317 results about "Astronomy" patented technology

A highly sensitive, high-speed dual tunnel diode detector is described for use in Ultra Wideband (UWB) object detection systems, such as a radar. The extended capability of the detector to both extremely short (sub-foot) and long distance (tens of thousands of feet) ranges is unique and permits the application of low power UWB radar to a wide variety of applications including high resolution radar altimetry at altitudes exceeding 10,000 feet and for autonomous on-deck landing operations (e.g., one-foot altitudes), the detection of extremely low radar cross section (RCS) targets for such applications as suspended wire detection for helicopters and other manned and unmanned craft, etc. High noise and interference immunity of the detector permits co-location of a UWB radar sensor with other active systems. The invention has immediate and significant application to all areas, both military and commercial, of precision distance measurement, intrusion detection, targeting, etc. over a wide range of distances.

The invention provides an attitude estimation method of a maneuvering acceleration-assisted extended Kalman filter (EKF) attitude and heading reference system (AHRS). The state quantity of the EKF contains an error of three attitude angles, a null bias error of a three-axis gyroscope and a three-axis carrier maneuvering acceleration error of a carrier system, and the observed quantity of the EKF contains a three-axis acceleration error and a three-axis earth magnetic field error. A strapdown attitude algorithm and the nine-state EKF algorithm are subjected to data fusion to acquire attitude estimation of the AHRS. A single-axis turntable experiment, a vehicle-mounted dynamic experiment and a flight experiment prove that the maneuvering acceleration-assisted nine-state EKF data fusion algorithm has stable attitude angle accuracy under different maneuvering conditions, and the mean square deviation of the attitude angle can be limited within 2 degrees.

A particle detection system including; at least one light source adapted to illuminate a volume being monitored at least two wavelengths; a receiver) having a field of view and being adapted to receive light from at least one light source after said light has traversed the volume being monitored and being adapted to generate signals indicative of the intensity of light received at regions within the field of view of the receiver; a processor associated with the receiver adapted to process the signals generated by the receiver to correlate light received at least two wavelengths in corresponding regions within the field of view of the receiver and generate an output indicative of the relative level of light received at the two wavelengths.

A device for inspecting a cargo container such as a motor vehicle or freight pallet, with penetrating radiation. A source of penetrating radiation is mounted on a moveable bed, thereby allowing a beam of penetrating radiation to sweep the large container. At least one detector is also mounted on the bed, either on the side of the source or on a boom, so that, as the beam is scanned across the container, the container and any contents of the container are characterized by transmitted or scattered radiation, or both.

Concentrating solar collector systems that utilize a concentrating reflector to direct incident solar radiation to a solar receiver are described. In one aspect, the reflective surface is arranged to direct light to the receiver in a non-imaging manner in which the solar rays reflected from the opposing edges of the reflective surface are generally directed towards a central portion of the solar receiver. Rays reflected from selected central portions of the reflective surface are directed closer to the edges of the receiver than the solar rays reflected from the edges of the reflective surface. The described reflectors are generally intended for use in solar collector systems that track movements of the sun along at least one axis.

A forward looking cross-track laser altimeter comprises: a first configuration of optical elements for guiding pulsed laser beams along a first optical path; a mirror element coupled to a scanner and disposed in the first optical path, the scanner operative to oscillate the mirror element to sweep the reflected laser beams back and forth across a line at a predetermined frequency; the scanner and mirror element configurable to reflect the pulsed laser beams along paths forward and downward at a predetermined angle to the flight path of the aircraft, wherein the pulsed laser beam paths are caused to be line swept across a ground track forward the aircraft; the mirror element for receiving returns of the pulsed laser beams from the terrain and objects on the terrain forward the aircraft and reflecting the returns along a second optical path to a light detector which produces a return signal in response thereto; a first circuit governed by the return signals for measuring times-of-flight of the returns and generating time-of-flight signals corresponding thereto; the scanner for generating a line sweep position signal; and a second circuit for generating for each return a data profile comprising range and line sweep position thereof based on the corresponding time-of-flight and position signals.

