CN206437237U - A kind of planetary probe of use Isotopes power supply - Google Patents
A kind of planetary probe of use Isotopes power supply Download PDFInfo
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- CN206437237U CN206437237U CN201621334285.3U CN201621334285U CN206437237U CN 206437237 U CN206437237 U CN 206437237U CN 201621334285 U CN201621334285 U CN 201621334285U CN 206437237 U CN206437237 U CN 206437237U
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- magnetometer
- rtg
- power supply
- detector
- isotopes
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Abstract
The utility model discloses a kind of planetary probe of use Isotopes power supply, the planetary probe uses isotope generator to be powered for whole star, including magnetometer extending arm, RTG power supplys, scientific instrument support bar, detector main structure, magnetometer, magnetometer bar shrink cylinder, communication antenna, pass through rational node configuration and layout, the electric energy supply that far-reaching space can not only be met is required, and can effectively mitigate the weight of transmission cable, effectively implement scientific exploration task.
Description
Technical field
The utility model is related to nuclear spacecraft field, is specifically related to visited in a kind of planet of use Isotopes power supply
Survey device.
Background technology
The embodiment that deep space is a national comprehensive strength is explored, with the transmitting of the serial lunar orbiter of the goddess in the moon, China must
The more remote space explorations such as Mars, Jupiter will be carried out.The invention discloses a kind of isotope planetary probe, light is carried
A variety of science load such as, microwave, physical field, Space Particle detection, it is ensured that effective implementation of scientific exploration task.Detector is adopted
Electric energy is provided for whole device with isotope generator RTG, current main deep space probe is the transmitting of the states such as America and Europe, the goddess in the moon No. three months
Isotope heat source RHU is used only in ball detector, and China not yet carries out the design work of the deep space probe based on RTG.
Utility model content
In view of this, the utility model provides a kind of planetary probe of use Isotopes power supply, using isotope
Power supply is that whole planetary probe is powered, and the electric energy supply that can not only meet far-reaching space is required, and can effectively mitigate biography
The weight of transmission cable, effectively implements scientific exploration task.
A kind of planetary probe of use Isotopes power supply, the planetary probe includes magnetometer extending arm, RTG electricity
Source, scientific instrument support bar, detector main structure, magnetometer, magnetometer bar shrink cylinder, communication antenna；
The detector main structure upper end is fixedly connected by waveform connecting bracket with communication antenna, detector main structure
Side is provided with scientific instrument support bar, scientific instrument support bar and is provided with optics load；The magnetometer extending arm and section
Learn instrument support bar collinearly arrangement and position on the contrary, magnetometer extending arm is connected by hinge with detector main structure side wall,
Junction is provided with magnetometer bar shrink cylinder, is drawn in during transmitting in magnetometer shrink cylinder, and magnetic strength is installed in magnetometer extending arm end
Meter；Two groups of RTG arms are connected to detector main structure opposite side by articulate, symmetrical along magnetometer extending arm, two groups
The angle that RTG arm elongated central lines are crossed between the structure centre of spacecraft, two groups of RTG arms is according to the trim of detector quality and thermal control
Design needs are designed, and a RTG power supply is provided with every group of RTG arm；
The planetary probe is in launching phase, and RTG arms, magnetometer extending arm and scientific instrument support bar, which are drawn in, to be fixed
In detector main structure side wall, during planetary probe operation on orbit, RTG arms, magnetometer extending arm and scientific instrument support bar
By central computer control expansion in place.
Further, the detector main structure lower surface is docked by fold-line-shaped connecting bracket with propelling module, selection bag
Band or blasting bolt unblock separation, the primary module of propelling module is a circular tank, and lower end is provided with four precise trackings；Visit
The lower surface for surveying device main structure and propelling module is designed with the interface being connected with carrier rocket.
Further, the communication antenna includes high-gain aerial, low-gain antenna, circular support ring, parabolic shape
High-gain aerial one end is connected by circular support ring with waveform connecting bracket, and X-band feed reflects positioned at high-gain aerial
Face center, upper end connects low-gain antenna by support；Antenna reflective face is by aluminium honeycomb core graphite epoxy epidermis composite structure
Into.
