CN112865700A - Power supply system for satellite and satellite - Google Patents

Power supply system for satellite and satellite Download PDF

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Publication number
CN112865700A
CN112865700A CN202110265295.5A CN202110265295A CN112865700A CN 112865700 A CN112865700 A CN 112865700A CN 202110265295 A CN202110265295 A CN 202110265295A CN 112865700 A CN112865700 A CN 112865700A
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CN
China
Prior art keywords
optical element
satellite
solar cell
power supply
supply system
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Pending
Application number
CN202110265295.5A
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Chinese (zh)
Inventor
冯田雨
陈雪芹
郭金生
张冀鹞
陈天星
陈健
李化义
王峰
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Harbin Institute of Technology
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Harbin Institute of Technology
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Filing date
Publication date
Application filed by Harbin Institute of Technology filed Critical Harbin Institute of Technology
Priority to CN202110265295.5A priority Critical patent/CN112865700A/en
Publication of CN112865700A publication Critical patent/CN112865700A/en
Pending legal-status Critical Current

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    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02S—GENERATION OF ELECTRIC POWER BY CONVERSION OF INFRARED RADIATION, VISIBLE LIGHT OR ULTRAVIOLET LIGHT, e.g. USING PHOTOVOLTAIC [PV] MODULES
    • H02S40/00—Components or accessories in combination with PV modules, not provided for in groups H02S10/00 - H02S30/00
    • H02S40/20—Optical components
    • H02S40/22—Light-reflecting or light-concentrating means
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/34—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering
    • H02J7/35—Parallel operation in networks using both storage and other dc sources, e.g. providing buffering with light sensitive cells
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/50—Photovoltaic [PV] energy
    • Y02E10/52—PV systems with concentrators

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  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Photovoltaic Devices (AREA)

Abstract

The embodiment of the invention discloses a power supply system for a satellite, which comprises: a solar cell for converting received light into electric energy, the solar cell being fixedly disposed on a main body of the satellite; an optical element, wherein the light ray changes the propagation direction when entering the optical element and exits from the optical element, and the optical element is used for receiving the incident light ray from the sun and enabling the exiting light ray to propagate towards the solar cell slice; the driving mechanism is used for driving the optical element to change the direction relative to the main body of the satellite when the direction relative to the sun changes during the flight of the satellite, so that the emergent ray always propagates towards the solar cell.

