WO2007128010A1 - Dispositif permettant de façon sélective de recouvrir et de découvrir des surfaces d'un engin spatial - Google Patents

Dispositif permettant de façon sélective de recouvrir et de découvrir des surfaces d'un engin spatial Download PDF

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Publication number
WO2007128010A1
WO2007128010A1 PCT/AT2007/000180 AT2007000180W WO2007128010A1 WO 2007128010 A1 WO2007128010 A1 WO 2007128010A1 AT 2007000180 W AT2007000180 W AT 2007000180W WO 2007128010 A1 WO2007128010 A1 WO 2007128010A1
Authority
WO
WIPO (PCT)
Prior art keywords
slats
spacecraft
lamellae
covering
pivot
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/AT2007/000180
Other languages
German (de)
English (en)
Inventor
Aleksandar Vujanic
Jovan Matovic
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
IMA Integrated Microsystems Austria GmbH
Original Assignee
IMA Integrated Microsystems Austria GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by IMA Integrated Microsystems Austria GmbH filed Critical IMA Integrated Microsystems Austria GmbH
Publication of WO2007128010A1 publication Critical patent/WO2007128010A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/52—Protection, safety or emergency devices; Survival aids
    • B64G1/58—Thermal protection, e.g. heat shields
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
    • B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control

