CN110901959A - Passive satellite derailment device, remote sensing satellite and satellite - Google Patents
Passive satellite derailment device, remote sensing satellite and satellite Download PDFInfo
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- CN110901959A CN110901959A CN201911230645.3A CN201911230645A CN110901959A CN 110901959 A CN110901959 A CN 110901959A CN 201911230645 A CN201911230645 A CN 201911230645A CN 110901959 A CN110901959 A CN 110901959A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
- B64G1/242—Orbits and trajectories
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Abstract
The application provides a passive off-orbit device of a satellite, a remote sensing satellite and the satellite. The passive satellite derailment device comprises a derailment sail, a sheet-shaped solar power generation assembly and a conductive cable. The off-orbit sail is connected to the satellite body through a flexible traction cable; the solar power generation assembly comprises a plurality of sheet-shaped solar cells, and each sheet-shaped solar cell is arranged on the flexible traction rope at intervals; when the off-orbit sail is in a closed state, the plurality of sheet-shaped solar cells are arranged at a preset position of the satellite body in a stacking manner; when the off-orbit sail is opened and the flexible traction cable is pulled, the solar power generation assembly is arranged between the satellite body and the off-orbit sail, and the plurality of sheet-shaped solar cells are sequentially arranged along the length direction of the flexible traction cable. The conductive cable is used to connect the plurality of sheet-like solar cells in series with each other and to electrically connect the solar power generation module and the power storage device in the satellite body. The method and the device can enable the satellite body to continue to work under the condition of battery attenuation, and ensure the performance of the satellite in the end-stage service life.
Description
Technical Field
The application relates to the field of spacecraft derailment, in particular to a satellite passive derailment device, a remote sensing satellite and a satellite.
Background
Because the electric energy of the satellite is limited, the satellite can not work after the electric energy of the satellite reaches a threshold value, in the prior art, after the satellite can not work, the satellite which can not work can be directly abandoned, but the satellite which can not work can be retained in space to become space rubbish. Some satellite companies usually set passive off-orbit devices such as an off-orbit sail on the satellite in order to avoid the satellite which cannot work staying in space and becoming space debris. When the satellite normally operates, the off-orbit sail is in a closed state, when the satellite does not need to work, the satellite enters the off-orbit state, the off-orbit sail is opened, the opened off-orbit sail can increase the resistance of the satellite in circular motion, and the orbit of the satellite in operation is lower and lower (namely, the satellite is closer to the earth) until the satellite finally falls back to the earth.
The remote sensing satellite in the satellite mainly works to shoot images to the ground. For remote sensing satellites, the lower the orbit, the closer to the ground, the higher the resolution of the pictures taken. Therefore, after the remote sensing satellite enters the off-orbit stage, the shooting effect of the remote sensing satellite is more excellent as the remote sensing satellite is continuously close to the earth. However, after the satellite usually reaches an inoperable state and enters an off-orbit stage, the electric energy of the battery is very insufficient, and the remote sensing satellite cannot be supported to shoot when approaching the earth.
Disclosure of Invention
An object of the present invention is to provide a passive satellite derailment device, which can make the satellite in the derailment phase continue to work under the condition of battery attenuation, so as to ensure the performance of the satellite in the end life as much as possible.
In a first aspect, an embodiment of the present application provides a satellite passive off-orbit device, which includes:
the off-orbit sail is connected to the satellite body through a flexible traction cable;
a solar power generation module including a plurality of sheet-shaped solar cells, each of the sheet-shaped solar cells being disposed on the flexible traction cable at an interval; the plurality of sheet-shaped solar cells are arranged at a preset position of the satellite body in a stacking mode when the derail sail is in a closed state; when the off-orbit sail is opened and the flexible traction cable is pulled, the solar power generation assembly is arranged between the satellite body and the off-orbit sail, and the plurality of sheet-shaped solar cells are sequentially arranged along the length direction of the flexible traction cable;
and the conductive cable is used for connecting the plurality of sheet-shaped solar cells in series with each other and electrically connecting the solar power generation assembly and the power storage device in the satellite body.
