AE9/AP9/SPM Radiation Environment Model - dtic.mil RADIATION ENVIRONMENT MODEL: USER'S GUIDE . ......

AFRL-RV-PS- AFRL-RV-PS- TR-2014-0013 TR-2014-0013

AE9/AP9/SPM RADIATION ENVIRONMENT MODEL: USER'S GUIDE

Christopher Roth

Atmospheric and Environmental Research, Inc. 131 Hartwell Ave. Lexington, MA 02421

18 February 2014

Technical Report

APPROVED FOR PUBLIC RELEASE; DISTRIBUTION IS UNLIMITED.

AIR FORCE RESEARCH LABORATORY Space Vehicles Directorate 3550 Aberdeen Ave SE AIR FORCE MATERIEL COMMAND KIRTLAND AIR FORCE BASE, NM 87117-5776

DTIC COPY

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//SIGNED// //SIGNED// _______________________________________ ______________________________________ Michael J. Starks, DR-III Edward J. Masterson, Colonel, USAF Senior Electrical Engineer, RVBXR Chief, Battlespace Environment Division

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Approved for public release; distribution is unlimited.

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3. DATES COVERED (From - To)11 Jul 2012 to 30 Jul 2013

4. TITLE AND SUBTITLE AE9/AP9/SPM Radiation Environment Model: User's Guide

5a. CONTRACT NUMBER

FA9453-12-C-0231

5b. GRANT NUMBER

5c. PROGRAM ELEMENT NUMBER 63401F

6. AUTHOR(S) Christopher Roth

5d. PROJECT NUMBER 5021 5e. TASK NUMBER PPM00012019 5f. WORK UNIT NUMBER EF007946 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)

Atmospheric and Environmental Research, Inc. 131 Hartwell Ave. Lexington, MA 02421

8. PERFORMING ORGANIZATION REPORTNUMBER

9. SPONSORING / MONITORING AGENCY NAME(S) AND ADDRESS(ES)

Air Force Research Laboratory Space Vehicles Directorate 3550 Aberdeen Avenue SE Kirtland AFB, NM 87117-5776

10. SPONSOR/MONITOR’S ACRONYM(S)

AFRL/RVBXR

11. SPONSOR/MONITOR’S REPORT NUMBER(S)

AFRL-RV-PS-TR-2014-0013 12. DISTRIBUTION / AVAILABILITY STATEMENT

Approved for public release; distribution is unlimited. (377ABW-2012-1280 dtd 25 Sep 2012)

13. SUPPLEMENTARY NOTES

14. ABSTRACTThis document is the user's guide for the AE9/AP9/SPM radiation environment model software. AE9/AP9/SPM is a climatological specification model for trapped energetic particles and plasma in the near-Earth environment. The report provides instructions for model installation and operation of the model through both the Command-Line and Graphical User interfaces. Detailed listings of model options are included plus instructions on how to obtain various desired outputs including flux, fluence and dose, and statistics on these quantities.

15. SUBJECT TERMSAE9/AP9/SPM, radiation belt model, space plasma model, user’s guide

16. SECURITY CLASSIFICATION OF: 17. LIMITATION OF ABSTRACT

18. NUMBER OF PAGES

19a. NAME OF RESPONSIBLE PERSON Dr. Michael Starks

a. REPORT Unclassified

b. ABSTRACTUnclassified

c. THIS PAGEUnclassified Unlimited 44

19b. TELEPHONE NUMBER (include area code)

Standard Form 298 (Rev. 8-98) Prescribed by ANSI Std. Z39.18

This page is intentionally left blank.


Table of Contents

AE9/AP9/SPM MODEL PROGRAM OVERVIEW ....................................................................................................... 3

MODEL INSTALLATION ........................................................................................................................................... 4

INSTALLATION TESTING .................................................................................................................................................... 4

COMMAND-LINE PROGRAM .................................................................................................................................. 5

INPUT FILE CONSTRUCTION .............................................................................................................................................. 5 BASIC MODEL INPUTS ..................................................................................................................................................... 6

Details about the Flux Data Modes .................................................................................................................... 10 AGGREGATION INPUTS .................................................................................................................................................. 11 DOSE CALCULATION INPUTS ........................................................................................................................................... 12 ORBITER PROPAGATOR INPUTS ....................................................................................................................................... 14

Two-Line Element Files ........................................................................................................................................ 17 ORBIT EPHEMERIS FILE DESCRIPTION ............................................................................................................................... 18 MODEL OUTPUT FILES .................................................................................................................................................. 18

Tandem AE9/AP9 and Plasma Model Calculations ............................................................................................. 19

GRAPHICAL USER INTERFACE PROGRAM ............................................................................................................. 20 SATELLITE TAB ............................................................................................................................................................. 21 MODEL TAB ................................................................................................................................................................ 24

AE9/AP9-specific notes ....................................................................................................................................... 25 PLOT TAB ................................................................................................................................................................... 27 EXAMPLE GUI-BASED MODEL RUNS ................................................................................................................................ 28

Example 1: MeanSample .................................................................................................................................... 29 Example 2: MonteCarloSample ........................................................................................................................... 31 Example 3: PerturbedMeanSample .................................................................................................................... 32

REFERENCES......................................................................................................................................................... 33

APPENDIX A: LEGACY MODELS AE8/AP8 AND CRRESELE/PRO-SPECIFIC PARAMETERS ........................................ .34

APPENDIX B: LEGACY MODEL CAMMICE/MICS-SPECIFIC PARAMETERS ............................................................... 36

APPENDIX C: MODIFIED JULIAN DATE .................................................................................................................. 37


i

Model Run Performance Tuning ........................................................................................................................ 19

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ii

AE9/AP9/SPM Radiation

Environment Model

User’s Guide

Windows and Linux Platforms


1

The AE9/AP9/SPM model was developed by the National Reconnaissance Office and the Air Force Research Laboratory in partnership with MIT Lincoln Laboratory, Aerospace Corporation, Boston College Institute for Scientific Research, Atmospheric and Environmental Research, Incorporated, and Los Alamos National Laboratory.

AE9/AP9 development team: Gregory Ginet1 (PI), T. Paul O’Brien2 (PI), Dave Byers3, Michael Starks4, Stuart Huston5,6, Wm. Robert Johnston4, Tim Guild2, Christopher Roth6, Paul Whelan6, Rick Quinn6, Reiner Friedel7, Chad Lindstrom4, Dan Madden5, Steve Morley7, and Yi-Jiun Su4.

Information on AE9/AP9 may be found on line at the NASA SET Radiation Model User Forum (http://lws-set.gsfc.nasa.gov/radiation_model_user_forum.html).

To contact the AE9/AP9 team, email [email protected].

V1.05.001 release: August 2013

1 MIT Lincoln Laboratory 2 Aerospace Corporation 3 National Reconnaissance Office 4 Air Force Research Laboratory, Space Vehicles Directorate 5 Boston College Institute for Scientific Research 6 Atmospheric and Environmental Research, Incorporated 7 Los Alamos National Laboratory


2

http://lws-set.gsfc.nasa.gov/radiation_model_user_forum.html

mailto:[email protected]

AE9/AP9/SPM Model Program Overview This delivery contains all files needed to install and execute the C++-based AE9/AP9/SPM Radiation Environment model, using a command-line program execution, or through a graphical user interface (GUI).

The Command-Line program ‘CmdLineAe9Ap9.exe’ reads model parameters and orbit specifications from user-constructed input files and produces the requested set of files containing flux and fluence calculation results. Dose calculation results are also available.

The GUI program ‘testAe9Ap9Gui.exe’ provides a graphical user interface to specify an orbital path and various model parameters in a user-friendly format. The GUI program executes the CmdLineAe9Ap9 program using the input files automatically generated according to the user’s selections in the interface. Basic 2D plots of the model results may also be produced.

In addition to this User’s Guide, there are several other files of information provided in this distribution. The ‘Readme_CmdLineAe9Ap9’ file provides a complete list of various database and supporting files used in the model. Several annotated samples of command-line input files are also supplied:

- Ae9Ap9CmdlineInputSample_V1_0.txt - Ae9Ap9CmdlineOrbitSample.txt - Ae8Ap8CrresCmdlineInputSample_V1_0.txt - CammiceCmdlineInputSample_V1_0.txt

Additional subdirectories contain several test files (both input and output) for verifying proper model installation and operation.

AE9/AP9 Code Stack

Graphical User Interface -User-friendly access to AE9/AP9, and other models, with basic graphical outputs High-level Utility Layer -Command line interface for producing mission statistics Aggregates results of many MC scenarios (flux, fluence, mean, percentiles) Provides access to orbit propagator and other models (e.g. AP8/AE8, CRRES) Provides dose rate and dose for user-specified thicknesses (ShieldDose-2) Application Layer -Simple C++ interface to single Monte-Carlo scenario “flyin()” routines AP9/AE9 Model Layer -Main workhorse; manages database access, coordinate transforms and Monte Carlo cycles; error matrix manipulations Low-level Utility Layer -Database access, Magnetic field, Hdf5 and Boost


3

Model Installation Version 1.00.003 of the AE9/AP9 Radiation Environment model is distributed as a zipfile, ‘Ae9Ap9_version_1.00.003.zip’, containing Windows release-mode binaries and libraries, model databases, sample input and output files and supporting documentation files. A separate source distribution may also be provided, upon request, for generating Windows debug-mode binaries, or for building the binaries on Linux platforms.

For a Windows installation, simply unzip the distribution file in the desired directory location. The directory structure will be as shown below:

For a Linux-based installation, unzip the source distribution file in the desired location, then refer to the detailed instructions in the ‘Build_Instructions_for_AE9AP9.pdf’ file in the ‘Ae9Ap9/documents’ directory.

Installation Testing Open a command line window, navigate to the directory containing the binary executables (ie Ae9Ap9/bin/win32), enter the command: CmdLineAe9Ap9 –i ../../consoleTests/short.txt

The resulting output files will be written in this same directory. Verify that the number of files generated, and respective file contents match that of the “shortOutput”-prefixed files located in the ‘../../consoleTests/expectedTestOutputs’ directory. Other test input files are also available in this ‘consoleTests’ directory, and their corresponding output files in the ‘expectedTestOutputs’ subdirectory.

Much more information regarding the CmdLineAe9Ap9 program is provided in the next section of this document.


4

To start the GUI program, enter the command (or double-click the icon for): testAe9Ap9Gui.exe

A detailed description of the GUI program follows in a later section of this document.

Command-Line Program The CmdLineAe9Ap9 program is a lightweight client application for running the ‘AE9/AP9’ and ‘Plasma’ models at time-tagged orbital positions. The requested model calculation results are written to comma-separated value (CSV) format text files. Other ‘legacy’ radiation belt models, ‘AE8’, ‘AP8’, ‘CRRESELE’, ‘CRRESPRO’ and ‘CAMMICE/MICS’, are also available within this same application.

The command-line utility takes input settings from an external file, which is passed to it using the input parameter ‘–i <filename>’. This feature permits the CmdLineAe9Ap9 program to be used in “batch” mode or within a script, and/or distributing large modeling tasks across multiple processors and servers. Very long model runs can easily be broken up by time or species, and the results merged using user-supplied post-processing scripts.

