Device for connecting altitude controller of integrated system of backup devices to pilot-navigation system
FIELD: physics; navigation.
SUBSTANCE: invention relates to instrument making particularly to aircraft navigation devices. To achieve the given result, the device includes a unit of inertial initial information sensors, a three-component magnetometre, an analogue-to-digital converter (ADC), a computer, a reference voltage source, an analogue inverter, a signaling device, three control channels, a protection device and an analogue switch. The device also includes a test-control of the magnetometre by applying direct voltage across its input from the reference voltage source. The magnetometre changes its output signal, from the value of which working capacity of the device is determined.
EFFECT: increased reliability.
The invention relates to an aircraft, in particular to the orientation units.
Known unit orientation course system , containing the gyrocompass, magnetic induction sensor, an analog-to-digital Converter, a computing machine.
The disadvantage of this device is the lack of test-control magnetic induction sensor.
Known block orientation , comprising a sensor unit of the first information, consisting of three accelerometers, three angular velocity sensors, three-component magnetometer, inverter-based analog-to-digital Converter (ADC), a computing machine.
The disadvantage of this device is the lack of test-control three-component magnetometer, which reduces reliability.
The claimed invention is directed to improving the reliability of the device.
This object is achieved in that the device for the unit, the orientation of the integrated system backup devices in flight-navigation complex containing block inertial sensors of the primary information and the three-component magnetometer, is connected through an analog-to-digital Converter to the external bus interface of a computing machine according to the invention additionally introduced a source of reference voltage, an analog inverter, signalization, connected to the output of the computing machine, and three control channels, each of which contains a protection device and an analog switch, a digital input which is connected to the internal bus interface of the computer, the first analog input connected to the output of the analog inverter, whose input is connected to the reference voltage and the second analog input of the analog switch, the output of which is connected through a protection device to the input of the three-component magnetometer.
Significant differences between the proposed device is the introduction of test-control by submitting to the input of a three-component magnetometer constant voltage from the voltage reference. While the magnetometer changes its output signal, the magnitude of which can be judged on its performance, which increases the reliability of the device.
The present invention is illustrated in the drawing, which shows a structural diagram of the device containing the block 1 of the inertial sensors of the primary information, a three-component magnetometer 2, ADC 3, computer 4, the source 5 of the reference voltage, the analog inverter 6, a detector 7, three channels 8-10 control device 11 protection, the analog switch 12.
Block 1 of the inertial sensors of the primary information and the three-component mA is sitomer 2 is connected via ADC 3 to the external bus interface of the computer 4, to the internal bus interface which is connected in each channel 8-10 digital input analog switch 12, the first analog input of which is connected to the analog output of the inverter 6, the inlet of which is connected to the source 5 of the reference voltage and the second analog input of the analog switch 12, the output of which is connected through the device 11 protection to the input of the three-component magnetometer 2, the detector 7 is connected to the output of the computer 4.
The device operates as follows.
Block 1 of the inertial sensors of the primary information and the three-component magnetometer 2 given the current values of acceleration, angular rate, magnetic field of the Earth in the form of analog electrical signals by the ADC 3 is converted into a digital code received at a computing machine 4, where the computation of the values of the navigation parameters. The internal bus interface of the computer 4 in each of the channels 8-10 to the digital input of the analog switch 12 comes numeric code, which can be connected to positive or negative reference voltage through the device 11 protection on the input three-component magnetometer 2, which starts to give a test analog signal through the ADC 3 computer 4. If the magnitude of this signal is and match the expected value, this indicates normal operation of the device and a signal is generated health, which is issued by the warning device 7, if not match, then the condition is removed and the detector 7 indicates failure.
The source 5 of the reference voltage generates a voltage of one polarity, and to get the voltage of the other polarity, provides an analog inverter 6. Due to the fact that the line of communication between the three-component magnetometer 2 and ADC 3 is of considerable length, to reduce noise induced on it, provided by the device 5 protection.
The proposed device is used in the block orientation of the integrated system backup devices.
