Satellite solar generator wing and satellite

Abstract

Satellite solar generator wing including solar panels having at least two fixed solar panels and at least one semi-fixed solar panel. The solar panels are connected to one another in order to assume an operating position and a transport position, and, in the transport position, the solar panels are retained on top of one another and the semi-fixed solar panel is arranged in a freely oscillating manner between the two fixed solar panels.

Claims

1. A satellite solar generator wing comprising: solar panels including at least two fixed solar panels and at least one semi-fixed solar panel, wherein the solar panels are connected to one another in order to assume an operating position and a transport position, and wherein, in the transport position, the solar panels are retained on top of one another, and the semi-fixed solar panel is connected to one of the at least two fixed solar panels via a joint arranged at a first edge of the semi-fixed solar panel and is decoupled from the at least two fixed solar panels between the first edge and at least one second edge different from the first edge, so that the semi-fixed solar panel can oscillate between the at least two fixed solar panels.

2. The satellite solar generator wing according to claim 1, further comprising at least one coupling unit that is structured and arranged to be releasable to assume the operating position, and is structured and arranged to couple the two fixed solar panels to one another in the transport position.

3. The satellite solar generator wing according to claim 1, wherein the at least two fixed solar panels are oscillation-coupled to one another in the transport position.

4. The satellite solar generator wing according to claim 3, wherein the at least two fixed solar panels are oscillation-coupled to one another in the transport position by at least one coupling unit.

5. The satellite solar generator wing according to claim 2, wherein the semi-fixed solar panel comprises at least one opening located in a region of the at least one coupling unit that is dimensioned so that at least one segment of the at least one coupling unit extends through the opening without binding the semi-fixed solar panel to the at least one coupling unit.

6. The satellite solar generator wing according to claim 1, further comprising movement restrictors structured and arranged to limit movement amplitude of the semi-fixed solar panels relative to the fixed solar panels.

7. The satellite solar generator wing according to claim 6, wherein at least the fixed solar panels comprise the movement restrictors.

8. The satellite solar generator wing according to claim 7, wherein, in the transport position, a gap is present between the movement restrictors and a corresponding contact surface on an opposing component, in order to allow oscillation of the solar panels relative to one another.

9. The satellite solar generator wing according to claim 8, wherein the movement restrictors and the corresponding contact surfaces are embodied so as to limit movements of the semi-fixed solar panel relative to the fixed solar panels on the panel plane.

10. The satellite solar generator wing according to claim 9, wherein, in the transport position, the movement restrictors and the corresponding contact surfaces are engageable with one another and secure the semi-fixed solar panel against a lateral deflection between the fixed solar panels.

11. The satellite solar generator wing according to claim 1, further comprising reinforcing elements on the at least one semi-fixed solar panel.

12. The satellite solar generator wing according to claim 11, wherein the reinforcing elements have contact surfaces arranged to face movement restrictors in order to limit a movement amplitude of the semi-fixed solar panel.

13. The satellite solar generator wing according to one of claim 12, wherein the reinforcing elements form at least one frame for the semi-fixed solar panel.

14. The satellite solar generation wing according to claim 1, wherein the at least one semi-fixed solar panel comprises two semi-fixed solar panels arranged to lie directly on top of one another in the transport position and arranged in a freely oscillating manner between two fixed solar panels in the transport position.

15. The satellite solar generator wing according to claim 14, wherein at least one of the two semi-fixed solar panels comprises movement restrictors structured and arranged to limit an amplitude of the movement relative to the other of the two semi-fixed solar panel.

16. The satellite solar generator wing according to claim 1, wherein the two fixed solar panels and the at least one semi-fixed solar panel form a solar panel system.

17. The satellite solar generator wing according to claim 16, comprising a plurality of the solar panel systems.

18. A satellite comprising at least one satellite solar generator wing according to claim 1.

19. A method for deploying a satellite that assumes a transport position and operating position, the method comprising: connecting solar panels of a satellite solar generator wing, which include at least two-fixed panels and at least one semi-fixed panel, to one another; and arranging the solar panels in the transport position so that the solar panels are arranged one on top of the other, wherein the at least one semi-fixed solar panel is connected to one of the at least two fixed solar panels via a joint arranged at a first edge of the at least one semi-fixed solar panel and is decoupled from the at least two fixed solar panels between the first edge and at least one second edge different from the first edge, so that the at least one semi-fixed solar panel can oscillate manner between the at least two fixed solar panels.

