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 |
Requirements
ID | Requirements |
FRR-38.1.0 | The system shall allow the user to calculate or set the following object properties with respect to any celestial body in FRR-16: |
FRR-38.1.1.0 | 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. 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 apogee (read/write) |
FRR-38.1.1.16 | 16. Radius of perigee (read/write) |
FRR-38.1.1.17 | 17. Magnitude of position vector (read only) |
FRR-38.1.1.18 | 18. Orbit semi-latus rectum (read only) |
FRR-38.1.1.19 | 19. Orbit 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-38.2.0 | The system shall allow the user to calculate or set the following object properties with respect to any celestial body 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) |
FRR-38.2.1.10 | 10. Hyperbolic anomaly (read/write) |
FRR-38.2.1.11 | 11. Orbit angular momentum components (read only) |
FRR-38.2.1.12 | 12. Orbit inclination (read/write) |
FRR-38.2.1.13 | 13. Orbits 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 velocity (read/write) |
FRR-38.2.1.20 | 20. Components of position (read/write) |
FRR-38.2.1.21 | 21. Right Asencsion of Outgoing Aysptote (read/write) |
FRR-38.2.1.22 | 22. Declination of Outgoing Aysptote (read/write) |
FRR-38.3.0 | The system shall allow the user to calculate or set the following object properties: |
FRR-38.3.1.0 | 1) Spacecraft and orbit parameters |
FRR-38.3.1.3 | 3. Spacecraft Angular velocity components (read/write) |
FRR-38.3.1.4 | 4. Drag coefficient (read/write) |
FRR-38.3.1.5 | 5. SRP coefficient (read/write) |
FRR-38.3.1.6 | 6. Direction cosine matrix components ( 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) |
FRR-38.3.1.11 | 11. Euler angles for any sequence (read/write) |
FRR-38.3.1.12 | 12. Euler angle rates for any sequence (read/write) |
FRR-38.3.1.13 | 13. Quaternion components (read/write) |
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. Spacecraft 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-38.3.2.0 | 2) Impulsive burn parameters |
FRR-38.3.2.1 | 1. Element1 (read/write) |
FRR-38.3.2.2 | 2. Element2 (read/write) |
FRR-38.3.2.3 | 3. Element3 (read/write) |
FRR-38.3.2.4 | 4. Velocity component (read/write) |
FRR-38.3.2.5 | 5. Normal component (read/write) |
FRR-38.3.2.6 | 6. 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. 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. |
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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. |
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Spacecraft
Parameter | Units | Description | ||
ElapsedSecs | N | Y | s | Spacecraft Data Type: Real Number |
ElapsedDays | N | Y | d | Spacecraft Data Type: Real Number |
A1ModJulian | Y | Y | d | Spacecraft orbit epoch in the A.1 system and the Modified Julian format. Data Type: Real Number |
A1Gregorian | Y | N | N/A | Spacecraft orbit epoch in the A.1 system and the Gregorian format. Data Type: String |
TAIModJulian | Y | Y | d | Spacecraft orbit epoch in the TAI system and the Modified Julian format. Data Type: Real Number |
TAIGregorian | Y | N | N/A | The spacecraft orbit epoch in the TAI system and the Gregorian format. Data Type: String |
TTModJulian | Y | Y | d | The spacecraft orbit epoch in the TT system and the Modified Julian format. Data Type: Real Number |
TTGregorian | Y | N | N/A | Spacecraft orbit epoch in the TT system and the Gregorian format. Data Type: String |
TDBModJulian | Y | Y | d | Spacecraft orbit epoch in the TDB system and the Modified Julian format. Data Type: Real Number |
TDBGregorian | Y | N | N/A | Spacecraft orbit epoch in the TDB system and the Gregorian format. Data Type: String |
UTCModJulian | Y | Y | d | Spacecraft orbit epoch in the UTC system and the Modified Julian format. Data Type: Real Number |
