CN205675262U - A kind of double cell cube satellite platform - Google Patents
A kind of double cell cube satellite platform Download PDFInfo
- Publication number
- CN205675262U CN205675262U CN201620528723.3U CN201620528723U CN205675262U CN 205675262 U CN205675262 U CN 205675262U CN 201620528723 U CN201620528723 U CN 201620528723U CN 205675262 U CN205675262 U CN 205675262U
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- China
- Prior art keywords
- cell array
- load bearing
- terrace
- primary load
- bearing mechanism
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- Withdrawn - After Issue
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Abstract
The utility model discloses a kind of double cell cube satellite platform, it includes primary load bearing mechanism, windward side cell array, lee face cell array, to terrace cell array, to ground cell array, first launches cell array and second launches cell array and circuit module group, along cube satellite flight direction, windward side cell array is arranged on the windward side of primary load bearing mechanism, lee face cell array is arranged on the lee face of primary load bearing mechanism, terrace cell array is arranged on primary load bearing mechanism on terrace, ground cell array is arranged on primary load bearing mechanism on ground, first expansion cell array and second is launched cell array and is separately positioned on two other face of primary load bearing mechanism, circuit module group is fixed in primary load bearing mechanism.This utility model has the significant advantages such as light weight, volume be little, low cost, the lead time is short, functional density is high, application is wide.
Description
Technical field
This utility model belongs to a cube star technical field, particularly a kind of double cell cube satellite platforms.
Background technology
Along with deepening continuously of space research, for space exploration task and the earth observation mission requirements quilt of low orbit
Constantly proposing, the field such as biology, medicine, communication simultaneously is the most increasing to the demand of space environment test.Conventional satellite industry
When meeting this type of demand, there is the deficiencies such as cost height, R&D cycle length.Low cost cube Nano satellite is just for this type of
Low earth orbital task and a kind of low cost spacecraft platform possessing multi-load suitability of developing.
Space Industry, especially civil aerospace technology industry, on the basis of satellite platform technology relative maturity, various at present
The imagination of space test task is suggested in succession.But for cost and the restriction of emitting times, conventional satellite industry can not
Adapt to current space flight demand completely.Especially for this kind of needs of Space environment detection, formation, networking and earth observation two
The task that even multi-satellite completes jointly, high satellite cost makes project holistic cost be substantially increased, to a certain extent
Also make some urgently to be resolved hurrily or the problem in science of test haves no alternative but be interrupted.
Summary of the invention
The purpose of this utility model is to provide a kind of double cell cube satellite platform, solves current below 500km
Space test and the application demand of Low Earth Orbit are continuously increased, but design of satellites manufacturing cost is high, the problem of lead time length.
The technical solution realizing this utility model purpose is: a kind of double cell cube satellite platforms, it includes main
Load mechanism, windward side cell array, lee face cell array, to terrace cell array, to ground cell array, first launch cell array and
Second launches cell array and circuit module group, and along cube satellite flight direction, windward side cell array is arranged on primary load bearing mechanism
Windward side on, lee face cell array is arranged on the lee face of primary load bearing mechanism, and terrace cell array is arranged on primary load bearing machine
Structure on terrace, ground cell array is arranged on primary load bearing mechanism on ground, first launches cell array and second launches
Cell array is separately positioned on two other face of primary load bearing mechanism, and circuit module group is fixed in primary load bearing mechanism.
Described circuit module group includes that the accumulator battery from the setting of lee face to windward side successively parallel interval, power supply control
Plate, AIS load, house keeping computer, UV antenna receiving and sending machine, launch battle array burn line plate group, momentum wheels, interface board, magnetic torquer,
GPS, three axis magnetometer, Gamalink and UV communication antenna；Power board by PC104 respectively with accumulator battery,
House keeping computer, AIS load, UV antenna receiving and sending machine are connected, and are connected with interface board by jumper cable, and interface board passes through PC104
It is connected with three axis magnetometer, magnetic torquer, GPS, Gamalink respectively, burns line with expansion battle array respectively by jumper cable
Plate group, momentum wheels, UV communication antenna, solar array are connected；House keeping computer is received and dispatched with UV antenna respectively by PC104
Machine, AIS load be connected, by jumper cable respectively with three axis magnetometer, magnetic torquer, GPS, interface board,
Gamalink is connected, and wherein UV antenna receiving and sending machine is connected with UV communication antenna.