20. The method according to claim 19, further comprising releasing the solar panels from the transport position so that the satellite solar wing generator assumes an operating position.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) The present invention is further described in the detailed description which follows, in reference to the noted plurality of drawings by way of non-limiting examples of exemplary embodiments of the present invention, in which like reference numerals represent similar parts throughout the several views of the drawings, and wherein:

(2) FIG. 1 shows a schematic illustration of a satellite solar generator wing according to the invention in its operating position;

(3) FIG. 2 shows the satellite solar generator wing from FIG. 1 in its transport position;

(4) FIG. 3 shows a perspective view of the folded satellite solar generator wing, without the upper fixed solar panel;

(5) FIG. 4 shows a detailed view of a semi-fixed solar panel from FIG. 3;

(6) FIG. 5 shows a sectional illustration through the satellite solar generation wing in FIG. 2 in the region of the coupling unit;

(7) FIG. 6a shows a sectional illustration of the satellite solar generator wing in FIG. 2 in the edge region at a first point in time and load state during the launch phase;

(8) FIG. 6b shows a sectional illustration of the satellite solar generator wing in FIG. 2 in the edge region at a second point in time and load state during the launch phase;

(9) FIG. 7 shows a sectional illustration of the satellite solar generator wing in FIG. 2 in the edge region at a third point in time and load state during the launch phase;

(10) FIG. 8 shows a detailed view of the satellite solar generator wing in FIG. 3, wherein the fixed solar panel shown in FIG. 3 is omitted to improve clarity;

(11) FIG. 9 shows a sectional illustration of the satellite solar generator wing in its transport position in the edge region according to a second embodiment;

(12) FIG. 10 shows a sectional illustration of the satellite solar generator wing in its transport position in the edge region according to a third embodiment; and

(13) FIG. 11 shows a schematic illustration of a satellite according to the invention.

DETAILED DESCRIPTION OF THE EMBODIMENTS

(14) The particulars shown herein are by way of example and for purposes of illustrative discussion of the embodiments of the present invention only and are presented in the cause of providing what is believed to be the most useful and readily understood description of the principles and conceptual aspects of the present invention. In this regard, no attempt is made to show structural details of the present invention in more detail than is necessary for the fundamental understanding of the present invention, the description taken with the drawings making apparent to those skilled in the art how the several forms of the present invention may be embodied in practice.

(15) In FIG. 1, a satellite solar generator wing 10 is schematically illustrated in its operating position, which wing is attached to a satellite wall not shown here by an articulated rod system 12, also known as a yoke.

(16) In the embodiment shown, the satellite solar generator wing 10 comprises two fixed solar panels 14, 16 and two semi-fixed solar panels 18, 20, which are embodied as solar panels lateral to the fixed solar panel 16.

(17) The solar panels 14 through 20 comprise respectively one solar cell side 14a through 20a, on which side the solar cells S are attached and which is aligned with the sun in the operating position.

(18) The individual solar panels 14 through 20 are pivotably connected to one another via joints 22 which are arranged at the edge of the solar panels 14 through 20 and which can be used to move the solar panels 14 through 20 out of the folded transport position shown in FIG. 2 into the operating position shown in FIG. 1. For this purpose, the joints 22 are typically pre-stressed in the unfolding direction, that is, in the direction of the operating position. In this way, solar panels 14, 16 are initially retained securely in their transport position by coupling units 24 (FIG. 2). The exact functioning of the coupling units 24 is explained later on the basis of FIG. 5.

(19) The transport position illustrated in FIG. 2 is characterized in that the solar panels 14 through 20 are folded relative to one another in such a manner that they are arranged congruently on top of one another. In this folded state, they are arranged at a distance from a satellite side wall.

(20) Alternatively, however, the solar panels 14 through 20 can also have different sizes, in particular the lateral solar panels. For example, these can be merely half as high.

(21) From the transport position of the satellite solar generator wing 10 shown in FIG. 2, it also follows that, in the folded state, the solar panels 14 through 20 are arranged such that the two fixed solar panels 14, 16 have accommodated the two semi-fixed solar panels 18, 20 between them. This means that, in its transport position, the satellite solar generator wing 10 is folded such that the two semi-fixed solar panels 18, 20 lie between the two fixed solar panels 14, 16.

(22) The fixed solar panels 14, 16, which are embodied in a stronger and thicker manner than the semi-fixed solar panels 18, 20, thus form in the transport position an outer protection for the thin, semi-fixed solar panels 18, 20. This applies not only to mechanical stresses, but also to radiation-induced stresses during the transport phase in outer space.

(23) In FIG. 3, the solar generator wing 10 is shown in a perspective illustration without the external upper fixed solar panel 14 or 16, so that one of the two semi-fixed solar panels 18 or 20 can be seen. Furthermore, segments of the coupling units 24 are also illustrated.

(24) Preferably, both solar panels 18, 20 are embodied identically.

(25) The semi-fixed solar panel 18, 20 is constructed from a foil, for example, from a reinforced Kevlar foil, on which the solar cells S are mounted. For the semi-fixed solar panel to nevertheless maintain its planar form, the semi-fixed solar panel 18, 20 comprises reinforcing elements 26 which form a frame 28 of the semi fixed solar panel 18, 20 and form additional cross braces 30 that run parallel to the shorter longitudinal sides of the frame 28. The semi-fixed solar panels 18, 20 obtain the necessary rigidity via the reinforcing elements 26. In this way, the desired rigidity of the semi-fixed solar panels 18, 20 can be achieved by the number of the cross braces 30, for example. Alternatively, the desired rigidity can also be achieved through density differences or thickness differences in the foil.

(26) Furthermore, the semi-fixed solar panel 18, 20 comprises multiple openings 32 which are provided in the region of the respective coupling units 24, as can be seen from FIG. 3.

(27) In FIG. 4, a partial view of one of the semi-fixed solar panels 18 or 20 is shown.

(28) In this illustration, one of the openings 32 can be readily identified, as well as the arrangement of the solar cells S on a solar cell side of the semi-fixed solar panel 18, 20.

(29) Furthermore, in FIG. 4, a segment of the frame 28 is shown, on which segment a movement restrictor 34 is arranged, the function of which is explained below on the basis of FIGS. 6a, 6b and 7.

(30) In FIG. 5, the satellite solar generator wing 10 from FIG. 2 is shown in cross section. Further, a region of the folded satellite solar generator wing 10 around one of the coupling units 24 is illustrated.

(31) The coupling unit 24 comprises a base element 36 which is attached to the satellite side wall not shown. Furthermore, the coupling unit 24 comprises a pin 38 and respectively one bushing 40 per fixed solar panel 14, 16.

(32) The pin 38 couples the two fixed solar panels 14, 16 to one another in that the pin 38 axially presses the bushings 40 against one another. The pin 38 engages in the base element 36 and an opposing front face 41, so that the fixed solar panels 14, 16 are coupled to the satellite side wall and securely spaced from one another.

(33) The coupling unit 24 is used to securely retain the solar panels 14 through 20 lying on top of one another against the pre-stress of the joints 22 at a predefined distance to one another in the transport position of the panels.

(34) To move the satellite solar generator wing 10 from the transport position shown in FIG. 2 into the operating position shown in FIG. 1, the pin 38 is released, so that the satellite solar generator wing 10 can unfold as a result of the pre-stressed joints 22. The release of the pin 38 can occur pyrotechnically, electrically or mechanically.

(35) Accordingly, the two fixed solar panels 14, 16 are oscillation-coupled to one another by the coupling unit 24 during the launch phase of the carrier rocket. The oscillations of the two fixed solar panels 14, 16 thus interact during the launch phase.

(36) Furthermore, from FIG. 5, it follows that the two semi-fixed solar panels 18, 20 are not coupled to the coupling unit 24, since the pin 38 and the bushings 40 of the coupling unit 24 extend through the respective opening 32 of the semi-fixed solar panels 18, 20 and have a radial distance from the edges of the openings 32.

(37) Via the coupling unit 24 and the openings 32 in the semi-fixed solar panels 18, 20, it is thus achieved that the satellite solar generator wing 10 comprises, in the folded state or in its transport position, two oscillation systems separate from one another. The first oscillation system is formed by the coupled oscillation system of the fixed solar panels 14, 16 and the second oscillation system is formed by the non-coupled, freely oscillating, semi-fixed solar panels 18, 20.

(38) In FIGS. 6a, 6b and 7, the satellite solar generator wing 10 is once again shown in its transport position in an enlarged sectional illustration. Moreover, these figures schematically show an edge region of the satellite solar generator wing 10 at three different points in time and load states during the launch phase.

(39) In the edge region, the semi-fixed solar panels 18, 20 comprise the reinforcing elements 26 which form the frame 28. The reinforcing elements 26 comprise contact surfaces 42 for the movement restrictors 34. The movement restrictors 34 are arranged on top of one another perpendicular to the respective panel plane in the region of the reinforcing elements 26. In this manner, the movement restrictors 34 can interact with the contact surfaces 42 in order to limit the movement of two adjacent solar panels 14 through 20 relative to one another.

(40) As mentioned previously, the two fixed solar panels 14, 16 are kept at a predefined distance from one another via the coupling unit 24, which distance is greater than the height of the semi-fixed solar panels 18, 20 lying therebetween together with the reinforcing elements 26 and movement restrictors 34. It is thus ensured that, in the transport position, a gap 44 is present between at least one movement restrictor 34 and a contact surface 42.

(41) This gap 44 guarantees that the semi-fixed solar panels 18, 20 are positioned in a freely oscillating manner between the two oscillation-coupled fixed solar panels 14, 16. During the launch phase of the carrier rocket, the semi-fixed solar panels 18, 20 can thus freely oscillate relative to the fixed solar panels 14, 16 by at least the width of the gap 44 in a manner perpendicular to the panel plane. The oscillation amplitude of the free relative movement of the semi-fixed solar panels 18, 20 is only limited upon contact by the contact surfaces 42 with the movement restrictors 34.

(42) In the embodiment shown, the two fixed solar panels 14, 16 respectively comprise on their rear side 14b, 16b the movement restrictors 34 which interact with the reinforcing elements 26 of the semi-fixed solar panels 18, 20.

(43) In addition, the semi-fixed solar panel 18 also comprises on its rear side 18b movement restrictors 34 which interact with the contact surfaces 42 of the reinforcing elements 26 of the other semi-fixed solar panel 20 in order to limit the movement of the semi-fixed solar panels 18, 20 relative to one another.

(44) The reinforcing elements 26 of the semi-fixed solar panels 18, 20 thus ensure not only the rigidity of the semi-fixed solar panel 18, 20, but at the same time serve the purpose of limiting the movement amplitude in that they can strike the movement restrictors 34.

(45) The reinforcing elements 26 comprise in cross section a curved, for example, oval shape which is formed from two regions semi-circular in cross section. The reinforcing elements 26 are thereby embodied as sections of a hollow tube and have a height within the range of 4 mm to 18 mm, in particular 11 mm. The reinforcing elements 26 are thereby embodied in an elastically damping manner, as they can deform elastically under stress.

(46) The movement restrictors 34 can also be formed from an elastic material, so that oscillation amplitudes and other movement amplitudes can be even more effectively decelerated and limited in a damping manner.

(47) Furthermore, the shapes of the reinforcing elements 26 and the movement restrictors 34 are matched (in particular, embodied in a mirror-inverted manner) such that movements parallel to the panel plane can also be limited by the movement restrictors 34 and the reinforcing elements 26 engaged with one another.

(48) This is illustrated in FIG. 6b, in which an exemplary load state of the satellite solar generator wing 10 is shown, which state illustrates the maximum deflection of the semi-fixed solar panel 18 on the panel plane.