In the implementation process, the passive satellite derailment device is arranged on the satellite body, and after the derailment sail is opened, the derailment sail can be separated from the satellite body but drifts in the space under the traction of the flexible traction cable. Set up the solar energy power generation subassembly including a plurality of slice solar cell on flexible traction cable, because illumination resource in the space is abundant, flexible traction cable is easy rotatory simultaneously, so slice solar cell can accept the sunlight of each illumination angle and generate electricity, and the electric energy that will convert simultaneously is carried for the power storage device of satellite body through electrically conductive cable. Because the electric energy input of the satellite body is increased, the satellite body can still continue to work under the condition of battery attenuation, and therefore the performance of the satellite in the end-stage service life can be guaranteed as far as possible.
In a possible embodiment, the electrically conductive cable is integrated in the flexible traction cable.
In the implementation process, the conductive cable is integrated in the flexible traction cable, so that the flexible traction cable and the conductive cable can be prevented from being wound with each other, and the structure of the satellite passive off-orbit device can be simplified.
In one possible embodiment, the satellite passive derailment apparatus further comprises:
and the storage cabin is arranged on the satellite body and used for accommodating the off-orbit sail, the flexible traction cable and the solar power generation assembly when the off-orbit sail is in a closed state.
In one possible embodiment, the storage compartment comprises:
the battery piece bin is positioned at the bottom of the storage cabin, a plurality of sheet-shaped solar batteries in the solar power generation assembly are stacked in the battery piece bin one by one, and the upper and lower surfaces of the sheet-shaped solar batteries are parallel to the bottom surface of the battery piece bin; when the off-rail sail is opened and the flexible traction cable is tensioned, the sheet-shaped solar cells on the flexible traction cable are moved out of the cell bin at an angle parallel to the bottom surface of the cell bin;
and the sail body bin is arranged at the upper part of the battery piece bin and is communicated with the outlet of the storage bin.
In the implementation process, the sail body bin for containing the off-rail sail is arranged at an outlet of the storage cabin, when the off-rail sail needs to be opened, the off-rail sail can be firstly separated from the storage cabin and enters space, and the solar power generation assembly and the off-rail sail are connected through the flexible traction cable.
In a possible implementation manner, limiting devices for limiting the moving track of the sheet-shaped solar cell are arranged on the pair of oppositely arranged inner side faces;
the limiting device comprises two oppositely arranged sliding chutes; the depth of the sliding groove is the same as that of the battery piece bin;
a plurality of sheet-shaped solar cells are stacked in a space defined by the two chutes.
In the implementation process, the limiting device is used for limiting the sliding track of each sheet-shaped solar cell in the solar power generation assembly, after the off-orbit sail enters the space, under the extension action of the flexible traction rope, the sheet-shaped solar cells are not interfered with each other, the angles of the sheet-shaped solar cells sliding out of the cell bin under the limitation of the limiting device are almost the same, and further after the flexible traction rope is completely extended, the states of the sheet-shaped solar cells are basically the same. The orientation of the sheet-shaped solar cells is the same, the effective area for receiving illumination is the largest, and more electric energy is favorably generated.
In a possible implementation manner, a partition plate for plugging an outlet of the battery piece bin is arranged between the battery piece bin and the sail body bin;
the partition plates comprise a first partition plate and a second partition plate, and the first partition plate and the second partition plate are respectively pivoted on the inner wall of the battery piece bin.
In the implementation process, the partition plate is used for preventing the sheet-shaped solar power generation assembly from shaking. The baffle adopts the structure of first baffle and second baffle, and the baffle of being convenient for can make the baffle structure continue to remain storing the under-deck not blockking under the condition that slice solar energy power generation subassembly worn out the cell piece storehouse export, avoids the baffle to produce the influence to solar energy power generation subassembly.
In one possible implementation, the satellite passive derailment apparatus further includes:
the cabin door is arranged at an outlet of the storage cabin to seal the storage cabin;
and the high-pressure gas generating device is arranged in the storage cabin and avoids the off-rail sail, the flexible traction cable and the solar power generation assembly, and the high-pressure gas generated by the high-pressure gas generating device is used for opening the cabin door.
