RU2561888C2 - Space convertible module - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to inflatable deployed space structures, mainly, manned modules. Proposed module comprises stiff load-bearing compartment (1) composed of scalene prism with useful zone (2) of permanent volume. Multiplayer tight shell (3) is laid between inner surface (5) of cowl and compartment (1). Said shell contains anti-meteorite and radiation protection, heat insulation and outer load-bearing layer. Shell (3) is laid in each of four zones between wide prism faces and surface (5) as two symmetric S-like loops developed towards each other and packed by elements (4) over outer load-bearing layer.

EFFECT: increased dimensions of zone of vital activities of astronauts, better protection against radiation.

3 dwg

Description

The invention relates to space technology, namely to inflatable transformable space structures.

The creation and implementation of technology of transformable space inhabited modules is aimed primarily at solving the following problems:

- the need to significantly increase the usable volume of sealed modules in the Russian segment of the international space station (ISS) and advanced space stations in order to increase the comfort of long-term crew stay and create the necessary conditions for complex scientific and technological experiments;

- the feasibility of ensuring high overall dimensions of the design of the inhabited modules in the starting and operating positions to ensure the possibility of their removal by existing and promising launch vehicles. The increase in the size of the rigid modules of the space station is complicated by the fact that the space under the fairing is limited. In addition, the increase in the size of rigid modules is difficult due to problems with transportation by modern railway and air transport;

- the need to more effectively ensure acceptable levels of protection for space station crews from the effects of ionizing radiation in outer space;

- the need to increase the resistance of habitable compartments to the effects of meteoroids and particles of industrial debris compared to traditional hard compartments, given the increasing danger of collision with space debris in near-Earth orbits.

As a prototype of a space transformable module, inflatable modules developed by American companies can be considered, for example, in the NASA project for creating the TransHab inflatable residential module (Paul Zarchan. Gossamer Spasecraft: Membrane and Inflatable Structures Technology for Space Applications. 2001. C 527-529, 546 .).

The module design contains a rigid carrier compartment and a multilayer transformable shell deployed around it. The rigid TransHab carrier compartment is made in the form of a cylindrical structure of small diameter, which does not allow using it as a full-fledged working area of a crew of traditional sizes. The size of the central zone depends on the laying of the said sheath around it in the transport position, since the total volume for placing the module in the payload zone (ZPG) under the fairing is limited. Given the requirements for a multilayer transformable shell, and existing materials, its thickness is at least 300 mm, which limits the minimization of bending radii when laying.

The usable zone has a small circular area and, as a consequence, a small volume due to the non-compact layout of the layered transformable shell. In the TransHab project, the shell over the entire diameter of the fairing is laid in three layers, which greatly limits the size of the rigid carrier compartment, despite its cylindrical shape.

The layout of the transformable module according to the American project does not allow providing an additional belt for the radiation protection of the crew for a long stay in space.

The main problems of this device are the laying of a multilayer transformable containment shell (MTGO) in the transport position due to restrictions on the radii of its bending and ensuring the maximum size of the hard load compartment with limited dimensions of the GPG under the fairing, as well as the insufficient protection of the crew from radiation of the said containment shell during long expeditions. MTGO occupies a significant amount in the folded position, and due to the limited size of the CGS under the cowl, it reduces the size of the hard carrier compartment and also worsens the ergonomics of the module.

The objective of the invention is to increase the size of the useful zone of constant volume for the life of astronauts by increasing the cross section of the hard carrier compartment, as well as increasing the level of protection of the crew from radiation during prolonged stay in space by providing the possibility of placing inside the hard carrier compartment around the useful zone of the constant volume of additional radiation protection .