Sources of information
1. U.S. patent No. 4347730, CL 73/1ST, 1982
2. Jubilee XV St. Petersburg international conference on integrated navigation systems. The collection of materials. Saint-Petersburg, 2008, str. Compensation for magnetic deviation of the integrated system backup devices. Vimala, Duvail (prototype).
Device for the unit, the orientation of the integrated system backup devices in flight-navigation complex containing block inertial sensors of the primary information and the three-component magnetometer, is connected through an analog-to-digital Converter to the external bus interface Vici the calculating machine, characterized in that it additionally introduced a source of reference voltage, an analog inverter, the alarm device is connected to the output of the computing machine, and three control channels, each of which contains a protection device and an analog switch, a digital input which is connected to the internal bus interface of the computer, the first analog input connected to the output of the analog inverter, whose input is connected to the reference voltage and the second analog input of the analog switch, the output of which is connected through a protection device to the input of the three-component magnetometer.
FIELD: physics; navigation.
SUBSTANCE: invention relates to instrument making and can be used in aircraft navigation systems. The technical outcome is widening of functional capabilities. To achieve this outcome, the device includes a unit of initial information sensors, an analogue-to-digital converter (ADC), a computer, an alternating voltage source, a decoder, conversion channels, a register, a digital-to-analogue converter (DAC) and a power amplifier.
EFFECT: device enables converting digital information on the current values of angles of position of the aircraft to analogue signals, proportional to their sine or cosine.
FIELD: aerospace engineering.
SUBSTANCE: astrohardware and Earth sounding hardware data is used to accurately determine spacecraft orbit and coordinates and orient it. Sounding data, apart from its designed purpose, is subjected to additional processing to be made in separate frames of the Earth image. This allows determining direction to the Earth center ("to plot local vertical"), correct current spacecraft coordinates and its orientation. Coordinates derived from combination of the Earth sounding area frames on one and several orbital passes are processed together to produce orbit parametres. Orbit parametre estimations are used for navigation-ballistic computations effected aboard the spacecraft till updating at another flight path. Note here that to do with aforesaid tasks, spacecraft needs no usual navigation data from ground appliances or satellite navigation systems, e.g. GLONASS. It does not required special means of orientation relative to the Earth centre (or horizon), say, infrared vertical. Model analyses have shown good chances of providing high accuracy in spacecraft current orientation and coordinate data on high-elliptical or geo-stationary orbit.
EFFECT: expanded operating performances in independent pilotless operation.
6 cl, 3 dwg
FIELD: physics; navigation.
SUBSTANCE: invention relates to navigation equipment of vehicles. The proposed navigation device can display directions on a display, receive a video signal from a camera and display a combination of the image from the camera and directions on the display. The device, which is a portable navigation device, includes a built-in camera. The device can provide an option from the menu which enables the user to regulate relative position of the displayed image from the camera with respect to the directions.
EFFECT: using the proposed device, instructions which can be quickly and easily interpreted are displayed for the user.
15 cl, 12 dwg
FIELD: physics; navigation.
SUBSTANCE: invention relates to navigation instrument making. The set problem is solved by that, conditions are created in which substantial connection appears and is used on a section of a ballistic trajectory between error models of inertial measurement modules when solving the problem of orientation and navigation. This connection appears and can be used in providing the following conditions: presence of fast rotation around a longitudinal axis and coning motion of precession of the control object about the centre of mass or only rotation of the object around a longitudinal axis on a ballistic trajectory; placing a unit of accelerometres of inertial measurement modules and a reception antenna for the satellite navigation system at a certain distance (basically on a transverse axis) from the centre of mass of the control object; solving the problem of orientation and navigation in the inertial measurement modules at the point of placing the unit of accelerometres at high frequency - approximately an order higher than frequency of rotation of the control object (due to necessity of generation of dynamic components in navigation parametres without distortions); formation of measured values of primary navigation parametres in the reception apparatus of the satellite navigation system where the reception antenna is placed using tracking measuring devices with bandwidth greater than the frequency of rotation of the control object. Also values of primary navigation parametres are calculated in the computer of the inertial measurement modules and these values are also used in the feedback in the reception apparatus of the satellite navigation system for narrowing the frequency band in tracking systems of carrier frequency and code delay.
