CN207482216U - A kind of low rail micro-nano satellite - Google Patents
A kind of low rail micro-nano satellite Download PDFInfo
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- CN207482216U CN207482216U CN201721592850.0U CN201721592850U CN207482216U CN 207482216 U CN207482216 U CN 207482216U CN 201721592850 U CN201721592850 U CN 201721592850U CN 207482216 U CN207482216 U CN 207482216U
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- low rail
- nano satellite
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- micro
- electric thruster
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Abstract
The utility model provides a kind of low rail micro-nano satellite, including：Pulse differential of the arc electric thruster, solar array, star sensor and sun sensor；The star sensor and sun sensor are respectively used to measure star chart and the sun, obtain the attitude information of low rail micro-nano satellite；For obtaining solar energy, the energy is provided for low rail micro-nano satellite operation on orbit for the solar array；The pulse differential of the arc electric thruster, for the pose adjustment of low rail micro-nano satellite.Low rail micro-nano satellite provided by the utility model using pulse differential of the arc electric thruster, can realize the pose adjustment of low rail micro-nano satellite more conveniently.
Description
Technical field
The utility model is related to satellite technology fields, and in particular to a kind of low rail micro-nano satellite.
Background technology
Electric thruster is to be sprayed working medium from thruster inner high speed using electric energy, so as to generate thrust.Due to have than
The advantages of leaping high, electric thruster will be widely used in satellite platform.Usually, electric thruster (predominantly ion or suddenly
Your thruster) thrust be chemical propulsion several one thousandths, in tens mN or so, therefore electric thruster is generally applied to and defends
On star process is kept for the north-south position of satellite.
But for micro-nano satellite, due to being constrained by power supply power consumption on star, using traditional electric thruster
(such as ion or hall thruster) can not realize in-orbit use, it is therefore desirable to a kind of lower electric thruster of power consumption.
Utility model content
For the defects in the prior art, the utility model provides a kind of low rail micro-nano satellite, provided by the utility model
Low rail micro-nano satellite using pulse differential of the arc electric thruster, can realize the pose adjustment of low rail micro-nano satellite more conveniently.
To achieve the above object, the utility model provides following technical scheme：
The utility model provides a kind of low rail micro-nano satellite, including：Pulse differential of the arc electric thruster, solar array, star are quick
Sensor and sun sensor；
Wherein, the star sensor and sun sensor are respectively used to measure star chart and the sun, obtain low rail micro-nano satellite
Attitude information；
For obtaining solar energy, the energy is provided for low rail micro-nano satellite operation on orbit for the solar array；
The pulse differential of the arc electric thruster, for the pose adjustment of low rail micro-nano satellite.
Further, the star sensor and sun sensor are installed on the privately face of low rail micro-nano satellite；
The solar array is symmetrically mounted on the side of ± Y-axis face of low rail micro-nano satellite；
The pulse differential of the arc electric thruster is symmetrically mounted on the side of ± X-axis face of low rail micro-nano satellite or, right
Ground is claimed to be mounted on the incline that the side of ± X-axis face and the side of ± Y-axis face are intersected；
Wherein, in satellite machinery coordinate system, Z axis positive normal refers to ground, and Y-axis positive direction is directed toward satellite north plate positive normal side
To X-axis meets the right-hand rule.
Further, the thrust of the pulse differential of the arc electric thruster is 10~100 μ N.
Further, the quantity of the pulse differential of the arc electric thruster is 2~3 pairs.
Further, the low rail micro-nano satellite further includes：Gyro.
Further, the low rail micro-nano satellite further includes：Antenna.
Further, the low rail micro-nano satellite further includes：Optical camera.
Further, the low rail micro-nano satellite further includes：Momenttum wheel.
Further, the low rail micro-nano satellite further includes：Analog sun sensor.
Further, the low rail micro-nano satellite further includes：Magnetic torquer.
Further, the low rail micro-nano satellite further includes：Magnetometer.
The utility model at least has following advantageous effect：
1st, in the utility model, the adjustment of low rail micro-nano satellite is realized using pulse differential of the arc electric thruster, due to pulse
The thrust that differential of the arc electric thruster generates is smaller, therefore is relatively specific for low rail micro-nano satellite.