The format of the input file used to drive the CmdLineAe9Ap9 program, as well as the detailed model settings specified within it, are described below. A working sample input file, ‘Ae9Ap9CmdLineInputSample_V1_0.txt’ is provided in the ‘Ae9Ap9/bin/win32’ directory. This annotated sample file contains complete descriptions of all available input parameters to the model and all of the allowed values for each.

Input File Construction The basic format of the input file is ‘keyword/value’ pairs on each line: the parameter keyword name, followed by a colon and then the value or values for the parameter. Keywords and string values are not case-sensitive. Lines beginning with a ‘#’ symbol are treated as comments, and are therefore ignored by the program.

CmdLineAe9Ap9 input file settings can be logically grouped into the following categories: Basic Model Inputs – core model parameters, required for any model run Aggregation Inputs – optional settings for combining complex output results Dose Calculation Inputs – optional settings to drive the ShieldDose2 dose calculations Orbit Propagator Inputs – optional settings for generating orbit ephemeris

Input file settings for each of these categories are described in the following tables. Descriptions of the parameters used for the legacy models may be found in the Appendices.


5

Basi

c M

odel

Inpu

ts

Para

met

er K

eyw

ord

Nam

e Al

low

ed V

alue

s Re

quire

d De

faul

t Val

ue

Desc

riptio

n

Mod

elTy

pe

AE9

, AP9

, PLA

SMA

Leg

acy

mod

els*

: AE

8, A

P8,

C

RRES

ELE,

CRR

ESPR

O, C

AMM

ICE

Req

uire

d n

one

Typ

e of

mod

el to

be

run

(req

uire

s cor

resp

ondi

ng d

atab

ase

file

spec

ified

in M

odel

DB p

aram

eter

)

*See

App

endi

ces A

and

B fo

r Leg

acy

mod

el p

aram

eter

s

Mod

elDB

A

E9V1

0_ru

ntim

e_ta

bles

.mat

A

P9V1

0_ru

ntim

e_ta

bles

.mat

S

PMEV

10_r

untim

e_ta

bles

.mat

S

PMHV

10_r

untim

e_ta

bles

.mat

S

PMHE

V10_

runt

ime_

tabl

es.m

at

SPM

OV1

0_ru

ntim

e_ta

bles

.mat

Req

uire

d n

one

Dat

abas

e fil

e us

ed to

driv

e th

e m

odel

, cor

resp

ondi

ng to

the

sele

cted

Mod

elTy

pe).

Mus

t inc

lude

pat

h to

file

(abs

olut

e, o

r re

lativ

e to

Cm

dLin

eAe9

Ap9

loca

tion)

.

For

PLA

SMA:

spec

ify th

e ap

prop

riate

‘SPM

*’ sp

ecie

s file

:

‘E’ (

elec

tron

s), ‘

H’, ‘

HE’ (

He),

‘O’;

Orb

itFile

v

alid

pat

h an

d fil

e na

me

of e

phem

eris

file

Requ

ired

non

e T

he p

ath

and

file

nam

e of

a v

alid

file

con

tain

ing

sets

of t

ime

and

orbi

t pos

ition

coo

rdin

ates

(in

CSV

form

at a

nd in

the

coor

dina

te sy

stem

spec

ified

by

the

Coor

dSys

par

amet

er).

Alte

rnat

ivel

y, w

hen

usin

g or

bit p

ropa

gatio

n in

puts

, thi

s pa

ram

eter

spec

ifies

the

path

and

file

nam

e of

the

ephe

mer

is in

form

atio

n to

be

writ

ten.

DirF

ile

val

id p

ath

and

file

nam

e of

dire

ctio

n fil

e O

ptio

nal

Om

ni-d

irect

iona

l flu

x T

he p

ath

and

file

nam

e of

a v

alid

file

con

tain

ing

(‘Coo

rdSy

s’)

dire

ctio

n ve

ctor

s ass

ocia

ted

with

the

posit

ions

in th

e sp

ecifi

ed

Orb

itFile

(‘C

oord

Sys’

mus

t be

one

of th

e Ca

rtes

ian

coor

dina

te

syst

ems f

or p

rope

r app

licat

ion)

.

Coo

rdSy

s G

EO, G

EI, G

DZ,

GSM

, GSE

, SM

, M

AG, S

PH, R

LL

Req

uire

d n

one

Coo

rdin

ate

syst

em o

f pos

ition

val

ues i

n th

e sp

ecifi

ed (i

nput

) O

rbitF

ile (a

nd o

ptio

nal D

irFile

) file

s

See

the

‘Sup

port

ed C

oord

inat

e Sy

stem

s’ ta

ble

on p

age

10.


6

Para

met

er K

eyw

ord

Nam

e Al

low

ed V

alue

s Re

quire

d De

faul

t Val

ue

Desc

riptio

n

Flu

xTyp

e 1

PtDi

ff, 2

PtDi

ff*, I

nteg

ral

Req

uire

d n

one

Typ

e of

flux

to b

e co

mpu

ted.

*Tw

o-po

int d

iffer

entia

l req

uire

sbo

th ‘E

nerg

ies’

and

‘Ene

rgie

s2’ p

aram

eter

val

ues

Ene

rgie

s A

E9: 0

.04

– 10

.0 (M

eV)

AP9

: 0.1

– 4

00.0

(MeV

)

Pla

sma/

elec

tron

s: 0

.001

– 0

.040

(MeV

)

Pla

sma/

ions

: 0.0

0115

– 0

.164

3 (M

eV)

Req

uire

d n

one

Com

ma-

sepa

rate

d lis

t of e

nerg

y le

vels,

in M

eV, a

t whi

ch fl

ux

valu

es a

re to

be

com

pute

d, a

t eac

h tim

e st

ep.

Ene

rgy

valu

es a

re re

stric

ted

to th

eir m

odel

-spe

cific

rang

es.

Ene

rgie

s2

(sam

e as

‘Ene

rgie

s’)

Opt

iona

l n

one

Use

d on

ly w

hen

‘Flu

xTyp

e’ =

‘2Pt

Diff’

. A

com

ma-

sepa

rate

d lis

t of e

nerg

y le

vels

that

def

ine

the

end

of th

e en

ergy

rang

es,

betw

een

whi

ch fl

uxes

are

com

pute

d. T

he ‘E

nerg

ies’

pa

ram

eter

def

ines

the

star

t of e

ach

rang

e. T

hese

two

para

met

er li

sts m

ust c

onta

in th

e sa

me

num

ber o

f ene

rgy

leve

ls.

Out

File

v

alid

pat

h an

d fil

e na

me

Req

uire

d n

one

A p

ath

and

file

nam

e "p

refix

" th

at w

ill b

e us

ed w

hen

gene

ratin

g th

e ou

tput

file

(s);

the

nam

ing

of th

ese

files

is

base

d on

this

pref

ix a

nd th

e va

rious

mod

el o

utpu

t and

ag

greg

atio

n pa

ram

eter

s also

spec

ified

in th

e in

put f

ile.

Any

pre

viou

sly

gene

rate

d ou

tput

file

s with

this

sam

e “p

refix

” w

ill b

e ov

erw

ritte

n.

Mag

field

DB

<pat

h>/ig

rfDB

.h5

Req

uire

d n

one

Mag

netic

fiel

d m

odel

's da

taba

se fi

le, i

nclu

ding

pat

h

KPh

iNN

etDB

<p

ath>

/fas

tPhi

_net

.mat

R

equi

red

non

e K

/Phi

coo

rdin

ate

neur

al n

etw

ork

data

base

file

, inc

ludi

ng p

ath


7

Para

met

er K

eyw

ord

Nam

e Al

low

ed V

alue

s Re

quire

d De

faul

t Val

ue

Desc

riptio

n

KHm

inN

Net

DB

<pat

h>/f

ast_

hmin

_net

.mat

R

equi

red

non

e K

/Hm

in c

oord

inat

e ne

ural

net

wor

k da

taba

se fi

le, i

nclu

ding

pa

th

Flu

xOut

m

ean

per

cent

ile,#

# p

ertu

rbed

,###

m

onte

carlo

,###

*

Req

uire

d n

one

Flu

x da

ta to

be

outp

ut.

This

para

met

er m

ay a

ppea

r mul

tiple

tim

es. T

he ‘m

ean’

is a

sim

ple

mea

n va

lue.

The

‘per

cent

ile’

num

ber m

ay b

e in

the

rang

e 1-

99. T

he ‘p

ertu

rbed

’ mea

n an

d/or

‘mon

teca

rlo’ s

cena

rio id

entif

icat

ion

num

bers

may

be

in th

e ra

nge

1-99

9. S

ee th

e fu

ll ex

plan

atio

n of

thes

e di

ffere

nt

type

s of m

odes

in th

e se

ctio

n fo

llow

ing

this

tabl

e.

*mon

teca

rlo is

not

app

licab

le fo

r ‘Pl

asm

a’ m

odel

Flu

eOut

m

ean

per

cent

ile

per

turb

ed

mon

teca

rlo*

Opt

iona

l n

one

Flu

ence

dat

a to

be

outp

ut. T

his p

aram

eter

may

also

app

ear

mul

tiple

tim

es.

No

perc

entil

e or

scen

ario

iden

tific

atio

n nu

mbe

rs a

re sp

ecifi

ed h

ere;

the

corr

espo

ndin

g ‘F

luxO

ut’

num

bers

will

be

used

.

*mon

teca

rlo is

not

app

licab

le fo

r ‘Pl

asm

a’ m

odel

Dos

eOut

* m

ean

per

cent

ile

per

turb

ed

mon

teca

rlo

Opt

iona

l n

one

Dos

e ra

te d

ata

to b

e ou

tput

. May

app

ear m

ultip

le ti

mes

. N

o pe

rcen

tile

or sc

enar

io id

entif

icat

ion

num

bers

shou

ld b

e us

ed

here

, as t

he o

nes f

rom

the

corr

espo

ndin

g Fl

uxO

ut v

alue

s will

be

use

d.

*Req

uire

s add

ition

al D

ose

Calc

ulat

ion

inpu

t par

amet

ers,

in a

follo

win

g se

ctio

n. N

ot a

pplic

able

for P

lasm

a m

odel

.


8

Para

met

er K

eyw

ord

Nam

e Al

low

ed V

alue

s Re

quire

d De

faul

t Val

ue

Desc

riptio

n

CDo

seO

ut*

mea

n p

erce

ntile

p

ertu

rbed

m

onte

carlo

Opt

iona

l n

one

Cum

ulat

ive

dose

dat

a to

be

outp

ut. M

ay a

ppea

r mul

tiple

tim

es.

No

perc

entil

e or

scen

ario

iden

tific

atio

n nu

mbe

rs

shou

ld b

e us

ed h

ere,

as t

he o

nes f

rom

the

corr

espo

ndin

g Fl

uxO

ut v

alue

s will

be

used

.

*Req

uire

s add

ition

al D

ose

Calc

ulat

ion

inpu

t par

amet

ers,

in a

follo

win

g se

ctio

n. N

ot a

pplic

able

for P

lasm

a m

odel

.

