## About Aerospace Coordinate Systems

### Fundamental Coordinate System Concepts

Coordinate systems allow you to keep track of an aircraft or spacecraft position and orientation in space. The Aerospace Blockset™ coordinate systems are based on these underlying concepts from geodesy, astronomy, and physics.

#### Definitions

The blockset uses *right-handed* (RH) *Cartesian*
coordinate systems. The right-hand rule establishes the
*x*-*y*-*z* sequence of
coordinate axes.

An *inertial frame* is a nonaccelerating motion reference frame. In an
inertial frame, Newton's second law holds: force = mass x acceleration. Loosely
speaking, acceleration is defined with respect to the distant cosmos, and an
inertial frame is often said to be nonaccelerated with respect to the fixed
stars. Because the Earth and stars move so slowly with respect to one another,
this assumption is a very accurate approximation.

Strictly defined, an inertial frame is a member of the set of all frames not accelerating
relative to one another. A noninertial frame is any frame accelerating relative
to an inertial frame. Its acceleration, in general, includes both translational
and rotational components, resulting in *pseudoforces*
(*pseudogravity,* as well as
*Coriolis* and *centrifugal
forces*).

The blockset models the Earth shape (the *geoid*) as an oblate spheroid,
a special type of ellipsoid with two longer axes equal (defining the
*equatorial plane*) and a third, slightly shorter
(*geopolar*) axis of symmetry. The equator is the
intersection of the equatorial plane and the Earth surface. The geographic poles
are the intersection of the Earth surface and the geopolar axis. In general, the
Earth geopolar and rotation axes are not identical.

Latitudes parallel the equator. Longitudes parallel the geopolar axis. The *zero
longitude* or *prime meridian* passes
through Greenwich, England.

#### Approximations

The blockset makes three standard approximations in defining coordinate systems relative to the Earth.

The Earth surface or geoid is an oblate spheroid, defined by its longer equatorial and shorter geopolar axes. In reality, the Earth is slightly deformed with respect to the standard geoid.

The Earth rotation axis and equatorial plane are perpendicular, so that the rotation and geopolar axes are identical. In reality, these axes are slightly misaligned, and the equatorial plane wobbles as the Earth rotates. This effect is negligible in most applications.

The only noninertial effect in Earth-fixed coordinates is due to the Earth rotation about its axis. This is a

*rotating, geocentric*system. The blockset ignores the Earth acceleration around the Sun, the Sun acceleration in the Galaxy, and the Galaxy acceleration through the cosmos. In most applications, only the Earth rotation matters.This approximation must be changed for spacecraft sent into deep space, such as outside the Earth-Moon system, and a heliocentric system is preferred.

#### Passive Transformations

All quaternions in Aerospace Blockset are passive transformations. In a passive transformation, the vector is unchanged and the coordinate system in which it is defined is rotated. For more information on transformations, see Active and passive transformations.

#### Motion with Respect to Other Planets

The blockset uses the standard WGS-84 geoid to model the Earth. You can change the equatorial axis length, the flattening, and the rotation rate.

You can represent the motion of spacecraft with respect to any celestial body that is well approximated by an oblate spheroid by changing the spheroid size, flattening, and rotation rate. If the celestial body is rotating westward (retrogradely), make the rotation rate negative.

### Coordinate Systems for Modeling

Modeling aircraft and spacecraft is simplest if you use a coordinate system fixed in the body itself. In the case of aircraft, the forward direction is modified by the presence of wind, and the craft motion through the air is not the same as its motion relative to the ground.

See Equations of Motion for further details on how the blockset implements body and wind coordinates.

### Body Coordinates

The noninertial body coordinate system is fixed in both origin and orientation to the moving craft. The craft is assumed to be rigid.

The orientation of the body coordinate axes is fixed in the shape of body.

The

*x*-axis points through the nose of the craft.The

*y*-axis points to the right of the*x*-axis (facing in the pilot's direction of view), perpendicular to the*x*-axis.The

*z*-axis points down through the bottom the craft, perpendicular to the*xy*plane and satisfying the RH rule.

#### Translational Degrees of Freedom

Translations are defined by moving along these axes by distances
*x*, *y*, and *z* from
the origin.

#### Rotational Degrees of Freedom

Rotations are defined by the Euler angles *P*,
*Q*, *R* or Φ, Θ, Ψ. They are:

P or Φ | Roll about the x-axis |

Q or Θ | Pitch about the y-axis |

R or Ψ | Yaw about the z-axis |

Unless otherwise specified, by default the software uses ZYX rotation order for Euler angles.

### Wind Coordinates

The noninertial wind coordinate system has its origin fixed in the rigid aircraft.
The coordinate system orientation is defined relative to the craft velocity ** V**.

The orientation of the wind coordinate axes is fixed by the velocity ** V**.

The

*x*-axis points in the direction of.*V*The

*y*-axis points to the right of the*x*-axis (facing in the direction of), perpendicular to the*V**x*-axis.The

*z*-axis points perpendicular to the*xy*plane in whatever way needed to satisfy the RH rule with respect to the*x*- and*y*-axes.

