CN104237653A - Sensor for space electric field detection - Google Patents
Sensor for space electric field detection Download PDFInfo
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- CN104237653A CN104237653A CN201410446705.6A CN201410446705A CN104237653A CN 104237653 A CN104237653 A CN 104237653A CN 201410446705 A CN201410446705 A CN 201410446705A CN 104237653 A CN104237653 A CN 104237653A
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Abstract
The invention provides a sensor for space electric field detection. The sensor comprises a spherical shell, a built-in shell, a built-in circuit board, a left short rod and right short rod, wherein a front-end voltage detection circuit, a constant-current source circuit and a self gain circuit are arranged on the built-in circuit board; the outer surface of the spherical shell is coated with an epoxy carbon-doped coating, the ratio of the solar absorption coefficient of the coating to the total semisphere emission coefficient ranges from 0.95 to 1.2, and the thickness of the coating is not smaller than 1.5 microns; the left short rod and the right short rod are symmetrically arranged on the outer surface of the spherical shell, the built-in shell and the built-in circuit board are arranged in the spherical shell; the constant-current source circuit is connected to the outer surface of the spherical shell and used for applying bias current within the range from -300 nA to 300 nA to the surface of the spherical shell; the self gain circuit is connected with the spherical shell and the built-in shell and used for applying the electric potential of the built-in shell to the electric potential of the spherical shell; the front-end voltage detection circuit is connected with the outer surface of the spherical shell and used for acquiring and outputting the space electric potential induced by the surface of the spherical shell.
Description
Technical field
The present invention relates to a kind of sensor for space electric field detection, belong to Space environment detection technical field.
Background technology
Space electric field detection has great importance, and can be the applications such as seismic monitoring, radio wave propagation, thunderstorm monitoring and provides basic data and background accurately, improve the monitoring and warning to major natural disasters and evaluation capacity.The current space electric field detection mode of carrying detection instrument on satellite or on sounding rocket that adopts is carried out more, and electric field detecting sensor can be divided into pin type, pillar or ball again.In the world, the ICE electric field detecting instrument of French DEMETER Seeds of First Post-flight is comparatively famous, but does not still have document specifically to introduce the specific design of this sensor.The domestic space electric field detection instrument not still successfully being equipped on satellite platform.
Summary of the invention
The object of this invention is to provide a kind of sensor for space electric field detection, this sensor can inductive spacing electromotive force exactly, and the requirement that meeting spatial environment uses.
Realize technical scheme of the present invention as follows:
For a sensor for space electric field detection, comprise spherical shell, built-in housing, internal circuit board, left quarter butt and right quarter butt; Wherein said internal circuit board is provided with front voltage testing circuit, constant-current source circuit and from gain circuitry;
Spherical shell outer surface epoxy carbon dope coating, sun absorption coefficient and total hemisphere emission ratio ratio of described coating are 0.95 ~ 1.2, and coating thickness is not less than 15 μm; Left quarter butt and right quarter butt symmetry be arranged on the outside surface of spherical shell, built-in housing and internal circuit board are arranged at the inside of spherical shell; Described constant-current source circuit connects spherical shell outside surface, for the bias current of spherical shell surface applying scope at (-300nA, 300nA); Describedly connect spherical shell and built-in housing respectively from gain circuitry, for built-in housing electromotive force being placed in the electromotive force of spherical shell; Described front voltage testing circuit connects the outside surface of spherical shell, for gathering the space potential responded on spherical shell surface and exporting.
Beneficial effect:
The first, the present invention is in sensor surface coating epoxy carbon dope coating, by the design of coating, enhances the atomic oxygen erosion of sensor and the ability of uvioresistant irradiation, thus improves the life-span of sensor operation on orbit very well.
The second, the present invention arranges constant-current source circuit and applies bias current to spherical shell surface, effectively reduces plasma sheath layer impedance around sensor;
Three, the present invention utilizes and is placed on sensor electromotive force by the electromotive force of built-in housing from gain circuitry, thus reduces the stray capacitance of sensor.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of the sensor for space electric field detection.
Wherein, 1-spherical shell, 2-coating, the built-in housing of 3-, the left quarter butt of 4-, the right quarter butt of 5-.
Embodiment
Below in conjunction with accompanying drawing, the invention will be further described.
As shown in Figure 1, a kind of sensor for space electric field detection of the present invention, comprises spherical shell, built-in housing, internal circuit board, left quarter butt and right quarter butt; Wherein said internal circuit board is provided with front voltage testing circuit, constant-current source circuit and from gain circuitry.
The present invention adopts spherical shell, and the better radius of spherical shell that makes is greater than 35mm; Spherical probes is for aciculiform and cylindricality probe, and symmetry is good, and large at the area of space collection electron stream, ion current, and transducer sensitivity is high.
It is the epoxy carbon dope coating of 0.95 ~ 1.2 that the present invention applies too number sun absorption system and total hemisphere emission ratio ratio on spherical shell surface, and coating thickness is not less than 15 μm; Acting as of coating: the sub-oxygen attack of meeting spatial environmental antigens and uvioresistant irradiation application requirement, meet specific thermal radiation property; Make the surface work function of sensor have uniformity consistency simultaneously.
