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Known Bugs

 

JIRA ID Summary Recommendation 
GMT-585 Multiple redundant properties/fields for epochP3
GMT-1098 Tab key navigation failsAppears fixed
GMT-1346 Add ability for user-defined parametersImprovement
GMT-1439 Parameter design for multiple dependencyImprovement
GMT-1483 Ability to Calculate and Output Sun Vector to any pointImprovement
GMT-1899 Beta Angle is Off by about .003 degreesP1
GMT-1933 Earth Fixed RA changed from 0-360 to -180-180 measurementP1 (document)
GMT-2011 Larger angular momentum errors in 09/15 buildP1, assign to Joel
GMT-2318 STM Parameters are wrong when using Coordinate System other than EarthMJ2000EqP1, assign to Joel
GMT-2475 Provide a parameter to check convergence status of a VF13 optimizerImprovement
GMT-2673 User Reported: Parameter Select Dialog Box Silently Changes User's Selected ObjectNeeds verification
GMT-2755 ParameterCreateDialog does not close properly after adding string parameter on MacP2

 

Failing Tests

Failing tests listed as of 10/15/2012.

 

JIRA ID Test Summary Rec. 
TBDCbParams_Hyperbolic_2BodyIncorrect MA, OrbitPeriodInvestigate
TBDCSParams_Uranus1_2Body_UranusFixedNumeric issuesInvestigate
TBDCSParams_Saturn1_2Body_SaturnFixedNumeric issuesInvestigate
TBDCSParams_Pluto1_2Body_PlutoFixedTest issues, plus numericsInvestigate
TBDCSParams_Neptune1_2Body_NeptuneMJ2000EcTest issues, plus many incorrect parametersInvestigate
TBDCSParams_Neptune1_2Body_NeptuneFixedNumeric issuesInvestigate
TBDCSParams_Hyperbolic_2BodyNumeric issuesInvestigate
TBDCSParams_GEO_2BodyNumeric issuesInvestigate

 

Other Findings

 

JIRA ID Summary Rec. 
GMT-3164Inconsistent naming: RadApo/RadPer and VelApoapsis/RadPeriapsisP3
GMT-3165ParameterSelectDialog is badly namedP2
GMT-3166ParameterSelectDialog string consistency issuesP3
GMT-3167ParameterSelectDialog doesn't remove item from available list once chosenP2

 

Requirements

 

ID Requirements 
FRR-38.1.0The system shall allow the user to calculate or set the following object properties with respect to any celestial body in FRR-16:
FRR-38.1.1.01)      Spacecraft and orbit parameters
FRR-38.1.1.11.   Altitude (read only)
FRR-38.1.1.22.   Beta angle (read only)
FRR-38.1.1.33.   C3 energy (read only)
FRR-38.1.1.44.   Eccentric anomaly (read/write)
FRR-38.1.1.55.   Eccentricity (read/write)
FRR-38.1.1.66.   Orbit energy (read only)
FRR-38.1.1.77.    Magnitude of angular momentum (read only)
FRR-38.1.1.88.    Latitude (read only)
FRR-38.1.1.89.    Longitude (read only)
FRR-38.1.1.1010.                     Local sidereal time (read only)
FRR-38.1.1.1111.                     Mean anomaly (read/write)
FRR-38.1.1.1212.                     Mean hour angle (read only)
FRR-38.1.1.1313.                     Mean motion (read only)
FRR-38.1.1.1414.                     Orbit period (read only)
FRR-38.1.1.1515.                     Radius of apogee (read/write)
FRR-38.1.1.1616.                     Radius of perigee (read/write)
FRR-38.1.1.1717.                     Magnitude of position vector (read only)
FRR-38.1.1.1818.                     Orbit semi-latus rectum (read only)
FRR-38.1.1.1919.                     Orbit semi major axis (read/write)
FRR-38.1.1.2020.                     True anomaly (read/write)
FRR-38.1.1.2121.                     Velocity at apoapsis (read only)
FRR-38.1.1.2222.                     Velocity at periapsis (read only)
FRR-38.2.0The system shall allow the user to calculate the following object properties with respect to any coordinate system in FR-xxx:
FRR-38.2.1.01)      Spacecraft and orbit parameters
FRR-38.2.1.11.   Argument of periapsis (read/write)
FRR-38.2.1.22.   Azimuth (read/write)
FRR-38.2.1.33.   B dot T (read only)
FRR-38.2.1.44.   B dot R (read only)
FRR-38.2.1.55.   B vector angle (read only)
FRR-38.2.1.66.   B vector magnitude (read only)
FRR-38.2.1.77.   Declination (read/write)
FRR-38.2.1.88.   Declination of velocity (read/write)
FRR-38.2.1.99.   Flight path angle (read/write)
FRR-38.2.1.1010.                     Hyperbolic anomaly (read/write)
FRR-38.2.1.1111.                     Orbit angular momentum components (read only)
FRR-38.2.1.1212.                     Orbit inclination (read/write)
FRR-38.2.1.1313.                     Orbits transition matrix (read only)
FRR-38.2.1.1414.                     3x3 partitions of Orbit STM (read only)
FRR-38.2.1.1515.                     Right ascension (read/write)
FRR-38.2.1.1616.                     Right ascension of the ascending node (read/write)
FRR-38.2.1.1717.                     Right ascension of velocity (read/write)
FRR-38.2.1.1818.                     Magnitude of velocity (read/write)
FRR-38.2.1.1919.                     Components of velocity (read/write)
FRR-38.2.1.2020.                     Components of position (read/write)
FRR-38.2.1.2121.                     Right Asencsion of Outgoing Aysptote (read/write)
FRR-38.2.1.2222.                     Declination of Outgoing Aysptote (read/write)
FRR-38.3.0The system shall allow the user to calculate the following object properties:
FRR-38.3.1.01)      Spacecraft and orbit parameters
FRR-38.3.1.33.   Spacecraft Angular velocity components (read/write)
FRR-38.3.1.44.   Drag coefficient (read/write)
FRR-38.3.1.55.   SRP coefficient (read/write)
FRR-38.3.1.66.   Direction cosine matrix components ( read/write)
FRR-38.3.1.77.   Drag area (read/write)
FRR-38.3.1.88.   Dry mass (read/write)
FRR-38.3.1.99.   Elapsed days (read only)
FRR-38.3.1.1010.                     Elapsed seconds (read only)
FRR-38.3.1.1111.                     Euler angles for any sequence (read/write)
FRR-38.3.1.1212.                     Euler angle rates for any sequence (read/write)
FRR-38.3.1.1313.                     Quaternion components (read/write)
FRR-38.3.1.1414.                     SRP area (read/write)
FRR-38.3.1.1515.                     Epoch in TAI modified Julian (read/write)
FRR-38.3.1.1616.                     Epoch in TAI Gregorian (read/write)
FRR-38.3.1.1919.                     Epoch in TDB modified Julian (read/write)
FRR-38.3.1.2020.                     Epoch in TDB Gregorian (read/write)
FRR-38.3.1.2121.                     Epoch in TT modified Julian (read/write)
FRR-38.3.1.2222.                     Epoch in TT Gregorian (read/write)
FRR-38.3.1.2323.                     Epoch in UTC modified Julian (read/write)
FRR-38.3.1.2424.                     Epoch in UTC Gregorian (read/write)
FRR-38.3.1.2525.                     Spacecraft total mass (read only)
FRR-38.3.1.2626.                     Modified Rodrigues parameters (read/write)
FRR-38.3.1.2727.                     Euler Angles (read/write)
FRR-38.3.1.2828.                     Euler Angle Rates (read/write)
FRR-38.3.2.02)      Impulsive burn parameters
FRR-38.3.2.11.   Element1 (read/write)
FRR-38.3.2.22.   Element2 (read/write)
FRR-38.3.2.33.   Element3 (read/write)
FRR-38.3.2.44.  Velocity component (read/write)
FRR-38.3.2.55.   Normal component (read/write)
FRR-38.3.2.66.   Binormal component (read/write)
FRR-38.3.3.03)      Tank Properties
FRR-38.3.3.11.   Pressure (read/write)
FRR-38.3.3.22.  Volume (read/write)
FRR-38.3.3.33.   Fuel Density (read/write)
FRR-38.3.3.44.   Fuel Mass (read/write)
FRR-38.3.3.55.   Temperature (read/write)
FRR-38.3.3.66.   RefTemperature (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 three types: central-body-dependent parameters, coordinate-system-dependent 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.

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.

The nuances of fields and parameters in GMAT are explored in more detail in the script language documentation, and the individual parameters are documented along with the resources 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

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:

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 right. 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 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.

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


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.


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

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

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: Celestial Body

ECC

Y

Y

N/A

Orbit eccentricity.

Data Type: Real Number
Dependency: Celestial Body

INC

Y

Y

°

Orbit inclination.

Data Type: Real Number
Dependency: Coordinate System

RAAN

Y

Y

°

Orbit right ascension of the ascending node.

