JPH05308310A - Antenna driving device - Google Patents

Abstract

PURPOSE:To realize easy, highly precise direction control with simple constitution by generating a rotational angle command of a 1st space navigation body with a position vector estimated on the basis of a GPS signal and a position vector estimated on the basis of position information on a 1st space navigation body. CONSTITUTION:A GPS receiver 20 receives the GPS signal from a GPS satellite and measures the position and speed information of a satellite mounted with an antenna, inputs them to a track position estimation part 22 through a signal input part 21, and outputs the estimated position vector R1 to a command angle generation part 23. The position vector R2 of the direction satellite calculated by the calculation part 24a of a track calculation part 24 is inputted to the generation part 23. A processing part 25 receives track calculation parameters from a ground station and converts them into specific numerals, and then inputs them to the calculation part 24a. The calculation part 24a calculates the vector R2 from those parameters. The command angle generation part 23 calculates the rotational angle command of the antenna, a subtracter 26 subtracts the output of a sensor 27, and such a signal that the difference becomes zero is sent to an antenna driving mechanism 33 to control the direction of the antenna 32.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an antenna driving device used to control the orientation of an antenna mounted on a spacecraft such as a user satellite that uses data relay of a data relay satellite or an orbital work vehicle.

[0002]

2. Description of the Related Art Conventionally, as shown in FIG. 2, an antenna driving apparatus of this type has been used to transmit orbit calculation parameters of an on-board satellite, such as a user satellite, which is transmitted as a command from a ground station, and a data relay satellite. The command input processing unit 1 receives the orbit calculation parameter of the pointing satellite. The command processing unit 1 converts the input trajectory calculation parameter into a predetermined numerical value and then outputs it to the first and second calculation units 2a and 2b of the onboard trajectory calculation unit 2. The first and second calculators 2a and 2b of the onboard orbit calculator 2 calculate the position vectors R1 and R2 of the onboard satellite and the pointing satellite based on the input orbit calculation parameters, and the target angle generator 3 Output to. The target angle generation unit 3 calculates the rotation angle target values θx and θy of the onboard satellite and the pointing satellite based on the input position vectors R1 and R2, and outputs them to one input end of the subtractor 4.

The subtractor 4 is connected to the output end of the antenna angle detecting angle detection sensor 5 at the other input end, and to the output end of the first signal processing section 6a. .. The first signal processing unit 6a uses the target angle target value θ
The antenna drive signal is generated so that the difference between x and θy and the output of the angle sensor 5 becomes zero, and the fixed contact a of the switch 7 is generated.
Output to.

The fixed contact b of the switch 7 is connected to the output end of the second signal processing unit 6b, and the output end of the radio wave sensor 8 is connected to the input end of the second signal processing unit 6b.
The radio wave sensor 8 detects the radio wave of the antenna 9 to detect the antenna pointing error angle with the pointing satellite. The second signal processing unit 6b generates an antenna drive signal so that the input antenna pointing error signal becomes zero, and outputs it to the fixed contact b of the switch 7. An antenna driving mechanism 10 is connected to a movable contact c of the switch 7, and is switched to a fixed node a or b in response to a switching signal transmitted from the ground, for example, and the first and second signal processing units 6a, The antenna drive signal generated in 6b is output to the antenna drive mechanism 10. The antenna drive mechanism 10 controls the direction of the antenna 9 in response to an antenna drive signal input via the first and second signal processing units 6a and 6b.

However, in the above antenna drive device, since the trajectory calculation parameters transmitted from the ground include an error, the position vectors R1 and R2 calculated by the onboard trajectory calculator 2 are calculated as the time elapses. There is a problem that the error becomes large and the antenna pointing accuracy is lowered. Therefore, it is conceivable to improve the antenna pointing accuracy by transmitting the latest orbit calculation parameters sequentially from the ground by commands.

However, in the above configuration, the latest value of the trajectory calculation parameter has to be sequentially set, which causes a problem that the operation becomes very troublesome. Further, according to this, there is a problem that the size becomes large because the ability of the onboard trajectory calculation unit 2 to calculate the position vector based on the trajectory calculation parameter must be increased.

[0007]

As described above, the conventional antenna driving device has a problem that the antenna pointing accuracy is lowered as time passes.

The present invention has been made in view of the above circumstances, and it is an object of the present invention to provide an antenna driving device having a simple structure and capable of realizing highly accurate antenna pointing control. ..

[0009]

The present invention relates to an antenna drive mechanism for directing an antenna mounted on a first spacecraft to a second spacecraft flying at a predetermined interval, and A measuring means mounted on the first spacecraft, which receives GPS signals to detect position and velocity information, and the first spacecraft based on the position information of the first spacecraft measured by the measuring means. An estimating means for estimating the position vector of the navigation vehicle, an operation means for obtaining the position vector of the second space navigation vehicle based on the orbit calculation parameter of the second pointing spacecraft transmitted as a command; Target value generating means for generating a rotation angle target value based on the position vector of the second spacecraft calculated by the calculating means and the position vector of the first spacecraft estimated by the estimating means;
First signal processing means for generating an antenna drive signal based on the antenna directional angle and the rotation angle target value to drive the antenna drive mechanism to control the directional direction of the antenna; and a radio wave of the antenna. One of the first signal processing means and the second signal processing means for generating an antenna drive signal based on the direction and drivingly controlling the antenna drive mechanism to control the pointing direction of the antenna. The antenna drive device is configured to include a switch setting means for selecting and switching.

According to the above configuration, the position vector of the first spacecraft is estimated based on the GPS signal. Then, the position vector of the second spacecraft is calculated and generated based on the orbit calculation parameter transmitted by the command. Accordingly, as the error component of the antenna rotation angle target value of the first spacecraft that directs the antenna to the first to second spacecraft, the trajectory of the position vector of the second spacecraft is generated. By using only the calculation parameters, the error component of the antenna drive signal generated by the first signal processing unit is reduced as compared with the conventional case, and high-precision antenna pointing control can be performed for a long period of time.

The present invention also provides an antenna drive mechanism for directing an antenna mounted on a first spacecraft to a second spacecraft flying at a predetermined interval, and the first spacecraft. A measurement means for receiving GPS signals to detect position and velocity information and a position vector of the first spacecraft based on the position information of the first spacecraft measured by this measurement means. First estimating means for estimating, second estimating means for estimating a position vector of the second spacecraft based on position information of the second spacecraft transmitted as a command, and the first estimating means And target value generating means for generating an antenna rotation angle target value for directing the first to second spacecraft on the basis of the position information estimated by the second estimating means, the pointing angle of the antenna and the rotation angle target. Ante based on value First signal processing means for generating a drive signal to drive the antenna drive mechanism to control the pointing direction of the antenna, and to generate an antenna drive signal based on the radio wave direction of the antenna to drive the antenna. An antenna drive device comprising a second signal processing means for driving and controlling the mechanism to control the pointing direction of the antenna, and a switching setting means for selecting and switching one of the first and second signal processing means. Is configured.

According to the above configuration, the rotation angle target value of the first spacecraft is based on the position vector estimated based on the GPS signal and the position information of the second spacecraft transmitted by the command. And the position vector estimated by As a result, the error component of the antenna pointing rotation angle target value of the first spacecraft that is directed to the first to second spacecraft is almost eliminated, and the first signal processing unit drives the reliable antenna. A signal can be generated, and highly accurate antenna pointing control can be performed for a long period of time.

[0013]

Embodiments of the present invention will be described below in detail with reference to the drawings.

FIG. 1 shows an antenna driving device according to an embodiment of the present invention. A GPS receiver 20 receives a GPS signal from a GPS satellite as well known, and the position of the antenna mounting onboard satellite is received. And measure speed information. This G
A signal input unit 21 is connected to the PS receiver 20. At the signal input terminal 21, the position and speed information of the onboard satellite measured by the GPS receiver 20 is output to the orbit position estimation unit 22.
The trajectory position estimation unit 22 estimates the position vector R1 based on at least the position information of the input position and velocity and outputs the position vector R1 to the target angle generation unit 23.

The orbit position estimating unit 22 complements the orbit position when, for example, the update period of the position and speed information from the GPS receiver 20 is the same as or shorter than the operation period of the pointing control. Instead, perform the estimation operation.

Further, the output end of the calculation unit 24a of the onboard trajectory calculation unit 24 is connected to the target angle generation unit 23,
The position vector R of the pointing satellite calculated by the calculator 24a
2 is entered. Calculation unit 2 of on-board trajectory calculation unit 24
The output end of the input processing unit 25 is connected to 4a. The input processing unit 25 receives the orbit calculation parameter of the pointing satellite transmitted as a command from the ground station, converts it into a predetermined numerical value, and then outputs it to the calculation unit 24a. Calculator 24a
Calculates the above-described position vector R2 of the pointing satellite based on the input orbit calculation parameter.

The target angle generation unit 23 calculates the rotation angle target values θx and θy of the onboard satellite antenna for directing the antenna from the onboard satellite to the pointing satellite based on the input position vectors R1 and R2, and the subtracter 26 It outputs to one input end.

The subtractor 26 is connected to the output end of the antenna angle detecting angle detection sensor 27 at the other input end thereof, and to the input end of the first signal processing section 28 at the output end thereof. The first signal processing unit 28 generates an antenna drive signal so that the difference between the target angle target values θx and θy and the output of the angle sensor 27 becomes zero, and outputs the antenna drive signal to the fixed contact a of the switch 29.

The fixed contact b of the switch 29 is connected to the output end of the second signal processing section 30, and the input end of the second signal processing section 30 is connected to the output end of the radio wave sensor 31. .. The radio wave sensor 31 detects the radio wave of the antenna 32 to detect the antenna pointing error angle with the pointing satellite. The second signal processing unit 30 generates an antenna drive signal so that the input antenna pointing error signal becomes zero, and switches 29
To the fixed contact b. An antenna drive mechanism 33 is connected to the movable contact c of the switch 29, and is selectively controlled to be switched to the fixed node a or b in response to a switching signal transmitted from the ground, for example, to perform the first and second signal processing. Part 2
The antenna drive signal generated in 8 and 30 is output to the antenna drive mechanism 33. The antenna drive mechanism 33 controls the orientation of the antenna 32 in response to an antenna drive signal input via the first and second signal processing units 28 and 30.