Description

Power supply system for satellite and satellite
Technical Field
The invention relates to the technical field of satellite power supply, in particular to a power supply system for a satellite and the satellite.
Background
The satellite generally needs to convert solar energy into electric energy by using a solar cell to supply power.
At present, with the increase of the integration level of the satellite functions and the improvement of the requirements on volume and weight, the requirements on the electric energy generated by the solar cell and the requirements on the volume and the size of the solar cell are more and more strict, and the output power needs to be improved as much as possible within a limited size. In order to obtain higher electric energy output power on a satellite with a limited volume, an unfolded solar cell design is generally adopted, specifically, a plurality of solar cells are mounted on a structural plate with an unfolding and locking mechanism, the effective area of the solar cells is increased by converting the plurality of solar cells from a folded state to an unfolded state, and the whole solar cells need to be unfolded relative to the main body of the satellite so as to be beneficial to receiving solar rays.
However, in the above structure, cables need to be designed between the whole of the plurality of solar cells and the satellite main body and between the deployable solar cells, when the whole of the plurality of solar cells is extended relative to the satellite main body and between the deployable solar cells, the cable direction needs to be designed reasonably, so as to prevent the cable from being hooked with the external structure of the satellite, and the influence of cable bending and cable stress on extension and extension needs to be considered; meanwhile, the problem of cable space environment protection is also considered when the cable is designed outside the satellite, the requirements for the design and final assembly of the whole satellite are high, and the manual workload in the production process of the final assembly of the satellite is increased. Particularly, for commercial communication satellites, the required power is high, and a plurality of solar cells are needed to provide energy for the satellites, so that the problems are more prominent.
Disclosure of Invention
In order to solve the above technical problems, embodiments of the present invention desirably provide a power supply system for a satellite and a satellite, which can avoid the cable and the satellite external structure hooking and the cable bending and cable stress influence on the outward expansion and the outward expansion caused by the overall extension of a plurality of solar cells relative to a satellite main body and the extension between the solar cells, and generate energy to the greatest extent to provide electric energy for the satellite.
The technical scheme of the invention is realized as follows:
in a first aspect, an embodiment of the present invention provides a power supply system for a satellite, where the power supply system includes:
a solar cell for converting received light into electric energy, the solar cell being fixedly disposed on a main body of the satellite;
an optical element, wherein the light ray changes the propagation direction when entering the optical element and exits from the optical element, and the optical element is used for receiving the incident light ray from the sun and enabling the exiting light ray to propagate towards the solar cell slice;
the driving mechanism is used for driving the optical element to change the direction relative to the main body of the satellite when the direction relative to the sun changes during the flight of the satellite, so that the emergent ray always propagates towards the solar cell.
In a second aspect, an embodiment of the present invention provides a satellite, including:
the power supply system of the first aspect;
power consuming components fixedly arranged on the body of the satellite,
the power consumption component is connected with the solar cell through a cable, so that the electric energy converted by the solar cell can be supplied to the power consumption component.
The embodiment of the invention provides a power supply system for a satellite and the satellite; because the solar cell piece needing to be connected with the cable is fixedly arranged on the main body of the satellite, the cable can be kept fixed relative to the main body of the satellite, the problems that the cable is hooked with an external structure of the satellite and the cable is bent are avoided, incident light can irradiate the solar cell piece through the optical element in the power supply system, and meanwhile, when the direction of the driving mechanism in the power supply system relative to the sun changes in the operation process of the satellite, the driving mechanism drives the optical element to change the direction relative to the main body of the satellite, so that emergent light always transmits towards the solar cell piece, the solar cell piece can always receive more solar light, and electric energy can be continuously output.
Drawings
Fig. 1 is a schematic structural diagram of a power supply system for a satellite according to an embodiment of the present invention.
Fig. 2 is a schematic diagram illustrating an optical element of a power supply system for a satellite in a recovery state according to an embodiment of the present invention.
Fig. 3 is a schematic diagram of an optical element of a power supply system for a satellite according to an embodiment of the present invention.
Fig. 4 is a schematic view of a reflective element according to an embodiment of the present invention.
Fig. 5 is a schematic diagram of a refractive element according to an embodiment of the invention.
Fig. 6 is a schematic structural diagram of a tri-fold reflective device according to an embodiment of the present invention.
Fig. 7 is a schematic structural diagram of a three-fold refractive element according to an embodiment of the invention.
Fig. 8 is a schematic diagram of positions of the emergent light and the solar cell according to the embodiment of the invention.