Data Type: Real Number
Dependency: Coordinate System

AOP

Y

Y

°

Orbit argument of periapsis.

Data Type: Real Number
Dependency: Coordinate System

TA

Y

Y

°

True anomaly.

Data Type: Real Number
Dependency: Celestial Body

MA

Y

Y

°

Mean anomaly.

Data Type: Real Number
Dependency: Celestial Body

EA

Y

Y

°

Eccentric anomaly.

Data Type: Real Number
Dependency: Celestial Body

HA

Y

Y

°

Hyperbolic anomaly.

Data Type: Real Number
Dependency: Celestial Body

MM

N

Y

rad/s

Mean motion.

Data Type: Real Number
Dependency: Celestial Body

VelApoapsis

N

Y

km/s

Scalar velocity at apoapsis.

Data Type: Real Number
Dependency: Celestial Body

VelPeriapsis

N

Y

km/s

Scalar velocity at periapsis.

Data Type: Real Number
Dependency: Celestial 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: Celestial 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: Celestial Body

OrbitPeriod

N

Y

s

Osculating orbit period.

Data Type: Real Number

Dependency: Celestial Body

RadApo

Y

Y

km

Radius of apoapsis.

Data Type: Real Number

Dependency: Celestial Body

RadPer

Y

Y

km

Radius of periapsis.

Data Type: Real Number

Dependency: Celestial Body

C3Energy

N

Y

MJ/kg (km2/s2)

C3 (characteristic) energy.

Data Type: Real Number

Dependency: Celestial Body

Energy

N

Y

MJ/kg (km2/s2)

Specific orbital energy.

Data Type: Real Number

Dependency: Celestial Body

RMAG

Y

Y

km

Magnitude of the orbital position vector.

Data Type: Real Number

Dependency: Celestial Body

RA

Y

Y

°

Right ascension of the orbital position.

Data Type: Real Number

Dependency: Coordinate System

DEC

Y

Y

°

Declination of the orbital position.

Data Type: Real Number

Dependency: Coordinate System

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

DECV

Y

Y

°

Declination of orbital velocity.

Data Type: Real Number

Dependency: Coordinate System

AZI

Y

Y

°

Orbital velocity azimuth.

Data Type: Real Number

Dependency: Coordinate System

FPA

Y

Y

°

Orbital flight path angle.

Data Type: Real Number

Dependency: Coordinate System

SemilatusRectum

N

Y

km

Semilatus rectum of the osculating orbit.

Data Type: Real Number

Dependency: Celestial Body

HMAG

N

Y

km2/s

Magnitude of the angular momentum vector.

Data Type: Real Number

Dependency: Celestial Body

HX

N

Y

km2/s

X component of the angular momentum vector.

Data Type: Real Number

Dependency: Coordinate System

HY

N

Y

km2/s

Y component of the angular momentum vector.

Data Type: Real Number

Dependency: Coordinate System

HZ

N

Y

km2/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

RLA

N

Y

°

Right ascension of the outgoing hyperbolic asymptote.

Data Type: Real Number

Dependency: Coordinate System

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: Celestial Body

MHA

N

Y

°

Greenwich hour angle.

Data Type: Real Number

Dependency: Celestial Body

Longitude

N

Y

°

Planetodetic longitude.

Data Type: Real Number

Dependency: Celestial Body

Latitude

N

Y

°

Planetodetic latitude.

Data Type: Real Number

Dependency: Celestial Body

LST

N

Y

°

Local sidereal time.

Data Type: Real Number

Dependency: Celestial Body

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: Celestial Body

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

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)

EulerAngle2

Y

Y

°

Attitude Euler angle 2.

Data Type: Real Number

Dependency: (None)

EulerAngle3

Y

Y

°

Attitude Euler angle 3.

Data Type: Real Number

Dependency: (None)

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

m2

Area used to compute acceleration due to atmospheric drag.

Data Type: Real Number

Dependency: (None)

SRPArea

Y

Y

m2

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

Units

 Description

FuelMass

Y

Y

kg

Mass of fuel in the tank.

Data Type: Real Number

Dependency: (None)

Volume

Y

Y

m3

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/m3

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

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/s2

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

Data Type: Real Number
Dependency: (None)

C1

Y

Y

N

Thrust coefficient C1.

Data Type: Real Number
Dependency: (None)

C2

Y

Y

N/kPa

Thrust coefficient C2.

Data Type: Real Number
Dependency: (None)

C3

Y

Y

N

Thrust coefficient C3.