The invention relate to a high-precision laser gyroscope single-shaft rotating inertial navigation system which comprises an inertial measuring unit, a single-shaft rotating platform, a circuit box, a UPS power supply, a display control device, and the like, wherein the inertial measuring unit 1 is installed on the single-shaft rotating platform 2 and carries out shock absorption by a shock absorber 3. The periodic rotation of the single-shaft rotating platform is used for modulating literal drift of an inertial device in the inertial measuring unit and improving the posture, speed and position precision of the inertial navigation system. The system concretely comprises precise installation and calibration of the inertial measuring unit, the selection of a single-shaft rotating way, precise multiposition initial alignment, the error analysis, modeling and temperature compensation of the inertial navigation system and the inertial device and a navigation algorithm of a single-shaft rotating strapdown inertial navigation system. The invention can provide a real-time, complete and high-precision navigation posture and speed and position information for a carrier (warship) for a long time and improve the comprehensive combat capability of the carrier.

A debris removing system prevents debris from being scattered from an X-ray source. The debris removing system includes an attracting unit, disposed between a light emission point of the X-ray source and the optical system, for attracting debris. The attracting unit has an attracting surface parallel or approximately parallel to an axis passing through the light emission point. The debris removing system further includes a rotation unit for rotating the attracting unit about the axis. This debris removing system assures a superior debris removing effect and a good EUV light utilization efficiency, being compatible with each other.

The invention relates to a target positioning method and a target positioning device for airborne equipment. The device comprises a signal processing unit, a laser distance measuring instrument, a thermal infrared imager, a visible light camera, a combined inertial navigation module and an angle meter, wherein output signals of the laser distance measuring instrument, the thermal infrared imager, the visible light camera, the combined inertial navigation module and the angle meter are all connected to the signal processing unit, and the signal processing unit is used for solving positional information of a target according to uploaded signals. Aerial carrier global positioning system (GPS) information, aerial carrier gesture information, angular deviation of observation equipment relative to an aerial carrier and distance measuring information of the target by the observation equipment are integrated to realize accurate positioning of longitude and latitude height of the target. The advantage of a multi-sensor is combined, a multi-dimensional spatial alternation principle is utilized so as to rapidly and effectively realize accurate target positioning in a non-contact and high-adaptability way, and the target positioning method can be applied to fields such as forest fire prevention, personnel rapid search and rescue and the like, and has wide technological and market prospects.

The automobile collision-proof one-dimensional scanning lidar system includes casing, laser, polarizing spectroscope, optical beam expander, quarter wave plate, reflector, one-dimensional scanning vibration mirror, light detector, amplifier, signal processing system, display and warning system and brake system. The present invention has low cost, small size, easy installation, high scanning frequency, precise detection of obstacle direction and long detection distance, and possesses functions of target distinction, ranging, measuring speed, intelligently keeping away from obstacle, etc. to prevent collision to various kinds of obstacle.

An exposure apparatus for exposing an object put on a first stage by irradiating light from a light source onto the object through an exposure optical system includes a partition for isolating a first space where the first stage is arranged and isolating a second space where the exposure optical system is arranged, a first management part that manages a degree of vacuum of the first space, and a second management part that manages a degree of vacuum of the second space.

A display (8) comprises a display panel (9), a polariser (10), a polarisation rotator (13), and a scatterer (12) arranged to scatter light having a first polarisation as compared with light having a second polarisation. The display (8) can be switched between 2D and 3D modes by operating the polarisation rotator (13) accordingly. In 3D mode, the polarisation rotator (13) transmits light with relatively little or no change to its polarisation. Light transmitted by the scatterer (12) is then used to present a three-dimensional image (50). In 2D mode, the polarisation rotator (13) alters the polarisation of the light and light that is scattered by the scatterer (12) is used to present a two-dimensional image (51). The polarisation rotator (13) maybe arranged so that light incident on a first area thereof undergoes a different change in polarisation to light incident on a second area, in order to allow simultaneous presentation of 2D and 3D images (51, 50).

The invention discloses a radiation detection aircraft, which belongs to the technical field of radiation detection, and aims at solving the problem that an existing robot for nuclear radiation detection is poor in capacity for emergency management. A camera is arranged on a flying front-end shell of a four-rotor aircraft carrier; a nuclear detector is mounted at the lower end of the shell of the four-rotor aircraft carrier; a global position system (GPS) locator is used for locating the flying position of the four-rotor aircraft carrier; a detected signal output end of the nuclear detector is connected with a detected signal input end of a signal conditioning circuit; an imaging signal output end of the camera is connected with an imaging signal input end of the signal conditioning circuit; a locating signal output end of the GPS locator is connected with a locating signal input end of the signal conditioning circuit; a conditioning signal output by the signal conditioning circuit is transmitted through a wireless general packet radio service (GPRS) data transmission unit. The radiation detection aircraft is applied to nuclear radiation detection.

