Abstract: The present invention provides a maneuver device for an artificial satellite, which causes small attitude error during maneuver and which requires a shorter period of setting time for obtaining a target attitude. The maneuver device is provided with: a feed forward torque instruction signal generator 8 which outputs a feed forward torque instruction signal 11 based on a maneuver plan; a thruster 10 which outputs control torque based on the feed forward torque instruction signal 11; and an attitude control signal calculator 6 to which an attitude angle and an angular velocity of the artificial satellite as well as a target attitude angle and a target angular velocity are input and which outputs an attitude control signal 13. The maneuver device is further provided with a disturbance compensating signal calculator to which the feed forward torque instruction signal 11 and a detected angular velocity signal 16 are input, and which generates and outputs a disturbance compensating signal 12.

Abstract: A 6-degree-of-freedom control apparatus for a spacecraft includes a plurality of thrusters, thruster modulator, position/velocity detector, target position/velocity generator, attitude/angular velocity detector, target attitude/angular velocity generator, and 6-degree-of-freedom controller. The thrusters control three position axes and three attitude axes of a spacecraft by jet. The thruster modulator selectively drives the thrusters on the basis of a thruster control signal. The position/velocity detector measures a position and velocity of the spacecraft. The target position/velocity generator generates target position and velocity values of the spacecraft. The attitude/angular velocity detector measures an attitude and angular velocity of the spacecraft. The target attitude/angular velocity generator generates target attitude and angular velocity values of the spacecraft.

Abstract: An attitude detection system for an artificial satellite includes an interpolator for interpolating an angular-velocity signal to generate an interpolated angular-velocity signal, a sequential Kalman filter for generating a low-frequency attitude-angle signal, and an adder for adding the low-frequency attitude-angle signal and a high-frequency attitude-angle signal generated by a high-frequency angular sensor to generate a broad-band attitude-angle signal.

Abstract: The present invention provides a maneuver device for an artificial satellite, which causes small attitude error during maneuver and which requires a shorter period of setting time for obtaining a target attitude.

Abstract: This invention provides an offline attitude determining apparatus capable of detecting an artificial satellite attitude at a high precision in wide band. Averaging and addition processing are carried out on a low-frequency attitude interpolation signal generated by interpolating a low-frequency attitude detection signal obtained by inputting an attitude angle determination signal generated by a sequential Kalman filter computation device and a high-frequency attitude detection signal obtained by inputting a high-frequency attitude angle sensor detection signal extracted by a high-frequency attitude angle sensor data extracting device into a band pass filter computation device, so as to generate a high-precision attitude detection signal. By combining the low-frequency attitude detection signal with the high-frequency attitude detection signal with an interpolation processing computation device and an attitude data generator, the attitude can be determined at a high precision in wide band.

Abstract: A 6-degree-of-freedom control apparatus for a spacecraft includes a plurality of thrusters, thruster modulator, position/velocity detector, target position/velocity generator, attitude/angular velocity detector, target attitude/angular velocity generator, and 6-degree-of-freedom controller. The thrusters control three position axes and three attitude axes of a spacecraft by jet. The thruster modulator selectively drives the thrusters on the basis of a thruster control signal. The position/velocity detector measures a position and velocity of the spacecraft. The target position/velocity generator generates target position and velocity values of the spacecraft. The attitude/angular velocity detector measures an attitude and angular velocity of the spacecraft. The target attitude/angular velocity generator generates target attitude and angular velocity values of the spacecraft.

Abstract: This invention provides an offline attitude determining apparatus capable of detecting an artificial satellite attitude at a high precision in wide band. Averaging and addition processing are carried out on a low-frequency attitude interpolation signal generated by interpolating a low-frequency attitude detection signal obtained by inputting an attitude angle determination signal generated by a sequential Kalman filter computation device and a high-frequency attitude detection signal obtained by inputting a high-frequency attitude angle sensor detection signal extracted by a high-frequency attitude angle sensor data extracting device into a band pass filter computation device, so as to generate a high-precision attitude detection signal. By combining the low-frequency attitude detection signal with the high-frequency attitude detection signal with an interpolation processing computation device and an attitude data generator, the attitude can be determined at a high precision in wide band.

Abstract: An attitude angle sensor correcting apparatus for an artificial satellite of the present invention includes a satellite attitude estimator. The satellite attitude estimator reads geographical image data out of an image data memory, produces a GCP (Ground Control Point) position included in the image data by stereo image measurement, and then estimates the instantaneous satellite attitude angle on the basis of a relation between the measured GCP position and a true GCP position. An attitude angle sensor data corrector corrects measured attitude angle data with estimated satellite attitude data output from the satellite attitude estimator and corresponding in time to the measured attitude angle data. The attitude angle sensor data corrector outputs an estimated satellite attitude signal.

Abstract: An optical antenna pointing controller for an optical antenna system having an optical antenna and biaxial gimbal mechanism coupled to the optical antenna and mounted on the satellite is provided. Feedback control in the controller is gain-stabilized by a nominal compensator, and disturbance is suppressed by a robust compensator, further, a target satellite is captured quickly with the aid of a reference model and feedforward, thus providing quick response without dependency on the band width of feedback control system.