UTCGregorian | Y | N | N/A | Spacecraft orbit epoch in the UTC system and the Gregorian format. Data Type: String |
X | Y | Y | km | Cartesian x-component of the spacecraft position. Data Type: Real Number |
Y | Y | Y | km | Cartesian y-component of the spacecraft position. Data Type: Real Number |
Z | Y | Y | km | Cartesian z-component of the spacecraft position. Data Type: Real Number |
VX | Y | Y | km/s | Cartesian x-component of the spacecraft velocity. Data Type: Real Number |
VY | Y | Y | km/s | Cartesian y-component of the spacecraft velocity. Data Type: Real Number |
VZ | Y | Y | km/s | Cartesian z-component of the spacecraft velocity. Data Type: Real Number |
SMA | Y | Y | km | Orbit semi-major axis. Data Type: Real Number |
ECC | Y | Y | N/A | Orbit eccentricity. Data Type: Real Number |
INC | Y | Y | ° | Orbit inclination. Data Type: Real Number |
RAAN | Y | Y | ° | Orbit right ascension of the ascending node. Data Type: Real Number |
AOP | Y | Y | ° | Orbit argument of periapsis. Data Type: Real Number |
TA | Y | Y | ° | True anomaly. Data Type: Real Number |
MA | Y | Y | ° | Mean anomaly. Data Type: Real Number |
EA | Y | Y | ° | Eccentric anomaly. Data Type: Real Number |
HA | Y | Y | ° | Hyperbolic anomaly. Data Type: Real Number |
MM | N | Y | rad/s | Mean motion. Data Type: Real Number |
VelApoapsis | N | Y | km/s | Scalar velocity at apoapsis. Data Type: Real Number |
VelPeriapsis | N | Y | km/s | Scalar velocity at periapsis. Data Type: Real Number |
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 |
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 (km^{2}/s^{2}) | C_{3} (characteristic) energy. Data Type: Real Number Dependency: Celestial Body |
Energy | N | Y | MJ/kg (km^{2}/s^{2}) | 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 |
DEC | Y | Y | ° | Declination of the orbital position. Data Type: Real Number |
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 |
DECV | Y | Y | ° | Declination of orbital velocity. Data Type: Real Number |
AZI | Y | Y | ° | Orbital velocity azimuth. Data Type: Real Number |
FPA | Y | Y | ° | Orbital flight path angle. Data Type: Real Number |
SemilatusRectum | N | Y | km | Semilatus rectum of the osculating orbit. Data Type: Real Number Dependency: Celestial Body |
HMAG | N | Y | km^{2}/s | Magnitude of the angular momentum vector. Data Type: Real Number Dependency: Celestial 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 |
RLA | N | Y | ° | Right ascension of the outgoing hyperbolic asymptote. Data Type: Real Number |
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 |
Longitude | N | Y | ° | Planetodetic longitude. Data Type: Real Number |
Latitude | N | Y | ° | Planetodetic latitude. Data Type: Real Number |
LST | N | Y | ° | Local sidereal time. Data Type: Real Number |
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 |
BdotT | N | Y | km | B-plane B·T magnitude. Data Type: Real Number |
BdotR | N | Y | km | B-plane B·R magnitude. Data Type: Real Number |
BVectorMag | N | Y | km | B-plane B vector magnitude. Data Type: Real Number |
BVectorAngle | N | Y | ° | B-plane angle between the B vector and the T unit vector. Data Type: Real Number |
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 |
EulerAngle2 | Y | Y | ° | Attitude Euler angle 2. Data Type: Real Number |
EulerAngle3 | Y | Y | ° | Attitude Euler angle 3. Data Type: Real Number |
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 | 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 | 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 |
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 |
GravitationalAccel | Y | Y | m/s^{2} | Value of the gravitational acceleration used for the FuelTank/Thruster calculations. Data Type: Real Number |
