Abstract: A guidance method for guidance systems is disclosed. The method includes forming a target track point with a target tracker. The method corrects the track point with a manual correction signal. A speed of rotation of the line of sight is determined with the target tracker. A track control system dynamic model is provided for forming an estimated value for the rotation speed of the line of sight. The estimated value for the rotation speed of the line of sight is formed from the determined speed of rotation of a line of sight corrected with a correction value generated with the dynamic model of the track control circuit based on the manual correction signal. The estimated value of the speed of rotation of the line of sight is then used for guidance.

Abstract: A method for determining a frequency of a signal includes transforming the analog signal to the complex frequency range through a digital filtering, preferably a FFT, so that result vectors with amplitude and phase components are generated in the frequency range. As a result, a continuous sequence of transformation intervals (FFT intervals) develops within a measuring interval that can be predetermined. Subsequently, pairs of result vectors, which belong to the same predetermined frequency, are selected from predetermined transformation intervals (FFT intervals). Associated phase differences are then formed from which a weighted phase difference is determined. The weighted phase difference is used to correct the signal frequency determined from the amplitude spectrum. This method permits very accurate frequency measuring, especially for pulsed HF signals.

Abstract: A direction-finding method for determining an incident angle of a high-frequency electromagnetic signal in a system including at least two receiving antennas spaced apart by a known distance. the antenna output signals of the at least two receiving antennas are converted, together (in accordance with a multiplexing procedure) or individually, into the frequency domain through a Fourier transformation, followed by a conversion into an IF range and an A/D conversion. In this range, the phase difference between the output signals is determined and the signal frequency of the incident wave is determined through a phase-sequence analysis. The incident angle of the incident wave is determined from the phase difference and the signal frequency.

Abstract: This invention provides a method of forming a component made of an artificially and plastically formable material which can be hardened by artificial aging. The component is first shot-peen-formed in the unhardened condition and is subsequently, artificially aged. During artificial aping it is subjected to an exterior pressure load causing a creep of the impact-body-forming material to conform to a mold having the desired shape.

Abstract: The invention particularly relates to the detection of fast-flying targets by means of an HPRF radar system that operates with a plurality of switchable pulse-repetition frequencies (PRFs). In the method, a high velocity resolution is attained, which permits a reliable detection of a multiple-target situation. At the same time, a precise range determination is attained with a high range resolution by means of a pure transit-time measurement of the pulses. The length of the used range gates is selected to correspond to the anticipated target length.

Abstract: Apparatus for simultaneous calibration of several multi-axis gyro systems, particularly fiber-optical gyro systems, in all measuring axes, uses a single-axle rotary table. A rotary frame is connected with the axis of rotation of the single-axis rotary table, and the gyro systems are arranged thereon in such a manner that corresponding measuring axes of the gyro systems experience an identical component of the rotation of the rotary frame, and none of the components is zero.

Abstract: The invention relates to a method for monitoring the earth's surface with a moving aircraft using a radar sensor with a synthetic aperture. In order to produce high resolution radar images, the flight parameters of the aircraft are also required. According to the inventive method, key parameters, such as speed and acceleration, are detected in the sight line of the radar sensor from the radio signals received. One of the advantages of the invention is that an inertial navigation system (INS) is no longer required for this purpose.

Abstract: A lift body has a variable camber to achieve a flow-favorable profile. The lift body has a structure which is elastically deformable at least in one area. An integrated adjusting device includes at least one dimensionally stable adjusting body which can be rotated about an axis and which is in an operative connection with the deformable structure. Each adjusting body has a curved conical shape whose local cross-section corresponds to the local profile thickness. Each adjusting body is in a direct and/or, via a sliding layer, an indirect contact with the deformable structure.

Abstract: The object of the invention is to provide a lock-in process and device for a YIG-tuned oscillator which takes into account ageing and hysteresis of the YIG-tuned oscillator. This object is attained in that during a predetermined frequency change, the frequency of the YIG-tuned oscillator (1) is preset by means of a microprocessor (17) that progressively changes the current (I.sub.SP) in the main tuning coil (13) of the YIG-tuned oscillator (1) by an iterative capture routine, until the capture range (.DELTA.FM) of the switched-on frequency-locked loop, which changes with the coil current (I.sub.SP), includes the new operating frequency (f.sub.SET). The switched-on frequency-locked loop then pulls the oscillator frequency into the capture range of the PLL and the PLL locks-in the oscillator frequency to the new operating frequency (f.sub.SET). The microprocessor (17) interrupts the capture routine when a PLL-LOCK detector (11) announces to the microprocessor (17) that the new operating frequency (f.sub.