EFFECT: increased accuracy and noise immunity of integrated systems of orientation and navigation (ISON), which have inertial measurement modules (IMM) on "rough" micromechanical gyroscopes and a miniature reception apparatus of satellite navigation systems (RA SNS), in generating orientation parametres of control objects (CO) on a section of its ballistic trajectory for a long period of time, ie provision for stationary character and limited level of errors of integrated systems of orientation and navigation in solving the problem of orientation of a control object on a ballistic trajectory, as well as high level of noise immunity.
FIELD: physics; navigation.
SUBSTANCE: invention relates to navigation satellite corrected inertial navigation and gyrostabilisation systems for sea objects and can be used on ships and other vessels in a wide range of navigating conditions. The inertial-satellite navigation, orientation and stabilisation system has a gyrostabilised platform in a triaxial cardan suspension with angle sensors, on which are mounted three rate integrating gyroscopes and three accelerometres, digital device, corrector, where outputs of the angle sensors for rotation of the rings of the cardan suspension and outputs of the accelerometres of the gyrostabilised platform are connected to inputs of the digital device, one of the outputs of which is connected to the input of the gyrostabilised platform, and the other to the corrector. The inertial-satellite navigation system is fitted with a control console which generates system control signals, and the system is also fitted with an accelerated correction unit, the input of which receives current values of coordinates of navigation satellites used, generated by the satellite receiving device and current device values of parametres of orientation of the gyrostabilised platform, a channel switch for standard and accelerated correction, where outputs of the correctors are connected to inputs of the switch, outputs of which are connected to the digital device.
EFFECT: determination of course error from coordinate data of only two satellites of a satellite navigation system and current device parametres of orientation of an object, generated by an inertial navigation system.
4 dwg, 1 tbl
SUBSTANCE: invention relates to methods of determining angular motion parametres of winged pilotless aircraft and can be used in controlling pilotless aircraft, maneuvering with different flight modes: ricochet, gliding and combined mode. According to the proposed method, if the sections of the ground surface are not even, the platform is stabilised parallel to the plane of the local horizon using gyroscopic devices, and with radio altimetres if the ground surface is even, and angular motion parametres of the pilotless aircraft are measured relative this platform.
EFFECT: increased accuracy of determining angular motion parametres of pilotless aircraft.
FIELD: physics; optics.
SUBSTANCE: invention relates to optical instrument making and can be used for determining coordinates of a ship from navigational stars. The optical astronavigation system has a periscope, goniometric device which has a stabilised sighting prim, stabilised base which is placed on a cardan suspension, collimator with a floating mark, adjustment device and an eyepiece, fitted in the lower part of the periscope, as well as two unstabilised sighting prisms, lying in one vertical plane parallel each other. The goniometric device is placed in the lower part of the periscope. One of the unstablised sighting prisms is fitted in the head of the periscope, and the other - in front of the goniometric device. The device also has a mirror, beam splitter and a cube, fitted such that, the direction of the light beam with the floating mark into the eyepiece is provided through the unstabilised sighting prism in front of the goniometric device, mirror, beam splitter and cube, and the direction of the viewed image of the object in the eyepiece is provided through the beam splitter.
EFFECT: smaller dimensions of the device while retaining accuracy of measurement.
FIELD: instrument making.
SUBSTANCE: invention is related to magnetic measurements on moving objects, in particular to instruments intended for measurement of components and complete vector of Earth magnetic field induction, and also to magnetic course indication and navigation in transport means. Device comprises serially connected and mutually closely located three-component detector of magnetic field, which is rigidly connected to axes of object, and transceiving device installed in fixed position on object, which includes serially connected commutator, analog memorising device, unit of analog-digital conversion and microcomputer.
EFFECT: higher accuracy of magnetic measurements on moving object by elimination of electromagnetic noise effect from transceiving device of magnetic-measurement instrument.
FIELD: instrument making.