Further, the detector main structure uses ten prism carbon fiber loaded cylinder structure types, inside carbon fiber
The cellular board of strut and carbon fiber skin aluminium honeycomb core takes out the installing space of platform device.
Further, the magnetometer extending arm selects coiling extending arm.
Further, the optics load installed on the scientific instrument support bar has：Panchromatic/multispectral camera, infrared phase
Machine, ultraviolet full spectral coverage imaging spectrometer, full polarization analysis instrument；Scientific instrument support bar center line and detector main structure intersection point
Low energy discharge ion detector is installed on inwall.
Further, the detector main structure lower end is provided with one group of totally four precise tracking, and side wall is uniformly installed
There are four pieces of radiating surfaces and four groups of attitude control engines, every group of attitude control engine is made up of 3 puffers.
Further, the detector main structure outer wall is enclosed with heat-control multilayer component, is aluminized mylar, poly- fluorine second
Alkene sandwich construction, outermost layer is black high temp resistance conductive material to prevent buildup of static electricity.
Further, the RTG arms are made of carbon fibre material, are adopted with the moving part of detector main structure junction
With flexible heat pipe so that the position that the heat of RTG power supplys needs to be incubated by heat pipe guide probe.
Further, posted on the detector main structure lateral wall microwave radiometer, Terahertz Atmospheric components survey meter,
Integrated electronicses subsystem has been installed concentratedly on γ/X-ray spectrometer, madial wall.
Beneficial effect：
1st, the utility model uses isotope generator to be powered for whole planetary probe, without solar panel, meets
The electric energy supply in far-reaching space is required.
2nd, the utility model uses Integrated Electronic System, the Trinity such as electric, information and control.In design process, body
Existing hardware synthesis, software synthesis and informix, and pass through the reliability of comprehensive means raising system.
3rd, the utility model is used is communicated between the spaceborne information system of fiber buss, each hardware using WIFI, can be had
Effect mitigates the weight of transmission cable.
4th, the utility model is carried using atmospheric environment detection class load, Space Particle detection class load, physical field detection class
A variety of advanced load such as lotus, can more effectively implement scientific exploration task.
5th, the main optics load of the utility model is arranged on scientific instrument support bar, is easy to balance the weight of RTG power supplys
Amount, while can also ensure that the unobstructed visual field of optics load is required.
6th, the utility model node configuration, rationally distributed, detector transverse direction barycenter can subtract close proximity to the longitudinal axis of whole device
Impact of the delivery to whole device during few detector transmitting；Magnetometer extending arm is collinearly arranged but position phase with scientific instrument support bar
Instead, it can avoid interfering with each other.
Brief description of the drawings
Fig. 1, Fig. 3 are the utility model different visual angles deployed condition schematic diagrames；
Fig. 2, Fig. 4 are the utility model different visual angles rounding state schematic diagrames；
Working state schematic representation when Fig. 5 is the utility model in-orbit flight；
Fig. 6 is the rounding state schematic diagram that the utility model does not carry propelling module.
Wherein, 1- high-gain aerials, 2- magnetometer extending arms, 3-RTG power supplys, 4- propelling modules, 5- scientific instrument support bars,
6- detector main structures, 7- magnetometers, 8- magnetometer bar shrink cylinders, 9-RTG arms, 10- low-gain antennas.
Embodiment
With reference to the accompanying drawings and examples, the utility model is described in detail.
The utility model provides a kind of planetary probe of use Isotopes power supply, and the planetary probe uses same position
Plain power supply is powered, including magnetometer extending arm 2, RTG power supplys 3, scientific instrument support bar 5, detector main structure 6, magnetometer 7,
Magnetometer extending arm shrink cylinder 8, RTG arms 9, communication antenna, as shown in Figure 1 and Figure 2.