The left quarter butt of the present invention and right quarter butt symmetry be arranged on spherical shell outside surface, left quarter butt and right quarter butt are identical columnar hollow quarter butt, and the spherical shell radius that quarter butt one end is greater than 2 times to the distance of the centre of sphere, quarter butt external diameter is greater than 0.25 times of spherical shell radius, is less than 0.33 times of spherical shell radius.This parameter designing both ensure that the swept area of different azimuth spherical shell was consistent, ensured that again the area that spherical shell exposes is enough large aloft.A pair symmetrical quarter butt can make the spherical sensors solar radiation area being in space diverse location identical, namely ensures the consistance that sensor surface photocurrent is launched.
The built-in housing of the present invention and internal circuit board are arranged at the inside of spherical shell.
Constant-current source circuit connects spherical shell outside surface, for the bias current of spherical shell surface applying scope at (-300nA, 300nA); Acting as of constant-current source circuit: for reducing plasma sheath layer impedance around sensor, improves electric field measurement precision.What adopt compared to existing space electric field acquisition sensor in the world is applicable to the ionospheric (-300nA of F2, bias current 100nA), sensor designed by the present invention expands the scope of bias current, be applicable to F2 ionosphere until magnetosphere, improve the environmental suitability of sensor.Constant-current source circuit design bias current response frequency of the present invention is not less than 10kHz, to improve the stability of sensor bias current when responding high-frequency electric field, thus improves electric field measurement precision.
Spherical shell and built-in housing is connected respectively from gain circuitry, for the electromotive force of built-in housing being placed in sensor electromotive force (for making the electromotive force of spherical shell identical with the electromotive force of built-in housing), thus reduce the stray capacitance of sensor, improve sensor bias current response frequency etc.
Front voltage testing circuit connects the outside surface of spherical shell, for gathering the space potential that spherical shell surface is responded to, is then exported by wire.
By above design, sensor can reach the electric field measurement function in the plasma ambient of space, and has that response is fast, precision is high, the feature of good stability.
Claims (3)
1., for a sensor for space electric field detection, it is characterized in that, comprise spherical shell, built-in housing, internal circuit board, left quarter butt and right quarter butt; Wherein said internal circuit board is provided with front voltage testing circuit, constant-current source circuit and from gain circuitry;
Spherical shell outer surface epoxy carbon dope coating, sun absorption coefficient and total hemisphere emission ratio ratio of described coating are 0.95 ~ 1.2, and coating thickness is not less than 15 μm; Left quarter butt and right quarter butt symmetry be arranged on the outside surface of spherical shell, built-in housing and internal circuit board are arranged at the inside of spherical shell; Described constant-current source circuit connects spherical shell outside surface, for the bias current of spherical shell surface applying scope at (-300nA, 300nA); Describedly connect spherical shell and built-in housing respectively from gain circuitry, for built-in housing electromotive force being placed in the electromotive force of spherical shell; Described front voltage testing circuit connects the outside surface of spherical shell, for gathering the space potential responded on spherical shell surface and exporting.
2. according to claim 1 for the sensor of space electric field detection, it is characterized in that, described left quarter butt is identical with right quarter butt, the spherical shell radius that quarter butt one end is greater than 2 times to the distance of the centre of sphere, quarter butt external diameter is greater than 0.25 times of spherical shell radius, is less than 0.33 times of spherical shell radius.
3., according to claim 1 for the sensor of space electric field detection, it is characterized in that, the radius of described spherical shell is greater than 35mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410446705.6A CN104237653A (en) | 2014-09-04 | 2014-09-04 | Sensor for space electric field detection |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410446705.6A CN104237653A (en) | 2014-09-04 | 2014-09-04 | Sensor for space electric field detection |
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| CN104237653A true CN104237653A (en) | 2014-12-24 |
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| CN201410446705.6A Pending CN104237653A (en) | 2014-09-04 | 2014-09-04 | Sensor for space electric field detection |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105158586A (en) * | 2015-09-11 | 2015-12-16 | 兰州空间技术物理研究所 | Active space electric field detection sensor built-in circuit |
| CN106597131A (en) * | 2016-12-19 | 2017-04-26 | 兰州空间技术物理研究所 | Ground signal input device for space electric field detecting sensor |
| CN106771675A (en) * | 2016-12-19 | 2017-05-31 | 兰州空间技术物理研究所 | Using the probe and measuring method of bias current measurement Plasma space potential |
| CN109813973A (en) * | 2018-12-18 | 2019-05-28 | 兰州空间技术物理研究所 | A kind of bias current calibration method for space electric field survey meter |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105158586A (en) * | 2015-09-11 | 2015-12-16 | 兰州空间技术物理研究所 | Active space electric field detection sensor built-in circuit |
| CN106597131A (en) * | 2016-12-19 | 2017-04-26 | 兰州空间技术物理研究所 | Ground signal input device for space electric field detecting sensor |
| CN106771675A (en) * | 2016-12-19 | 2017-05-31 | 兰州空间技术物理研究所 | Using the probe and measuring method of bias current measurement Plasma space potential |
| CN109813973A (en) * | 2018-12-18 | 2019-05-28 | 兰州空间技术物理研究所 | A kind of bias current calibration method for space electric field survey meter |
| CN109813973B (en) * | 2018-12-18 | 2021-02-19 | 兰州空间技术物理研究所 | Bias current calibration method for space electric field detector |
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