Abstract: A user verifying method comprises: receiving an enrollment request signal including biometric information for enrollment from a user terminal; extracting feature information from the biometric information; embedding the feature information extracted from the biometric information; generating a projection parameter and a decision hyperplane parameter based on the embedding result; storing the projection parameter and the decision hyperplane parameter; generating a first template by applying a cryptographic hashing function to a pre-generated first key; receiving a verification request signal including biometric information from the user terminal; extracting feature information from the biometric information; embedding the feature information extracted from the biometric information; generating a second key corresponding to the first key based on the embedding result; generating a second template by applying the cryptographic hashing function to the second key; comparing the first template with the second templ

Abstract: A personal information security system and a method thereof ensuring irreversibility and similarity are proposed. According to specific exemplary embodiments of the present technology, the personal information security system includes a feature vector extraction unit for extracting a feature vector from user modality information, an Absolute Value Equations Transform (AVET) unit for performing absolute value equations transform on the feature vector, and a transformed-template generation unit for generating a transformed template (TT) from which the feature vector is unable to be predicted reversely from a result of the AVET.

Abstract: Systems and methods are disclosed for phase locking multiple clocks of different frequencies. In certain embodiments, an apparatus may be configured to downsample a first clock having a first frequency and a second clock having a second frequency into downsampled clocks having the same frequency. The apparatus may adjust a frequency of the second clock so that the downsampled clocks are phase aligned. The apparatus may reset counters of the divider circuits that perform the downsampling so align them to a counter for the first clock. A counter for the second clock may also be reset to align with the counter for the first clock. The synchronized clocks may be applied in data storage operations, such as self-servo writing operations, where the first clock may be a read clock and the second clock may be a write clock.

Abstract: Communication bottlenecks, particularly in the downlink direction, are a common problem for many CubeSat developers. As described herein, a CubeSat module for a CubeSat comprises an optical transmitter to transmit data to a remote terminal, a receiver to acquire an optical beacon from a remote terminal, and a fine-pointing module operably and directly coupleable to a coarse-pointing module of the CubeSat. The fine-pointing module is configured to point the optical transmitter toward the remote terminal with an accuracy range that overlaps with an accuracy range of the coarse-pointing module of the CubeSat so as to establish a communications link between the CubeSat and the remote terminal over a low-Earth-orbit (LEO) distance.

Abstract: The air eliminator valve helps to eliminate air in the plastic resin used for composite products manufacturing. During operation, it continuously eliminates the air bubbles in the plastic resin running through the valve, and then transfers the filtered plastic resin into the mold. The design of the air eliminator valve consists of: inlet, inlet lock, air vent, upper cover, main body, ultrasonic generator, outlet lock and outlet. In which, the ultrasonic generator plays a role in generating ultrasonic waves to the plastic resin in the valve body that allows speeding up the air releasing process out the plastic resin. The air content in the valve could go out through the air vent on the upper cover, its status “open/close” is controlled by airlock with automatic response mechanism.

Abstract: A method may generate a demodulated sine component for a sequence of samples of a servo burst window of a position error signal using a sine weight look up table and generate a demodulated cosine component for the sequence of samples of the servo burst window of the position error signal using a cosine weight look up table. The sine weight and the cosine weight look up tables may have indexes representing a phase range. The method may generate a demodulated phase component signal and a demodulated amplitude component signal for the sequence of samples of the servo burst window of the position error signal based on the demodulated sine component and the demodulated cosine component using a Coordinate Rotation Digital Computer at least in part by iteratively rotating a vector based on the demodulated sine component and the demodulated cosine component and summing angular changes in the vector.

Abstract: Communication bottlenecks, particularly in the downlink direction, are a common problem for many CubeSat developers. As described herein, a CubeSat module for a CubeSat comprises an optical transmitter to transmit data to a remote terminal, a receiver to acquire an optical beacon from a remote terminal, and a fine-pointing module operably and directly coupleable to a coarse-pointing module of the CubeSat. The fine-pointing module is configured to point the optical transmitter toward the remote terminal with an accuracy range that overlaps with an accuracy range of the coarse-pointing module of the CubeSat so as to establish a communications link between the CubeSat and the remote terminal over a low-Earth-orbit (LEO) distance.

Abstract: Communication bottlenecks, particularly in the downlink direction, are a common problem for many CubeSat developers. As described herein, a CubeSat module for a CubeSat comprises an optical transmitter to transmit data to a remote terminal, a receiver to acquire an optical beacon from a remote terminal, and a fine-pointing module operably and directly coupleable to a coarse-pointing module of the CubeSat. The fine-pointing module is configured to point the optical transmitter toward the remote terminal with an accuracy range that overlaps with an accuracy range of the coarse-pointing module of the CubeSat so as to establish a communications link between the CubeSat and the remote terminal over a low-Earth-orbit (LEO) distance.

Abstract: Described herein are systems and methods for attitude determination using infrared Earth horizon sensors (EHSs) with Gaussian response characteristics. Attitude information is acquired by detecting Earth's infrared electromagnetic radiation and, subsequently, determining the region obscured by Earth in the sensors' fields of view to compute a nadir vector estimation in the spacecraft's body frame. The method can be applied when two sensors, each with known and distinct pointing directions, detect the horizon, which is defined as having their fields of view partially obscured by Earth. The method can be implemented compactly to provide high-accuracy attitude within small spacecraft, such as CubeSat-based satellites.