FIG. 9 is a schematic diagram of incident light and the position of an optical element according to an embodiment of the invention.
Fig. 10 is a schematic structural diagram of a satellite according to an embodiment of the present invention.
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.
Referring to fig. 1, a power supply system 10 of a satellite 1 according to an embodiment of the present invention is shown, where the power supply system 10 may include:
a solar cell sheet 102 for converting received light into electric energy, the solar cell sheet 102 being fixedly disposed on the main body 101 of the satellite 1;
an optical element 103, wherein when light enters the optical element 103, the light changes the propagation direction and exits from the optical element 103, and the optical element 103 is used for receiving an incident light i from the sun and making an emergent light e propagate towards the solar cell sheet 102;
a driving mechanism 104, wherein the driving mechanism 104 is configured to drive the optical element 103 to change the orientation relative to the main body 101 of the satellite 1 when the orientation relative to the sun changes during the flight of the satellite 1, so that the emergent ray e always propagates toward the solar cell 102. As shown in particular in fig. 1, the drive mechanism 104 drives a lever 105 articulated to the optical element 103 to produce a movement of the optical element 103.
It can be understood that, as shown in fig. 1, when the irradiation direction of the solar ray is changed due to the flight of the satellite 1, that is, when the incident ray i is changed from the direction indicated by the solid arrow in the figure to the direction indicated by the dashed arrow in the figure, in order to ensure that the optical element 103 can receive the incident ray and make the emergent ray e irradiate on the solar cell sheet 102, the optical element 103 can be driven by the driving mechanism 104 such that, as the direction of the incident ray i is changed, the optical element 103 can be changed from the position i (indicated by the solid line in the figure) to the position ii (indicated by the dashed line in the figure) so that the emergent ray e still propagates on the solar cell sheet 102.
Because the solar cell piece needing to be connected with the cable is fixedly arranged on the main body of the satellite, the cable can be kept fixed relative to the main body of the satellite, the problems that the cable is hooked with an external structure of the satellite and the cable is bent are avoided, incident light can irradiate the solar cell piece through the optical element in the power supply system, and meanwhile, when the direction of the driving mechanism in the power supply system relative to the sun changes in the operation process of the satellite, the driving mechanism drives the optical element to change the direction relative to the main body of the satellite, so that emergent light always transmits towards the solar cell piece, the solar cell piece can always receive more solar light, and electric energy can be continuously output.
In order to save the launching space during launching of the satellite 1, as shown in fig. 2, the optical element 103 should be capable of being folded at the side of the satellite 1 and kept integral with the satellite 1; in order to provide electrical energy to ensure proper operation of the satellite 1 when the satellite 1 has reached a predetermined orbit in space, the optical element 103 should be capable of abduction with respect to the body 101 of the satellite 1 and allow the solar rays to pass onto the optical element 103, as shown in fig. 1. Thus, the optical element 103 may be configured to be switchable with respect to the body 101 of the satellite 1 between a deployed state, as shown in fig. 1, in which the optical element 103 is distant from the body 101 of the satellite 1 to receive incident light from the sun, and a retracted state, as shown in fig. 2, in which the optical element 103 is close to the body 101 of the satellite 1 to reduce the space occupied by the satellite 1.
Referring to fig. 2, the power supply system 10 further includes a locking mechanism 201, when the optical element 103 is in the recovery state, the locking mechanism 201 can lock the optical element 103 to the main body 101 of the satellite 1 to prevent the optical element 103 from being damaged due to vibration when the satellite 1 is launched, the locking mechanism 201 may specifically include components such as a spring and a fixing pin, and may also include components such as a screw and a pressing screw sleeve, and of course, in an embodiment of the present invention, the locking mechanism 201 is not limited to the above components. When the satellite 1 reaches a designated orbit, the locking mechanism 201 can also unlock so that the optical element 103 is unfolded and receives incident solar rays, and the emergent rays are transmitted to the solar cell sheet 102, thereby achieving the purpose of supplying electric energy to the satellite 1.
In the embodiment of the present invention, the unlocking of the locking mechanism 201 may be achieved by sending an initiating explosive device control command to ignite the initiating explosive device, driving a cutter inside the initiating explosive device by the pressure generated by the ignition of the initiating explosive device, and cutting off the locking mechanism 201 to unlock the optical element 103.
In a specific embodiment of the present invention, referring to fig. 3, the optical element 103 may include a plurality of plate-shaped members 301, the plurality of plate-shaped members 301 being connected by hinges 302 therebetween such that the optical element 103 can be switched between an unfolded state in which the plurality of plate-shaped members 301 are unfolded with respect to each other to receive incident light from the sun, and a folded state in which the plurality of plate-shaped members 301 are folded with respect to each other to reduce a space occupied by the optical element 103.
