公开(公告)号：WO1986005284A1

公开(公告)日：1986-09-12

申请号：PCT/US1986000425

申请日：1986-02-28

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： HUGHES AIRCRAFT COMPANY ,  BRAULT, Robert, G.

IPC: G03F07/10

CPC classification number: G03F7/0757 ,  G03F7/094

Abstract: A method for providing a high temperature imaging resist layer for use in a multilayer resist system. A relatively thick planarizing resist layer is coated onto a suitable substrate to provide a planarizing resist layer having a planar surface. A relatively thin layer of a solvent soluble polysilsesquioxane polymer resist is applied to the planar surface to form an imaging resist which remains solvent soluble at temperatures up to 250 C. The hydroxyl or alkoxy content of the polysilsesquioxane must be 0.05 weight percent or less in order to prevent cross linking of the polysilsesquioxane. The polysilsesquioxane polymer resist is prepared by hydrolizing and polymerizing trichlorosilanes having the formula RSiCl3 where R is methyl, phenyl, vinyl, n-butyl, t-butyl, chlorophenyl, or chloromethylphenyl. The hydroxyl content of the polysilsesquioxane is reduced to 0.05 weight percent by capping the polymer with monoreactive silanes. The polysiloxane imaging resist is designed for use in high temperature electron beam and ion beam lithography.

Abstract translation: 一种用于提供用于多层抗蚀剂体系的高温成像抗蚀剂层的方法。 将相对厚的平坦化抗蚀剂层涂覆到合适的基底上以提供具有平坦表面的平坦化抗蚀剂层。 将相对薄的溶剂可溶性聚倍半硅氧烷聚合物抗蚀剂层施加到平面表面以形成在高至250℃的温度下保持溶剂可溶的成像抗蚀剂。 为了防止聚倍半硅氧烷的交联，聚倍半硅氧烷的羟基或烷氧基含量必须为0.05重量％以下。 聚倍半硅氧烷聚合物抗蚀剂通过水解和聚合具有式RSiCl 3的三氯硅烷来制备，其中R是甲基，苯基，乙烯基，正丁基，叔丁基，氯苯基或氯甲基苯基。 通过用单反应硅烷封端聚合物，聚倍半硅氧烷的羟基含量降低至0.05重量％。 聚硅氧烷成像抗蚀剂设计用于高温电子束和离子束光刻。

公开(公告)号：WO1986005158A1

公开(公告)日：1986-09-12

申请号：PCT/US1986000379

申请日：1986-02-24

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： HUGHES AIRCRAFT COMPANY ,  ROSEN, Harold, A. ,  WITTMANN, Alois

IPC: B64G01/14

CPC classification number: B64G1/14

Abstract: An apparatus for transporting a spacecraft (28) and fluid propellant from the earth to a substantially low gravity environment above the earth with substantially reduced loading of the spacecraft due to forces upon the fluid propellant during the transport, the apparatus including a vehicle for carrying the spacecraft and the fluid propellant from the earth to a substantially low gravity environment above the earth; a plurality of external tanks (20, 22, 24, 26) disposed within the vehicle, external to the spacecraft, for containing the fluid propellant as the vehicle carries the spacecraft and the fluid propellant from the earth to the substantially low gravity environment above the earth; a plurality of spacecraft tanks (30, 32, 34, 36) disposed within the spacecraft for receiving the fluid propellant and for containing the fluid propellant; and means for transferring the fluid propellant from the external tanks to the spacecraft tanks in the substantially low gravity environment above the earth.

公开(公告)号：WO1986004730A1

公开(公告)日：1986-08-14

申请号：PCT/US1985002394

申请日：1985-12-05

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： HUGHES AIRCRAFT COMPANY ,  REED, Elmer, E. ,  MANOLY, Arthur, E.

IPC: H01B11/18

CPC classification number: H01B11/1834 ,  H01R24/545 ,  H01R2103/00

Abstract: A high-power coaxial cable (10) comprising an inner conductor (14), an outer conductor (16) coaxially disposed about and spaced from the inner conductor (14), and insulating fittings (20, 52) disposed between the inner and outer conductors (14, 16) near opposite ends of the cable (10) to maintain a desired spacing between the inner and outer conductors (14, 16). The insulating fitting (26) at one end of the cable has a plurality of longitudinal holes (30) therethrough to reduce the dielectric constant and the impedance of the fitting (20). The fitting (20) is formed in two like sections (22) joined at right angles to one another along a substantially 45o interface (28), thereby defining a short 90o turn for the inner conductor (14) near the end of the cable (10). The fitting sections (22) are retained in position by a surrounding mounting block (34), the opposite ends of which respectively receive a conductive sleeve (38) and an end (42) of the outer coaxial conductor (16) in press-fit relationship.

