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. 发明授权

US4790641A Space telescope connected to a star tracker 失效
标题翻译：空间望远镜连接到星形跟踪器
公开(公告)号：US4790641A
公开(公告)日：1988-12-13
申请号：US937366
申请日：1986-12-03
申请人： Thorsteinn Halldorsson
发明人： Thorsteinn Halldorsson
IPC分类号： B60Q1/46 , G02B23/00 , G02B23/16 , G01B11/26 , G01J1/32
CPC分类号： G02B23/16 , G02B23/00
摘要： In order to be able to determine in a simple manner the angular deviationsetween the optical axes (OT, OS) of a telescope lens (2) and of a star tracker lens (8) which arise during the course of operation of a space telescope due to external influences, the entry (7a) of an orderly arranged light conductor bundle (7) is arranged in the focal plane (f.sub.t) of the space telescope lens (2) and the exit (7b) of the light conductor bundle (7) is lead into the focal plane (f.sub.k) of a collimator (9) arranged in the object-side opening of the star tracker lens (8). The angular deviation is determined by comparing the coordinates (y.sub.o, z.sub.o, y'.sub.o, z'.sub.o) of the images (S, S') of a reference star arising in the space telescope and in the star tracker. The collimator (9) may be mounted at the edge of the star tracker opening and a prism system (10, 11) may be provided for reflecting or imaging its beam path into the beam path of the star tracker.
摘要翻译：为了能够以简单的方式确定在太空望远镜的操作过程中出现的望远镜（2）和星形跟踪透镜（8）的光轴（OT，OS）之间的角度偏差由于外部影响，有序布置的光导体束（7）的入口（7a）被布置在空间望远镜（2）的焦平面（ft）和光导体束（7）的出口（7b））引导到布置在星形跟踪透镜（8）的物体侧开口中的准直器（9）的焦平面（fk）。通过比较在空间望远镜和星形跟踪器中出现的参考星的图像（S，S'）的坐标（哟，zo，y'o，z'o）来确定角度偏差。准直器（9）可以安装在星形跟踪器开口的边缘处，并且可以设置棱镜系统（10,11），用于将其光束路径反射或成像到星形跟踪器的光束路径中。

2. 发明授权

US4762294A Elevator control system especially for an aircraft 失效
标题翻译：电梯控制系统特别适用于飞机
公开(公告)号：US4762294A
公开(公告)日：1988-08-09
申请号：US94824
申请日：1987-09-09
申请人： Udo Carl
发明人： Udo Carl
IPC分类号： B64C13/42 , B64C13/50 , G05D1/00
CPC分类号： G05D1/0077 , B64C13/42 , B64C13/503 , Y02T50/44
摘要： An elevator control system especially for an aircraft such as an airplane,s equipped with an electrically controllable elevator flap drive system for the elevator flap on each side of the aircraft. Additionally, the system is equipped with a mechanically controlled auxiliary drive system which is responsive to a hand wheel operated by the pilot. A single hand wheel has mechanical connecting links to the elevator flaps on both sides of the aircraft. Monitoring features enable the pilot to test the auxiliary mechanical drive system without actually switching on that system. The auxiliary mechanically operated system is functional even if all other power systems failed, since a ram air turbine is provided for generating the hydraulic pressure for driving the auxiliary system.
摘要翻译：特别是用于诸如飞机的飞机的电梯控制系统配备有用于在飞行器的每一侧上的电梯翼片的电可控电梯折翼驱动系统。此外，该系统配备有机械控制的辅助驱动系统，其响应于由驾驶员操作的手轮。单手轮具有到飞机两侧的电梯襟翼的机械连接连接。监控功能使飞行员能够在没有实际打开该系统的情况下测试辅助机械驱动系统。即使所有其他电力系统故障，辅助机械操作系统也是有效的，因为提供了用于产生用于驱动辅助系统的液压的冲压空气涡轮机。

