JPH08164899A - Plural artificial satellite mounting mechanism - Google Patents

Abstract

PURPOSE: To realize input of a member to partition a lower side satellite and an upper side satellite to an orbit of a plural number of the artificial satellites without abandoning an adapter by providing a device to connect it to a member to store the lower side satellite through a hinge and to actuate the partition member to open. CONSTITUTION: A first artificial satellite 4 to be separated first is loaded on the upper side and a second artificial satellite 5 is loaded on the lower side on a rocket placed with its forward direction directed upward. Thereafter, an adapter 7A which is a member to partition the first artificial satellite 4 and the second artificial satellite 5 is connected to a lower part fairing 8 which is a member to store the second artificial satellite 5 through a hinge 1, and a device to actuate the adapter 7A to open is provided. Consequently, as the adapter 7A is not separated and abandoned and does not become space dust, it does not damage instruments such as the artificial satellites on their orbit.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a mechanism for mounting a plurality of artificial satellites used when mounting and storing a plurality of artificial satellites on a rocket.

[0002]

2. Description of the Related Art FIG. 4 is a perspective view of a conventional multi-satellite mounting mechanism in a rocket that launches a plurality of artificial satellites at one time. In the figure, 4 is a first satellite to be separated first, 5 is a second satellite to be separated second, 6 is an upper fairing covering the first satellite, 8 is a lower fairing surrounding the side surface of the second satellite. , 7X are adapters which are provided at the upper end of the lower fairing, act as a lid for covering the upper surface of the second satellite, and serve as a mounting base for the first satellite.

The upper fairing is separated and falls before the rocket enters the satellite orbit. After the rocket enters the satellite orbit, the first satellite 4, the adapter 7X, and the second satellite 5 are sequentially separated and projected. FIG. 5 shows the order of the above-mentioned detachment, and the rocket detaches the satellite and the adapter while changing the attitude in the order of (1) to (12).

[0004]

The adapter, which is abandoned when a plurality of artificial satellites are put into orbit, stays in the operational orbit area of the artificial satellite and is damaged by the closest approach or collision to the artificial satellite. It becomes space garbage that gives.

The present invention intends to solve the above problems of conventional rockets and to provide an artificial satellite mounting mechanism that allows a plurality of artificial satellites to be put into orbit without abandoning the adapter. is there.

[0006]

DISCLOSURE OF THE INVENTION The present invention has been made to solve the above-mentioned problems, in which a rocket placed with its traveling direction facing upwards, a satellite which is separated first, is separated upward and a satellite which is separated later is separated. With the artificial satellite on the lower side, in a multiple artificial satellite mounting mechanism used when mounting, a member for partitioning the lower satellite and the upper satellite is coupled to a member for housing the lower satellite via a hinge, Further, the present invention relates to a mechanism for mounting a plurality of artificial satellites, which is provided with a device for opening the partition member.

[0007]

After the upper satellite is separated and projected, the device for opening the partition member is activated to open the partition member, and the lower satellite is separately projected. Since the partition member is not separated and discarded, it does not become space waste and does not damage artificial satellites in orbit.

[0008]

1 is a vertical sectional view of a multi-satellite mounting mechanism according to a first embodiment of the present invention. FIG. 1A is an initial sectional view and FIG. 1B is an adapter open state. FIG. In the figure (a), 10 is the final stage of the rocket, 8 is the lower fairing attached to the upper part, 5 is the second satellite accommodated in the lower fairing, and 7A is the upper part of the lower fairing. Installed adapter,
Reference numeral 1 is a hinge of an adapter mounting portion, 4 is a first satellite mounted on the upper portion of the adapter, and 6 is an upper fairing covering the first satellite. The parts other than the adapter 7A, the hinge 1 to which it is attached, and the parts related thereto are the same as in the prior art.