#### Translational Degrees of Freedom

Translations are defined by moving along these axes by distances
*x*, *y*, and *z* from
the origin.

#### Rotational Degrees of Freedom

Rotations are defined by the Euler angles Φ, γ, χ:

Φ | Bank angle about the x-axis |

γ | Flight path about the y-axis |

χ | Heading angle about the z-axis |

Unless otherwise specified, by default the software uses ZYX rotation order for Euler angles.

### Coordinate Systems for Navigation

Modeling aerospace trajectories requires positioning and orienting the aircraft or spacecraft with respect to the rotating Earth. Navigation coordinates are defined with respect to the center and surface of the Earth.

#### Geocentric and Geodetic Latitudes

The *geocentric latitude* λ on the Earth surface is defined by the angle
subtended by the radius vector from the Earth center to the surface point with
the equatorial plane.

The *geodetic latitude* µ on the Earth surface is defined by the angle
subtended by the surface normal vector n and the equatorial plane.

#### NED Coordinates

The north-east-down (NED) system is a noninertial system with its origin fixed at the aircraft or spacecraft center of gravity. Its axes are oriented along the geodetic directions defined by the Earth surface.

The

*x*-axis points north parallel to the geoid surface, in the polar direction.The

*y*-axis points east parallel to the geoid surface, along a latitude curve.The

*z*-axis points downward, toward the Earth surface, antiparallel to the surface outward normal.*n*Flying at a constant altitude means flying at a constant

*z*above the Earth surface.

#### ECI Coordinates

The Earth-centered inertial (ECI) system is non-rotating. For most applications, assume this frame to be inertial, although the equinox and equatorial plane move very slightly over time. The ECI system is considered to be truly inertial for high-precision orbit calculations when the equator and equinox are defined at a particular epoch (e.g. J2000). Aerospace functions and blocks that use a particular realization of the ECI coordinate system provide that information in their documentation. The ECI system origin is fixed at the center of the Earth (see figure).

The

*x*-axis points towards the vernal equinox (First Point of Aries ♈).The

*y*-axis points 90 degrees to the east of the*x*-axis in the equatorial plane.The

*z*-axis points northward along the Earth rotation axis.

**Earth-Centered Coordinates**

#### ECEF Coordinates

The Earth-center, Earth-fixed (ECEF) system is noninertial and rotates with the Earth. Its origin is fixed at the center of the Earth (see preceding figure).

The

*x*′-axis points towards the intersection of Earth equatorial plane and the Greenwich Meridian.The

*y*′-axis points 90 degrees to the east of the*x*’-axis in the equatorial plane.The

*z*′-axis points northward along the Earth rotation axis.

### Coordinate Systems for Display

Several display tools are available for use with the Aerospace Blockset product. Each has a specific coordinate system for rendering motion.

#### MATLAB Graphics Coordinates

See the Axes Appearance for more information about the MATLAB^{®} Graphics
coordinate axes.

MATLAB Graphics uses this default coordinate axis orientation:

The

*x*-axis points out of the screen.The

*y*-axis points to the right.The

*z*-axis points up.

#### FlightGear Coordinates

FlightGear is an open-source, third-party flight simulator with an interface supported by the blockset.

Work with the Flight Simulator Interface discusses the blockset interface to FlightGear.

See the FlightGear documentation at

`www.flightgear.org`

for complete information about this flight simulator.

The FlightGear coordinates form a special body-fixed system,
rotated from the standard body coordinate system about the *y*-axis
by -180 degrees:

The

*x*-axis is positive toward the back of the vehicle.The

*y*-axis is positive toward the right of the vehicle.The

*z*-axis is positive upward, e.g., wheels typically have the lowest*z*values.

#### AC3D Coordinates

AC3D is a low-cost, widely used, geometry editor available from
`https://www.inivis.com`

. Its body-fixed coordinates are
formed by inverting the three standard body coordinate axes:

The

*x*-axis is positive toward the back of the vehicle.The

*y*-axis is positive upward, e.g., wheels typically have the lowest*y*values.The

*z*-axis is positive to the left of the vehicle.

## References

[1] *Recommended
Practice for Atmospheric and Space Flight Vehicle Coordinate
Systems*, R-004-1992, ANSI/AIAA, February 1992.

[2] Rogers, R. M.,
*Applied Mathematics in Integrated Navigation Systems,* AIAA,
Reston, Virginia, 2000.

[3] Sobel, D.,
*Longitude*, Walker & Company, New York,
1995.

[4] Stevens, B. L., and F. L.
Lewis, *Aircraft Control and Simulation,* 2nd ed.,
*Aircraft Control and Simulation,* Wiley-Interscience, New
York, 2003.

[5] Thomson, W. T.,
*Introduction to Space Dynamics,* John Wiley & Sons, New
York, 1961/Dover Publications, Mineola, New York, 1986.