Abstract: A directly driven power swing rod device without dead points includes a control rod provided with a coordinate rod base, two L-shaped frames respectively provided with a hole base having a bearing fixed therein, two motors respectively provided with a position detecting coder for receiving a coordinate message and transmitting it to a control device which is able to control the rotating angles of the motor shafts respectively connected with the two L-shaped frames, a first interacting member inserted through a guide hole of the coordinate rod base and secured with the first L-shaped frame, and a second interacting member having one end inserted in a positioning hole of said coordinate rod base and the other end connected with the second L-shaped frame. Then the control rod may be deflected by the motors for driving a high speed, sensitive response system.

Abstract: A method, apparatus, article of manufacture, and a memory structure for designing a robust controller. The method comprises the steps of determining a plant model G of the system dynamics; bounding system dynamics unmodeled by the plant model G of the system dynamics by a weighting function W; applying a transform to an augmented plant model T having the plant model G and the weighting function W; defining a controller {tilde over (F)} from the transformed plant model T; and applying an inverse of the transform to the controller {tilde over (F)} defined from the transformed plant model and the weighting function W to generate the robust controller F.

Abstract: A directly driven power swing rod device without dead points includes a control rod provided with a coordinate rod base, two L-shaped frames respectively provided with a hole base having a bearing fixed therein, two motors respectively provided with a position detecting coder for receiving a coordinate message and transmitting it to a control device which is able to control the rotating angles of the motor shafts respectively connected with the two L-shaped frames, a first interacting member inserted through a guide hole of the coordinate rod base and secured with the first L-shaped frame, and a second interacting member having one end inserted in a positioning hole of said coordinate rod base and the other end connected with the second L-shaped frame. Then the control rod may be deflected by the motors for driving a high speed, sensitive response system.

Abstract: A method and apparatus for determining star tracker misalignments is disclosed. The method comprises the steps of defining a defining a reference frame for the star tracker assembly according to a boresight of the primary star tracker and a boresight of a second star tracker wherein the boresight of the primary star tracker and a plane spanned by the boresight of the primary star tracker and the boresight of the second star tracker at least partially define a datum for the reference frame for the star tracker assembly; and determining the misalignment of the at least one star tracker as a rotation of the defined reference frame.

Abstract: An applied control system of the power periphery of a health apparatus having function of power generation is connected with a health apparatus able to generate electricity and a peripheral device unit. The applied control system includes a voltage-controlling oscillator, an analog digital converter and an intellectual control system. The peripheral device unit includes several peripheral devices arranged in sequence. DC generated by the health apparatus is transmitted to the voltage control oscillator, which modulates the DC to a proper frequency. The analog digital converter, detects the electric power that the voltage controlled oscillator can output, transmits the detected data to the intellectual control system and controls the intellectual control system to decide the number of the peripheral devices to be started according to the electric power, the sequence and the power consumption of the peripheral devices, able to utilize electric power completely.

Abstract: An apparatus for star catalog equalization to enhance attitude determination includes a star tracker, a star catalog and a controller. The star tracker is used to sense the positions of stars and generate signals corresponding to the positions of the stars as seen in its field of view. The star catalog contains star location data that is stored using a primary and multiple secondary arrays sorted by both declination (DEC) and right ascension (RA), respectively. The star location data stored in the star catalog is predetermined by calculating a plurality of desired star locations, associating one of a plurality of stars with each of the plurality of desired star locations based upon a neighborhood association angle to generate an associated plurality of star locations: If an artificial star gap occurs during association, then the neighborhood association angle for reassociation is increased.

Abstract: The stability of a recursive estimator process (e.g., a Kalman filter is assured for long time periods by periodically resetting an error covariance P(tn) of the system to a predetermined reset value Pr. The recursive process is thus repetitively forced to start from a selected covariance and continue for a time period that is short compared to the system's total operational time period. The time period in which the process must maintain its numerical stability is significantly reduced as is the demand on the system's numerical stability. The process stability for an extended operational time period To is verified by performing the resetting step at the end of at least one reset time period Tr whose duration is less than the operational time period To and then confirming stability of the process over the reset time period Tr.

Abstract: Methods are provided for dynamically processing successively-generated star tracker data frames and associated valid flags to generate processed star tracker signals that have reduced noise and a probability greater than a selected probability Pslctd of being valid. These methods maintain accurate spacecraft attitude control in the presence of spurious inputs (e.g., impinging protons) that corrupt collected charges in spacecraft star trackers. The methods of the invention enhance the probability of generating valid star tracker signals because they respond to a current frame probability Pfrm by dynamically selecting the largest valid frame combination whose combination probability Pcmb satisfies a selected probability Pslctd. Noise is thus reduced while the probability of finding a valid frame combination is enhanced. Spacecraft structures are also provided for practicing the methods of the invention.

