CN112363201A - Method for acquiring high-energy electronic energy spectrum data of medium orbit satellite - Google Patents

Method for acquiring high-energy electronic energy spectrum data of medium orbit satellite Download PDF

Info

Publication number
CN112363201A
CN112363201A CN202011249443.6A CN202011249443A CN112363201A CN 112363201 A CN112363201 A CN 112363201A CN 202011249443 A CN202011249443 A CN 202011249443A CN 112363201 A CN112363201 A CN 112363201A
Authority
CN
China
Prior art keywords
energy
flux
orbit
medium
1mev
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN202011249443.6A
Other languages
Chinese (zh)
Other versions
CN112363201B (en
Inventor
薛炳森
周颜
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
National Satellite Meteorological Center
Original Assignee
National Satellite Meteorological Center
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by National Satellite Meteorological Center filed Critical National Satellite Meteorological Center
Priority to CN202011249443.6A priority Critical patent/CN112363201B/en
Publication of CN112363201A publication Critical patent/CN112363201A/en
Application granted granted Critical
Publication of CN112363201B publication Critical patent/CN112363201B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01T—MEASUREMENT OF NUCLEAR OR X-RADIATION
    • G01T1/00—Measuring X-radiation, gamma radiation, corpuscular radiation, or cosmic radiation
    • G01T1/36—Measuring spectral distribution of X-rays or of nuclear radiation spectrometry
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01T—MEASUREMENT OF NUCLEAR OR X-RADIATION
    • G01T1/00—Measuring X-radiation, gamma radiation, corpuscular radiation, or cosmic radiation
    • G01T1/02—Dosimeters

Landscapes

  • Physics & Mathematics (AREA)
  • Spectroscopy & Molecular Physics (AREA)
  • Health & Medical Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • General Physics & Mathematics (AREA)
  • High Energy & Nuclear Physics (AREA)
  • Molecular Biology (AREA)
  • Measurement Of Radiation (AREA)

Abstract

The invention discloses a method for acquiring high-energy electron spectrum data of a medium orbit satellite, which comprises the steps of collecting high-energy electron 24-hour integral flux with energy more than 2MeV on a geosynchronous orbit; calculating the maximum differential flux of the 1MeV high-energy electrons corresponding to 4 passes in 24 hours according to the integral flux; and calculating the energy spectrum of the high-energy electrons according to the maximum value of the maximum differential flux. According to the invention, the high-energy electron flux and energy spectrum conditions of the core area of the external radiation zone passed by the medium orbit satellite can be calculated according to the high-energy electron flux data monitored by the stable geosynchronous orbit.

