Astronomical Applications Department, U.S. Naval Observatory - Newcomb (Page 11)

Astronomical Applications Department, U.S. Naval Observatory Newcomb Page 11

1. PHYSICAL MODEL

1.1. Newtonian Formulation

1.2. General Relativistic Formulation

1.3. The Lunar Orbit

2. NUMERICAL INTEGRATION ALGORITHMS

3. AN OBJECT-ORIENTED APPROACH

4. ANALYSIS SUBMODULES

4.1. Automatic Detection of Mean-Motion Resonances

4.2. Close Approach Detection

4.3. Frequency Analysis

5. EPHEMERIS GENERATION

C

HAPTER

4: T

HE

I

NTEGRATION

M

ODULE

M

ARC

A. M

URISON

Astronomical Applications Department

U.S. Naval Observatory, Washington, DC

C

HAPTER

4: T

HE

I

NTEGRATION

M

ODULE

11

Figure 8 -- The integration module.

Integration

initialize the

physical model

integrate the

equations of

motion

parameters

initial

conditions

ephemeris

- body masses
- gravity model

- planets
- asteroids
- natural satellites
- planetary spins

initialize the

integrator

parameters

- integrator type
- accuracy
- start/stop times
- output interval

- planets
- asteroids
- natural satellites