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Known Bugs

 

JIRA ID Summary Recommendation 
GMT-585 Multiple redundant properties/fields for epoch 
GMT-1098 Tab key navigation fails 
GMT-1346 Add ability for user-defined parameters 
GMT-1439 Parameter design for multiple dependency 
GMT-1483 Ability to Calculate and Output Sun Vector to any point 
GMT-1899 Beta Angle is Off by about .003 degrees 
GMT-1933 Earth Fixed RA changed from 0-360 to -180-180 measurement 
GMT-2011 Larger angular momentum errors in 09/15 build 
GMT-2318 STM Parameters are wrong when using Coordinate System other than EarthMJ2000Eq 
GMT-2475 Provide a parameter to check convergence status of a VF13 optimizer 
GMT-2673 User Reported: Parameter Select Dialog Box Silently Changes User's Selected Object 
GMT-2755 ParameterCreateDialog does not close properly after adding string parameter on Mac 

 

Failing Tests

Failing tests listed as of 09/11/2012.

 

JIRA ID Test Summary Rec. 
 

CSParams_UserAsteroid_2Body_VenusFixed

  
 

CSParams_UserComet_2Body_VenusFixed

  
 

CSParams_UserMoon_2Body_VenusFixed

  
 

CSParams_UserPlanet_2Body_VenusFixed

  
 CSParams_Uranus1_2Body_UranusFixed  
 CSParams_Saturn1_2Body_SaturnFixed  
 CSParams_Pluto1_2Body_PlutoFixed  
 CSParams_Neptune1_2Body_NeptuneMJ2000Ec  
 CSParams_Neptune1_2Body_NeptuneFixed  
 CSParams_Hyperbolic_2Body  
 CSParams_GEO_2Body  

 

Other Findings

 

JIRA ID Summary Rec. 
 Inconsistent naming: RadApo/RadPer and VelApoapsis/RadPeriapsis 
 ParameterSelectDialog is badly named 
 ParameterSelectDialog string consistency issues 
 ParameterSelectDialog doesn't remove item from available list once chosen 

 

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 Rodriguez 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. Unlike resource fields, which can be set in the initialization portion of a script (or in the GUI's Resources tree),  parameters are derived properties that can only be used to get data, not store it. There is some overlap between the two categories, however: the ECC property of Spacecraft is both a field (i.e. settable during initialization) and a parameter (i.e. usable by Mission Sequence commands).

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 simple 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 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

ParameterUnits Description
ElapsedSecsNYs

Spacecraft

Data Type: Real Number
Dependency: None

ElapsedDaysNYd

Spacecraft

Data Type: Real Number
Dependency: None

A1ModJulianYYd

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

Data Type: Real Number
Dependency: None

A1GregorianYNN/A

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

Data Type: String
Dependency: None

TAIModJulianYYd

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

Data Type: Real Number
Dependency: None

TAIGregorianYNN/A

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

Data Type: String
Dependency: None

TTModJulianYYd

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

Data Type: Real Number
Dependency: None

TTGregorianYNN/A

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

Data Type: String
Dependency: None

TDBModJulianYYd

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

Data Type: Real Number
Dependency: None

TDBGregorianYNN/A

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

Data Type: String
Dependency: None

UTCModJulianYYd

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

Data Type: Real Number
Dependency: None

UTCGregorianYNN/A

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

Data Type: String
Dependency: None

XYYkm

Cartesian x-component of the spacecraft position.

Data Type: Real Number
Dependency: Coordinate System

YYYkm

Cartesian y-component of the spacecraft position.

Data Type: Real Number
Dependency: Coordinate System

ZYYkm

Cartesian z-component of the spacecraft position.

Data Type: Real Number
Dependency: Coordinate System

VXYYkm/s

Cartesian x-component of the spacecraft velocity.

Data Type: Real Number
Dependency: Coordinate System

VYYYkm/s

Cartesian y-component of the spacecraft velocity.

Data Type: Real Number
Dependency: Coordinate System

VZYYkm/s

Cartesian z-component of the spacecraft velocity.

Data Type: Real Number
Dependency: Coordinate System

SMAYYkm

Orbit semi-major axis.

Data Type: Real Number
Dependency: Celestial Body

ECCYYN/A

Orbit eccentricity.

Data Type: Real Number
Dependency: Celestial Body

INCYY°

Orbit inclination.

Data Type: Real Number
Dependency: Coordinate System

RAANYY°

Orbit right ascension of the ascending node.

Data Type: Real Number
Dependency: Coordinate System

AOPYY°

Orbit argument of periapsis.