Described expansion battle array is burnt line plate group and is included that two expansion battle arrays of being arranged side by side burn line plates, one with to terrace homonymy, separately
One with to ground homonymy.
Momentum wheels use two-shipper cold standby, momenttum wheel with to terrace homonymy, another with to ground homonymy.
Described first launches cell array includes body dress plate, expansion plate and hinge, and body dress plate and expansion plate pass through gemel connection,
Body dress plate uses single surface pasting, and inner surface posts thermal control coating, and expansion plate uses two-sided paster；Second launches cell array and first
Launch cell array structure identical.
Also including pressure transducer, pressure transducer is fixed on the body dress plate centre position launching cell array, pressure sensing
Device is connected with house keeping computer and interface board respectively by jumper cable.
Described windward side cell array, lee face cell array, it is single surface pasting to terrace cell array with to ground cell array,
And inner surface posts thermal control coating.
Also including gps antenna, gps antenna is fixed on terrace cell array centre position, gps antenna by jumper cable with
GPS is connected.
Described first expansion cell array and second is launched cell array and is arranged symmetrically with about the satellite centre of form；Windward side cell array and
Lee face cell array is arranged symmetrically with about the satellite centre of form, to terrace cell array and to ground cell array about satellite centre of form symmetry cloth
Put.
Compared with prior art, its remarkable advantage is this utility model:
(1) light weight, at about 2.2kg.
(2) volume is little, overall largest enveloping size 112.8mm × 112.3mm × 227.6mm.
(3) low cost, a large amount of space flight level devices using commercial components and parts to replace costliness, greatly reduce research and development and be manufactured into
This, only about the 10% of conventional satellite.
(4) functional density is high, and module integrated level is high.
(5) application is wide, can be applicable to Atmospheric Survey, the various fields such as boats and ships are monitored, earth observation.
Accompanying drawing explanation
Fig. 1 is the perspective view of the double cell cube satellite platform of this utility model.
Fig. 2 is the attachment structure schematic diagram of the double cell cube satellite platform circuit module group of this utility model.
Detailed description of the invention
Below in conjunction with the accompanying drawings this utility model is described in further detail.
A kind of double cell cube satellite platform, including primary load bearing mechanism 23, windward side cell array 14, lee face cell array
15, to terrace cell array 16, ground cell array, the first expansion cell array 17 and second are launched cell array 18 and circuit module
Group, along cube satellite flight direction, windward side cell array 14 is arranged on the windward side of primary load bearing mechanism 23, lee face battery
Battle array 15 is arranged on the lee face of primary load bearing mechanism 23, terrace cell array 16 is arranged on primary load bearing mechanism 23 on terrace,
Ground cell array is arranged on primary load bearing mechanism 23 on ground, first launches cell array 17 and second launches cell array 18 points
Not being arranged on two other face of primary load bearing mechanism 23, circuit module group is fixed in primary load bearing mechanism 23.
Described circuit module group includes the accumulator battery 1 from the setting of lee face to windward side successively parallel interval, power supply control
Making sheet 2, AIS load 3, house keeping computer 4, UV antenna receiving and sending machine 5, expansion battle array burn line plate group 6, momentum wheels 7, interface board 8, magnetic
Torquer 9, GPS 10, three axis magnetometer 11, Gamalink12 and UV communication antenna 13；Power board 2 passes through
PC104 is connected with accumulator battery 1, house keeping computer 4, AIS load 3, UV antenna receiving and sending machine 5 respectively, by jumper cable with connect
Oralia 8 is connected, interface board 8 by PC104 respectively with three axis magnetometer 11, magnetic torquer 9, GPS 10, Gamalink12
It is connected, burns line plate group 6, momentum wheels 7, UV communication antenna 13, solar array phase with expansion battle array respectively by jumper cable
Even；House keeping computer 4 is connected with UV antenna receiving and sending machine 5, AIS load 3, by jumper cable respectively with three respectively by PC104
Axle gaussmeter 11, magnetic torquer 9, GPS 10, interface board 8, Gamalink12 are connected, wherein UV antenna receiving and sending machine 9 and UV
Communication antenna 13 is connected.
