JPH0237100A - Meteorite preventive device for space structure - Google Patents

Abstract

PURPOSE:To obtain a meteorite preventive device with an effective preventing function from space meteorite and space dust by disposing a multilayer insulating material in contact with the outer surface of a pressurized wall and further disposing an inner prevent board and an outer prevent board with a space outside the multilayer insulating material. CONSTITUTION:Space meteorites and space dust collided against an outer preventive board 1 are shattered or dissolved at the moment of a collision and directed toward an inner preventive board expanding. In this case, a part of the outer preventive board 1 is melted and directed toward the inner preventive board 2. The space meteorites, space dust, and splinters and melted particles of the outer preventive board are expanded in the space between both these preventive boards 1, 2 before reaching the inner preventive board 2, dispersed comparatively in a wide area and collided. As a result, the collision energy per unit area becomes extremely small, and most collided objects are inhibited to penetrate through the inner preventive board 2. In case the collided objects are penetrated through the inner preventive board 2, their penetration is inhibited at the time of collision against a multilayer insulating material 3 fitted in contact with the outer surface of a space base pressurized part.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a device for protecting structures in outer space, such as space bases, from damage caused by collisions with space meteorites and space dust.

[Prior Art] Conventionally, meteorite protection plates and heat insulating materials for structures in outer space have been independently designed and manufactured for the purposes of meteorite protection and heat insulation, respectively.

That is, for example, as shown in FIG. 2, a local heat insulating material 06 is attached to the outer end of a spacer 05 fixed to the outer wall 04 of the pressurized part of the Space Station with screws, etc., and the heat insulating material 03 is glued to the inside of the spacer 05. The protection plate 01 was attached to the spacer 05 with the local heat insulating material 06 interposed therebetween using screws or the like.

[Problems to be Solved by the Invention] The above-mentioned conventional device protects large structures in outer space, such as space bases, for long periods of time using wedge-structured protection plates. The thickness of the plate that protects it from space dust has become thicker (the thickness of the meteorite protection plate O1 shown in Figure 2 is usually about 10 to 20 mm thick), and its weight has become excessive. (This makes it difficult to launch into orbit by a rocket, space shuttle, etc.)

The present invention aims to provide a defense device for outer space structures that is lightweight and has an effective protection function from space rocks and space dust.

[Means for Solving t1 Problem I] The meteorite protection device for a space structure according to the present invention includes a heat insulating material disposed in contact with the outer surface of a preloaded part of the structure, and a space provided on the outside of the multilayer heat insulating material. and an outer defense plate disposed at intervals outside the inner defense plate.

[Operation] Since the present invention is constructed and implemented as described above, when space dust collides with the outer protection plate, it is crushed or melted when it penetrates the outer protection plate, and some of the pieces of the outer protection plate are broken. At the same time, it spreads radially and reaches the surface of the inner defense plate. For this reason, the collision energy per unit area against the surface of the inner protection plate becomes small, and penetration is prevented.

In addition, at the corner of space, where the initial impact energy is large and even penetrates the inner shield plate, space dust is crushed or melted again and diffused, becoming low impact energy and reaching the surface of the insulation material, where it is blocked.

In the present invention, as described above, the defense plates are configured in double layers with intervals, and at the same time as they are crushed or melted at the outer defense plate, they spread toward the inner defense plate, and the first outer defense plate Collision with the inner defense plate is distributed over a much wider area than the cross-sectional area of the section 5 that collides with the plate.
Become. Therefore, the total thickness of the outer and inner defense plates required to block the same collision object can be made thinner than in the case of - two defense plates, and the weight can be reduced.

Furthermore, because the insulation provided at a distance from the inner protection plate is in contact with the pressurized outer wall of the structure, the impact is distributed over a wider area, and the energy [fl] due to the multilayer insulation is Therefore, defense can be carried out efficiently.

[Example] An embodiment of the present invention will be described with reference to FIG.

The pressurized part 4 of the space station is provided with a spacer 5 attached by screws, grips, etc., and a spacer 5° formed on the pressurized part 4.