Abstract: A release element for a holddown device, on a solar generator, for example, with a retaining bolt which is under pretension in the direction of its lengthwise axis, releases the retaining bolt from its pretensioned position. Pretensioning force is exerted on the retaining bolt through thread located at the end of retaining bolt into a corresponding internal thread in the release device. Internal thread is located half in a housing of release device and half in an opener. Opener is inserted pivotably in a cutout of housing and held in place by a wire coil wound around housing and opener. To release retaining bolt, the wire coil is released by fuse elements and expands to a larger diameter, releasing the retaining bolt.

Abstract: The helicopter rotor blade connection has a support beam which connects the lift-generating wing section of the rotor blade with the rotor hub, and transmits centrifugal and lateral forces as well as bending and torsional moments. The connection is torsionally elastic and, at least in a main plane, bending elastic. A damping device for damping bending vibrations of the support beam is constructed alternately of elastomer layers and intermediate layers which are stiff in the direction of their extension. According to the invention, the damping device consists of a plurality of separate individual dampers which are arranged with their elastomer and intermediate layers in the direction of the main bending plane of the support beam.

Abstract: An attitude controller for a 3-axis stabilized, Earth oriented bias momentum spacecraft is described, where only 2-axis attitude measurements from the Earth sensor are available. In contrast to the classical spacecrafts that are controlled w.r.t. a fixed orbital Earth pointing reference frame, (possibly large angle) time varying reference signals are considered here, i.e. the control task consists of a tracking problem. The controller design consists of a decoupling controller and axis-related PID controllers based on yaw observer estimates.

Abstract: A waveguide oscillator by means of which carrier waves can be generated in a waveguide. The waveguide oscillator takes the form of a planar slotted guide structure arranged in the waveguide approximately perpendicularly to the longitudinal axis of the waveguide and has two transmitting slotted guides, at least one semiconductor oscillator element and at least one compensation slotted guide.

Abstract: A direction-finding method for determining an incident angle of a high-frequency electromagnetic signal in a system including at least two receiving antennas spaced apart by a known distance. the antenna output signals of the at least two receiving antennas are converted, together (in accordance with a multiplexing procedure) or individually, into the frequency domain through a Fourier transformation, followed by a conversion into an IF range and an A/D conversion. In this range, the phase difference between the output signals is determined and the signal frequency of the incident wave is determined through a phase-sequence analysis. The incident angle of the incident wave is determined from the phase difference and the signal frequency.

Abstract: A low earth orbiting satellite control arrangement according to the invention has an earth sensor for measuring roll and pitch of the satellite relative to an earth oriented moving reference system, a spin wheel mounted along an axis perpendicular to the orbital plane of the satellite for measuring spin of the satellite, and two magnet coils for generating control. A first of the two magnet coils is aligned substantially in parallel to a roll axis of the satellite, and the second is aligned substantially parallel to the yaw axis. Alternative control algorithms are disclosed for controlling attitude, nutation and spin of the satellite based on information from the earth sensor, spin wheel and an observer which is also mounted on the satellite.

Abstract: The invention concerns a diode-pumped solid-state ring laser gyroscope consisting of a diode-pumped solid-state laser made from a doped crystal or glass in the form of a square or cube for monoaxial or triaxial measurements; limitation and stabilization of the laser mode is achieved by precise matching of the pumping radiation to the mode volume of the ring laser. Outcoupling of the laser radiation is done by making the light tunnel through a slit to a dielectric plate which is moved by an actuator. Frequency modulation of the signal is done as required by coupling an acoustic wave into the laser medium or by precise spatial modulation of the diode excitation.

Abstract: In a process and apparatus for controlling the attitude of a spacecraft, drive signals for driving attitude control units of the spacecraft are generated based on control unit signals related to the three principle axes of a spacecraft oriented coordinate system, using the rule k=B.sup.I e+cu.sub.2. The drive matrix B.sup.I, a definite vector u.sub.2 and the constant c result from the application of a matrix decomposition according to the Singular Value Decomposition (SVD) method to a nozzle matrix B. The latter matrix contains as elements, the momentum and force vectors which can be generated by the attitude control units, and the drive matrix B.sup.I is multiplied directly with the vector e derived from the axis-related control unit signals.

Abstract: A system for guiding the end phase of guided autonomous missiles consists of a marker unit having a sensor, a signature transmitter and a device for attachment to the target, as well as a cooperating direction finder in the guided missile.

Abstract: An arrangement for attitude control and stabilization of a three-axis stabilized, bias momentum spacecraft which is equipped with a spin wheel arrangement that is capable of generating an angular momentum vector in a predeterminable direction, as well as control torques about all three axes of a spacecraft fixed system of coordinates, independently of one another. The control arrangement is equipped with an attitude sensor, which measures the attitude deviation about a first lateral axis (roll axis) oriented perpendicularly to the predetermined direction, with actuators for generating external control torques.

Abstract: An armor plating for vehicles has at its outer side a layer (13) of plastics material bound explosive containing radar absorbing materials.