In the implementation process, the cabin door seals the storage cabin, and various components such as the off-rail sail, the solar power generation assembly and the conductive cable which are placed in the cabin door can be well protected.
In one possible implementation, the shape of the sheet-shaped solar cell is a regular polygon. The shape of the sheet-type solar cell includes, but is not limited to, a quadrangle, a pentagon, a hexagon, an octagon, and the like.
In one possible implementation manner, the sheet-shaped solar cell comprises a first solar cell sheet, a second solar cell sheet and a support plate;
the flexible traction cable is fixed on the supporting plate through a screw;
the conductive cable is connected with the first solar cell piece and the second solar cell piece in a cold rolling mode.
In a second aspect, embodiments of the present application further provide a remote sensing satellite, including a passive satellite derailment apparatus as described above.
In a third aspect, embodiments of the present application also provide a satellite including a satellite passive derailment apparatus as described above.
According to the technical scheme, the flexible traction cable is used for traction of the off-orbit sail, the solar power generation assembly is arranged on the flexible traction cable and comprises a plurality of sheet solar cells, illumination resources in the space are abundant, and the flexible traction cable is easy to rotate, so that the sheet solar cells can receive sunlight of all illumination angles and generate power, and the converted electric energy is transmitted to the power storage device of the satellite body through the conductive cable. Because the electric energy input of the satellite body is increased, the satellite body can still continue to work under the condition of battery attenuation, and therefore the performance of the satellite in the end-stage service life can be guaranteed as far as possible.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained from the drawings without inventive effort.
Fig. 1 is a schematic structural diagram of a passive satellite derailment apparatus according to an embodiment of the present disclosure;
fig. 2 is a schematic structural diagram of another passive satellite derailment apparatus according to an embodiment of the present disclosure;
fig. 3 is a schematic structural diagram of a passive satellite derailment device when an derailment sail is in a closed state according to an embodiment of the present disclosure;
fig. 4 is a schematic structural diagram of a sheet-type solar power generation assembly provided in an embodiment of the present application.
Icon: 100-off-orbit sails; 200-a solar power generation assembly; 210-a first solar cell sheet; 230-a support plate; 220-a second solar cell; 240-through holes; 250-a sheet solar cell; 300-a conductive cable; 400-a flexible traction cable; 500-a satellite body; 600-storage cabin; 610-battery plate bin; 620-sail body bin; 630-a limiting device; 640-a separator; 650-a hatch door; 660-high pressure gas generating device.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. The components of the embodiments of the present application, generally described and illustrated in the figures herein, can be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present application, presented in the accompanying drawings, is not intended to limit the scope of the claimed application, but is merely representative of selected embodiments of the application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.
Fig. 1 is a schematic structural diagram of a passive satellite derailment apparatus according to an embodiment of the present disclosure. Referring to fig. 1, the passive satellite derailment apparatus includes an derailment sail 100, a solar power generation assembly 200, and a conductive cable 300. The off-orbit sail 100 is connected to the satellite body 500 through a flexible hauling cable 400. The solar power generation module 200 includes a plurality of sheet-shaped solar cells 250; the plurality of sheet-shaped solar cells 250 are arranged on the flexible traction rope 400, and when the off-orbit sail 100 is opened and the flexible traction rope 400 is pulled, the sheet-shaped solar cells 250 are sequentially arranged along the longitudinal direction of the flexible traction rope 400. The conductive cable 300 is used to connect the plurality of sheet-shaped solar cells 250 in series with each other and to electrically connect the solar power generation module and the power storage device inside the satellite body 500.
In the implementation process, the passive satellite derailment device is arranged on the satellite body 500, and after the derailment sail 100 is opened, the derailment sail 100 can be separated from the satellite body 500 but can drift in space under the traction of the flexible traction cable 400. The sheet-shaped solar cell 250 is disposed on the flexible traction cable 400, and since the illumination resource in the space is abundant and the flexible traction cable 400 is easy to rotate, the sheet-shaped solar cell 250 can receive sunlight of various illumination angles and generate electricity, and transmit the converted electric energy to the power storage device of the satellite body 500 through the conductive cable 300. Due to the fact that the electric energy input of the satellite body 500 is increased, the satellite body 500 can still continue to work under the condition that the battery is attenuated, and therefore the performance of the satellite in the end-stage service life can be guaranteed as far as possible.