SUBSTANCE: invention is related to facilities of navigation and control of moving objects, namely to inertial navigation systems. In platform-free inertial metering converter comprising three accelerometres, three gyroscopic angular speed metres (GASM), computing device, devices for compensation of errors, devices for error compensation in conversion coefficient are arranged in each GASM, devices of compensation of cross connection between each GASM. Each device of GASM conversion coefficient error compensation comprises the first and second repeaters, operational amplifier, inverter and creates a differential outlet for tracking systems of aircraft control-surface actuators control. Each device for compensation of cross connection comprises switch, resistive divider and compensation resistor connected to outlet of resistive divider. Devices for compensation of cross connection are connected between each of GASM conversion coefficient error compensation.
EFFECT: expansion of functional resources of platform-free inertial metering converter.
2 cl, 1 dwg
FIELD: physics, measurement.
SUBSTANCE: invention is related to satellite navigation and may be used to build orbit-based functional addition to global navigation satellite system (GLONASS). Substance of method consists in the fact that on board of low-orbit spacecraft navigation equipment of user is installed, which is used to receive navigation messages, as well as additional equipment used to receive signals of on-air television of ground stationary television radio stations, bearing frequencies of two or more television channels are separated, on the basis of which Doppler shift of bearing frequencies is detected, orbit parametres are detected, calculating ephemerids of spacecraft, and navigation messages are formed in accordance with specified structure of navigation message, then radio navigation signals are broadcasted in direction of navigation information consumer location.
EFFECT: higher reliability of navigation detections of navigation information consumers performed with the help of GLONASS, due to increase of orbit-based navigation message sources number.
FIELD: indirect measurement of flying vehicle attitude.
SUBSTANCE: proposed system includes angular velocity and linear acceleration sensors, satellite navigation system and digital computer which is used for synchronous reception of data from information systems for matching the trajectory formed by signal of angular velocity and linear acceleration sensors with trajectory measured by satellite navigation system. Besides that, computer ensure functioning of recurrent algorithm of estimation of bank, pitch and yawing angles at sliding time interval.
EFFECT: enhanced accuracy.
FIELD: instrument engineering.
SUBSTANCE: device has optical spectrum filter, slit mask, multi-element photo-sensitive detector, threshold elements, photo-detector register, counter, output register, clock pulse generator. Multi-element photo-sensitive detector consists of elementary photo-detectors placed behind one another along quadratic curve. Normal lines to sensitive areas of each elementary photo-detector and quadratic curve lie in same plane.
EFFECT: higher effectiveness and efficiency.
FIELD: location finding.
SUBSTANCE: according to the method module and angle of increment vectors of motion are determined which vectors relate to motion of transportation vehicle. Then correspondent position of transportation vehicle is determined automatically at specified points within specific area when the transportation vehicle passes those points. Current position of transportation vehicle within area is found by means of vector addition of increment vectors of motion with vector of position of current position. Automatical finding of the position of transportation vehicle is performed by means of pick-up unit mounted on transportation vehicle which unit interacts with corresponding control mark without having contact with it. Control mark has reflecting and non-reflecting surfaces which are subject to scanning simultaneously by means of two signals sent from transportation vehicle. Coordinates of control position of transportation vehicle and angle of movement are determined due to estimation of reflected signals depending on time.
EFFECT: improved precision; improved reliability.
13 cl, 5 dwg
FIELD: gyro instrument engineering.
SUBSTANCE: components of apparent acceleration are measured by means of accelerometers mounted onto at least two gyro platforms, signals for controlling gyro platforms are formed and formed signals are controlled in response by means of gyros. Gyro platform is controlled by signals, which provide non-linear communication between value of speed deviation and value of horizontal component of absolute angular speed.
EFFECT: improved precision data; widened dynamic capabilities.
FIELD: navigation of moving objects.
SUBSTANCE: proposed method includes measurement of phantom acceleration by means of accelerometers, forming the gyro-platform control signals and following these signals by means of gyroscope. Gyro-platform is used for controlling the signals which contain signals proportional to components of phantom acceleration generated by accelerometers ensuring invariance of generation of speed deviation of gyro-platform relative to horizon plane. Compass heading is generated by means of optical follow-up system. Components of absolute angular velocity of Darbu trihedral as well as components of speed deviation of gyro-platform relative to horizon plane are generated by accelerometer signals. Navigation parameters such as heading of object and its local coordinates are determined by components of absolute angular velocity of Darbu trihedral.