Detector main structure 6 uses ten prism carbon fiber loaded cylinder structure types, inside carbon fiber stay bar and carbon fiber
The cellular board of covering aluminium honeycomb core takes out the installing space of platform device.Magnetometer extending arm 2 selects coiling extending arm, RTG
Arm 9 is made of carbon fibre material, uses flexible heat pipe with the moving part of the junction of detector main structure 6 so that RTG power supplys
The position that 3 heat needs to be incubated by heat pipe guide probe.
Communication antenna includes high-gain aerial 1, low-gain antenna 10, circular support ring, the high-gain aerial 1 of parabolic shape
One end is connected by circular support ring with waveform connecting bracket, and X-band feed is located at the reflecting surface center of high-gain aerial 1, on
End connects low-gain antenna 10 by support；Antenna reflective face is made up of aluminium honeycomb core graphite epoxy epidermis composite.
The upper end of detector main structure 6 is fixedly connected by waveform connecting bracket with communication antenna, detector main structure 6 one
Side is provided with scientific instrument support bar 5, scientific instrument support bar 5 and is provided with optics load, is so easy to balance RTG power supplys 3
Weight, while can also ensure that the unobstructed visual field of optics load is required.Optics load has：Panchromatic/multispectral camera, infrared phase
Machine, ultraviolet full spectral coverage imaging spectrometer, full polarization analysis instrument；The center line of scientific instrument support bar 5 and the intersection point of detector main structure 6
Inwall on low energy discharge ion detector is installed, RTG power supplys 3 radiation intensity of itself can be detected.
Magnetometer extending arm 2 is collinearly arranged with scientific instrument support bar 5 and position is on the contrary, magnetometer extending arm 2 passes through
Hinge is connected with the side wall of detector main structure 6, and junction is provided with magnetometer bar shrink cylinder 8, is drawn in and is shunk in magnetometer during transmitting
In cylinder 8, magnetometer 7 is installed in the end of magnetometer extending arm 2；Two groups of RTG arms 9 are connected to detector main structure 6 by articulate
Opposite side, symmetrical along magnetometer extending arm 2, two groups of elongated central lines of RTG arms 9 cross the structure centre of spacecraft, two groups of RTG
Angle between arm 9 is needed to be designed according to the trim of detector quality and thermal control design, and one is provided with every group of RTG arm 9
RTG power supplys 3.
The lower surface of detector main structure 6 is docked by fold-line-shaped connecting bracket with propelling module 4, selection band or blasting bolt
Unblock separation, the primary module of propelling module 4 is a circular tank, and lower end is provided with four precise trackings；Detector main structure
The interface that is connected with carrier rocket is designed with the lower surface of propelling module, is connected when launching for whole device with carrier rocket.Propelling module 4
It can be adjusted according to the emissivities of delivery, if carrying capacity enough, can not carry propelling module 4, as shown in Figure 5, Figure 6,
The lower end of detector main structure 6 is provided with one group of totally four precise tracking, and side wall is uniformly provided with four pieces of radiating surfaces and four groups of appearances
Engine is controlled, every group of attitude control engine is made up of 3 puffers.
The outer wall of detector main structure 6 is enclosed with heat-control multilayer component, is aluminized mylar, polyvinyl fluoride sandwich construction,
Outermost layer is black high temp resistance conductive material to prevent buildup of static electricity.Posted on the lateral wall of detector main structure 6 microwave radiometer,
Integrated electronicses subsystem has been installed concentratedly on Terahertz Atmospheric components survey meter, γ/X-ray spectrometer, madial wall.
Planetary probe is in launching phase, and RTG arms 9, magnetometer extending arm 2 and scientific instrument support bar 5, which are drawn in, to be fixed
In the side wall of detector main structure 6, impact of the delivery to whole device during to reduce detector transmitting, detector transverse direction barycenter close proximity to
The longitudinal axis of whole device.During planetary probe operation on orbit, RTG arms 9, magnetometer extending arm 2 and scientific instrument support bar 5 are by center
Computer control deploys in place, as shown in Figure 3, Figure 4.