Fig. 2 is a schematic structural diagram of another satellite passive derailment apparatus according to an embodiment of the present disclosure. Referring to fig. 2, in the passive satellite derailment apparatus shown in fig. 2, the conductive cable 300 is integrated in a flexible tow cable 400.
When the derailed sail 100 is in an unopened state, that is, the flexible traction cables 400 are not stretched but in a converged state, the flexible traction cables 400 are stacked together, and correspondingly, the conductive cables 300 are in a contracted state, and the contracted flexible traction cables 400 and the conductive cables 300 are easy to be wound to influence the extension of the flexible traction cables 400 and the conductive cables 300. In the implementation process, the conductive cable 300 is integrated in the flexible traction cable 400, so that the flexible traction cable 400 and the conductive cable 300 can be prevented from being wound with each other, and the structure of the satellite passive off-orbit device can be simplified.
Fig. 3 is a schematic structural diagram of a passive satellite derailing apparatus when an derailing sail 100 is in a closed state according to an embodiment of the present disclosure. Referring to fig. 3, the passive satellite derailment device includes a storage compartment 600, and the derailment sail 100, the flexible traction cable 400 and the sheet-type solar cell 250 are placed in the storage compartment 600. It should be noted that the storage compartment 600 in this embodiment may be independently disposed with respect to the satellite body 500, and when the satellite passive off-orbit device in this application needs to be mounted on the satellite body 500, the storage compartment 600 only needs to be directly mounted at a predetermined position of the satellite. As another embodiment, the storage compartment 600 in the present application may also be a part of the satellite body 500, for example, a groove is formed on the satellite body 500 to form the storage compartment 600, or a space required for accommodating the derailed sail 100, the flexible tow cable 400 and the solar power generation assembly 200 may be formed by using structural features in the satellite body 500. The arrangement position and the structural form of the storage cabin 600 are not particularly limited in the present application, and all the structural forms capable of configuring the accommodating space required by the off-rail sail 100, the flexible traction cable 400 and the solar power generation assembly 200 fall within the protection scope of the present application.
In one possible implementation, the storage compartment 600 includes a cell compartment 610 and a sail compartment 620. Wherein, the battery piece bin 610 is positioned at the bottom of the storage cabin 600, and the sheet-shaped solar cells 250 are stacked in the battery piece bin 610 one by one. The sail body compartment 620 is disposed at an upper portion of the cell compartment 610 and communicates with an outlet of the storage compartment 600.
In the implementation process, the sail body 620 for containing the off-rail sail 100 is configured at the outlet of the storage compartment 600, when the off-rail sail 100 needs to be opened, the off-rail sail 100 can be firstly separated from the storage compartment 600 to enter space, and since the sheet-shaped solar cells 250 and the off-rail sail 100 are both connected through the flexible traction cables 400, after the off-rail sail 100 enters space, the sheet-shaped solar cells 250 gradually leave the storage compartment 600 and enter space, so that the situation that the flexible traction cables 400 cannot be fully extended due to mutual interference of the sheet-shaped solar cells 250 in the extension process of the flexible traction cables 400 is avoided, and the quick preparation and opening of the off-rail sail 100 is facilitated.
In one possible implementation, referring to fig. 3, at least one pair of oppositely disposed interior sides are provided within the battery compartment 610. On the oppositely disposed inner side face, a limiting means 630 for limiting the movement trajectory of the sheet-like solar cell is provided. The restraining means 630 comprises two oppositely disposed runners; the depth of the sliding groove is the same as that of the battery piece bin; a plurality of sheet-shaped solar cells are stacked in a space defined by the two chutes.
In the implementation process, the limiting device 630 is used for limiting the sliding track of each sheet-shaped solar cell 250, after the off-orbit sail 100 enters space, under the extension action of the flexible traction rope 400, each sheet-shaped solar cell 250 does not interfere with each other, and the angle of each sheet-shaped solar cell 250 sliding out of the cell bin 610 under the limitation of the limiting device 630 is almost the same, so that the state of each sheet-shaped solar cell 250 is kept basically the same after the flexible traction rope 400 is completely extended. The sheet-shaped solar cells 250 are oriented in the same direction, and have the largest effective area for receiving light, which is beneficial to generating more electric energy.
