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817results about "Instruments for comonautical navigation" patented technology

Device for concentrating optical radiation

A holographic planar concentrator (HPC) for collecting and concentrating optical radiation is provided. The holographic planar concentrator comprises a planar highly transparent plate and at least one multiplexed holographic optical film mounted on a surface thereof. The multiplexed holographic optical film has recorded therein a plurality of diffractive structures having one or more regions which are angularly and spectrally multiplexed. Two or more of the regions may be configured to provide spatial multiplexing. The HPC is fabricated by: (a) recording the plurality of diffractive structures in the multiplexed holographic optical film employing angular, spectral, and, optionally, spatial multiplexing techniques; and (b) mounting the multiplexed holographic optical film on one surface of the highly transparent plate. The recording of the plurality of diffractive structures is tailored to the intended orientation of the holographic planar concentrator to solar energy. The HPC is mounted in the intended orientation for collecting solar energy and at least one solar energy-collecting device is mounted along at least one edge of the holographic planar concentrator. Examples of suitable solar energy-collecting devices include photovoltaic cells and fiber optic light guides for transmitting collected light into an interior of a building for illumination purposes and for transmitting collected solar radiation into a hot water tank for heating. The HPC permits efficient collection of solar energy without expensive requirements, while minimizing energy losses.

Autonomous Space Flight System and Planetary Lander for Executing a Discrete Landing Sequence to Remove Unknown Navigation Error, Perform Hazard Avoidance and Relocate the Lander and Method

An autonomous unmanned space flight system and planetary lander executes a discrete landing sequence including performing an initial velocity braking maneuver to remove velocity at altitude, coasting during which the planet surface is imaged and correlated to reference maps to estimate cross-track and along-track navigation errors and one or more lateral braking maneuvers are performed to reduce cross-track navigation error, and performing a terminal velocity braking maneuver(s) to reduce the along-track braking maneuver and remove the remainder of the velocity just prior to landing. A bi-propellant propulsion system provides a very high T/M ratio, at least 15:1 per nozzle. Short, high T/M divert maneuvers provide the capability to remove cross-track navigation error efficiently up to the maximum resolution of the reference maps. Short, high T/M terminal velocity braking maneuver(s) provide the capability to remove along-track navigation error to a similar resolution and remove the remaining velocity in a very short time window, approximately 3-15 seconds prior to touchdown. The propulsive efficiency frees up mass which can be allocated to a fuel to remove the unknown navigation errors, perform hazard avoidance and/or relocate the lander by flying it to another site or be allocated to additional payload.

Remote high-precision independent combined navigation locating method

The invention relates to a remote high precision autonomous integrated navigation and positioning method, which is characterized in that a Strapdown Inertial Navigation System (SINS) is used as a main navigation system during the whole flight course of the aircraft, assisted by 3D high precision position and attitude angle information provided by celestial navigation system (CNS) based on the least square differential correction in boost phase (or middle segment). In reentry phase (terminal), using the characteristics of synthetic aperture radar (SAR), such as strong penetration capability, high resolving precision and all-weather, the SINS can be corrected through accurate location information and course information provided by SAR scene matching after motion compensation when the aircraft reentry into atmospheres, so the impact point (hit) accuracy of the aircraft can be increased and the invention has remarkable effects of eliminating or decreasing non-guidance error. The invention has advantages of autonomy and high precision, which can be used for improving remote ballistic missile, remote cruise missile, navigation and positioning accuracy of remote aircraft, such as long-endurance unmanned aerial vehicle, etc.

Navigation method for unmanned aerial vehicle

The invention discloses a navigation method for an unmanned aerial vehicle, which is characterized in that an air route detection module with an air route data reckoning function is additionally arranged on the unmanned aerial vehicle and is capable of reckoning real-time navigation data independent on satellite navigation according to parameters including flight attitude, navigational speed and height of airborne equipment, an existing satellite navigation device and existing inertial navigation equipment, which are on the vehicle in flight, are combined to generate combined navigation data, the air route detection module is used for continuously comparing the real-time navigation data with the combined navigation data and judging confidence level of the satellite navigation according to comparison data. When satellite navigation is normal, the combined navigation data are preferentially used by the unmanned aerial vehicle for flight, and the real-time navigation data are temporarily suspended; and when satellite navigation is abnormal, the real-time navigation data are automatically started by the unmanned aerial vehicle for flight. By the navigation method, flight missions of the unmanned aerial vehicle can be guaranteed to be still completed according to preset air routes under the satellite navigation losing condition, and the unmanned aerial vehicle can be prevented from flying by no-fly zones or lands in no-landing zones, so that shortcomings of the prior art are overcome.

