EQUATIONS OF MOTION FOR FLIGHT SIMULATION OF THE ASROC MISSILE
Abstract
Equations of motion are presented for a three dimensional trajectory simulation under the assumption that, during the thrust phase, the configuration is a rigid body and has 90 degree rotational symmetry. For flight simulation during the after-burning phase equations based on particle ballistic theory are presented. The instantaneous position of the missile in space is defined relative to a spherical, rotating earth. Aerodynamic coefficients considered during the thrust phase are functions of Mach number, angle of attack and effective roll angle. During the after-burning phase the aerodynamic drag coefficient is a function of Mach number. The formulation was designed for the specific purpose of generating accurate fire control data for the ASROC missile but may have wide application among other types of rockets. For this reason certain terms have been included in the model which are not significant for the ASROC application. Among them are terms to simulate effects of a rotating earth. As an option the free-flight after-burning phase may be simulated by a six-degree-of-freedom model.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 29, 1962
- Accession Number
- AD0283561
Entities
People
- Herman P. Caster
Organizations
- Naval Surface Warfare Center Dahlgren Division