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公开(公告)号：US4784350A
公开(公告)日：1988-11-15
申请号：US22125
申请日：1979-02-12
Applicant: Ralph M. Darden
Inventor： Ralph M. Darden
Abstract: A passive step trimmer for a maneuvering re-entry body (MRB) which uses existing inertial forces acting on the MRB to deploy a free flowing mass from the rear of the MRB to trim the MRB altitude. The mass deployment from the MRB causes a forward shift in the center of gravity (CG) which in turn creates a more stable body which flies at a reduced angle-of-attack (.alpha.).
Abstract translation: 用于机动重返机体（MRB）的被动步进修剪器，其使用作用在MRB上的现有惯性力来从MRB的后部部署自由流动的质量以修剪MRB高度。 来自MRB的大规模部署引起重心（CG）的向前移动，这又产生了一个更加稳定的身体，以减小的攻角（Alpha）飞行。
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公开(公告)号：US4568041A
公开(公告)日：1986-02-04
申请号：US591159
申请日：1984-03-19
Applicant: Kent G. Whitham
Inventor： Kent G. Whitham
CPC classification number: F42B10/64 , Y10T403/4681 , Y10T403/7039
Abstract: An improved fin attachment having a socket for reception of a tang mountedn a missile fin, an element for drawing the tang into the socket, and frusto-conical concentric rings which engage the tang and the socket to connect them rigidly in a predetermined angular relation. All elements of the attachment are retained so as not to be lost when the fin is detached, and the attachment provides effective connection without the use of complex shapes or precise manufacturing tolerances.
Abstract translation: 改进的翅片附件具有用于接收安装在导弹翅片上的脚的插座，用于将脚部拉入插座的元件以及与脚部和插座接合的截头圆锥形同心环，以使它们以预定的角度关系刚性地连接 。 附件的所有元件被保持以便当散热片脱离时不会损失，并且附件提供有效的连接而不使用复杂的形状或精确的制造公差。
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公开(公告)号：US4456202A
公开(公告)日：1984-06-26
申请号：US418895
申请日：1982-09-16
Applicant: Donald A. Price, Jr. , Charles A. Louis, III
Inventor： Donald A. Price, Jr. , Charles A. Louis, III
Abstract: A method of increasing the predictable effectiveness of a ballistic reentryody having a predicted nominal reentry trajectory. Beginning at reentry or another predetermined location, the distance travelled by said reentry body is calculated based on measured longitudinal acceleration and preset predicted trajectory parameters. When the reentry body reaches a predetermined altitude as measured by an onboard radar, the calculated distance travelled to the altitude is compared with the predicted nominal distance travelled to the altitude to determine the actual trajectory of the reentry body. Based on this actual trajectory, the actual distance travelled from reentry to a preferred fuzing location is determined. When the calculated distance travelled equals the distance required to reach the preferred fuzing location, the fuze signal is sent to the fire set and then to the warhead.
Abstract translation: 一种增加具有预测的名义折返轨迹的弹道折返体的可预测有效性的方法。 从折返或其他预定位置开始，基于所测量的纵向加速度和预设的预测轨迹参数来计算所述折回体所行进的距离。 当折返体达到通过机载雷达测量的预定高度时，将计算出的到高度的距离与行进到高度的预测的标称距离进行比较，以确定折返体的实际轨迹。 基于该实际轨迹，确定从再入行驶到优选位置的实际距离。 当计算出的行驶距离等于达到优选扶正位置所需的距离时，引信信号被发送到火力组，然后发送到弹头。
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公开(公告)号：US4364530A
公开(公告)日：1982-12-21
申请号：US184823
申请日：1980-09-08
Applicant: Michael J. Ripley-Lotee , Robert B. Dillinger , Keith E. Clark
Inventor： Michael J. Ripley-Lotee , Robert B. Dillinger , Keith E. Clark
CPC classification number: F42B15/36 , F42B10/665
Abstract: A modular, apogee-control package is disclosed which can be added to exisg missiles, and which will limit the apogee of the missile trajectory by implementation of thrust vector control (TVC). The package comprises a boost guidance unit, a solid rocket propellant motor, and jet vane TVC.
Abstract translation: 公开了一种模块化的远地点控制组件，可以将其添加到现有的导弹中，并通过实施推力矢量控制（TVC）来限制导弹轨迹的远地点。 该包装包括增压引导单元，固体火箭推进剂马达和喷气叶片TVC。
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公开(公告)号：US4245890A
公开(公告)日：1981-01-20
申请号：US327
申请日：1979-01-02
Applicant: Richard L. Hartman , Bob D. Guenther
Inventor： Richard L. Hartman , Bob D. Guenther
Abstract: A missile having a sensor in the nose thereof. The nose is in the shape of transparent ogive window which has an index of refraction that assumes different values at different positions on the window whereas the window appears to the sensor as if it were a hemispherical window.
