version: "1.0.1" name: matlab-compute-aerospace-environment description: > Compute aerospace environment properties including atmosphere (ISA, COESA, NRLMSISE-00, non-standard, CIRA), gravity (spherical harmonic, WGS84, zonal, centrifugal), horizontal wind (HWM), magnetic field (WMM, IGRF), geoid height, geocentric radius, space weather data, planetary ephemeris, Earth orientation (polar motion, nutation, delta-UT1, CIP). Use when computing atmospheric density, temperature, pressure, gravity vectors, wind profiles, magnetic field components, geoid undulation, solar flux indices, planet positions, or Earth orientation parameters for aerospace vehicle analysis, spacecraft environment modeling, or navigation corrections. license: https://www.mathworks.com/content/dam/mathworks/license/pmrl/license.md metadata: author: MathWorks version: "1.1"

Compute Aerospace Environment

Calculate environment properties for aerospace vehicle analysis: atmosphere, gravity, wind, magnetic field, geoid, space weather, planetary ephemeris, and Earth orientation using Aerospace Toolbox functions.

When to Use

• Computing atmospheric properties (temperature, pressure, density, speed of sound)
• Calculating gravity vectors or acceleration for any planet
• Modeling horizontal wind at altitude
• Getting magnetic field components for navigation or compass correction
• Computing geoid height or geocentric radius
• Reading space weather data for NRLMSISE-00 inputs
• Computing planet or Moon positions (ephemeris)
• Getting Earth orientation parameters (polar motion, nutation, UT1-UTC, CIP)
• Any prompt mentioning: atmosphere model, ISA, COESA, NRLMSISE, pressure, temperature, density, speed of sound, gravity model, WGS84, wind model, HWM, magnetic model, WMM, IGRF, geoid, space weather, solar flux, F10.7, Ap index, planet ephemeris, Moon position, Earth nutation, polar motion, UT1, IERS

When NOT to Use

• Coordinate frame conversions or rotations — use matlab-convert-aerospace-coordinates
• Orbital mechanics or trajectory propagation (use ephemeris for positions, not orbit propagation)
• Aerodynamic coefficient calculations
• Simulink environment model blocks — use Aerospace Blockset

Workflow

1. Identify the quantity needed — use the decision table below
2. Call the function — follow the patterns in this skill for correct syntax
3. Verify results — check units and magnitude are physically reasonable

Decision Table

Patterns

Standard and COESA Atmosphere

% International Standard Atmosphere
[T, a, P, rho] = atmosisa(1000);
 
% 1976 COESA (valid 0-1000 km)
[T, a, P, rho] = atmoscoesa(1000);

Pressure Altitude (atmospalt)

Converts pressure (Pa) to altitude (m) using the International Standard Atmosphere.

% Pressure altitude at standard sea-level pressure
alt = atmospalt(101325);  % returns 0 m
 
% Pressure altitude at multiple pressures
alt = atmospalt([101325, 79501, 54048, 26500]);
 
% Typical use: convert measured pressure to altitude
measuredPressure_Pa = 75000;
pressureAltitude_m = atmospalt(measuredPressure_Pa);

Input: pressure in Pascals. Output: geometric altitude in meters based on 1976 COESA.

Non-Standard Atmosphere (atmosnonstd)

Uses positional string arguments — not name-value pairs.

Profile type (single altitude extreme):

[T, a, P, rho] = atmosnonstd(height, 'Profile', extremeParam, frequency, extremeAltitude)

Envelope type (altitude range extreme — NO extremeAltitude argument):

[T, a, P, rho] = atmosnonstd(height, 'Envelope', extremeParam, frequency)

Optional trailing args: action ('Warning'|'Error'|'None'), specification ('310'|'210c').

% Profile: high density, 1% of time, at 5 km altitude (extremeAltitude is NUMERIC)
[T, a, P, rho] = atmosnonstd(5000, 'Profile', 'High density', '1%', 5);
 
% Envelope: high pressure, 20% of time, MIL-STD-210C
[T, a, P, rho] = atmosnonstd([1000; 11000; 20000], 'Envelope', ...
    'High pressure', '20%', 'None', '210c');

Valid extremeParam: 'High temperature', 'Low temperature', 'High density', 'Low density', 'High pressure', 'Low pressure'

Valid frequency: 'Extreme values', '1%', '5%', '10%', '20%'

Valid extremeAltitude (Profile only, numeric): 5, 10, 20, 30, 40

CIRA 1986 Model

% By geopotential height, monthly mean, October
[T, P, zonalWind] = atmoscira(45, 'GPHeight', 20000, 'Monthly', 10);
 
% By pressure level
[T, alt, zonalWind] = atmoscira(45, 'Pressure', 101300, 'Monthly', 1);

Arguments: (latitude, ctype, coord, mtype, month) where ctype is 'Pressure' or 'GPHeight'.