2nd, in the utility model, since the thrust that pulse differential of the arc electric thruster generates is smaller, according to traditional installation
Mode can not then obtain the on-orbit calibration size of pulse differential of the arc electric thruster, and to solve the problems, such as this, the utility model is micro- by pulse
Arc electric thruster is symmetrically mounted on the side of ± X-axis face of low rail micro-nano satellite or, is symmetrically mounted at ± X-axis just
To side and ± Y-axis face the incline that intersects of side on, by this mounting means, work feelings in conjunction with Attitude and orbit control system
Condition can obtain the on-orbit calibration value of pulse differential of the arc electric thruster.
Certainly, implement the either method of the utility model or product is not necessarily required to reach all the above excellent simultaneously
Point.
Description of the drawings
It in order to illustrate the embodiment of the utility model or the technical proposal in the existing technology more clearly, below will be to embodiment
Or attached drawing needed to be used in the description of the prior art is briefly described, it should be apparent that, the accompanying drawings in the following description is this
Some embodiments of utility model, for those of ordinary skill in the art, without creative efforts, also
Other attached drawings can be obtained according to these attached drawings.
Fig. 1 is the structure diagram for the low rail micro-nano satellite that one embodiment of the utility model provides；
Fig. 2 is the schematic view of the mounting position for the pulse differential of the arc electric thruster that one embodiment of the utility model provides；
Fig. 3 is the schematic view of the mounting position of prior art intermediate ion or Hall electric thruster.
Specific embodiment
Purpose, technical scheme and advantage to make the utility model embodiment are clearer, new below in conjunction with this practicality
Attached drawing in type embodiment carries out the technical scheme in the embodiment of the utility model clear, complete description, it is clear that retouched
The embodiment stated is the utility model part of the embodiment, instead of all the embodiments.Based on the implementation in the utility model
Example, those of ordinary skill in the art's all other embodiments obtained without creative efforts, belongs to
The range of the utility model protection.
As described in the background art, the thrust of existing ion or Hall electric thruster is generally in tens mN or so, but
It is, for micro-nano satellite, due to being constrained by power supply power consumption on star, using traditional electric thruster (such as ion or suddenly
That thruster) it can not realize in-orbit use.To solve the problems, such as this, one embodiment of the utility model provides a kind of low rail micro-nano and defends
Star, referring to Fig. 1, which includes：Pulse differential of the arc electric thruster 1, solar array 2, star sensor 3 and the sun are sensitive
Device 4；
Wherein, the star sensor 3 and sun sensor 4 are respectively used to measure star chart and the sun, obtain low rail micro-nano and defend
The attitude information of star；
For obtaining solar energy, the energy is provided for low rail micro-nano satellite operation on orbit for the solar array 2；
The pulse differential of the arc electric thruster 1, for the pose adjustment of low rail micro-nano satellite.
It is understood that the thrust of the pulse differential of the arc electric thruster 1 is 10~100 μ N, it is micro- to be relatively specific for low rail
The pose adjustment of Nano satellite.
Not delay the normal work of low rail micro-nano satellite, it is preferable that it is micro- that the low rail micro-nano satellite includes multipair pulse
Arc electric thruster, on the one hand, multipair pulse differential of the arc electric thruster can be used to be provided commonly for the pose adjustment of low rail micro-nano satellite,
To improve pose adjustment accuracy；It on the other hand, can also be using extra pulse differential of the arc electric thruster as thrust reserve device.It is excellent
Selection of land, the quantity of the pulse differential of the arc electric thruster is 2~3 pairs.
In the present embodiment, the southern pose adjustment of low rail micro-nano satellite is realized using pulse differential of the arc electric thruster, due to arteries and veins
The thrust for rushing the generation of differential of the arc electric thruster is smaller, therefore is relatively specific for low rail micro-nano satellite.
Referring to Fig. 2, since the thrust of existing ion or Hall electric thruster is generally in tens mN or so, it is existing
Ion or Hall electric thruster 1 ' be typically installed at the 2 ' side of solar array of high rail synchronous satellite, for the north and south position of satellite
During putting holding.By the track calibration result before and after task, the work effect of ion or Hall electric thruster 1 ' can be obtained
Rate and north-south position keep effect.However compared with ion or hall thruster, the thrust of pulse differential of the arc electric thruster is smaller,
Usually only tens μ N, it is contemplated that the time cycle, using traditional layout type using pulse differential of the arc electric thruster, no matter in height
Track or low orbit can not all obtain the on-orbit calibration size of thruster, and to solve the problems, such as this, the present embodiment additionally provides suitable
For the mounting means of pulse differential of the arc electric thruster, under the mounting means, with reference to Attitude and orbit control system working condition, can obtain
The on-orbit calibration value of pulse differential of the arc electric thruster.