Abstract translation: 在其鼻子中具有传感器的导弹。 鼻子是透明的窗户的形状，其具有折射率，其在窗口的不同位置处呈现不同的值，而窗口看起来像传感器一样是半球形的窗口。
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Patent Agency Ranking6.发明授权Ideal trajectory shaping for anti-armor missiles via time optimal controller autopilot 失效通过时间优化控制器自动驾驶仪，进行反铠装导弹的理想轨迹整形
公开(公告)号：US4198015A
公开(公告)日：1980-04-15
申请号：US910307
申请日：1978-05-30
Applicant: Robert E. Yates , John P. Leonard , Robert E. Alongi
Inventor： Robert E. Yates , John P. Leonard , Robert E. Alongi
CPC classification number: F41G7/343 , F41G7/008 , F41G7/2253 , F41G7/226 , F41G7/2293 , G05D1/107
Abstract: A missile system in which a missile is guided in a predetermined trajectoryrom launch or shortly thereafter in yaw by proportional navigation and in pitch first by a pitch programmer until said missile reaches a predetermined angle between a line of sight of a seeker of the missile and a centerline of the missile, then in pitch by a time optimal controller to direct the missile at a predetermined angle toward a target and finally by proportional navigation in pitch of the missile to the target.
Abstract translation: 一种导弹系统，其中导弹在预定轨迹中从发射引导或不久之后通过比例导航在偏航中被引导，并且首先由俯仰编程员进行俯仰，直到所述导弹达到导弹的引导者的视线之间的预定角度， 导弹的中心线，然后按时间优化控制器，将导弹以预定角度瞄准目标，最后通过导弹到目标的俯仰比例导航。
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公开(公告)号：US4116404A
公开(公告)日：1978-09-26
申请号：US818188
申请日：1977-07-22
Applicant: Thomas H. Howell
Inventor： Thomas H. Howell
CPC classification number: F42B10/30
Abstract: An automatic balancing concept including two annular containers used to dmically balance a rocket during flight. The containers are partially filled with a high density fluid and are installed forward and aft of the longitudinal CG of the rocket. When spin is induced in the rocket the radial CG will shift to the spin axis and the fluid will couple itself to the outside diameter of the ring.
Abstract translation: 一种自动平衡概念，包括两个环形容器，用于在飞行过程中动态平衡火箭。 容器部分地填充有高密度流体，并且安装在火箭的纵向CG的前方和后方。 当在火箭中引起旋转时，径向CG将移动到旋转轴线，并且流体将其自身联接到环的外径。
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公开(公告)号：US4044237A
公开(公告)日：1977-08-23
申请号：US667819
申请日：1976-03-16
Applicant: Paul N. Cowgill , John L. Pearson
Inventor： Paul N. Cowgill , John L. Pearson
Abstract: A lifting body missile is controlled by pitch and roll commands wherein theaw autopilot is caused to change in accordance with the roll and estimated angle of attack input information. A command logic is provided to determine the polarity of the command signals to the autopilot.
Abstract translation: 提升体导弹由俯仰和滚转命令控制，其中偏航自动驾驶仪根据滚动和估计的迎角输入信息而改变。 提供命令逻辑以确定自动驾驶仪的命令信号的极性。
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公开(公告)号：US3924824A
公开(公告)日：1975-12-09
申请号：US40712173
申请日：1973-10-17
Applicant: SINGER CO
Inventor： BRODIE PETER M , SOLOV EDWIN G
Abstract: A simplified strapdown inertial guidance system is provided for the cross track or inertial ''''line-of-sight'''' planar guidance of an unmanned tactical vehicle, or the like; wherein one of the attitude angles can be of large magnitude. The system includes three orthogonally-mounted accelerometers and two gyroscopes. The large attitude angle is accommodated by torquing the appropriate gyroscope in a capture loop. The system implements the body attitude angles to inertial attitude angles in two steps. First a transformation is made from body to gyroscope coordinates, and then a transformation is made from gyroscope to inertial coordinates.
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公开(公告)号：US3912198A
公开(公告)日：1975-10-14
申请号：US40900764
申请日：1964-11-04
Applicant: LTV AEROSPACE CORP
Inventor： DELL CHARLES C , HARMS JR A D , KNOWLES ALBERT B , MEREDITH FRED D , SUTHERLAND SPURGEON
CPC classification number: F41G7/2253 , F41G7/007 , F41G7/2293
Abstract: 1. A tracking system including: a device having means providing a surface on which light from a predetermined optical field may be focused, said means emitting electrons at each point of said surface in accordance with the intensity of light impinging thereon, an anode, and means for focusing electrons emitted from a small area of said surface on said anode; moving means for continuously changing in a predetermined manner the position of said small area of said surface from which emitted electrons are focussed on said anode; and means and operatively associated with last mentioned means responsive to the intensity of the emitted electrons focussed on said anode for causing the position of said small area to be within a large area of said surface on which impinges light of an intensity different than that of the light impinging on areas of said surface about said large area by causing said moving means to move the position of said small area back into said large area and away from an edge of said large area when said small area tends to move past an edge of said large area.
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