Abstract: An antenna tracking control device includes detectors for detecting speed and the steering angle of a movable body, a device for calculating the estimated azimuth angle of the movable body based on the detected speed and steering angle, and a detector for detecting the azimuth angle of the movable body. Also, an azimuth angle error estimator is provided for calculating the error between the calculated estimated azimuth angle and the detected azimuth angle. In addition, a directing angle error detector is used for detecting antenna directing angle error, and a directing angle error corrector is used for correcting the detected antenna directing angle error, with the result that the antenna tracking control device causes an antenna mounted on a moveable body, such as an automobile, to track a wave generating source based on the corrected antenna directing angle error.

Abstract: A piezoelectric buzzer includes a piezoelectric diaphragm stored in a case having a case body and a back cover, and a pair of metal terminals which are electrically connected to the piezoelectric diaphragm and drawn out from the back cover. The metal terminals have terminal drawing portions, terminal fixing portions which are arranged along an inner surface of the back cover, and connecting portions which are bent from inner ends of the terminal fixing portions so that the bent portions are substantially U-shaped as viewed from above while forward ends thereof are separated from the inner surface of the back cover and brought into contact with the piezoelectric diaphragm.

Abstract: In a vehicle-mounted antenna tracking system, a bearing error between the bearing angle of the antenna and the direction of arrival of a signal from a satellite, the bearing angle of the antenna, and a vehicle attitude is detected and summed together to produce a satellite position signal. The vehicle attitude and the antenna's bearing angle are summed together to produce an absolute antenna bearing signal. If the antenna is in line of sight to the satellite, the satellite position signal is stored into a memory and the bearing error signal is applied through a filter circuit to an antenna drive system so that the antenna's bearing is controlled to reduce the bearing error to a minimum. If the antenna is not in line of sight to the satellite, the stored signal is read out of the memory and a pseudo-error signal is produced by taking the difference between the signal from the memory and the absolute antenna bearing signal, and applied through the filter circuit to the antenna drive.

Abstract: Dialkyl-trisulfides having a minimum grade of copper-strip corrosivity which are suitable as extreme-pressure additives, are produced at high selectivity by reacting alkyl-mercaptans and sulfur at a quantitative ratio in a range of 0.5 to 1.0 gram atom of sulfur to 1 mol of alkyl-mercaptan in the presence of magnesium oxide as catalyst.

Abstract: A parallel type piezoelectric bimorph vibrator is used for a piezoelectric buzzer or a piezoelectric loud-speaker, which is cemented at both ends of a conductive diaphragm together with piezoelectric elements, and is provided at part of the outer periphery of a diaphragm with a cutout, the outer peripheries of the piezoelectric elements facing the cutout. Electrodes outside both the piezoelectric elements are connected by a conductor at the position corresponding to the cutout, so that the existence of the cutout prevents the conductor from being brought into contact with the diaphragm.

Abstract: A new anti-inflammatory, analgesic, and antipyretic pharmaceutical composition is disclosed which contains a 3,5-di-tert-butyl-4-hydroxystyrene derivative of the formula: ##STR1## wherein R.sup.1 stands for a group represented by COR.sup.3 [R.sup.3 denotes a group of OR.sup.4 (R.sup.4 is a hydrogen atom or an alkyl group with C.sub.1 .about.C.sub.4), an alkyl group with C.sub.1 .about.C.sub.3, a phenyl group, or an amino group], a nitro group, or an alkylsulfonyl group represented by SO.sub.2 R.sup.5 (R.sup.5 is an alkyl group with C.sub.1 .about.C.sub.3); and R.sup.2 stands for a hydrogen atom, an alkyl group with C.sub.1 .about.C.sub.4, a hydroxyalkyl group with C.sub.1 .about.C.sub.4, a cyano group, or an acyl group represented by COR.sup.6 (R.sup.6 is an alkyl group with C.sub.1 .about.C.sub.3),or its pharmaceutically acceptable salt as an active ingredient in association with pharmaceutical excipients.

Abstract: Novel compounds, 3,5-di-tert-butylstyrene derivatives and their salts, are disclosed, which derivatives are represented by the general formula: ##STR1## wherein R.sup.1 stands for an acyloxy group represented by R.sup.3 COO (R.sup.3 is a hydrogen atom or an alkyl group with C.sub.1 -C.sub.6), an alkoxyl group of R.sub.4 O (R.sup.4 is an alkyl group with C.sub.1 -C.sub.4), a hydroxyl group, or a hydrogen atom; R.sup.2 stands for ##STR2## (R.sup.5 is a hydrogen atom or an alkyl group with C.sub.1 -C.sub.3 and X.sup.1 is CH.sub.2 or an oxygen atom), ##STR3## (R.sup.5 and X.sup.1 are each the same as defined above), or ##STR4## (X.sup.2 is an oxygen or sulfur atom).

Abstract: A new antibiotic designated as auromomycin is prepared from the culture broth of Streptomyces macromomyceticus, a macromomycin-producing strain, as yellow crystals. Auromomycin is recovered in pure form from the culture broth by using hydrophobic chromatography with Octyl Sephalose CL-4B or Phenyl Sepharose CL-4B.