To this end, the object of the invention is a space transformable module, placed in the payload area under the fairing, containing a multilayer transformable pressure envelope, including anti-meteoroid and radiation shields, thermal insulation and an external support layer, a rigid load compartment with a useful zone of constant volume, transient sealing elements of a multilayer transformable pressure envelope the rigid carrier compartment is made in the form of a non-equilateral prism, while the cross section perpendicular to the central axis of the prism is is a polygon that has four long sides that are equal to each other, axisymmetric with respect to the central axis of the prism, and the rigid bearing compartment with the inner surface of the fairing forms the laying areas of the multilayer transformable pressure envelope, while in each of the four zones between the long sides of the prism and the inner surface of the fairing the containment is laid in the form of two symmetric S-shaped loops facing each other and interlocked with each other along the outer bearing layer.

Figure 1. - a cross section of a space transformable module in a transport position;

Figure 2. - MTGO checkout scheme;

Figure 3. - a cross-section of the space transformable module in the working position.

In the figures:

1 - hard load compartment;

2 - useful zone of constant volume;

3 - multilayer transformable pressure envelope;

4 - elements of the MTGO checkout;

5 - the inner surface of the fairing.

The transformable space module consists of a central rigid carrier compartment 1 in the form of an unequal prism and a multilayer transformable pressure envelope 3. A basic length of MTGO 3 is folded into four zones formed between the sides of the prism having long sides in this section and the inner surface of the fairing 5.

The multilayer transformable pressure envelope 3 is fixed in the transport position using the MTGO 4 check elements. An example of the MTGO 3 check pattern is shown in FIG.

When disclosing the elements of the MTGO 4 carriage under the influence of excessive pressure, the MTGO 3 is deployed in the working position. A cross section of a transformable module in the operating position is shown in FIG. 3.

Here is an example embodiment of the invention.

The rigid carrier compartment 1 is made of a prismatic shape, the cross section perpendicular to the central axis of the prism is, for example, an octagon, inside there is a usable area of constant volume of 2 square sections, having dimensions 2000 × 2000 mm, which corresponds to the dimensions of a full compartment on the ISS. Mentioned zone 2 can be used as a working zone, and its ergonomics is fully consistent with the working areas of the traditional compartments of the space station.

The dimensions of the hard load compartment 1 allow us to surround the usable zone of constant volume 2 with an additional radiation protection belt, for example, an instrument frame that protects the crew from radiation during long expeditions.

Reducing the number of places and the number of elements for the sealing of a multilayer transformable pressure envelope 3 to four increases the reliability of the invention and simplifies the installation of MTGOs, as well as reduces the weight of the invention.

Checking can be carried out, for example, in the following way: MTGO 3 is folded along the fold lines, forming S-shaped loops, which are pulled together by a coupling tape towards each other and fit into four main zones. Checking occurs using checks for loops on the outer supporting layer of MTGO 3. Stripping occurs using electromechanical or pyrotechnic means.

Between the inner surface of the fairing 5 and the short sides of the rigid carrier compartment 1, the multilayer transformable pressure chamber 3 is laid in one layer, which ensures the maximum diagonal section of the rigid carrier compartment 1 and, therefore, the maximum dimensions of the usable zone of constant volume 2.

The size and shape of the hard carrier compartment 1 allows you to place additional radiation protection inside it, for example, in the form of an instrument frame covering a useful area of constant volume 2, resulting in an increase in the level of protection during prolonged stay of the crew on board the spacecraft.

Claims (1)

A transformable space module located in the payload area under the fairing, containing a multilayer transformable pressure envelope, including anti-meteoroid and radiation shields, thermal insulation and an external support layer, a hard load compartment with a useful zone of constant volume, and the elements of the multilayer transformable pressure envelope shutdown, characterized in that the compartment is made in the form of a non-equilateral prism, while the cross section perpendicular to the central axis of the prism is a poly angle a nickname that has four long sides equal to each other, axisymmetric with respect to the central axis of the prism, and the rigid bearing compartment with the inner surface of the fairing forms the laying areas of the multilayer transformable pressure envelope, while in each of the four zones between the long sides of the prism and the inner surface of the fairing the said pressure envelope is laid in the form of two symmetrical counter-facing loops of an S-shaped, etched between each other along an external carrier layer.

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