JPS6022599A - Double spin satellite - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a dual spin satellite, and more particularly to an improvement in the structure of a dual spin satellite equipped with a large antenna with a large diameter.

Conventionally, in a double spin satellite equipped with a large antenna with a large diameter, each -
As shown in the side view and front view of the external appearance in the example space, the despanning platform section 2 is attached to the base of the satellite main body formed by the spin section 1 and the despanning platform section 2. A predetermined support structure 5
and 6, the predetermined large-diameter reflector 3 and the primary radiator 4 are set at predetermined corresponding positions, and the desired radiation beam characteristics are set in accordance with the original mission of the double spin satellite. generated. In this case, in conventional double-spin satellites, on the side of the satellite body opposite to the side on which the aboji kick motor or periji aboji kick motor is attached,
It is common to extend the support structures 5 and 6 to set up the large diameter reflector 3 and the primary radiator 4. When launching a conventional double-spin space shuttle or the like, the large-diameter reflector 3 and primary radiator 4 are Then, the support structures 5 and 6 are folded so that they are located at the positions shown as (3) and (4), and the perige kick motor (7) is attached to the satellite body. It is attached to the spin section 1 side of the spindle.

In this way, the large diameter reflector 3 and the primary radiator 4 are configured on the opposite side with respect to the satellite body from the perige aboge kick motor (7), and therefore the support structures 5 and 6 are arranged on the opposite side with respect to the satellite body. In the folded state, i.e. the configuration at the launch stage of the satellite, the satellite has a spin part 1,
Despan platform section 2, large diameter reflector (3), -
The center of gravity of the entire satellite is also located on the side of the despan platform 2. The moment balance of the spin axis 101 times as a whole is likely to become unbalanced. As a result, in the perige kick and aboge kick events at the time of satellite launch, various problems including deterioration of the accuracy of the injection orbit are caused in the orbit insertion operations for the predetermined transition orbit and the predetermined geostationary orbit, respectively. be.

In general, the despan platform section 2 constitutes the main part of the satellite body, with various mission equipment directly related to the mission operation of the satellite housed inside it or mounted externally. Even in the case of the conventional dual-SPIS satellite shown in the figure, the outer surface of the despan platform section 2 is equipped with a large antenna consisting of a large-diameter reflector 3 and a primary radiator 4, as well as an antenna related to the missillon. In many cases, various antenna systems and the like are additionally installed.

However, in conventional dual-spin satellites, the large-diameter reflector 3 and the primary radiator 4 are located on the despan platform 2 on the side opposite to the mounting side of the Perige-Avoji kick motor (7), as described above. In order to install various antenna systems related to the microphone 1 on the despan platform 2 during both the satellite launch and the satellite operation stages, the structural interface or electromagnetic wave There are also disadvantages in that various constraint problems related to interference and the like occur.

The object of the present invention is to eliminate the above-mentioned drawbacks and to provide a large antenna including a large-diameter reflector on the mounting side of an apogee kick motor or a perige aboge kick motor. The object of the present invention is to provide a double spin satellite equipped with a large antenna that can improve attitude stability during mission operations.

The double-spin satellite of the present invention is a double-spin satellite formed by a death-bump double-home part and a spin part, in which the double-spin satellite is used as a base to store the double-spin satellite in a predetermined manner when the double-spin satellite is launched. After the double-spin satellite is launched, it is folded into a predetermined support structure that is extended to the side where the aboji kick motor or the periji aboji kick motor of the satellite body is attached in space. The antenna is configured to include at least one large antenna with a large diameter.

Hereinafter, the present invention will be explained in detail with reference to the drawings.

FIGS. 2(a) and 2(b) are external views of the main parts of an embodiment of the present invention in space, shown as a side view and a front view, respectively. Figure 2 (a) and (
As shown in b), the main parts of the dual spin satellite of the present invention are the main part, the spin part 8, and the despan platform part 9.
．． Large diameter reflector 10, -order radiator 11, support structure 12
In addition, in the state at the time of launch, the large-diameter reflector 10 and the primary radiator 11 are folded through a predetermined folding mechanism related to the support structures 12 and 13, as shown by the broken line. A perigee apogee kick motor (14) is installed on the spin section 8 side.

In FIG. 2(a), in order to launch a double-spin satellite equipped with the large antenna of the present invention into a geostationary orbit by, for example, the space shuttle, it is necessary to The reflector 10 and the primary radiator 11 are housed and ejected into space according to a predetermined procedure. In this case, the main difference from the conventional dual spin satellite shown in FIG. On the side of (14), each large-diameter reflector (10
) and -order radiator (11). For this reason, compared to the case of a conventional double spin satellite equipped with a large antenna, the spin part 8, despan platform part 9, large diameter reflector (10) and -order radiator at the stage of launching into space The center of gravity of the satellite body formed by (Step 1) will be closer to the perigee or aboge motor.

