32 , F42B13/46
CPC分类号： F42B12/54
摘要： A warhead adapted to be mounted to a conventional missile fired from anti-tank weaponry is formed with a piercing cone secured to a base containing a source of knockout gas and an actuator assembly. Upon piercing an aircraft fuselage, a collar encircling the cone translates rearwardly causing deployment of panels pivotally secured to the base portion and connected to the collar via connecting rods. Movement of the collar into wedging contact with the base of the piercing cone deploys the panels to their maximum extended position and simultaneously actuates the trigger assembly causing the knockout gas to be delivered into the aircraft interior through the piercing cone projecting through the fuselage into the interior.
摘要翻译：适用于安装在由反坦克武器装备发射的常规导弹的弹头上形成有一个固定在底座上的穿孔，该底座上装有一个脱气源和一个致动器组件。在穿过飞行器机身时，围绕锥体的轴环向后平移，使得枢转地固定到基部部分并且经由连接杆连接到轴环的面板的展开。轴环与穿孔底部楔入接触的运动将面板部署到其最大延伸位置，并同时致动触发器组件，从而使排出气体通过穿过机身突出的穿刺锥体输送到飞行器内部进入内部。

3. 发明授权

US4607810A Passive constraint for aerodynamic surfaces 失效
标题翻译：空气动力学表面的被动约束
公开(公告)号：US4607810A
公开(公告)日：1986-08-26
申请号：US689351
申请日：1985-01-07
申请人： Alson C. Frazer
发明人： Alson C. Frazer
IPC分类号： F42B10/16 , F42B13/32
CPC分类号： F42B10/16
摘要： In a guided projectile such as a missile, it is often necessary to negate the lift force imparted by the wings (5) during early low velocity stages of flight. Thus, wings (5) can be flattened against the airframe (2) of the missile (1) by a passive constraint, e.g., a shrink tubing (35) which disintegrates due to aerodynamic heating at a higher velocity stage of the flight, allowing each wing (5) to deploy into a position generally orthogonal to the airframe (2). The deployment force can be provided by torsionally and compressionally preloaded springs (19).
摘要翻译：在诸如导弹的引导弹药中，通常需要在早期的低速飞行阶段期间否定由翼（5）施加的升力。因此，翼（5）可以通过被动约束（例如，由于在飞行的更高速度阶段的空气动力学加热而分解的收缩管（35））而平坦地抵靠导弹（1）的机身（2），允许每个翼（5）部署到大致垂直于机身（2）的位置。部署力可以通过扭转和压缩的预加载弹簧（19）来提供。

4. 发明授权

US4296894A Drone-type missile 失效
标题翻译：无人机型导弹
公开(公告)号：US4296894A
公开(公告)日：1981-10-27
申请号：US14720
申请日：1979-02-23
申请人： Werner Schnabele , Jack Buckley , Ulrich Rieger
发明人： Werner Schnabele , Jack Buckley , Ulrich Rieger
IPC分类号： F42B10/14 , F42B15/10 , F42B13/32 , F42B15/16
CPC分类号： F42B15/10 , F42B10/14
摘要： The invention relates to a drone-type missile for combatting ground targets from the ground, particularly for the use against targets which emit electromagnetic rays, such as radar stations; with built-in target-seeking head, guidance system, self-propulsion and take-off assist, preferably a booster rocket.
摘要翻译：本发明涉及一种用于与地面对抗地面目标的无人机型导弹，特别是用于抵抗发射电磁射线的目标（如雷达站）; 内置目标寻找头，引导系统，自推进和起飞辅助，最好是助推火箭。

5. 发明授权

US4209146A Device for extensible fin blade on shell or the like 失效
标题翻译：外壳上的可扩展翅片叶片的装置等
公开(公告)号：US4209146A
公开(公告)日：1980-06-24
申请号：US876089
申请日：1978-02-08
申请人： Kjell Mattson
发明人： Kjell Mattson
IPC分类号： F42B10/14 , F42B13/32 , F42B15/16
CPC分类号： F42B10/14
摘要： An extensible fin assembly for attachment with the tail section of a gas propelled projectile and the like, wherein a plurality of similarly shaped, hollow fin members are positioned about the periphery of the tail section, with each hollow fin member having a fin blade mounted in a slot formed in the fin member for pivoting between retracted and extended positions relative to the respective fin members.
摘要翻译：一种用于与气体推进射弹等的尾部连接的可扩展翅片组件，其中多个类似形状的中空翅片构件围绕尾部周边定位，每个中空翅片构件具有安装在翅片叶片形成在所述翅片构件中的槽，用于相对于所述翅片构件在缩回位置和伸出位置之间枢转。

6. 发明授权

US4195573A Sub-caliber projectile of arrow-shaped form having a resistance-stabilizing tail section 失效
标题翻译：具有电阻稳定尾部的箭头形状的子口径射弹
公开(公告)号：US4195573A
公开(公告)日：1980-04-01
申请号：US879507
申请日：1978-02-21
申请人： Jurgen Leeker , Hanjorg Becker , Rudolf Rombach
发明人： Jurgen Leeker , Hanjorg Becker , Rudolf Rombach
IPC分类号： F42B10/14 , F42B10/06 , F42B10/34 , F42B10/48 , F42B14/06 , F42B13/32 , F42B13/16
CPC分类号： F42B14/061 , F42B10/06 , F42B10/48
摘要： A limited range, supersonic, sub-caliber projectile having a main body and a resistance-stabilizing tail section. This tail section has at least two bores through which air passes during flight of the projectile. The axes of the bores may be parallel or inclined relative to the longitudinal axis of the main body of the projectile.
摘要翻译：具有主体和电阻稳定尾部的有限范围的超音速，子口径射弹。这个尾部至少有两个孔，空气在射弹飞行过程中通过。孔的轴线可以相对于射弹主体的纵向轴线平行或倾斜。

7. 发明授权

US4175720A Retainer/release mechanism for use on fin stabilized gun fired projectiles 失效
标题翻译：用于翅片稳定枪射弹的保持器/释放机构
公开(公告)号：US4175720A
公开(公告)日：1979-11-27
申请号：US893635
申请日：1978-04-05
申请人： W. Dale Craig
发明人： W. Dale Craig
IPC分类号： F42B10/14 , F42B13/32
CPC分类号： F42B10/14
摘要： The tail section of a fin-stabilized, guided projectile having centrifuga deployed fins is disclosed. A fin retainer and release mechanism engages the projectile fins and holds the fins within the projectile diameter during normal stowage, handling and travel of the projectile down the gun tube. The fin retainer and release mechanism is designed to operate from the forces of gun launch to enable centrifugal deployment of the fins due to projectile rotation after the projectile leaves the gun tube.
摘要翻译：公开了具有离心式展翅的翅片稳定的引导抛射体的尾部。翅片保持器和释放机构与弹射片接合，并且在正常的存放，处理和射弹向下移动枪管的过程中将翅片保持在射弹直径内。翅片保持器和释放机构被设计成从枪发射的作用下操作，以便在射弹离开喷枪管之后由于射弹旋转而使散热片能够离心展开。

8. 发明授权

US4013245A Homing projectile 失效
标题翻译：归巢弹丸
公开(公告)号：US4013245A
公开(公告)日：1977-03-22
申请号：US638138
申请日：1975-12-05
申请人： Lyman F. Vanbuskirk
发明人： Lyman F. Vanbuskirk
IPC分类号： F41G7/22 , F42B10/64 , F41G7/14 , F41G7/00 , F41G7/18 , F42B13/32
CPC分类号： F41G7/222 , F41G7/2253 , F41G7/2293 , F42B10/64
摘要： An optical guidance system for a spin-stabilized autorotative projectile ing a target radiation detector, a detector cooling means, a fixed-coil electromagnet and a tuned-frequency steering vane. During projectile flight the detector temperature is reduced for increasing the sensitivity of the detector to radiation. When target radiation is detected, a signal is generated that is representative of target deviation from the flight path of the projectile. This signal sets up a periodic oscillation in an electromagnet for generating an electromagnetic force which, periodically and in phase with the oscillation, projects a steering vane into the air stream, creating a lift on the projectile to steer it to a target.
摘要翻译：一种用于具有目标辐射检测器，检测器冷却装置，固定线圈电磁体和调频转向器的自旋稳定自旋放射体的光学引导系统。在射弹飞行期间，检测器温度降低，以提高检测器对辐射的敏感度。当检测到目标辐射时，产生代表与射弹的飞行路径的目标偏差的信号。该信号在电磁体中建立周期性振荡，用于产生电磁力，该电磁周期性地和与振荡相同步地将转向叶片投射到空气流中，在射弹上产生电梯以将其转向目标。

