JPS6216160Y2 - - Google Patents

Description

[Detailed Description of the Invention] This invention relates to an artificial satellite having a function of controlling the temperature inside the satellite by equipping the artificial satellite with a solar control board.

Conventional satellites often have a cylindrical shape, and in order to stabilize their attitude, the entire satellite is spun and operated in orbit. Next, conventional temperature control of an artificial satellite will be explained using diagrams.

Figure 1 shows a conceptual diagram of a conventional artificial satellite being illuminated by sunlight while in orbit. 2 represents the surface of the satellite structure in a state where sunlight is not irradiated, 3 represents the sun, 4 represents the earth, and 5 represents sunlight.

In this case, the temperature inside the satellite structure is determined by the total amount of heat generated by the electronic equipment installed inside the satellite structure, heat conduction from the surface of the satellite structure due to sunlight irradiation, and heat radiated from the satellite structure into space. There are two types of temperature control inside the satellite structure: passive heat control using paint, heat shielding materials, etc., and active heat control using heaters and louvers.In the case of active heat control, temperature data sent from the satellite is used. The received temperature data is received by the ground station, and the ground station sends a command signal to the satellite so that the temperature falls within the allowable temperature range, and sets the heater, louver, etc. control is in place. However, neither passive nor active thermal control has the concept of directly controlling sunlight, which is the largest source of heat input to satellites.

Conventionally, heat control has had the disadvantage of imposing structural, weight, mass, and power burdens on the interior and surface of the satellite itself.

This idea is a means to reduce the load on the internal surface of the satellite by installing a sunlight control plate on the outside of the satellite structure that can control the direction at any angle with respect to the sun, and to arbitrarily control the temperature inside the satellite structure. It provides:

An embodiment of this invention shown in FIGS. 2, 3, 4, and 5 below will be described.

FIG. 2 shows a conceptual diagram of a satellite equipped with a solar control plate having a solar shielding and reflecting function according to this invention, in which sunlight is irradiated.
In FIG. 2, S denotes the satellite body 6, which is a solar control plate; 7 denotes a despin motor mechanism for controlling the solar control plate 6 at an arbitrary angle with respect to the direction of the sun so that the temperature inside the satellite is within the allowable temperature range; 8 denotes the despin motor mechanism 7 for controlling the solar control plate 6;
A support rod for supporting the despin motor mechanism 7 is provided, a balance weight 9 is provided for maintaining mechanical balance around the rotation axis of the despin motor mechanism 7, and a solar control plate 6 is provided,
This is a solar sensor that detects the satellite's spin rate and solar direction so that the satellite can be pointed at any angle relative to the solar direction.

Figure 3 shows the satellite main body S and the despin motor mechanism 7.
This view shows the state in which the sunlight control plate 6 is blocking sunlight that is irradiated onto the outer surface of the satellite.

FIG. 4 shows an embodiment in which the sunlight control plate 6 reflects sunlight and irradiates it onto the outer surface of the satellite.

FIG. 5 is a system diagram of a device that controls the sunlight control board 6 to a position where sunlight is shielded and reflected. It has a circuit 11 and a despin motor mechanism 7.

This despin control electronic circuit 11 compares an electric signal corresponding to temperature data inside the artificial satellite with a preset electric signal corresponding to an allowable temperature range, and outputs an electric signal depending on the difference between these two signals to the solar sensor 10. A control signal is outputted to the despin motor mechanism 7 as to how many positions the sunlight control board 6 should be directed in the direction of the sun using an electrical signal corresponding to the direction of the sun.

The operation for controlling the direction of the sunlight control plate 6 having sunlight shielding and reflecting plate functions to an arbitrary position will be described. 3 and 4, one pulse signal is input from the sun sensor 10 to the despin control electronic circuit for each rotation of the satellite, and the period of the pulse signal is used as the spin rate of the satellite, and the pulse width is used as the sun direction with respect to the satellite. Detected. For example, in FIG. 3, when the temperature data inside the satellite is lower than the allowable temperature range, the despin motor mechanism 7 is directed toward the sun by a control signal from the despin control electronic circuit 11 regarding how many positions to direct toward the sun. By rotating the light control plate 6 to a position relative to the sun as shown in FIG. 4 and increasing the amount of sunlight irradiated onto the satellite, the temperature inside the satellite is controlled within an allowable temperature range. In this case, the angle of the sunlight control board 6 with respect to the sun direction depends on the difference between the electrical signal corresponding to the temperature data inside the satellite and the preset electrical signal corresponding to the allowable temperature range. The temperature is controlled within the permissible temperature range.

This idea uses a solar control board to control the amount of sunlight irradiated onto the satellite, making it possible to arbitrarily control the temperature inside the satellite, making it possible to perform strict thermal design like conventional satellites. no longer needed,
We can provide low-cost artificial satellites.

Although the above embodiments have been described with respect to spin-stabilized satellites, the solar control board according to the present invention can be used not only for spin-stabilized satellites but also for all types of artificial satellites.

[Brief explanation of drawings]

Figure 1 is a conceptual diagram showing sunlight irradiating the surface of the satellite's structure, Figure 2 is a conceptual diagram showing one implementation of the artificial satellite of this invention, and Figures 3 and 4 are shown in Figure 2. FIG. 5 is a system diagram for directing the sunlight control plate 6 shown in FIGS. 2, 3, and 4 to a position where sunlight is shielded or reflected. be. In the figure, S is the satellite body, 3 is the sun, 4 is the earth,
5 is sunlight, 6 is solar control board, 7 is despin motor mechanism, 8 is support rod, 9 is balance weight,
10 is a solar sensor, and 11 is a despin control electronic circuit. It should be noted that the same or corresponding parts in the drawings are designated by the same reference numerals.

Claims (1)

[Scope of utility model registration request] A solar control board that has a function of shielding and reflecting sunlight and is directional controlled at an arbitrary angle with respect to the direction of the sun, a solar sensor, and the solar control board based on the output of this solar sensor. The satellite is equipped with a means for controlling the direction at an arbitrary angle with respect to the direction of the sun, and is configured to adjust the amount of sunlight irradiated onto the outer surface of the artificial satellite using the sunlight control board, and to control the temperature inside the satellite. An artificial satellite characterized by: