U.S. patent application number 10/502777 was filed with the patent office on 2005-04-21 for apparatus for cooling components in spacecraft.
Invention is credited to Korpan, Nikolai, Leshchenko, Volodymyr, Zharkov, Jaroslav.
Application Number | 20050082038 10/502777 |
Document ID | / |
Family ID | 3642031 |
Filed Date | 2005-04-21 |
United States Patent
Application |
20050082038 |
Kind Code |
A1 |
Korpan, Nikolai ; et
al. |
April 21, 2005 |
Apparatus for cooling components in spacecraft
Abstract
The invention relates to an apparatus for cooling components in
spacecraft, comprising a heat radiator (5) and a heat conductor (3;
3a, 3b). A versatile applicability is achieved in such a way that
the heat conductor (3, 3a, 3b) penetrates an outside wall (1) of
the spacecraft and is provided in the interior of the spacecraft
with several coupling places (8) for components to be cooled (20)
and/or for other heat conductors (10).
Inventors: |
Korpan, Nikolai; (Vienna,
AU) ; Zharkov, Jaroslav; (Kiew, UA) ;
Leshchenko, Volodymyr; (Kyiw, UA) |
Correspondence
Address: |
DYKEMA GOSSETT PLLC
FRANKLIN SQUARE, THIRD FLOOR WEST
1300 I STREET, NW
WASHINGTON
DC
20005
US
|
Family ID: |
3642031 |
Appl. No.: |
10/502777 |
Filed: |
September 13, 2004 |
PCT Filed: |
October 24, 2002 |
PCT NO: |
PCT/EP02/11881 |
Current U.S.
Class: |
165/104.21 ;
165/104.11 |
Current CPC
Class: |
F28F 13/00 20130101;
B64G 1/641 20130101; B64G 1/506 20130101; B64G 1/58 20130101; B64G
1/503 20130101 |
Class at
Publication: |
165/104.21 ;
165/104.11 |
International
Class: |
F28D 015/00 |
Foreign Application Data
Date |
Code |
Application Number |
Jan 29, 2002 |
AT |
A 142/2002 |
Claims
1-11. (canceled)
12. An apparatus for cooling components in spacecraft, comprising a
heat radiator and a heat conductor, wherein the heat conductor is
constructed so as to penetrate an outside wall of the spacecraft
when installed and comprises several coupling places for
selectively coupling components to be refrigerated and/or further
heat conductors, wherein the heat conductor consists of an inner
part and an outer part which are connected at a conical connecting
section.
13. An apparatus as claimed in claim 12, wherein the heat conductor
is designed in two parts.
14. An apparatus as claimed in claim 13, wherein the connection
between an outer part of the heat conductor and an inner part of
the heat conductor is arranged in the zone of the outside wall of
the spacecraft.
15. An apparatus as claimed in claim 13, wherein the connection
between the outer part of the heat conductor and the inner part of
the heat conductor is arranged in a substantially conical way.
16. An apparatus as claimed in claim 13, wherein the connection
between the outer part of the heat conductor and the inner part of
the heat conductor is pretensioned by a spring.
17. An apparatus as claimed in claim 13, wherein the connection
between the outer part of the heat conductor and the inner part of
the heat conductor is provided with a fluid of high heat
conductivity.
18. An apparatus as claimed in claim 12, wherein the coupling
places of the heat conductor are arranged as closeable opening in
an insulation layer which encloses the heat conductor.
19. An apparatus as claimed in claim 12, wherein the heat conductor
is provided with a liquid-filled hollow space.
20. An apparatus as claimed in claim 12, wherein the heat conductor
is substantially made of copper.
21. An apparatus as claimed in claim 12, wherein the further heat
conductors are made of copper wires.
22. An apparatus as claimed in claim 21, wherein the further heat
conductors are flexible.
Description
[0001] The invention relates to an apparatus for cooling components
in space flight bodies, comprising a heat radiating body and a heat
conducting body.
[0002] The research of space is one of the most predominant tasks
of man from the planet earth. This task will increase in importance
particularly for future generations of manhood, because as a result
of newly made findings from space research man can profit not only
due to new technologies but also due to the newly created spheres
of living and the exploration of the unknown, mysterious and
enigmatic.
[0003] The duration of flights into space with astronauts and other
living beings, in conjunction with their stay in space, can extend
in future to several earth years. Moreover, individual trips of
tourists and interested persons may later be a part of daily life.
The provision of effective medical and surgical help and diagnosis
for travellers into space will therefore become a global problem. A
system and a technology, tailored specifically for space and
medicine, needs to be developed and adapted for this purpose.
Cosmic medicine differs from conventional medicine on earth in
respect of the following aspects:
[0004] In the state of zero gravity illnesses progress with their
own specific properties, which is why specific diagnostic and
treatment methods are gradually coming to light.
[0005] For this purpose it is necessary to create a new efficient
medical technology which is adapted for space.
[0006] Since dimensions such a weight, volume and other technical
parameters of space station equipment, including the medical
technology, play a special role, they need to be adapted
accordingly, i.e. they need to be reduced, minimized and
optimized.
[0007] The ambient conditions of space need to be utilized in an
optimal way such as the use of solar energy by means of solar
batteries for the supply with energy of the space station.
Moreover, other physical factors of space such as the cosmic cold
which is also a property of space and is approx. -273.degree. C.
must be used for the proper operation of both the space station as
well as the cosmic devices within the station itself, including the
electrical and medical technology and the provision of living
conditions for the travellers.
[0008] As is generally known, low temperatures are already highly
used in our time in modern electron and medical technology. Low
temperatures are produced on earth by means of refrigerating
machines, liquid gases and other heat-absorbing methods in order to
use them in practice. A high input of energy is required for this
purpose. During the trip through space there is deep coldness
outside of the space station. For this reason it is possible to
develop new methods and a concomitant respective technology for
heat absorption directly from the inside to the outside by various
objects within the space station. The heat absorption can be dosed.
The following objects can be used for the dosed heat
absorption:
[0009] Elements of electronic devices (processors, receiving and
master control devices of the system for remote cosmic connections,
etc.) which are a component of the on-board system of the space
station and various research devices.
[0010] Medical technology and surgeries for hypothermia as well as
cryomedical technology or cryosurgical and cryotherapeutical
surgeries (miniature operating theaters) which may allow the
optimal use of the cold in the treatment of various illnesses
during the trip through space. The use of hypothermia, cryotherapy
and refrigerating engineering and cryotechnology will become an
unquestioned advantage in comparison with alternative methods and
will lead not only with respect to medical differentiation to a
high accessibility and possibility for the application of cold in
the space station and its equipment.
[0011] Cosmic ice chambers for the long-term storage of foodstuffs.
Cosmic cryopreservation allows avoiding the use of preservatives.
Foodstuffs can thus maintain their high quality during storage.
[0012] Cosmic refrigerating chambers offer the long-term storage of
pharmaceuticals, viruses and other biological objects.
[0013] Cosmic cryochambers for the long-term storage of
cryologically preserved items and other biological objects (e.g.
blood components, cells, tissue and other biological
components).
[0014] From U.S. Pat. No. 5,699,982 A, a spacecraft is known which
is provided with heat radiating bodies which discharge the heat
which is produced by transmitting and receiving devices on board.
So-called heat pipes are used to ensure heat transportation.
[0015] DE 43 44 025 C1 describes a spacecraft with a cooling unit
which is an insulated box. Cooling is limited to items inside the
box so that use of such cooling unit is limited. Particularly it is
not possible to cool devices located in some distance from the
cooling unit. EP 870 677 A shows another cooling system. However,
no solution is given to the above problem.
[0016] As described above, the requirements to provide low
temperatures are numerous and are also subject to certain changes
in the course of a manned mission of a longer duration. A
universally applicable and adaptable supply with cold cannot be
achieved with the systems known to date.
[0017] It is the object of the present invention to avoid such
disadvantages and to further develop the apparatus of the kind
mentioned above in such a way that a plurality of different devices
and applications can be supplied with low temperatures. Special
emphasis shall be placed on the flexibility in a spatial and
temporal respect as well as in respect to the required temperature
level.
[0018] It is provided in accordance with the invention that the
heat conducting body penetrates an outside wall of the spacecraft
and is provided in the interior of the spacecraft with several
coupling positions for components to be refrigerated and/or for
further heat conducting bodies. The solution in accordance with the
invention provides a universally applicable cryogenic system which
can easily be adapted to the respective requirements. The coupling
places allow the simultaneous supply of different devices.
[0019] It is particularly appropriate when the heat conducting body
is designed in two parts. In particular, the connection should be
disposed between an outside part of the heat conducting body and an
inner part of the heat conducting body in the zone of the
spacecraft's outside wall. This allows providing the ideal
adaptation of the heat conducting body to the conditions in space
on the one hand and to the conditions in the interior of the
spacecraft on the other hand.
[0020] A particularly favorable heat transmission is achieved in
this connection in such a way that the connection between the outer
part of the heat conducting body and the inner part of the heat
conducting body is provided with a substantially conical
arrangement. It is particularly preferable in this respect when the
connection between the outside part of the heat conducting body and
the inside part of the heat conducting body is pretension by a
spring.
[0021] A further improvement of the heat transmission is achieved
when the connection between the outer part of the heat conducting
body and the inner part of the heat conducting body is provided
with fluid of high heat conductivity. Such a heat conducting paste
which is respectively suitable for low-temperature applications
compensates the unevenness of any mutually touching parts.
[0022] In a further preferred embodiment of the present invention
it is provided that the coupling places of the heat conducting body
are arranged as closeable openings in an insulation layer which
encloses the heat conducting body. Devices can thus be simply
plugged into our out of the apparatus, which considerably
simplifies modifications or other changes.
[0023] It can further be provided for the improvement of the heat
transmission and for avoiding losses that the heat conducting body
is provided with a liquid-filled hollow space. The liquid is
preferably chosen in such a way that during operation it boils at
one end of the hollow space and condenses at the other end. A
particularly effective heat transport can be achieved by so-called
heat pipes.
[0024] Heat transport can occur alternatively in such a way that
the heat conducting body is substantially made of copper.
Preferably, high-purity oxygen-free copper is used for this
purpose. The further heat conducting bodies can be made similarly
of copper wires.
[0025] The invention is now explained in closer detail by reference
to the embodiment shown in the drawing.
[0026] The FIGURE shows the apparatus in a sectional view.
[0027] The outside wall of a spacecraft (not shown in closer
detail) is designated in FIG. 1 with reference numeral 1. A sealing
bush 2 is situated in the outside wall 1 in which a heat conductor
3 is received in an insulated and sealed way. The heat conductor 3
consists of an inner part 3a and an outer part 3b which are
connected at a conical connecting section 4 in a favorable heat
conducting manner by using a heat conducting paste. Heat radiators
5 are attached to the outer part 3b of the heat conductor 3 which
are arranged in this case in the form of cooling ribs.
[0028] The part 6 of the heat conducting body 3 which is situated
in the interior of the space craft is provided with a respective
insulating layer 7 in order to avoid heat losses. Furthermore, said
part 6 comprises several coupling places 8 for components to be
refrigerated or the like which, when not in use, can be closed off
by seals 9. Further heat conductors 10 can be connected to the
coupling places 8, which conductors consist of bundles of copper
wire 13 and are provided on the outside with an elastic
heat-insulating covering 14. The further heat conductors 10 can be
provided with a working surface 11 of a working probe 12 which
allows direct cryotechnical applications. A temperature sensor 16
can be provided in the working surface 11 through which the
temperature is determined and which allows a precise temperature
control by using a heating element 17 which is also integrated in
the zone of the working surface 11. The temperature control can be
realized by a respective regulator 18. The heat conductor 10 can
also be provided with a heat pipe 15.
[0029] Instead of heat conductors, the components to be
refrigerated could also be connected directly to the coupling
places 8, such as a refrigerating chamber 20, which is also
provided with a temperature sensor 16 and a heating element 17.
[0030] The apparatus in accordance with the invention can be
provided with an arrangement so as to be telescopically extendible
from and retractable back to the sealing bush 2 in order to avoid
being an obstruction during the start or re-entry into the
atmosphere. A spring 19 is used to press the two parts 3a, 3b of
the heat conductor 3 against one another and to pretension the zone
4.
[0031] The apparatus in accordance with the invention is suitable
for a large number of different applications and can be adapted
easily to changing requirements.
* * * * *