Data Type: Real Number
Dependency: Coordinate System

TAYY°

True anomaly.

Data Type: Real Number
Dependency: Celestial Body

MAYY°

Mean anomaly.

Data Type: Real Number
Dependency: Celestial Body

EAYY°

Eccentric anomaly.

Data Type: Real Number
Dependency: Celestial Body

HAYY°

Hyperbolic anomaly.

Data Type: Real Number
Dependency: Celestial Body

MMNYrad/s

Mean motion.

Data Type: Real Number
Dependency: Celestial Body

VelApoapsisNYkm/s

Scalar velocity at apoapsis.

Data Type: Real Number
Dependency: Celestial Body

VelPeriapsisNYkm/s

Scalar velocity at periapsis.

Data Type: Real Number
Dependency: Celestial Body

ApoapsisNYN/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

PeriapsisNYN/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
OrbitPeriodNYs

Osculating orbit period.

Data Type: Real Number
Dependency: Celestial Body
RadApoYYkm

Radius of apoapsis.

Data Type: Real Number
Dependency: Celestial Body
RadPerYYkm

Radius of periapsis.

Data Type: Real Number
Dependency: Celestial Body
C3EnergyNYMJ/kg (km2/s2)

C3 (characteristic) energy.

Data Type: Real Number
Dependency: Celestial Body
EnergyNYMJ/kg (km2/s2)

Specific orbital energy.

Data Type: Real Number
Dependency: Celestial Body
RMAGYYkm

Magnitude of the orbital position vector.

Data Type: Real Number
Dependency: Celestial Body
RAYY°

Right ascension of the orbital position.

Data Type: Real Number
Dependency: Coordinate System
DECYY°

Declination of the orbital position.

Data Type: Real Number
Dependency: Coordinate System
VMAGYYkm/s

Magnitude of the orbital velocity vector.

Data Type: Real Number
Dependency: Coordinate System
RAVYY°

Right ascension of orbital velocity.

Data Type: Real Number
Dependency: Coordinate System
DECVYY°

Declination of orbital velocity.

Data Type: Real Number
Dependency: Coordinate System
AZIYY°

Orbital velocity azimuth.

Data Type: Real Number
Dependency: Coordinate System
FPAYY°

Orbital flight path angle.

Data Type: Real Number
Dependency: Coordinate System
SemilatusRectumNYkm

Semilatus rectum of the osculating orbit.

Data Type: Real Number
Dependency: Celestial Body
HMAGNYkm2/s

Magnitude of the angular momentum vector.

Data Type: Real Number
Dependency: Celestial Body
HXNYkm2/s

X component of the angular momentum vector.

Data Type: Real Number
Dependency: Coordinate System
HYNYkm2/s

Y component of the angular momentum vector.

Data Type: Real Number
Dependency: Coordinate System
HZNYkm2/s

Z component of the angular momentum vector.

Data Type: Real Number
Dependency: Coordinate System
DLANY°

Declination of the outgoing hyperbolic asymptote.

Data Type: Real Number
Dependency: Coordinate System
RLANY°

Right ascension of the outgoing hyperbolic asymptote.

Data Type: Real Number
Dependency: Coordinate System
AltitudeNYkm

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
MHANY°

Greenwich hour angle.

Data Type: Real Number
Dependency: Celestial Body
LongitudeNY°

Planetodetic longitude.

Data Type: Real Number
Dependency: Celestial Body
LatitudeNY°

Planetodetic latitude.

Data Type: Real Number
Dependency: Celestial Body
LSTNY°

Local sidereal time.

Data Type: Real Number
Dependency: Celestial Body
BetaAngleNY°

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
BdotTNYkm

B-plane B·T magnitude.

Data Type: Real Number
Dependency: Coordinate System
BdotRNYkm

B-plane B·R magnitude.

Data Type: Real Number
Dependency: Coordinate System
BVectorMagNYkm

B-plane B vector magnitude.

Data Type: Real Number
Dependency: Coordinate System
BVectorAngleNY°

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

Data Type: Real Number
Dependency: Coordinate System
DCM11YY(None)

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

Data Type: Real Number
Dependency: (None)
DCM12YY(None)

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

Data Type: Real Number
Dependency: (None)
DCM13YY(None)

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

Data Type: Real Number
Dependency: (None)
DCM21YY(None)

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

Data Type: Real Number
Dependency: (None)
DCM22YY(None)

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

Data Type: Real Number
Dependency: (None)
DCM23YY(None)

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

Data Type: Real Number
Dependency: (None)
DCM31YY(None)

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

Data Type: Real Number
Dependency: (None)
DCM32YY(None)

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

Data Type: Real Number
Dependency: (None)
DCM33YY(None)

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

Data Type: Real Number
Dependency: (None)
EulerAngle1YY°

Attitude Euler angle 1.