Planetary probe is after transmitting is entered the orbit, and propelling module 4 is started working, and detector is accelerated into more speed, and planet is visited
Survey after device is entered the orbit and separated with propelling module, detector improves space pointing accuracy using three-axis stabilization technology.Using integrated electronicses system
Unite, the Trinity such as electric, information, control.The utility model in the design process, embody hardware synthesis, software synthesis and
Informix, and pass through the reliability of comprehensive means raising system.Using the spaceborne information system of fiber buss, adopted between each hardware
Communicated with WIFI, can effectively mitigate the weight of transmission cable；Using atmospheric environment detection class load, Space Particle detection class
A variety of advanced load such as load, physical field detection class load, can more effectively implement scientific exploration task.
In summary, preferred embodiment of the present utility model is these are only, is not intended to limit of the present utility model
Protection domain.It is all it is of the present utility model spirit and principle within, any modification, equivalent substitution and improvements made etc. all should be wrapped
It is contained within protection domain of the present utility model.
Claims (10)
1. a kind of planetary probe of use Isotopes power supply, it is characterised in that the planetary probe stretches including magnetometer
Arm, RTG power supplys, scientific instrument support bar, detector main structure, magnetometer, magnetometer bar shrink cylinder, communication antenna；
The detector main structure upper end is fixedly connected by waveform connecting bracket with communication antenna, detector main structure side
It is provided with installation optics load on scientific instrument support bar, scientific instrument support bar；The magnetometer extending arm and scientific instrument
The conllinear arrangement and position is on the contrary, magnetometer extending arm is connected by hinge with detector main structure side wall, junction of support bar
Provided with magnetometer bar shrink cylinder, drawn in during transmitting in magnetometer shrink cylinder, magnetometer is installed in magnetometer extending arm end；Two groups
RTG arms are connected to detector main structure opposite side by articulate, symmetrical along magnetometer extending arm, in two groups of RTG arms
The angle that heart extended line is crossed between the structure centre of spacecraft, two groups of RTG arms is according to the trim of detector quality and thermal control design need
It is designed, a RTG power supply is installed on every group of RTG arm；
The planetary probe draws in launching phase, RTG arms, magnetometer extending arm and scientific instrument support bar and is fixed on spy
Device main structure side wall is surveyed, during planetary probe operation on orbit, RTG arms, magnetometer extending arm and scientific instrument support bar are in
Heart computer control expansion is in place.
2. as claimed in claim 1 using the planetary probe of Isotopes power supply, it is characterised in that the main knot of the detector
Structure lower surface is docked by fold-line-shaped connecting bracket with propelling module, selection band or blasting bolt unblock separation, the master of propelling module
Module is a circular tank, and lower end is provided with four precise trackings；The lower surface of detector main structure and propelling module is all set
There is the interface being connected with carrier rocket.
3. as claimed in claim 1 using the planetary probe of Isotopes power supply, it is characterised in that the communication antenna bag
High-gain aerial, low-gain antenna, circular support ring are included, high-gain aerial one end of parabolic shape passes through circular support ring and ripple
Shape wave connecting bracket is connected, and X-band feed is located at high-gain aerial reflecting surface center, and upper end connects low gain day by support
Line；Antenna reflective face is made up of aluminium honeycomb core graphite epoxy epidermis composite.
4. as claimed in claim 1 using the planetary probe of Isotopes power supply, it is characterised in that the main knot of the detector
Structure uses ten prism carbon fiber loaded cylinder structure types, the cellular board of inside carbon fiber stay bar and carbon fiber skin aluminium honeycomb core
Take out the installing space of platform device.
5. as claimed in claim 1 using the planetary probe of Isotopes power supply, it is characterised in that the magnetometer stretches
Arm selects coiling extending arm.
6. as claimed in claim 1 using the planetary probe of Isotopes power supply, it is characterised in that the scientific instrument branch
The optics load installed on strut has：Panchromatic/multispectral camera, infrared camera, ultraviolet full spectral coverage imaging spectrometer, full polarization point
Analyzer；Scientific instrument support bar center line is with being provided with the detection of low energy discharge ion on the inwall of detector main structure intersection point
Device.