Definitions

  • the invention relates to a device for selectively covering and releasing surfaces of a spacecraft as a function of the temperature with a plurality of relatively rotatable relative to the surface of the spacecraft lamellae, wherein the pivot drive comprises at least one planar element of a memory alloy, which when passing through a Temperature range changes its shape and pivots the slats.
  • Spacecraft surfaces to be covered and released are formed, for example, by heat exchange surfaces that can absorb heat in the form of radiation from the surrounding space or release it to space.
  • heat exchange surfaces are placed on the surface of spacecraft to cool the electrical circuits inside the spacecraft.
  • the required cooling only succeeds if the heat exchange surfaces are not irradiated by the sun.
  • the heat exchange surfaces In sunlight, the heat exchange surfaces must be covered accordingly to prevent heat input from the outside into the spacecraft. Only when the heat exchange surfaces come to lie after a corresponding movement or rotation of the spacecraft on a side facing away from the sun, the heat exchange surfaces can be released to allow the heat transfer from the spacecraft or its units to be cooled to space.
  • spacecraft should not only include powered spacecraft and space stations, but also satellites in particular.
  • Devices for selectively covering and releasing surfaces of a spacecraft are, for example, in the form of blinds consisting of lamellae arranged in parallel known.
  • the lamellae are each pivotable about mutually parallel pivot axes, the pivot drive is carried out using parts that change their shape depending on the temperature, so that after exceeding a defined temperature or after passing through a defined temperature range, the lamellae of the surface or the spacecraft covering Position can be pivoted in a releasing this position or vice versa.
  • bimetallic coils may be used to form the temperature varying parts that are used, but with the bimetal being heated by conduction and the relationship between its temperature and the angle of rotation of the lamellae being approximately linear, a pivotal drive formed by bi-metal spirals will be slow Changes in environmental conditions responds.
  • An improved construction consists in the arrangement of flat elements of a memory alloy, which change their shape and in particular curvature when passing through a defined temperature range and thus pivot the slats.
  • the memory elements can be distributed over the entire length of the lamella, whereby the lamellae can be made much lighter overall. Thanks to their low mass and thanks to the thermal conduction of their feet, the memory elements quickly change their temperature, allowing them to quickly cross a temperature transition range. As a result, the slats go quickly from the open to the closed position or from the closed to the open position, so that the time behavior is significantly improved.
  • Memory alloys are known per se, for example from US Pat. No. 4,435,229 and US Pat. No. 4,707,196, to which reference is expressly made here. In these, not only the composition of such alloys is given, but also various methods for the initialization of memory elements. Initialization describes procedures for their treatment that give them the desired behavior in the event of temperature changes. They consist of repeated changes in temperature and mechanical stress. Preferably, so-called double-acting memory alloys (“two-way shape memory alloys”) are used, which, depending on their temperature, change their shape by their own power between two different forms.
  • a disadvantage of the blind devices described above for spacecraft, in which a plurality of mutually parallel slats is provided, which are each pivotable about mutually parallel pivot axes, is the fact that such a device its full effectiveness due to the parallel arrangement of Slats unfolded only when the sun's radiation is from predetermined directions. Particularly in the case of a laterally incident sun, that is to say when the sun begins to radiate from a direction parallel to the pivot axes of the slats, the correct functioning of the blind device is no longer completely guaranteed.
  • the present invention therefore aims to improve the construction of a covering device of the type mentioned in that the correct function is independent of the sun's direction of incidence and the angle of sunlight. Furthermore, the present invention aims to reduce the weight and increase the efficiency of the cover.
  • the device of the type mentioned is substantially further developed such that the pivot axes of the slats together form a polygon.
  • the lamellae are thus no longer pivotable about mutually parallel pivot axes, but about pivot axes, which together form a polygon or its extension. Any type of polygon is conceivable here, but a regular polygon is particularly preferred, since such regular polygons can be composed in a particularly simple manner to larger areas.
  • the pivot axes of the individual slats no longer run parallel to one another, an embodiment is created in which the slats, whose pivot axes form a polygon, form a group which can be folded out and folded like petals, whereby the individual slats can support each other and an overlap of the individual slats is given, so that a stable construction results, with which can cover any areas without gaps.
  • the device according to the invention is suitable for so-called micro or mini satellites which, for example, only have a diameter of 30 to 50 cm.
  • a construction with slats running parallel to one another would be disadvantageous since adaptation to a defined area to be covered is difficult.
  • a single satellite can be shield-like covered by the majority of the respective pivoting about each pivoting axis extending in different directions axes slats.
  • arbitrary surfaces can be covered with the device according to the invention, preferably surfaces between 1 mm 2 and 500 cm 2 , in particular 1-100 cm 2 .
  • the individual lamellae can be mutually supported according to a preferred development, at least in one end position, so that separate Schwenkwinkelbegrenzer are unnecessary and thus weight can be saved.
  • the lamellae may overlap one another in their covering the surface of the spacecraft or be arranged abutting, so that complete coverage of the surface of the spacecraft to be covered in each case succeeds.
  • the lamellae are fixed via a common support on the surface to be covered or the spacecraft.
  • each slat only with a single support Aus GmbH, preferably, as already mentioned, all slats on a common support are fixed. By reducing the number of supports succeeds in further weight reduction.
  • the support has a length which is at least equal to the length of a part of the slat protruding from the joint in the direction of the surface or spacecraft.
