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Description  |
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The present invention relates to a generator for producing electrical
energy from solar energy, hereinafter referred to as a solar generator.
This generator, mounted on board an artificial satellite, is constituted by
a plurality of pivoted panels, stacked but unfoldable, each of which
comprises a thick frame inside which is disposed a thin, flexible support
carrying solar cells, said frame comprising intermediate stiffeners
connecting two opposite sides of the frame.
Solar generators of this type are already known, which comprise a plurality
of panels adapted to occupy two relative positions. In the first of these
positions, which corresponds for example to the launching of the
satellite, the panels are superposed and rest on one another via their
frame. In the second of said positions, the panels are unfolded and are at
least approximately in line with one another.
To avoid the flexible supports of the solar cells of two consecutive
panels, in folded position, banging against each other due to the
vibrations to which said generator is subjected, the total displacement
possible of a flexible support perpendicularly to the plane of its frame
is provided to be shorter than the thickness of said frame.
To this end, two assemblies of the flexible support in its frame are
already known. The first assembly consists in stretching the flexible
support by means of springs between two end uprights of the frame and in
providing, on either side of said support, a certain number of
intermediate uprights, whose role is, on the one hand, to allow the
flexible support to move freely parallel to its plane under the effect of
the tension to which it is subjected, and, on the other hand, to prevent
this support from moving, at the location of the intermediate uprights,
perpendicularly to its plane, these intermediate uprights thus creating
nodes of forced vibrations for the support.
In this way, the frame and the support being divided into compartments by
the different uprights, the assembly is given a pseudo-rigidity which
prevents the support of the solar cells from knocking against the
structure of the body of the satellite or against the support of an
adjacent frame, when it is subjected to considerable vibrations,
particularly when said satellite is launched.
This support therefore acquires a resonance frequency proportional to the
tension to which it is subjected and the displacement of the support in
such a compartment, perpendicular to its plane, is as little as the
resonance frequency is high.
However, such a mode of fixing the support of the solar cells presents
numerous drawbacks. In fact, the solar cells are assembled in
interconnected modules on the flexible support; then said latter is fixed
to its frame and stretched. The tension established is relatively high and
causes elongations of the flexible support. These elongations are
distributed in the intercellular spaces where seriesparallel conductors
for interconnecting said cells are located. Now, by design, these
interconnection conductors are provided with an expansion loop so as to be
able to absorb the differential thermal expansions when the satellite is
on orbit and avoid considerable stresses being induced at the weld spots
between the solar cells and the conductors. Due to the tension exerted on
the flexible support during its assembly on the frame, the elongation of
the support which results therefrom considerably absorbs the expansion
loops provided for the conductors. In this way, said loops can no longer
completely fulfill the role for which they are provided. Moreover on orbit
and in phase of eclipse, the frame and the flexible support expand and
contract differently. The springs for assembly of the flexible support on
its frame must therefore be able to absorb considerable variations in
length without introducing too great a stress on the flexible support.
Furthermore, for the resonance frequency of the flexible support to be
substantially the same in each compartment of the frame, or in any case
for it not to drop below a minimum value corresponding to a value
determined by the thickness of the frame and the vibrations to which the
generator is subjected, it is indispensable that the tension can be
distributed uniformly in each compartment, from one set of springs to the
opposite set. To this end, the intermediate uprights must leave the
support free, parallel to its plane. Experience shows that these uprights
are, however, not infinitely rigid and that they themselves start to
vibrate. The two elements of the same upright can touch each other, thus
gripping the flexible support and preventing it from moving parallel to
the direction of its tension. Consequently, the frequency in the central
compartments is increased with respect to the nominal value whilst the
frequency in the end compartments directly connected to the springs
reduces with respect to the nominal value whilst the frequency in the end
compartments directly connected to the springs reduces with respect to the
nominal value. In consequence, the amplitudes of the displacements of the
flexible support perpendicularly to its plane (which vary inversely
proportionally to the square of the frequency) increase in the end
compartments and, at these locations, the flexible support of a frame may
bump against the flexible support of the adjacent frames or against the
structure of the body of the satellite. In this way, such a flexible
support assembly in the frame by means of end springs, causes:
a strict dependence between the frequency desired for the flexible support
and the geometry of the interconnection loop conductors;
a strict dependence between the frequency desired for the flexible support
and the structural dimensions of the frame;
a considerable difficulty in maintaining, in each compartment, the
frequences of the flexible support within the limits centered around the
desired nominal value or, in any case, above a minimum value (in order to
effect a decoupling of resonance frequency between the solar panel and the
body of the satellite).
The second known mode of assembling a flexible support in its frame
consists in providing, inside the frame, a trellis structure stretched in
the manner of the strings of a tennis racquet. The flexible substrate,
itself carrying the solar cells, is then adhered to the stretched trellis.
The advantage of this second mode of assembly over the first lies in the
fact that it eliminates the permanent tension in the supple support and
therefore the elongations of the conductors interconnecting the cells.
Moreover, in this case, each skin compartment delimited in the frame by
transverse stiffeners, presents a resonance frequency which is
substantially identical to the desired nominal value. On the other hand,
the drawback of this second mode of assembly lies in that any dynamic
deformation in flexion of the uprights of the frame induces considerable
variations in tension in the stretched trellis and therefore in the
flexible support, these variations in tension being able to occur during
very short intervals of time. A phenomenon of banging therefore often
appears which deteriorates the network of the solar cells.
It is an object of the present invention to remedy the drawbacks of the
known panels for solar generators. The invention enables panels to be
obtained in which the flexible support is not subjected to any tension,
whilst presenting the necessary rigidity for avoiding too considerable
displacements transversely to its plane.
To this end, the present invention relates to a generator for producing
electrical energy from solar energy, mounted on board an artificial
satellite and constituted by a plurality of pivoted panels, stacked but
unfoldable, each of which comprises a thick frame inside which is disposed
a thin flexible support carrying solar cells, said frame comprising
intermediate stiffeners connecting two opposite sides of the frame,
wherein each panel comprises, between two intermediate stiffeners and
between the end intermediate stiffeners and the sides of the frame
there-opposite, a plurality of wide, flat, auxiliary stiffeners,
transverse with respect to the intermediate stiffeners and on which said
flexible support is fixed at least partially.
In this way, due to the rigidity of said auxiliary stiffeners and to their
support on the sides of the frame and/or on the intermediate stiffeners,
the displacements of the flexible support, perpendicularly to its plane,
are considerably hindered.
Said solar cells being disposed in lines and columns on the flexible
support, the auxiliary stiffeners are preferably of width substantially
equal to that of a row of said cells. The cells of each row may then rest
flat, via the flexible support, either on one auxiliary stiffener, or
astride two adjacent stiffeners.
Each auxiliary stiffener is advantageously formed by a section in the form
of a rectangular omega and the flexible support is fixed, for example by
adhesion, on the opposite flat flanges of said section. In this case, it
is also advantageous if the sides of the thick frame and the intermediate
stiffeners are themselves each constituted by two sections of rectangular
omega cross-section, the cavities of which are opposite and which are
assembled by their flanges. In this way, the ends of the auxiliary
stiffeners may be fixed on said flanges for assembling the sides of the
frame or the intermediate stiffeners.
In an advantageous embodiment of the invention, the frame is formed of two
superposable shells, each being made in one piece and comprising sides and
intermediate stiffeners having a rectangular omega cross-section. Such
shells may be obtained by moulding a structure of resistant fibres, for
example of carbon or boron, coated with synthetic resin. These two shells
may be identical and assembled by adhesion. To increase the rigidity of
the assembly, a reinforcement, for example a honeycomb arrangement, may
preferably be provided inside the sides of the frame and/or the
intermediate stiffeners.
The auxiliary stiffeners may be either securely connected to one of the
shells or may be integral with one of said shells at the moment of
manufacture thereof. In both cases, they may present the same composite
structure as the sides and intermediate stiffeners.
The flexible support of the solar cells may either be in one piece for all
the frame, or be composed of a plurality of parts, each of which covers a
frame compartment, defined by two adjacent intermediate stiffeners or by a
side of the frame and the end intermediate stiffener opposite.
The invention will be more readily understood on reading the following
description, with reference to the accompanying drawings, in which:
FIG. 1 is a schematic representation of a solar generator of the type to
which the present invention relates.
FIG. 2 shows a perspective view of a panel, according to the invention, for
the generator of FIG. 1.
FIG. 3 is an enlarged perspective view, with parts torn away, of part of
the panel of FIG. 2.
FIG. 4 is an exploded view in perspective showing the structure of the
frame of the panel of FIG. 2.
FIG. 5 is an enlarged perspective view illustrating the fixing of the
auxiliary stiffeners on the uprights and intermediate transverse
stiffeners of the frame of the panel of FIG. 2.
FIG. 6 illustrates a variant embodiment of the structure of the panel of
FIG. 2.
FIG. 7 illustrates in perspective, with parts torn away, part of the panel
obtained according to FIG. 6.
FIG. 8 illustrates a detail of the panel of FIGS. 6 and 7.
FIG. 9 illustrates, in perspective, a detail of a variant embodiment of a
panel for a solar generator according to the invention.
FIG. 10 shows, in perspective, an embodiment of the sections used in the
manufacture of the panels illustrated in FIGS. 2 to 9.
FIG. 11 gives a variant embodiment of a frame, according to the invention,
for the solar generator of FIG. 1.
In these Figures, identical references designate like elements.
Referring now to the drawings, the solar generator shown schematically in
FIG. 1, is intended to be mounted on a satellite, of which only a portion
1 of the outside wall has been shown. This solar generator comprises a
plurality of identical panels 2,3,4,5 and 6, each provided with a thick
peripheral frame 7. Inside this frame 7 is disposed an insulating flexible
support 8, for example made of synthetic material bearing the registered
Trade Mark KAPTON. This flexible support 8 is disposed substantially in
the median plane of the thick frame 7 and on one of its faces it carries
solar cells 9. The panel 2 is fixed to the wall 1 of the satellite, the
panel 3 is pivotally mounted on panel 2, panel 4 on panel 3, and so on,
the pivots being located alternately on one side and the other of the
panels. These panels are pivoted via complementary pivot fittings 10
carried by the frames and through which pins 11 pass.
When the solar generator is not in use, the panels 2 to 6 are folded on one
another, in the manner shown in FIG. 1, their frames 7 being superposed
and in contact with one another. On the other hand, when it is desired to
use the generator of FIG. 1, the panels 2 to 6 are unfolded by pivoting
them about pivots in order to direct the solar cells 9 towards the sun.
It is readily appreciated that in folded position (cf. FIG. 1), when the
generator is subjected to considerable vibrations (for example at the
moment of launching of the satellite 1), it is important that the possible
movement of the supports 8 perpendicularly to their plane be shorter than
the thickness of the frames 7, in order to avoid any banging against
adjacent supports 8.
As has been explained hereinabove, in the prior art, this was attempted by
subjecting the supports 8 to strong tensions in their plane, with the
drawbacks mentioned.
FIGS. 2 to 11 illustrate embodiments of solar panels according to the
invention in which the supports 8 are prevented from banging one another,
without being subjected to considerable tensions in their plane.
FIG. 2 shows a plan view in perspective of a panel (which may be any one of
panels 2 to 6 of FIG. 1), of rectangular form.
The frame 7 of this panel 2 has two longitudinal sides 13 and 14 on which
are fixed the pivot fittings 10, and two transverse sides 15 and 16. These
sides 13,14,15 and 16 are thick and, inside this frame, approximately in
the median plane of the frame, there is disposed a flexible support 8 made
of KAPTON, on one face of which are arranged interconnected solar cells 9.
This frame comprises, moreover, stiffeners 17 and 18 (cf. FIG. 4) parallel
to sides 15 and 16 of the frame and securely connected at their ends to
sides 13 and 14 respectively. The stiffeners 17 are disposed on the side
of the face of the support 8 carrying the cells 9, whilst the stiffeners
18 are disposed on the opposite side of said support 8. The stiffeners 17
and 18 are disposed opposite each other in two's.
FIG. 4 shows an advantageous embodiment of the frame 7 of the panel of FIG.
2 an its stiffeners 17 and 18.
The frame 7 of FIG. 4 is formed by two superposable identical halves 7a and
7b. The sides 13a, 14a, 15a and 16a of the frame half 7a, as well as the
stiffeners 17 fast with this frame half, are formed by sections of
rectangular omega cross-section, the flat flanges of which are coplanar.
Similarly, the sides 13b, 14b, 15b and 16b of flame 7b as well as
stiffeners 18 are formed by rectangular omegas whose flat flanges are
coplanar. In the frame part 7b, the sides 15b, 16b and the stiffeners 18
determine compartments 19 in which are disposed, as shown in FIG. 3,
auxiliary stiffeners 20 parallel to sides 13b and 14b. These auxiliary
stiffeners 20 are also in the form of rectangular omega sections fixed by
their ends to the flat flanges of two adjacent intermediate stiffeners 18
or of a stiffener 18 and the corresponding side 15b or 16b. The cavities
of the auxiliary stiffeners 20 are directed in the same direction as the
cavities of sides 13b, 14b, 15b and 16b and the intermediate stiffeners
18.
On the flat flanges of the auxiliary stiffeners 20, are fixed, at the
moment of assembly of these auxiliary stiffeners 20 in the corresponding
compartments 19, portions of flexible support 8 corresponding to the
dimensions of said compartments. The portions of flexible support 8 may be
adhered to the auxiliary stiffeners 20, at least in their major part,
whilst the edges of said skin portions are gripped between the flanges of
the corresponding omega sections.
