FRR-38 Calculation Parameters

Explore

Known Bugs

 

JIRA ID  

Summary  

Recommendation  

GMT-585  

Multiple redundant properties/fields for epoch

P3

GMT-1098  

Tab key navigation fails

Appears fixed

GMT-1346  

Add ability for user-defined parameters

Improvement

GMT-1439  

Parameter design for multiple dependency

Improvement

GMT-1483  

Ability to Calculate and Output Sun Vector to any point

Improvement

GMT-1899  

Beta Angle is Off by about .003 degrees

P1

GMT-1933  

Earth Fixed RA changed from 0-360 to -180-180 measurement

P1 (document)

GMT-2011  

Larger angular momentum errors in 09/15 build

P1, assign to Joel

GMT-2318  

STM Parameters are wrong when using Coordinate System other than EarthMJ2000Eq

P1, assign to Joel

GMT-2475  

Provide a parameter to check convergence status of a VF13 optimizer

Improvement

GMT-2673  

User Reported: Parameter Select Dialog Box Silently Changes User's Selected Object

Needs verification

GMT-2755  

ParameterCreateDialog does not close properly after adding string parameter on Mac

P2

 

Failing Tests

Failing tests listed as of 10/15/2012.

 

JIRA ID  

Test  

Summary  

Rec .  

TBD

CbParams_Hyperbolic_2Body

Incorrect MA , OrbitPeriod

Investigate

TBD

CSParams_Uranus1_2Body_UranusFixed

Numeric issues

Investigate

TBD

CSParams_Saturn1_2Body_SaturnFixed

Numeric issues

Investigate

TBD

CSParams_Pluto1_2Body_PlutoFixed

Test issues, plus numerics

Investigate

TBD

CSParams_Neptune1_2Body_NeptuneMJ2000Ec

Test issues, plus many incorrect parameters

Investigate

TBD

CSParams_Neptune1_2Body_NeptuneFixed

Numeric issues

Investigate

TBD

CSParams_Hyperbolic_2Body

Numeric issues

Investigate

TBD

CSParams_GEO_2Body

Numeric issues

Investigate

 

Other Findings

 

JIRA ID  

Summary  

Rec.  

GMT-3164

Inconsistent naming: RadApo/RadPer and VelApoapsis/RadPeriapsis

P3

GMT-3165

ParameterSelectDialog is badly named

P2

GMT-3166

ParameterSelectDialog string consistency issues

P3

GMT-3167

ParameterSelectDialog doesn't remove item from available list once chosen

P2

GMT-3173

Clarification needed on HA output range

P1

GMT-3205

ParameterSelectDialog shouldn't use list box for single-parameter selection

P3

 

Requirements

 

C:\images\icons\emoticons\warning.png

To reviewers: I'm considering removing "or set" and the "(read only)/(read/write)" bits from the requirements. All of the "write" parameters should already be described on the requirement for the parent resource.

ID  

Requirements  

FRR-38.1.0

The system shall allow the user to request or set the following object properties with respect to any celestial body in FRR-16:

FRR-38.1.1.0

1)           Spacecraft and orbit parameters

FRR-38.1.1.1

1.                                           Altitude (read only)

FRR-38.1.1.2

2.                                           Beta angle (read only)

FRR-38.1.1.3

3.                                           C3 energy (read only)

FRR-38.1.1.4

4.                                           Eccentric anomaly (read/write)

FRR-38.1.1.5

5.                                           Eccentricity (read/write)

FRR-38.1.1.6

6.                                           Orbit energy (read only)

FRR-38.1.1.7

7.                                             Magnitude of angular momentum (read only)

FRR-38.1.1.8

8.                                           Planetodetic latitude (read only)

FRR-38.1.1.8

9.                                           Longitude (read only)

FRR-38.1.1.10

10.                                         Local sidereal time (read only)

FRR-38.1.1.11

11.                                         Mean anomaly (read/write)

FRR-38.1.1.12

12.                                         Mean hour angle (read only)

FRR-38.1.1.13

13.                                         Mean motion (read only)

FRR-38.1.1.14

14.                                         Orbit period (read only)

FRR-38.1.1.15

15.                                         Radius of apoapsis (read/write)

FRR-38.1.1.16

16.                                         Radius of periapsis (read/write)

FRR-38.1.1.17

17.                                         Magnitude of position vector (read/write)

FRR-38.1.1.18

18.                                       Semilatus rectum (read only)

FRR-38.1.1.19

19.                                       Semi-major axis (read/write)

FRR-38.1.1.20

20.                                         True anomaly (read/write)

FRR-38.1.1.21

21.                                         Velocity at apoapsis (read only)

FRR-38.1.1.22

22.                                         Velocity at periapsis (read only)

FRR-38.1.1.23

23.                                         Hyperbolic anomaly (read/write)

FRR-38.1.1.24

24.                                         Apoapsis crossing indicator (read only)

FRR-38.1.1.25

25.                                         Periapsis crossing indicator (read only)

FRR-38.2.0

The system shall allow the user to request or set the following object properties with respect to any coordinate system in FRR-35:

FRR-38.2.1.0

1)           Spacecraft and orbit parameters

FRR-38.2.1.1

1.                                           Argument of periapsis (read/write)

FRR-38.2.1.2

2.                                           Azimuth (read/write)

FRR-38.2.1.3

3.                                           B dot T (read only)

FRR-38.2.1.4

4.                                           B dot R (read only)

FRR-38.2.1.5

5.                                           B vector angle (read only)

FRR-38.2.1.6

6.                                           B vector magnitude (read only)

FRR-38.2.1.7

7.                                           Declination (read/write)

FRR-38.2.1.8

8.                                           Declination of velocity (read/write)

FRR-38.2.1.9

9.                                           Flight path angle (read/write)

(delete)

10.                                         Hyperbolic anomaly (read/write)

FRR-38.2.1.11

11.                                       Components of angular momentum (read only)

FRR-38.2.1.12

12.                                       Inclination (read/write)

FRR-38.2.1.13

13.                                       Orbit state transition matrix (read only)

FRR-38.2.1.14

14.                                         3x3 partitions of Orbit STM (read only)

FRR-38.2.1.15

15.                                         Right ascension (read/write)

FRR-38.2.1.16

16.                                         Right ascension of the ascending node (read/write)

FRR-38.2.1.17

17.                                         Right ascension of velocity (read/write)

FRR-38.2.1.18

18.                                         Magnitude of velocity (read/write)

FRR-38.2.1.19

19.                                         Components of Cartesian velocity (read/write)

FRR-38.2.1.20

20.                                         Components of Cartesian position (read/write)

FRR-38.2.1.21

21.                                         Right ascension of outgoing hyperbolic asymptote (read only)

FRR-38.2.1.22

22.                                         Declination of outgoing hyperbolic asymptote (read only)

FRR-38.3.0

The system shall allow the user to request or set the following object properties:

FRR-38.3.1.0

1)           Spacecraft and orbit parameters

FRR-38.3.1.3

3.                                           Components of angular velocity (read/write)

FRR-38.3.1.4

4.                                           Drag coefficient (read/write)

FRR-38.3.1.5

5.                                           Reflectivity coefficient (read/write)

FRR-38.3.1.6

6.                                           Components of attitude direction cosine matrix (read/write)

FRR-38.3.1.7

7.                                           Drag area (read/write)

FRR-38.3.1.8

8.                                           Dry mass (read/write)

FRR-38.3.1.9

9.                                           Elapsed days (read only)

FRR-38.3.1.10

10.                                         Elapsed seconds (read only)

(delete)

11.                                         Euler angles for any sequence (read/write)

(delete)

12.                                         Euler angle rates for any sequence (read/write)

FRR-38.3.1.13

13.                                       Components of attitude quaternion (read only)

FRR-38.3.1.14

14.                                         SRP area (read/write)

FRR-38.3.1.15

15.                                         Epoch in TAI modified Julian (read/write)

FRR-38.3.1.16

16.                                         Epoch in TAI Gregorian (read/write)

FRR-38.3.1.19

19.                                         Epoch in TDB modified Julian (read/write)

FRR-38.3.1.20

20.                                         Epoch in TDB Gregorian (read/write)

FRR-38.3.1.21

21.                                         Epoch in TT modified Julian (read/write)

FRR-38.3.1.22

22.                                         Epoch in TT Gregorian (read/write)

FRR-38.3.1.23

23.                                         Epoch in UTC modified Julian (read/write)

FRR-38.3.1.24

24.                                         Epoch in UTC Gregorian (read/write)

FRR-38.3.1.25

25.                                       Total mass (read only)

FRR-38.3.1.26

26.                                         Modified Rodrigues parameters (read/write)

FRR-38.3.1.27

27.                                         Euler angles (read/write)

FRR-38.3.1.28

28.                                         Euler angle rates (read/write)

FRR-38.3.1.29

29.                                         Epoch in A.1 modified Julian (read/write)

FRR-38.3.1.30

30.                                         Epoch in A.1 Gregorian (read/write)

FRR-38.3.1.31

31.                                         Attitude quaternion (read/write)

FRR-38.3.2.0

2)           Impulsive burn parameters

FRR-38.3.2.1

1.                                           Thrust vector element 1 (read/write)

FRR-38.3.2.2

2.                                           Thrust vector element 2 (read/write)

FRR-38.3.2.3

3.                                           Thrust vector element 3 (read/write)

(delete)

4.                                           Thrust vector velocity component (read/write)

(delete)

5.                                           Thrust vector normal component (read/write)

(delete)

6.                                           Thrust vector binormal component (read/write)

FRR-38.3.3.0

3)           Tank parameters

FRR-38.3.3.1

1.                                           Pressure (read/write)

FRR-38.3.3.2

2.                         Volume (read/write)

FRR-38.3.3.3

3.                                           Fuel density (read/write)

FRR-38.3.3.4

4.                                           Fuel mass (read/write)

FRR-38.3.3.5

5.                                           Temperature (read/write)

FRR-38.3.3.6

6.                                           Reference temperature (read/write)

FRR-38.3.4.0

4)           Thruster parameters

FRR-38.3.4.1

1.                                             Duty cycle (read/write)

FRR-38.3.4.2

2.                                             Thrust scale factor (read/write)

FRR-38.3.4.3

3.                                             Gravitational acceleration for thrust equation (read/write)

FRR-38.3.4.4

4.                                             Thrust coefficients (read/write)

FRR-38.3.4.5

5.                                             Isp coefficients (read/write)

FRR-38.3.4.6

6.                                             Components of thrust direction (read/write)

 

Interface/Functional Spec

Overview  

Data property available for use by commands

Description  

Parameters are named resource properties that can be used to obtain data for use by Mission Sequence commands or by output resources. Some parameters, such as the Altitude parameter of Spacecraft , are calculated values that can only be used to retrieve data. They cannot be set directly. Others, such as the Element1 parameter of ImpulsiveBurn , share the same name as a resource field and can be used both to set data and retrieve it. Parameters are distinguished from resource fields by their extra functionality: fields are static resource properties that are usually set in initialization (or in the GUI Resources tree), while parameters can be calculated on the fly and used in plots, reports, and mathematical expressions.

Parameters are classified as one of four types: central-body-dependent parameters, coordinate-system-dependent parameters, attached-hardware parameters, and standalone parameters. Standalone parameters are the simplest type, in that they have no dependencies. The ElapsedSecs parameter of Spacecraft is an example of this; it is simply referenced as Spacecraft .ElapsedSecs .

Central-body-dependent parameters, as the name suggests, have a value that is dependent on the chosen celestial body. The Altitude parameter of Spacecraft is an example of this. To reference this parameter, you must specify a central body, such as Spacecraft .Mars.Altitude . Any built-in central body or user-defined Asteroid , Comet , Moon , or Planet is valid as a dependency. If the dependency is omitted, Earth is assumed.

Likewise, coordinate-system-dependent parameters have a value that is dependent on the chosen coordinate system. The DEC parameter of Spacecraft is an example of this. To reference this parameter, you must specify the name of a CoordinateSystem resource, such as Spacecraft .EarthFixed.DEC . Any default or user-defined CoordinateSystem resource is valid as a dependency. If the dependency is omitted, EarthMJ2000Eq is assumed.

Attached-hardware parameters have no dependencies, but are themselves dependent on being attached to a Spacecraft . FuelTank and Thruster parameters are examples of this. The FuelMass parameter of FuelTank cannot be referenced without first attaching the FuelTank to a Spacecraft . Then, the parameter can be referenced as: Spacecraft . FuelTank .FuelMass .

The individual parameters are resource-specific, and are documented along with the their parent resources. The GUI, however, has a parameter selection interface that is common to all parameters. This interface is documented in GUI, below.
 
See Also: Script Language, FuelTank, ImpulsiveBurn, Spacecraft, Thruster

GUI  

Parameters can be used as input in several places throughout GMAT, such as the ReportFile and XYPlot resources and the If / Else , Propagate , and Report commands. In the GUI, all of these use a common interface called the ParameterSelectDialog that allows for interactive parameter selection. A basic ParameterSelectDialog window looks like the following:

C:\attach_3b5600a724407fcdaa6ab07e0e1428b9

The ParameterSelectDialog window is used to build a parameter, along with any dependencies, for use in a command or resource. Some resources and commands have different requirements for the types of parameters that can be used, so the ParameterSelectDialog can take slightly different forms, depending on where it's used. This section will describe the generic interface, then mention any resource- or command-specific exceptions.

