公开(公告)号：WO1988001106A1

公开(公告)日：1988-02-11

申请号：PCT/US1987001755

申请日：1987-07-21

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： HUGHES AIRCRAFT COMPANY ,  LEE, Jar, Jueh ,  TANG, Raymond

IPC: H01Q21/22

CPC classification number: H01Q21/22 ,  H01Q21/0025

Abstract: A low sidelobe, solid state array antenna apparatus comprises a large radiating aperture divided into a large number, N, of small, closely spaced radiating apertures, each small radiating aperture having associated therewith a radiating element and a linearly polarized solid state power module. The large radiating aperture is divided into M, preferably between (3) and about (10), differently sized, elliptically shaped, concentric radiating zones superimposed, for analysis purposes, upon another. Each such zone has an output voltage amplitude, Ei, and semi-major and semi-minor axes of respective lengths, ai and bi, each zone being considered separately in the far field equation: G( theta , PHI ) = [f( theta ,$ gamma ( PHI ) (â theta cos PHI - â PHI sin PHI cos theta )] , wherein f( theta , PHI ) = (I), ui = (II), J1 i is the first order Bessel function, â theta and â PHI are unit vectors in the spherical coordinates and Ko is the wave number associated with the radiated field. Using the far field equation, values of Ei, ai and bi for each zone are computed which result in the far field sidelobe peak gain being a minimum or being a specified number of dB, for example, at least about 30 dB, below the far field mainlobe gain. The values of Ei in overlapping zones are summed to establish the required voltage amplitudes of the underlying power modules associated with the N radiation apertures.

Abstract translation: 低旁瓣固体阵列天线装置包括被分成大量N个小的紧密间隔的辐射孔的大辐射孔，每个小辐射孔具有辐射元件和线偏振固态功率模块。 大的辐射孔被分成M，优选在（3）和（10）之间，不同尺寸的椭圆形同心辐射区域，用于分析目的叠加在另一个上。 每个这样的区域具有相应长度的输出电压幅度Ei和半主轴和半短轴ai和bi，每个区域在远场方程中分别考虑：G（θ，PHI）= [f ，其中f（θ，PHI）=（I），ui =（II），J1（i）），其中f（θ，PHI） 是第一阶贝塞尔函数，Θ和âPHI是球面坐标中的单位矢量，Ko是与辐射场相关联的波数，使用远场方程，计算每个区域的Ei，ai和bi值 这导致远场旁瓣峰值增益是最小值或者是指定数量的dB，例如至少约30dB，远远于主场主瓣增益，重叠区域中的Ei值相加以建立所需电压 与N个辐射孔相关联的底层功率模块的振幅。

公开(公告)号：WO1988000730A1

公开(公告)日：1988-01-28

申请号：PCT/US1987001340

申请日：1987-06-08

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： HUGHES AIRCRAFT COMPANY ,  McINTYRE, John, E.

IPC: G05D01/08

CPC classification number: B64G1/281 ,  B64G1/24 ,  G05D1/0883

Abstract: A method for passively stabilizing the attitude of a spinning orbiting body subject to orbital precession to maintain the spin axis orientation of the body essentially fixed and stable relative to the orbital plane. The preferred embodiment comprises selecting a body mass geometry and orbital parameters, including an orbit inclination, an orbital rate and a rate of regression of orbit line of nodes, so that the precessional motion of the body and the orbit are equal and opposite in direction and locating the spin axis of the body in a plane containing the north axis of the body and the orbit normal and between the north axis and the orbit normal, so that the gravity gradient precession of the spin axis equals the regressional motion of the orbit normal to produce a planar equilibrium configuration.

公开(公告)号：WO1988000370A1

公开(公告)日：1988-01-14

申请号：PCT/US1987001591

申请日：1987-07-01

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： HUGHES AIRCRAFT COMPANY ,  MYERS, Terrence, L. ,  HARRINGTON, William, A.

IPC: G05F07/00

CPC classification number: G05F7/00 ,  H03K17/0826 ,  H03K17/64 ,  H03K17/662

Abstract: A device-implemented method for driving a ferrimagnetic load (10), such as a phase shifter in an antenna array, which precisely meters the amount of magnetic flux imparted to the load (10) by sensing the voltage applied to a winding and integrating the sensed voltage over time. The time integrated voltage is proportional to the magnetic flux imparted to the load (10) and is constantly compared to a preprogrammed value stored in a memory (18). When the sensed voltage reaches the preprogrammed value, the voltage is removed from the load (10) so that a metered amount of magnetic flux, proportional to the preprogrammed value, remains in the load (10). The load (10) is initially reset by delivering current in one direction through its winding until saturation is reached. The load (10) is set with a metered amount of magnetic flux by delivering current in the opposite direction through the winding. A current sensing circuit (68) senses the point at which the load (10) becomes saturated during the reset cycle and also senses current flow through the winding during the set cycle in order to prevent a current overload.