NRLMSISE-00

% Basic call (uses default flux values)
[T, rho] = atmosnrlmsise00(altitude, latitude, longitude, year, dayOfYear, UTseconds);
 
% With flux data and no anomalous oxygen
[T, rho] = atmosnrlmsise00(altitude, lat, lon, year, dayOfYear, UTsec, ...
    f107Average, f107Daily, magneticIndex, 'NoOxygen');

Output: T is N-by-2 [exospheric temp, local temp]. rho is N-by-9 (densities).

Lapse Rate Atmosphere (atmoslapse)

Requires 10 positional arguments — not just altitude. All physical parameters must be specified explicitly.

% TEMPLATE — not executable (shows calling convention)
[T, a, P, rho] = atmoslapse(altitude, g, gamma, R, lapseRate, ...
    heightTroposphere, heightTropopause, density0, pressure0, temperature0);
 
% Example: ISA conditions
[T, a, P, rho] = atmoslapse([0 5000 11000 20000], ...
    9.80665, 1.4, 287.0531, 0.0065, 11000, 20000, 1.225, 101325, 288.15);

Arguments: (height, g, heatRatio, gasConstant, lapseRate, hTroposphere, hTropopause, rho0, P0, T0). Use for custom planetary atmospheres or non-standard sea-level conditions.

Horizontal Wind Model (atmoshwm)

Uses name-value arguments. Returns M-by-2 array [meridional, zonal] in m/s.

% Total wind with Ap index
wind = atmoshwm(-45, -85, 25000, model='total', day=150, ...
    seconds=11*3600, apindex=80);
 
% Quiet wind at multiple altitudes (day/seconds must match array size)
wind = atmoshwm([50; 50], [-20; -20], [100000; 150000], ...
    model='quiet', day=[30; 30], seconds=[0; 0]);
 
% Disturbed wind
wind = atmoshwm(70, -65, 150000, model='disturbance', day=166, seconds=0);

Name-value options: model ('quiet'|'disturbance'|'total'), day, seconds, apindex, version ('14'|'07').

Gravity: Spherical Harmonic

Input is Planet-Centered Planet-Fixed (PCPF) [x,y,z] coordinates in meters — NOT lat/lon/alt.

% Earth: 25,000 m over South Pole (z-axis = polar axis)
[gx, gy, gz] = gravitysphericalharmonic([0, 0, -(6356752 + 25000)]);
 
% Mars GMM2B: equator + pole
pos = [3396200 + 15000, 0, 0;   % equator
       0, 0, 3376200 + 11000];  % north pole
[gx, gy, gz] = gravitysphericalharmonic(pos, 'GMM2B');

Models: 'EGM2008' (default), 'EGM96', 'LP100K', 'LP165P', 'GMM2B', 'EIGENGL04C', 'Custom'.

Note: Polar positions on oblate bodies will trigger a "Radial position is less than equatorial radius" warning — this is expected (polar radius < equatorial radius) and results are still valid.

Gravity: WGS84

Uses geodetic coordinates (height in meters, latitude/longitude in degrees).

For the Exact method with optional effects, pass flags as a single vector [noatm, nocent, prec, jd]:

% Taylor series (default) — only h and lat, no method string
g = gravitywgs84(1000, 45);
 
% CloseApprox — requires lon as 3rd argument
g = gravitywgs84(1000, 45, 20, 'CloseApprox');
 
% Exact with precession — requires lon + flag vector
[gn, gt] = gravitywgs84(1000, 0, 20, 'Exact', [false, false, true, 2451545]);

Calling conventions:

• Default (Taylor series): gravitywgs84(h, lat) — do NOT pass 'TaylorSeries' as a string
• CloseApprox: gravitywgs84(h, lat, lon, 'CloseApprox') — requires lon
• Exact: gravitywgs84(h, lat, lon, 'Exact', [noatm, nocent, prec, jd]) — requires lon + flag vector

Flag vector [noatm, nocent, prec, jd]:

• noatm: true = exclude atmosphere correction
• nocent: true = exclude centrifugal effect
• prec: true = include precession
• jd: Julian date (0 = no precession date)

Gravity: Zonal Harmonic

Input is PCPF [x,y,z] in meters. Degree is a numeric scalar.

% Earth, 4th degree, at equator surface
Re = 6378137;
[gx, gy, gz] = gravityzonal([Re, 0, 0], 'Earth', 4);
 
% Mars at two positions
[gx, gy, gz] = gravityzonal([3396200+15000, 0, 0; 0, 0, 3376200+11000], 'Mars');

Gravity: Centrifugal

Input is PCPF [x,y,z] in meters.

% Earth at equator surface
[gx, gy, gz] = gravitycentrifugal([6378137, 0, 0]);
 
% Mars
[gx, gy, gz] = gravitycentrifugal([3396200, 0, 0], 'Mars');

Magnetic Field Models

Both wrldmagm and igrfmagm take height in meters, latitude/longitude in degrees, and decimal year. Use decyear to convert calendar dates.