General Usage

The first step in choosing a parameter is to select the object (or resource) type from the Object Type list in the upper left. Five types can appear in this list: Spacecraft , ImpulsiveBurn , Variable , Array , and String .

Once you've selected a type, The Object List box is populated with all existing resources of that type. Use this list to choose the specific resource you'd like to reference.

If the Spacecraft type is selected, the Attached Hardware List appears below the Object List . This list displays any hardware (such as FuelTank resources) attached to the selected Spacecraft . If the Array type is selected, Row and Col boxes appear. Use these to specify a row and column to select an individual array element, or check Select Entire Object to choose the entire array.

Once a resource is selected, the Object Properties list is populated with all available parameters provided by that resource. Some resources, such as instances of Variable or Array , are themselves parameters, so this list remains empty.

Parameters with different dependency types are commingled in the Object Properties list. When you select one, the appropriate dependency (if any) appears below the list. For example, after selecting the Spacecraft AOP parameter, a Coordinate System list appears. After selecting the Spacecraft Apoapsis parameter, a Central Body list appears. And after selecting the Spacecraft Cd parameter, no dependency list appears. To select a range of parameters from the Object Properties list, hold down the Shift key while selecting the second endpoint of the range. To select multiple individual parameters, hold down the Ctrl key while making each selection.

To select a parameter, select the appropriate Object Type , the specific resource from the Object List or Attached Hardware List , the desired parameter from the Object Properties list, and the required dependency, and add it to the Selected Value(s) list on the right. There are six buttons available to control this list:

  • UP : Move the selected item in the Selected Value(s) list up one position (if allowed).
  • DN : Move the selected item in the Selected Value(s) list down one position (if allowed).
  • -> : Add the selected item in the Object Properties list to the Selected Value(s) list.
  • <- : Remove the selected item in the Selected Value(s) list.
  • => : Add all items to the Selected Value(s) list.
  • <= : Remove all items from the Selected Value(s) list.

When finished, the Selected Value(s) list contains the final selected parameters. Click OK to accept the selection.

The ordering of the Selected Value(s) list is significant in certain circumstances (such as in the Add field of ReportFile ), but not in others. See the documentation for each resource or command for details.

Special Considerations

Some resources and commands (such as the Propagate command Parameter argument) only accept a single parameter as input; in this context the ParameterSelectDialog only allows one parameter in the Selected Value(s) list and does not allow use of the UP , DN , and => buttons.

In some instances (such as in the Vary command), only parameters that are also fields (and so can be set in the Mission Sequence ) can be used. In this case only the allowed parameters will be shown in the Object Properties list.

In the Propagate command Parameter argument, only parameters of Spacecraft can be used. In this case only Spacecraft will be shown in the Object Type list.

Parameters

 

C:\images\icons\emoticons\warning.png

To Reviewer: These tables will be merged into the parent reference pages and labeled as "Field" or "Parameter". For existing fields, the description already in the spec will be used instead of the description below. Each section below will be linked to the parent reference page.

C:\images\icons\emoticons\warning.png

To Technical Writer: The "pencil" icon in the following tables is from http://www.famfamfam.com/lab/icons/silk/ . They're free to use, but we need to credit them.

Spacecraft

Parameter

C:\attach_075809f41a1cb53fad376b7098fec03b

C:\attach_95dc371c23f9ef4eabfae3c50265c5c6

Units

  Description

ElapsedSecs

N

Y

s

Spacecraft

Data Type: Real Number
Dependency: None

ElapsedDays

N

Y

d

Spacecraft

Data Type: Real Number
Dependency: None

A1ModJulian

Y

Y

d

Spacecraft orbit epoch in the A.1 system and the Modified Julian format.

Data Type: Real Number
Dependency: None

A1Gregorian

Y

N

N/A

Spacecraft orbit epoch in the A.1 system and the Gregorian format.

Data Type: String
Dependency: None

TAIModJulian

Y

Y

d

Spacecraft orbit epoch in the TAI system and the Modified Julian format.

Data Type: Real Number
Dependency: None

TAIGregorian

Y

N

N/A

The spacecraft orbit epoch in the TAI system and the Gregorian format.

Data Type: String
Dependency: None

TTModJulian

Y

Y

d

The spacecraft orbit epoch in the TT system and the Modified Julian format.

Data Type: Real Number
Dependency: None

TTGregorian

Y

N

N/A

Spacecraft orbit epoch in the TT system and the Gregorian format.

Data Type: String
Dependency: None

TDBModJulian

Y

Y

d

Spacecraft orbit epoch in the TDB system and the Modified Julian format.

Data Type: Real Number
Dependency: None

TDBGregorian

Y

N

N/A

Spacecraft orbit epoch in the TDB system and the Gregorian format.

Data Type: String
Dependency: None

UTCModJulian

Y

Y

d

Spacecraft orbit epoch in the UTC system and the Modified Julian format.

Data Type: Real Number
Dependency: None

UTCGregorian

Y

N

N/A

Spacecraft orbit epoch in the UTC system and the Gregorian format.

Data Type: String
Dependency: None

CurrA1MJD

Y

Y

d

Deprecated. Spacecraft orbit epoch in the A.1 system and the Modified Julian format.

Data Type: Real Number
Dependency: None

X

Y

Y

km

Cartesian x-component of the spacecraft position.

Data Type: Real Number
Dependency: Coordinate System

Y

Y

Y

km

Cartesian y-component of the spacecraft position.

Data Type: Real Number
Dependency: Coordinate System

Z

Y

Y

km

Cartesian z-component of the spacecraft position.

Data Type: Real Number
Dependency: Coordinate System

VX

Y

Y

km/s

Cartesian x-component of the spacecraft velocity.

Data Type: Real Number
Dependency: Coordinate System

VY

Y

Y

km/s

Cartesian y-component of the spacecraft velocity.

Data Type: Real Number
Dependency: Coordinate System

VZ

Y

Y

km/s

Cartesian z-component of the spacecraft velocity.

Data Type: Real Number
Dependency: Coordinate System

SMA

Y

Y

km

Orbit semi-major axis.

Data Type: Real Number
Dependency: Central Body

ECC

Y

Y

N/A

Orbit eccentricity.

Data Type: Real Number
Dependency: Central Body

INC

Y

Y

°

Orbit inclination.

Data Type: Real Number
Dependency: Coordinate System

Output Range: 0° ≤ INC ≤ 180°

RAAN

Y

Y

°

Orbit right ascension of the ascending node.

Data Type: Real Number
Dependency: Coordinate System
Output Range: 0° ≤ RAAN < 360°

AOP

Y

Y

°

Orbit argument of periapsis.

Data Type: Real Number
Dependency: Coordinate System
Output Range: 0° ≤ AOP < 360°

TA

Y

Y

°

True anomaly.

Data Type: Real Number
Dependency: Central Body
Output Range: 0° ≤ TA < 360°

MA

N

Y

°

Mean anomaly.