EFFECT: enhanced efficiency.
FIELD: programmed positioning and orientation of mobile objects; angular orientation or positioning of spacecraft.
SUBSTANCE: proposed method includes measurement of angles of position of optical axes of astro-visual units tracking the stars relative to body-axis coordinate system. For determination of orientation of mobile object, use is made of coordinates of its center of mass in geocentric coordinate system which are determined by means of high-precision global navigation satellite system.
EFFECT: enhanced accuracy of orientation of mobile objects.
FIELD: attitude control and navigation systems.
SUBSTANCE: inertial attitude-and-heading reference system has angular velocity transducer three-channel unit, linear accelerometers three-channel unit, integrator unit, orientation angles derivative former, correction unit, observed attitude-and-heading reference system unit, unit for calculating errors in attitude-and-heading reference system, filter, route adjustment unit. Angular velocities measured by angular velocity transducer three-channel unit and transformed to derivatives from angles of orientation. Those velocities have errors provided by systematic and random errors of measurement. If angular velocities are integrated by integrator unit, the error is not accumulated as permanent component of error is deducted from input signals coming to integrator unit. Roll and pitch are corrected by correction unit by means of using unit for calculating observed vertical and linear accelerator unit. Route is corrected by correction unit together with route adjustment unit. Unit for calculating errors in attitude-and-heading reference system computes difference between observed and calculated angles of orientation. Filters stores mainly statistic errors which are applied to correction unit to compensate errors of platform inertial attitude-and-heading reference system. The compensation has to be actual and total as it is performed according to closed scheme where sign inversion is present; the compensation includes also integration operation.
EFFECT: reduced error for adjustment of angular error.
FIELD: aircraft instrumentation engineering; manned flying vehicle information representation systems.
SUBSTANCE: proposed device is provided with computer module, memory module and graphical module and is designed for dynamic forming of sequence of cartographic mimic frames and their animation demonstration on displays of onboard multi-functional indicators. Device employs cartographic data kept in memory and present flight data. Actual navigational information pertaining to present moment may be obtained by personnel in graphical form at high level of clearness and readability, which is achieved due to realization of definite modes and conditions of flight and conditions of several modes of flight of synthesis of cartographic mimic frames which differ in criterion of selected representations, methods of representation, cartographic projections and rules of positioning, orientation and scaling-up of cartographic representations. Mode of synthesis of cartographic mimic frames is selected automatically according to results of identification of present stage, mode and conditions of flight or at the discretion of personnel.
EFFECT: possibility of keeping the personnel informed on flight conditions at all phases of flight.
5 cl, 2 dwg
SUBSTANCE: method comprises processing the signals from the gyroscope or pickups of absolute angular velocity. The gyroscopic platform controls the signals, which include the signals proportional to the components of the virtual acceleration generated by accelerometers, keeping the gyroscopic platform at a given angle with respect to the horizontal plane. The outer axis of the double-axle gimbal suspension is perpendicular to the base plane. The base is made of a platform stabilized in the horizontal plane.
EFFECT: enhanced reliability of determining.
FIELD: the invention refers to tracing and control of tilting bodies.
SUBSTANCE: tracing and control of attitude of a tilting body is executed on the basis of the signals derived from a gyroscope. The gyroscope signal is transformed and integrated for forming of information of assessed position in the form of modified quarternion in which a multiplier of yawing is limited by zero value. Modified quarternionic information in an analogous form is also formed from the signals derived from a sensor of inclination and is used for definition and correction of a multiplier of an error in the information of the assessed position. Gyroscope drift is also corrected on the basis of a derived signal of the sensor of inclination.
EFFECT: increases reliability of tracing of an object's orientation in a more wide frequency bandwidth and also simplifies computing process.
11 cl, 4 dwg