Abstract translation: 一种用于驱动诸如天线阵列中的移相器的亚铁磁负载（10）的器件实现方法，其通过感测施加到绕组的电压来精确地计量施加到负载（10）的磁通量，并将 感测电压随时间变化。 时间积分电压与施加到负载（10）的磁通成比例，并且与存储在存储器（18）中的预编程值不断地进行比较。 当感测到的电压达到预编程值时，从负载（10）中去除电压，使得与预编程值成比例的计量量的磁通量保持在负载（10）中。 负载（10）首先通过在一个方向上传递电流通过其绕组而复位，直到达到饱和。 负载（10）通过沿相反方向传递电流通过绕组而设置有计量的磁通量。 电流感测电路（68）检测在复位周期期间负载（10）变得饱和的点，并且还在设定的周期期间感测通过绕组的电流，以便防止电流过载。

公开(公告)号：WO1987007447A1

公开(公告)日：1987-12-03

申请号：PCT/US1987000955

申请日：1987-05-01

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： HUGHES AIRCRAFT COMPANY ,  POLLACK, Slava, A. ,  CHANG, David, B.

IPC: H01S03/16

CPC classification number: H01S3/11 ,  H01S3/08072 ,  H01S3/094038 ,  H01S3/094092 ,  H01S3/1608 ,  H01S3/1611 ,  H01S3/165 ,  H01S3/17

Abstract: A laser incorporating a laser medium disposed within a laser cavity and a pumping arrangement for selectively applying excitation energy to said laser medium. The laser medium contains upconverting material of the type which allows for the exchange of energy between electrons of the lasing ions at a given energy state below the meta-stable initial lasing state so that some of said exchanging electrons are upconverted to energy states at or above the meta-stable initial lasing state. The pumping arrangement applied energy of suitable wavelength and intensity for elevating electrons from energy levels below the given state to that state in sufficient numbers to support substantial upconversion and the resulting lasing.

Abstract translation: 一种激光器，其包括设置在激光腔内的激光介质和用于选择性地向所述激光介质施加激发能量的泵送装置。 激光介质包含上变频材料，其类型允许在低于等稳定的初始激光状态的给定能量状态下使激光离子的电子之间的能量交换，使得一些所述交换电子被上转换成等于或高于 元稳定的初始激光状态。 泵浦装置施加适当波长和强度的能量，以将电子从低于给定状态的能级提升到足够数量的电压，以支持实质的上变频和所产生的激光。

公开(公告)号：WO1987007389A2

公开(公告)日：1987-12-03

申请号：PCT/US1987001156

申请日：1987-05-13

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： HUGHES AIRCRAFT COMPANY ,  WELLS, Donald, R.

IPC: G01S07/02

CPC classification number: G01S7/026

Abstract: An adaptive radar apparatus (10) for substantially reducing background clutter, particularly relatively time-invariant clutter, such as sea clutter, and especially at low radar grazing angles. The apparatus (10) includes a transmitting antenna (12) having horizontally and vertically oriented, transmitting elements (26, 28) and a relative phase control therebetween and a receiving antenna (14) also with horizontally and vertically oriented receiving elements (30, 32) also having relative phase detection and phase shift possible therebetween. A controllable radar signal generator (16) is provided for supplying signals to the transmitting antenna (12) and a controllable signal processor (18) is provided for processing return signals from the receiving antenna (14). Means (20) are included for determining, from return test signals, a background mean null polarization for a number of radar range and azimuth cells and for providing null polarization control signals Ho, Vo and oo, to the signal generator (16) and return signal processor (18) to cause the radar to operate at a polarization state which is the same as the clutter mean null polarization. A corresponding method is provided for reducing background clutter, especially relatively time-invariant sea clutter, in low grazing angle radar.

公开(公告)号：WO1987007235A2

公开(公告)日：1987-12-03

申请号：PCT/US1987000926

申请日：1987-04-24

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： HUGHES AIRCRAFT COMPANY ,  WITTMANN, Alois

IPC: B64G01/64

CPC classification number: B64G1/641

Abstract: A clamping connection assembly for separable parts of a spacecraft is provided and includes a tension belt for securing a plurality of retainers against camming surfaces on flange members on separable spacecraft component parts. The other peripheral edges of the flange members have detents to respectively receive a single shear pin mounted on each of the retainers. The shear pins receive any shear and torsional forces and transmit them between the structural parts of the spacecraft components without creating additional forces on the tension belt.

Abstract translation: 提供了一种用于航天器可分离部件的夹紧连接组件，包括用于将多个保持器固定在可分离的航天器部件上的凸缘部件上的凸轮表面上的张力带。 凸缘构件的其它周缘具有棘爪以分别容纳安装在每个保持器上的单个剪切销。 剪切销承受任何剪切力和扭转力，并将它们在航天器部件的结构部件之间传递，而不会在张力带上产生额外的力。

公开(公告)号：WO1987006091A2

公开(公告)日：1987-10-08

申请号：PCT/US1987000317

申请日：1987-02-17

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： HUGHES AIRCRAFT COMPANY ,  LONGERICH, Ernest, P. ,  D'AGOSTINO, Saverio

