CN106291649A - A kind of utilization ground magnetic rigidity carries out space ion detector and determines calibration method - Google Patents

Abstract

The invention provides and a kind of utilize ground magnetic rigidity to carry out space ion detector determine calibration method, described method includes: step 1) the space ion detector that flies in-orbit of acquisition suffers the energy deposition result after the ion incidence of space at every sensor；Step 2) according to the Ring current calculating its present position in the geomagnetic latitude of orbit aerocraft, calculate selected space ionic charge number simultaneously, thus calculate the minimum ion energy that space ion detector is detected, utilize DSMC to calculate space ion energy deposition in every sensor according to minimum ion energy；Step 3) utilize step 1) the measurement result of energy deposition of every sensor and step 2) the space ion that the calculates energy deposition in every sensor, calculate the measurement error of space ion detector；Step 4) utilize measurement error that space ion detector is calibrated.

Description

A kind of utilization ground magnetic rigidity carries out space ion detector and determines calibration method

Technical field

The present invention relates to satellite space radiation environment monitoring technical field in-orbit, particularly relate to a kind of utilization ground magnetic rigidity Carry out space ion detector and determine calibration method.

Background technology

Space ion is the most important composition of space radiation environment, is also to threaten safety satellite, solar-system operation One of direct factor.Space charged particle is the main study subject in spatial environments research.Charged particle detection The history of existing decades, recognizes existing certain basis at present, but is as space section space charged particle Learn research deeply, the extensive infiltration of space technology, the mankind to the understanding of space charged particle and effect thereof constantly across More New step, also the continuous accuracy to space ion detector, resolution etc. propose new requirement.In order to ensure The indexs such as the accuracy of space ion detector, resolution reach requirement, not only need to carry out ground before transmission fixed Mark, in addition it is also necessary to after aircraft is entered the orbit, it is carried out test calibration.

Owing to there is deflection and the effect of restraint in earth's magnetic field at terrestrial space, space charged particle distribution is caused to present Go out anisotropy, and the most different in the ion power spectrum of differing heights, the different longitude and latitude earth, and then make band electrochondria The radiation effect of satellite be there is also each to difference by son.Earth's magnetic field makes to come from the space ion deflecting in universe, makes Become energetic ion to cannot be introduced into earth low orbit, and diverse location also differs, partially for space ion deflecting ability The ability that turns generally uses ground magnetic rigidity to be described.When the space ion coming from universe is less than the ground at locus Magnetic rigidity, then will be unable to arrive less than the ion of ground magnetic rigidity correspondence energy, ion energy corresponding to rigidity will be to Reaching the minimum energy ion of position, local magnetic field configuration keeps stable the most then its rigidity by holdings stably, its mental retardation Amount ion is also stable by holding.

The test calibration of the mission phase in-orbit of space ion detection at present uses and intersects calibration or carry radioactive source two The method of kind.The calibrating method that intersects needs to find the other space ion detection accepting same or like ion source irradiation Instrument is compared test, and when not having other detection instrument, the method cannot use.Carry radioactive source method needs All carry radioactive source at whole flight course, there is the problem increasing instrument complexity.

Summary of the invention

It is an object of the invention to the problems referred to above overcoming current satellite spatial ion detection instrument In-flight calibration to exist, Providing and a kind of utilize ground magnetic rigidity to carry out space ion detector to determine calibration method, the method utilizes ultra rays ion Entering after terrestrial space, deflecting due to the effect by magnetic field of the earth, cause low-energy ion without Method enters, and this ability in magnetic field of the earth is referred to as earth cut-off rigidity, when the situation of terrestrial space ambient stable Under, position, magnetic field of the earth shape is also stable by holding, and earth cut-off rigidity is also stable by holding, now can arrive the earth The space ultra rays ion energy of overhead ad-hoc location keeps stable, and its energy can be quantified, and utilizes space The nearest low-energy These characteristics of cosmos line, can be used to calibrate space ion detector.

For achieving the above object, the present invention propose a kind of utilize ground magnetic rigidity carry out space ion detector calibration Method, described method includes:

Step 1) obtain the space ion detector that flies in-orbit and suffer after the ion incidence of space the energy at every sensor Amount deposition results Δ E_i；

Step 2) according to calculating the Ring current of its present position in the geomagnetic latitude of orbit aerocraft, calculate simultaneously Selected space ionic charge number, thus calculates the minimum ion energy that space ion detector is detected, according to Ion energy utilizes DSMC to calculate space ion energy deposition δ E in every sensor_i；

Step 3) utilize step 1) the measurement result of energy deposition of every sensor and step 2) calculate Space ion energy deposition in every sensor, the measurement error of calculating space ion detector:

${\mathrm{\ϵ}}_i=\left|\frac{\mathrm{\Δ}{E}_i-\mathrm{\δ}{E}_i}{\mathrm{\δ}{E}_i}\right|\×100\%$

Step 4) utilize measurement error that space ion detector is calibrated.

In technique scheme, described step 2) specifically include:

Step 201) calculate its present position according to geographic logitude, geographic latitude and the altitude data at orbit aerocraft Geomagnetic latitude:

φ=pi/2-arccos (sin θ × sin θ₀+cosθ×cosθ₀×cos(λ-λ₀)) (1)

Wherein, φ is the geomagnetic latitude at orbit aerocraft, θ and λ is in the geographic latitude of orbit aerocraft and geographic logitude, θ₀And λ₀For magnetic north latitude and magnetic north longitude, unit is radian；H is the elevation at orbit aerocraft；

Step 202) according to step 201) to calculate the geomagnetic cutoff of space ion detector firm for the geomagnetic latitude that calculates Degree:

R_c=(59.6cos⁴φ)(r+h)^-2[1+(1-cosXcos³φ)^1/2]^-2 (2)

Wherein, R_cFor Ring current；R is earth radius, and X is ion detector visual field, space and position The angle in west；

Step 203) type of selected space ion, and calculate space ionic charge number q:

Q=0.98+1.45 × ln (Z)+0.78 × [ln (Z)]² (3)

Wherein, the charge number that q is carried by space ion, Z is the atomic of selected space ion；

Step 204) according to step 202) calculate Ring current and step 203) the space ion that calculates The minimum ion energy that charge number calculating space ion detector is detected:

$E_c={[{(q\×\frac{R_c}{A})}^2+{E_0}^2]}^{1/2}-E_0---\left(4\right)$

Wherein, E₀=0.938GeV, A are the atomic mass of space ion；E_cFor the minimum energy of ion can be measured Amount；

Step 205) according to step 204) the minimum ion energy that calculates, utilize DSMC calculate its Energy deposition δ E in i-th sensor_i。

In technique scheme, the sensor type of described space ion detector is quasiconductor or scintillator.

It is an advantage of the current invention that:

1, the space ion detection instrument flown in-orbit can be calibrated by the method for invention, it is to avoid radioactive source peace Dress and the problem of management, it is simple to apply at instrument development, the in-orbit stage such as management and market demand；

2, the calibrating method of the present invention is suitable for the space ion detector calibration of various kinds of sensors on orbit aerocraft.

Accompanying drawing explanation

Fig. 1 is that the ground magnetic rigidity that utilizes of the present invention carries out space ion detector and determines the flow chart of calibration method.

Detailed description of the invention

With specific embodiment, the method for the present invention is described in detail below in conjunction with the accompanying drawings.

As it is shown in figure 1, a kind of utilization ground magnetic rigidity carries out space ion detector and determines calibration method, described method bag Include following steps:

Step 1) obtain the space ion detector that flies in-orbit and suffer after the ion incidence of space at every sensor measurement Energy deposition result Δ E_i；

The energy deposition measurement result of i-th sensor is designated as Δ E_i, unit MeV；Described space ion detector Sensor type is quasiconductor or scintillator.

Step 2) calculate space ion energy deposition in every sensor；Specifically include:

Step 201) calculate its present position according to geographic logitude, geographic latitude and the altitude data at orbit aerocraft Geomagnetic latitude:

φ=pi/2-arccos (sin θ × sin θ₀+cosθ×cosθ₀×cos(λ-λ₀)) (1)

Wherein, φ is the geomagnetic latitude at orbit aerocraft, θ and λ is in the geographic latitude of orbit aerocraft and geographic logitude, Wherein, earth south poles, overhead, South Atlantic Ocean are abnormal area；θ₀And λ₀For magnetic north latitude and magnetic north Longitude, unit is radian；H is the elevation at orbit aerocraft, and unit is rice.

Step 202) calculate the Ring current of space ion detector:

R_c=(59.6cos⁴φ)(r+h)^-2[1+(1-cosXcos³φ)^1/2]^-2 (2)

Wherein, R_cFor Ring current, unit is GeV；R is earth radius, and unit is rice；X be space from Sub-detector field of view and the angle in west, position.

Step 203) type of selected space ion, and calculate space ionic charge number q:

Q=0.98+1.45 × ln (Z)+0.78 × [ln (Z)]² (3)

Wherein, the charge number that q is carried by space ion, Z is the atomic of selected space ion.

The atomic of selected ion is less than 30, it is to avoid atomic is too high and flux is extremely low and energy is high.

Step 204) according to step 202) calculate Ring current and step 203) the space ion that calculates The minimum ion energy that charge number calculating space ion detector is detected:

$E_c={[{(q\×\frac{R_c}{A})}^2+{E_0}^2]}^{1/2}-E_0---\left(4\right)$

Wherein, E₀=0.938GeV, A are the atomic mass of space ion.E_cAlso measure for space ion detector The least energy arrived

Step 205) according to step 204) the minimum ion energy that calculates, utilize DSMC to calculate space Ion energy deposition δ E in i-th sensor_i；

In the present embodiment, when the least energy calculating helium (He) ion is 400MeV, Monte Carlo is utilized The method energy deposition obtained in silicon (Si) sensor of continuous 3 1mm is followed successively by 5.69MeV, 5.75MeV And 5.81MeV.

Step 3) utilize step 1) the measurement result of energy deposition of every sensor and step 2) calculate Space ion energy deposition in every sensor, the measurement error of calculating space ion detector:

${\mathrm{\ϵ}}_i=\left|\frac{\mathrm{\Δ}{E}_i-\mathrm{\δ}{E}_i}{\mathrm{\δ}{E}_i}\right|\×100\%$

Step 4) utilize measurement error that space ion detector is calibrated.

It should be noted last that, above example is only in order to illustrate technical scheme and unrestricted.Although With reference to embodiment, the present invention is described in detail, it will be understood by those within the art that, to the present invention Technical scheme modify or equivalent, without departure from the spirit and scope of technical solution of the present invention, it is equal Should contain in the middle of scope of the presently claimed invention.

Claims (3)

1. utilizing ground magnetic rigidity to carry out space ion detector and determine a calibration method, described method includes:

Step 1) obtain the space ion detector that flies in-orbit and suffer after the ion incidence of space the energy at every sensor Amount deposition results Δ E_i；

Step 2) according to calculating the Ring current of its present position in the geomagnetic latitude of orbit aerocraft, calculate simultaneously Selected space ionic charge number, thus calculates the minimum ion energy that space ion detector is detected, according to Ion energy utilizes DSMC to calculate space ion energy deposition δ E in every sensor_i；

Step 3) utilize step 1) the measurement result of energy deposition of every sensor and step 2) calculate Space ion energy deposition in every sensor, the measurement error of calculating space ion detector:

${\mathrm{\ϵ}}_i=\left|\frac{{\mathrm{\ΔE}}_i-{\mathrm{\δE}}_i}{{\mathrm{\δE}}_i}\right|\×100\%$

Step 4) utilize measurement error that space ion detector is calibrated.

Utilization ground the most according to claim 1 magnetic rigidity carries out space ion detector and determines calibration method, and it is special Levy and be, described step 2) specifically include:

Step 201) calculate its present position according to geographic logitude, geographic latitude and the altitude data at orbit aerocraft Geomagnetic latitude:

φ=pi/2-arccos (sin θ × sin θ₀+cosθ×cosθ₀×cos(λ-λ₀)) (1)

Wherein, φ is the geomagnetic latitude at orbit aerocraft, θ and λ is in the geographic latitude of orbit aerocraft and geographic logitude, θ₀And λ₀For magnetic north latitude and magnetic north longitude, unit is radian；H is the elevation at orbit aerocraft；

Step 202) according to step 201) to calculate the geomagnetic cutoff of space ion detector firm for the geomagnetic latitude that calculates Degree:

R_c=(59.6cos⁴φ)(r+h)^-2[1+(1-cosXcos³φ)^1/2]^-2 (2)

Wherein, R_cFor Ring current；R is earth radius, and X is ion detector visual field, space and position The angle in west；

Step 203) type of selected space ion, and calculate space ionic charge number q:

Q=0.98+1.45 × ln (Z)+0.78 × [ln (Z)]² (3)

Wherein, the charge number that q is carried by space ion, Z is the atomic of selected space ion；

Step 204) according to step 202) calculate Ring current and step 203) the space ion that calculates The minimum ion energy that charge number calculating space ion detector is detected:

$E_c={[{(q\×\frac{R_c}{A})}^2+{E_0}^2]}^{1/2}-E_0---\left(4\right)$

Wherein, E₀=0.938GeV, A are the atomic mass of space ion；E_cFor the minimum energy of ion can be measured Amount；

Step 205) according to step 204) the minimum ion energy that calculates, utilize DSMC calculate its Energy deposition δ E in i-th sensor_i。

Utilization ground the most according to claim 1 and 2 magnetic rigidity carries out space ion detector and determines calibration method, It is characterized in that, the sensor type of described space ion detector is quasiconductor or scintillator.