7. as claimed in claim 1 using the planetary probe of Isotopes power supply, it is characterised in that the main knot of the detector
Structure lower end is provided with one group of totally four precise tracking, and side wall is uniformly provided with four pieces of radiating surfaces and four groups of attitude control engines, often
Group attitude control engine is made up of 3 puffers.
8. as claimed in claim 1 using the planetary probe of Isotopes power supply, it is characterised in that the main knot of the detector
Structure outer wall is enclosed with heat-control multilayer component, is aluminized mylar, polyvinyl fluoride sandwich construction, and outermost layer is led for black high temp resistance
Electric material is to prevent buildup of static electricity.
9. as claimed in claim 1 using the planetary probe of Isotopes power supply, it is characterised in that the RTG arms are used
Carbon fibre material is made, and flexible heat pipe is used with the moving part of detector main structure junction so that the heat of RTG power supplys leads to
Superheater tube guide probe needs the position being incubated.
10. as claimed in claim 1 using the planetary probe of Isotopes power supply, it is characterised in that the detector master
Post and installed concentratedly on microwave radiometer, Terahertz Atmospheric components survey meter, γ/X-ray spectrometer, madial wall on structures outlet side-wall
There is integrated electronicses subsystem.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621334285.3U CN206437237U (en) | 2016-12-07 | 2016-12-07 | A kind of planetary probe of use Isotopes power supply |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621334285.3U CN206437237U (en) | 2016-12-07 | 2016-12-07 | A kind of planetary probe of use Isotopes power supply |
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| CN206437237U true CN206437237U (en) | 2017-08-25 |
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| CN201621334285.3U Active CN206437237U (en) | 2016-12-07 | 2016-12-07 | A kind of planetary probe of use Isotopes power supply |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110450979A (en) * | 2019-08-14 | 2019-11-15 | 上海卫星工程研究所 | The more device combined wood galaxies of multiple-energy-source and planet pass through detector |
| CN111409863A (en) * | 2020-03-19 | 2020-07-14 | 上海卫星工程研究所 | Multi-unit combined type wooden star system and planet traversing detector based on thermoelectric conversion energy |
| CN111510067A (en) * | 2019-12-17 | 2020-08-07 | 北京空间飞行器总体设计部 | Spectrum measurement method for thermophotovoltaic power generation system |
| CN112304365A (en) * | 2020-09-25 | 2021-02-02 | 北京空间飞行器总体设计部 | On-orbit micro space debris multi-parameter measuring probe and measuring method |
| CN113325483A (en) * | 2021-04-23 | 2021-08-31 | 上海卫星工程研究所 | Space-based multi-mode extrasystematic and extraterrestrial planet comprehensive detection method and system |
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2016
- 2016-12-07 CN CN201621334285.3U patent/CN206437237U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110450979A (en) * | 2019-08-14 | 2019-11-15 | 上海卫星工程研究所 | The more device combined wood galaxies of multiple-energy-source and planet pass through detector |
| CN111510067A (en) * | 2019-12-17 | 2020-08-07 | 北京空间飞行器总体设计部 | Spectrum measurement method for thermophotovoltaic power generation system |
| CN111510067B (en) * | 2019-12-17 | 2021-03-12 | 北京空间飞行器总体设计部 | Spectrum measurement method for thermophotovoltaic power generation system |
| CN111409863A (en) * | 2020-03-19 | 2020-07-14 | 上海卫星工程研究所 | Multi-unit combined type wooden star system and planet traversing detector based on thermoelectric conversion energy |
| CN112304365A (en) * | 2020-09-25 | 2021-02-02 | 北京空间飞行器总体设计部 | On-orbit micro space debris multi-parameter measuring probe and measuring method |
| CN113325483A (en) * | 2021-04-23 | 2021-08-31 | 上海卫星工程研究所 | Space-based multi-mode extrasystematic and extraterrestrial planet comprehensive detection method and system |
| CN113325483B (en) * | 2021-04-23 | 2022-10-25 | 上海卫星工程研究所 | Space-based multi-mode extrasystematic and extraterrestrial planet comprehensive detection method and system |
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