As described above, the antenna driving apparatus mounts the GPS receiver 20 on the on-board satellite on which the antenna 32 is mounted, and calculates the position vector R1 based on the position and speed information measured by the GPS receiver 20. By estimating, only the position vector of the pointing satellite was calculated based on the orbit calculation parameter transmitted from the ground by a command. According to this, since the error components of the rotation angle target values θx and θy are only the errors generated in the generation of the position vector R2 of the pointing satellite, the error of the antenna drive signal generated in the first signal processing unit 28 is generated. The amount is reduced as compared with the conventional one, and high-precision antenna pointing control can be performed for a long period of time. Further, according to this, since the onboard processing is reduced, the electronic circuit including the memory can be reduced, and the size of the onboard orbit calculation unit 24 can be reduced, which is required in recent space development. Contributes to the promotion of shaping.

In the above embodiment, the on-board satellite uses GPS.
The receiver 20 is mounted to detect the position and velocity from the GPS signal to estimate the position vector R1, and the position vector R2 of the pointing satellite is estimated based on the orbit calculation parameter transmitted by the command. When the satellite is equipped with a GPS receiver, the on-board satellite receives the position and speed information of the on-board satellite detected by the on-board satellite by other communication means such as radio communication, and based on this position and speed information, the position vector R2 May be estimated. In this case, an effective effect can be expected by further removing the error component. The position vectors R1 and R2 can be estimated based on position information or position and velocity information. Therefore, it is needless to say that the present invention is not limited to the above-described embodiments, and various modifications can be made without departing from the scope of the present invention.

[0022]

As described above in detail, according to the present invention, it is possible to provide an antenna driving device having a simple structure and capable of realizing highly accurate antenna pointing control with ease.

[Brief description of drawings]

FIG. 1 is a diagram showing an antenna driving device according to an embodiment of the present invention.

FIG. 2 is a diagram showing a conventional antenna driving device.

[Explanation of symbols]

20 ... GPS receiver, 21 ... Signal input unit, 22 ... Orbit position estimation unit, 23 ... Target angle generation unit, 24 ... Onboard trajectory calculation unit, 24a ... Orbit calculation unit, 25 ... Command input processing unit, 26 ... Subtraction 27 ... Angle detection sensor, 28 ... First signal processing unit, 29 ... Switch, 30 ... Second signal processing unit, 31 ... Radio wave sensor, 32 ... Antenna, 33 ... Antenna drive mechanism.

Claims (5)

[Claims] 1. An antenna drive mechanism for directing an antenna mounted on a first spacecraft to a second spacecraft flying at a predetermined interval, and mounted on the first spacecraft, Measuring means for receiving GPS signals to detect position and velocity information, and estimating means for estimating a position vector of the first spacecraft based on the position information of the first spacecraft measured by the measuring means. And a calculating means for obtaining a position vector of the second spacecraft based on the orbit calculation parameter of the pointing second spacecraft, which is transmitted as a command, and a second spacecraft calculated by the calculating means. Target value generation means for generating a rotation angle target value based on the position vector of the body and the position vector of the first space navigation body estimated by the estimation means, and based on the pointing angle of the antenna and the rotation angle target value. Each Generating an antenna drive signal to drive the antenna drive mechanism to control the directional direction of the antenna; and generating an antenna drive signal based on the radio wave direction of the antenna, A second signal processing means for driving and controlling the antenna driving mechanism to control the pointing direction of the antenna, and a switching setting means for selecting and switching one of the first and second signal processing means. An antenna drive device characterized by: 2. The antenna driving apparatus according to claim 1, wherein the estimating means estimates the position vector of the first spacecraft based on the position and velocity information detected by the measuring means. 3. An antenna drive mechanism for directing an antenna mounted on a first spacecraft to a second spacecraft flying at a predetermined interval, and mounted on the first spacecraft, Measuring means for receiving a GPS signal to detect position and velocity information; and first for estimating a position vector of the first spacecraft based on the position information of the first spacecraft measured by the measuring means. Estimating means for estimating the position vector of the second spacecraft based on the position information of the second spacecraft transmitted as a command, and the first and second Target value generating means for generating an antenna rotation angle target value of the first spacecraft for directing the antenna to the first to second spacecraft based on the position information estimated by the estimating means; And the rotation angle First signal processing means for generating an antenna drive signal based on a target value and driving the antenna drive mechanism to control the pointing direction of the antenna; and generating an antenna drive signal based on the radio wave direction of the antenna. A second signal processing means for driving and controlling the antenna driving mechanism to control the pointing direction of the antenna; and a switching setting means for selecting and switching one of the first and second signal processing means. An antenna driving device comprising: 4. The first estimating means estimates the position vector of the first spacecraft on the basis of the position and velocity information detected by the measuring means. Antenna drive. 5. The second estimating means estimates the position vector of the second spacecraft based on the position and velocity information of the second spacecraft. The antenna driving device described.