Sensor for determining the angular position of a radiating point source in two dimensions and method of operation

A sensor for determining the angular position of a radiating point source in two dimensions includes a mask encoded in two skewed directions with waveforms consisting of several frequencies in prescribed patterns. The frequency spectra of the received detector patterns are computed. In order to facilitate such computations, the constituent frequencies are separated so as to be distinguished in the Fast Fourier Transform (FFT). Each of the frequency patterns that are coded on the variable transmissivity mask consists of a series of low frequencies followed by a series of variable frequencies, and a series of high frequencies. The variable frequencies exhibit frequency changes responsive to various image positions. The low and high frequencies are responsive in phase to variations in image position. The frequency variations in the variable frequencies are used to indicate coarse position while the phases of the fixed low and high frequencies are used to indicate medium and fine position. In a second embodiment, the mask pattern is formed by a first pattern including low variable and high frequency components, a second pattern with fixed low and high frequency components, and a third pattern with variable frequency components. The method of determining position is also disclosed.

ARM (advanced RISC (reduced instruction set computer) machines) and FPGA (field-programmable gate array) based navigation and flight control system for unmanned helicopter

The invention discloses an ARM (advanced RISC (reduced instruction set computer) machines) and FPGA (field-programmable gate array) based navigation and autonomous flight control system for an unmanned helicopter. The system comprises a PC (personal computer), an integrated navigation subsystem, a power supply module and controllers, wherein the integrated navigation subsystem comprises a sensor group; the sensor group comprises a GPS (global positioning system), a gyroscope, an accelerometer, a magnetoresistive sensor, a barometric altimeter and a sonar altimeter; the controllers include a main controller and a steering engine controller; the main controller adopts an ARM microprocessor to operate the integrated navigation algorithm and flight control PID (proportion integration differentiation) algorithm and simultaneously completes data acquisition of the GPS, the barometric altimeter and the sonar altimeter; and the steering engine controller adopts an FPGA to realize data acquisition of the gyroscope, the accelerometer and the magnetoresistive sensor and transfers the data to the main controller via a concurrent bus to carry out attitude calculation and control operation on the unmanned helicopter. With the unmanned helicopter as a carrier, the hardware environment of a whole set of flight control system integrating study of the aircraft navigation and control theory problem, data acquisition, information transfer and embedded control is set up.

Occupancy sensor and override unit for photosensor-based control of load

An occupancy sensor is provided with a separable override unit which can selectively override the operation of the occupancy sensor at designated times and for selected time intervals. The occupancy sensor includes a light sensor for actuating the occupancy sensor and a light assembly when the ambient light is below a predetermined level and to deactivate the occupancy sensor when the ambient light is above a threshold level to prevent the light assembly from being actuated when the light level is sufficient to avoid the need for actuating the light assembly. The override unit is removably attached to the occupancy sensor and is provided with a light source, such as an LED. The override unit is coupled to the occupancy sensor to emit light to actuate the light sensor of the occupancy sensor, thereby controlling the operation of the occupancy sensor, such as by preventing the occupancy sensor from being actuated regardless of the light level in the surrounding areas. The occupancy sensor includes a cavity on a top surface for receiving the override unit. The light sensor of the occupancy sensor is positioned in the cavity. The LED on the override unit is on an end that is inserted into the cavity to align with the light sensor. A control unit is operatively connected to one or more override units for selectively controlling the normal operation of the occupancy sensor.

Non-cooperative spacecraft attitude estimation method based on virtual sliding mode control

The invention discloses a non-cooperative spacecraft attitude estimation method based on virtual sliding mode control, and belongs to the technical field of non-cooperative spacecraft navigation. The non-cooperative spacecraft attitude estimation method comprises the following steps: utilizing a virtual control sliding mode controller based on the Lyapunov principle; using target satellite absolute attitude obtained by a stereoscopic vision system as a control objective; according to motion characteristics of the target satellite, establishing a virtual satellite motion model of the target satellite; using a kinetic model of the virtual satellite as a controlled member to obtain attitude parameters of the virtual satellite; using attitude parameters estimated by the virtual satellite and the target satellite absolute attitude obtained by the stereoscopic vision system as controlled input, and calculating the virtual revolving moment on the motion model of the virtual satellite through the virtual sliding mode controller, so as to realize the estimation of the target satellite attitude parameters by the virtual control sliding mode controller. The non-cooperative spacecraft attitude estimation method disclosed by the invention is low in calculated amount, and can still achieve higher convergence rate and higher precision when the initial error of the state variables is high or the system error emerges, so as to meet the requirements of the high performance navigation system.
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