IPC: H05K01/14

CPC classification number: H05K7/20236 ,  G02B6/001 ,  H01R12/52 ,  H05K1/144 ,  H05K7/1434 ,  H05K2201/0314

Abstract: A configuration of an electronics unit wherein a plurality of circular circuit cards are arranged in an aligned, parallel relationship. Each card has a central circular inner opening formed therein. A plurality of inner and outer spacer elements support the respective inner and outer peripheries of the cards. The conductive patterns on the cards include a plurality of conductive pads arranged around the inner and outer peripheries of the cards. Circular metal-on-elastomer inner and outer connectors engage respective one of the inner and outer spacers, and the metal traces of the connectors make electrical contact with aligned conductive pads of adjacent cards. The unit includes a cover structure which envelops the circuit card configuration to form a sealed unit, and an electrically insulating coolant liquid is disposed in the sealed unit in direct contact with the circuit cards and electrical components mounted thereon to absorb heat generated by electrical power dissipation. The electronics unit is particularly well suited to use with a guided vehicle configuration, such as a missile, wherein a tubular center structural member extends forwardly from the aft missile body, and the electronics unit is assembled with the tubular member extending through the central opening in the electronics unit. The sensor platform of the missile receives the tubular support member through a central opening. The sensor platform is secured by a fastener exerting compression forces along the central missile axis, thereby also aligning the sensor platform with the aft missile body containing the missile propulsion system.

公开(公告)号：WO1987004857A1

公开(公告)日：1987-08-13

申请号：PCT/US1986002504

申请日：1986-11-24

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： HUGHES AIRCRAFT COMPANY ,  LIAO, Kuan, Y. ,  LEE, William, W., Y.

IPC: H01L21/82

CPC classification number: H01L21/266 ,  H01L21/0272 ,  H01L21/823892 ,  H01L27/0928 ,  Y10S438/951

Abstract: A technique for obtaining a self-aligned twin-well structure in a CMOS process. A double layer (35, 40) of two different photoresist materials is employed to obtain an overhang photoresist structure used for the p-well masking and ion implantation process. After the p-well implantation (50), pure aluminum is deposited over the wafer, forming a first layer (60) over the p-well region and a second layer (65) over the photoresist layers (35, 40). A metal lift-off procedure is performed to dissolve the photoresist layers (35, 40) and thereby remove the second layer (65) of metal. The first layer (60) of aluminum remaining on the wafer forms a conjugate of the p-well pattern and serves as the n-well mask for ion implantation (70). The invention provides a straightforward method for achieving the self-aligned twin-well structure in CMOS processes, and is adapted to high energy ion implantation for achieving retrograde impurity profiles.

公开(公告)号：WO1987004810A1

公开(公告)日：1987-08-13

申请号：PCT/US1986002515

申请日：1986-11-24

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： HUGHES AIRCRAFT COMPANY ,  BRAULT, Robert, G. ,  MILLER, Leroy, J.

IPC: G03F07/26

CPC classification number: G03F7/322

Abstract: haocess for forming an image with a positive resist, said process involves the steps of forming on a substrate a positive resist layer of poly(methacrylic anhydride). The resist layer is baked at a temperature of 170 DEG C to 260 DEG C and thereafter irradiated with a predetermined pattern of ionizing radiation. The irradiated area is then developed utilizing a developer solvent that is composed of solution of a base selected from the group consisting of alkali metal hydroxides, ammonium hydroxides (including quaternary ammonium hydroxides), alkali metal alkoxides and alkali metal carbonates; and a hydroxylic solvent selected from the group consisting of branched or straight chain alcohols having a C1 - C12 carbon content and water or mixtures thereof; and rinsing the resist with the same solvent selected above.

Abstract translation: 用正性抗蚀剂形成图像的方法，所述方法包括在基底上形成聚（甲基丙烯酸酐）的正性抗蚀剂层的步骤。 抗蚀剂层在170℃至260℃的温度下烘烤，然后用预定的电离辐射图案照射。 然后利用由碱金属氢氧化物，氢氧化铵（包括季铵氢氧化物），碱金属醇盐和碱金属碳酸盐组成的组中的碱的溶液组成的显影剂溶剂显影照射区域。 和选自具有C1-C12碳含量的支链或直链醇和水或其混合物的羟基溶剂; 并用与上述相同的溶剂冲洗抗蚀剂。

公开(公告)号：WO1987004518A1

公开(公告)日：1987-07-30

申请号：PCT/US1986002808

申请日：1986-12-19

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： HUGHES AIRCRAFT COMPANY ,  FINK, David

IPC: G01J03/12

CPC classification number: H01S3/005 ,  G01J3/12 ,  G01J3/14 ,  G01J3/18 ,  G01J2003/1282 ,  G01J2003/1286

Abstract: An optical receiver system operative to allow a set of fixed positioned detectors (70A-D) in the same Dewar to be optically directed to concurrently sense any subset of a known set of spectral lines (30A-D). The system also has a transmitter mode that allows a group of radiation sources having a subset of a possible set of spectral lines to be relatively optically overlapped at the transmitter aperture.