% WMM-2025
[XYZ, H, D, I, F] = wrldmagm(1000, 40.44, -79.99, decyear(2025,7,4), '2025');
 
% IGRF-14
[XYZ, H, D, I, F] = igrfmagm(3000, 41.50, -81.69, decyear(2028,7,4), 14);

Output: XYZ = [North, East, Down] in nT; H = horizontal intensity; D = declination (deg); I = inclination (deg); F = total intensity (nT).

Geoid Height and Geocentric Radius

% Geoid undulation (EGM96 default) — longitude must be [0, 360]
N = geoidheight(42.4, 289.0);
 
% EGM2008
N = geoidheight(42.4, 289.0, 'EGM2008');
 
% Geocentric radius at multiple latitudes (input: geocentric lat in degrees)
r = geocradius([0, 45, 90]);           % default WGS84
r = geocradius([0, 45, 90], 'WGS84');  % explicit model

Planetary Ephemeris and Earth Orientation

Ephemeris functions require data from aeroDataPackage. All take Julian dates as time input.

% Planet/Moon position and velocity (km, km/s by default)
jd = juliandate(2022, 10, 27, 12, 0, 0);
[pos, vel] = planetEphemeris(jd, 'Earth', 'Moon');
[pos, vel] = planetEphemeris(jd, 'SolarSystem', 'Mars', '430', 'AU');
 
% Earth nutation (radians)
[angles, rates] = earthNutation(jd);  % angles = [dpsi, depsilon]
 
% Moon libration (radians)
[angles, rates] = moonLibration(jd);  % 3 Euler angles + rates
 
% Earth polar motion (radians) — input is UTC as Julian date
utc = juliandate(2020, 1, 1);
[pm, pmError] = polarMotion(utc);  % pm = [xp, yp]
 
% Celestial Intermediate Pole adjustment (radians)
[dcip, dcipError] = deltaCIP(utc);  % dcip = [dX, dY]
 
% UT1-UTC difference (seconds)
[dut1, dut1Error] = deltaUT1(utc);

Valid planetEphemeris targets/centers: 'Sun', 'Mercury', 'Venus', 'Earth', 'Moon', 'Mars', 'Jupiter', 'Saturn', 'Uranus', 'Neptune', 'Pluto', 'SolarSystem', 'EarthMoon'.

Models: '405' (default), '421', '423', '430', '432t'.

Note: polarMotion, deltaCIP, and deltaUT1 use IERS data from aeroiersdata.mat (shipped) or a custom source. To get updated IERS data:

% Download latest Earth orientation data and save as MAT file
iersFile = aeroReadIERSData(pwd);
% Then pass to Earth orientation functions via Source name-value
[pm, pmError] = polarMotion(utc, Source=iersFile);
[dcip, dcipError] = deltaCIP(utc, Source=iersFile);
[dut1, dut1Error] = deltaUT1(utc, Source=iersFile);

Space Weather Pipeline

The full pipeline for realistic NRLMSISE-00 inputs:

% Step 1: Read CSV (downloaded from CelesTrack) into MAT file
% TEMPLATE — requires user-provided CSV file
matFile = aeroReadSpaceWeatherData('spaceWeatherFile.csv');
 
% Step 2: Extract flux and magnetic indices for a specific date/time
dt = datetime(2022, 10, 27, 6, 30, 0, 'TimeZone', 'UTC');
[f107avg, f107daily, magIdx] = fluxSolarAndGeomagnetic(dt, matFile, ...
    F107ExtrapMethod='constant', MagneticIndexExtrapMethod='constant');
 
% Step 3: Feed into NRLMSISE-00
dayOfYear = day(dt, 'dayofyear');
UTsec = seconds(timeofday(dt));
[T, rho] = atmosnrlmsise00(400e3, 45, -50, dt.Year, dayOfYear, UTsec, ...
    f107avg, f107daily, magIdx, 'NoOxygen');

Notes:

• aeroReadSpaceWeatherData takes a user-provided CSV (CelesTrack format) — no sample ships with the toolbox
• It returns a MAT file containing the space weather data for use with fluxSolarAndGeomagnetic
• The pre-built aeroSpaceWeatherData.mat (via which('aeroSpaceWeatherData.mat')) is available if no CSV is provided
• fluxSolarAndGeomagnetic accepts either (datetime, matFile) or (year, dayOfYear, UTCseconds, matFile)

Common Mistakes

Conventions

• Height units: All atmosphere, gravity, and magnetic functions use meters (not km, not feet)
• Latitude/longitude: Degrees for geodetic functions; PCPF [x,y,z] meters for gravitysphericalharmonic, gravityzonal, gravitycentrifugal
• Decimal year: Use decyear(year, month, day) for magnetic model date inputs
• Time: day = day of year (1-366); seconds = seconds since midnight UTC
• PCPF coordinates: x-axis through 0N/0E, y-axis through 0N/90E, z-axis through North Pole
• `geoidheight` longitude: Must be in [0, 360] degrees (east positive). Use mod(lon, 360) to convert from [-180, 180]
• South Pole in PCPF: [0, 0, -(Rp + altitude)] where Rp is polar radius
• Equator in PCPF: [Re + altitude, 0, 0] where Re is equatorial radius

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