Specifically, referring to Fig. 3, the installation site provided in this embodiment suitable for pulse differential of the arc electric thruster is as follows：
Pulse differential of the arc electric thruster 1 is symmetrically mounted on the side of ± X-axis face of low rail micro-nano satellite (in Fig. 3 not
This situation is shown)；
Or,
Pulse differential of the arc electric thruster 1 is symmetrically mounted at the side that the side of ± X-axis face and the side of ± Y-axis face are intersected
On rib (situation shown in Figure 3)；
As shown in figure 3, in satellite machinery coordinate system, Z axis positive normal refers to ground, and Y-axis positive direction is directed toward satellite north plate and is executed
Line direction, X-axis meet the right-hand rule；
Correspondingly, the solar array 2 is symmetrically mounted on the side of ± Y-axis face of low rail micro-nano satellite；It is described
Star sensor 3 and sun sensor 4 are installed on the privately face 5 of low rail micro-nano satellite.
According to being described above it is found that since the thrust that pulse differential of the arc electric thruster generates is smaller, according to traditional installation
Mode can not then obtain the on-orbit calibration size of pulse differential of the arc electric thruster, and to solve the problems, such as this, the present embodiment is by the pulse differential of the arc
Electric thruster is symmetrically mounted on the side of ± X-axis face of low rail micro-nano satellite or, is symmetrically mounted at ± X-axis face
Side and ± Y-axis face the incline that intersects of side on, by this mounting means, work feelings in conjunction with Attitude and orbit control system
Condition can obtain the on-orbit calibration value of pulse differential of the arc electric thruster.
For example, by mounting means above, in conjunction with following operating procedure, pulse differential of the arc electric thruster can be obtained
On-orbit calibration value：
Step 101：The micro-nano satellite platform mass characteristic of pulse differential of the arc electric thruster mounting arrangement need to be carried out by confirming, including
Position of the centroid of satellite in satellite machinery coordinate system after Stretching of solar wings, in satellite machinery coordinate system, Z axis positive normal refers to
Ground, Y-axis positive direction are directed toward satellite north plate positive normal direction, and X-axis meets the right-hand rule.
Step 102：Confirm micro-nano satellite platform user demand and satellite on install all kinds of sensors, solar array,
Antenna and optical camera are to the restrictive condition of pulse differential of the arc electric thruster；Wherein user demand includes：Satellite three-axis attitude controls
Required torque；All kinds of sensors, solar array, antenna and optical camera include the restrictive condition of pulse differential of the arc electric thruster
Installation site, geometric dimension, disturbance torque, visual field influences and space environment pollution condition.
Step 103：On the basis of beginning of lifetime centroid position, and/or, ± X the sides of satellite and defend in ± X the sides of satellite
Pulse differential of the arc electric thruster symmetric configuration is carried out on the incline that ± Y sides of star are intersected；± X the sides of the satellite refer to ± X-axis face
Side, ± Y the sides of the satellite refer to the side of ± Y-axis face.
Step 104：The pulse differential of the arc electric thruster layout that step 103 obtains is iterated optimization, to cruise down day
Orbital plane normal angle Momentum accumulation caused by three orbital periods carries out preliminary placement for known conditions, then in conjunction with gyro and in advance
If the precision for the sensor specified is modified, if more than gyro and the default precision of sensor specified, it is micro- to adjust pulse
The installation site and angle of arc electric thruster；Wherein, the angular momentum accumulation is emulated to obtain by Attitude and orbit control system.
Step 105：The pulse differential of the arc electric thruster layout and the gesture stability thrust of micro-nano satellite platform that step 104 is obtained
Device carries out trouble shooting optimization, and optimization principles are：There is event in the cold air thruster for being responsible for gesture stability during gesture stability
Barrier can realize that identical attitude angle is adjusted, to ensure micro-nano satellite energy using the mounting arrangement of pulse differential of the arc electric thruster
Enough normal operation on orbit.
