JPH053097U - Position signal generator for spacecraft - Google Patents

Abstract

(57) [Summary] [Purpose] The purpose of the spacecraft is to obtain position signals in orbit independently and with high accuracy. [Structure] A position signal generator that autonomously updates an error of position integration data and a corrected position signal generation means for correcting an error of a position detection signal are provided.

Description

[Detailed description of the device]

[0001]

[Industrial applications]

 The present invention relates to a spacecraft position signal generation device mounted on a spacecraft for detecting the position of the spacecraft itself in orbit.

[0002]

[Prior Art]

 A conventional spacecraft position signal generator for detecting the position of the spacecraft on orbit will be described with reference to FIG.

In FIG. 3, 7 is an integrator, and 16 is a ground station. The integrator 7 generates the position detection signal 8 of the spacecraft at that time by integrating the position detection signal 8 of the spacecraft. Since the integrator 7 generates an error when integrating the position detection signal 8 of the spacecraft, it was necessary to periodically correct the error.

When the spacecraft is visible from the ground station 16, the position detection signal 8 of the spacecraft is updated by updating the position detection signal 8 of the integrator 7 of the spacecraft by the command 17 from the ground station. The error occurring in 8 is corrected.

[0005]

[Problems to be solved by the device]

 In the conventional spacecraft position signal generator as described above, it is necessary to periodically transmit the command 17 from the ground station 16 and update the position detection signal 8 during the operation of the spacecraft. There was a drawback that operation became complicated.

The present invention has been made to solve the above-mentioned problem, and the spacecraft automatically updates the position update signal in orbit to enhance the automatic operation of the spacecraft and to improve the position by the corrected position detection signal. The purpose is to correct the detection signal and improve the accuracy of the position detection signal.

[0007]

[Means for Solving the Problems]

 In the position signal generator for a spacecraft according to this invention, a solar cell element that generates electricity by sunlight, a voltage detector that detects the voltage generated by the solar cell element, and a time measuring device that measures the time A position signal generator that generates a position update signal on the spacecraft's orbit at that time and a corrected position detection signal from the signals of the voltage detector and time measuring device is provided.

[0008]

[Action]

 In the spacecraft position signal generator configured as described above, the time when the voltage is generated and the time when the voltage generation is stopped in the solar cell element installed in the spacecraft body is detected, and the position of the sun at that time is detected. It becomes possible to generate the position update signal of the spacecraft itself and update it automatically by the signal of the time measuring instrument indicating. Further, since the corrected position detection signal is also updated according to the generation of the position update signal, it is possible to always obtain a highly accurate position signal.

[0009]

【Example】

 Example 1. An embodiment of the present invention will be described below with reference to the drawings. FIG. 1 is a block diagram for explaining an embodiment of the present invention. In the figure, 1 is a voltage detector, which detects the time when the voltage is generated in the solar cell element 2 installed in the spacecraft body and the time when the voltage generation is stopped. Reference numeral 3 in the figure is a time measuring device, which detects the position of the sun on the ecliptic by integrating the operating time signal. In the figure, reference numeral 4 denotes a position signal generator, which outputs a position update signal 5 which is an integral increment of the position detection signal from the signals of the voltage detector 1 and the time measuring device 3 and a corrected position detection signal 6 of the position detection signal. To generate. Reference numeral 7 is an integrator for integrating the position detection signal. Reference numeral 8 is a position detection signal output from the integrator 7.

FIG. 2 is a diagram showing an example of the positional relationship between the spacecraft and the sun when the spacecraft position detection signal according to the present invention is generated. In the figure, 9 is the orbit of the spacecraft, 10 is the sun, 11a and 11b are spacecrafts, 12 is an arrow indicating the traveling direction of the spacecraft 11a, 13 is the spring equinox, and 14 is the earth.

It is assumed that the time at this time is the equinox, and therefore the sun 10, the equinox 13 and the earth 14 are on a straight line. Moreover, the solar cell element 2 is installed in the main body of the spacecraft 11 so as to generate a voltage while the satellite is exposed to the sunlight in the orbit. Reference numeral 15 indicates an ascending node of the orbit 9 of the spacecraft.

The voltage of the solar cell element 2 stops when it passes a position on the orbit where the earth shadows the earth like the spacecraft 11a in FIG. 2 (this time is designated as time A). Next, a voltage is generated in the solar cell element 2 when passing through a position where the spacecraft 11b comes out of the shadow of the earth in orbit (this time is designated as time B). The position signal generator 4 calculates the time interval between the time A and the time B, the time A measured one cycle before and the time A measured this time, and the position signal generator 4 considers the output signal of the time measuring device 3 at the time of the equinox. Then, the position update signal 5 of the spacecraft itself is calculated, and the position detection signal integration data of the integrator 7 is updated. Further, the corrected position detection signal 6 is calculated and the position detection signal 8 is updated.

The calculation formula of the position update signal 5 is as shown in Equation 1. The formula for calculating the corrected position detection signal 6 is as shown in Equation 2.

[0014]

[Equation 1]

[0015]

[Equation 2]

In this way, the position update signal 5 of the integrator 7 is updated each time the voltage of the solar cell element 2 is stopped / generated, and the position detection signal 8 is updated by the corrected position detection signal 6.

[0017]

[Effect of the device]

 As described above, the present invention updates the position update signal 5 and the position detection signal 7 of the integrator 7 each time the voltage generated in the solar cell element 2 is stopped / generated, so that the attitude control of the spacecraft 11, etc. Is automated, and the accuracy of the position detection signal 7 is improved.

[Brief description of drawings]

FIG. 1 is a block diagram showing an embodiment of the present invention.

FIG. 2 is a diagram showing an example of a positional relationship between a spacecraft and the sun when a spacecraft position detection signal according to the present invention is generated.

FIG. 3 is a block diagram showing a conventional position signal generator.

[Explanation of symbols] 1 voltage detector 2 solar cell element 3 time measuring device 4 position signal generator 5 position update signal 6 corrected position detection signal 7 integrator 8 position detection signal 9 spacecraft orbit 10 sun 11 spacecraft 12 space Arrow indicating the direction of flight of the aircraft 13 Spring equinox 14 Earth 15 Ascending / descending point 16 Ground station 17 Command from ground station

Claims (1)

[Claims for utility model registration] 1. A position signal generation device for generating a position signal in orbit, which is mounted on a spacecraft, wherein a solar cell element that generates electricity by sunlight and the solar cell element A voltage detector that detects the generated voltage, a time measuring device that measures the time by integrating the count value, and a position update signal on the orbit of the spacecraft at that time from the signals of the voltage detector and the time measuring device. An orbital position signal generator for a spacecraft, comprising a position signal generator that generates a corrected position detection signal and an integrator that integrates the position detection signal of the spacecraft.