(49) The movement of the semi-fixed solar panel 18 relative to the immediately adjacent solar panels 14, 20 on the panel plane is limited, since the reinforcing element 26 of the semi-fixed solar panel 18 contacts the movement restrictor 34 of the fixed solar panel 16 with a right edge section of the contact surface 42. Furthermore, the reinforcing element 26 of the semi-fixed solar panel 20 contacts the movement restrictor 34 of the semi-fixed solar panel 18 with a left edge section of the contact surface 42. In this manner, the relative movement of the semi-fixed solar panel 18 on the panel plane is efficiently limited.

(50) Thus, not only is the oscillation amplitude limited, but rather every movement of the semi-fixed solar panels 18, 20 relative to the fixed solar panels 14, 16 is limited beginning at a certain deflection.

(51) The at least one gap 44 and the curves of the movement restrictors 34 and reinforcing elements 26 engaged with one another do not allow a lateral movement of the semi-fixed solar panel 18, 20 out of the fixed solar panels 14, 16 in any relative position.

(52) In this manner, a lateral sliding of the semi-fixed solar panels 18, 20 out of the casing surrounding it, which casing is formed by the two fixed solar panels 14, 16, can be prevented during the launch phase.

(53) In FIG. 7, the satellite solar generator wing 10 is shown at a third point in time or load state during the launch phase, at which a different oscillation state is present that can also be referred to as the neutral position. At this point in time, a gap 44a through 44c lies between each of the movement restrictors 34 and its corresponding contact surface 42. The two semi-fixed solar panels 18, 20 have moved relative to the fixed solar panels 14, 16 such that respectively one gap 44a, 44b has been produced between the movement restrictor 34 arranged on the rear side 14b, 16b of the fixed solar panels 14, 16 and the corresponding contact surface 42. Furthermore, the two semi-fixed solar panels 18, 20 have moved relative to one another such that a gap 44c has been produced between them as well.

(54) From the comparison of FIGS. 6a, 6b and 7, which show two different exemplary oscillation states of the folded satellite solar generator wing 10 during the launch phase, it becomes clear that the semi-fixed solar panels 18, 20 are arranged between the two fixed solar panels 14, 16 in a freely oscillating manner in the transport position, but that they cannot deflect laterally.

(55) In FIG. 8, the folded satellite solar generator wing 10 is shown in a perspective illustration, so that the upper fixed solar panel 16 is not shown.

(56) The movement restrictors 34 arranged on the rear side 16b of the upper fixed solar panel 16 are illustrated, however, and bear against the reinforcing elements 26 or the corresponding contact surfaces 42 in the illustration shown.

(57) Furthermore, it follows from FIG. 8 that the bushings 40 of the coupling unit 24 extend through the opening 32 without touching the edge thereof. From this, it then becomes clear that the semi-fixed solar panels 18, 20 are not coupled to the coupling unit 24.

(58) The openings 32 are also sized such that no contact occurs between the bushings 40 and the edge of the opening 32, despite the maximum deflection of the semi-fixed solar panels 18, 20. For this purpose, the openings 32 are embodied in a roughly circular manner and have a diameter of 50 mm to 150 mm, in particular 100 mm.

(59) The foil of the semi-fixed solar panels 18, 20 furthermore has a thickness of 50 m to 200 m, in particular 100 m, so that the semi-fixed solar panels 18, 20 can also unfold in an unimpeded manner. In contrast, the fixed solar panels 14, 16, which are constructed from a CFRP honeycomb structure, have a thickness of 15 mm to 25 mm. This thickness provides adequate protection against the radiation in outer space.

(60) In addition, several different damping elements 45 are provided in FIG. 8 which are arranged on the solar cell side 18a of the semi-fixed solar panel 18. The damping elements 45 are even partially arranged on the solar cells S themselves. In addition, the damping elements 45 can also be arranged in recesses of the solar cells S, so as not to impair the active surface of the solar cells S.