3. 发明授权

US4759515A Drive control for a vertical rudder of an aircraft 失效
标题翻译：驱动控制飞机的垂直方向舵
公开(公告)号：US4759515A
公开(公告)日：1988-07-26
申请号：US94830
申请日：1987-09-09
申请人： Udo Carl
发明人： Udo Carl
IPC分类号： B64C13/42 , B64C13/50 , G05D1/00 , B64C13/04
CPC分类号： B64C13/503 , B64C13/42 , G05D1/0077 , Y02T50/44
摘要： A vertical rudder control and drive system for an aircraft, such as an aiane, is equipped with electrically controllable vertical rudder drive systems on each side of the aircraft. Additionally, the control system is equipped with a mechanically controllable auxiliary drive system for the operation of the vertical rudder in response to foot pedals operated by the pilot when there should be a failure in the electrically controlled drive systems. A mechanical control signal transmitting link is provided between the foot pedals and the hydro-mechanical drive for the vertical rudder. Monitoring features enable the pilot to test the mechanical drive system without actually using that system in flight. Preflight tests may be performed.
摘要翻译：用于飞机（例如飞机）的垂直方向舵控制和驱动系统在飞行器的每一侧配备有电可控垂直方向舵驱动系统。此外，控制系统配备有机械可控的辅助驱动系统，用于在电控驱动系统中应该发生故障时响应于由飞行员操作的脚踏板来操作垂直方向舵。在脚踏板和用于垂直方向舵的水力机械驱动器之间提供机械控制信号传输链路。监控功能使飞行员无需在飞行中实际使用该系统即可测试机械驱动系统。可以执行预检测试。

4. 发明授权

US4717224A Laser scanning device for fastest possible deflection or sweep velocities 失效
标题翻译：激光扫描装置可以实现最快的偏转或扫描速度
公开(公告)号：US4717224A
公开(公告)日：1988-01-05
申请号：US923003
申请日：1986-10-24
申请人： Christian Diehl , Horst Kirsche
发明人： Christian Diehl , Horst Kirsche
IPC分类号： G02B26/08 , G02B26/10
CPC分类号： G02B26/10 , G02B26/0816 , G02B26/0875
摘要： A laser scanning device for fastest possible deflection or sweep velocitiess constructed for use in a laser guide or pilot beam system. The scanning device has two symmetric scanning cylinders which each are caused to rotate about their respective rotational axis or axis of symmetry by a gas stream so as to achieve a rapid beam deflection. Due to the low structural weight and small dimensions of the scanning cylinders with their respective scanning mirrors passing through the scanning cylinder at a slant, angular velocities up to the breaking limit of the material can be achieved.
摘要翻译：用于最快可能的偏转或扫描速度的激光扫描装置被构造用于激光导向器或导向束系统中。扫描装置具有两个对称的扫描气缸，它们各自通过气流绕其各自的旋转轴线或对称轴线旋转，以实现快速的光束偏转。由于扫描气缸的低结构重量和小尺寸，其各自的扫描反射镜以倾斜方式通过扫描气缸，所以可以实现高达材料断裂极限的角速度。

5. 发明授权

US4699468A Liquid crystal modulator for the transmission of information, including speech, in the visible and infrared range 失效
标题翻译：用于传输信息的液晶调制器，包括语音在可见光和红外范围内
公开(公告)号：US4699468A
公开(公告)日：1987-10-13
申请号：US811668
申请日：1985-12-20
申请人： Anton Harasim , Klaus Dietrich
发明人： Anton Harasim , Klaus Dietrich
IPC分类号： H04B10/00 , G02F1/13 , G02F1/133 , G02F1/137 , H04B10/04 , H04B10/06 , H04B10/14 , H04B10/142 , H04B10/152 , H04B10/26 , H04B10/28 , G02F1/00 , H04B9/00
CPC分类号： G02F1/133382 , G02F1/1313 , G02F1/13306 , G02F1/13718
摘要： A liquid crystal light modulator is constructed for the transmission of sch signals modulated onto a light carrier passing through gaseous, liquid, and solid media such as air, water, or glass. A large surface area modulation of the light is accomplished in the visible and infrared range over narrow, however adjustable, wave length ranges or widths. Several circuit arrangements for such modulators are disclosed and their function described.
摘要翻译：液晶光调制器被构造用于传输调制到通过气体，液体和固体介质如空气，水或玻璃的轻载体上的语音信号。光的大的表面积调制在可见光和红外范围内通过窄的可调节的波长范围或宽度实现。公开了这种调制器的几种电路装置，并描述了它们的功能。

