JPH0121040B2 - - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to triple spin satellites having deployable solar panels, and in particular, to making the envelope solar panels of conventional spin satellites deployable and sun-oriented, thereby generating large amounts of electrical power. The present invention relates to a triple-spin satellite that has a thermally stable radiation zone.

A conventional spin satellite, as shown in FIG. 1, is composed of a spinning solar panel 3, an antenna 1 pointing toward the earth, and a despan section 2 that supports the antenna. However, in this type of satellite, the solar panel 3 spins, so the solar cells attached to the panel cannot operate efficiently all the time, and electricity is generated only from the portion where sunlight is projected. It was unsuitable for handling large amounts of electricity. In addition, since thermal control is performed using the solar panel surface, during a solar eclipse without sunlight, the temperature of the solar panel surface drops significantly, complicating the thermal control of the on-board equipment in the satellite.

In order to eliminate the above-mentioned drawbacks, a structure is known in which double solar cell panels 3 and 4 are provided as shown in FIG. 2, and the outer panel 4 extends downward. Because the satellite spins as shown in Figure 1, the power generation efficiency of the solar cells is poor, and the amount of power generated is small compared to the larger size of the satellite. Also, as in Figure 1, the satellite's heat is controlled by the solar panel surface 3 and the radiation zone 5, so the temperature of the solar panel and the radiation zone decreases significantly during a solar eclipse when there is no sunlight, and the heat of the equipment onboard the satellite decreases significantly. This made control complicated.

FIG. 3 is an example of a spin satellite that eliminates the above-mentioned power disadvantage. In addition to the solar panel 3 on the satellite envelope, there is also a sun-oriented deployable solar array paddle 7.
It is equipped with the following. In this type of satellite, the satellite main body consisting of a solar panel 3 and a radiation zone 5 spins, the antenna section consisting of an antenna 1 and a despan section 2 despans and points towards the earth, and the solar cell paddle sections 6 and 7 spin. It is a triple spin type that despans and points toward the sun. By having the satellite with a deployable paddle, a spinning satellite that can obtain high power is realized. However, similar to the above, the satellite's thermal control is carried out by the solar panel 3.
Since the solar eclipse is carried out in the radiation zone 5, heat control during a solar eclipse when no sunlight is incident is complicated. Furthermore, since the solar battery paddle 7 has a rectangular shape in contrast to the cylindrical shape of the satellite, mounting efficiency in the rocket fairing at the time of satellite launch is poor, and it is not suitable for increasing the size of the satellite body.

The present invention addresses the inefficiency of power generation, that is, the inability to obtain large amounts of power, of the spin satellites of the type shown in FIGS. The complexity of heat control during solar eclipses on spin-type satellites and the inefficiency of implementation when mounted inside the rocket fairing have been eliminated, and the solar panel attached to the satellite body has been made deployable and solar pointing control type. The purpose is to provide a triple spin satellite.

In the triple spin satellite according to the present invention, the deployable solar panel of the spin satellite is constructed by connecting a plurality of rectangular panels with hinges in one direction, and when the panel is not deployed, the solar panel covers the entire side surface of the satellite body. It has a deployable structure that opens and closes on hinges so that when the panel is deployed, it has a large elongated rectangular shape as a whole, and it is of a sun pointing control type, and when the panel is deployed, the deployable solar panel is attached to the satellite main body. One rectangular panel portion of the solar cell panel is attached to the satellite despan section via a support rod so as to block sunlight from entering the solar cell panel.

DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, the present invention will be described in detail with reference to embodiments with reference to the drawings.

FIG. 4 is an embodiment of the present invention, and shows the state of the solar cell panel when it is expanded. 1 is an earth-oriented antenna, 2 is a despan part that supports the antenna, 5 is a radiation zone, and 8 is a deployable solar cell panel. In this way, the solar panel attached to the satellite body expands and points towards the sun, making it possible to obtain a large amount of power (approximately three times that of a satellite of the same shape) that could not be obtained with conventional spin satellites. Furthermore, since the deployed solar panel 8 blocks sunlight from entering the satellite main body, a stable radiation zone can be obtained regardless of sunlight or eclipse, making it easier to control the satellite's heat.

FIG. 5 is a longitudinal section of a satellite according to the present invention, and 6
is a satellite despan section that supports the deployable solar panel 8.

FIG. 6 shows the state of the expandable solar cell panel before it is expanded. There are transfer orbits and drift orbits between satellite launch and geostationary orbit. In the two orbits,
The satellite is in the state shown in Figure 6. In the transfer and drift orbits, the internal heat generation of the satellite is small, and the satellite tends to become cooler.
This has the advantage of preventing the satellite from becoming too cold. FIG. 7 is a view of FIG. 6 from below, with reference numeral 12 the hinge and expansion mechanism between each rectangular panel of the solar cell panel, 9 the lower thermal barrier, and 10 the support for the solar cell panel 8 and the despan section 6. Rod, 11 is AKM (Apogee Kitsuku Motor)
Showing the nozzle. When the solar battery panel is deployed, the solar battery panel is deployed in the A direction in the same figure, and the fourth
It will be in the state shown in the figure.

As explained above, in the present invention, the solar cell panel attached to the main body of the spin-type satellite is of an expandable type, and solar pointing control is performed, thereby providing the following advantages.

(b) Approximately three times more power can be obtained compared to conventional spin satellites of the same shape.

(b) Since the deployable solar panel blocks sunlight from entering the satellite body, a stable radiation area for satellite heat control can be obtained regardless of sunlight or shade.

(c) Since the deployable solar panel before being deployed has a polygonal column shape, it is efficient to mount inside the rocket fairing.

(iv) During launch, the heat generation inside the satellite is small.Due to the deployable solar panel covering the radiation zone, the temperature of the satellite can be prevented.

[Brief explanation of drawings]

Figure 1 is a schematic perspective view of a conventional dual-spin satellite, Figure 2 is a perspective view of a dual-spin satellite with dual solar panels, Figure 3 is a perspective view of a triple-spin satellite with deployable solar array paddles, FIG. 4 is a perspective view of a triple spin satellite with a deployable solar panel according to an embodiment of the present invention, and FIG.
FIG. 6 is a vertical cross-sectional view of the triple spin satellite shown in the figure, FIG. 6 is an external perspective view showing the state of the deployable solar cell panel before deployment, and FIG. 7 is an enlarged bottom view with a portion of FIG. 6 cut away. DESCRIPTION OF SYMBOLS 1...Earth-oriented antenna, 2...Antenna support despan section, 3...Solar battery panel, 4...Solar battery panel extending downward, 5...Radiating zone, 6
... Satellite despan section, 7 ... Deployable solar battery paddle, 8 ... Deployable solar battery panel, 9 ... Lower thermal barrier, 10 ... Support rod, 11 ... AKM
(Apogee kick motor) nozzle, 12...hinge and deployment mechanism.

Claims (1)

[Claims] 1. The deployable solar panel of a spin-type satellite is constructed by connecting multiple rectangular panels with hinges in one direction, and when the panel is not deployed, the solar battery panel covers the entire side of the satellite body, and when the panel is deployed. has a deployable structure that opens and closes on hinges so that it has a large elongated rectangular shape as a whole, and is of a solar orientation control type, and when the panel is deployed, the deployable solar panel blocks sunlight from entering the satellite body. A triple spin satellite having an elongated deployable solar cell panel, characterized in that one rectangular panel portion of the solar cell panel is attached to a satellite despan section via a support rod.