阅读说明：本技术 一种柔性太阳电池翼 (Flexible solar cell wing ) 是由 段波涛 王柳 邢路 舒斌 田源 马祯 康昱 乔卫新 宋猛 付诗意 于 2020-12-03 设计创作，主要内容包括：本发明公开了一种柔性太阳电池翼,所述柔性太阳电池翼包括：至少两个太阳电池单板；所述太阳电池单板包括设置有太阳电池阵列的柔性基板和框架；所述柔性基板置于所述框架中,所述框架对所述柔性基板提供刚性支撑；相邻两个所述太阳电池单板之间通过双向卷簧铰链连接。本发明公开的柔性太阳电池翼,具有输出功率大、刚度高、展开可靠等优点。(The invention discloses a flexible solar cell wing, which comprises: at least two solar cell single plates; the solar cell single plate comprises a flexible substrate provided with a solar cell array and a frame; the flexible substrate is placed in the frame, and the frame provides rigid support for the flexible substrate; and two adjacent solar cell single plates are hinged through a bidirectional coil spring. The flexible solar cell wing disclosed by the invention has the advantages of high output power, high rigidity, reliability in unfolding and the like.)

1. A flexible solar cell wing, characterized in that it comprises: at least two solar cell single plates;

the solar cell single plate comprises a flexible substrate provided with a solar cell array and a frame;

the flexible substrate is placed in the frame, and the frame provides rigid support for the flexible substrate;

and two adjacent solar cell single plates are hinged through a bidirectional coil spring.

2. The flexible solar cell wing according to claim 1, wherein the bidirectional coil spring hinge comprises: a hinge, a rotating shaft and a coil spring;

the hinges are respectively connected with the frames of the two adjacent solar cell single plates, and the coil springs are respectively connected with the frames of the two adjacent solar cell single plates;

the rotating shaft penetrates through the hinge and the coil spring along the longitudinal direction;

the hinge rotates around the rotating shaft, and the coil spring provides unfolding pretightening force or reverse damping for the solar cell single plate.

3. The flexible solar cell wing according to claim 1, wherein the solar cell single plate is pressed against a spacecraft bulkhead by a press release device.

4. The flexible solar cell wing according to claim 3, characterized in that the compression release means comprises: an initiating explosive cutting device, a pressing line and a winder;

the winder comprises spool and torsional spring, under the flexible solar cell wing compresses tightly the state, the line one end of compressing is fixed on the spool, the other end of compressing is fixed in the firer cutting device.

5. The flexible solar cell wing according to claim 4, characterized in that the compression line is a strong steel wire or a carbon fiber rope.

6. The flexible solar cell wing according to claim 4, characterized in that the diameter of the compression wire should be smaller than 1/4 of the diameter of the compression hole.

7. The flexible solar cell wing according to claim 4,

after the spacecraft is in orbit, a ground unlocking instruction is received, the compression wire is cut off by the fire cutting device, and the scroll returns to rotate under the action of the pretightening force of the torsion spring so as to wind the compression wire into the winder;

when the pressing line is cut off, the solar cell wing is unfolded under the action of the pre-tightening force of the bidirectional coil spring hinge; when the solar cell single plates are unfolded and parallel, the in-place baffle triggers the in-place locking device, and the locking pins in the in-place locking device are inserted into the in-place locking holes of the adjacent solar cell single plates under the action of the elastic force of the springs.

8. The flexible solar cell wing according to claim 1, wherein the flexible substrate is a polyimide substrate comprising a first polyimide layer, a flexible printed board, and a second polyimide layer;

the solar cell, the isolation diode and the temperature sensor are adhered to the flexible printed board and are electrically connected to form a solar cell array;

the solar cell array is electrically connected through a printed copper wire in the flexible printed board;

the first polyimide layer, the flexible printed board provided with the solar cell array and the second polyimide layer are sequentially stacked to form the solar cell single board.

9. The flexible solar cell wing according to claim 1, wherein the frame comprises an upper frame and a lower frame, the upper frame being shape-matched to the lower frame.