Epo

ch

Date

/tim

e (in

Mod

ified

Julia

n da

te*

form

) O

ptio

nal

Firs

t eph

emer

is po

int t

ime

Spe

cify

an

alte

rnat

e tim

e as

the

epoc

h va

lue

for a

mod

el ru

n.

This

perm

its m

odel

runs

with

long

eph

emer

is pe

riods

to b

e br

oken

up

into

mul

tiple

runs

(ove

r tim

e) w

hen

perf

orm

ing

“Mon

te C

arlo

” an

d/or

“Pe

rtur

bed

Mea

n” sc

enar

io

calc

ulat

ions

. Se

e th

e flu

x da

ta m

ode

expl

anat

ion

belo

w.

*See

App

endi

x C

for i

nfor

mat

ion

on M

odifi

ed Ju

lian

Date

s.

Supp

orte

d C

oord

inat

e Sy

stem

s

Coor

dSys

Fu

ll Co

ordi

nate

Sys

tem

Nam

e Co

ordi

nate

Val

ues(

units

) G

EI

Geo

cent

ric E

arth

Iner

tial

or

Ear

th-C

ente

red

Iner

tial (

ECI)

X(R

e), Y

(Re)

, Z(R

e)

GEO

G

eoce

ntric

Car

tesia

n

X(Re

), Y(

Re),

Z(Re

) G

DZ

Geo

detic

alt(

km),

lat(

deg)

, lon

(deg

) G

SM

Geo

cent

ric S

olar

Mag

neto

sphe

ric

X(

Re),

Y(Re

), Z(

Re)

GSE

G

eoce

ntric

Sol

ar E

clip

tic

X(

Re),

Y(Re

), Z(

Re)

SM

S

olar

Mag

netic

X(Re

), Y(

Re),

Z(Re

) M

AG

Mag

netic

X(Re

), Y(

Re),

Z(Re

) S

PH

Sph

eric

al

ra

dius

(Re)

, col

atitu

de(d

eg),

lon(

deg)

R

LL

Rad

ius,

Lat

itude

, Lon

gitu

de

ra

dius

(Re)

, lat

(deg

), lo

n(de

g)

1 Re

= 6

371.

2 km

Se

e [B

havn

ani a

nd V

anco

ur, 1

991]

for f

ull d

escr

iptio

ns o

f the

se c

oord

inat

e sy

stem

s.


9

Det

ails

abo

ut th

e Fl

ux D

ata

Mod

es

The

‘Flu

xOut

’, an

d as

soci

ated

par

amet

ers,

is u

sed

spec

ify th

e va

rious

type

s of f

lux

data

to b

e re

turn

ed b

y th

e m

odel

. Th

e ‘m

ean’

and

‘p

erce

ntile

’ mod

es c

aptu

re th

e st

atis

tical

beh

avio

r of t

he d

ata

upon

whi

ch th

e m

odel

was

bui

lt. T

he ‘p

ertu

rbed

’ mod

e ad

ds th

e un

certa

intie

s in

the

mea

n flu

x m

aps t

hat a

re d

ue to

mea

sure

men

t and

gap

-fill

ing

erro

rs.

The

‘mon

teca

rlo’ m

ode

cont

ains

all

thes

e un

certa

intie

s of t

he ‘p

ertu

rbed

’ mod

e, th

en a

dds a

n es

timat

e of

the

dyna

mic

var

iatio

ns d

ue to

spac

e w

eath

er p

roce

sses

. Th

e m

ultip

le

“sce

nario

s” o

f the

latte

r tw

o m

odes

are

spec

ified

with

scen

ario

iden

tific

atio

n nu

mbe

rs (u

sed

to p

rodu

ce a

rand

om n

umbe

r see

d), e

ach

prod

ucin

g a

diff

eren

t flu

x pr

ofile

for e

very

orb

it, b

ound

ed b

y th

e va

rianc

es d

ue to

mea

sure

men

t err

or a

nd sp

ace

wea

ther

. Th

ese

varia

tions

repr

esen

t the

rang

e as

soci

ated

with

spac

e w

eath

er o

n m

ultip

le ti

mes

cale

s and

span

the

varia

bilit

y ob

serv

ed th

roug

hout

a

sola

r cyc

le; h

owev

er, t

he so

lar c

ycle

pha

se is

not

repr

oduc

ed.

This

scen

ario

“se

ed”

num

ber e

nabl

es th

ese

resu

lts o

f the

mod

el

calc

ulat

ions

to b

e fu

lly re

prod

ucib

le, p

rovi

ded

that

the

sam

e ep

hem

eris

info

rmat

ion

and

‘epo

ch’ t

ime

refe

renc

e ar

e us

ed.

Unl

ess

othe

rwis

e sp

ecifi

ed, t

he ‘e

poch

’ tim

e de

faul

ts to

the

first

tim

e of

the

ephe

mer

is in

form

atio

n.

The

‘Epo

ch’ p

aram

eter

is v

ital w

hen

brea

king

up

a lo

ng ti

me

serie

s ‘pe

rtur

bed’

or ‘

mon

teca

rlo’-

mod

e si

mul

atio

n in

to se

para

te m

odel

ru

ns. E

ach

time

segm

ent c

an b

e ru

n se

para

tely

and

then

man

ually

com

bine

d af

terw

ards

if th

e sa

me

‘Epo

ch’ v

alue

is sp

ecifi

ed fo

r all

time

segm

ent m

odel

runs

.

By

aggr

egat

ing

the

resu

lts o

f a la

rge

num

ber o

f mis

sion

scen

ario

s (ea

ch w

ith a

diff

eren

t see

d nu

mbe

r), t

he p

erce

ntile

flux

leve

ls o

f any

qu

antit

y de

rivab

le fr

om th

e flu

x sp

ectru

m, e

.g. f

luen

ce (t

ime

inte

grat

ed fl

ux) o

r tot

al d

ose,

may

be

calc

ulat

ed in

term

s of p

roba

bilit

ies

of o

ccur

renc

e du

ring

the

cour

se o

f the

mis

sion

or o

n ot

her t

imes

cale

s.

Muc

h m

ore

info

rmat

ion

abou

t the

mod

el m

ay b

e fo

und

in [G

inet

, et a

l, 20

13].


10

Aggr

egat

ion

Inpu

ts

Mod

el a

ggre

gatio

n va

lues

are

ava

ilabl

e w

hen

the

‘Flu

xOut

/per

turb

ed,#

##’ a

nd/o

r ‘Fl

uxO

ut/m

onte

carlo

,###

’ par

amet

ers a

re sp

ecifi

ed,

but a

re st

atis

tical

ly m

eani

ngfu

l onl

y w

hen

at le

ast f

ive

scen

ario

s are

use

d. E

ach

of th

ese

para

met

ers m

ay a

ppea

r mul

tiple

tim

es in

or

der t

o sp

ecify

the

desi

red

aggr

egat

e ou

tput

file

s. ‘M

onte

Carlo

’ agg

rega

tions

are

not

app

licab

le to

‘Pla

sma’

mod

el o

utpu

ts.

Para

met

er K

eyw

ord

Nam

e Al

low

ed V

alue

s Re

quire

d De

faul

t Val

ue

Desc

riptio

n

PM

AggX

m

ean

med

ian

per

cent

ile,#

#

Opt

iona

l n

one

Agg

rega

te fl

ux re

sults

acr

oss ‘

pert

urbe

d m

ean’

scen

ario

s def

ined

in

Flu

xOut

sett

ings

. Com

pute

s the

mea

n, m

edia

n or

per

cent

ile #

# (1

..99)

acr

oss t

he sc

enar

ios a

t eac

h tim

este

p.

PM

AggF

m

ean

med

ian

per

cent

ile,#

#

Opt

iona

l n

one

Agg

rega

te fl

uenc

e re

sults

acr

oss ‘

pert

urbe

d m

ean’

scen

ario

s de

fined

in F

lueO

ut se

ttin

gs. C

ompu

tes t

he m

ean,

med

ian

or

perc

entil

e ##

(1..9

9) a

cros

s the

scen

ario

s at e

ach

times

tep.

PM

AggD

m

ean

med

ian

per

cent

ile,#

#

Opt

iona

l n

one

Agg

rega

te d

ose

rate

resu

lts a

cros

s ‘pe

rtur

bed

mea

n’ sc

enar

ios

defin

ed in

Dos

eOut

sett

ings

. Com

pute

s the

mea

n, m

edia

n or

pe

rcen

tile

## (1

..99)

acr

oss t

he sc

enar

ios a

t eac

h tim

este

p.

PM

AggC

D m

ean

med

ian

per

cent

ile,#

#

Opt

iona

l n

one

Agg

rega

te c

umul

ativ

e do

se re

sults

acr

oss ‘

pert

urbe

d m

ean’

sc

enar

ios d

efin

ed in

CDo

seO

ut se

ttin

gs. C

ompu

tes t

he m

ean,

m

edia

n or

per

cent

ile #

# (1

..99)

acr

oss t

he sc

enar

ios a

t eac

h tim

este

p.

MCA

ggX*

m

ean

med

ian

per

cent

ile,#

#

Opt

iona

l n

one

Agg

rega

te fl

ux re

sults

acr

oss ‘

mon

te c

arlo

’ sce

nario

s def

ined

in

Flux

Out

sett

ings

. Com

pute

s the

mea

n, m

edia

n or

per

cent

ile #

# (1

..99)

acr

oss t

he sc

enar

ios a

t eac

h tim

este

p.

*mon

te c

arlo

agg

rega

tions

are

not

app

licab

le fo

r ‘Pl

asm

a’ m

odel


11

Para

met

er K

eyw

ord

Nam

e Al

low

ed V

alue

s Re

quire

d De

faul

t Val

ue

Desc

riptio

n

MCA

ggF

mea

n m

edia

n p

erce

ntile

,##

Opt

iona

l n

one

Agg

rega

te fl

uenc

e re

sults

acr

oss ‘

mon

te c

arlo

’ sce

nario

s def

ined

in

Flu

eOut

sett

ings

. Com

pute

s the

mea

n, m

edia

n or

per

cent

ile #

# (1

..99)

acr

oss t

he sc

enar

ios a

t eac

h tim

este

p.

MCA

ggD

mea

n m

edia

n p

erce

ntile

,##

Opt

iona

l n

one

Agg

rega

te d

ose

rate

resu

lts a

cros

s ‘m

onte

car

lo’ s

cena

rios

defin

ed in

Dos

eOut

sett

ings

. Com

pute

s the

mea

n, m

edia

n or

pe

rcen

tile

## (1

..99)

acr

oss t

he sc

enar

ios a

t eac

h tim

este

p.

MCA

ggCD

m

ean

med

ian

per

cent

ile,#

#

Opt

iona

l n

one

Agg

rega

te c

umul

ativ

e do

se re

sults

acr

oss ‘

mon

te c

arlo

’ sce

nario

s de

fined

in C

Dose

Out

sett

ings

. Com

pute

s the

mea

n, m

edia

n or

pe

rcen

tile

## (1

..99)

acr

oss t

he sc

enar

ios a

t eac

h tim

este

p.