公开(公告)号：WO1986003844A1

公开(公告)日：1986-07-03

申请号：PCT/US1985002309

申请日：1985-11-25

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： HUGHES AIRCRAFT COMPANY ,  WELNER, Jerome, M.

IPC: G01S03/78

CPC classification number: G01S3/781 ,  G01J9/00 ,  G01S3/784

Abstract: Spectral analyzer and direction indicator systems (10, 20, 30, 40, 50) include optical elements (11, 17, 27b, 33b, 35b, 39b) for providing optical information which depend on incidence direction and spectral content, and further includes optical elements (23, 27a, 33a, 35a, 39a) for providing non-diffracted optical information which depend on incidence direction. The respective optical information as detected by detector arrays (15, 21, 25, 31, 37) are utilized together to provide information for specifically identifying spectral content and incidence direction of collimated or nearly collimated radiation.

公开(公告)号：WO1986001794A1

公开(公告)日：1986-03-27

申请号：PCT/US1985001521

申请日：1985-08-12

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： HUGHES AIRCRAFT COMPANY ,  BLAIR, Richard, G. ,  PIKULSKI, Joseph, L.

IPC: C03C13/04

CPC classification number: C03C13/045 ,  C03B37/01807 ,  C03B2201/28 ,  C03B2201/30 ,  G02B6/02 ,  G02B6/443

Abstract: An optical fiber waveguide resistant to ionizing radiation having a glass core of predetermined refractive index surrounded by glass cladding having a lower predetermined refractive index. The glass core and glass cladding are each composed of high purity silica incorporating gallium as a constituent. The gallium is present in the form of Ga2O3 in a concentration of about 0.01 to .15 mole percent ratio to the silica. The glass of the optical waveguide can further include phosphorus in the form of P2O5 as an additional constituent in the amount of from about 5 to 16 mole percent ratio to the total amount of all constituents. The waveguide of the invention is preferably manufactured by using GaCl3 in combination with an internal vapor phase process to produce a silica soot (16) containing Ga2O3 on the interior surface of a high purity silica tube (10). The soot is then consolidated and the tube collapsed to form a substantially voidless solid rod preform of high purity SiO2 containing Ga2O3. The process of manufacture is controlled so as to disposed Ga2O3 within the preform in a concentration of about .01 to .15 mole percent ratio to the total constituents of the silica preform. The process can further include the deposition of P2O5 within the preform.

公开(公告)号：WO1986001649A1

公开(公告)日：1986-03-13

申请号：PCT/US1985001465

申请日：1985-08-05

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： HUGHES AIRCRAFT COMPANY ,  SHELDON, John, C. ,  HISAYASU, Dennis, M.

IPC: H01S03/139

CPC classification number: H01S3/086 ,  G02B7/1827 ,  H01S3/1398

Abstract: A device (10), for allowing axial displacement of an optical element (12) within a laser cavity (14), so as to control the optical path length in the cavity, includes a generally cylindrical container (16) arranged to be connected to an end of the laser cavity where the optical element is located, and a piezoelectric stack (38) mounted in the container so that the length of the stack in the axial direction can be varied by an amount corresponding to the desired optical element movement in response to an electric field applied to the stack. One end of the cylindrical container comprises a belle-ville shaped diaphragm (26) to which is mounted the optical element within the laser cavity. A very stiff threaded cap (20) forming the end of the cylindrical container preloads the stack and diaphragm by a prescribed torque to allow the device to perform satisfactorily when subjected to extreme environmental conditions (e.g., above 5 KHz). The stack is mounted within the cylindrical container by ball and cone joints which permit only axial forces to be applied to or from the stack, thus insuring reliable control over the degree of desired optical element movement in the cavity. The stack and electrical connections are outside of the laser cavity and do not contribute to outgassing contamination.

公开(公告)号：WO1986001347A1

公开(公告)日：1986-02-27

申请号：PCT/US1985001409

申请日：1985-07-24

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： HUGHES AIRCRAFT COMPANY ,  DEWHIRST, Donald, R. ,  DUVALL, Robert, L., III

IPC: H01S03/11

CPC classification number: H01S3/125

Abstract: A CO2 TEA laser utilizing an intra-cavity rotating prism Q-switch (70) for angularly switching the resonator gain by periodically causing the resonator mirrors (54, 56) to be in alignment. An opto-electronic timing device (79), which includes a graded index glass rod (76) rotating with the Q-switch prism, generates a pulse to initiate the laser discharge at the proper time before the mirrors are aligned so that the laser output pulse occurs when peak gain is achieved. The Q-switch speed of rotation is chosen such that the time interval in which the mirrors are aligned is not long enough to support the tail portion of the pulse typical of the gain switched CO2 TEA laser.