Estimating cement voids in between a casing and a borehole wall of a borehole penetrating the earth formation includes forming with a computing device an actual ratio of radiation induced by a neutron source and measured by a first detector and a second detector when the tool is at two or more different locations in the borehole. A relationship between the actual ratio and the porosity at each of the two or more different locations is used and compared to two different cases of estimates of the ratio. Based on the comparison, an estimate of the cement voids at the two or more locations.

An apparatus for providing pan and tilt capability to a stationary imaging device comprises a first achromatic prism doublet positioned on a first axis, a second achromatic prism doublet positioned on the first axis, and at least one motor for rotating the first and second achromatic prism doublets about the first axis whereby polychromatic electromagnetic radiation from a portion of an area of interest is directed toward an imaging device. A method of using the apparatus is also provided.

The invention discloses a flight attitude determining method based on a polarized light sensor. According to the invention, adopted equipment comprises a three-axis gyroscope, a three-axis accelerometer, the polarized light sensor, a GPS and a flight control computer. A complementary filter algorithm is used to fuse sensor data; pitch angle and rolling angle errors of the angular speed of the gyroscope are revised through measured data of the accelerometer; and an course angle error of the angular speed of the gyroscope is revised through measured data of the polarized light sensor, so that the attitude measurement precision of an aircraft is improved. Compared with a traditional flight attitude reference system, the flight attitude determining method has the advantages that the flight attitude determining method is not interfered by electromagnetism, the measurement precision of static and dynamic environments is high and the like.

Apparatus for scanning large cargo to detect concealed contents include a mobile platform configured to carry and position at least one X-ray or gamma-ray source and at least one detector array at a plurality of positions with respect to a stationary cargo. The detector array may be mounted on a boom moveably affixed to the mobile platform. Multiple measurements of radiation passing through the cargo for various source-detector orientations can be used to compute volumetric images of concealed content within the cargo.

A system and method uses light signals to detect and display the position of an airborne vehicle, such as a helicopter, during takeoff or landing or low speed, low altitude operation. A transmitter on the vehicle emits light signals while an optical receiver retrieves reflected light signals. Using light detection and ranging techniques, various parameters, such as altitude, ground speed and relative wind, are calculated based on the Doppler shift within the reflected light signals. The signals are transmitted in three different directions to facilitate the measurements of different Doppler shifts. The parameters are also displayed on a screen or other visual device within the vehicle.

A static multi-optical-path star simulator comprises a flange and at least four starlight pipes, wherein each starlight pipe can produce a simulation star, optical spectrum and brightness of each starlight pipe can be separately adjusted, the starlight pipes are installed on the flange by an angular adjustment mechanism, optical axles of two arbitrary star pipes are not parallel, relative angle between two arbitrary star pipes can be adjusted in a range not smaller than 10 degrees, a large amount of simulation constellations with different constructions can be produced, brightness and spectral characteristic of all asterions can be different, geometrical similarity between two arbitrary simulation constellations is relatively low, and physical characteristics of actual star field can be well simulated.

An automated luminaire which allows for the selection of a diffuser or a hot mirror which is mounted to engage the light beam at an angle non perpendicular to the central axis of the light beam and nonparallel or not in the same plane as the diffuser. The selector is articulated in a manner to automatically engage a selector based on what other light modulators are selected to engage the light beam and to automatically oscillate or scan when there is a likelihood of damage to the hot mirror or diffuser based on how long it is engaged and/or light intensity and/or other modulators selected and or temperature sensor data in the luminaire.

The invention relates to a method for testing the dynamic performance of a star sensor. The star sensor is placed on a three-axis turntable, three axes of the star sensor are parallel to those of the three-axis turntable, and the three-axis turntable is adjusted to ensure that the X axis and the Z axis of the three-axis turntable point to J2000.0 mean equinox and the north pole of a mean equatorial plane respectively. When the static accuracy of the star sensor is tested, the Z axis rotates at an angular speed, and both the X axis and the Y axis remain relatively still; when the dynamic accuracy of the star sensor is tested, the three axes of the three-axis turntable rotate at an angular speed set by a user; and after long-time running, the method is used for performing statistics on the two groups of data respectively. Therefore, the method can be used for not only testing the static accuracy and dynamic accuracy of the star sensor, but also testing the polarity of the star sensor, and can reduce testing apparatuses and testing costs of the star sensor.