Abstract: Control systems and methods are provided which enhance acquisition range, transient response and offset pointing accuracy in beacon-assisted orientation of a spacecraft to a desired spacecraft attitude Adsrd. The methods receive a beacon signal with antennas that are arranged in a fixed angular relationship to thereby form an attitude error signal Serr whose magnitude is a measure of the attitude difference between a current spacecraft attitude Acrnt and the desired spacecraft attitude Adsrd. A sum power P&Sgr; that is the sum of the signal powers from the antennas is sensed and a signal modifier Smod is generated that increases with decreases in the sum power P&Sgr;. The attitude error signal Serr is then modified with a term (1+Smod) to form an enhanced attitude error signal Serrenhd. In one embodiment, the signal modifier Smod is n|Pmax−P&Sgr;|m wherein n and m are positive numbers and Pmax is the sum power P&Sgr; when the attitude error is zero.

Abstract: A method and system for minimizing attitude errors resulting from dynamic spacecraft maneuvers or time-varying mismatched attitude sensor measurements. The method includes time-tagging a primary attitude value from a primary attitude sensor and storing the value and associated time stamp in a buffer. A secondary attitude value, generated by a secondary attitude sensor, having a different associated time-stamp is then time-matched to the primary attitude valve. The corrected spacecraft attitude is then calculated as a function of the time-matched primary and secondary attitude values. In one aspect of the invention, the primary attitude sensor generates attitude data at a faster rate than the secondary attitude sensor. This primary attitude data is stored in a buffer such that, when the secondary attitude data becomes available, several nearest-in-time primary attitude data points are retrieved from the buffer. These data points are then used to interpolate a higher time-matched resolution data point.

Abstract: An attitude sensing system utilizing simplified techniques and apparatus includes a spacecraft control processor which receives signals from an inertial measurement unit and two attitude sensors. The spacecraft control processor calculates a time-varying gain matrix for estimating attitude errors and gyroscope drifts corresponding to the axes of the inertial measurement unit. In special cases where the separation angle between the attitude sensor vectors is less than approximately 10 degrees, the time-varying gain matrix is computed as a fixed gain matrix and a corresponding desensitizing factor.

Abstract: A method and apparatus for estimating attitude sensor bias in a satellite system uses attitude sensors and a spacecraft control processor. Attitude sensors provide output signals, which may contain bias. The present invention interprets the signals, determines the bias present in the signals, and generates an output signal to offset the bias in the signals from the attitude sensors, thereby leading to more accurate positioning of the satellite employing the present invention.

Abstract: Spacecraft attitude is efficiently controlled by utilizing spatial noise and temporal noise in the calculation of gains to a Kalman filter. Spatial noise is modeled in a dynamic fashion so as to provide optimal spatial noise attenuation.

Abstract: A light-emitting safety device is embedded in the transparent heel of shoe and is composed of a base, a circuit board housed in a receiving space of the base, and a deformable cap engaged with the base. The circuit board is composed of a light-emitting body, a control integrated circuit, a battery, and two connection points. The cap is provided with a conductive member capable of connecting the two connection points so as to trigger the control integrated circuit to make the power supply available to the light-emitting body when the cap is deformed by the pressure of a foot wearing the shoe. As soon as the cap is relieved of the pressure of the foot, the cap is capable of recovering its original form such that the conductive member disengages the two connection points, thereby resulting in the interruption of the power supply to the light-emitting body.

Abstract: A footwear shock-absorbing device comprises a main body, at least one shock-absorbing body having a plurality of cavities, and a pliable base equal in number to the shock-absorbing body for sealing off the bottom openings of the cavities such that the pliable base and the cavities form jointly a plurality of the closed air cells capable of alleviating the shock.

Abstract: A shoe warning light device comprises: a fastening seat having a holding space and disposed in a shoe midsole such that the front wall of the fastening seat is exposed; a luminous body fastened to the front wall of the fastening seat and provided with two polar feet extending into the holding space to form two conducting connections; a housing mounted detachably in the holding space and provided in the top wall thereof with a U-shaped slot forming a flexible tongue; two conducting pieces provided respectively with one end forming a power source connection engageable with one of the two conducting connections, with one of the two conducting pieces extending downwards to locate over the bottom wall of the housing, and with another one of the two conducting pieces extending upwards to locate under the tongue; and a battery disposed in the housing such that it is in contact with one of the two conducting pieces.