  • a particularly advantageous development results in an arrangement in which the planar element of a memory alloy in the surface covering the pivot position is flat and bent in the surface releasing position.
  • Such a design is particularly suited to the peculiarities of the double-acting memory alloys.
  • the lamellae have the same outline, so that a regular structure is created and it is ensured that the individual lamellae interact with one another in a petal-like manner during the opening and closing process.
  • planar element made of memory alloy is fixed on the one hand to the lamella and on the other hand to the common support, wherein the planar element itself forms the joint, so that no further components are required and the weight is further minimized can.
  • planar element engages the lamella at a radial distance from the inner edge of the lamella, whereby a covering of the spacecraft surface from the joint axis appears both in a radially outer region and in a radially inner region.
  • FIG. 2 shows a view of the device according to the invention in the open state
  • FIG. 3 shows a sectional view along the line III-III of FIG. 1
  • FIG. 4 shows a perspective view of FIG 5 shows a modified embodiment of the device according to FIG. 4
  • FIG. 6 shows a view of a further modified embodiment of the device according to the invention in the closed state
  • FIG. 7 shows a view of the device according to FIG. 6 in the open state.
  • FIG. 1 shows a support structure 1 with a support 2, on which four planar elements 3 made of a memory alloy are arranged, which each support a lamella 4.
  • the slats are in the Spacecraft covering position shown in which adjacent slats 4 each overlap areas 5 have.
  • the mutual overlapping of the lamellae 4 means that in the closed position shown in FIG. 1, that is covering a surface of the spacecraft, between the individual lamellae 4 there are no gaps, and in particular no gaps, which cause the passage of solar radiation would allow.
  • the overlaps 5 lead to the fact that in the open position shown in FIG. 2, that is to say the surface of the spacecraft, the lamellae 4 mutually support one another at the points 6.
  • the lamellae 4 are shown in a position pivoted upward by 90 ° compared to FIG. 1, so that a large part of the surface 7 of the spacecraft is uncovered.
  • the pivoting takes place essentially about the pivot axes 8 and it can be seen that the pivot axes 8 and their extension form a square.
  • the surface 7 of the spacecraft to be covered is visible, wherein the surface is formed by heat exchange surfaces which, in the open position of the lamellae 4 shown in FIG. 3, allow heat to be released to space.
  • the memory alloy elements 3 assume a curved shape in the open position of the slats and in the closed position of the slats 4 shown in dashed lines are flat. The memory alloy elements 3 are in this case all fixed to a common support 2.
  • the lamella-side connection of the flat memory alloy elements 3 takes place at a distance a from the radially inner edge of the lamella 4, so that in the closed position of the lamellae 4 as far as possible and complete coverage of the underlying surface 7 takes place.
  • the perspective view of FIG. 4 is used for further illustration.
  • the cover device is shown as in Fig. 2 in the open, the surface of the spacecraft releasing position. In this position, the fins 4 together with the support structure 1 and the elements 3 define an upwardly open space 11, which contributes to the elements 3 emit less heat to the environment and are heated faster when sun hits the device.
  • the rapid heating of the elements 3 causes the memory elements 3 to reach the temperature range causing their deformation faster, so that the time behavior is significantly improved.
  • the slats have been pivoted to the closed position starting from the open position shown in FIG. 4 and the space 11 disappears, the slats can in turn release the previously absorbed heat energy to the environment.
  • At least one of the fins 4 may have an angled or angled region 9, as shown in Fig. 5.
  • This area 9 is used in the open position of the slats 4 of the cover of the room 11, so that the space 11 is completely closed and heat radiation from the elements 3 to the environment is better prevented.
  • both surfaces of the slats, both the top 12 and the bottom 13, should be made of Sirireflektivem material - the bottom 13, that is the surface to be covered in the closed position of the fins 4 side facing the heat transfer between the surface to be covered, so for example the heat exchange surfaces, and to reduce the lamella and thereby minimize the heat input from the sun to the heat exchange surfaces, the top 12 to the heat radiation and in particular special to be able to better reflect the infrared radiation of the sun.
  • the upper side 12 and the lower side 13 of the lamellae preferably consist of mirror surfaces, wherein preferably the mirror surface of the underside 13 has a low emissivity and the mirror surface of the upper side 12 has a high emissivity.
  • the lower emissivity bottoms 13 of the fins 4 are in the open position on the outside and the higher emissivity tops 12 on the inside, that is, the tops 12 form the interior walls of the space 11 off.
  • the heat generated by the "rising" sun (irradiation direction 14) on at least one of the fins 4 is, as it were, trapped in the space 11, so that the memory elements 3 warm up quickly have been pivoted into the closed position, the lower sides 13 of the lamellae 4 reach a position facing the surface to be covered, the low emissivity of the underside 13 serving to reduce the heat transfer from the hot lamella 4 to the surface to be covered facing away from the surface facing the sun, wherein the high emissivity of the top 12 causes a reflection of the radiated heat into space.
  • the material of the support 2 can be selected using the following considerations. If it is desired that the slats not only due to the direct
  • Support 2 made of good heat conducting material, such as aluminum or titanium, exist. In this case, the
  • small spacers may be provided on the slats. These spacers can be formed, for example, by portions of the lamella that are bent out of the lamellar surface, which engage in the closed position of the lamellas with the surface to be covered. The contact surface is so small that no significant heat transfer takes place. In FIG. 5, such spacers are shown by way of example on one of the lamellae 4 and designated by 10.
  • the slats can each have stiffening ribs, which are formed for example from folds of the fin material.
  • FIGS. 6 and 7 show a modified embodiment in which there is no square but a hexagon is trained.
  • slats 4 are provided, which are articulated in each case via a flat memory alloy element 3 to a central support element 1 pivotally. Between the individual slats 4 overlap areas 5 are again provided.
  • the pivot axes are again denoted by 8, which in the embodiment according to FIGS. 6 and 7 form a regular hexagon.