Description

Method for acquiring high-energy electronic energy spectrum data of medium orbit satellite
Technical Field
The invention belongs to the field of high-energy electronic energy spectrum data of a medium orbit satellite, and particularly relates to a method for acquiring the high-energy electronic energy spectrum data of the medium orbit satellite.
Background
The medium orbit (MEO) is a satellite orbit with the height of about 20000 kilometers, and is the operation orbit of most global navigation satellites, the height of the medium orbit is just the height of the center of an earth external radiation zone, an equatorial region through which the medium orbit passes is just the center region of the external radiation zone, high-energy electrons can pass through a protective layer of the satellite and deposit on a medium inside the satellite, a deep charging effect can be caused, and the abnormal condition and even the fault condition of the satellite can be caused in the serious condition.
To estimate the severity of the deep charging effect of materials at different thicknesses, it is necessary to accurately know the worst high-energy electron environment, i.e., the worst high-energy electron spectrum, in the satellite orbit. However, not all the medium orbit satellites are equipped with high-energy electronic monitoring equipment, and therefore, the severe high-energy electronic environment of the medium orbit needs to be inverted through continuous monitoring data of related elements, so that timely grasping of the flux and energy spectrum of the high-energy electronic orbit of the medium orbit satellite is an important part for guaranteeing the safety of the satellite space environment, but most of the medium orbit satellites are not equipped with high-energy electronic detection equipment, and high-energy electronic detection data cannot be downloaded in real time, so that a satellite management mechanism cannot timely grasp the high-energy electronic environment of the satellite. Therefore, a method for acquiring the high-energy electronic energy spectrum data of the medium-orbit satellite is needed.
Disclosure of Invention
The invention aims to provide a method for acquiring high-energy electronic spectrum data of a medium orbit satellite.
The method comprises the following steps:
step 1: collecting high-energy electron 24-hour integral flux with energy more than 2MeV on a geosynchronous orbit;
step 2: calculating the maximum differential flux of the 1MeV high-energy electrons corresponding to 4 passes in 24 hours according to the integral flux;
and step 3: and calculating the energy spectrum of the high-energy electrons according to the maximum value of the maximum differential flux and calculating the logarithm relative error of the high-energy electrons.
Further, the differential flux of 1MeV high-energy electrons during the transit of the mid-orbit satellite through the core region of the outer radiating zone over the same 24 hour period can be expressed as:
fm1＝1.7×106+3.75×106×(log10FG-6.845) (1)
wherein fm1 is the high-energy electron differential flux of the middle orbital 1MeV, and the unit is cm-2s-1sr-1MeV-1(ii) a FG is the fluence in cm of high-energy electrons with energies greater than 2MeV in the last 24 hours of geosynchronous orbit-2sr-1。
Further, the formula for the differential flux of high energy electrons of 1MeV can be expressed as:
fm(E)＝10-1.11(E-1)+lg(fm1)
(2)
where fm (E) represents the high energy electron differential flux with energy E in cm-2s-1sr-1MeV-1(ii) a E represents the energy of the high-energy electron in MeV.
Further, the formula for calculating the logarithmic relative error of the high-energy electron flux of the middle orbit 1MeV is as follows:
Figure BDA0002771131310000031
in the formula f0To monitor the value, fcIs a calculated value. The calculated log relative error for the maximum high energy electron flux for orbital 1MeV during that day was 2.89%.
The invention has the following beneficial effects:
according to the invention, the high-energy electron flux and energy spectrum conditions of the core area of the external radiation zone penetrated by the medium orbit satellite can be calculated according to the high-energy electron flux data monitored by the stable geosynchronous orbit.
Drawings
FIG. 1 is a schematic flow diagram of the present invention;
Detailed Description
As shown in fig. 1, in this example, the present invention takes 30/4/2020 as an example, and calculates the maximum flux of 1MeV high-energy electrons of the medium-orbit satellite and the corresponding high-energy electron energy spectrum by using the daily integrated flux of high-energy electrons with energy greater than 2MeV measured by the GOES satellite, as a result of verifying that the detected data of the medium-orbit high-energy electrons is the GPS satellite with number 70.
In the present example, the present invention is 1.1X 10 in 2017, 4 months and 30 days (UT)9cm-2sr-1. Equation (1) is called, and FG is made 1.1 × 109Fm1 is obtained by9cm-2sr-1s-1MeV-1. Comparing with the data of satellite detection running on the middle orbit on the same day, the maximum flux on the same dayThe 1MeV high-energy electron differential flux of the region is 6.1X 106cm-2sr-1s-1MeV-1。
Step one, calculating the integrating flux of the geosynchronous orbit high-energy electrons in the last 24 hours, wherein the input data of the geosynchronous orbit high-energy electron flux can be obtained from a web site of the American space weather forecast center, and the integrating flux of the geosynchronous orbit high-energy electrons in the last 24 hours can be obtained.
And step two, substituting the integrated flux of which the energy is more than 2MeV in the last 24 hours of the geosynchronous orbit obtained in the step one into the formula (1), so as to obtain the maximum value of the 1MeV high-energy electronic differential flux in the process that the orbiting satellite passes through the core area of the outer radiation zone in the same time period.
Step three, changing Fm1 to 9.8 × 109Substituting equation (2) into E1.6 MeV, the differential flux of high-energy electrons with energy of 1.6MeV in the maximum flux region of the middle orbit is 2.14 × 109cm-2sr-1s-1MeV-1(ii) a When E is 2MeV, the differential flux of high-energy electrons having an energy of 2MeV in the maximum flux region of the middle orbit is 7.91 × 105cm-2sr-1s-1MeV-1. The high-energy electron differential flux of the orbit 1.6MeV in the day is 2.2 multiplied by 109cm-2sr-1s-1MeV-1(ii) a 2MeV high-energy electron differential flux of 4.5X 105cm-2sr-1s-1MeV-1. According to equation (3), the logarithmic relative errors are respectively: 0.19% and 4.31%.
The invention can evaluate the orbit high-energy electron energy spectrum in calculation according to the electron flux of 24 hours with the geosynchronous orbit energy being more than 2 MeV.
In order to test the feasibility of the provided calculation method, the maximum value of the high-energy electron differential flux of 1MeV, 1.6MeV and 2MeV of the medium orbit satellite P70 satellite at the independent (UT) of 2016 (8 months) to 10 months is selected for testing, and the input data is that the energy of the GOES satellite in the same time period is larger than the high-energy electron 24-hour integral flux of 2 MeV.
According to the calculation method given in "implementation procedure", the maximum values of the high-energy electron differential fluxes of the mid-orbit satellites 1MeV, 1.6MeV, and 2MeV of the above 41 time periods are calculated respectively and compared with the measured values of the mid-orbit satellites at the desired energy, and the results are shown in table 1.
The calculation results of the high-energy electron flux mode of the orbit in Table 1 are compared with the actual measurement results
Figure BDA0002771131310000051
Figure BDA0002771131310000061
In the evaluation of the high-energy particle flux model of the medium and high orbit satellite, the logarithmic flux relative error is generally adopted for evaluation, and the formula is as follows:
Figure BDA0002771131310000062
where err is the log flux relative error; lgf0(m) observations of differential flux at a certain energy of the medium orbit moat satellite, lgfc(m) is a differential flux calculation value of a corresponding time period, and m is a sample number.
By applying the method given in the formula (4), the present invention evaluates the calculation results of the middle orbits 1MeV, 1.6MeV and 2MeV provided in table 1 against the detection results of the corresponding energies of the middle orbits in the same period, and obtains relative errors of the differential fluxes of 1MeV, 1.6MeV and 2MeV of 5.13%, 6.28% and 7.28%, respectively.
The evaluation result shows that the method for deducing the high-energy electron energy spectrum of the medium-orbit high-energy electron E >1MeV based on the 24-hour integrated flux with the geosynchronous orbit energy larger than 2MeV is feasible.
Although the embodiments of the present invention have been described above, the above descriptions are only for the convenience of understanding the present invention, and are not intended to limit the present invention. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.

