Method of space navigation and device to this end

FIELD: physics, navigation.

SUBSTANCE: invention relates to instrument making and can be used in space navigation systems to determine aircraft position coordinates. To this end, artificial Earth satellites (AES) are used as celestial reference points. Note here that zenith angle of AES being fixed is measured to be referenced to central zenith angle, aircraft position coordinates are determined from measured and referenced angle and AES coordinates.

EFFECT: higher accuracy.

2 cl, 2 dwg

 

The invention relates to the field of navigation definitions and can be used for determining location coordinates of a moving object, such as aircraft (LA).

There is a method of navigation definitions based on stabilization of astrotelescopes relative to the local vertical, direction-finding navigation stars, measurements and course angle of the star and the calculation of the course of a moving object - LA [1].

The disadvantages of this method are:

insufficient number defined navigation parameters, and consequently, the inability to determine coordinates and reckoning;

low precision navigation definitions.

Closest to the invention are the method and apparatus of navigation definitions [2], based on the stabilization of astrotelescopes using a gyro-stabilized platform through a system of targeting and tracking system relative to the local vertical, alternating direction-finding navigation stars (astroarena), measurement Zenith angles of each of the stars, the calculation on the measured angle (h) and the coordinates of the star (d, a) coordinates of the location of a moving object - LA (F, L) of expressions of the form

hi=arcsin[sin(di)sin(F)+cos(di)cos(F)cos(L-ai)], where i=1, 2 [2].

The device adopted for the prototype contains a gyro-stabilized platform, the witness is the system, block and guidance systems, and mechanical output of the gyro-stabilized platform through a guidance system and a tracking system connected to the mechanical input astrotelescopes, the first input of the computing unit of the angles associated with the electrical output of the tracking system and the second external information source, the output of the computing unit of the angles associated with the output of the computing unit coordinates whose output is the output of the claimed device.

The disadvantages of these methods and devices are low accuracy of determination of coordinates of a location and for a long time measurements to achieve the required accuracy.

The basis of the claimed invention is the problem of increasing the accuracy of determining the location coordinates of LA and the reduction in the time direction finding of astroarena to achieve the required accuracy of definition of coordinates of LA, which is an object of the invention.

The technical result of the invention is achieved in that in the method of space navigation, including the stabilization of astrotelescopes, using a gyro-stabilized platform through a system of targeting and tracking system relative to the local vertical, alternate bearing several astroarena, measurement Zenith angle of each of them, the calculation on the measured Zenith angle and coordinates astrokitty is in the position of a moving object (LA), installed astrosecond, as astroarena use artificial Earth satellites (AES) and measure the Zenith angle of each of the processed artificial satellites of the Earth, measured from built on a movable object local vertical, bringing the measured Zenith angle to the Central Zenith angle by calculating the Central Zenith angle with the vertex in the center of the Earth, calculating the measured and the calculated Zenith angles and the coordinates of the satellites location coordinates of a moving object (LA)that is astrosecond.

Suggested usage as astroarena stars instead of artificial Earth satellites.

Implements the inventive method in a device containing a gyrostabilized platform, servo system, block and guidance systems, and mechanical output of the gyro-stabilized platform through a guidance system and a tracking system connected to the mechanical input astrotelescopes, the first input of the computing unit of the angles associated with the electrical output of the tracking system and the second external information source, the output of the computing unit of the angles associated with the output of the computing unit coordinates whose output is the output of the claimed device, the electrical input astrotelescopes system through the mu guidance associated with the output block controller the first input of which is connected with an external information source, and the second with electrical outlet gyrostabilized platform.

New features with significant differences in method are the following:

1. Use as astroarena artificial Earth satellites.

2. Bringing the measured Zenith angle to the Central Zenith angle.

3. Determining from the measured and calculated angles and coordinates of the satellite coordinates of the location LA,

and the following elements of device:

1. Unit guidance, and electrical input astrotelescopes connected with the output unit guidance, the first input of which is connected with an external information source, and the second with electrical outlet gyrostabilized platform.

The application of existing and all new features can improve the accuracy of navigation and reduce the time direction finding of astroarena due to the fact that as astroarena instead of the navigational stars used movable object artificial satellite.

The specified statement is based on the well-known fact that the angular velocity of the low - and MEO satellites much more angular movements of the stars, and the information content of the measurements is higher, the greater the angular velocity of the line of sight, therefore, the information content of the satellite as astroarena considerable the above, than navigational stars.

It is also known that the accuracy of navigation definitions and processing time information determined by the information content of the measurements, providing these definitions, i.e. the observability of the measurements, and it is the higher, the higher the information content [3].

Figure 1 shows a diagram of the measurements of astroarena explaining the proposed method.

Figure 2 - block diagram of the device for implementing the method of space navigation.

The essence of the proposed method space navigation explains the device for its implementation.