6. 发明授权

US4676455A Guide beam and tracking system 失效
标题翻译：导轨和跟踪系统
公开(公告)号：US4676455A
公开(公告)日：1987-06-30
申请号：US798759
申请日：1985-11-15
申请人： Christian Diehl , Werner Schnaebele , Karl-Heinz Allgaier , Horst Kirsche
发明人： Christian Diehl , Werner Schnaebele , Karl-Heinz Allgaier , Horst Kirsche
IPC分类号： F41G7/26
CPC分类号： F41G7/263
摘要： A guide beam and tracking system for acquiring a target and for guiding a ying body into the target operates in accordance with the beam rider principle. A tracking laser beam is imaged into the path of a guide laser beam so that both beams travel through the same optical devices and through the same deflection device. All components of the system, except the receiver are controlled by a central processing unit which may control one, two, or three laser generators to produce, in timed sequence, laser beams for different purposes. A highly precise target acquisition and a precise target tracking is achieved.
摘要翻译：用于获取目标并用于将飞行体引导到目标中的引导光束和跟踪系统根据光束骑手原理进行操作。跟踪激光束被成像到引导激光束的路径中，使得两个光束穿过相同的光学器件并穿过相同的偏转装置。除了接收器之外，系统的所有组件由中央处理单元控制，中央处理单元可以控制一个，两个或三个激光发生器以定时顺序产生用于不同目的的激光束。实现了高精度的目标采集和精确的目标跟踪。

7. 发明授权

US4674717A Aircarft wing 失效
标题翻译： Aircarft翼
公开(公告)号：US4674717A
公开(公告)日：1987-06-23
申请号：US888082
申请日：1986-07-16
申请人： Gerhard Loebert
发明人： Gerhard Loebert
IPC分类号： B64C21/04
CPC分类号： B64C21/04 , B64C2230/04 , Y02T50/166
摘要： An aircraft wing is equipped with at least one low compression fan which blows into a longitudinal flow channel extending lengthwise or spanwise of the wing and leading into air blowing nozzle arranged along the upper wing surface where the reduced pressure is largest for directly mixing the propulsion air jet or jets with the boundary layer air flowing along and adjacent to the upper wing surface. Both, the flow channel and the air blowing nozzles extend substantially along the entire length of the wing for increasing the resulting propulsion force and/or the resulting lift due to the mixing of the propulsion air jet with the boundary layer air directly in the boundary layer.
摘要翻译：飞机机翼配备有至少一个低压缩风扇，其吹入沿着翼的纵向或翼展方向延伸的纵向流动通道，并且引导沿着上翼面排列的空气吹送喷嘴，其中减压最大，用于直接混合推进空气喷射或射流，边界层空气沿着并靠近上翼面流动。两者，流动通道和吹气喷嘴基本上沿翼的整个长度延伸，用于增加所得到的推进力和/或由于推进空气射流与边界层空气直接在边界层中混合而产生的升力。

8. 发明授权

US4658659A Gyroscope 失效
标题翻译：陀螺仪
公开(公告)号：US4658659A
公开(公告)日：1987-04-21
申请号：US682653
申请日：1984-12-17
申请人： Ernst Gruber
发明人： Ernst Gruber
IPC分类号： G01C19/18 , G01C19/22
CPC分类号： G01C19/18 , Y10T74/125 , Y10T74/1257 , Y10T74/1279 , Y10T74/1293
摘要： A gyroscope with a rotor which rotates about a nonrotating axis is simple its structure and has but a few movable parts because the rotor axis (2) is divided into two sections by an articulation piece (8), whereby one section (2a) is connected with the housing (11) and the other section (2b) is tiltable about the articulation piece and carries the bearing axis (13) for the rotor (5). The articulation piece (8) is arranged approximately in the center of gravity of the rotor (5). The gyroscope (10) may be constructed to have one or two degrees of freedom and it may be equipped with the measuring device necessary for its operation as a displacement gyroscope or as a rate gyroscope. For a measuring operation in which the rotor (5) is driven only for the uptake, a compensating circuit is provided with an amplifier (23), a servo-control (24), and a multiplier (25) for producing a measured signal proporational to the measured quantity independently of the r.p.m. of the rotor (5). The gyroscope (10) may be driven by a spiral spring (16), electrically or pneumatically. Besides an electrical captivation, a rigid or soft captivation of the rotor axis (2) is also possible.
摘要翻译：具有绕非旋转轴线旋转的转子的陀螺仪的结构简单，并且具有可移动部件，因为转子轴线（2）由铰接片（8）分成两部分，因此一个部分（2a）是与所述壳体（11）连接，并且所述另一部分（2b）能够围绕所述关节运动件倾斜并承载所述转子（5）的轴承轴线（13）。铰接片（8）大致设置在转子（5）的重心上。陀螺仪（10）可以构造成具有一个或两个自由度，并且其可以配备有作为位移陀螺仪或速率陀螺仪作为其操作所需的测量装置。对于其中转子（5）仅被驱动而被驱动的测量操作，补偿电路设置有放大器（23），伺服控制器（24）和用于产生测量信号的乘法器（25）与转速无关的转子（5）。陀螺仪（10）可以由螺旋弹簧（16）电动地或气动地驱动。除了电气捕捉，转子轴线（2）的刚性或柔软的捕捉也是可能的。