Described expansion battle array is burnt line plate group 6 and is included that two expansion battle arrays of being arranged side by side burn line plates, one with to terrace homonymy, separately
One with to ground homonymy.
Momentum wheels 7 use two-shipper cold standby, momenttum wheel with to terrace homonymy, another with to ground homonymy.
Described first launches cell array 17 includes body dress plate, expansion plate and hinge 21, and body dress plate and expansion plate pass through hinge
21 connect, and body dress plate uses single surface pasting, and inner surface posts thermal control coating, and expansion plate uses two-sided paster；Second launches battery
It is identical that battle array 18 launches cell array 17 structure with first.
Also include that pressure transducer 22, pressure transducer 22 are fixed on the body dress plate centre position launching cell array, pressure
Sensor 22 is connected with house keeping computer 4, interface board 8 respectively by jumper cable, and pressure transducer 22 is given as separating switch
Satellite provides and launches whether cell array launches signal.
Described windward side cell array 14, lee face cell array 15, it is list to terrace cell array 16 with to ground cell array
Face paster, and inner surface posts thermal control coating.
Also including that gps antenna 19, gps antenna 19 are fixed on terrace cell array 16 centre position, gps antenna 19 is by jumping
Line cable is connected with GPS 10.
Described first expansion cell array 17 and the second expansion cell array 18 are arranged symmetrically with about the satellite centre of form；Windward side battery
Battle array 14 and lee face cell array 15 be arranged symmetrically with about the satellite centre of form, to terrace cell array 16 and to ground cell array about satellite
The centre of form is arranged symmetrically with.
The main force support structure 23 of described pair of cell cube satellite platform ensures that satellite is not damaged in emission process, and
Mechanically and thermally deform little；Use three axis magnetometer 11 to realize double vector attitude of satellite to determine, use momentum wheels 7 and magnetic torquer
9 realize three-axis attitude control；House keeping computer 4 is to whole star United Dispatching, it is achieved the structure thermal environment of whole star is monitored, electrically and
The functions such as data-interface is supported, energy distribution, three-axis stabilization control, star ground data transmission；Power board 2 is responsible for whole star power supply
Distribution, the first expansion plate launching cell array 17 and the second expansion cell array 18 is affixed on satellite surface before launching, launches after transmitting
Certain angle is operated；UV communication antenna 13 communicates with earth station with carrying out star.
Claims (9)
1. a double cell cube satellite platform, it is characterised in that: include primary load bearing mechanism (23), windward side cell array
(14), lee face cell array (15), to terrace cell array (16), to ground cell array, first launch cell array (17) and second
Launching cell array (18) and circuit module group, along cube satellite flight direction, windward side cell array (14) is arranged on primary load bearing
On the windward side of mechanism (23), lee face cell array (15) is arranged on the lee face of primary load bearing mechanism (23), to terrace battery
Battle array (16) be arranged on primary load bearing mechanism (23) on terrace, ground cell array is arranged on primary load bearing mechanism (23) to ground
On, the first expansion cell array (17) and second launches cell array (18) and is separately positioned on two other face of primary load bearing mechanism (23)
On, circuit module group is fixed in primary load bearing mechanism (23).
The most according to claim 1 pair of cell cube satellite platform, it is characterised in that: described circuit module group include from
The lee face accumulator battery (1) that parallel interval is arranged successively to windward side, power board (2), AIS load (3), Star Service calculate
Machine (4), UV antenna receiving and sending machine (5), expansion battle array burn line plate group (6), momentum wheels (7), interface board (8), magnetic torquer (9), GPS
Receiver (10), three axis magnetometer (11), Gamalink(12) and UV communication antenna (13)；Power board (2) passes through PC104
Be connected with accumulator battery (1), house keeping computer (4), AIS load (3), UV antenna receiving and sending machine (5) respectively, by jumper cable with
Interface board (8) be connected, interface board (8) by PC104 respectively with three axis magnetometer (11), magnetic torquer (9), GPS
(10), Gamalink(12) be connected, by jumper cable respectively with launch that battle array burns line plate group (6), momentum wheels (7), UV communicate
Antenna (13), solar array are connected；House keeping computer (4) by PC104 respectively with UV antenna receiving and sending machine (5), AIS load
(3) be connected, by jumper cable respectively with three axis magnetometer (11), magnetic torquer (9), GPS (10), interface board (8),
Gamalink(12) being connected, wherein UV antenna receiving and sending machine (5) is connected with UV communication antenna (13).
