Patents Assigned to Deutsche Aerospace AG
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Patent number: 5509747Abstract: An articulation arrangement connects individual elements of a folding structure which consists of two or more individual elements and is configured to be unfolded and locked in an unfolded position and swivellably disposed on a central body. The arrangement comprises two hinge parts each rigidly fastened at one of two adjacent individual elements and swivellable about a common hinge axle, a slotted disk provided with a slot and forming part of one of the two hinge parts, a lever swivellably disposed on the other of the two hinge parts and provided with a pin. The pin is configured and arranged such that, before the unfolded position is completely reached, the pin slides on an edge of the slotted disk and, in the completely unfolded position at which locking occurs, the pin is engaged in the slot.Type: GrantFiled: October 22, 1993Date of Patent: April 23, 1996Assignee: Deutsche Aerospace AGInventor: Helmut Kiendl
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Patent number: 5505053Abstract: Cryosystem for cryogenic liquids which contain small amounts of foreign fluids with higher melting and boiling points, wherein the cryosystem comprises at least one tank, pipelines and assembly units and is used under defined gravitation conditions. The pipelines slope, at least in some areas, toward the tank, and areas of the pipelines and assembly units, from which the cryogenic liquid and the foreign fluids cannot flow back into the tank under the action of gravity, are provided with drain openings and drain lines, which open into the tank or into at least one additional collection tank.Type: GrantFiled: December 8, 1994Date of Patent: April 9, 1996Assignee: Deutsche Aerospace AGInventors: Peter Luger, Franz Grafwallner, Helmuth Peller, Martin Muller, Valentin V. Malyshev, Alexsander S. Shengardt
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Patent number: 5497157Abstract: Monitoring an area with the aid of a frequency-modulated continuous-wave radar includes emitting a frequency-modulated continuous-wave transmitting signal with at least one transmitting antenna having a directional pattern whose main azimuthal direction depends on the frequency of the transmitting signal. Related to a predeterminable direction, an azimuthal region is selected, and in the selected region, an azimuthal swivelling of the directional pattern of the transmitting antenna is carried out by changing the frequency of the transmitting signal. Also in the selected region, each azimuthal value is assigned a frequency value of the transmitting signal. The selected region is divided into a predeterminable number of azimuthal increments adjoining one another, and in each of the increments, a monotonous change of the frequency of the transmitting signal occurs.Type: GrantFiled: August 22, 1994Date of Patent: March 5, 1996Assignee: Deutsche Aerospace AGInventors: Wilhelm Gruener, Tiang-Gwan Liem
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Patent number: 5488328Abstract: A constant-current source that contains two substantial identical field effect transistors as well as a simple resistance network. The actual saturation current of one of the field effect transistors is measured and converted by the resistance network into a control voltage for the other field effect transistor which produces the desired constant current. With such a circuit, production tolerances, especially tolerances for field effect transistor, as well as operation-dependent temperature variations can be compensated for within a wide range.Type: GrantFiled: October 20, 1994Date of Patent: January 30, 1996Assignee: Deutsche Aerospace AGInventors: Michael Ludwig, Rolf Reber, Heinz-Peter Feldle
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Patent number: 5485383Abstract: This invention relates to an attitude and orbit control system in which a standard interface is provided between an attitude and orbit control electronics unit and all peripheral systems. For this purpose microprocessors with expandable processing capability are used, and processing power is decentralized, with data processing being performed on the periphery. All functions such as automatic controllers, modulators, etc. are implemented with expandable microprocessors.Type: GrantFiled: March 12, 1993Date of Patent: January 16, 1996Assignee: Deutsche Aerospace AGInventor: Wolfgang Schreiber
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Patent number: 5473633Abstract: A digital modulation process and apparatus for converting an input signal comprising a time variable series of sampling values, each of which sampling values remains constant within a fixed sampling period, into output signals representing a sequence of positive and/or negative pulses having a constant amplitude and a variable pulse width and frequency. The input signal and modulator parameters are supplied to a data processor. In order to reduce computing expenditures and at the same time achieve an increase in precision, by means of the computing system, the switch-on and switch-off points in time t.sub.se, t.sub.sa of the pulses as well as their operational signs are computed in one operation directly for each sampling period .DELTA.t.sub.k.Type: GrantFiled: April 2, 1993Date of Patent: December 5, 1995Assignee: Deutsche Aerospace AGInventors: Horst-Dieter Fischer, Helmut Bittner
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Patent number: 5465924Abstract: An inertial stabilizing system for a platform supported on a carrier, which is moved in a dynamically high-frequency and low-frequency manner, in which a base is arranged between the carrier and the platform which is mounted on the carrier so that it is vibration-insulated in a high-frequency manner via a damping device. On this base the platform is disposed in an adjustably movable manner by at least one control circuit which has an inertial sensor sensing the actual movements of the platform, a controller which forms an adjusting signal from the actual-desired value difference of the platform, and an adjusting device which is controlled by the adjusting signal and acts between the base and the platform. The control circuit has a further sensor which senses the low-frequency motion components of the damping device between the carrier and the base, and a control circuit element connected behind the sensor.Type: GrantFiled: November 15, 1993Date of Patent: November 14, 1995Assignee: Deutsche Aerospace AGInventor: Heinrich Schneider