Data Type: Real Number
Dependency: (None)

C4

Y

Y

N/kPa

Thrust coefficient C4.

Data Type: Real Number
Dependency: (None)

C5

Y

Y

N/kPa2

Thrust coefficient C5.

Data Type: Real Number
Dependency: (None)

C6

Y

Y

N/kPaC7

Thrust coefficient C6.

Data Type: Real Number
Dependency: (None)

C7

Y

Y

(None)

Thrust coefficient C7.

Data Type: Real Number
Dependency: (None)

C8

Y

Y

N/kPaC9

Thrust coefficient C8.

Data Type: Real Number
Dependency: (None)

C9

Y

Y

(None)

Thrust coefficient C9.

Data Type: Real Number
Dependency: (None)

C10

Y

Y

N/kPaC11

Thrust coefficient C10.

Data Type: Real Number
Dependency: (None)

C11

Y

Y

(None)

Thrust coefficient C11.

Data Type: Real Number
Dependency: (None)

C12

Y

Y

N

Thrust coefficient C12.

Data Type: Real Number
Dependency: (None)

C13

Y

Y

(None)

Thrust coefficient C13.

Data Type: Real Number
Dependency: (None)

C14

Y

Y

1/kPa

Thrust coefficient C14.

Data Type: Real Number
Dependency: (None)

C15

Y

Y

(None)

Thrust coefficient C15.

Data Type: Real Number
Dependency: (None)

C16

Y

Y

1/kPa

Thrust coefficient C16.

Data Type: Real Number
Dependency: (None)

K1

Y

Y

s

Isp coefficient K1.

Data Type: Real Number
Dependency: (None)

K2

Y

Y

s/kPa

Isp coefficient K2.

Data Type: Real Number
Dependency: (None)

K3

Y

Y

s

Isp coefficient K3.

Data Type: Real Number
Dependency: (None)

K4

Y

Y

s/kPa

Isp coefficient K4.

Data Type: Real Number
Dependency: (None)

K5

Y

Y

s/kPa2

Isp coefficient K5.

Data Type: Real Number
Dependency: (None)

K6

Y

Y

s/kPaC7

Isp coefficient K6.

Data Type: Real Number
Dependency: (None)

K7

Y

Y

(None)

Isp coefficient K7.

Data Type: Real Number
Dependency: (None)

K8

Y

Y

s/kPaC9

Isp coefficient K8.

Data Type: Real Number
Dependency: (None)

K9

Y

Y

(None)

Isp coefficient K9.

Data Type: Real Number
Dependency: (None)

K10

Y

Y

s/kPaC11

Isp coefficient K10.

Data Type: Real Number
Dependency: (None)

K11

Y

Y

(None)

Isp coefficient K11.

Data Type: Real Number
Dependency: (None)

K12

Y

Y

s

Isp coefficient K12.

Data Type: Real Number
Dependency: (None)

K13

Y

Y

(None)

Isp coefficient K13.

Data Type: Real Number
Dependency: (None)

K14

Y

Y

1/kPa

Isp coefficient K14.

Data Type: Real Number
Dependency: (None)

K15

Y

Y

(None)

Isp coefficient K15.

Data Type: Real Number
Dependency: (None)

K16

Y

Y

1/kPa

Isp coefficient K16.

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

Units

Description

Element1

YY(None)

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

Data Type: Real Number
Dependency: (None)

Element2

YY(None)

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

Data Type: Real Number
Dependency: (None)

Element3

YY(None)

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

Data Type: Real Number
Dependency: (None)

V

YY(None)

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

Data Type: Real Number
Dependency: (None)

N

YY(None)

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

Data Type: Real Number
Dependency: (None)

B

YY(None)

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

Data Type: Real Number
Dependency: (None)

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

Assumptions 

If you are making assumptions about how tests will be performed or that other test areas will cover some of this functionality describe that here.

Existing Tests

The existing tests have very high tolerances across the board; this needs further investigation and data-matching.

PriorityStatusSummary
   
   
   

 

Recommended Additional Tests 

Nominal Tests

PriorityStatusSummary
  [for Resources only] Cloning the resource in the Mission Sequence, using all non-default values in all field configurations
   
   

 Edge/Corner/Stres

PriorityStatusSummary
   
   
   

 Unique Validation

PriorityStatusSummary
   
   
   

Unique Mode Tests

PriorityStatusSummary
   
   
   

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.

PriorityStatusSummary
   
   
   


The orbital argument of periapsis expressed in the coordinate system chosen in the CoordinateSystem field.

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