The most according to claim 2 pair of cell cube satellite platform, it is characterised in that: described expansion battle array burns line plate group
(6) include that two expansion battle arrays of being arranged side by side burn line plates, one with to terrace homonymy, another with to ground homonymy.
The most according to claim 2 pair of cell cube satellite platform, it is characterised in that: momentum wheels (7) use two-shipper
Cold standby, momenttum wheel with to terrace homonymy, another with to ground homonymy.
The most according to claim 2 pair of cell cube satellite platform, it is characterised in that: described first launches cell array
(17) including body dress plate, expansion plate and hinge (21), body dress plate and expansion plate are connected by hinge (21), and body dress plate uses one side
Paster, inner surface posts thermal control coating, and expansion plate uses two-sided paster；Second launches cell array (18) and first launches cell array
(17) structure is identical.
The most according to claim 5 pair of cell cube satellite platform, it is characterised in that: also include pressure transducer
(22), pressure transducer (22) is fixed on the body dress plate centre position launching cell array, and pressure transducer (22) is by wire jumper electricity
Cable is connected with house keeping computer (4) and interface board (8) respectively.
The most according to claim 2 pair of cell cube satellite platform, it is characterised in that: described windward side cell array
(14), lee face cell array (15), to terrace cell array (16) and ground cell array is single surface pasting, and inner surface posts
Thermal control coating.
The most according to claim 7 pair of cell cube satellite platform, it is characterised in that: also include gps antenna (19),
Gps antenna (19) is fixed on terrace cell array (16) centre position, and gps antenna (19) passes through jumper cable and GPS
(10) it is connected.
The most according to claim 1 pair of cell cube satellite platform, it is characterised in that: described first launches cell array
(17) and the second launches cell array (18) is arranged symmetrically with about the satellite centre of form；Windward side cell array (14) and lee face cell array
(15) it is arranged symmetrically with about the satellite centre of form, to terrace cell array (16) and ground cell array is arranged symmetrically with about the satellite centre of form.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620528723.3U CN205675262U (en) | 2016-06-03 | 2016-06-03 | A kind of double cell cube satellite platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620528723.3U CN205675262U (en) | 2016-06-03 | 2016-06-03 | A kind of double cell cube satellite platform |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205675262U true CN205675262U (en) | 2016-11-09 |
Family
ID=57436820
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620528723.3U Withdrawn - After Issue CN205675262U (en) | 2016-06-03 | 2016-06-03 | A kind of double cell cube satellite platform |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205675262U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105883005A (en) * | 2016-06-03 | 2016-08-24 | 南京理工大学 | Dual-unit cube satellite platform |
| CN113401370A (en) * | 2021-07-23 | 2021-09-17 | 上海卫星工程研究所 | Body-mounted solar shell and double-satellite combined heat control system |
| US11465780B2 (en) | 2018-02-19 | 2022-10-11 | Mazarom Impex S.R.L. | Small-size artificial satellite—“Card-Sat” |
-
2016
- 2016-06-03 CN CN201620528723.3U patent/CN205675262U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105883005A (en) * | 2016-06-03 | 2016-08-24 | 南京理工大学 | Dual-unit cube satellite platform |
| US11465780B2 (en) | 2018-02-19 | 2022-10-11 | Mazarom Impex S.R.L. | Small-size artificial satellite—“Card-Sat” |
| CN113401370A (en) * | 2021-07-23 | 2021-09-17 | 上海卫星工程研究所 | Body-mounted solar shell and double-satellite combined heat control system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20161109 Effective date of abandoning: 20171229 |