In order to enable the optical element 103 to move to different angular positions depending on the azimuth of the sun to receive incident light, the optical element 103 can be rotated about at least one pivot with respect to the body 101 of the satellite 1 when driven by the driving mechanism 104, see fig. 1, and as shown in detail in fig. 1, the optical element 103 can be rotated about three pivots. It should be noted that, in the embodiment of the present invention, the number of the pivots is not limited to three as shown in fig. 1, and the positional relationship between the pivots is not limited to that shown in fig. 1, for example, the two pivots may be perpendicular to each other.
In the embodiment of the present invention, in order to enable the incident light ray incident to the optical element 103 to be irradiated onto the solar cell sheet 102 after the propagation direction of the incident light ray is changed by the optical element 103, referring to fig. 4 and 5, the optical element 103 may be a reflecting element 601 for reflecting the light ray or a refracting element 701 for refracting the light ray.
That is, as shown in fig. 4, when the incident light i (indicated by a dotted arrow in the figure) is irradiated onto the reflective element 601 and reflected, the emergent light e (indicated by a solid arrow in the figure) can be irradiated onto the solar cell 102.
As shown in fig. 5, when the incident light i (shown by a dotted arrow) is incident on the refractive element 701 and refracted, the emergent light e (shown by a solid arrow) can be incident on the solar cell 102.
Preferably, in an embodiment of the present invention, the refraction element 701 may be a transparent lens plate to implement refraction of the solar light.
It should be noted that, in the actual design process, the reflective element 601 and/or the refractive element 701 may be selected for use according to the attitude requirement of the satellite 1.
In case the optical element 103 is a reflecting element 601 for reflecting light rays and the optical element comprises a plurality of plate-like members 301, the light reflecting surfaces of said plurality of plate-like members 301 may be arranged to reflect the incoming light rays i in a mutually different way, such that each plate-like member is capable of propagating outgoing light rays e towards the solar cell sheet, when said plurality of plate-like members 301 are in the same plane as shown in fig. 6.
In the case where the optical element 103 is a refractive element 701 for refracting light and the optical element includes a plurality of plate-shaped members 301, the plurality of plate-shaped members 301 may be arranged to refract incident light differently from each other so that each plate-shaped member can propagate outgoing light toward the solar cell sheet when the plurality of plate-shaped members 301 are in the same plane as shown in fig. 7.
In order to enable the solar cell sheet 102 to output more energy to meet the normal operation of the satellite 1, referring to fig. 8, corresponding to the condition that the whole solar cell sheet 102 receives the emergent ray e when the whole emergent ray e does not propagate to the solar cell sheet 102, the driving mechanism 104 drives the optical element 103 to enable the propagation direction of the emergent ray e to be as perpendicular as possible to the solar cell sheet 102 under the condition that the whole solar cell sheet 102 receives the emergent ray e, as specifically shown in fig. 8, the optical element 103 is driven from a position I (shown by a dotted line) to a position II (shown by a dotted line), wherein the angle between the emergent ray e (shown by the solid line) generated by the optical element 103 at the position I and the solar cell sheet 102 is alpha, and the emergent ray e (shown by the dotted line) generated by the optical element 103 at the position II and the solar cell sheet 102 is alpha The angle between them is alpha' > alpha. It can be understood that since the emergent ray e can be regarded as a parallel ray, when the whole solar cell piece 102 can receive the emergent ray e, the more the emergent ray e is perpendicular to the solar cell piece 102, the more the solar cell piece 102 can receive more rays and thus generate more electric energy.
On the other hand, referring to fig. 9, in response to only a partial region of the solar cell sheet 102 receiving the outgoing light ray e when all of the outgoing light rays e are transmitted to the solar cell sheet 102, the driving mechanism 104 drives the optical element 103 such that the reflecting surface of the optical element 103 is perpendicular to the incoming light ray I as much as possible under the condition that all of the outgoing light rays e are transmitted to the solar cell sheet 102, and as specifically shown in fig. 9, the optical element 103 is driven from a position I (shown by a solid line) to a position II (shown by a dotted line), wherein an angle between the plane reflecting surface of the optical element 103 at the position I and the incoming light ray I is θ, and an angle θ' > θ between the plane reflecting surface of the optical element 103 at the position II and the incoming light ray I. It can be understood that the more the planar reflective surface of the optical element 103 is perpendicular to the incident light ray i, the more the planar reflective surface can reflect the incident light ray i, so as to generate the more the emergent light ray e, and in the case that the emergent light ray e is all transmitted to the solar cell sheet 102, the more the solar cell sheet 102 can receive the incident light ray, so as to generate the more electric energy.
Referring to fig. 10, an embodiment of the present invention further provides a satellite 1, where the satellite 1 may include:
the power supply system 10 described in the previous solution;
a power consuming component 20 fixedly arranged on the body 101 of the satellite 1,
the power consumption component 20 and the solar cell 102 are connected by a cable 30, so that the electric energy converted by the solar cell 102 can be supplied to the power consumption component 20.
It should be noted that: the technical schemes described in the embodiments of the present invention can be combined arbitrarily without conflict.
The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present invention, and all the changes or substitutions should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.