Dos

e Ca

lcul

atio

n In

puts

Th

ese

para

met

ers,

used

as i

nput

s to

the

“Shi

eldD

ose2

” m

odel

, are

requ

ired

whe

n ‘D

oseO

ut’ a

nd/o

r ‘CD

oseO

ut’ p

aram

eter

s are

sp

ecifi

ed.

Dos

e ca

lcul

atio

ns a

re n

ot a

pplic

able

for t

he ‘P

lasm

a’ m

odel

. M

ore

deta

ils a

bout

thes

e Sh

ield

Dos

e2 m

odel

par

amet

ers m

ay

be fo

und

in [S

eltz

er, 1

994]

. N

ote

that

the

Shie

ldD

ose2

“B

rem

sstra

hlun

g” d

ata

tabl

es b

eing

use

d by

the

Cm

dLin

eAe9

Ap9

app

licat

ion

have

bee

n up

date

d to

cor

rect

an

erro

r pre

sent

in th

e or

igin

al S

HIE

LDO

SE2

publ

icat

ion.

In

the

‘elb

rbas

2.da

t’ fil

e, w

ith th

e ex

cept

ion

of th

e Al

det

ecto

r tar

gets

, the

fini

te sl

ab a

nd se

mi-i

nfin

ite sl

ab d

ata

tabl

es h

ad b

een

switc

hed

[Hey

nder

ickx

, 201

3].

Para

met

er K

eyw

ord

Nam

e Al

low

ed V

alue

s Re

quire

d fo

r Dos

e ca

lc.

Defa

ult V

alue

De

scrip

tion

Dos

eDep

ths

0.1

11 –

111

.1 (m

m)

4.3

74 –

437

4 (m

ils)

0.0

3 –

30.0

(g/c

m2 )

Req

uire

d n

one

Com

ma-

sepa

rate

d lis

t of A

lum

inum

shie

ldin

g th

ickn

ess d

epth

s,

in u

nits

spec

ified

by

the

Dose

Dept

hU p

aram

eter

.

Dep

th v

alue

s are

reco

mm

ende

d to

be

limite

d to

thes

e ra

nges

sp

ecifi

ed; v

alid

ity o

f res

ults

for d

epth

s out

side

thes

e ra

nges

is

unce

rtai

n.


12

Para

met

er K

eyw

ord

Nam

e Al

low

ed V

alue

s Re

quire

d fo

r Dos

e ca

lc.

Defa

ult V

alue

De

scrip

tion

Dos

eDep

thU

m

illim

eter

s m

ils

gpe

rcm

2

Opt

iona

l m

illim

eter

s U

nits

of A

lum

inum

shie

ldin

g th

ickn

ess d

epth

Dos

eDet

Geo

m

sphe

rical

fi

nite

slab

se

miin

finite

slab

Opt

iona

l sp

heric

al

Geo

met

ry o

f Alu

min

um sh

ield

ing

in fr

ont o

f (or

aro

und)

det

ecto

r -

½ d

ose

at c

ente

r of s

olid

alu

min

um sp

here

-

dose

at t

rans

mis

sion

surf

ace

of fi

nite

alu

min

um sl

ab

- do

se in

sem

i-inf

inite

alu

min

um m

ediu

m

Dos

eDet

Type

A

lum

inum

, gra

phite

, sili

con,

air,

b

one,

cal

cium

, gal

lium

, lith

ium

, g

lass

, tiss

ue, w

ater

Opt

iona

l a

lum

inum

D

etec

tor m

ater

ial t

ype

Dos

eAtt

nMd

non

e

nuc

lear

inte

ract

ions

nuc

lear

andn

eutr

ons

Opt

iona

l "n

one"

N

ucle

ar a

tten

uatio

n m

ode

for d

ose

calc

ulat

ions

-n

o nu

clea

r att

enua

tion

-nuc

lear

att

enua

tion,

but

neg

lect

ing

neut

ron

ener

gy tr

ansp

ort

-nuc

lear

att

enua

tion

incl

udin

g ne

utro

n en

ergy

tran

spor

t

Dos

eInt

rvl

tim

e in

terv

al (d

ays)

O

ptio

nal

0.0

*

(=ea

ch ti

mes

tep)

Inte

grat

ion

inte

rval

(in

days

) ove

r whi

ch to

cal

cula

te d

ose

rate

. If

only

the

tota

l dos

e in

form

atio

n fo

r the

ent

ire ti

me

perio

d is

desir

ed, s

peci

fy a

ver

y la

rge

num

ber (

ie ‘9

999’

) *N

ote

that

dos

e co

mpu

tatio

ns a

re sl

ow; u

se o

f a lo

nger

inte

rval

can

signi

fican

tly im

prov

e ov

eral

l mod

el p

erfo

rman

ce. I

t is a

lso

reco

mm

ende

d th

at th

e in

terv

al b

e se

t to

an e

xact

mul

tiple

of t

he

orbi

t cad

ence

. Ca

lcul

atio

ns a

ssum

e th

e ep

hem

eris

time

step

s are

co

nsta

nt.


13

Orb

iter

Pro

paga

tor

Inpu

ts

Whe

n th

e ap

prop

riate

set o

f the

se o

rbit

para

met

ers i

s spe

cifie

d, th

e ge

nera

ted

ephe

mer

is in

form

atio

n is

writ

ten

to th

e fil

e sp

ecifi

ed b

y th

e ‘O

rbitF

ile’ p

aram

eter

(in

the

Basi

c M

odel

Inpu

ts g

roup

), re

plac

ing

the

ephe

mer

is fi

le if

it a

lrea

dy e

xist

s. H

owev

er, b

e aw

are

that

the

ephe

mer

is ti

me

and

posi

tion

and

info

rmat

ion

(sup

plie

d or

gen

erat

ed) i

s alw

ays i

nclu

ded

in a

ll m

odel

out

put f

iles.

Para

met

er K

eyw

ord

Nam

e Al

low

ed V

alue

s U

sage

Co

ordi

natio

n De

faul

t Val

ue

Desc

riptio

n

Orb

TLE

Valid

pat

h an

d fi

le n

ame

of T

wo

Line

Ele

men

ts (T

LE) f

ile

Con

ditio

nally

R

equi

red*

n

one

Pat

h an

d fil

enam

e of

the

TLE

file

used

to g

ener

ate

an o

rbit

file,

us

ing

‘Sat

Eph’

or ‘

SGP4

’ pro

paga

tors

.

*Orb

it pr

opag

atio

n re

quire

s tha

t eith

er th

is fie

ld o

r Orb

Elm

Tim

mus

t be

set.

Orb

Star

t D

ate/

time*

A

lway

s R

equi

red

non

e S

tart

dat

e an

d tim

e, in

mod

ified

Julia

n da

te (M

JD*)

form

, of

orbi

t pos

ition

s to

gene

rate

. *S

ee A

ppen

dix

C fo

r inf

orm

atio

n on

Mod

ified

Julia

n Da

tes.

Orb

End

Dat

e/tim

e A

lway

s R

equi

red

non

e E

nd d

ate

and

time,

in M

JD fo

rmat

, of o

rbit

posit

ions

to

gene

rate

Orb

Step

>

0 A

lway

s R

equi

red

non

e T

ime

inte

rval

(in

seco

nds)

bet

wee

n or

bit p

ositi

ons.

Rec

omm

ende

d va

lues

, acc

ordi

ng to

gen

eral

orb

it ty

pe:

L

EO: 1

0 se

c; M

EO: 3

00 se

c; H

EO: 6

0 se

c; G

EO: 3

600

sec.

Orb

Prop

Type

S

GP4,

Sat

Eph,

Kep

ler

Alw

ays

Req

uire

d n

one

Typ

e of

orb

it pr

opag

ator

to u

se fo

r gen

erat

ing

the

orbi

t ep

hem

eris

info

rmat

ion.

‘SGP

4’ is

a c

omm

only

-use

d or

bit

prop

agat

or. ‘

SatE

ph’ i

s ano

ther

nam

e fo

r the

Lok

angl

e pr

opag

ator

, dev

elop

ed a

nd u

sed

by A

FRL

for d

ecad

es. ‘

Kepl

er’ i

s a

very

bas

ic o

rbit

prop

agat

or w

ith o

ptio

nal J

2 pe

rtur

batio

n ef

fect

s.


14

Para

met

er K

eyw

ord

Nam

e Al

low

ed V

alue

s U

sage

Co

ordi

natio

n De

faul

t Val

ue

Desc

riptio

n

Orb

Elm

Tim

D

ate/

time

Con

ditio

nally

R

equi

red*

n

one

Tim

e, in

Mod

ified

Julia

n da

y+ form

, ass

ocia

ted

with

the

spec

ified

orb

ital e

lem

ent v

alue

s

*Orb

it pr

opag

atio

n re

quire

s tha

t eith

er th

is fie

ld o

r ‘O

rbTL

E’m

ust b

e sp

ecifi

ed.

+ See

Appe

ndix

C fo

r inf

orm

atio

n on

Mod

ified

Julia

n Da

tes.

Orb

Mod

e S

tand

ard,

Impr

oved

R

equi

red

for

‘SGP

4’

Sta

ndar

d R

un m

ode

for ‘

SGP4

’ pro

paga

tor

Orb

Datu

m

72O

ld,

72,

84

Req

uire

d fo

r ‘S

GP4’

n

one

WGS

Dat

um c

onst

ants

to u

se.

Wor

ld G

eode

tic S

yste

m

sphe

roid

al d

efin

ition

of t

he E

arth

.

Orb

Elem

Type

‘s

olar

’, ‘m

ean’

, ‘c

lass

ical

’, ‘g

eosy

nc’,

or ‘r

v’

Req

uire

d fo

r ‘K

eple

r’ n

one

Typ

e of

orb

ital e

lem

ent v

alue

inpu

ts to

be

used

with

the

‘Kep

ler’

prop

agat

or (N

o TL

E fil

es).

The

nec

essa

ry p

aram

eter

s for

the

diffe

rent

type

s of e

lem

ents

ar

e an

nota

ted

by th

eir n

ame

in th

e ‘R

equi

red’

col

umn

here

.

Orb

Use

J2

true

, fa

lse

Req

uire

d fo

r ‘K

eple

r’ fa

lse

Use

J2 p

ertu

rbat

ions

in K

eple

r pro

paga

tion

algo

rithm

Orb

Incl

* 0

– 1

80 (d

egre

es)

‘mea

n’ o

r ‘s

olar

’ or

‘c

lass

ical

’

non

e O

rbita

l inc

linat

ion

(deg

rees

)

*Orb

ital e

lem

ent p

aram

eter

s, h

ere

and

belo

w, t

hat a

re m

arke

dw

ith ’m

ean’

may

be

used

with

any

of t

he th

ree

prop

agat

ors.

All

othe

rs m

ay o

nly

be u

sed

with

the

‘Kep

ler’

prop

agat

or.