C1 | Y | Y | N | Thrust coefficient C_{1}. Data Type: Real Number |
C2 | Y | Y | N/kPa | Thrust coefficient C_{2}. Data Type: Real Number |
C3 | Y | Y | N | Thrust coefficient C_{3}. Data Type: Real Number |
C4 | Y | Y | N/kPa | Thrust coefficient C_{4}. Data Type: Real Number |
C5 | Y | Y | N/kPa^{2} | Thrust coefficient C_{5}. Data Type: Real Number |
C6 | Y | Y | N/kPa^{C7} | Thrust coefficient C_{6}. Data Type: Real Number |
C7 | Y | Y | (None) | Thrust coefficient C_{7}. Data Type: Real Number |
C8 | Y | Y | N/kPa^{C9} | Thrust coefficient C_{8}. Data Type: Real Number |
C9 | Y | Y | (None) | Thrust coefficient C_{9}. Data Type: Real Number |
C10 | Y | Y | N/kPa^{C11} | Thrust coefficient C_{10}. Data Type: Real Number |
C11 | Y | Y | (None) | Thrust coefficient C_{11}. Data Type: Real Number |
C12 | Y | Y | N | Thrust coefficient C_{12}. Data Type: Real Number |
C13 | Y | Y | (None) | Thrust coefficient C_{13}. Data Type: Real Number |
C14 | Y | Y | 1/kPa | Thrust coefficient C_{14}. Data Type: Real Number |
C15 | Y | Y | (None) | Thrust coefficient C_{15}. Data Type: Real Number |
C16 | Y | Y | 1/kPa | Thrust coefficient C_{16}. Data Type: Real Number |
K1 | Y | Y | s | I_{sp} coefficient K_{1}. Data Type: Real Number |
K2 | Y | Y | s/kPa | I_{sp} coefficient K_{2}. Data Type: Real Number |
K3 | Y | Y | s | I_{sp} coefficient K_{3}. Data Type: Real Number |
K4 | Y | Y | s/kPa | I_{sp} coefficient K_{4}. Data Type: Real Number |
K5 | Y | Y | s/kPa^{2} | I_{sp} coefficient K_{5}. Data Type: Real Number |
K6 | Y | Y | s/kPa^{C7} | I_{sp} coefficient K_{6}. Data Type: Real Number |
K7 | Y | Y | (None) | I_{sp} coefficient K_{7}. Data Type: Real Number |
K8 | Y | Y | s/kPa^{C9} | I_{sp} coefficient K_{8}. Data Type: Real Number |
K9 | Y | Y | (None) | I_{sp} coefficient K_{9}. Data Type: Real Number |
K10 | Y | Y | s/kPa^{C11} | I_{sp} coefficient K_{10}. Data Type: Real Number |
K11 | Y | Y | (None) | I_{sp} coefficient K_{11}. Data Type: Real Number |
K12 | Y | Y | s | I_{sp} coefficient K_{12}. Data Type: Real Number |
K13 | Y | Y | (None) | I_{sp} coefficient K_{13}. Data Type: Real Number |
K14 | Y | Y | 1/kPa | I_{sp} coefficient K_{14}. Data Type: Real Number |
K15 | Y | Y | (None) | I_{sp} coefficient K_{15}. Data Type: Real Number |
K16 | Y | Y | 1/kPa | I_{sp} coefficient K_{16}. Data Type: Real Number |
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 |
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 |
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 |
ImpulsiveBurn
Parameter | Units | Description | ||
Element1 | Y | Y | (None) | X-component of the applied impulsive burn (delta-V). Data Type: Real Number |
Element2 | Y | Y | (None) | Y-component of the applied impulsive burn (delta-V). Data Type: Real Number |
Element3 | Y | Y | (None) | Z-component of the applied impulsive burn (delta-V). Data Type: Real Number |
V | Y | Y | (None) | Deprecated. Velocity component of the applied impulsive burn (delta-V). Data Type: Real Number |
N | Y | Y | (None) | Deprecated. Normal component of the applied impulsive burn (delta-V). Data Type: Real Number |
B | Y | Y | (None) | Deprecated. Binormal component of the applied impulsive burn (delta-V). Data Type: Real Number |
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.
Priority | Status | Summary |
Recommended Additional Tests
Nominal Tests
Priority | Status | Summary |
[for Resources only] Cloning the resource in the Mission Sequence, using all non-default values in all field configurations | ||
Edge/Corner/Stres
Priority | Status | Summary |
Unique Validation
Priority | Status | Summary |
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 |
The orbital argument of periapsis expressed in the coordinate system chosen in the CoordinateSystem field.
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