FIG. 2 is a cross-sectional view showing the structure of the hinge 1 of the above-mentioned embodiment and its vicinity, showing two types. Either type of (a) or (b) may be used. In the figure, (a) is the first type, and 1 is an adapter 7.
A hinge that rotatably attaches A to the lower fairing 8, 2 is an actuator, 3 is a roller provided at the tip of the rod of the actuator, and 11 is an adapter 7.
It is a guide attached to A. Actuator 2
When the roller 3 moves upward due to, the guide 11 is pushed up and the adapter 7A is opened. 9 is the lower fairing 8
When a rocket is launched, the adapter 7A is fixed to the lower fairing 8 by a separating bolt provided at a connecting portion between the adapter 7A and the adapter 7A. FIG. 2B shows the second type, and 12 is a link connecting the actuator 2 and the adapter 7A. This type is similar to the first type in that the link 12 is formed by the actuator 2.
Is pushed up, the adapter 7 connected to it
A opens.

In this embodiment, the upper fairing 6
After the rocket is separated and removed, when the rocket enters the satellite orbit,
First, the first satellite 4 is separated and projected, and then the adapter 7A is opened. After that, the second satellite is separated and projected. The adapter 7A is separated and not abandoned, and is connected to the lower fairing to the end.
It doesn't become space garbage like. Therefore, the adapter does not damage the satellite.
Incidentally, the uppermost stage of the rocket equipped with this separation mechanism is generally operated to change the orbit after the completion of the satellite loading,
Measures are taken to avoid becoming space trash.

FIG. 3 is a vertical sectional view of a multi-satellite mounting mechanism according to a second embodiment of the present invention. FIG. 3 (a) is a sectional view in an initial state, and FIG. 3 (b) is a sectional view in an adapter open state. It is a figure. In the figure, 7B is an adapter. The adapter 7B of the present embodiment is divided into a plurality of parts that are axially symmetric with respect to the rocket axis, and each has a structure that opens. The structure and operation of each part other than the above are the same as those of the first embodiment. The adapter 7B of the present embodiment has the advantage that the center of gravity of the machine does not deviate from the machine axis even when the adapter 7B is open, and the relative movement when the second satellite 5 is separately projected is correctly performed along the machine axis.

As described above, according to each of the above embodiments, since the adapter is hinged to the lower fairing, there is no structure abandoned due to the introduction of a plurality of satellites. It is effective in increasing the safety and reliability of space activities by eliminating the possibility of damaging other devices operating in orbit.

[0013]

In the multi-satellite mounting mechanism of the present invention, the member for partitioning the lower satellite and the upper satellite is joined to the member for housing the lower satellite via a hinge, and the partition member is used. Since the opening operation device is provided, the partition member is not separated and discarded, and it does not become space trash, so that it does not damage the artificial satellite or other equipment in orbit.

[Brief description of drawings]

FIG. 1 is a vertical cross-sectional view of a multi-satellite mounting mechanism according to a first embodiment of the present invention, in which (a) is a vertical cross-sectional view in an initial state,
(B) is a vertical cross-sectional view of the adapter in an opened state.

FIG. 2 is a cross-sectional view showing a hinge used in the above embodiment and a mechanism in the vicinity thereof.

FIG. 3 is a vertical cross-sectional view of a multi-satellite mounting mechanism according to a second embodiment of the present invention, in which (a) is a vertical cross-sectional view in an initial state,
(B) is a vertical cross-sectional view of the adapter in an opened state.

FIG. 4 is a perspective view of a conventional multi-satellite mounting mechanism.

FIG. 5 is an explanatory view of a conventional separation sequence of a plurality of artificial satellites.

[Explanation of symbols]

 1 Hinge 2 Actuator 3 Roller 4 First Satellite 5 Second Satellite 6 Upper Fairing 7A, 7B Adapter (Example) 7X Adapter (Conventional) 8 Lower Fairing 9 Separation Bolt 10 Rocket Top Stage 11 Guide 12 Link

Claims (1)

[Claims] 1. A plurality of artificial bodies used when mounting a rocket placed with its traveling direction upwards, with the artificial satellites separated first on the upper side and the artificial satellites separated later on the lower side. In the satellite mounting mechanism, there is provided a device for connecting a member for partitioning the lower satellite and the upper satellite to a member for housing the lower satellite via a hinge and for opening the partition member. Multi-satellite onboard mechanism.