Data Type: Real Number
Dependency: Central Body
Output Range: 0° ≤ MA < 360° (elliptic orbits)

EA

N

Y

°

Eccentric anomaly.

Data Type: Real Number
Dependency: Central Body
Output Range: 0° ≤ EA < 360°

HA

N

Y

°

Hyperbolic anomaly.

Data Type: Real Number
Dependency: Central Body

MM

N

Y

rad/s

Mean motion.

Data Type: Real Number
Dependency: Central Body

VelApoapsis

N

Y

km/s

Scalar velocity at apoapsis.

Data Type: Real Number
Dependency: Central Body

VelPeriapsis

N

Y

km/s

Scalar velocity at periapsis.

Data Type: Real Number
Dependency: Central Body

Apoapsis

N

Y

N/A

A parameter that equals zero when the spacecraft is at orbit apoapsis. This parameter is intended to be used as a stopping condition in the Propagate command.

Data Type: Real Number
Dependency: Central Body

Periapsis

N

Y

N/A

A parameter that equals zero when the spacecraft is at orbit periapsis. This parameter is intended to be used as a stopping condition in the Propagate command.

Data Type: Real Number
Dependency: Central Body

OrbitPeriod

N

Y

s

Osculating orbit period.

Data Type: Real Number
Dependency: Central Body

RadApo

Y

Y

km

Radius of apoapsis.

Data Type: Real Number

Dependency: Central Body

RadPer

Y

Y

km

Radius of periapsis.

Data Type: Real Number
Dependency: Central Body

C3Energy

N

Y

MJ/kg (km 2 /s 2 )

C 3 (characteristic) energy.

Data Type: Real Number
Dependency: Central Body

Energy

N

Y

MJ/kg (km 2 /s 2 )

Specific orbital energy.

Data Type: Real Number
Dependency: Central Body

RMAG

Y

Y

km

Magnitude of the orbital position vector.

Data Type: Real Number
Dependency: Central Body

RA

Y

Y

°

Right ascension of the orbital position.

Data Type: Real Number
Dependency: Coordinate System
Output Range: -180° ≤ RA   ≤ 180°

DEC

Y

Y

°

Declination of the orbital position.

Data Type: Real Number
Dependency: Coordinate System
Output Range: -90° ≤ DEC ≤ 90°

VMAG

Y

Y

km/s

Magnitude of the orbital velocity vector.

Data Type: Real Number
Dependency: Coordinate System

RAV

Y

Y

°

Right ascension of orbital velocity.

Data Type: Real Number
Dependency: Coordinate System
Output Range: -180° ≤ RAV ≤ 180°

DECV

Y

Y

°

Declination of orbital velocity.

Data Type: Real Number
Dependency: Coordinate System
Output Range: -90° ≤ DECV ≤ 90°

AZI

Y

Y

°

Orbital velocity azimuth.

Data Type: Real Number
Dependency: Coordinate System
Output Range: -180° ≤ AZI ≤ 180°

FPA

Y

Y

°

Orbital flight path angle.

Data Type: Real Number
Dependency: Coordinate System
Output Range: 0° ≤ FPA ≤ 180°

SemilatusRectum

N

Y

km

Semilatus rectum of the osculating orbit.

Data Type: Real Number
Dependency: Central Body

HMAG

N

Y

km 2 /s

Magnitude of the angular momentum vector.

Data Type: Real Number
Dependency: Central Body

HX

N

Y

km 2 /s

X component of the angular momentum vector.

Data Type: Real Number
Dependency: Coordinate System

HY

N

Y

km 2 /s

Y component of the angular momentum vector.

Data Type: Real Number
Dependency: Coordinate System

HZ

N

Y

km 2 /s

Z component of the angular momentum vector.

Data Type: Real Number
Dependency: Coordinate System

DLA

N

Y

°

Declination of the outgoing hyperbolic asymptote.

Data Type: Real Number
Dependency: Coordinate System
Output Range: -90° ≤ DLA ≤ 90°

RLA

N

Y

°

Right ascension of the outgoing hyperbolic asymptote.

Data Type: Real Number
Dependency: Coordinate System
Output Range: -180° ≤ RLA ≤ 180°

Altitude

N

Y

km

Distance to the plane tangent to the surface of the specified celestial body at the sub-satellite point. GMAT assumes the body is an ellipsoid.

Data Type: Real Number
Dependency: Central Body

MHA

N

Y

°

Greenwich hour angle.

Data Type: Real Number
Dependency: Central Body
Output Range: 0° ≤ MHA < 360°

Longitude

N

Y

°

Planetodetic longitude.

Data Type: Real Number
Dependency: Central Body
Output Range: -180° ≤ Longitude ≤ 180°

Latitude

N

Y

°

Planetodetic latitude.

Data Type: Real Number
Dependency: Central Body
Output Range: -90° ≤ Latitude ≤ 90°

LST

N

Y

°

Local sidereal time.

Data Type: Real Number
Dependency: Central Body
Output Range: 0° ≤ LST < 360°

BetaAngle

N

Y

°

Beta angle (or phase angle) between the orbit normal vector and the vector from the celestial body to the sun.

Data Type: Real Number
Dependency: Central Body
Output Range: -90° ≤ BetaAngle ≤ 90°

BdotT

N

Y

km

B-plane B · T magnitude.

Data Type: Real Number
Dependency: Coordinate System

BdotR

N

Y

km

B-plane B · R magnitude.

Data Type: Real Number
Dependency: Coordinate System

BVectorMag

N

Y

km

B-plane B vector magnitude.

Data Type: Real Number
Dependency: Coordinate System

BVectorAngle

N

Y

°

B-plane angle between the B vector and the T unit vector.

Data Type: Real Number
Dependency: Coordinate System
Output Range: -180° ≤ BVectorAngle ≤ 180°

DCM11

Y

Y

(None)

Element (1,1) of the attitude direction cosine matrix.

Data Type: Real Number
Dependency: (None)

DCM12

Y

Y

(None)

Element (1,2) of the attitude direction cosine matrix.

Data Type: Real Number
Dependency: (None)

DCM13

Y

Y

(None)

Element (1,3) of the attitude direction cosine matrix.

Data Type: Real Number
Dependency: (None)

DCM21

Y

Y

(None)

Element (2,1) of the attitude direction cosine matrix.

Data Type: Real Number
Dependency: (None)

DCM22

Y

Y

(None)

Element (2,2) of the attitude direction cosine matrix.

Data Type: Real Number
Dependency: (None)

DCM23

Y

Y

(None)

Element (2,3) of the attitude direction cosine matrix.

Data Type: Real Number
Dependency: (None)

DCM31

Y

Y

(None)

Element (3,1) of the attitude direction cosine matrix.

Data Type: Real Number
Dependency: (None)

DCM32

Y

Y

(None)

Element (3,2) of the attitude direction cosine matrix.

