JPH08244699A - Space navigation body - Google Patents

Abstract

PURPOSE: To simplify the maintenance and inspection work by realizing a sure diagnosis on a failure position. CONSTITUTION: Multiple image pickup cameras 11a, 11b and lighting units 13a, 13b are mounted on a space navigation body main body 10 capable of freely flying in the outer space, and thrust is generated by a propulsion machine 15, and the space navigation body main body 10 approaches a target space navigation body. The spot illumination light is selectively irradiated by the lighting units 13a, 13b, the image pickup positions of the target space navigation body are photographed by the image pickup cameras 11a, 11b, image signals are signal-processed by a signal process controller 17, and the image data are transmitted to an external image observation section on a space base.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a spacecraft used to obtain image data by photographing each part of a spacecraft body including artificial satellites such as communication satellites and broadcasting satellites launched into geostationary orbits. Regarding the body

[0002]

2. Description of the Related Art As is well known, in a spacecraft such as an artificial satellite, various space-mounted devices such as electronic devices and space structures are mounted to realize a predetermined mission.
After being launched into outer space, these space-equipped devices are set to an operable state and desired operation is executed. In such a space-borne device, in order to confirm the operation when setting it to be operable, for example, a confirmation switch is provided in a movable part such as the deployment mechanism of the solar array paddle, and the confirmation switch It is configured to detect the operating state of the movable part based on the status signal.

However, in the above-mentioned operation confirming means, when a space-borne device fails, whether the status signal is a malfunction of the space-borne device itself on the ground based on the received status signal or a malfunction of the confirmation switch itself. Since it is difficult to determine whether or not it is difficult, it takes a lot of time and labor to repair the failure.

For example, in the operation of deploying a solar array paddle, if there is no response even when a paddle deploy command is sent from the ground to the spacecraft, is there an abnormality in the confirmation switch arranged at the deploy position of the paddle, or It is difficult to judge whether the paddle deployment mechanism itself is abnormal, and as a result, it is necessary to repeatedly execute various trials within the possible range to find a failure point, and it takes a lot of time and effort to avoid the failure. Requires.

[0005]

As described above, in the conventional spacecraft, it is difficult to understand the cause of the failure of the equipment mounted on the space. Therefore, it is difficult to avoid the failure, and it is very difficult to avoid the failure. It has the problem of requiring time and labor.

The present invention has been made in view of the above circumstances, and it is possible to realize a reliable diagnosis of a failure portion with a simple structure and to contribute to simplification of maintenance and inspection work. The purpose is to provide a navigation body.

[0007]

SUMMARY OF THE INVENTION According to the present invention, a propulsion unit for generating a propulsive force that flies at an arbitrary altitude and orbit in outer space and a plurality of image-capturing cameras whose direction can be adjusted are arranged in combination. , An image pickup means for photographing the target spacecraft, a spot lighting means for irradiating the photographing position of the target spacecraft photographed by the image pickup camera of the image pickup means with spot light, an image pickup camera for the image pickup means, and a spot lighting means. Is directed to the target spacecraft so that it can be photographed, signal processing means for processing image signals obtained by the image pickup camera of the image pickup means to generate image data, and signal processing means for generating the image data. And a data transmitting unit for transmitting the image data to the external image observing unit, which constitutes a spacecraft.

[0008]

According to the above structure, the image pickup camera flies by the propulsion means and approaches the target space vehicle, and selectively illuminates the spot illumination light at a predetermined position of the target space vehicle with the illuminator. Then, the image signal is processed by the signal processing means and transmitted as image data to the external image observation section. Therefore, the external image observation unit that has received the image data can determine the situation of each part of the target spacecraft based on the image data, and can take prompt measures against the failed part, for example.

[0009]

Embodiments of the present invention will be described below in detail with reference to the drawings. FIG. 1 shows a spacecraft according to an embodiment of the present invention. In a spacecraft body 10, for example, two imaging cameras 11a and 11b are mounted on a platform 12.
The direction is adjustable via a and 12b. Illuminators 13a and 13b having a flash function are integrally mounted on the imaging cameras 11a and 11b, respectively.
The imaging cameras 11a and 11b are provided with a zoom function and a wide-angle / telephoto function, respectively, and drive control units 14a and 14b (see FIG.
The focus position is set on the target by the selective adjustment via (see), and the video signal to be shot is selectively set to either a moving image or a still image.

A thruster 15, such as a thruster or an ion engine, is mounted on the spacecraft body 10 at a predetermined position, and the propulsive force generated by the thruster 15 flies at an arbitrary altitude and orbit in outer space. At the same time, the attitude control is performed.

A transmitting / receiving antenna 16 is mounted on the spacecraft body 10 via a pointing control mechanism (not shown). The transmission / reception antenna 16 transmits image data generated as described later to a ground station and other spacecraft that form an external image observation unit, and also sends a command command for the ground station and other spacecraft such as sky. To receive.

As shown in FIG. 2, the signal processing control section 17 is connected to the output terminals of the image pickup cameras 11a and 11b, respectively. The drive control units 14a and 14b are connected to the output ends of the signal processing control unit 17, and the imaging cameras 11a and 11 are connected to the output ends of the drive control units 14a and 14b.
b and the signal input ends of the illuminators 13a and 13b, the platform 12
a, 12b (not shown in FIG. 2 for the sake of convenience in FIG.
See) are connected respectively. The input / output terminal of the signal processing control unit 17 is connected to the telemetry / command modulator / demodulator 1
8 is connected, and the transmission / reception antenna 16 is connected to the telemetry / command modulator / demodulator 18.