Claims (4)

1. A method for acquiring high-energy electronic energy spectrum data of a medium orbit satellite comprises the following steps:
step 1: collecting high-energy electron 24-hour integral flux with energy more than 2MeV on a geosynchronous orbit;
step 2: calculating the maximum differential flux of the 1MeV high-energy electrons corresponding to 4 passes in 24 hours according to the integral flux;
and step 3: and calculating the energy spectrum of the high-energy electrons according to the maximum value of the maximum differential flux and calculating the logarithm relative error of the high-energy electrons.
2. The method for acquiring the energy spectrum data of the high-energy electrons of the medium-orbit satellite according to claim 1, wherein the differential flux of the high-energy electrons of 1MeV in the process that the medium-orbit satellite passes through the core area of the outer radiation zone in the same 24-hour time period can be expressed as follows:
fm1＝1.7×106+3.75×106×(log10FG-6.845) (1)
wherein fm1 is the high-energy electron differential flux of the middle orbital 1MeV, and the unit is cm-2s-1sr-1MeV-1(ii) a FG is the fluence in cm of high-energy electrons with energies greater than 2MeV in the last 24 hours of geosynchronous orbit-2sr-1。
3. The method for acquiring the energy spectrum data of the medium orbit satellite high-energy electrons as claimed in claim 1, wherein the formula of the differential flux of the high-energy electrons of 1MeV can be expressed as follows:
Figure FDA0002771131300000011
where fm (E) represents the high energy electron differential flux with energy E in cm-2s-1sr-1MeV-1(ii) a E represents the energy of the high-energy electron in MeV.
4. The method for acquiring the high-energy electron spectrum data of the medium-orbit satellite according to claim 1, wherein the formula for calculating the logarithmic relative error of the high-energy electron flux of the medium-orbit 1MeV is as follows:
Figure FDA0002771131300000021
in the formula f0To monitor the value, fcIs a calculated value. The calculated log relative error for the maximum high energy electron flux for orbital 1MeV during that day was 2.89%.
CN202011249443.6A 2020-11-10 2020-11-10 Method for acquiring high-energy electronic energy spectrum data of medium orbit satellite Active CN112363201B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202011249443.6A CN112363201B (en) 2020-11-10 2020-11-10 Method for acquiring high-energy electronic energy spectrum data of medium orbit satellite

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202011249443.6A CN112363201B (en) 2020-11-10 2020-11-10 Method for acquiring high-energy electronic energy spectrum data of medium orbit satellite

Publications (2)

Publication Number Publication Date
CN112363201A true CN112363201A (en) 2021-02-12
CN112363201B CN112363201B (en) 2023-03-14

Family

ID=74509547

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202011249443.6A Active CN112363201B (en) 2020-11-10 2020-11-10 Method for acquiring high-energy electronic energy spectrum data of medium orbit satellite

Country Status (1)

Country Link
CN (1) CN112363201B (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113126142A (en) * 2021-04-16 2021-07-16 应急管理部国家自然灾害防治研究院 High-energy particle detector performance evaluation method and system
CN115932937A (en) * 2022-12-26 2023-04-07 数字太空(北京)智能技术研究院有限公司 Method and system for determining medium-orbit high-energy electron energy spectrum