Data Type: Real Number
Dependency: (None)

DCM33

Y

Y

(None)

Element (3,3) of the attitude direction cosine matrix.

Data Type: Real Number
Dependency: (None)

EulerAngle1

Y

Y

°

Attitude Euler angle 1.

Data Type: Real Number
Dependency: (None)
Output Range: 0° ≤ EulerAngle1 < 360°

EulerAngle2

Y

Y

°

Attitude Euler angle 2.

Data Type: Real Number
Dependency: (None)
Output Range: 0° ≤ EulerAngle2 < 360°

EulerAngle3

Y

Y

°

Attitude Euler angle 3.

Data Type: Real Number
Dependency: (None)
Output Range: 0° ≤ EulerAngle3 < 360°

MRP1

Y

Y

(None)

Attitude modified Rodrigues parameter 1.

Data Type: Real Number
Dependency: (None)

MRP2

Y

Y

(None)

Attitude modified Rodrigues parameter 2.

Data Type: Real Number
Dependency: (None)

MRP3

Y

Y

(None)

Attitude modified Rodrigues parameter 3.

Data Type: Real Number
Dependency: (None)

Q1

N

Y

(None)

Attitude quaternion element 1 ( a ).

Data Type: Real Number
Dependency: (None)

Q2

N

Y

(None)

Attitude quaternion element 2 ( b ).

Data Type: Real Number
Dependency: (None)

Q3

N

Y

(None)

Attitude quaternion element 3 ( c ).

Data Type: Real Number
Dependency: (None)

Q4

N

Y

(None)

Attitude quaternion element 4 ( d ).

Data Type: Real Number
Dependency: (None)

Quaternion

Y

N

(None)

Attitude quaternion.

Data Type: Array (1×4)
Dependency: (None)

AngularVelocityX

Y

Y

°/s

X component of the attitude angular velocity vector.

Data Type: Real Number
Dependency: (None)

AngularVelocityY

Y

Y

°/s

Y component of the attitude angular velocity vector.

Data Type: Real Number
Dependency: (None)

AngularVelocityZ

Y

Y

°/s

Z component of the attitude angular velocity vector.

Data Type: Real Number
Dependency: (None)

EulerAngleRate1

Y

Y

°/s

Rate of attitude Euler angle 1.

Data Type: Real Number
Dependency: (None)

EulerAngleRate2

Y

Y

°/s

Rate of attitude Euler angle 2.

Data Type: Real Number
Dependency: (None)

EulerAngleRate3

Y

Y

°/s

Rate of attitude Euler angle 3.

Data Type: Real Number
Dependency: (None)

DryMass

Y

Y

kg

Dry mass (without propellant).

Data Type: Real Number
Dependency: (None)

Cd

Y

Y

(None)

Coefficient of drag.

Data Type: Real Number
Dependency: (None)

Cr

Y

Y

(None)

Coefficient of reflectivity.

Data Type: Real Number
Dependency: (None)

DragArea

Y

Y

m 2

Area used to compute acceleration due to atmospheric drag.

Data Type: Real Number
Dependency: (None)

SRPArea

Y

Y

m 2

Area used to compute acceleration due to solar radiation pressure.

Data Type: Real Number
Dependency: (None)

TotalMass

N

Y

kg

Total mass, including fuel mass from attached Fuel Tank resources.

Data Type: Real Number
Dependency: (None)

OrbitSTM

N

N

(None)

State transition matrix.

Data Type: Array (6×6)
Dependency: Coordinate System

OrbitSTMA

N

N

(None)

Upper-left quadrant of the state transition matrix.

Data Type: Array (3×3)
Dependency: Coordinate System

OrbitSTMB

N

N

(None)

Upper-right quadrant of the state transition matrix.

Data Type: Array (3×3)
Dependency: Coordinate System

OrbitSTMC

N

N

(None)

Lower-left quadrant of the state transition matrix.

Data Type: Array (3×3)
Dependency: Coordinate System

OrbitSTMD

N

N

(None)

Lower-right quadrant of the state transition matrix.

Data Type: Array (3×3)
Dependency: Coordinate System

FuelTank

Parameter

C:\attach_075809f41a1cb53fad376b7098fec03b

C:\attach_95dc371c23f9ef4eabfae3c50265c5c6

Units

  Description

FuelMass

Y

Y

kg

Mass of fuel in the tank.

Data Type: Real Number
Dependency: (None)

Volume

Y

Y

m 3

Volume of the tank. GMAT checks to ensure that the input volume of the tank is larger than the calculated volume of fuel loaded in the tank and throws an exception in the case that the calculated fuel volume is larger than the input tank volume.

Data Type: Real Number
Dependency: (None)

FuelDensity

Y

Y

kg/m 3

Density of the fuel.

Data Type: Real Number
Dependency: (None)

Pressure

Y

Y

kPa

Pressure in the tank.

Data Type: Real Number
Dependency: (None)

Temperature

Y

Y

°C

Temperature of the fuel and ullage in the tank. GMAT currently assumes ullage and fuel are always at the same temperature.

Data Type: Real Number
Dependency: (None)

RefTemperature

Y

Y

°C

The temperature of the tank when fuel was loaded.

Data Type: Real Number
Dependency: (None)

Thruster

Parameter

C:\attach_075809f41a1cb53fad376b7098fec03b

C:\attach_95dc371c23f9ef4eabfae3c50265c5c6

Units

  Description

DutyCycle

Y

Y

  (None)

Fraction of time that the thrusters are on during a maneuver. The thrust applied to the spacecraft is scaled by this amount. Note that this scale factor also affects mass flow rate.

Data Type: Real Number
Dependency: (None)

ThrustScaleFactor

Y

Y

  (None)

Scale factor that is multiplied by the thrust vector, for a given thruster, before the thrust vector is added into the total acceleration. Note that the value of this scale factor does not affect the mass flow rate.

Data Type: Real Number
Dependency: (None)

GravitationalAccel

Y

Y

  m/s 2

Value of the gravitational acceleration used for the FuelTank/Thruster calculations.

Data Type: Real Number
Dependency: (None)

C1

Y

Y

N

Thrust coefficient C 1 .

Data Type: Real Number
Dependency: (None)

C2

Y

Y

N/kPa

Thrust coefficient C 2 .

Data Type: Real Number
Dependency: (None)

C3

Y

Y

N

Thrust coefficient C 3 .

Data Type: Real Number
Dependency: (None)

C4

Y

Y

N/kPa

Thrust coefficient C 4 .

Data Type: Real Number
Dependency: (None)

C5

Y

Y

N/kPa 2

Thrust coefficient C 5 .

Data Type: Real Number
Dependency: (None)

C6

Y

Y

N/kPa C 7

Thrust coefficient C 6 .