9. 发明授权

US3888175A Mechanical stabilizer 失效
标题翻译：机械稳定剂
公开(公告)号：US3888175A
公开(公告)日：1975-06-10
申请号：US58827966
申请日：1966-10-18
申请人： US ARMY
发明人： DUSOE GEORGE D , MESSINEO JOSEPH R
IPC分类号： F42B10/14 , F42B13/32 , F42B25/00
CPC分类号： F42B10/146
摘要： 1. In a munition having a body and a rear base, said rear base having a floor and an outer flange defining a recess, THE IMPROVEMENT COMPRISING, IN COMBINATION THEREWITH, A REAR STABILIZER FOR CONTROLLING THE TRAJECTORY OF SAID MUNITION, SAID REAR STABILIZER COMPRISING A HELICAL COIL SPRING HAVING CONVOLUTIONS OF GRADUALLY INCREASING WIDTHS, SAID SPRING BEING ATTACHED AT ITS INNERMOST CONVOLUTION DIRECTLY TO THE CENTER REGION OF SAID FLOOR OF SAID RECESS, AND A COLLAPSIBLE FRUSTOCONICAL COVERING FOR SAID SPRING EXTENDING FROM THE INNERMOST TO THE OUTERMOST CONVOLUTION OF SAID SPRING, SAID SPRING AND COVERING BEING NORMALLY CONFINED IN COMPRESSED AND COLLAPSED CONDITION IN SAID RECESS AND HAVING THE PORTION OF THE COVERING WHICH SURROUNDS THE OUTERMOST CONVOLUTION OF SAID SPRING IN ENGAGEMENT WITH THE FLANGE OF SAID RECESS, AND SAID COVERING FORMING IN THE RELEASED POSITION OF SAID SPRING AN EMPTY HOLLOW ELONGATED INVERTED FRUSTOCONICAL STABILIZING SURFACE AT THE REAR OF SAID MUNITION; WHEREBY WHEN SAID MUNITION IS LAUNCHED, SAID SPRING WILL EXTEND ITSELF OUTWARDLY UPON CENTRIFUGAL FORCES GENERATED BY IN-FLIGHT MOVEMENTS OF SAID MUNITION.
摘要翻译： 1.在具有主体和后底座的弹药中，所述后底座具有底板和限定凹部的外凸缘，其改进包括组合，用于控制所述移动轨迹的后稳定器，所述后置稳定器包括具有梯级增长宽度的旋转螺旋弹簧，直接连接到指定地面上的中心区域的直接旋转的连续弹簧，以及用于从内在扩展到内部弹簧的外部旋转的可折叠的FRUSTOCONICAL覆盖，SAID弹簧和盖子在被压缩和收缩的状态下被正常地限定在同样的记录中，并且具有覆盖的部分，该外壳包含与所述接收的法兰结合的外部弹簧的外部转换，并且在释放的位置中形成覆盖在后面的弹道上弹起一个空白的反转的自动稳定表面; 鉴于现在已经启动了这个机构，所谓的弹簧将不会因为飞行员的飞行员所产生的离散力而扩展。

10. 发明授权

US3790104A High/low aspect ratio dual-mode fin design 失效
标题翻译：高/低比例双模融合设计
公开(公告)号：US3790104A
公开(公告)日：1974-02-05
申请号：US3790104D
申请日：1973-03-12
申请人： US NAVY
发明人： JONES D
IPC分类号： F42B10/14 , F42B13/32
CPC分类号： F42B10/14
摘要： A dual-mode fin design for gun-launched, rocket-assisted, guided projectiles in which, from a flush position against the body, the fins rotate radially at launch to deploy in the low aspect-ratio mode for stability during the supersonic fly-out phase with transition to the high aspect-ratio mode for the transonic termianl maneuvering phase. Deployment of the fins to high aspect-ratio mode is effected by shearing restraining pins which allow the fins to rotate rearwardly about pivot pins and under the air stream influence.
摘要翻译：一种用于炮弹发射的火箭辅助引导弹体的双模式翅片设计，其中，从冲击位置抵靠身体的翅片在发射时径向旋转以部署在低纵横比模式以在超音速飞行时稳定，转换到跨音速termianl机动阶段的高纵横比模式。将翅片部署到高纵横比模式是通过剪切限制销实现的，该限制销允许翅片围绕枢轴销向后旋转并且在气流影响下旋转。

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