The two frame parts 7a and 7b are then assembled together so that the
sectioned elements which correspond to one another form in two's a hollow
element of rectangular or square section. When the parts 7a and 7b are
assembled, a reinforcement 21, composed of a honeycomb structure, may be
provided, which is housed inside the corresponding sides 13a,13b, 14a,14b,
15a,15b and 16a,16b of the two frame parts 7a and 7b. These two frame
parts 7a and 7b may each be formed by a shell in one piece and the two
shells are assembled by adhesion. The honey-comb structure 21 stabilises
the walls of the frame and improves the rigidity thereof. The angle
fittings 10 are secured in the two shells when the frame is assembled.
As shown in FIG. 5, the stiffeners 20 comprise shims 22 at their ends.
In this embodiment, the transverse sections which correspond to one another
from one shell to the other, i.e. sections 17,18,15a 15b and 16a,16b are
firstly assembled by their flanges 23, after which the auxiliary
stiffeners 20 are fixed for example by lacing, riveting or any other means
on said flanges 23 of said sections. In this way, the periphery of the
support 8 is gripped between these flanges 23 and the ends, provided with
shims 22, of the auxiliary stiffeners 20.
In the embodiment described with reference to FIGS. 3,4 and 5, the support
8 was divided into as many parts as there were compartments 19. FIGS. 6,7
and 8 illustrate an embodiment in which the support 8 may be in one piece.
As shown in FIG. 6, this variant embodiment comprises, as before, two
parts 7a and 7b to be assembled together. However, in this embodiment,
shims 24 are provided which completely fill the cavity of each omega
section forming the uprights of the frame parts 7a and 7b, as well as
shims 25 completely filling the intermediate stiffeners 17 and 18. Thus,
when the two parts 7a and 7b of the frame are assembled, said parts may
imprison the one-piece support 8 therebetween. Solar cells 9 are then
adhered in the spaces delimited between the intermediate stiffeners 17 and
between said stiffeners and the sides 15a and 16a.
As shown in FIG. 8, the ends of the auxiliary stiffeners 20 are fixed by
adhesion on the lower face of the flexible support 8 and by their end
under the side flange 23 of the sections 8,15b or 16b.
In the variant embodiment shown in FIG. 9, the lower shell 7b of the frame
7 is such that the auxiliary stiffeners 20 are integral with the rest of
said shell. Thus, in this embodiment, the lower part 7b of the frame is
formed by one casting which comprises the sides 13b, 14b, 15b and 16b, the
intermediate stiffeners 18 and also the auxiliary stiffeners 20. In this
case, the flexible support 8 may either be in one part or in as many parts
as there are compartments.
FIG. 10 illustrates how the shells 7a and 7b intended for forming a frame 7
can be obtained in one piece. These shells are obtained by moulding
materials such as fabrics reinforced with carbon fibres or any other type
of high characteristic fibres, impregnated with resin. This Figure shows
that the fibres may be orientated in different combinations (intersecting
and woven fibres, longitudinal fibres) to give the section, generally or
locally, according to requirements, the desired characteristics of
resistance and rigidity.
Of course, although in the embodiments described with reference to FIGS. 3
to 10 the possibility has been mentioned of obtaining frames 7 by
associating two shells 7a and 7b, it is obvious that the frame could,
according to the invention, also be constituted by an assembly of square
tubes 26 and fittings 27 as shown schematically in FIG. 11.
The structure of panels for a solar generator according to the invention is
therefore seen to eliminate the drawbacks of the known frames with support
under tension or with support adhered to a trellis under tension. Due to
the auxiliary stiffeners 20 carrying the flexible support, the design and
dimensions of the flexible support (as far as both the network of solar
cells with the interconnectors and the frequencies of the support in each
compartment are concerned) may be distinguihed from those of the frame.
The invention therefore allows a simple adaptation to all types of
satellites and launchers whatever the specific vibratory conditions. The
frame obtained from two moulded shells assembled together is particularly
adapted to the mode of supporting the network of cells 9 by the
rectangular omega stiffeners and to the use of resins reinforced with
fibres such as carbon, boron fibres . . . Furthermore, the structure of
the frame according to the invention allows the sections to be reinforced
by a honeycomb-structured core disposed between at least a part of the two
shells, this enabling the resistance of the frame to be locally or
generally improved.
The width 1 of an intermediate stiffener 20 is preferably substantially
equal to the width d of the solar cells 9. Each row of cells may then be
arranged so as to rest on one stiffener 20 or astride two adjacent
stiffeners 20, the cells being disposed in lines and in columns.
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