Data Type: Real Number
Dependency: (None)

C7

Y

Y

(None)

Thrust coefficient C 7 .

Data Type: Real Number
Dependency: (None)

C8

Y

Y

N/kPa C 9

Thrust coefficient C 8 .

Data Type: Real Number
Dependency: (None)

C9

Y

Y

(None)

Thrust coefficient C 9 .

Data Type: Real Number
Dependency: (None)

C10

Y

Y

N/kPa C 11

Thrust coefficient C 10 .

Data Type: Real Number
Dependency: (None)

C11

Y

Y

(None)

Thrust coefficient C 11 .

Data Type: Real Number
Dependency: (None)

C12

Y

Y

N

Thrust coefficient C 12 .

Data Type: Real Number
Dependency: (None)

C13

Y

Y

(None)

Thrust coefficient C 13 .

Data Type: Real Number
Dependency: (None)

C14

Y

Y

1/kPa

Thrust coefficient C 14 .

Data Type: Real Number
Dependency: (None)

C15

Y

Y

(None)

Thrust coefficient C 15 .

Data Type: Real Number
Dependency: (None)

C16

Y

Y

1/kPa

Thrust coefficient C 16 .

Data Type: Real Number
Dependency: (None)

K1

Y

Y

s

I sp coefficient K 1 .

Data Type: Real Number
Dependency: (None)

K2

Y

Y

s/kPa

I sp coefficient K 2 .

Data Type: Real Number
Dependency: (None)

K3

Y

Y

s

I sp coefficient K 3 .

Data Type: Real Number
Dependency: (None)

K4

Y

Y

s/kPa

I sp coefficient K 4 .

Data Type: Real Number
Dependency: (None)

K5

Y

Y

s/kPa 2

I sp coefficient K 5 .

Data Type: Real Number
Dependency: (None)

K6

Y

Y

s/kPa C 7

I sp coefficient K 6 .

Data Type: Real Number
Dependency: (None)

K7

Y

Y

(None)

I sp coefficient K 7 .

Data Type: Real Number
Dependency: (None)

K8

Y

Y

s/kPa C 9

I sp coefficient K 8 .

Data Type: Real Number
Dependency: (None)

K9

Y

Y

(None)

I sp coefficient K 9 .

Data Type: Real Number
Dependency: (None)

K10

Y

Y

s/kPa C 11

I sp coefficient K 10 .

Data Type: Real Number
Dependency: (None)

K11

Y

Y

(None)

I sp coefficient K 11 .

Data Type: Real Number
Dependency: (None)

K12

Y

Y

s

I sp coefficient K 12 .

Data Type: Real Number
Dependency: (None)

K13

Y

Y

(None)

I sp coefficient K 13 .

Data Type: Real Number
Dependency: (None)

K14

Y

Y

1/kPa

I sp coefficient K 14 .

Data Type: Real Number
Dependency: (None)

K15

Y

Y

(None)

I sp coefficient K 15 .

Data Type: Real Number
Dependency: (None)

K16

Y

Y

1/kPa

I sp coefficient K 16 .

Data Type: Real Number
Dependency: (None)

ThrustDirection1

Y

Y

(None)

ThrustDirection1, divided by the RSS of the three direction components, forms the x   component of the spacecraft thrust vector direction.

Data Type: Real Number
Dependency: (None)

ThrustDirection2

Y

Y

(None)

ThrustDirection2, divided by the RSS of the three direction components, forms the   y   component of the spacecraft thrust vector direction.

Data Type: Real Number
Dependency: (None)

ThrustDirection3

Y

Y

(None)

ThrustDirection3, divided by the RSS of the three direction components, forms the   z   component of the spacecraft thrust vector direction.

Data Type: Real Number
Dependency: (None)

ImpulsiveBurn

Parameter

C:\attach_075809f41a1cb53fad376b7098fec03b

C:\attach_95dc371c23f9ef4eabfae3c50265c5c6

Units

Description

Element1

Y

Y

(None)

X-component of the applied impulsive burn (delta-V).

Data Type: Real Number
Dependency: (None)

Element2

Y

Y

(None)

Y-component of the applied impulsive burn (delta-V).

Data Type: Real Number
Dependency: (None)

Element3

Y

Y

(None)

Z-component of the applied impulsive burn (delta-V).

Data Type: Real Number
Dependency: (None)

V

Y

Y

(None)

Deprecated. Velocity component of the applied impulsive burn (delta-V).

Data Type: Real Number
Dependency: (None)

N

Y

Y

(None)

Deprecated. Normal component of the applied impulsive burn (delta-V).

Data Type: Real Number
Dependency: (None)

B

Y

Y

(None)

Deprecated. Binormal component of the applied impulsive burn (delta-V).

Data Type: Real Number
Dependency: (None)

Array, String, Variable

Array, String, and Variable resources are themselves parameters, and can be used as any other parameter would. All of these are writable parameters, though only Variable resources and individual elements of Array resources can be plotted.

Examples  

Using parameters in the Mission Sequence:

Create Spacecraft aSat

Create Propagator aProp

Create ReportFile aReport

 

BeginMissionSequence

 

% propagate for 100 steps

For i=1:100

              Propagate aProp(aSat)

              % write four parameters (one standalone, three coordinate-system-dependent) to a file

              Report aReport aSat.TAIGregorian aSat.EarthFixed.X aSat.EarthFixed.Y aSat.EarthFixed.Z

EndFor

Using parameters as plot data:

Create Spacecraft aSat

Create Propagator aProp

 

Create XYPlot aPlot

aPlot.XVariable = aSat.TAIModJulian

aPlot.YVariables = {aSat.Earth.Altitude, aSat.Earth.ECC}

 

BeginMissionSequence

 

% propagate for 100 steps

For i=1:100

              Propagate aProp(aSat)

EndFor

Using parameters as stopping conditions:

Create Spacecraft aSat

aSat.SMA = 6678

 

Create ForceModel anFM

anFM.Drag.AtmosphereModel = MSISE90

 

Create Propagator aProp

aProp.FM = anFM

 

BeginMissionSequence

 

Propagate aProp(aSat) {aSat.Earth.Altitude = 100, aSat.ElapsedDays = 365}

 

Test Procedures

I generated truth data using STK 9 through the STK Object Model. These scripts are located in   extern\Resources\FRR-38_CalculationParameters\stk . I matched data between the two tools as follows:

  1. Central-body physical properties (mu, radii) are configured in the STK .cb files in the scenario directory, based on default GMAT data.
  2. I used EOP data for GMAT and STK from 2012-10-30. I had to replace the default application-wide data for each tool.  
  3. Some mu values are hard-coded in the GMAT and STK scripts. These are all set to the GMAT default mu values.

The following table lists all available parameters and where each is tested (if at all). Calculation tests are tests that perform some calculation that affects the parameter. Read tests check that the parameter can be read in a script. Write tests check that the parameter can be assigned to in the Mission Sequence.