The space navigation device includes a gyro platform 1, the mechanical output of which is through the guidance system 2 and tracking system 3 is connected with a mechanical input astrotelescopes 4, electric entrance through which the guidance system 2 is connected with the output unit guidance 5, the first input of which is connected with an external information source, and the second with electrical outlet gyrostabilized platform, the first input unit 6 calculate the angles associated with the electrical output of the servo system 3 and the second external information source, the output of block 6 calculate the angles associated with the input unit 7 calculate the coordinates whose output is the output of the device.

Gyro-stabilized platform 1, the guidance system 2, the tracking system 3, astrotelekom 4, unit guidance 5 - known [3, 4]. Unit 6 calculation of angles implements the expressions (4)to(8). Unit 7 calculate the coordinates implements expression(1)-(3).

Using a gyro-stabilized platform 1 through the guidance system 2 and tracking system 3 is stabilizing astrotelescopes 4 relative to the local vertical. In block 5 of the guidance for more information about the coordinates of the satellite XCTheWith, ZCand the orientation angles from LA gyrostabilized platform 1 are calculated angles a, d satellites, which are received in the guidance system 2. The guidance system 2 through the servo system 3 expands astrocalendar 4 along the line of sight to the satellite, which captures the satellite and using the system 3 accompanies it. When this occurs, the measurement of the Zenith angle of the satellite bwithrelative to the local vertical, and this information is passed to the block 6 calculation of angles. In block 6 the calculation of the corners of the conversion of the measured Zenith angle bwithto the Central Zenith angle bwiththe peak in the center of the Earth. Similarly is finding one or two satellites, depending on the need to identify two or three location coordinates and measurement Zenith angles. Information about Zenith angles bwithand Central Zenith angles bientered in block 7 of the calculations within the inat, in which determining the location coordinates (X, Y, Z) LA according to the expressions of the form:

where R=X+Y+Z, Rc=Xc+Yc+Zc; Ro=(Xc-X)+(Yc-Y)+(ZcZ), X, Y, Z - coordinates of the movable object - LA, Xc, Ywith, Zccoordinates of the satellite, i=1, 2, 3.

Thus, performing alternate bearing three satellites, we get the system of six equations, solving that can determine the three coordinates of a moving object in the earth's rectangular coordinate system.

The conversion of rectangular coordinates X, Y, Z in geographical F, L, R possible by solving the following system of equations:

where R1 is the radius - vector of a moving object.

Conclusion expression (1), (2) is carried out using the direction finding scheme, depicted in figure 1.

According to figure 1 can be written

Equating the right hand sides, we get

After transformation (5) the expression to determine the Zenith angle bwithtakes the form

The expression to determine the Zenith angle b, according to Fig 1, has the form

From (7)

The use of the claimed invention improves the accuracy of determining the coordinates of the place is the provisions of a rolling object LA by increasing the information content of measurements of the rolling object artificial satellite. Reliability improve the accuracy of the inventive method is confirmed by the above known facts on the process direction finding satellites in comparison with the stars and theory of information content of the measurements. In addition, the authors conducted a comparative study of the method of mathematical modeling method described in the prototype, and the proposed method, under the same initial measurement errors and conditions. The result is that for an artificial satellite with a period of T=120 min, the proposed method can improve the accuracy of determining the coordinates of LA 1.9-2 times, and also in 2-2,5 times to reduce the time measurements to achieve the required accuracy.

Sources of information

1. Pomykaev I.I., Seleznev VP, Dmitrichenko D.A. Navigation devices and systems. - M.: Mashinostroenie, 1983, s-202.

2. Pomykaev I.I., Seleznev VP, Dmitrichenko D.A. Navigation devices and systems. - M.: Mashinostroenie, 1983, s-215 (prototype).

3. Malyshev V.V., Krasilnikov M.N., Charles VI Optimization of surveillance and control aircraft. - M.: Mashinostroenie, 1989, 311 S.

4. Aircraft instruments and navigation systems / edited Oaaea.- M: vvia. N. E. Zhukovsky, 1981, 648 S.

1. The way space navigation, including the stabilization of astrotel the Copa, using a gyro-stabilized platform through a system of targeting and tracking system relative to the local vertical, alternate bearing several astroarena, measurement Zenith angle of each of them, the calculation on the measured Zenith angle and coordinates of astroarena location coordinates of a moving object that is astrosecond, characterized in that as astroarena use artificial Earth satellites (AES), the measurement Zenith angle of each of the processed satellite-based built on a movable object local vertical, bringing the measured Zenith angle to the Central Zenith angle by calculating the Central Zenith angle with the vertex in the center of the Earth, calculating the measured and the calculated Zenith angles and the coordinates of the satellites location coordinates of a moving object (LA)that is astrosecond.

2. Device for space navigation contains a gyro-stabilized platform, the mechanical output of which is through the guidance system and a tracking system connected to the mechanical input astrotelescopes, the first input of the computing unit of the angles associated with the electrical output of the tracking system and the second external information source, the output of the computing unit of the angles associated with the input block is and calculate the coordinates, the output which is the output of the device, characterized in that the electrical input astrotelescopes through the guidance system is connected with the output unit guidance, the first input of which is connected with an external information source, and the second with electrical outlet gyrostabilized platform.



 

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Sun attitude pickup // 2308005

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