专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明申请

WO2017105586A1 BASE DRAG REDUCTION FAIRING USING SHAPE MEMORY MATERIALS 审中-公开
标题翻译：使用形状记忆材料进行基础减载
公开(公告)号：WO2017105586A1
公开(公告)日：2017-06-22
申请号：PCT/US2016/055229
申请日：2016-10-03
申请人： RAYTHEON COMPANY
发明人： SUMMERS, Matthew H. , KOEHLER, Frederick B. , DANFORTH, Jeremy C. , VILLARREAL, James K.
IPC分类号： F42B10/14 , F42B10/40 , F42B10/44
CPC分类号： F42B10/38 , B63G8/00 , F42B10/14 , F42B10/40 , F42B10/44
摘要： A device (100) is provided. The device includes at least one SMM component (115, 120, 130) fabricated from a shape memory material (SMM). The SMM component is configured to change shape in response to receiving a stimulus. The SMM component is also configured to deploy from a device body (105) of the device allowing the device to change shape in an advantageous way. A method (1000) implemented by a device (100) is also provided. The method includes changing (1010) a shape of an SMM component (115, 120, 130) of the device in response to receiving a stimulus. The SMM component is fabricated from an SMM. The method also includes deploying (1015) the SMM component from a device body (105) of the device allowing the device to change shape in an advantageous way.
摘要翻译：提供了一种设备（100）。该装置包括由形状记忆材料（SMM）制造的至少一个SMM部件（115,120,130）。 SMM组件配置为响应接收刺激而改变形状。 SMM部件还被配置为从装置的装置主体（105）展开，允许装置以有利的方式改变形状。还提供了由设备（100）实现的方法（1000）。该方法包括响应于接收刺激而改变（1010）设备的SMM组件（115,120,130）的形状。 SMM组件是由SMM制造的。该方法还包括从设备的设备主体（105）部署（1015）SMM组件，允许设备以有利的方式改变形状。

2. 发明申请

WO2015179101A2 GUN LAUNCHED MUNITION WITH STRAKES 审中-公开
标题翻译：枪支发射枪
公开(公告)号：WO2015179101A2
公开(公告)日：2015-11-26
申请号：PCT/US2015/028592
申请日：2015-04-30
申请人： BAE SYSTEMS LAND & ARMAMENTS L.P.
发明人： CITRO, Robert, W. , O'BRIEN, Paul, M. , JANKE, Patrick, J. , QUOTRUP, Conlee, O.
IPC分类号： F42B10/00 , F42B14/00 , B64C39/02
CPC分类号： F42B14/06 , F42B10/14
摘要： A projectile that includes strakes mounted about the perimeter of the midsection of the projectile and a pusher plate assembly mounted about the aft of the projectile so that a sub- caliber projectile may be fired from a larger caliber gun. The pusher plate assembly forms a seal with the bore at the aft end of the projectile. The strakes maintain the center line position of the projectile within the bore. The pusher plate assembly further designed to fragment upon exiting the bore while the strakes remain with the projectile to enhance aerodynamic qualities of the projectile in flight.
摘要翻译：一种抛射体，其包括围绕射弹中部周边安装的斜面，以及围绕射弹后部安装的推板组件，以便可以从较大的口径枪射出一个机芯射弹。推动板组件与射弹尾端处的孔形成密封。桅杆将炮弹的中心线位置保持在钻孔内。推进板组件进一步设计成在离开钻孔时分裂，同时该挡板保留在抛射体上，以提高飞行中弹丸的空气动力学质量。