In a possible implementation manner, a partition 640 for sealing the outlet of the battery piece bin 610 is arranged between the battery piece bin 610 and the sail body bin 620. The arrangement of the partition 640 is used for preventing the solar power generation assembly 200 from shaking, the flexible traction cable 400 is clamped between the sheet-shaped solar cells 250 in the contraction state, so the flexible traction cable 400 can play a certain isolation role for the adjacent sheet-shaped solar cells 250, but because the power generation assembly of the sheet-shaped solar cells 250 is usually arranged on the outer surface, if the sheet-shaped solar cells 250 shake, the damage of the outer surface of the sheet-shaped solar cells 250 is easily caused, the power generation cannot be carried out, the electric energy input of the satellite body 500 is further influenced, and the satellite body 500 cannot be ensured to still continue to work under the condition of battery attenuation.
In one possible implementation, the partition 640 includes a first partition and a second partition, and the first partition and the second partition are respectively pivoted on the inner wall of the battery compartment 610.
If the partition 640 is a complete plate, since the partition 640 is located between the off-rail sail 100 and the sheet-type solar cell 250, and the off-rail sail 100 and the sheet-type solar cell 250 are connected by the flexible traction cable 400 and need to be completely separated from the storage compartment 600, in this case, the complete plate also needs to be threaded on the flexible traction cable 400 and enter the space along with the off-rail sail 100. The partition 640 can shield the solar panel after entering the space, so in the implementation process, the partition 640 adopts the structure of the first partition and the second partition, which is convenient for the partition to continuously keep the partition structure in the storage compartment 600 under the condition that the partition does not prevent the sheet-shaped solar cell 250 from passing through the cell compartment 610, thereby avoiding the influence of the partition 640 on the sheet-shaped solar cell 250.
Further, after the first and second partitions are opened, the first and second partitions may be locked by a locking member to prevent the first and second partitions from rebounding to interfere with the flexible lanyard 400.
In one possible implementation, the satellite passive derailment apparatus further comprises a hatch 650. A hatch 650 is provided at the outlet of the storage compartment 600 to close off the storage compartment 600.
In the implementation process, the storage compartment 600 is sealed by the compartment door 650, so that various components such as the off-rail sail 100, the sheet-shaped solar cell 250 and the conductive cable 300 placed in the storage compartment can be well protected.
In one possible implementation, a high-pressure gas generating device 660 is disposed in the storage compartment 600, and in the storage compartment 600, the high-pressure gas generating device 660 avoids the off-rail sail 100, the flexible haulage cable 400, and the solar power generation assembly 200. The high-pressure gas generating device 660 is used for generating high-pressure gas when the derailed sail 100 needs to be opened. The high pressure gas generated from the high pressure gas generating device 660 is used to open the door 650.
It should be noted that the manner of opening the door 650 by using the high-pressure gas generating device 660 is only an example, and the form and structure of how to open the door 650 are not specifically limited in the present application, and any structure that enables the door 650 to be opened when the derailed sail 100 needs to be opened and does not interfere with the flexible traction cable 400, i.e., the various components thereon, falls within the scope of the present application.
In one possible implementation, the shape of the sheet-shaped solar cell 250 is a regular polygon. The shape of the sheet-shaped solar cell 250 includes, but is not limited to, a triangle, a quadrangle, a pentagon, a hexagon, an octagon, and the like.
Taking the sheet-shaped solar cell 250 as an example of a quadrilateral, in a possible implementation manner, the length of the flexible traction cable 400 is 1-2 meters, the sheet-shaped solar cell 250 adopts a square sheet structure with the length and width of 100-200 mm, the thickness is 0.8-1.6 mm, and a solar power generation assembly is arranged at intervals of about 120-220 mm.