A multilayer heat insulating material 3 having a thickness of about 8 g++s is attached to the outer surface of the pressurized part 4 by an adhesive or a band, and its side ends are in contact with the side surfaces of the spacers 5 and 5 degrees. The inner defense plate 2 and the spacer 7 having a thickness of about 21 mm are attached to the tip of the spacer 5.5'' with a local heat insulating material 6 interposed therebetween using screws, grips, etc. There is a gap (for example 60e) between the inner protection plate 2 and the multilayer insulation material 3.
u+) is provided. At the tip of the spacer 7, an outer protective plate 1 with a thickness of about 2 mm is attached using screws, grips, etc.
is attached, and a gap (for example, 60ea+) is provided between the outer protection plate 1 and the inner protection plate 2. Aluminum alloy A2024 is used as the inner and outer protective plates, and a combination of aluminum vapor-deposited Kapton and polyester net is used as the multilayer insulation material. Also spacers 5 and 7
Aluminum alloy A7075 is used as the material, and polyimide is used as the local heat insulating material.

Since the present embodiment is configured as described above, the cosmic corner surface and cosmic dust that collide with the outer protection plate 1 at a relative speed of several Km/sec to several tens of Km/sec are crushed or dissolved upon impact and spread inside. Head towards defense board 2.

At this time, a part of the outer protection plate also becomes fragmented or melted and moves towards the inner protection plate 2.

The above-mentioned space corners, space dust, fragments of the outer defense vi1, and molten particles spread in the interval between the two protection plates until reaching the inner protection plate 2, and are dispersed and collided over a relatively wide area of the inner protection plate 2. The collision energy per unit area of a collision with the inner protection plate 2 is significantly smaller than that of a collision with the outer protection plate 1, so most of the colliding objects cannot penetrate the inner protection plate 2 and are stopped here. .

Cosmological term 5, where the initial collision energy is particularly large, in the case of a collision of cosmic dust, it may penetrate the inner protection plate 2, but in this case as well, the second collision with and penetration of the protection plate generates even more energy. Because of this, when it collides with the multilayer insulation material 3 attached to the outer surface of the pressurized part of the space station, it cannot penetrate through it and is blocked. In addition, the impact of the collision at this time is absorbed by the multilayer insulation material 3. The collision energy transmitted to the pressurized part 4 is reduced.

As described above, in this embodiment, the outer protection plate 1, the inner protection plate 2, and the multilayer insulation material 3 provided in contact with the outer surface of the pressurized chamber 4, which are provided at intervals from each other, are used to protect against impact objects such as meteorites. By sequentially decreasing the collision energy and increasing the collision area, the space base pressurized chamber can be protected from corners and the like.

In addition, an impact object such as a stone that collides with the outer protection plate 1 will break or melt and spread when it passes through the outer protection plate 1 and head toward the inner protection plate 2, so that it will not collide with the inner protection plate 2. The area becomes much larger than the cross-sectional area of the collision object, which is the original collision area with the outer protection plate 1. Therefore, the total thickness of the outer protection plate 1 and the inner protection plate 2 for blocking the same collision object is thinner than in the case of - number of protection plates, and the weight can be reduced.

In the present invention, the following materials can be used in addition to the materials shown in the above embodiments.

Inner and outer protective materials: Multilayer insulation materials such as aluminum alloys such as ^2219 and 2290, and composite materials such as carbon fiber wefts, boron fibers, and glass fibers: Kapton, Mylar, polyimide,
Silica, aluminosilicate, etc. [Effects of the invention] The present invention provides outer defense plates arranged at intervals,
Many Jlls that come into contact with the inner defense plate and the outer surface of the pressurized chamber! Since 7 is equipped with a heat material, it is possible to protect the space structure by dispersing the collision energy of colliding objects such as limited stones, and it is also possible to reduce the total thickness of the defense plate, resulting in weight reduction. can be measured.

[Brief explanation of the drawing]

FIG. 1 shows a cross-sectional view of one embodiment of the invention. FIG. 2 is a sectional view of a conventional example. 1...Outer defense plate 2...Inner defense plate 3...
・Multilayer insulation material 4... Space base pressurized section wall 5.5
°...Spacer 6...Local cross section material 7...Spacer

Claims (1)

[Claims] A thermal insulation material placed in contact with the outer surface of the preloaded wall of the structure, an inner defense plate placed at intervals on the outside of the multilayer insulation material,
and a meteorite protection device for a space structure, comprising: an outer defense plate disposed at intervals on the outside of the inner protection plate.