9. 发明授权

US4658265A Foldable and unfoldable antenna reflector 失效
标题翻译：可折叠和可折叠的天线反射器
公开(公告)号：US4658265A
公开(公告)日：1987-04-14
申请号：US739826
申请日：1985-05-31
申请人： Horst Heinze , Henning Herbig
发明人： Horst Heinze , Henning Herbig
IPC分类号： H01Q1/08 , H01Q15/16 , H01Q15/20
CPC分类号： H01Q1/08 , H01Q15/161 , Y10S343/02
摘要： An antenna reflector, for example for a satellite or spacecraft, has ribs urnalled to a central body by a first journal axis. Each rib has a radially inner section tiltable and lockable relative to the central body, and a radially outer section journalled to the inner rib section at a second journal axis for tilting and locking the outer rib section relative to the inner rib section. A motor driven cable drive and respective pulleys are so arranged that the inner rib sections are first partially unfolded before the outer rib sections begin to be unfolded. The outer rib sections then are moved faster than the inner rib sections so that both rib sections reach the fully unfolded state substantially simultaneously. The folding takes place in the reverse order, whereby the outer rib sections are folded first. The reflector netting is stretched out only after the ribs have been locked into the unfolded state.
摘要翻译：天线反射器，例如用于卫星或航天器，具有通过第一轴颈轴线连接到中心体的肋。每个肋具有可相对于中心体可倾斜和锁定的径向内部，并且径向外部在第二轴颈轴颈处轴颈连接到内肋部，用于相对于内肋部倾斜和锁定外肋部。电动机驱动的电缆驱动器和相应的滑轮被布置成使得在外部肋部段开始展开之前，内部肋部分首先部分展开。然后外肋部分比内肋部分移动得更快，使得两个肋部分基本上同时达到完全展开状态。折叠以相反的顺序进行，由此外部肋部首先被折叠。只有在肋已经锁定到展开状态之后，反射器网才被拉伸。

10. 发明授权

US4643374A Steering apparatus for a flying body 失效
标题翻译：用于飞行体的转向装置
公开(公告)号：US4643374A
公开(公告)日：1987-02-17
申请号：US739825
申请日：1985-05-31
申请人： Oskar Friederich
发明人： Oskar Friederich
IPC分类号： B64C15/02 , F02K1/00
CPC分类号： F02K1/002 , B64C15/02
摘要： The steering of a jet propelled flying body is improved by positioning jeteflector flaps into the propulsion jet for deflecting the propulsion jet. The deflector flaps can steer the flying body automatically in response to a flight control unit either alone or as a support steering system for the control surfaces of the flying body. The jet deflector flaps are arranged in the jet nozzle in a cross or star configuration and preferably near the periphery of the jet nozzle.
摘要翻译：通过将喷射偏转片定位到推进射流中以偏转推进射流来改善喷射推进飞行体的转向。偏转翼片可以单独或作为用于飞行体的控制表面的支撑转向系统的飞行控制单元自动地引导飞行体。喷射偏转器翼片以十字或星形配置在喷嘴中，优选地在喷嘴的周边附近。

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