3. 发明申请

WO2011002530A3 REINFORCED INFLATABLE WINGS FOR FITMENT-CONSTRAINED AIR VEHICLES 审中-公开
标题翻译：用于配装有限的空气车辆的加强的可充气翼
公开(公告)号：WO2011002530A3
公开(公告)日：2011-02-24
申请号：PCT/US2010024307
申请日：2010-02-16
申请人： RAYTHEON CO , SANDERSON TERRY M , EISENTRAUT RUDY A , HATFIELD DAVID B
发明人： SANDERSON TERRY M , EISENTRAUT RUDY A , HATFIELD DAVID B
IPC分类号： F42B10/14 , F42B10/20
CPC分类号： B64C3/30 , B64C2201/102 , B64C2201/105 , F42B10/14 , F42B10/146 , F42B10/20
摘要： A reinforced inflatable wing improves the tolerance of the OML and reinforces the wing in at least the high load areas. This approach provides fitment constrained air vehicles with wings having increased surface area to improve flight endurance or aerodynamic control. A wing box (20,108, 208, 308, 400) forms a first portion of the wing. A skin having a plurality of rigid plates (40,122, 222, 322, 406) affixed thereto is inflated to form a second portion of the wing to either increase the chord length or lengthen the wing span. The skin is suitably inflated with foam to form a solid wing.
摘要翻译：增强的充气翼改善了OML的公差，并加强了至少在高负载区域中的机翼。这种方法提供具有增加的表面面积的具有翼的装备受限的空中车辆，以改善飞行耐力或空气动力学控制。机翼箱（20,108,208,308,400）形成机翼的第一部分。具有固定到其上的多个刚性板（40,122,222,322,406）的皮肤被充气以形成机翼的第二部分，以增加弦长或延长机翼跨度。皮肤适当地用泡沫充气以形成固体翼。

4. 发明申请

WO2011002530A2 REINFORCED INFLATABLE WINGS FOR FITMENT-CONSTRAINED AIR VEHICLES 审中-公开
标题翻译：用于配装有限的空气车辆的加强的可充气翼
公开(公告)号：WO2011002530A2
公开(公告)日：2011-01-06
申请号：PCT/US2010/024307
申请日：2010-02-16
申请人： RAYTHEON COMPANY , SANDERSON, Terry, M. , EISENTRAUT, Rudy, A. , HATFIELD, David, B.
发明人： SANDERSON, Terry, M. , EISENTRAUT, Rudy, A. , HATFIELD, David, B.
IPC分类号： F42B10/14
CPC分类号： B64C3/30 , B64C2201/102 , B64C2201/105 , F42B10/14 , F42B10/146 , F42B10/20
摘要： A reinforced inflatable wing improves the tolerance of the OML and reinforces the wing in at least the high load areas. This approach provides fitment constrained air vehicles with wings having increased surface area to improve flight endurance or aerodynamic control. A wing box forms a first portion of the wing. A skin having a plurality of rigid plates affixed thereto is inflated to form a second portion of the wing to either increase the chord length or lengthen the wing span. The skin is suitably inflated with foam to form a solid wing.
摘要翻译：增强的充气翼改善了OML的公差，并加强了至少在高负载区域中的机翼。这种方法提供具有增加的表面面积的具有翼的装备受限的空中车辆，以改善飞行耐力或空气动力学控制。翼盒形成翼的第一部分。具有固定到其上的多个刚性板的皮肤被充气以形成机翼的第二部分，以增加弦长或延长机翼跨度。皮肤适当地用泡沫充气以形成固体翼。

5. 发明申请

WO2009103939A2 CONTROL OF PROJECTILES OR THE LIKE 审中-公开
标题翻译：控制弹丸或类似物
公开(公告)号：WO2009103939A2
公开(公告)日：2009-08-27
申请号：PCT/GB2009/000082
申请日：2009-01-13
申请人： QINETIQ LIMITED , BUCKLAND, Roy, William , SMITH, Stephen, George, Gladwell
发明人： BUCKLAND, Roy, William , SMITH, Stephen, George, Gladwell
IPC分类号： F42B10/14 , F42B10/64
CPC分类号： F42B10/14 , F42B10/64
摘要： A gun-fired projectile or ballistic missile (1) is equipped with a pair of canards (3) and an array of tail fins (2). Selected tail fins can be retracted or jettisoned following the ballistic phase to vary the geometry of the array from a rotationally symmetrical configuration to an asymmetric configuration for the glide phase, which together with the canards tends to stabilise the projectile in roll. The canards (3) can be independently extended and retracted with respect to the body of the projectile to generate differential lift for banking the projectile to turn. The canards (3) also preferably have a positive dihedral angle with respect to the intended gliding attitude. In an alternative embodiment the canards are replaced by functionally equivalent thrusters.
摘要翻译：炮射弹或弹道导弹（1）配有一对鸭翼（3）和一组尾翼（2）。选定的尾鳍可以在弹道阶段后缩回或抛弃，以将阵列的几何结构从旋转对称结构改变为滑翔阶段的不对称结构，其与鸭翼一起倾向于使抛射物稳定地卷绕。鸭嘴（3）可以独立地相对于抛射体的主体伸出和缩回，以产生用于储存抛射体的差动升力。鸭嘴（3）也优选相对于预期的滑行姿态具有正二面角。在另一个实施例中，鸭嘴被功能相当的推进器替换。