It is micro- as it can be seen that the utility model proposes the pulse differential of the arc electric thruster mounting arrangement mode that thrust is tens μ N
Nano satellite realizes that diversified carrying task provides selectable thinking.
It is understood that the low rail micro-nano satellite can also include：Gyro.
It is understood that the low rail micro-nano satellite can also include：Antenna.
It is understood that the low rail micro-nano satellite can also include：Optical camera.
It is understood that the low rail micro-nano satellite can also include：Momenttum wheel.
It is understood that the low rail micro-nano satellite can also include：Analog sun sensor.
It is understood that the low rail micro-nano satellite can also include：Magnetic torquer.
Above example is merely to illustrate the technical solution of the utility model, rather than its limitations；Although with reference to aforementioned reality
Example is applied the utility model is described in detail, it will be understood by those of ordinary skill in the art that：It still can be to preceding
The technical solution recorded in each embodiment is stated to modify or carry out equivalent replacement to which part technical characteristic；And these
Modifications or substitutions, the spirit and model of various embodiments of the utility model technical solution that it does not separate the essence of the corresponding technical solution
It encloses.
Claims (10)
1. a kind of low rail micro-nano satellite, which is characterized in that including：Pulse differential of the arc electric thruster, solar array, star sensor and too
Positive sensor；
Wherein, the star sensor and sun sensor are respectively used to measure star chart and the sun, obtain the appearance of low rail micro-nano satellite
State information；
For obtaining solar energy, the energy is provided for low rail micro-nano satellite operation on orbit for the solar array；
The pulse differential of the arc electric thruster, for the pose adjustment of low rail micro-nano satellite.
2. low rail micro-nano satellite according to claim 1, which is characterized in that the star sensor and sun sensor are pacified
On the privately face of low rail micro-nano satellite；
The solar array is symmetrically mounted on the side of ± Y-axis face of low rail micro-nano satellite；
The pulse differential of the arc electric thruster is symmetrically mounted on the side of ± X-axis face of low rail micro-nano satellite or, symmetrically
On the incline intersected mounted on the side of the side of ± X-axis face and ± Y-axis face；
Wherein, in satellite machinery coordinate system, Z axis positive normal refers to ground, and Y-axis positive direction is directed toward satellite north plate positive normal direction, X-axis
Meet the right-hand rule.
3. low rail micro-nano satellite according to claim 1, which is characterized in that the thrust of the pulse differential of the arc electric thruster is
10~100 μ N.
4. low rail micro-nano satellite according to claim 1, which is characterized in that the quantity of the pulse differential of the arc electric thruster is
2~3 pairs.
5. low rail micro-nano satellite according to claim 1, which is characterized in that further include：Gyro.
6. low rail micro-nano satellite according to claim 1, which is characterized in that further include：Antenna.
7. low rail micro-nano satellite according to claim 1, which is characterized in that further include：Optical camera.
8. low rail micro-nano satellite according to claim 1, which is characterized in that further include：Momenttum wheel.
9. low rail micro-nano satellite according to claim 1, which is characterized in that further include：Analog sun sensor.
10. low rail micro-nano satellite according to claim 1, which is characterized in that further include：Magnetic torquer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721592850.0U CN207482216U (en) | 2017-11-24 | 2017-11-24 | A kind of low rail micro-nano satellite |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721592850.0U CN207482216U (en) | 2017-11-24 | 2017-11-24 | A kind of low rail micro-nano satellite |
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| CN207482216U true CN207482216U (en) | 2018-06-12 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107985631A (en) * | 2017-11-24 | 2018-05-04 | 北京千乘探索科技有限公司 | Low rail micro-nano satellite and the in-orbit installation method suitable for pulse differential of the arc electric thruster |
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2017
- 2017-11-24 CN CN201721592850.0U patent/CN207482216U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107985631A (en) * | 2017-11-24 | 2018-05-04 | 北京千乘探索科技有限公司 | Low rail micro-nano satellite and the in-orbit installation method suitable for pulse differential of the arc electric thruster |
| CN107985631B (en) * | 2017-11-24 | 2024-01-26 | 北京千乘探索科技有限公司 | Low-orbit micro-nano satellite and on-orbit installation method suitable for pulse micro-arc electric thruster |
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