In particular embodiments, the length of the flexible lanyard 400 may be set to 1 meter, 1.1 meter, 1.2 meters, 1.3 meters, 1.4 meters, 1.5 meters, 1.6 meters, 1.7 meters, 1.8 meters, 1.9 meters, or 2 meters. The sheet-shaped solar cell 250 has a side length of 100mm, 110mm, 120mm, 130mm, 140mm, 150mm, 160mm, 170mm, 180mm, 190mm or 200 mm. The thickness is 0.8mm, 0.9mm, 1.0mm, 1.1mm, 1.2mm, 1.3mm, 1.4mm, 1.5mm or 1.6 mm. The spacing distance between adjacent solar power generation assemblies is 120mm, 130mm, 140mm, 150mm, 160mm, 170mm, 180mm, 190mm, 200mm, 210mm and 220 mm.
It should be noted that, the above-mentioned spacing distance between the adjacent solar power generation assemblies is only exemplary, and the application does not specifically limit the spacing distance between the adjacent solar power generation assemblies, and the spacing distance between the adjacent solar power generation assemblies can be comprehensively selected according to the shape of the sheet-shaped solar power generation assembly and the length of the flexible traction cable 400, so that all the two solar power generation assemblies can be prevented from colliding, and the distance between the two solar power generation assemblies which does not form light shielding falls into the protection range of the application.
Fig. 4 is a schematic structural diagram of a sheet-type solar cell 250 provided in an embodiment of the present application, and referring to fig. 4, the sheet-type solar cell 250 includes a first solar cell sheet 210, a second solar cell sheet 220, and a support plate 230. The material of the support plate 230 includes, but is not limited to, epoxy. The first solar cell sheet 210 and the second solar cell sheet 220 are respectively bonded on both side planes of the support plate 230.
In another possible implementation manner, the first solar cell piece 210, the support plate 230, and the second solar cell piece 220 are provided with through holes 240, and threaded fasteners, such as bolts and nuts, which are engaged with the bolts, are inserted into the through holes of the first solar cell piece 210, the support plate 230, and the second solar cell piece 220 to fix the first solar cell piece 210, the support plate 230, and the second solar cell piece 220.
In another possible implementation, the flexible pull cable 400 is secured to the support plate 230 by screws, see FIG. 4.
In another possible implementation, the conductive cable 300 is connected with the first solar cell sheet 210 and the second solar cell sheet 220 by means of cold rolling.
The flexible pull cable 400 described herein includes, but is not limited to, flexible rope, flexible glass filaments, and the like.
According to the technical scheme, the off-orbit sail 100 is pulled through the flexible traction cable 400, the sheet-shaped solar cells 250 are arranged on the flexible traction cable 400, illumination resources in the space are abundant, and meanwhile, the flexible traction cable 400 is easy to rotate, so that the sheet-shaped solar cells 250 can receive sunlight of various illumination angles and generate electricity, and the converted electric energy is transmitted to the power storage device of the satellite body 500 through the conductive cable 300. Due to the fact that the electric energy input of the satellite body 500 is increased, the satellite body 500 can still continue to work under the condition that the battery is attenuated, and therefore the performance of the satellite in the end-stage service life can be guaranteed as far as possible.
In a second aspect, the embodiment of the present application further provides a remote sensing satellite using the above structure. By adopting the remote sensing satellite of the passive satellite derailment device, after the remote sensing satellite opens the derailment sail 100, the solar power generation assembly 200 can absorb solar energy and generate electric energy, and the electric energy is transmitted to the remote sensing satellite so as to make up for the performance loss caused by the performance reduction of the remote sensing satellite battery. Under the condition that the electric energy is sufficient and the normal work of the remote sensing satellite is ensured, the remote sensing satellite can fully exert the imaging advantage after the orbit is reduced, so that the remote sensing satellite can shoot more pictures with utilization value.
In a third aspect, an embodiment of the present application further provides a satellite using the above satellite passive off-orbit device, and the working principle and advantages of the satellite are referred to a remote sensing satellite, which is not described herein again.
The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
In the description of the present application, it is also to be noted that, unless otherwise explicitly specified or limited, the terms "disposed" and "connected" are to be interpreted broadly, e.g., as being either fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.
