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Parameter

Units

 Description

AccelerationNYkm/s^2

The total acceleration with respect to the inertial system.

Data Type: Real Number

Dependency: ForceModel.

AccelerationXNYkm/s^2

The x-component of acceleration with respect to the inertial system.

Data Type: Real Number

Dependency: ForceModel.

AccelerationYNYkm/s^2

The y-component of acceleration with respect to the inertial system.

Data Type: Real Number

Dependency: ForceModel.

AccelerationXNYkm/s^2

The z-component of acceleration with respect to the inertial system.

Data Type: Real Number

Dependency: ForceModel.

AtmosDensityNYkg/m^3km^3

The atmospheric density at the current spacecraft epoch and location. 

Data Type: Real Number

Dependency: ForceModel.

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

CurrA1MJDYYd

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 can only 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 can only 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 (km2/s2)

C3 (characteristic) energy.

Data Type: Real Number
Dependency: Central Body

Energy

N

Y

MJ/kg (km2/s2)

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°

EquinoctialH

Y

Y

N/A

Equinoctial H element.

Data Type: Real Number
Dependency: Coordinate System

EquinoctialK

Y

Y

N/A

Equinoctial K element.

Data Type: Real Number
Dependency: Coordinate System

EquinoctialP

Y

Y

N/A

Equinoctial P element.

Data Type: Real Number
Dependency: Coordinate System

EquinoctialQ

Y

Y

N/A

Equinoctial Q element.

Data Type: Real Number
Dependency: Coordinate System

MLONG

Y

Y

°

Mean longitude.

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

SemilatusRectum

N

Y

km

Semilatus rectum of the osculating orbit.

Data Type: Real Number
Dependency: Central Body

HMAG

N

Y

km2/s

Magnitude of the angular momentum vector.

Data Type: Real Number
Dependency: Central 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
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

°

Angle between celestial body's body-fixed and inertial axes. For Earth, this is the 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 of the spacecraft from the celestial body's inertial x-axis.

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. See the BdotR parameter for notes on this calculation.

Data Type: Real Number
Dependency: Coordinate System

BdotR

N

Y

km

B-plane B·R magnitude.

GMAT computes the B-plane coordinates in the coordinate system specified in the dependency. In many implementations, the B-plane coordinates are computed in a pseudo-rotating coordinate system where the ω×r term is not applied when transforming velocity vectors. GMAT does apply the ω×r term in the velocity transformation. When computing B-plane coordinates in inertial systems, this term is identically zero. For rotating systems such as the Sun-Earth body-body rotating system, the effect of including ω×r is small but noticeable when comparing results between systems. When the rotation of the selected coordinate system is "fast", the values may differ significantly.

Data Type: Real Number
Dependency: Coordinate System

BVectorMag

N

Y

km

B-plane B vector magnitude. See the BdotR parameter for notes on this calculation.

Data Type: Real Number
Dependency: Coordinate System

BVectorAngle

N

Y

°

B-plane angle between the B vector and the T unit vector. See the BdotR parameter for notes on this calculation.

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

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

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