Data Type: Real Number
Dependency: (None)
EulerAngle2YY°

Attitude Euler angle 2.

Data Type: Real Number
Dependency: (None)
EulerAngle3YY°

Attitude Euler angle 3.

Data Type: Real Number
Dependency: (None)
MRP1YY 

Modified Rodriguez parameter 1.

Data Type: Real Number
Dependency: (None)
MRP2YY 

Modified Rodriguez parameter 2.

Data Type: Real Number
Dependency: (None)
MRP3YY 

Modified Rodriguez parameter 3.

Data Type:
Dependency:
Q1NY 

 

Data Type:
Dependency:
Q2NY 

 

Data Type:
Dependency:
Q3NY 

 

Data Type:
Dependency:
Q4NY 

 

Data Type:
Dependency:
QuaternionYN 

 

Data Type:
Dependency:
AngularVelocityX Y 

 

Data Type:
Dependency:
AngularVelocityY Y 

 

Data Type:
Dependency:
AngularVelocityZ Y 

 

Data Type:
Dependency:
EulerAngleRate1 Y 

 

Data Type:
Dependency:
EulerAngleRate2 Y 

 

Data Type:
Dependency:
EulerAngleRate3 Y 

 

Data Type:
Dependency:
DryMass Y 

 

Data Type:
Dependency:
Cd Y 

 

Data Type:
Dependency:
Cr Y 

 

Data Type:
Dependency:
DragArea Y 

 

Data Type:
Dependency:
SRPArea Y 

 

Data Type:
Dependency:
TotalMass Y 

 

Data Type:
Dependency:
OrbitSTM N 

 

Data Type:
Dependency:
OrbitSTMA N 

 

Data Type:
Dependency:
OrbitSTMB N 

 

Data Type:
Dependency:
OrbitSTMC N 

 

Data Type:
Dependency:
OrbitSTMD N 

 

Data Type:
Dependency:

ImpulsiveBurn

 

ParameterDescription
Element1ImpulsiveBurnYY
Element2ImpulsiveBurnYY
Element3ImpulsiveBurnYY
VImpulsiveBurnYY
NImpulsiveBurnYY
BImpulsiveBurnYY
  

FuelTank

ParameterDescription
FuelMassSpacecraftYY
VolumeSpacecraftYY
FuelDensitySpacecraftYY
PressureSpacecraftYY
TemperatureSpacecraftYY
RefTemperatureSpacecraftYY
DutyCycleSpacecraftYY
ThrustScaleFactorSpacecraftYY
GravitationalAccelSpacecraftYY
  
  

Thruster

ParameterDescription
C1SpacecraftYY
C2SpacecraftYY
C3SpacecraftYY
C4SpacecraftYY
C5SpacecraftYY
C6SpacecraftYY
C7SpacecraftYY
C8SpacecraftYY
C9SpacecraftYY
C10SpacecraftYY
C11SpacecraftYY
C12SpacecraftYY
C13SpacecraftYY
C14SpacecraftYY
C15SpacecraftYY
C16SpacecraftYY
K1SpacecraftYY
K2SpacecraftYY
K3SpacecraftYY
K4SpacecraftYY
K5SpacecraftYY
K6SpacecraftYY
K7SpacecraftYY
K8SpacecraftYY
K9SpacecraftYY
K10SpacecraftYY
K11SpacecraftYY
K12SpacecraftYY
K13SpacecraftYY
K14SpacecraftYY
K15SpacecraftYY
K16SpacecraftYY
ThrustDirection1SpacecraftYY
ThrustDirection2SpacecraftYY
ThrustDirection3SpacecraftYY


Examples 

Describe the example with a short sentence two and include minimal script for example below

Create Spacecraft aSat;
Create ForceModel aForceModel;
Create Propagator aProp;
aProp.FM              = aForceModel;
aProp.Type            = PrinceDormand78;
aProp.InitialStepSize   = 60;
aProp.Accuracy        = 1e-011;
aProp.MinStep         = 0;
aProp.MaxStep         = 86400;
aProp.MaxStepAttempts = 50;
aProp.StopIfAccuracyIsViolated = true;
 
BeginMissionSequence
 
Propagate aProp(aSat) {aSat.ElapsedDays = .2};

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

Describe existing test types using a row for each class of test.

 

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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