Abstract: A method may generate a demodulated sine component for a sequence of samples of a servo burst window of a position error signal using a sine weight look up table and generate a demodulated cosine component for the sequence of samples of the servo burst window of the position error signal using a cosine weight look up table. The sine weight and the cosine weight look up tables may have indexes representing a phase range. The method may generate a demodulated phase component signal and a demodulated amplitude component signal for the sequence of samples of the servo burst window of the position error signal based on the demodulated sine component and the demodulated cosine component using a Coordinate Rotation Digital Computer at least in part by iteratively rotating a vector based on the demodulated sine component and the demodulated cosine component and summing angular changes in the vector.

Abstract: Described herein are systems and methods for attitude determination using infrared Earth horizon sensors (EHSs) with Gaussian response characteristics. Attitude information is acquired by detecting Earth's infrared electromagnetic radiation and, subsequently, determining the region obscured by Earth in the sensors' fields of view to compute a nadir vector estimation in the spacecraft's body frame. The method can be applied when two sensors, each with known and distinct pointing directions, detect the horizon, which is defined as having their fields of view partially obscured by Earth. The method can be implemented compactly to provide high-accuracy attitude within small spacecraft, such as CubeSat-based satellites.

Abstract: Communication bottlenecks, particularly in the downlink direction, are a common problem for many CubeSat developers. As described herein, a CubeSat module for a CubeSat comprises an optical transmitter to transmit data to a remote terminal, a receiver to acquire an optical beacon from a remote terminal, and a fine-pointing module operably and directly coupleable to a coarse-pointing module of the CubeSat. The fine-pointing module is configured to point the optical transmitter toward the remote terminal with an accuracy range that overlaps with an accuracy range of the coarse-pointing module of the CubeSat so as to establish a communications link between the CubeSat and the remote terminal over a low-Earth-orbit (LEO) distance.

Abstract: Described herein are systems and methods for attitude determination using infrared Earth horizon sensors (EHSs) with Gaussian response characteristics. Attitude information is acquired by detecting Earth's infrared electromagnetic radiation and, subsequently, determining the region obscured by Earth in the sensors' fields of view to compute a nadir vector estimation in the spacecraft's body frame. The method can be applied when two sensors, each with known and distinct pointing directions, detect the horizon, which is defined as having their fields of view partially obscured by Earth. The method can be implemented compactly to provide high-accuracy attitude within small spacecraft, such as CubeSat-based satellites.

Abstract: Communication bottlenecks, particularly in the downlink direction, are a common problem for many CubeSat developers. As described herein, a CubeSat module for a CubeSat comprises an optical transmitter to transmit data to a remote terminal, a receiver to acquire an optical beacon from a remote terminal, and a fine-pointing module operably and directly coupleable to a coarse-pointing module of the CubeSat. The fine-pointing module is configured to point the optical transmitter toward the remote terminal with an accuracy range that overlaps with an accuracy range of the coarse-pointing module of the CubeSat so as to establish a communications link between the CubeSat and the remote terminal over a low-Earth-orbit (LEO) distance.

Abstract: Communication bottlenecks, particularly in the downlink direction, are a common problem for many CubeSat developers. As described herein, a CubeSat module for a CubeSat comprises an optical transmitter to transmit data to a remote terminal, a receiver to acquire an optical beacon from a remote terminal, and a fine-pointing module operably and directly coupleable to a coarse-pointing module of the CubeSat. The fine-pointing module is configured to point the optical transmitter toward the remote terminal with an accuracy range that overlaps with an accuracy range of the coarse-pointing module of the CubeSat so as to establish a communications link between the CubeSat and the remote terminal over a low-Earth-orbit (LEO) distance.

Abstract: Described herein are systems and methods for attitude determination using infrared Earth horizon sensors (EHSs) with Gaussian response characteristics. Attitude information is acquired by detecting Earth's infrared electromagnetic radiation and, subsequently, determining the region obscured by Earth in the sensors' fields of view to compute a nadir vector estimation in the spacecraft's body frame. The method can be applied when two sensors, each with known and distinct pointing directions, detect the horizon, which is defined as having their fields of view partially obscured by Earth. The method can be implemented compactly to provide high-accuracy attitude within small spacecraft, such as CubeSat-based satellites.

Abstract: Techniques for developing a graphical editor using an incremental development approach. Externally-stored descriptors are used to specify information on which a graphical editor engine operates to create a graphical editor. Developers can thus redefine the look and feel of the graphical editor by modifying these descriptors, effectively re-configuring the elements of visual models without changing the code of the graphical editor engine. Visual models for modeling a domain can be created and used, without first requiring the domain model to be defined.

Abstract: Techniques for developing a graphical editor using an incremental development approach. Externally-stored descriptors are used to specify information on which a graphical editor engine operates to create a graphical editor. Developers can thus redefine the look and feel of the graphical editor by modifying these descriptors, effectively re-configuring the elements of visual models without changing the code of the graphical editor engine. Visual models for modeling a domain can be created and used, without first requiring the domain model to be defined.

Abstract: Techniques for developing a graphical editor using an incremental development approach. Externally-stored descriptors are used to specify information on which a graphical editor engine operates to create a graphical editor. Developers can thus redefine the look and feel of the graphical editor by modifying these descriptors, effectively re-configuring the elements of visual models without changing the code of the graphical editor engine. Visual models for modeling a domain can be created and used, without first requiring the domain model to be defined.