6. 发明申请

WO2009051865A1 LOCKING ASSEMBLY FOR ROTARY SHAFTS 审中-公开
标题翻译：旋转装置的锁定装置
公开(公告)号：WO2009051865A1
公开(公告)日：2009-04-23
申请号：PCT/US2008/068817
申请日：2008-06-30
申请人： HR TEXTRON INC. , MOCK, M. Robert , WOODRUFF, Mark
发明人： MOCK, M. Robert , WOODRUFF, Mark
IPC分类号： F42B10/14 , F42B10/64
CPC分类号： F42B10/14 , F42B10/64 , Y10T403/60 , Y10T403/604
摘要： A locking assembly has a base (40) and a rotary shaft (42) which is capable of rotating relative to the base (40). The rotary shaft (42) has a shaft body and a set of capture portions (48A, B) supported by the shaft body. The locking assembly further includes a set of detention mechanisms (44) supported by the base (40). The set of detention mechanisms (44) is arranged to (i) initially apply retention force to the set of capture portions (48A, B) to provide resistance against rotation of the rotary shaft (42) from an initial angular position, and (ii) remove application of the retention force from the set of capture portions (48A, B) in response to an amount of rotational torque on the rotary shaft (42). The amount of rotational torque on the rotary shaft (42) exceeds a predetermined threshold and is sufficient to substantially rotate the rotary shaft (42) from the initial angular position.
摘要翻译：锁定组件具有能够相对于基座（40）旋转的基座（40）和旋转轴（42）。旋转轴（42）具有轴体和由轴体支撑的一组捕获部分（48A，B）。锁定组件还包括由基座（40）支撑的一组拘留机构（44）。所述一组拘留机构（44）被布置成：（i）首先向所述一组捕获部分（48A，B）施加保持力，以提供抵抗所述旋转轴（42）从初始角位置旋转的阻力，以及（ii 响应于旋转轴（42）上的旋转扭矩的量，去除了该组捕获部分（48A，B）的保持力的施加。旋转轴（42）上的旋转扭矩的量超过预定的阈值并且足以使旋转轴（42）从初始角位置大致旋转。

7. 发明申请

WO2009005540A1 SYSTEMS AND METHODS FOR A PROJECTILE HAVING A STABILIZER FOR SPIN STABILIZATION 审中-公开
标题翻译：用于具有稳定性的旋转稳定性的项目的系统和方法
公开(公告)号：WO2009005540A1
公开(公告)日：2009-01-08
申请号：PCT/US2007/087814
申请日：2007-12-17
申请人： TASER INTERNATIONAL, INC.
发明人： GAVIN, William David , ZEKONOVIC, Dubravko
IPC分类号： F42B10/00 , F42B15/01
CPC分类号： F42B10/14 , F41H13/0025 , F41H13/0031 , F42B10/26
摘要： A round, according to various aspects of the present invention, launches an electrified projectile for spin stabilized flight. The projectile provides a current through a target to incapacitate the target by causing skeletal muscle contractions. The projectile includes a body and a stabilizer. The stabilizer has a first torsion stored along a first axis and a second torsion stored along a second axis. Torsions are released to deploy the stabilizer and to bias the stabilizer during flight.
摘要翻译：根据本发明的各个方面，一轮发射自旋稳定飞行的带电弹丸。射弹通过引起骨骼肌收缩的目标提供目标，使目标失能。射弹包括身体和稳定器。稳定器具有沿第一轴线存储的第一扭矩和沿第二轴线存储的第二扭矩。释放扭矩来部署稳定器并在飞行期间偏置稳定器。