Further, the telemetry / command modulator / demodulator 16
The orbit / attitude control unit 19 is connected to the command signal output end of the, and the propulsion unit 15 is connected to the orbit / attitude control unit 19. Then, the telemetry / command modulator / demodulator 1
When a command command is input through the transmission / reception antenna 16, the command demodulator 8 demodulates the command command and outputs the command command to the signal processing control unit 17 and the orbit / attitude control unit 19, and the image data is output from the signal processing control unit 17. Is input, it is modulated and output to the transmitting / receiving antenna 16 for transmission.

In the above structure, the spacecraft body 10 is provided with a mooring portion (not shown), and normally, the mooring portion (not shown) is coupled to a space station such as a space station and moored to selectively. The mooring is released and the flight is released. Then, the command command is transmitted / received by the antenna 16
Is input to the orbit / attitude control unit 19 via the telemetry / command modulator / demodulator 18, and the propulsion unit 15 is driven. Here, the spacecraft body 10 flies in space by the propulsive force of the propulsion device 15 while its attitude is controlled, and approaches the observed structure, for example, the target spacecraft.

As a procedure of this photographing, for example, the main body 10 of the spacecraft temporarily stops after passing the target spacecraft, and the drive control units 14a and 14b of the target spacecraft 10 passing through the platform are used. 12a, 12b are driven to align the illuminators 13a, 13b and the imaging cameras 11a, 11b with the imaging position, and the illuminators 13a, 13b intermittently irradiate spot illumination light with the imaging cameras 11a, 11b.
Shoot from various directions with b.

The video signals acquired by the image pickup cameras 11a and 11b are input to the signal processing control unit 17. The signal processing control unit 17 performs signal processing on the video signal to generate image data, and outputs the image data to the telemetry / command modulator / demodulator 18. The telemetry / command modulator / demodulator 18 modulates the input image data and outputs it to the transmitting / receiving antenna 16.
The transmitting / receiving antenna 16 is, for example, pointing-controlled to the above-mentioned space station and transmits image data toward this space station. The space station monitors the received image data and observes the image data to determine, for example, the failure status of the imaged part of the target spacecraft.

As described above, in the spacecraft, the plurality of imaging cameras 11a and 11b and the illuminators 13a and 13b are mounted on the body 10 of the spacecraft which can freely fly in outer space, and propelled by the propulsion unit 15. A force is generated to approach the target spacecraft, and the imaging position of the target spacecraft is set to the illuminator 13
a, 13b to selectively irradiate the spot illumination light, the image pickup cameras 11a, 11b shoot the image signal, and the signal processing control unit 17 signal-processes the video signal to obtain image data as an external image observation unit such as a space station. Configured to send to. According to this, in the external image observation unit that received the image data,
It is possible to determine the situation of each part of the target spacecraft based on the image data, and for example, it is possible to take quick countermeasures for the failed part.

Incidentally, in the above embodiment, the illuminators 13a, 1a
Although 3b has been described as having the flash function of intermittently irradiating the spot illumination light, the configuration is not limited to this, and the spot illumination light may be continuously irradiated.

Further, in the above embodiment, the image pickup camera 11
Although the case where two units are used as a and 11b has been described, the present invention is not limited to this. Not limited to this number, 2
A more effective effect can be expected by configuring with more than one unit. Therefore, it is needless to say that the present invention is not limited to the above-described embodiment, and that various modifications can be made without departing from the scope of the present invention.

[0020]

As described above in detail, according to the present invention, it is possible to realize a reliable diagnosis of a failure point with a simple structure and to contribute to simplification of maintenance and inspection work. Spacecraft can be provided.

[Brief description of drawings]

FIG. 1 is a diagram showing an outer appearance of a spacecraft according to an embodiment of the present invention.

FIG. 2 is a diagram showing a detailed configuration of FIG.

[Explanation of symbols]

 10 ... Spacecraft body. 11a, 11b ... Imaging cameras. 12a, 12b ... pan head. 13a, 13b ... Illuminator. 14a, 14b ... Drive control unit. 15 ... Propulsion machine. 16 ... Transmission antenna. 17 ... Signal processing control unit. 18 ... Telemetry / command modulator / demodulator. 19 ... Orbit / attitude control unit.

Claims (3)

[Claims] 1. A combination of a propulsion unit that generates a propulsive force that flies in an arbitrary altitude and orbit of outer space and a plurality of image-capturing cameras whose direction can be adjusted,
Imaging means for photographing the target space navigation body with the imaging camera, spot illuminating means for irradiating the photographing position of the target space navigation body with the imaging camera of the imaging means with spot light, an imaging camera for the imaging means, Driving means for directing the spot illuminating means so that it can be photographed toward the target spacecraft, signal processing means for signal-processing the video signal acquired by the imaging camera of the imaging means to generate image data, and this signal processing A spacecraft comprising a data transmission unit for transmitting the image data generated by the unit to an external image observation unit. 2. The spacecraft according to claim 1, wherein the spot illuminating means has a flash function for intermittently illuminating and illuminating an image pickup position of the target spacecraft with spot light. 3. A mooring portion is further provided, and the spacecraft is moored to another spacecraft via the mooring portion, and in a state where the mooring is released, the propulsion means flies into outer space. The spacecraft according to 1 or 2.