10. The flexible solar cell wing according to claim 9, wherein the frame thickness is 2 mm.

Technical Field

The invention belongs to the technical field of spacecraft solar cell wings, and particularly relates to a flexible solar cell wing.

Background

The unfolded solar cell wing is an energy conversion system commonly used by a spacecraft, and directly converts solar energy into electric energy for the spacecraft to use. Rigid solar cell wings, semi-rigid solar cell wings, flexible solar cell wings and the like are common, and each structural form has advantages and disadvantages.

The span-opening structure of the rigid and semi-rigid solar cell is relatively simple, the rigidity is relatively high, but the thickness and the installation envelope of the substrate are limited, and the generated power is usually in the level of several kilowatts; the flexible solar cell wing adopts the flexible thin substrate, so that the cloth area of the solar cell wing under the same installation envelope is increased, the generated power can reach about twenty kilowatts, but the rigidity of the flexible solar cell wing is much lower than that of a rigid and semi-rigid substrate, the whole wing support needs to be improved by adopting a truss structure, and the truss structure is used for unfolding and folding, so that the unfolding and folding mechanism is complex, and the technical difficulty and risk are higher.

In China, rigid and semi-rigid solar cell wings are applied to a plurality of spacecrafts, but flexible solar cell wings cannot be applied to the spacecrafts or space power stations due to the complex unfolding and folding mechanism of the flexible solar cell wings.

Disclosure of Invention

The technical problem to be solved by the invention is as follows: the flexible solar cell wing has high power and can be applied to spacecrafts or space power stations.

In order to solve the above technical problem, the present invention discloses a flexible solar cell wing, wherein the flexible solar cell wing includes: at least two solar cell single plates;

the solar cell single plate comprises a flexible substrate provided with a solar cell array and a frame;

the flexible substrate is placed in the frame, and the frame provides rigid support for the flexible substrate;

and two adjacent solar cell single plates are hinged through a bidirectional coil spring.

Optionally, the bidirectional coil spring hinge comprises: a hinge, a rotating shaft and a coil spring;

optionally, the hinges are respectively connected with the frames of two adjacent solar cell single plates, and the coil springs are respectively connected with the frames of two adjacent solar cell single plates;

the rotating shaft penetrates through the hinge and the coil spring along the longitudinal direction;

the hinge rotates around the rotating shaft, and the coil spring provides unfolding pretightening force or reverse damping for the solar cell single plate.

Optionally, the solar cell single plate is pressed on the bulkhead of the spacecraft through a pressing and releasing device.

Optionally, the compression release device comprises: an initiating explosive cutting device, a pressing line and a winder; the winder comprises spool and torsional spring, under the flexible solar cell wing compresses tightly the state, the line one end of compressing is fixed on the spool, the other end of compressing is fixed in the firer cutting device.

Optionally, the compression line is a strength steel wire or a carbon fiber rope.

Optionally, the compression wire diameter should be less than 1/4 of the compression hole diameter.

Optionally, after the spacecraft enters the orbit, a ground unlocking instruction is received, the fire cutting device cuts off the pressing line, and under the action of the pretightening force of the torsion spring, the scroll returns to rotate to wind the pressing line into the winder; when the pressing line is cut off, the solar cell wing is unfolded under the action of the pre-tightening force of the bidirectional coil spring hinge; when the solar cell single plates are unfolded and parallel, the in-place baffle triggers the in-place locking device, and the locking pins in the in-place locking device are inserted into the in-place locking holes of the adjacent solar cell single plates under the action of the elastic force of the springs.

Optionally, the flexible substrate is a polyimide substrate, and the polyimide substrate includes a first polyimide layer, a flexible printed board, and a second polyimide layer;

the solar cell, the isolation diode and the temperature sensor are adhered to the flexible printed board and are electrically connected to form a solar cell array;

the solar cell array is electrically connected through a printed copper wire in the flexible printed board;

the first polyimide layer, the flexible printed board provided with the solar cell array and the second polyimide layer are sequentially stacked to form the solar cell single board.