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  • Engineering & Computer Science (AREA)
  • General Health & Medical Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Health & Medical Sciences (AREA)
  • Remote Sensing (AREA)
  • Critical Care (AREA)
  • Emergency Medicine (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Biodiversity & Conservation Biology (AREA)
  • Environmental & Geological Engineering (AREA)
  • Environmental Sciences (AREA)
  • Toxicology (AREA)
  • Blinds (AREA)

Abstract

Dans un dispositif permettant de façon sélective de recouvrir et de découvrir des surfaces (7) d'un engin spatial en fonction de la température, avec une pluralité de lamelles (4) disposées de façon pivotante par rapport à la surface (7) de l'engin spatial, la commande de basculement comportant au moins un élément plat (3) à base d'un alliage à mémoire de forme, lequel, dans le cas du dépassement d'une plage de température, modifie sa forme et fait pivoter les lamelles (4), les axes de pivotement (8) des lamelles (4) forment ensemble un polygone.
PCT/AT2007/000180 2006-05-09 2007-04-19 Dispositif permettant de façon sélective de recouvrir et de découvrir des surfaces d'un engin spatial Ceased WO2007128010A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
AT0037506U AT9271U1 (de) 2006-05-09 2006-05-09 Vorrichtung zum wahlweisen abdecken und freigeben von oberflächen eines raumfahrzeugs
ATGM375/2006 2006-05-09

Publications (1)

Publication Number Publication Date
WO2007128010A1 true WO2007128010A1 (fr) 2007-11-15

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WO (1) WO2007128010A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109899258A (zh) * 2019-03-29 2019-06-18 中国科学院广州能源研究所 通过记忆金属进行温差发电的装置

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008029338B4 (de) * 2008-06-20 2012-08-23 Audi Ag Vorrichtung zur Temperatursteuerung

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4435229A (en) 1979-09-25 1984-03-06 Johnson Alfred D Method of preparing a two-way shape memory alloy
US4707196A (en) 1982-02-27 1987-11-17 Tohoku Metal Industries Ltd. Ti-Ni alloy articles having a property of reversible shape memory and a method of making the same
JPS6483498A (en) * 1987-09-28 1989-03-29 Hitachi Ltd Heat dissipation controller
JPH01219000A (ja) * 1988-02-29 1989-09-01 Hitachi Ltd 放熱量制御装置
JPH0354097A (ja) * 1989-07-19 1991-03-08 Nec Corp サーマルルーバー装置
JPH0725397A (ja) * 1993-07-12 1995-01-27 Nec Corp サーマルルーバ装置

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4435229A (en) 1979-09-25 1984-03-06 Johnson Alfred D Method of preparing a two-way shape memory alloy
US4707196A (en) 1982-02-27 1987-11-17 Tohoku Metal Industries Ltd. Ti-Ni alloy articles having a property of reversible shape memory and a method of making the same
JPS6483498A (en) * 1987-09-28 1989-03-29 Hitachi Ltd Heat dissipation controller
JPH01219000A (ja) * 1988-02-29 1989-09-01 Hitachi Ltd 放熱量制御装置
JPH0354097A (ja) * 1989-07-19 1991-03-08 Nec Corp サーマルルーバー装置
JPH0725397A (ja) * 1993-07-12 1995-01-27 Nec Corp サーマルルーバ装置

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109899258A (zh) * 2019-03-29 2019-06-18 中国科学院广州能源研究所 通过记忆金属进行温差发电的装置

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