If a script name appears in a column, the parameter is tested as a part of the Calculation Parameters tests (specifically in the named script). If another requirement appears, then the parameter is being tested as a part of the test suite for that requirement. If (N/A) appears, that test type does not apply to the parameter. A ( (error) ) indicates that the parameter is not currently being tested, and that it should be tested as a part of the Calculation Parameters tests unless another requirement is listed afterwards.

There is an assumption being made that the ability to plot plottable parameters is being tested as part of XYPlot QA.

Even if a parameter has a test name listed, it needs work until the following are true:

  • central-body parameters are tested using:
    • central body of the Spacecraft CoordinateSystem
    • another planet (Venus or Earth)
    • Luna (or another planet)
    • user-defined body (UserMars or UserSaturn)  
  • coordinate-system parameters are tested using:
    • Spacecraft CoordinateSystem
    • EarthMJ2000Eq (or Venus)
    • EarthFixed
    • user-created body-fixed (central body of the Spacecraft CoordinateSystem or Saturn)

All tests that need work by any of the above criteria are highlighted red in the table. Finished tests are highlighted green.

Parameter

Calculation Tests

Read Tests

Write Tests

ElapsedSecs

SpacecraftElapsedTimeParams

SpacecraftElapsedTimeParams

(N/A)

ElapsedDays

SpacecraftElapsedTimeParams

SpacecraftElapsedTimeParams

(N/A)

A1ModJulian

FRR-2

FRR-2

FRR-2

A1Gregorian

FRR-2

FRR-2

FRR-2

TAIModJulian

FRR-2

FRR-2

FRR-2

TAIGregorian

FRR-2

FRR-2

FRR-2

TTModJulian

FRR-2

FRR-2

FRR-2

TTGregorian

FRR-2

FRR-2

FRR-2

TDBModJulian

FRR-2

FRR-2

FRR-2

TDBGregorian

FRR-2

FRR-2

FRR-2

UTCModJulian

FRR-2

FRR-2

FRR-2

UTCGregorian

FRR-2

FRR-2

FRR-2

CurrA1MJD

FRR-2

FRR-2

FRR-2

X

FRR-1

FRR-1

FRR-1

Y

FRR-1

FRR-1

FRR-1

Z

FRR-1

FRR-1

FRR-1

VX

FRR-1

FRR-1

FRR-1

VY

FRR-1

FRR-1

FRR-1

VZ

FRR-1

FRR-1

FRR-1

SMA

FRR-1

FRR-1

FRR-1

ECC

FRR-1

FRR-1

FRR-1

INC

FRR-1

FRR-1

FRR-1

RAAN

FRR-1

FRR-1

FRR-1

AOP

FRR-1

FRR-1

FRR-1

TA

FRR-1

FRR-1

FRR-1

MA

CbParams_*_2Body_*
CbParams_GEO_*

CbParams_*_2Body_*
CbParams_GEO_*

(N/A)

EA

CbParams_*_2Body_*
CbParams_GEO_*
CBParams_Earth_EA

CbParams_*_2Body_*
CbParams_GEO_*

CBParams_Earth_EA

(N/A)

HA

CbParams_*_2Body_*
CbParams_GEO_*

HyperbolicAnomaly_Valid

CbParams_*_2Body_*
CbParams_GEO_*

HyperbolicAnomaly_Valid

(N/A)

MM

CBParams_Earth_MM
CbParams_*_2Body_*
CbParams_GEO_*

CBParams_Earth_MM
CbParams_*_2Body_*
CbParams_GEO_*

(N/A)

VelApoapsis

CbParams_*_2Body_*
CbParams_GEO_*

CBParams_Earth_VelApoapsis

CbParams_*_2Body_*
CbParams_GEO_*

CBParams_Earth_VelApoapsis

(N/A)

VelPeriapsis

CbParams_*_2Body_*
CbParams_GEO_*

CBParams_Earth_VelPeriapsis

CbParams_*_2Body_*
CbParams_GEO_*

CBParams_Earth_VelPeriapsis

(N/A)

Apoapsis

FRC-10

FRC-10

(N/A)

Periapsis

FRC-10

FRC-10

(N/A)

OrbitPeriod

CbParams_*_2Body_*
CbParams_GEO_*

CbParams_*_2Body_*
CbParams_GEO_*

(N/A)

RadApo

FRR-1

FRR-1

FRR-1

RadPer

FRR-1

FRR-1

FRR-1

C3Energy

CbParams_*_2Body_*
CbParams_GEO_*

CbParams_*_2Body_*
CbParams_GEO_*

(N/A)

Energy

CBParams_Earth_OrbitEnergy
CbParams_*_2Body_*
CbParams_GEO_*

CBParams_Earth_OrbitEnergy

CbParams_*_2Body_*
CbParams_GEO_*

(N/A)

RMAG

FRR-1

FRR-1

FRR-1

RA

FRR-1

FRR-1

FRR-1

DEC

FRR-1

FRR-1

FRR-1

VMAG

FRR-1

FRR-1

FRR-1

RAV

FRR-1

FRR-1

FRR-1

DECV

FRR-1

FRR-1

FRR-1

AZI

FRR-1

FRR-1

FRR-1

FPA

FRR-1

FRR-1

FRR-1

SemilatusRectum

CbParams_*_2Body_*
CbParams_GEO_*

CBParams_Earth_SemiLatusRectum

CbPa rams_*_2Body_*
CbParams_GEO_*

CBParams_Earth_SemiLatusRectum

(N/A)

HMAG

CbParams_*_2Body_*
CbParams_GEO_*

CbParams_*_2Body_*
CbParams_GEO_*

(N/A)

HX

CSParams_*_2Body
CSParams_*_2Body_*

CSParams_*_2Body
CSParams_*_2Body_*

(N/A)

HY

CSParams_*_2Body
CSParams_*_2Body_*

CSParams_*_2Body
CSParams_*_2Body_*

(N/A)

HZ

CSParams_*_2Body
CSParams_*_2Body_*

CSParams_*_2Body
CSParams_*_2Body_*

(N/A)

DLA

SelectedHyperbolicParams_*

SelectedHyperbolicParams_*

(N/A)

RLA

SelectedHyperbolicParams_*

SelectedHyperbolicParams_*

(N/A)

Altitude

CbParams_*_2Body_*
CbParams_GEO_*

CbParams_*_2Body_*
CbParams_GEO_*

(N/A)

MHA

CbParams_*_2Body_*
CbParams_GEO_*

CbParams_*_2Body_*
CbParams_GEO_*

(N/A)

Longitude

CbParams_*_2Body_*
CbParams_GEO_*

CbParams_*_2Body_*
CbParams_GEO_*

(N/A)

Latitude

CbParams_*_2Body_*
CbParams_GEO_*

CbParams_*_2Body_*
CbParams_GEO_*

(N/A)