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Patent number: 5461384Abstract: The invention relates to a method for monitoring an area by a plurality of economical radar systems. These systems operate with CW modulation at low transmission power and can therefore be fully realized in semiconductor technology. The area is divided into base cells that are directly contiguous without gaps.Type: GrantFiled: January 5, 1994Date of Patent: October 24, 1995Assignee: Deutsche Aerospace AGInventors: Ing. W. Sieprath, David Robinson
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Patent number: 5457756Abstract: A process for the manufacturing a fiber optic depolarizer as well as an arrangement of that type uses two optical fiber sections which obtain the polarization planes of the light and which are connected with one another in such a manner that the principal axes of the optical fiber sections enclose an angle of 45.degree.. An optical fiber piece which obtains no polarization is inserted between the optical fiber sections whose principal axes enclose an angle of 45.degree., in that the optical fiber sections and the optical fiber piece are fixed to one another at their connecting areas. The principal axis orientations of the optical fiber sections are adjusted in such a manner that, in the case of a firm positioning of one of the two connecting areas by the torsional twisting of the other connecting area, an angle of 45.degree. is adjusted.Type: GrantFiled: July 12, 1993Date of Patent: October 10, 1995Assignee: Deutsche Aerospace AGInventors: Engelbert Hartl, Reinhard Muller, Hans Poisel
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Patent number: 5446464Abstract: A high frequency transceiver includes a transmit/receive switch which is coupled to a transmission path and to a receive path of the module. The transmit/receive switch includes a 3 dB directional coupler having first, second and third ports, and a decoupled port which is connected to the receive path. Two HF power amplifiers are connected to the first and second ports of the transmit/receive switch to form a balanced amplifier in the transmission path. An HF switch is connected to the first and second ports of the transmit receive switch for short-circuiting the HF output of the balanced amplifier. A switching device is connected to the HF switch and to the receive path for selectively switching the transmission path and the receive path to be operational.Type: GrantFiled: October 8, 1993Date of Patent: August 29, 1995Assignee: Deutsche Aerospace AGInventor: Heinz-Peter Feldle
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Patent number: 5442951Abstract: An arrangement for examining pipes for interior leaks, comprises two mirror-inverted sections, each having at least one clamping device and at least one pair of runners. A pneumatic pressure source is provided for inspection of the pipes, as well as a sealing arrangement and a control arrangement. Each section has an outer cylinder, at least one intermediate cylinder concentrically disposed in the outer cylinder and displaceable with respect thereto, and at least one inner cylinder concentrically disposed in the center cylinder and displaceable with respect thereto. The two inner cylinders of the two sections are connected with the pneumatic pressure source so that pneumatic energy for the internal-pressure test is also for used to move the two sections.Type: GrantFiled: May 6, 1994Date of Patent: August 22, 1995Assignee: Deutsche Aerospace AGInventors: Erwin Gollner, Horst Hutter
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Patent number: 5436847Abstract: The invention relates to a method for determining a periodic pattern in an amplitude spectrum, for example, in a Doppler spectrum of a radar echo. A residual spectrum is formed using Fuzzy Set Theory, and the periodic pattern is determined for each residual spectrum by histogramming the original spectrum. The method can be used for identifying aircraft, for example helicopters, that have periodically-moving components, e.g., rotors, that generate a periodic pattern in a Doppler spectrum.Type: GrantFiled: May 26, 1994Date of Patent: July 25, 1995Assignee: Deutsche Aerospace AGInventors: Wolfgang Schroer, Christoph Bauer, Johannes Schmid
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Patent number: 5433123Abstract: A measuring and transmitting system of measuring signals for the deflection of an interior frame angle of a position gyro cardanically mounted in an exterior housing, in which the position gyro has an interior frame and an exterior frame, is provided with a gyro rotor and a permanent magnet in the gyro rotor. The permanent magnet forms a signal generator of the interior frame, and has a magnetic field generator center. A plurality of measuring coils form a signal receiver formed on the exterior frame, the measuring coils having measuring axes aligned in parallel to one another and eccentrically with respect to the magnetic field generator center. An analysis unit is connected behind the measuring coils and performs a measuring signal analysis.Type: GrantFiled: January 18, 1994Date of Patent: July 18, 1995Assignee: Deutsche Aerospace AGInventors: Fritz Hofmann, Ernst Gruber