(61) Additionally, damping elements 45 of this type can also be arranged on the rear side, which is not shown here, of the semi-fixed solar panels 16, 18. These damping elements 45 can, for example, interact with the damping elements 45 on the opposing solar cell side of the adjacent solar panel.

(62) Generally, the damping elements 45 are intended to protect the solar cells S. Damping elements 45 of this type can be provided on all solar cell sides 14a through 20a of the solar panels 14 through 20 in order to protect the solar cells S. The damping elements 45 form additional movement restrictors which are only operative after the closing of the gap 44 or gaps 44a-44c.

(63) In FIG. 9, a second embodiment of the satellite solar generator wing 10 is illustrated which comprises two fixed solar panels 14, 16 and only one semi-fixed solar panel 18. The semi-fixed solar panel 18 is arranged between the two fixed solar panels 14, 16. The two fixed solar panels 14, 16 comprise movement restrictors 34 on their respective rear sides 14b, 16b. The movement restrictors 34 interact with the reinforcing elements 26 or the contact surfaces 42 of the semi-fixed solar panel 18 in a manner analogous to the previously described embodiment, so that the movement amplitudes of the semi-fixed solar panel 18 are limited.

(64) Alternatively, it can also be provided that more than two semi-fixed solar panels that can oscillate freely are arranged between two oscillation-coupled fixed solar panels 14, 16. For this purpose, it is merely necessary to adjust the distance between the two fixed solar panels 14, 16 accordingly by the coupling unit 24.

(65) In FIG. 10, a third embodiment of the satellite solar generator wing 10 is shown which comprises four fixed solar panels 14, 16, 114, 116 and four semi-fixed solar panels 18, 20, 118, 120, that is, eight solar panels in total.

(66) In the embodiment shown, two semi-fixed solar panels 18, 20 are respectively arranged between two fixed solar panels 14, 16 in a known manner. These two semi-fixed solar panels 18, 20 and the two fixed solar panels 14, 16 surrounding them form a first panel system 46 of the satellite solar generator wing 10.

(67) Analogously, the two other semi-fixed solar panels 118, 120 and the two fixed solar panels 114, 116 form a second panel system 48 of the satellite solar generator wing 10, so that the satellite solar generator wing 10 according to the third embodiment is constructed from two panel systems 46, 48.

(68) Furthermore, on the front side of at least one of the two fixed solar panels 16, 114, at least one damping element 50 is provided which prevents the two solar cell sides 16a, 114a of the two solar panels 16, 114 arranged opposite of one another from contacting each other during the oscillations, whereby the solar cells S would be damaged. This damping element 50 is primarily necessary when the solar panel systems 46, 48 are not oscillation-coupled to one another.

(69) The fixed solar panels 14, 16, 114, 116 of the third embodiment can be oscillation-coupled to one another by a shared coupling unit 24, so that the satellite solar generator wing 10 in the third embodiment also comprises a first oscillation system that is formed from all fixed solar panels 14, 16, 114, 116.

(70) Furthermore, other additional panel systems can also be provided for a satellite solar generator wing 10. The result of this is that the satellite solar generator wing 10 can be modularly expanded, preferably by two fixed solar panels with intermediately positioned semi-fixed solar panels.

(71) With a satellite solar generator wing 10 of this type, a power-to-weight ratio of over 150 W/kg can be achieved, so that all masses are included.

(72) Additionally, in FIG. 11 a satellite 52 is illustrated schematically which comprises a satellite body 54 and two satellite solar generator wings 10 of the type described previously, which wings are attached to opposite sides of the satellite body 54.

(73) It is noted that the foregoing examples have been provided merely for the purpose of explanation and are in no way to be construed as limiting of the present invention. While the present invention has been described with reference to an exemplary embodiment, it is understood that the words which have been used herein are words of description and illustration, rather than words of limitation. Changes may be made, within the purview of the appended claims, as presently stated and as amended, without departing from the scope and spirit of the present invention in its aspects. Although the present invention has been described herein with reference to particular means, materials and embodiments, the present invention is not intended to be limited to the particulars disclosed herein; rather, the present invention extends to all functionally equivalent structures, methods and uses, such as are within the scope of the appended claims.