Therefore, as in the case of conventional dual-spin satellites, the perige
In each kick and aboji fist kick event,
The attitude of the satellite with respect to the spin axis 102 does not become unstable, and the attitude is always maintained stably. In other words, the insertion of the satellite itself into the transition orbit and geostationary orbit,
It is carried out under the prescribed normal control, and in the expected manner,
It becomes possible to set the satellite at a predetermined position on the geostationary orbit.

Moreover, even in the predetermined mission operation stage after setting a predetermined position on the geostationary orbit, as is clear from FIG. 2(a), the spin section 8. Despan platform section 9, large diameter reflector 10. - secondary radiator 11, support structure 12 and 1;
The moment balance of the spin axis 102 of the main part of the dual spin satellite, which is formed by 3, is because the length along the spin axis 102 of the spin part 8 covered with the solar cell panel is relatively long. Despite this, Figure 1 (
Compared to the conventional double spin satellite shown in a), it is less likely to become unbalanced. As a result, a relatively small amount of fuel is required for station-keeping operations to maintain the attitude and orbital position of the satellite, and as a result, the life of the satellite is extended. Furthermore, as mentioned above,
Even when a predetermined missimin device including an antenna or the like is mounted outside the despan Blatt-Bohm section 9, the large-diameter reflector 10 and the primary radiator 11 are designed for the mounting and operation of the missimin device. , does not cause any hindrance.

In the above explanation, the case where the large antenna installed on the dual spin satellite is formed by - large-diameter reflectors and one primary radiator was explained, but in general, it is formed by multiple reflectors and one primary radiator. It goes without saying that the invention also applies to dual spin satellites equipped with multiple large antennas, including multiple primary radiators. In addition, when the primary radiator forming the large antenna includes a predetermined high-frequency device such as a transponder, a predetermined heat sink is attached to the housing case of the high-frequency device so as to align with the equatorial plane, and Corresponding to cases where a large-diameter reflector is equipped with a movable adjustment mechanism for adjusting the radiation beam azimuth angle.
The present invention is also applicable to double spin satellites equipped with large antennas. Furthermore, it goes without saying that the present invention is also applicable to double spin satellites in which the large antenna is formed using an array method, a radio wave lens method, or the like.

As described above in detail, the present invention provides a double spin satellite equipped with a large antenna, in which the large antenna is extended toward the spin section side where the aboji kick motor or the periji apogee kick motor is installed. By configuring the structure via a predetermined support structure, the attitude stability of the satellite is improved during satellite launch and during on-orbit mission operation, and the structure between the large antenna and predetermined mission equipment, etc. is improved. This has the effect of eliminating various obstacles related to mechanical and electrical interfaces.

[Brief explanation of drawings]

FIG. 1 is an external view showing the main parts of a conventional double spin satellite equipped with a large antenna, and FIG. 2 is an external view showing the main parts of an embodiment of the present invention. In the figure, 1.8...spin ms 2. 'i... Despan Platform Department, 3. (3), 10. (10)・−・・−・
Large diameter reflector, 4. (4), 11. (il)...
...-Next radiator, 5, 6, 12° 13... Support structure, (7), (14)... Periji aboji kick motor. (17) Iku l Figure l Z diagram and b no 561-

Claims (1)

[Scope of Claims] (1) In a double-spin satellite formed by two deathbump platforms and a spin part, the despan platform part is used as a base to store the double-spin satellite in a predetermined manner when the double-spin satellite is launched. After the double-spin satellite is launched, it is configured via a predetermined support structure that is extended to the side where the aboji kick motor or the periji aboge motor of the satellite body is attached in space. be done,
A double spin satellite characterized by having at least one large antenna with a large diameter. (2) the large antenna includes at least one large-diameter reflector attached to each of a pair of support structures extending from corresponding sides of the despan platform; (3) The large antenna includes at least one large-diameter reflector attached to each of the pair of support structures extending from corresponding opposite sides of the two-deathbump home portion; A dual spin satellite according to claim 1, characterized in that it is formed in combination with at least one primary radiator containing a corresponding predetermined radio frequency device. (4) A predetermined double spin satellite is mounted on the predetermined high-frequency equipment accommodation case. (5) Claims (2), (3), or (4), characterized in that the large-diameter reflecting mirror is provided with a movable adjustment mechanism for adjusting the azimuth angle of one radiation beam. Dual spin satellite described.