Optionally, the frame includes an upper frame and a lower frame, and the upper frame is matched with the lower frame in shape.

Optionally, the frame thickness is 2 mm.

The invention has the following advantages:

on one hand, the flexible solar cell wing disclosed by the embodiment of the invention improves the rigidity of the flexible solar cell wing through the frame support and frame butt joint technology, reduces the complexity and risk of the traditional flexible solar cell wing unfolding device on the premise of meeting the high-power requirement, and improves the on-orbit use reliability of the device. In the second aspect, the adjacent solar cell panels are connected through the bidirectional coil spring hinge, so that the stability of the unfolded solar cell wing can be improved; in a third aspect, the flexible solar cell has large wing area and high power. In conclusion, the flexible solar cell wing provided by the invention has the advantages of high output power, high rigidity, reliability in unfolding and the like.

Drawings

Fig. 1 is a schematic diagram illustrating connection between single solar cells according to an embodiment of the present invention;

FIG. 2 is a schematic diagram of a connection between single solar cells according to an embodiment of the present invention;

fig. 3 is a schematic drawing showing the flexible solar cell wings folded according to the embodiment of the invention.

Detailed Description

The present invention will be described in detail below with reference to specific embodiments and with reference to the attached drawings. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

Fig. 1 is a schematic diagram of connection between single solar cells according to an embodiment of the present invention.

The flexible solar cell wing of the embodiment of the invention comprises: a schematic diagram of a connection relationship between at least two solar cell single plates and adjacent solar cell single plates is shown in fig. 1.

The solar cell single plate comprises a flexible substrate 2 provided with a solar cell array and a frame 1;

the flexible substrate 2 is arranged in the frame, and the frame 1 provides rigid support for the flexible substrate 2 to form a solar cell single plate;

two adjacent solar cell single plates are connected through a bidirectional coil spring hinge 5.

The flexible substrate is used as a core part of the solar cell single plate and used for bearing components such as solar cells and the like, and the flexibility basically comprises a flexible printed board, a base layer and the like. The flexible printed board is used for electrically connecting the battery pieces arranged on the flexible substrate to form a solar battery array.

In an alternative embodiment, the flexible substrate 2 is a polyimide substrate comprising a first polyimide layer, a flexible printed board 4 and a second polyimide layer;

the solar cell 3, the isolation diode and the temperature sensor (the isolation diode and the temperature sensor are not shown in the figure) are pasted on the flexible printed board and electrically connected to form a solar cell array; the solar cell array is electrically connected through printed copper wires in the flexible printed board 4, and power and signals between the solar cell single boards are transmitted through the flexible printed board 4; the first polyimide layer, the flexible printed board provided with the solar cell array and the second polyimide layer are sequentially stacked to form the solar cell single board.

In an alternative embodiment, the frame 1 includes an upper frame and a lower frame, the upper frame and the lower frame are matched in shape, the flexible substrate 2 is placed between the upper frame and the lower frame, the edge of the flexible substrate 2 is surrounded by the frame, and the flexible substrate 2 is tightly attached to the frame. The sandwich structure formed by the upper frame, the flexible substrate and the lower frame is a supporting structure of the solar cell single plate, and the rigidity of the solar cell single plate can be increased.

Optionally, the frame thickness is set to 2 mm.

In an alternative embodiment, as shown in fig. 2, the bidirectional wrap spring hinge 5 comprises: a hinge 51, a rotation shaft 52, and a coil spring 53; the hinges 51 are respectively connected with the frames 1 of two adjacent solar cell single plates, and the coil springs 52 are respectively connected with the frames 1 of two adjacent solar cell single plates; the rotating shaft 52 longitudinally penetrates through the hinge 51 and the coil spring 53; the hinge 51 rotates around the rotating shaft 52, and the coil spring 53 provides unfolding pre-tightening force or reverse damping for the solar cell single plate. Specifically, the coil spring 53 provides an unfolding pre-tightening force for the folding of the solar cell single plates, provides reverse damping for the unfolding of the solar cell single plates, and can improve the connection rigidity between the solar cell single plates.

On one hand, the flexible solar cell wing disclosed by the embodiment of the invention improves the rigidity of the flexible solar cell wing through the frame support and frame butt joint technology, reduces the complexity and risk of the traditional flexible solar cell wing unfolding device on the premise of meeting the high-power requirement, and improves the on-orbit use reliability of the device. In the second aspect, the adjacent solar cell panels are connected through the bidirectional coil spring hinge, so that the stability of the unfolded solar cell wing can be improved; in a third aspect, the flexible solar cell has large wing area and high power. In conclusion, the flexible solar cell wing provided by the invention has the advantages of high output power, high rigidity, reliability in unfolding and the like.

In an alternative implementation, as shown in a schematic drawing of a flexible solar cell wing shown in fig. 3, a solar cell single plate 1 is pressed against a bulkhead of a spacecraft by a pressing and releasing device, where the pressing and releasing device includes: an initiating explosive device 2, a pressing line 3 and a winder 4; the pyrotechnic cutting device 2 may inherit the use of a traditional rigid or semi-rigid pyrotechnic cutting device, requiring modification of the mounting fixing interface with the compression wire 3. The winder comprises spool 11 and torsional spring 12, and under the flexible solar cell wing compression state, 3 one ends of pressing wire are fixed on spool 11, and the other end of pressing wire 3 is fixed in fire cutting device 2.

The pressing line 3 can be made of a material with the strength more than twice that of the solar cell single plate pressing force, and optionally, the pressing line 3 is a strength steel wire or a carbon fiber rope, and the diameter of the pressing line 3 is smaller than 1/4 of the diameter of the pressing hole.

In an optional embodiment, after the spacecraft is in orbit, a ground unlocking instruction is received, the fire cutting device 2 cuts off the compression wire 3, and under the action of the pretightening force of the torsion spring 12, the scroll 11 returns to rotate to reel the compression wire 3 into the winder 4; the pyrotechnic cutting device 2 cuts off the compression wire 3 placed inside thereof. When the pressing line 3 is cut off, the solar cell wing is unfolded under the pre-tightening force of the bidirectional coil spring hinge 5; when the solar cell single plates are unfolded and parallel, the in-place baffle 6 triggers the in-place locking device, and the locking pins 8 in the in-place locking device are inserted into in-place locking holes 10 of the adjacent solar cell single plates under the action of the elastic force of the springs 9. Wherein, the in-position locking device is composed of a trigger button 7, a locking pin 8 and a spring 9.

The flexible solar cell wing adopts the flexible printed board as a substrate for supporting and transmitting electricity, devices such as a solar cell, an isolating diode, a temperature sensor and the like are adhered to the flexible printed board and are electrically connected to form a solar cell array, and the solar cell array collects and outputs current through a printed copper wire in the flexible printed board. And a thin frame with high rigidity is adopted to provide rigid support for the flexible printed board and the solar cell array to form the solar cell single board. The adjacent solar cell single plates are connected through a bidirectional coil spring hinge, and the coil spring hinge can provide unfolding torque when the solar cell wing is released and improve the stability of the unfolded solar cell wing; the frame in-place butting device is arranged in the thin frame, so that butting and locking among the thin frames are realized when the solar cell wing is unfolded in place, and the rigidity of the whole wing after being unfolded in place is improved. The solar cell wing is provided with a line pressing and releasing device, solar cell single plates are stacked, pressed and folded through pressing lines, when the rail is released, the pressing lines are cut off by a cutter, the solar cell array is unfolded under the action of the bidirectional coil springs, and the in-place butting device is triggered after the solar cell array is unfolded in place to be butted and locked in place.

It should be noted that the above description is only a preferred embodiment of the present invention, and it should be understood that various changes and modifications can be made by those skilled in the art without departing from the technical idea of the present invention, and these changes and modifications are included in the protection scope of the present invention.

The embodiments in the present description are all described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.

The above description is only for the best mode of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention.

Those skilled in the art will appreciate that the details of the invention not described in detail in this specification are well within the skill of those in the art.