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Patent number: 5433402Abstract: This device is used for controlling the attitude of a spacecraft to be rotated about a body's axis of rotation. Actuators generate torques about the axis of rotation and two lateral axes. Angular velocity signals .omega..sub.X, .omega..sub.Y with respect to the lateral axes are in each case fed to first and second signal paths. The latter contain an integrator. Modulators, which each comprise a variable dead zone, supply control signals for the actuators. In order to limit the nutation amplitude to a constant value in a reliable manner, multiplication elements are provided in the first and second signal paths. The lateral-axis angular velocity signals .omega..sub.X, .omega..sub.Y or the angular position signals .PHI., .theta. are acted upon by factors which are proportional to the rotation axis angular velocity signal .omega..sub.Z or its square in the multiplication elements. Furthermore, the thresholds of the dead zones of the modulators are varied proportionally to .omega..sub.Z.sup.2.Type: GrantFiled: June 23, 1994Date of Patent: July 18, 1995Assignee: Deutsche Aerospace AGInventors: Michael Surauer, Helmut Bittner
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Patent number: 5432138Abstract: A gamma lithium aluminate matrix layer for a molten carbonate fuel cell is manufactured using a slurry whose liquid phase is formed by an aqueous polyvinyl alcohol solution.Type: GrantFiled: November 15, 1993Date of Patent: July 11, 1995Assignee: Deutsche Aerospace AGInventor: Hans Hofmann
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Patent number: 5431440Abstract: A vehicle's restraint system for passengers such as airbags, belt tighteners or similar devices to protect the passengers in case of a crash against injury including an electronic sensor circuit for the release of the restraint system, only upon the occurrence of predetermined conditions. An energy supply is provided for supply of the electronic sensor circuit with a proper and set voltage value to be monitored at least from time to time and compared with a reference voltage wherein at least an emergency voltage supply is to be held in a steady state such as at the set voltage value to provide power to electrically ignite a pyrotechnic or propellant charge if triggered by said electronic sensor circuit, in the case that one or more of said predetermined conditions evaluated in said electronic sensor circuit by comparing it with chosen threshold values are fulfilled, indicating that a crash event is detected by an acceleration responsive signal generator in said electronic sensor circuit.Type: GrantFiled: May 21, 1993Date of Patent: July 11, 1995Assignee: Deutsche Aerospace AGInventors: Hans Spies, Horst Daxer
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Patent number: 5430818Abstract: The protective cladding for a mono-mode directional coupler made of at least two incoming and outgoing fiber optic waveguides which are fused to one another along a coupling segment comprises at least two open cladding parts which can be connected to form a tube-shaped cladding. The material of the cladding parts has the same coefficient of expansion as the waveguide material of the mono-mode directional coupler. The protective cladding, being mechanically tightly connected with the incoming and outgoing fiber optic waveguides while leaving open the coupling segment of the mono-mode directional coupler, is closed off in a gas-tight manner such that in the case of temperature changes, there are no mechanical tensions in the coupling segment.Type: GrantFiled: January 11, 1994Date of Patent: July 4, 1995Assignee: Deutsche Aerospace AGInventors: Engelbert Hartl, Gert Trommer, Hans Poisel
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Patent number: 5430544Abstract: In the case of a fiber optic gyro having a 4.times.4-coupler, the two arms of the coupler which are not connected with the fiber coil are each connected with a monitoring detector. From the output signals of these monitoring detectors, in the case of a desired wavelength, a reference or desired quotient is formed. During the operation of the fiber optic gyro, an actual quotient is in each case formed from these output signals and is compared with the stored desired quotient. The wavelength of a semiconductor laser is controlled by controlling the operating current and/or the temperature of the light source (L) such that the two quotients are identical. The measuring signals will then be error free.Type: GrantFiled: January 21, 1994Date of Patent: July 4, 1995Assignee: Deutsche Aerospace AGInventors: Hans Poisel, Gert Trommer
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Patent number: 5418534Abstract: The present invention relates to a method and apparatus for producing compensated baseband signal components for a moving radar antenna. A fixed frequency oscillator is used and a baseband signal is complex multiplied by a time dependent multiplicand to produce a signal free of overlap convolution so that clutter signal components are centered around the Doppler frequency f.sub.D =0. Consequently, target detection is as easy as for a stationary radar antenna.Type: GrantFiled: September 7, 1993Date of Patent: May 23, 1995Assignee: Deutsche Aerospace AGInventor: Peter Schmitt
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Patent number: 5402966Abstract: A missile optical waveguide for the transmission of signals is wound as a package body, can be withdrawn from the package body during missile flight, and is provided with an outer coating having a rectangular outer contour and a wall thickness which is cross-sectionally non-uniform and is thickest in the corner areas of the outer coating. The coating can be provided with embedded fiber reinforcements, whereby the light-signal-transmitting glass fiber of the optical waveguide is effectively protected from unacceptably high tensile and pressure loads which interfere with the quality of the transmission. The winding volume is thereby reduced and problem-free axial withdrawal of the optical waveguide from the package body is ensured.Type: GrantFiled: November 5, 1992Date of Patent: April 4, 1995Assignee: Deutsche Aerospace AGInventor: Wolfgang von Hoessle