8. 发明申请

WO2008143707A2 COURSE CORRECTING FUZE 审中-公开
标题翻译：课程校正FUZE
公开(公告)号：WO2008143707A2
公开(公告)日：2008-11-27
申请号：PCT/US2007/086798
申请日：2007-12-07
申请人： PEMERY CORP. , PRISTASH, David, J.
发明人： PRISTASH, David, J.
IPC分类号： F42C19/12
CPC分类号： F42C19/00 , F42B10/14 , F42B10/54 , F42B10/64
摘要： A course correcting fuze for use in artillery warheads or other military projectiles. Mechanisms are provided whereby air brake fins and spin control fins can be deployed and retracted under computer control during projectile flight to improve targeting accuracy. Power is supplied by an innovative fuel cell module that allows for long term storage of the fuze, rapid activated during launch of the artillery shell, and sufficient power for use by the electronics and actuator motors during operation.
摘要翻译：修改用于炮弹或其他军用射弹的引信课程。提供机构，由此在抛射飞行期间可以在计算机控制下展开和缩回空气制动片和旋转控制翼，以提高瞄准精度。电力由创新的燃料电池模块提供，其允许长期存储引信，在发射炮弹期间快速激活，以及在操作期间由电子和致动器电动机使用的足够的电力。

9. 发明申请

WO2007133247A2 FIN RETENTION AND DEPLOYMENT MECHANISM 审中-公开
标题翻译：财产保留和部署机制
公开(公告)号：WO2007133247A2
公开(公告)日：2007-11-22
申请号：PCT/US2006/038901
申请日：2006-10-05
申请人： GENERAL DYNAMICS ORDNANCE AND TACTICAL SYSTEMS, INC.
发明人： SCHROEDER, Richard, W.
IPC分类号： F42B10/00
CPC分类号： F42B10/14 , F42B10/64
摘要： A fin retention and deployment mechanism that has the advantage of providing for the deployment of aerodynamic control surfaces on command without the need for an additional actuation device or control circuitry separate from the actuator that controls the angle of the fins during flight. The actuator that is already required for operation of the control surfaces after deployment initiates the deployment of the fins, as well. A latch mechanism comprises a retaining member and a latch, which engages the retaining member enabling a biasing mechanism to force the fins from a stowed position to a fully deployed position.
摘要翻译：翅片保持和部署机构具有提供空中动力学控制表面部署的优点，而不需要与控制飞行中翅片角度的致动器分离的附加致动装置或控制电路。已经在部署之后操作控制表面所需的执行器也启动了散热片的部署。闩锁机构包括保持构件和闩锁，其接合保持构件，使得能够将偏压机构从收起位置强制到完全展开位置。

10. 发明申请

WO2003081165A1 MISSILE HAVING DEPLOYMENT MECHANISM FOR STOWABLE FINS 审中-公开
标题翻译：有可能存在的FINS的部署机构的MISSILE
公开(公告)号：WO2003081165A1
公开(公告)日：2003-10-02
申请号：PCT/US2003/007931
申请日：2003-03-14
申请人： RAYTHEON COMPANY
发明人： EISENTRAUT, Rudolph, Adolph , KEBSCHULL, Martin, Allen , PARINE, John, Christopher
IPC分类号： F42B10/14
CPC分类号： F42B10/14
摘要： A missile (10) having a deployment mechanism (14) that automatically pivots and rotates a fin (12) from a stowed orientation to a deployed orientation. The deployment mechanism (14) includes a spring (38) that provides a biasing forces that urges the fin (12) to move quickly, simply and reliably from the stowed orientation to the deployed orientation.
摘要翻译：具有展开机构（14）的导弹（10），所述展开机构（14）能够使翅片（12）从收起的方向自动枢转并旋转到展开方向。展开机构（14）包括弹簧（38），弹簧（38）提供促使翅片（12）快速，简单且可靠地从收起的方向移动到展开方位的偏压力。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式