Claims (10)

1. A power supply system for a satellite, the power supply system comprising:
a solar cell for converting received light into electric energy, the solar cell being fixedly disposed on a main body of the satellite;
an optical element, wherein the light ray changes the propagation direction when entering the optical element and exits from the optical element, and the optical element is used for receiving the incident light ray from the sun and enabling the exiting light ray to propagate towards the solar cell slice;
the driving mechanism is used for driving the optical element to change the direction relative to the main body of the satellite when the direction relative to the sun changes during the flight of the satellite, so that the emergent ray always propagates towards the solar cell.
2. The power supply system of claim 1, wherein the optical element is configured to be switchable relative to the body of the satellite between a deployed state in which the optical element is distal from the body of the satellite to receive incident light from the sun, and a stowed state in which the optical element is proximal to the body of the satellite to reduce the space occupied by the satellite.
3. The power supply system of claim 2, further comprising a locking mechanism capable of locking the optical element to the body of the satellite when the optical element is in the retracted state.
4. The power supply system of claim 1, wherein the optical element comprises a plurality of plate-like members connected by hinges such that the optical element is transitionable between an unfolded state in which the plurality of plate-like members are unfolded relative to each other to receive incident light from the sun and a folded state in which the plurality of plate-like members are folded relative to each other to reduce a space occupied by the optical element.
5. The power supply system of claim 1, wherein the optical element rotates relative to the body of the satellite about at least one pivot when driven by the drive mechanism.
6. A power supply system according to any one of claims 1 to 5, characterized in that the optical element is a reflective element for reflecting light or a refractive element for refracting light.
7. The power supply system of claim 6, wherein said reflective element has a planar reflective surface.
8. The power supply system according to claim 7, wherein the driving mechanism drives the optical element such that the traveling direction of the outgoing light is as perpendicular as possible to the solar cell sheet while ensuring that the outgoing light is received by the entire solar cell sheet, in response to the entire solar cell sheet receiving the outgoing light when not all of the outgoing light is transmitted to the solar cell sheet.
9. The power supply system of claim 7, wherein the drive mechanism drives the optical element such that the planar reflective surface of the optical element is as perpendicular as possible to the incident light rays while ensuring that the outgoing light rays are all transmitted to the solar cell sheet, in response to only a portion of the area of the solar cell sheet receiving the outgoing light rays when the outgoing light rays are all transmitted to the solar cell sheet.
10. A satellite, comprising:
the power supply system according to any one of claims 1 to 9;
power consuming components fixedly arranged on the body of the satellite,
the power consumption component is connected with the solar cell through a cable, so that the electric energy converted by the solar cell can be supplied to the power consumption component.
CN202110265295.5A 2021-03-11 2021-03-11 Power supply system for satellite and satellite Pending CN112865700A (en)

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CN202110265295.5A CN112865700A (en) 2021-03-11 2021-03-11 Power supply system for satellite and satellite

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Application Number Priority Date Filing Date Title
CN202110265295.5A CN112865700A (en) 2021-03-11 2021-03-11 Power supply system for satellite and satellite

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CN112865700A true CN112865700A (en) 2021-05-28

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