Orb

ArgP

er

0 –

360

(deg

rees

) ‘m

ean’

n

one

Arg

umen

t of p

erig

ee (d

egre

es)

Orb

Mea

nAn

0 –

360

(deg

rees

) ‘m

ean’

n

one

Mea

n an

omal

y (d

egre

es)


15

Para

met

er K

eyw

ord

Nam

e Al

low

ed V

alue

s U

sage

Co

ordi

natio

n De

faul

t Val

ue

Desc

riptio

n

Orb

1stD

er

-10

– +1

0 ‘m

ean’

n

one

Firs

t der

ivat

ive

of m

ean

mot

ion

(rev

/day

2 )

Orb

Ecce

n 0

.0 –

1.0

‘m

ean’

or

‘cla

ssic

al’

non

e E

ccen

tric

ity (u

nitle

ss)

Orb

RAAs

Nd

0.0

– 3

60.0

(deg

rees

) ‘m

ean’

or

‘cla

ssic

al’

non

e R

ight

asc

ensio

n of

asc

endi

ng n

ode

(deg

rees

), al

so k

now

n as

the

cele

stia

l lon

gitu

de o

f the

asc

endi

ng n

ode.

Orb

Mea

nMo

>0.

0 –

30.

0 ‘m

ean’

n

one

Orb

ital m

ean

mot

ion

(rev

olut

ions

/day

)

Orb

2ndD

er

-1 –

+1

‘mea

n’

non

e S

econ

d de

rivat

ive

of m

ean

mot

ion

(rev

/day

3 )

Orb

BSta

r -1

– +

1 ‘m

ean’

n

one

Bal

listic

coe

ffici

ent

Orb

AltP

er

>0

– ~5

0xRe

‘s

olar

’ n

one

Alti

tude

of p

erig

ee (k

m)

Orb

AltA

po

>0

– ~5

0xRe

‘s

olar

’ n

one

Alti

tude

of a

poge

e (k

m)

Orb

LocT

imeA

po

0 –

24

(hou

rs)

‘sol

ar’

non

e L

ocal

tim

e of

apo

gee

(hou

rs)

Orb

LocT

imeM

axIn

cl

0 –

24

(hou

rs)

‘sol

ar’

non

e L

ocal

tim

e of

max

imum

incl

inat

ion

[ie, m

ax la

titud

e] (h

ours

)

Orb

SmjA

xis

>0

– ~5

0xRe

‘c

lass

ical

’ n

one

Sem

i-maj

or a

xis (

Re)

Orb

Tim

Perig

D

ate/

time

‘cla

ssic

al’

non

e T

ime

of p

erig

ee, i

n M

JD fo

rm

Orb

PosX

yz

|<1

25,0

00km

| ‘r

v’

non

e P

ositi

on (X

,Y,Z

in G

EI [k

m])

at o

rbita

l ele

men

t tim

e

Orb

VelX

yz

|<5

0km

/sec

| ‘r

v’

non

e V

eloc

ity (X

,Y,Z

in G

EI [k

m/s

]) at

orb

ital e

lem

ent t

ime

Orb

GeoL

on

0 –

360

(deg

rees

) ‘g

eosy

nc’

non

e G

eogr

aphi

c lo

ngitu

de (d

eg) a

t orb

ital e

lem

ent t

ime


16

Two-Line Element Files Two-Line Element (TLE) is a standard NORAD data format used to convey sets of orbital element values that describe the orbital motion of Earth-orbiting satellites. Current and archived TLE data for many satellites may be obtained from various online sources, such as http://www.celestrak.com.

The orbit propagator routines, such as ‘SGP4’ and ‘SatEph’, can use TLE files that contain multiple entries of TLE (in chronological order) for a single satellite. The ‘SatEph’ routines perform interpolation between adjacent TLE entries for smooth ephemeris results.

The standard NORAD format for the Two-Line Elements is shown in the table below:

TLE Line 1 TLE Line 2 Column Description Column Description 01 Line Number of Element Data 01 Line Number of Element Data 03-07 Satellite Number 03-07 Satellite Number 08 Classification (U=Unclassified) 09-16 Inclination [Degrees] 10-11 International Designator (Last two digits of

launch year) 18-25 Right Ascension of the Ascending Node

[Degrees] 12-14 International Designator (Launch number of

the year) 27-33 Eccentricity (decimal point assumed)

15-17 International Designator (Piece of the launch)

35-42 Argument of Perigee [Degrees]

19-20 Epoch Year (Last two digits of year) 44-51 Mean Anomaly [Degrees] 21-32 Epoch (Day of the year and fractional

portion of the day) 53-63 Mean Motion [Revs per day]

34-43 First Time Derivative of the Mean Motion 64-68 Revolution number at epoch [Revs] 45-52 Second Time Derivative of Mean Motion

(decimal point assumed) 69 Checksum (Modulo 10)

54-61 BSTAR drag term (decimal point assumed) 63 Ephemeris type 65-68 Element number 69 Checksum (Modulo 10)

Example Two-Line Element set (32765 = C/NOFS satellite):

1 32765U 08017A 11150.09749074 +.00010799 +00000-0 +47888-3 0 0797 2 32765 013.0015 105.8044 0295409 031.4522 330.3172 14.8643027916917

Some potentially helpful online resources for understanding the orbital element definitions:

http://www.braeunig.us/space/orbmech.htm http://www.amsat.org/amsat/keps/kepmodel.html http://marine.rutgers.edu/mrs/education/class/paul/orbits.html http://en.wikipedia.org/wiki/Orbital_elements


17

http://www.braeunig.us/space/orbmech.htm

http://www.amsat.org/amsat/keps/kepmodel.html

http://marine.rutgers.edu/mrs/education/class/paul/orbits.html

http://en.wikipedia.org/wiki/Orbital_elements

Orbit Ephemeris File Description The ephemeris file, required for performing the model calculations, can be generated by one of the available orbit propagators, or can be supplied by the user (but must be in the expected format). The user-supplied (input) or generated (output) ephemeris file name is specified with the required ‘OrbitFile’ parameter.

The comma-separated value (CVS)-formatted ephemeris file may contain any number of header lines (comments), designed with a ‘#’ in the first column. The data values are expected in four columns: date/time (in Modified Julian day+fraction form, see Appendix C), and three coordinates of one of the supported coordinate systems (in the specified order and appropriate units). The coordinate system of the user-supplied ephemeris file is specified by the ‘CoordSys’ parameter.

Any ephemeris files generated by the orbit propagator during the model runs will always use the GEI coordinate system and units. The ephemeris information, from either source, is included the model output files.

Model Output Files The input file specifications define the types of model calculations to be performed, and the corresponding output file or files are generated. The different types of output files are distinguished by the type of data, its calculation mode, and aggregation/division.

The names of the model output files are constructed from the required ‘OutFile’ and ‘FluxOut’ parameter values, other optional model output parameter values, and any model output aggregation parameter specifications. The basic output file name assembly scheme is below. This scheme ensures unique output file names that provide descriptive information about its contents.

Prefix Data Mode

based on <*Out> value

Data Type based on

<*Out> keyword

Scenario/Aggregation based on

<*Agg*> keyword Suffix

<OutFile>

_mean_flux _fluence _dose _totaldose

(-n/a- for mean)

.txt

_pctile _## (percentile, in <FluxOut> value)

_pert _mc

_### (scenario identification #) _agg_mean _agg_median _agg_pctile_##

Each model output file contains several header lines (comments, defined by ‘#’ in first column) that identify the model, its parameters, type of output values, and other pertinent information (but not necessarily the complete set of model parameters). The last header line specifies the data


18

column labels and units. Each (CSV-format) data line contains the date/time (as Modified Julian day+fraction, see Appendix C), the GEI Cartesian coordinates (in Re), followed by one or more data values, as appropriate for the file’s data type/mode/aggregation.

Tandem AE9/AP9 and Plasma Model Calculations The ‘AE9/AP9’ model and ‘Plasma’ model (for the ‘electron’ and ‘H+’ species) may be used in tandem to provide results over a broader energy range. However, because these two models were developed independently, the results where their energy ranges overlap will not always match. When used together, it is recommend that the ‘Plasma’ model energy levels specified be less than 0.04MeV for electrons, and less than 0.1MeV for protons.

The ‘Plasma’ model differential flux values returned may be used as-is. However, to obtain true integral flux results, information for the energy levels that are above the ‘Plasma’ model energy limits needs to be included. Pseudo-integral flux Plasma model runs may be performed at the desired energies, using ‘FluxType’=‘2PtDiff’, with the ‘Energies2’ list values all set to 0.04MeV for electrons or 0.1MeV for protons. Integral flux ‘AE9/AP9’ model runs are required at 0.04MeV (and other energies, if desired) for electrons and 0.1MeV (and others) for protons, using the same ephemeris information as the Plasma runs. When all runs have been executed, use the ‘IntegralPlasma.exe’ command-line application utility to perform a post-processing adjustment of the Plasma results. This rewrites the Plasma integral output files, revising the ‘2PtDiff’ values to be ‘Integral’ values, incorporating the respective ‘AE9/AP9’ integral results at their lowest energies. More information about this utility program may be found in the accompanying ‘IntPlasma_Readme.txt’ file. For user convenience, this entire post-processing adjustment operation is performed automatically within the GUI program for these types of model calculations.

Model Run Performance Tuning When executing the model program on systems with limited amounts of free memory, the overall performance may be improved by specifying an additional parameter in the model run input file. The (optional) tuning parameter ‘PtsPerCall’ (default value = 240) defines the number of orbital positions being processed during each call to the lower-level model routines. The size of this processing ‘chunk’ directly relates to the amount of memory needed beyond the model overhead. Specifying a lower value, such as 120, should improve performance times on limited-memory systems. Lower values will also increase the frequency of progress updates.

No parallel processing capabilities are currently implemented in the model program. Separate model runs may executed simultaneously, provided an adequate amount of memory is available to support this. See the ‘Epoch’ parameter (in Basic Model Inputs) for related information.


19

Graphical User Interface Program The GUI program provides a simple graphical user interface front-end for performing model runs with the CmdLineA9Ap9 program. Based on the selections and specifications made in the user interface, the appropriate parameter input files are generated and executed. Basic 2-D plots of the calculated model results may be produced.

The GUI program writes files to a subdirectory (default name = “Run”) of the program installation location. This directory is created if it does not exist; the user may choose another name and/or location for this directory. For each model run, the necessary input files are written in this directory, and used with the command line program. The generated ephemeris files, model run output files, and plot data files are also written to this same directory, with a user-supplied ‘RunName’ prefix in their filenames.

The ‘Ae9Ap9GuiDBConfig.txt’ configuration file is used to identify the names and locations of the various model data base files; these are referenced in the model run input files generated by the GUI program. Use extreme caution when modifying this database configuration file, as changes made here will alter model results and/or cause model run failures. The previously-discussed model performance tuning parameter, ‘PtsPerCall’, may also be specified in this configuration file.

The GUI controls are divided into three tabbed pages, labeled ‘Satellite’, ‘Model’ and ‘Plot’. The usage and available features on each of these pages are described in the following sections.


20

Satellite Tab This page collects all necessary information for defining the times and orbital positions at which the radiation environment model values are to be calculated, usually along a satellite orbital path for a specific time segment and increment.

The ‘Satellite Name’ is only required when specifying custom orbital elements, and is used as part of the filename of the generated ephemeris file, in the form: ‘ephem_<SatName>.dat’. If not supplied, the default name of ‘sat’ will be used.

For the orbit specification ‘Input type’, select ‘Ephemeris (Time+Position)’ to use an existing ephemeris file (CSV-formatted) containing a list of times and positions, in one of the supported coordinate system, as specified by the drop-down box to the right. Note that the times are expected to be in Modified Julian date plus fractional day form, and the coordinate values that follow are in the listed order, and in the specified units. See the “Supported Coordinate Systems” table, on page 10.


21

Model calculations at a grid of positions for a particular date and time may be also performed using the ‘Ephemeris’ input type. However, these results at a single fixed time are unable to be plotted in the user interface ‘Plot’ page, due to its limited capabilities.

The orbital path may also be defined by specifying a file containing NORAD-standard ‘Two-Line Elements’ (TLE) entries, as previously discussed in the CmdLineAe9Ap9 program description section. The TLE file can contain multiple entries, but for a single vehicle only.

The use of the ‘Mean Element Entry’ or ‘Solar Element Entry’ selection permits their respective sets of orbital element values to be specified manually. Please note the units for each of the parameters, in particular for ‘Mean Motion’. The ‘Element Time’ value associated with these orbital element values is also required.

An ephemeris file is generated (during the model run) from the specified orbital element inputs, using one of three orbit propagators, whose availability depends on the ‘Input Type’ selection. The generated ephemeris positions are always in the GEI (ECI) coordinate system. The available orbit propagators are briefly described below.

• The 'Lokangle' (or ‘SatEph’) propagator, developed and used by researchers at AFRL for several decades. Itaccounts for secular and periodic perturbations, gravitational effects, and atmospheric drag. Thispropagator performs interpolation of the orbital elements between adjacent TLE entries.

• The ‘SGP4’ (Simplified General Perturbations) propagator (sometimes called SPACETRACK) considerssecular and periodic variations due to Earth oblateness, solar and lunar gravitational effects, gravitationalresonance effects, and orbital decay using a drag model. It uses the latest TLE entry for the given time,and may exhibit a slight discontinuity in the ephemeris position at the time of next TLE entry.

• The 'Kepler' propagator is very basic orbit propagator, without applying any perturbations, except for 'J2'effects if selected. The 'J2' perturbation accounts for secular variations in the orbit due to oblateness ofthe Earth. The minimal/no perturbations makes the Kepler propagator ideal for the generation ofextremely long-duration ephemeris information with stable orbit characteristics. By neglecting higher-order physics, this propagator simulates the effects of station keeping maneuvers.

Both the 'SGP4' and 'Kepler' propagators are 'forward-generating' only. That is, they are unable to compute ephemeris at times prior to the specified 'Element Time', or prior to the first time value in the supplied TLE file.

The time limits of the ephemeris file to be generated are specified by the ‘Start Time’ and ‘End Time’ entries, with an associated time increment. Please keep in mind that a small ‘Time Step’ value will result in more time values at which the model values are being calculated. Model runs for long time periods with small time steps could potentially require many hours, days or weeks to complete, depending on your computer system performance. The recommended time step values for adequate model resolution, based on the general orbit type, are: LEO: 10 seconds; MEO: 300 seconds; HEO: 60 seconds; GEO: 3600 seconds. The optimal time step size will depend on the exact characteristics of the satellite orbit being used.


22

For TLE input files, the 'Autofill' button is available – when pressed, the TLE file is scanned, and the ‘Start Time’ is set to match to the first element entry time, and the ‘End Time’ is set to be the last element entry time plus one day. The filename of the generated ephemeris file will be in the form: ‘ephem_<TLE_input_file>.dat’.

When all selections and specifications have been made, press the ‘Set’ button. The various inputs are checked, ensuring valid element values and time entries. If applicable, the input file is also scanned, confirming the expected format and that its values are within their respective acceptable ranges. An informative dialog box will be displayed if any problems are detected.


23

Model Tab This page collects all user-specified parameters required for calculating the various model values at the defined ephemeris positions. Each set of model run input and output files will be written in the specified ‘Run' directory, with their file names containing the prefix specified in the ‘RunName’ entry.

Five models are available from the ‘Model’ drop-down box – ‘AE9/AP9’, ‘Plasma’, and three “legacy” models: ‘AE8/AP8’, ‘CRRES ELE/PRO’ and ‘CAMMICE/MICS’. Depending on which model is selected, the appropriate parameter selections are shown in the GUI window.

For the ‘AE9/AP9’, ‘AE8/AP8’ and ‘CRRES ELE/PRO’ models, dose calculations may also be performed using the calculated particle flux and fluence results. This feature is activated by checking the ‘Compute Dose’ checkbox, which enables the selection of the “ShieldDose2” model parameters, and also automatically selects all energy levels of both electrons and protons. The ‘Dose Interval’ value specifies the frequency (in ephemeris data time) at which the dose


24

calculations are performed. A value of “0.0” means the calculations are performed at every timestep, which may significantly lengthen the overall model execution time. A value of “0.25” (days) means the calculations are performed on the aggregation of flux values for the preceding 6 hours-worth of ephemeris positions. Additional information about the other “ShieldDose2” model parameters may be found in the previous Command-Line Program/Dose Calculation Inputs section (page 14) of this document, and [Seltzer, 1994].

The values in the ‘Shield Depths’ list may be displayed in units of ‘g/cm2’, ‘mm’ or ‘mils’. Using the drop-down box to select a different unit will automatically convert the existing entry values to the new units.

The values comprising the 'Shield Depths' list may also be customized. Double-click on an entry to edit its value (or alternatively, use Shift+Ctrl+click). When the editing of an entry is complete, its position in the list will automatically be adjusted to maintain increasing numerical order. Entering “0” or blank will delete the entry. New entries may be added to the list byselecting the special ‘[-Add-]’ entry at the bottom of the list. The list’s pop-up “tooltip” information shows the expected range of valid values, as well as these editing instructions. These customized list values may be saved to a file by pressing ‘Shift’ when clicking on a list entry. A saved list of values may be reloaded by pressing ‘Ctrl’ when clicking on a list entry. Only valid list entries from appropriate list files will be loaded. Appropriate error, warning or informational dialogs will be displayed as needed.

The energy lists for the ‘AE9/AP9’ and ‘Plasma’ models only may be customized in the same manner as that of the ‘Shield Depths’ list. The energy list values used with the legacy models

AE9/AP9-specific notes: The Electron and Proton energy lists show two distinct sets of values within each list. Those energy values with five digits to the right of the decimal point are calculated using the SPM ‘Plasma’ model for ‘electrons’ and/or ‘H+’(protons). Those energy values with only two digits are calculated with the AE9/AP9 model. “Monte Carlo”-type calculations will not be available if any of the ‘Plasma’ energy values are selected. These energies may be removed from the list toggling the provided checkbox.

The calculation of Integral flux values of the ‘plasma’ energies will automatically invoke a calculation of the integral flux values of the AE9/AP9 at their respective lowest energy levels, if not already selected. The results produced for the plasma energy levels will be adjusted to incorporate the results of these lowest energy AE9/AP9 energies. This post-processing adjustment of the plasma results is performed automatically within the operation of the GUI. For manually-performed model runs, the ‘IntegralPlasma’ utility may be used to perform this post-processing adjustment, provided that the specific set of requirements of the associated model runs are met.


25

cannot be changed. The ‘CAMMICE/MICS’ legacy model always calculates results for all of its pre-defined energy bins.

If one of the legacy ‘AE8/AP8’ or ‘CRRES ELE/PRO’ models is selected, additional parameters are available via the ‘Advanced’ button. A warning is displayed: un-physical results may be produced if the default ‘Advanced’ settings are altered. After acknowledging this warning, an extra dialog box is shown, containing two checkboxes. The “Use Native Epoch” option is checked by default, and imposes the use of model-specific year values (rather than the year specified by the satellite ephemeris) for the magnetic field model when performing the flux calculations for these legacy models. The “Translate SAA” option, unchecked by default, can be used to shift the SAA from its ‘native epoch’ year location to that for the current year specified in the satellite ephemeris. See [Heynderickx et al, 1996] for more details.

When all model parameters and settings have been selected, press the ‘Run’ button. The various model parameter inputs are verified to contain proper and/or compatible settings. An informative error dialog is displayed if problems are detected. If the ‘RunName’ specification has been used before, a dialog box will ask if the previously generated files may be overwritten. When the various selections have all been verified, a set of input files are generated, named in the form: ‘<RunDir>/<RunName>.<Model>.CLinput.txt’. These input files are supplied to the Command-Line program for the model execution. Model runs that require multiple portions to be executed (ie, Electrons and Protons), are done in a serial manner (no parallel execution is available at this time). Any required ephemeris file generation will be performed during the first portion, and the resulting file will be used as input for subsequent portions. If an error occurs during one of the model run portions, any remaining portions will not be run, and the model run files associated with ‘RunName’ will be marked as “incomplete”. An error dialog will notify the user if this occurs.

During the execution of the necessary model runs, the ‘Run’ button will show ‘-busy-’, and the run status will be shown in the ‘% Complete’ progress bar. The update rate and frequency of this progress bar will vary, depending on the number of ephemeris positions being used, the model and species selected, and the types of calculations being performed. While “busy”, the various satellite and model GUI selections are able to be viewed, but no changes are permitted. When the model runs have successfully completed, the button is changed back to showing ‘Run’. The generated model output files are named in the form: ‘<RunDir>/<RunName>.<Model>.CLoutput_<type>.txt’. The pre-defined ‘<Model>’ names are shown in the next section. The various permutations for ‘<type>’ are shown in the previous Command-Line Program/Model Output Files section.


26

Plot Tab This page provides a method for producing basic 2-D plots of the model calculation results.

For the specified ‘Directory’ location, all available ‘RunName’ model runs are shown in the drop-down list. These can be from this current or any previous GUI program session. Manually-configured and -executed model runs may also be selected, provided that the expected input and output file-naming form has been used:

Input file = “<RunName>.<Model>.CLinput.txt”, and containing ‘OutFile’ parameter = “<RunName>.<Model>.CLoutput.txt”.

Where <Model> is one of : ‘AE9’, ‘AP9’, ‘PLASMA_E’, ‘PLASMA_O’, ‘PLASMA_H’, or ‘PLASMA_HE’, and/or: - for AE9/Ap9/SPM “tandem” runs : ‘PLASMAelec’ and ‘PLASMAprot’ - for legacy models: ‘AE8’, ‘AP8’, ‘CRRESELE’, ‘CRRESPRO’ or ‘CAMMICE’.


27

Based on the input and output files of the selected 'RunName', the model name and flux type are identified, and the lists for energy levels and shield depths used are appropriately populated. Other pertinent information, such as scenario collections, pitch angles and/or species are also shown. Additional details of the full set of model parameters are always available from the model run input files.

If the selected ‘RunName’ has been marked as “incomplete”, a warning dialog is displayed. Attempts to plot from this may show incorrect results and/or cause program instability.

The selection methods for the desired energy levels or shield depth values will depend on the type of plot desired: versus ‘Time’, ‘Energy’ or ‘Thickness’. The model run parameters may also dictate additional selections are needed, such as species, or scenario numbers and/or percentiles.

For plots of values versus ‘Energy’ or ‘Thickness’, two time-slice specification methods are available. The ‘Time Selection’ slider allows a specific time value within the dataset to be selected. Alternatively, when the ‘Num Times’ spinbox is changed from zero, this specifies the number of evenly-spaced time slices to plot, the first one always at time “t=0” of the time period.

Press the ‘Plot’ button when selections are complete. An informative error dialog is displayed if additional selections are required. The plot is displayed in a new window; the GUI will remain frozen until this plot window is closed. However, if the selected model results are all zeros, no plot will be produced and a notice is displayed.

Based on the selections made, one or more sets of data values are plotted, each using a different color and/or dot/dash pattern. The key below identifies each of these lines. Dose values are plotted based on their ‘Dose Interval’ specification, and so these graphs versus time may appear as steps rather than curves if a non-zero interval is used.

For each plot produced, a CSV-formatted file of the data plotted is written in the same directory. These files are suitable for use by other plotting programs. The file-naming form is: ‘<RunName>_Plot_<###>.txt’, where ‘###’ is simply the number of the plot generated during the current GUI program session. Parameter labels for each data column are included in these plot data files, but do not provide model run parameters. These details are always available in the associated ‘RunName’-prefix model input files.

Example GUI-based Model Runs Several examples of using the GUI to perform model runs and produce basic plots are shown in the series of screenshots below.


28

Exam

ple

1: M

eanS

ampl

e Sa

telli

te T

ab:

-Sel

ect ‘

Ephe

mer

is’

-Ent

er ‘s

hort_

leo.

csv’

for I

nput

File

-P

ress

‘Set

’

Mod

el T

ab:

-Ent

er ‘M

eanS

ampl

e’ fo

r Run

Nam

e -S

elec

t a d

irect

ory

for f

iles

-Che

ck ‘C

ompu

te D

ose’

che

ckbo

x

(

all e

lect

ron

and

prot

on e

nerg

ies w

ill

auto

mat

ical

ly b

e se

lect

ed)

-Dou

ble-

clic

k on

the

first

four

line

s in

the

‘Shi

eld

Dep

ths’

list

, ent

erin

g th

e va

lues

of

0.50

, 1.0

, 10.

0 an

d 50

.0 (u

nits

= ‘m

m’)

-C

heck

the

‘All’

che

ckbo

x be

low

the

Shie

ld D

epth

s lis

t -P

ress

‘Run

’ -T

he p

rogr

ess b

ar w

ill sh

ow th

e ru

n co

mpl

etio

n st

atus

.

Plo

t Tab

:

At t

he c

oncl

usio

n of

the

mod

el ru

n, sw

itch

to th

e ‘P

lot’

tab;

the

Run

Nam

e w

ill

auto

mat

ical

ly b

e se

t to

the

‘Mea

nSam

ple’

na

me.

The

ele

ctro

n an

d pr

oton

ene

rgy

leve

ls a

nd sh

ield

dep

ths,

as se

lect

ed o

n th

e M

odel

tab,

will

pop

ulat

e th

eir r

espe

ctiv

e lis

ts o

n th

e Pl

ot ta

b.


29

Mea

nSam

ple,

Con

tinue

d (P

lot T

ab)

-Sel

ect a

few

ele

ctro

n en

ergy

leve

ls

-Pre

ss ‘P

lot’

A p

op-u

p w

indo

w c

onta

inin

g th

e gr

aph

will

app

ear.

This

use

r int

erfa

ce p

rovi

des t

he a

bilit

y to

ge

nera

te m

any

diff

eren

t typ

es o

f 2D

plo

ts

from

the

avai

labl

e m

odel

run

outp

ut d

ata

files

, suc

h as

:

Fl

ux o

r Flu

ence

vs T

ime

Fl

ux o

r Flu

ence

vs E

nerg

y,

at a

sing

le ti

me,

or m

ultip

le ti

mes

D

ose

Rat

e or

Tot

al D

ose

vs T

ime

D

ose

Rat

e or

Tot

al D

ose

vs T

hick

ness

a

t a si

ngle

tim

e, o

r mul

tiple

tim

es


30

Exam

ple

2: M

onte

Carl

oSam

ple

Sate

llite

Tab

:

-Sel

ect ‘

Two-

Line

Ele

men

ts’ i

nput

type

-S

elec

t ‘Lo

kang

le’ p

ropa

gato

r -E

nter

‘cno

fs_t

le.d

at’ f

or In

put F

ile

-Pre

ss ‘A

utof

ill’

-Set

Tim

eSte

p to

be

300

seco

nds

-Pre

ss ‘S

et’

Mod

el T

ab:

-Ent

er M

CSa

mpl

e fo

r Run

Nam

e -S

elec

t ‘M

onte

Car

lo’ a

s Mod

el M

ode

-Set

‘# R

uns’

to “

25”

-Sel

ect ‘

Inte

gral

’ as F

lux/

Flue

nce

Type

-U

nche

ck ‘I

nclu

de P

lasm

a En

ergy

Lev

els’

ch

eckb

ox

-Sel

ect e

lect

ron

ener

gies

0.0

4 –

0.75

and

3.0

– 6.

0 -S

elec

t pro

ton

ener

gies

0.1

– 0

.80

and

6.

0 –

80.0

-P

ress

‘Run

’, w

ait f

or ru

n co

mpl

etio

n.

Plot

Tab

:

-Sel

ect ‘

Flue

nce’

-S

elec

t Ele

ctro

n en

ergi

es 3

.0 a

nd 6

.0,

an

d Pr

oton

ene

rgy

10.0

-C

heck

‘Mea

n’ a

nd ‘9

5th’ p

erce

ntile

s

-Ent

er ‘1

2’ in

Sce

nario

s -P

ress

‘Plo

t’


31

Exam

ple

3: P

ertu

rbed

Mea

nSam

ple

Sate

llite

Tab

:

-Sel

ect ‘

Mea

n El

emen

t Ent

ry’

-Sel

ect ‘

SGP4

’ pro

paga

tor

-Ent

er e

lem

ent v

alue

s, tim

e lim

its a

nd

time

step

val

ue, a

s sho

wn

belo

w

-Pre

ss ‘S

et’

Mod

el T

ab:

-Ent

er ‘P

MSa

mpl

e’ fo

r Run

Nam

e -S

elec

t ‘Pe

rturb

ed M

ean’

, with

#R

uns=

15

-Unc

heck

‘Inc

lude

Pla

sma

Ener

gy L

evel

s’

-Che

ck ‘C

ompu

te D

ose’

che

ckbo

x

(all

elec

tron

and

prot

on e

nerg

ies w

ill a

utom

atic

ally

be

sele

cted

) -E

nter

Shi

eld

Dep

ths o

f 0.2

5, 0

.50,

1.0

, 1.

50 a

nd 3

.00

-Che

ck 'A

ll' u

nder

Shi

eld

Dep

ths

-Sel

ect a

0.0

8 da

y do

se in

terv

al

-Pre

ss ‘R

un’

Plot

Tab

:

-Man

y ty

pes o

f plo

ts a

re a

vaila

ble

-Sel

ectio

ns c

an b

e de

term

ined

from

eac

h pl

ot’s

labe

ls a

nd le

gend

s


32

References:

Bhavnani, K.H., and R.P. Vancour, “Coordinate systems for space and geophysical applications,” PL-TR-91-2296, Phillips Laboratory, Hanscom AFB, MA, [http://www.dtic.mil/dtic/tr/fulltext/u2/a247550.pdf], 11 Dec. 1991.

Ginet, G.P., T.P. O’Brien, S.L. Huston, W.R. Johnston, T.B. Guild, R. Friedel, C.D. Lindstrom, C.J. Roth, P. Whelan, R.A. Quinn, D. Madden, S. Morley, and Yi-Jiun Su, “AE9, AP9 and SPM: New Models for Specifying the Trapped Energetic Particle and Space Plasma Environment,” Space Science Reviews, [http://dx.doi.org/10.1007/s11214-013-9964-y], March 2013.

Seltzer, Stephen M., “Updated Calculations for Routine Space-Shielding Radiation Dose Estimates: SHIELDOSE-2,” National Institute of Standards and Technology Publication NISTIR 5477, 1994.

Heynderickx, D., J. Lemaire, E.J. Daly, and H.D.R. Evans, “Calculating Low-Altitude Trapped Particle Fluxes with the NASA Models AP-8 and AE-8,” Radiation Measurements, Vol. 26, pp. 947-952, 1996.

Heynderickx, D., private communication, May 2013.


33

http://www.dtic.mil/dtic/tr/fulltext/u2/a247550.pdf

http://dx.doi.org/10.1007/s11214-013-9964-y

Appe

ndix

A: L

egac

y M

odel

s AE

8/AP

8 an

d CR

RESE

LE/P

RO-s

peci

fic p

aram

eter

s Th

ese

lega

cy m

odel

par

amet

ers a

re to

be

used

alo

ng w

ith th

e st

anda

rd o

rbita

l spe

cific

atio

n pa

ram

eter

s, an

d op

tiona

lly w

ith th

e D

ose

calc

ulat

ion

para

met

ers.

Para

met

er K

eyw

ord

Nam

e Al

low

ed V

alue

s Re

quire

d De

faul

t Val

ue

Desc

riptio

n

Mod

elTy

pe

AE8

, AP8

,

CRR

ESEL

E, C

RRES

PRO

Requ

ired

non

e T

ype

of m

odel

to b

e ru

n

Mod

elDB

<

path

>/ra

diat

ionB

eltD

B.h5

Re

quire

d n

one

Dat

abas

e fil

e us

ed to

driv

e th

e m

odel

. M

ust i

nclu

de p

ath

to fi

le

(abs

olut

e, o

r rel

ativ

e to

Cm

dLin

eAe9

Ap9

loca

tion)

.

Out

Data

F

lux,

Flu

ence

, Dos

eRat

e, C

umDo

se R

equi

red

non

e M

odel

val

ue fo

r out

put.

Thi

s par

amet

er m

ay a

ppea

r mul

tiple

tim

es.

Flu

xTyp

e 1

PtDi

ff, In

tegr

al

Requ

ired

non

e T

ype

of fl

ux v

alue

s to

be c

ompu

ted.

Ene

rgie

s A

E8: 0

.04

– 8.

0

AP8

: 0.1

– 2

50.0

CRR

ESEL

E: 0

.65,

0.9

5, 1

.60,

2.0

, 2

.35,

2.7

5, 3

.15,

3.7

5, 4

.55,

5.7

5

CRR

ESPR

O: 1

.5, 2

.1, 2

.5, 2

.9, 3

.6,

4.3

, 5.7

, 6.8

, 8.5

, 9.7

, 10.

7, 1

3.2,

1

6.9,

19.

4, 2

6.3,

30.

9, 3

6.3,

41.

1,

47.

0, 5

5.0,

65.

7, 8

1.3

Requ

ired

non

e C

omm

a-se

para

ted

list o

f ene

rgy

leve

ls, in

MeV

, at w

hich

flux

va

lues

are

to b

e co

mpu

ted,

at e

ach

time

step

.

Ene

rgy

valu

es fo

r AE8

or A

P8 a

re re

stric

ted

to th

eir m

odel

-sp

ecifi

c ra

nges

.

For

the

CRRE

S m

odel

s, o

nly

thes

e sp

ecifi

c en

ergy

leve

ls (o

r a

subs

et) m

ay b

e us

ed.


34

Para

met

er K

eyw

ord

Nam

e Al

low

ed V

alue

s Re

quire

d De

faul

t Val

ue

Desc

riptio

n

REA

ctLv

l A

E8 o

r AP8

: ‘m

in’,

‘max

’

CRR

ESPR

O: ‘

activ

e’, ‘

quie

t’

Requ

ired*

n

one

Act

ivity

Lev

el (*

exce

pt fo

r CRR

ESEL

E)

REA

ctRa

nge

‘5

-7.5

’, ‘7

.5-1

0’, ‘

10-1

5’, ‘

15-2

0’,

‘20

-25’

, ‘>2

5’, ‘

avg’

, ‘m

ax’,

or ‘a

ll’

Crre

sele

* n

one

Act

ivity

Lev

el fo

r CRR

ESEL

E

*thi

s or ‘

RE15

DayA

P’ p

aram

eter

is re

quire

d

RE1

5Day

AP

0.0

– 4

00.0

Cr

rese

le*

non

e 1

5 da

y av

erag

e AP

inde

x fo

r CRR

ESEL

E

*thi

s or ‘

REAc

tRan

ge’ p

aram

eter

is re

quire

d

REF

ixEp

och

T

rue

, Fal

se

Opt

iona

l tr

ue

Use

the

mod

el-s

peci

fic fi

xed

epoc

h (y

ear)

val

ues f

or th

e m

agne

tic

field

mod

el in

the

flux

calc

ulat

ions

. It

is h

ighl

y re

com

men

ded

to u

se th

e de

faul

t ‘tr

ue’ v

alue

. U

n-ph

ysic

al fl

ux re

sults

may

be

prod

uced

(esp

ecia

lly a

t low

al

titud

es) i

f set

to ‘f

alse

’. S

ee [H

eynd

eric

kx e

t al,

1996

], fo

r mor

e in

form

atio

n.

RES

hift

SAA

T

rue,

Fal

se

Opt

iona

l fa

lse

Shi

ft th

e SA

A fr

om it

s fix

ed-e

poch

loca

tion

to th

e lo

catio

n fo

r the

cu

rren

t yea

r of t

he e

phem

eris

. S

ee [H

eynd

eric

kx e

t al,

1996

], fo

r mor

e in

form

atio

n.

Thi

s opt

ion

is ig

nore

d if

REFi

xEpo

ch is

‘fal

se’.


35

Appe

ndix

B: L

egac

y M

odel

CAM

MIC

E/M

ICS-

spec

ific

para

met

ers

Thes

e C

AM

MIC

E/M

ICS

mod

el p

aram

eter

s are

to b

e us

ed a

long

with

the

stan

dard

orb

ital s

peci

ficat

ion

para

met

ers.

No

ener

gy le

vel

spec

ifica

tions

are

nee

ded

– va

lues

are

alw

ays o

utpu

t for

the

twel

ve p

re-d

efin

ed e

nerg

y bi

ns (1

.0-1

.3, 1

.8-2

.4, 3

.2-4

.2, 5

.6-7

.4, 9

.9-1

3.2,

17

.5-2

3.3,

30.

9-41

.1, 5

4.7-

72.8

, 80.

3-89

.7, 1

00.1

-111

.7, 1

24.7

-139

.1, 1

55.3

-193

.4 k

eV).

Dos

e ca

lcul

atio

n pa

ram

eter

s may

als

o be

spec

ified

fo

r the

CA

MM

ICE/

MIC

S m

odel

, but

will

gen

eral

ly p

rodu

ce n

on-z

ero

dose

resu

lts o

nly

for t

he to

p th

ree

ener

gy b

ins (

>0.1

MeV

).

Para

met

er K

eyw

ord

Nam

e Al

low

ed V

alue

s Re

quire

d De

faul

t Val

ue

Desc

riptio

n

Mod

elTy

pe

CAM

MIC

E R

equi

red

non

e T

ype

of m

odel

to b

e ru

n (r

equi

res c

orre

spon

ding

dat

abas

e fil

e sp

ecifi

ed in

Mod

elDB

par

amet

er)

Mod

elDB

<

path

>/ca

mm

iceD

B.h5

R

equi

red

non

e D

atab

ase

file

used

to d

rive

the

mod

el, c

orre

spon

ding

to th

e se

lect

ed M

odel

Type

. M

ust i

nclu

de p

ath

to fi

le (a

bsol

ute,

or

rela

tive

to C

mdL

ineA

e9Ap

9 lo

catio

n).

Flu

xTyp

e 1

PtDi

ff, In

tegr

al

Req

uire

d n

one

Typ

e of

flux

val

ues t

o be

com

pute

d.

CIM

odel

igrf

, igr

fop

Req

uire

d n

one

Mag

netic

fiel

d m

odel

to u

se w

ith C

AMM

ICE

(i

grfo

p =

IGRF

w/ O

lson

Pfitz

er e

xter

nal f

ield

mod

el)

CID

stDa

ta

all,

filte

red

Req

uire

d n

one

CAM

MIC

E da

ta fi

lter:

use

all d

ata,

or d

ata

for D

ST >

-100

CIS

peci

es

h+,

he+

, he+

2, o

+, h

, he,

o, i

ons

Req

uire

d n

one

CAM

MIC

E sp

ecie

s for

whi

ch to

retu

rn fl

ux d

ata.

Thi

s par

amet

er

may

app

ear m

ultip

le ti

mes

.

CIP

Angl

e

‘0-1

0’, ‘

10-2

0’, ‘

20-3

0’, ‘

30-4

0’,

‘40-

50’,

‘50-

60’,

‘60-

70’,

‘70-

80’,

‘80-

90’,

‘90-

100’

, ‘10

0-11

0’,

‘110

-120

’, ‘1

20-1

30’,

‘130

-140

’,

‘140

-150

’, ‘1

50-1

60’,

‘160

-170

’,

‘170

-180

’, or

‘om

ni’

Req

uire

d n

one

Bin

of p

itch

angl

es fo

r whi

ch to

retu

rn fl

ux d

ata

in C

AMM

ICE

(o

mni

=om

nidi

rect

iona

l)


36

Appe

ndix

C: M

odifi

ed Ju

lian

Dat

e Th

e M

odifi

ed Ju

lian

Dat

e (M

JD) i

s an

astro

nom

ical

tim

e co

nven

tion

that

has

the

grea

t adv

anta

ge o

f bei

ng a

con

tinuo

us ti

me

varia

ble,

w

ithou

t the

dis

cont

inui

ties i

ntro

duce

d by

the

usua

l civ

il tim

e co

nven

tion

of y

ears

, mon

th, d

ays,

hour

s, m

inut

es a

nd se

cond

s. T

his

mak

es it

idea

l for

com

pute

r man

ipul

atio

n of

long

tim

e se

ries.

The

Mod

ified

Julia

n D

ate

is d

eriv

ed fr

om a

muc

h ol

der s

yste

m c

alle

d ‘J

ulia

n D

ate’

, whi

ch w

as d

efin

ed a

s the

tim

e, in

day

s, si

nce

noon

(1

200G

MT)

on

1 Ja

nuar

y 47

13 B

C. T

he M

JD si

mpl

y su

btra

cts 2

4000

00.5

from

the

Julia

n D

ate

(the

extra

0.5

shift

s the

star

t of d

ays

from

mid

dle

to th

e be

ginn

ing)

. Thu

s, th

e us

e of

MJD

requ

ires o

nly

use

of 5

(rat

her t

han

7) d

igits

to th

e le

ft of

the

deci

mal

poi

nt.

It is

de

fined

as d

ays s

ince

17

Nov

185

8, 0

000G

MT.

For e

xam

ple

0

1 Ja

n 20

00, 1

200G

MT

is Ju

lian

Dat

e 24

5154

5.0,

and

Mod

ified

Julia

n D

ate

5154

4.5

1

0 O

ct 2

012,

000

0GM

T is

Julia

n D

ate

2456

210.

5, a

nd M

odifi

ed Ju

lian

Dat

e 56

210.

0

01

Jan

1950

, 000

0GM

T is

Julia

n D

ate

2433

282.

5, a

nd M

odifi

ed Ju

lian

Dat

e 33

282.

0

Man

y to

ols a

nd a

lgor

ithm

s exi

sts t

o co

nver

t bet

wee

n ca

lend

ar d

ate

and

time

to Ju

lian

or M

odifi

ed Ju

lian

Dat

es

http

://w

ww

.onl

inec

onve

rsio

n.co

m/ju

lian_

date

.htm

ht

tp://

scie

ncew

orld

.wol

fram

.com

/ast

rono

my/

Mod

ified

Julia

nDat

e.ht

ml

http

://w

ww

.csg

netw

ork.

com

/julia

nmod

ifdat

econ

v.ht

ml

In E

xcel

, if y

ou h

ave

a da

te/ti

me

in c

ell A

1, th

en th

e fo

llow

ing

form

ula

will

con

vert

it to

MJD

(but

you

'll n

eed

to se

t the

form

ula's

cel

l fo

rmat

to "n

umbe

r")"

=A1-date(1950,1,1)+33282

Th

is w

orks

bec

ause

Exc

el u

ses a

dat

e se

rial t

hat i

s a d

ecim

al n

umbe

r of d

ays s

ince

som

e re

fere

nce

epoc

h.

Mat

lab

also

use

s som

e re

fere

nce

epoc

h. T

his s

nipp

et o

f Mat

lab

code

will

con

vert

a da

te st

ring

to M

JD:

mjd = datenum(date_string)+33282-datenum(1950,1,1);

An

impo

rtant

war

ning

for u

sers

of S

PEN

VIS

– a

NO

N-S

TAN

DAR

D d

efin

ition

for ‘

Mod

ified

Julia

n D

ate’

is u

sed:

“F

inal

ly, n

ote

that

the

Mod

ified

Jul

ian

Dat

e (M

JD) u

sed

in S

PEN

VIS

is d

efin

ed a

s the

num

ber o

f day

s fro

m 1

st Ja

nuar

y 19

50 0

0:00

UT.

” se

e

http

://w

ww

.spen

vis.o

ma.

be/h

elp/

mod

els/

sapr

e.ht

ml


37

http://www.onlineconversion.com/julian_date.htm

http://scienceworld.wolfram.com/astronomy/ModifiedJulianDate.html

http://www.csgnetwork.com/julianmodifdateconv.html

http://www.spenvis.oma.be/help/models/sapre.html

DISTRIBUTION LIST

DTIC/OCP 8725 John J. Kingman Rd, Suite 0944 Ft Belvoir, VA 22060-6218 1 cy

AFRL/RVIL Kirtland AFB, NM 87117-5776 2 cys

Official Record Copy AFRL/RVBXR/Dr. Michael Starks 1 cy


38

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