LST

CbParams_*_2Body_*
CbParams_GEO_*

CbParams_*_2Body_*
CbParams_GEO_*

(N/A)

BetaAngle

CbParams_*_2Body_*
CbParams_GEO_*

CbParams_*_2Body_*
CbParams_GEO_*

(N/A)

BdotT

SelectedHyperbolicParams_*

SelectedHyperbolicParams_*

(N/A)

BdotR

SelectedHyperbolicParams_*

SelectedHyperbolicParams_*

(N/A)

BVectorMag

SelectedHyperbolicParams_*

SelectedHyperbolicParams_*

(N/A)

BVectorAngle

SelectedHyperbolicParams_*

SelectedHyperbolicParams_*

(N/A)

DCM11

FRR-3

FRR-3

(error) (FRR-3)

DCM12

FRR-3

FRR-3

(error) (FRR-3)

DCM13

FRR-3

FRR-3

(error) (FRR-3)

DCM21

FRR-3

FRR-3

(error) (FRR-3)

DCM22

FRR-3

FRR-3

(error) (FRR-3)

DCM23

FRR-3

FRR-3

(error) (FRR-3)

DCM31

FRR-3

FRR-3

(error) (FRR-3)

DCM32

FRR-3

FRR-3

(error) (FRR-3)

DCM33

FRR-3

FRR-3

(error) (FRR-3)

EulerAngle1

FRR-3

FRR-3

(error) (FRR-3)

EulerAngle2

FRR-3

FRR-3

(error) (FRR-3)

EulerAngle3

FRR-3

FRR-3

(error) (FRR-3)

MRP1

FRR-3

FRR-3

(error) (FRR-3)

MRP2

FRR-3

FRR-3

(error) (FRR-3)

MRP3

FRR-3

FRR-3

(error) (FRR-3)

Q1

FRR-3

FRR-3

(N/A)

Q2

FRR-3

FRR-3

(N/A)

Q3

FRR-3

FRR-3

(N/A)

Q4

FRR-3

FRR-3

(N/A)

Quaternion

(error) (FRR-3)

(error) (FRR-3)

(error) (FRR-3)

AngularVelocityX

FRR-3

FRR-3

(error) (FRR-3)

AngularVelocityY

FRR-3

FRR-3

(error) (FRR-3)

AngularVelocityZ

FRR-3

FRR-3

(error) (FRR-3)

EulerAngleRate1

FRR-3

FRR-3

(error) (FRR-3)

EulerAngleRate2

FRR-3

FRR-3

(error) (FRR-3)

EulerAngleRate3

FRR-3

FRR-3

(error) (FRR-3)

DryMass

(N/A)

SpacecraftPhysicalParams

SpacecraftPhysicalParams

Cd

(N/A)

SpacecraftPhysicalParams

SpacecraftPhysicalParams

Cr

(N/A)

SpacecraftPhysicalParams

SpacecraftPhysicalParams

DragArea

(N/A)

SpacecraftPhysicalParams

SpacecraftPhysicalParams

SRPArea

(N/A)

SpacecraftPhysicalParams

SpacecraftPhysicalParams

TotalMass

FRR-11
FRR-9

FRR-11
FRR-9

(N/A)

OrbitSTM

FRR-13

FRR-13

(N/A)

OrbitSTMA

Params_STMSubsets_*

Params_STMSubsets_*

(N/A)

OrbitSTMB

Params_STMSubsets_*

Params_STMSubsets_*

(N/A)

OrbitSTMC

Params_STMSubsets_*

Params_STMSubsets_*

(N/A)

OrbitSTMD

Params_STMSubsets_*

Params_STMSubsets_*

(N/A)

FuelTank.FuelMass

FRR-11
FRR-9

TankParams
ReportSatHardware

ReportSatHardware

FuelTank.Volume

(error) (FRR-8)

TankParams
ReportSatHardware

ReportSatHardware

FuelTank.FuelDensity

(N/A)

TankParams
ReportSatHardware

ReportSatHardware

FuelTank.Pressure

(error) (FRR-8)

TankParams
ReportSatHardware

ReportSatHardware

FuelTank.Temperature

(N/A)

TankParams
ReportSatHardware

ReportSatHardware

FuelTank.RefTemperature

(N/A)

TankParams
ReportSatHardware

ReportSatHardware

Thruster.DutyCycle

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.ThrustScaleFactor

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.GravitationalAccel

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.C1

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.C2

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.C3

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.C4

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.C5

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.C6

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.C7

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.C8

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.C9

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.C10

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.C11

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.C12

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.C13

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.C14

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.C15

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.C16

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.K1

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.K2

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.K3

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.K4

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.K5

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.K6

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.K7

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.K8

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.K9

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.K10

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.K11

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.K12

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.K13

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.K14

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.K15

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.K16

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.ThrustDirection1

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.ThrustDirection2

(N/A)

ReportSatHardware

ReportSatHardware

Thruster.ThrustDirection3

(N/A)

ReportSatHardware

ReportSatHardware

ImpulsiveBurn.Element1

(N/A)

ImpulsiveBurnParams_VNB_Elements

ImpulsiveBurnParams_VNB_Elements

ImpulsiveBurn.Element2

(N/A)

ImpulsiveBurnParams_VNB_Elements

ImpulsiveBurnParams_VNB_Elements

ImpulsiveBurn.Element3

(N/A)

ImpulsiveBurnParams_VNB_Elements

ImpulsiveBurnParams_VNB_Elements

ImpulsiveBurn.V

(N/A)

ImpulsiveBurnParams_VNB_VNBComponents

ImpulsiveBurnParams_VNB_VNBComponents

ImpulsiveBurn.N

(N/A)

ImpulsiveBurnParams_VNB_VNBComponents

ImpulsiveBurnParams_VNB_VNBComponents

ImpulsiveBurn.B

(N/A)

ImpulsiveBurnParams_VNB_VNBComponents

ImpulsiveBurnParams_VNB_VNBComponents

Edge/Corner/Stress

Priority

Status

Summary

 

 

Test parameters after setting epoch manually, instead of through propagation.

 

 

 

 

 

 

  Unique Validation

Priority

Status

Summary

 

(tick)

Set non-settable params

 

(tick)

Set param w/ dependency

 

(tick)

Read w/ incorrect dependency type

 

(tick)

Set w/ incorrect data type

 

(tick)

Set/get w/ incorrect parent (attached hardware)

 

(tick)

Set/get w/ incorrect resource type

 

(tick)

Plot non-plottable params

Unique Mode Tests

Priority

Status

Summary

 

 

 

 

 

 

 

 

 

Unique GUI Tests  

These are tests that are unique to the GUI interface for this feature that are not covered by the standard GUI test template and procedures.

Priority

Status

Summary

 

 

 

 

 

 

 

 

 

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