Claims (10)
1. A passive satellite derailment apparatus, comprising:
the off-orbit sail is connected to the satellite body through a flexible traction cable;
a solar power generation module including a plurality of sheet-shaped solar cells, each of the sheet-shaped solar cells being disposed on the flexible traction cable at an interval; the plurality of sheet-shaped solar cells are arranged at a preset position of the satellite body in a stacking mode when the derail sail is in a closed state; when the off-orbit sail is opened and the flexible traction cable is pulled, the solar power generation assembly is arranged between the satellite body and the off-orbit sail, and the plurality of sheet-shaped solar cells are sequentially arranged along the length direction of the flexible traction cable;
and the conductive cable is used for connecting the plurality of sheet-shaped solar cells in series with each other and electrically connecting the solar power generation assembly and the power storage device in the satellite body.
2. The satellite passive derailment apparatus of claim 1, wherein the conductive cable is integrated in the flexible tow cable.
3. The satellite passive derailment apparatus of claim 2, further comprising:
and the storage cabin is arranged on the satellite body and used for accommodating the off-orbit sail, the flexible traction cable and the solar power generation assembly when the off-orbit sail is in a closed state.
4. The passive satellite derailment apparatus of claim 3, wherein the storage compartment comprises:
the battery piece bin is positioned at the bottom of the storage cabin, a plurality of sheet-shaped solar batteries in the solar power generation assembly are stacked in the battery piece bin one by one, and the upper and lower surfaces of the sheet-shaped solar batteries are parallel to the bottom surface of the battery piece bin; when the off-rail sail is opened and the flexible traction cable is tensioned, the sheet-shaped solar cells on the flexible traction cable are moved out of the cell bin at an angle parallel to the bottom surface of the cell bin;
and the sail body bin is arranged at the upper part of the battery piece bin, is communicated with the battery piece bin and is communicated with an outlet of the storage cabin.
5. The passive satellite derailment apparatus of claim 4,
at least one pair of oppositely arranged inner side surfaces is arranged in the battery piece bin;
limiting devices for limiting the moving track of the sheet-shaped solar cell are arranged on the pair of oppositely arranged inner side surfaces;
the limiting device comprises two oppositely arranged sliding chutes; the depth of the sliding groove is the same as that of the battery piece bin;
a plurality of sheet-shaped solar cells are stacked in a space defined by the two chutes.
6. The satellite passive derailment device according to claim 4, wherein a partition plate for sealing the outlet of the battery cell bin is arranged between the battery cell bin and the sail body bin;
the partition plates comprise a first partition plate and a second partition plate, and the first partition plate and the second partition plate are respectively pivoted on the inner wall of the battery piece bin.
7. The satellite passive off-orbit apparatus of any one of claims 3 to 6, further comprising:
the cabin door is arranged at an outlet of the storage cabin to seal the storage cabin;
and the high-pressure gas generating device is arranged in the storage cabin and avoids the off-rail sail, the flexible traction cable and the solar power generation assembly, and the high-pressure gas generated by the high-pressure gas generating device is used for opening the cabin door.
8. The satellite passive off-orbit device of claim 7, wherein the sheet-shaped solar cells in the solar power generation assembly comprise a first solar cell sheet, a second solar cell sheet and a support plate;
the flexible traction cable is fixed on the supporting plate through a screw;
the conductive cable is connected with the first solar cell piece and the second solar cell piece in a cold rolling mode.
9. A remote sensing satellite comprising a satellite passive derailment apparatus according to any of claims 1 to 8.
10. A satellite comprising a satellite passive derailment apparatus according to any of claims 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911230645.3A CN110901959B (en) | 2019-12-04 | 2019-12-04 | Passive satellite derailment device, remote sensing satellite and satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911230645.3A CN110901959B (en) | 2019-12-04 | 2019-12-04 | Passive satellite derailment device, remote sensing satellite and satellite |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110901959A true CN110901959A (en) | 2020-03-24 |
| CN110901959B CN110901959B (en) | 2020-07-31 |
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| CN201911230645.3A Active CN110901959B (en) | 2019-12-04 | 2019-12-04 | Passive satellite derailment device, remote sensing satellite and satellite |
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| CN110901959B (en) | 2020-07-31 |
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