GravityEngine2.EarthAtmosphereReentry Class Reference

Integrates the effect of Earth atmospheric drag on a spacecraft. More...

Static Public Member Functions
static double3[]	Alloc (double h0Km, double Cd, double area, double massKg, double mu_SI, double dtSec, bool shadowMode=false)
	Create a data[] block for core physics parameters/data and initialize.
static double	Density (double heightKm)
	Compute the density of the atmosphere at a given height in km.
static int double3 double3 v	EvolveSelfIntegrated (ref ExternalAccel.EAStateData eaState, int extAccelId, double tGE, double dt, ref GEPhysicsCore.GEPhysicsJob gePhysJob)
static void	UpdateShadow (double3 r, double3 v, double tSec, int paramBase, NativeArray< double3 > data)

Static Public Attributes
const int	DATA_SIZE = 5
static int double3	r
static int	status
const int	STATUS_IMPACT = 1
const int	STATUS_NAN = 2
const int	STATUS_OK = 0

Detailed Description

Integrates the effect of Earth atmospheric drag on a spacecraft.

This is a self-integrating external acceleration that can be used to model the reentry of a spacecraft into the Earth's atmosphere. It can also be used to model the path of a discarded stage of a multi-stage booster.

This block can be added in a "dormant" mode (e.g. a first stage prior to staging) and then activated when the stage is ready to reenter. In this mode it has a reference to the booster object and will take it's R and V from the booster object.

The data[] block is initialized with the following parameters:

Member Function Documentation

Alloc()

static double3[] GravityEngine2.EarthAtmosphereReentry.Alloc ( double h0Km, double Cd, double area, double massKg, double mu_SI, double dtSec, bool shadowMode = false )

static

Create a data[] block for core physics parameters/data and initialize.

Parameters

h0Km	radius of the body being reentered (used for height to deterine the atmo density)
Cd	coefficient of drag
area	cross-sectional area (for drag calculation)
massKg	spacecraft mass
mu_SI	GM for the body being reentered
dtSec	time step of the self-integrating semi-implicit Euler method

Returns

Density()

static double GravityEngine2.EarthAtmosphereReentry.Density ( double heightKm )

static

Compute the density of the atmosphere at a given height in km.

Parameters

heightKm

Returns

density in kg/m^3

---

The documentation for this class was generated from the following file:

• ge2/GE2/Assets/GravityEngine2/Runtime/Core/ExternalAcceleration/SelfIntegrating/EarthAtmosphereReentry.cs