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USH2171H1 (en) * 1997-12-31 2006-09-05 The United States Of America As Represented By The Secretary Of The Navy Method and apparatus for modeling cosmic ray effects on microelectronics
CN105701327A (en) * 2014-10-31 2016-06-22 中国科学院空间科学与应用研究中心 Method for assessing radiation dose rate of earth-orbiting satellite
CN107329146A (en) * 2017-07-05 2017-11-07 中国人民解放军装备学院 A kind of low rail of aeronautical satellite monitors the Optimization Design of constellation
CN110457780A (en) * 2019-07-23 2019-11-15 上海卫星装备研究所 Deep dielectric charging current potential and charge inside electric field acquisition methods and storage medium
CN111505454A (en) * 2020-04-22 2020-08-07 国家卫星气象中心(国家空间天气监测预警中心) Method for monitoring deep charging of internal medium of satellite

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USH2171H1 (en) * 1997-12-31 2006-09-05 The United States Of America As Represented By The Secretary Of The Navy Method and apparatus for modeling cosmic ray effects on microelectronics
CN105701327A (en) * 2014-10-31 2016-06-22 中国科学院空间科学与应用研究中心 Method for assessing radiation dose rate of earth-orbiting satellite
CN107329146A (en) * 2017-07-05 2017-11-07 中国人民解放军装备学院 A kind of low rail of aeronautical satellite monitors the Optimization Design of constellation
CN110457780A (en) * 2019-07-23 2019-11-15 上海卫星装备研究所 Deep dielectric charging current potential and charge inside electric field acquisition methods and storage medium
CN111505454A (en) * 2020-04-22 2020-08-07 国家卫星气象中心(国家空间天气监测预警中心) Method for monitoring deep charging of internal medium of satellite

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
杨晓超等: "中地球轨道高能电子辐射环境特性分析", 《空间科学学报》 *
王子凤等: "MEO卫星内部充电环境及典型材料充电特征分析", 《航天器环境工程》 *
王春琴等: "地球同步轨道系列卫星自主空间辐射环境监测及应用", 《上海航天》 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113126142A (en) * 2021-04-16 2021-07-16 应急管理部国家自然灾害防治研究院 High-energy particle detector performance evaluation method and system
CN115932937A (en) * 2022-12-26 2023-04-07 数字太空(北京)智能技术研究院有限公司 Method and system for determining medium-orbit high-energy electron energy spectrum

Also Published As

Publication number Publication date
CN112363201B (en) 2023-03-14

Similar Documents

Publication Publication Date Title
CN112363201B (en) Method for acquiring high-energy electronic energy spectrum data of medium orbit satellite
Walter et al. Evaluation of signal in space error bounds to support aviation integrity
Bornmann et al. GOES X-ray sensor and its use in predicting solar-terrestrial disturbances
CN113158533B (en) High-energy proton energy spectrum calculation method and calculation system
Griggs et al. Short-term GNSS satellite clock stability
Menn et al. Measurement of the Absolute Proton and Helium Flux at the Top of the Atmosphere using IMAX
Welling The long-term effects of space weather on satellite operations
Rosenqvist et al. Toolkit for updating interplanetary proton cumulated fluence models
Villoresi et al. Cosmic ray survey to Antarctica and coupling functions for neutron component near solar minimum (1996–1997): 1. Methodology and data quality assurance
CN111505454B (en) Method for monitoring deep charging of internal medium of satellite
Chen et al. Determining ionizing doses in medium Earth orbits using long-term GPS particle measurements
Reagan et al. The effects of energetic particle precipitation on the atmospheric electric circuit
CN109255143B (en) On-orbit spacecraft electrification risk assessment method based on multi-factor synergistic effect
US9372483B2 (en) Method for the calculation of flight paths taking into consideration events of relevance for radiation dose
Koons et al. Spatial and temporal correlation of spacecraft surface charging in geosynchronous orbit
Warnant et al. Mitigation of ionospheric effects on GNSS
Dhani et al. Systematic Biases in Estimating the Properties of Black Holes Due to Inaccurate Gravitational-Wave Models
Sellers et al. Rocket‐measured effective recombination coefficients in the disturbed D region
Chen et al. Calculating Ionizing Doses in Geosynchronous Orbit from In-situ Particle Measurements and Models
Xapsos et al. Periods of high intensity solar proton flux
Datta-Barua Ionospheric threats to the integrity of airborne GPS users
CN115932937A (en) Method and system for determining medium-orbit high-energy electron energy spectrum
Boyd et al. Environmental specification accuracy requirements for anomaly resolution in various orbits
Enengl et al. Characterization of Jason-3 Spacecraft Surface Charging in LEO Polar Regions From AMBER Observations
Galand Introduction to special section: Proton precipitation into the atmosphere

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant