An instrument (20) determines the attitude of a spacecraft (3) on which it is mounted, by interacting incident light (11) from the Sun with one or more light conditioning elements (12) and thereby forming a diffraction pattern at a photo-sensitive detector (13). The intensity distribution of light on the detector (13) is dependent on the angle of incidence of the light (11). An on-board computer (16) determines a direction vector to the Sun based on the light diffraction pattern detected by the detector (13).

Systems that enable observing celestial bodies during daylight or in under cloudy conditions.

Apparatus for electronically quantifying conditions of a person and an environment containing the person, as well as a sequence of positions occupied by the person and a direction the person faced at those positions. Wireless communications track a series of positions over time and provide user interfaces indicating where a person has been and who the person has come within a minimum distance of. Sensors may be operative to provide ongoing evaluation of a condition of the person, such as a body temperature and heartrate which may trigger an alarm state if the body temperature rises above a specified value. Electronic sensors may also be quantify environmental conditions over time and present the conditions in the user interface.

A laser measuring system including first and second laser base stations and a laser receiver is provided. The laser receiver detects a first laser signal from the first laser base station. Location information associated with the first laser base station is extracted from the detected first laser signal. The laser receiver detects a second laser signal from the second laser base station. Location information associated with the second laser base station is extracted from the detected second laser signal. A position of the laser receiver is determined based on the extracted location information associated with the first laser base station and the extracted location information associated with the second laser base station.

A method of fully autonomous geometric calibration for linear-array remote sensing satellite (LARSS) based on the joint observation for stars and earth by satellite, with the support of satellite's high maneuverability is proposed. This invention realizes the full-link processing from data acquisition to internal and external calibration. Based on the ultra-high attitude stability and agile maneuverability, this invention designs a joint observation mode for the star and the earth, which is suitable for autonomous geometric calibration. With the joint observations, this invention achieves the external calibration through the star observations acquired in the solar shadow area, and achieves the internal calibration through the ground overlapping images acquired in the solar illumination area. Therefore, the high-precision geometric imaging model of the LARSS would be restored by the method, under the condition without using the ground calibration sites.

Systems, methods, and devices for fluid conduit inspection using absolute velocity of a sensor device are provided. The method includes: receiving sensor data collected by a sensor device during a measurement run from an interior of the fluid conduit while traveling along a length of the fluid conduit, the sensor device including a first magnetometer and a second magnetometer each having a fixed position in the sensor device, the fixed positions defining a separation distance between the first magnetometer and second magnetometer, the sensor data including magnetic flux data comprising first magnetic flux data collected by the first magnetometer and second magnetic flux data collected by the second magnetometer; determining a time delay between when a magnetic signal is present in the first magnetic flux data and when the magnetic signal is present in the second magnetic flux data; determining an absolute velocity of the sensor device.

A device (800) for protecting an aircraft against missiles, includes a Short-Wave InfraRed based (SWIR-based) Missile Tracking Unit, having a SWIR-based optical imager that associated with an optical SWIR band filter. The device (800) further includes a SWIR signals processor; it analyzes the captured SWIR optical signals; and it performs a SWIR-based missile acquisition process, which is also based on raw angular position data of a missile as received from a Missile Approach Warning System (MAWS); and it performs a SWIR-based missile tracking process, which continuously and dynamically determines a precise angular position of the missile based on the captured SWIR optical signals. The device (800) includes a laser-based missile-jamming unit, having an internal laser emitter; and optionally also being operably associated with an external high-power laser emitter; to disrupt the missile, or to disrupt a guiding station of the missile.

A heliostat calibration system having a system controller, and a heliostat having a heliostat controller, wherein: the system controller is configured to receive a calibration data point and initial calibration offset angle guess, calculate a tracking error, identify a calibration offset angle, and the heliostat controller configured to transmit a calibration data point, receive adjustment instructions, and execute the adjustment instructions.

Apparatus and related methods are provided for evaluating effectiveness of a visual augmentation system (VAS), such as night vision goggles (NVGs). The apparatus and methods illustratively measure the response time of the visual augmentation system (VAS) as a function of targeting detection, engagement, and scan angle.

A bearing inner race for a solar panel tracker positioning system includes a semi-circular shaped body having a first upper land and an oppositely facing second upper land. A first elongated aperture is positioned proximate to the first upper land and a second elongated aperture is positioned proximate to the second upper land. A first alignment ring is centered within the first elongated through aperture and a second alignment ring is centered within the second elongated through aperture. The bearing inner race also includes a ground stud integrally connected to the body in an as-cast condition of the body.