公开(公告)号：WO1986000863A1

公开(公告)日：1986-02-13

申请号：PCT/US1985001378

申请日：1985-07-19

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： HUGHES AIRCRAFT COMPANY ,  SMAY, John, W. ,  ROSEN, Harold, A.

IPC: B64G01/38

CPC classification number: B64G1/281 ,  B64G1/24 ,  B64G1/38 ,  G05D1/0883

Abstract: A satellite communications system (100) incorporating a novel nutation control subsystem. A geosynchronous spin-stabilized satellite includes an antenna (113) for receiving rf signals from a ground station (101). An rf beacon pointing error sensor (115) associated with the antenna provides an error signal with a cyclic component at nutation frequency. A bandpass filter (117) is used to isolate this cyclic component. The cyclic component, which may be further phase shifted, activates a despin motor (119) of the satellite to affect spacecraft dynamics (at 121) to damp nutation.

Abstract translation: 一种包含新颖的章动控制子系统的卫星通信系统（100）。 地球同步自旋稳定卫星包括用于从地面站（101）接收rf信号的天线（113）。 与天线相关联的射频信标指向误差传感器（115）在章动频率处提供具有循环分量的误差信号。 带通滤波器（117）用于隔离该循环分量。 可以进一步相移的循环分量激活卫星的解索引电动机（119）以影响航天器的动力学（121）以减少章动。

公开(公告)号：WO1986000763A1

公开(公告)日：1986-01-30

申请号：PCT/US1985000608

申请日：1985-04-08

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： HUGHES AIRCRAFT COMPANY ,  HALMOS, Maurice, J. ,  HENDERSON, David, M.

IPC: H01S03/137

CPC classification number: H01S3/1398 ,  H01S3/107

Abstract: A chirp laser system includes an intracavity electro-optical crystal which is modulated at a relatively high frequency, for example 250 kilohertz, to sweep the frequency of the transmitter laser above and below its nominal center frequency. One of the mirrors associated with the laser transmitter is adjustable to vary the length of the laser cavity and to thereby shift the frequency of the transmitter laser. When the frequency of the transmitter laser is shifted, the output amplitude of the laser changes to some extent. With the center frequency of the laser at a maximum gain point, the amplitude of the output signals during the positive and negative frequency excursions of the transmitter laser will be substantially symmetrical. However, if thermal or other effects cause the frequency of the laser to shift away from the maximum gain point, the output during positive and negative excursions will be asymmetrical, for example, with the gain dropping off during an upward frequency excursion, and perhaps increasing or not dropping off nearly as much during a low frequency excursion. A small part of the output from the transmitter laser is sampled, and the amplitude during positive and negative frequency shift excursions is compared, using a square wave derived from the chirp modulating driver. Where the detected signals for the positive and negative frequency excursions are substantially equal, no change in the position of the mirror is accomplished; however, when the excursions result in a difference in the amplitude of the detected signals, the position of the piezoelectrically adjustable mirror is shifted to restore the nominal center frequency of the laser to its maximum amplitude point on the gain curve.

公开(公告)号：WO1986000653A1

公开(公告)日：1986-01-30

申请号：PCT/US1985001301

申请日：1985-07-08

Applicant: HUGHES AIRCRAFT COMPANY

Inventor： HUGHES AIRCRAFT COMPANY ,  PASTOR, Antonio, C.

IPC: C30B15/24

CPC classification number: C30B15/24 ,  Y10S117/90 ,  Y10T117/102 ,  Y10T117/1036

Abstract: An apparatus and method pulling a shaped crystalline fiber of a given crystal-forming material from a liquid reservoir (22) of the material. The apparatus includes a vessel (12) in which the liquid material is maintained as a liquid reservoir (22) at a temperature above the melting point or crystal-forming temperature of the material. A die (26) is provided having an inner-tubular surface (32) which includes a crystal shaping portion which is tapered. The liquid flows from the reservoir (22) through the die (26) so that the liquid flows from the narrow end (28) of the shaping portion to the wide end of the shaping portion (30). The temperature of the liquid crystal growth material is selectively lowered at the top end (30) of the die (26) to form crystalline material which is continually pulled from the crystal-liquid interface. The apparatus is operated to maintain the crystal-liquid interface within the crystal shaping portion of the die (26) to provide accurate shaping of the crystal by the tubular surface (32) and to maintain accurate alignment of the crystal fiber with the die (26).