The equations of motion of an elastic launch vehicle with varying mass. 1: Basic equations
Abstract
General three dimensional dynamic equations of motion for a launch vehicle with varying mass are derived, having effects of airframe bending, propellant sloshing, propellant flow and engine swivelling into account. The effect of propellant flow is considered as reaction forces of propellant to airframe, and using the theory of continuum mechanics the time rate of change of integrals of some quantities are being transferred out of the system. Sloshing and bending equations are derived accurately, in view of practical analysis of the whole motion of the vehicle.
- Publication:
-
NASA STI/Recon Technical Report N
- Pub Date:
- August 1974
- Bibcode:
- 1974STIN...7519324T
- Keywords:
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- Aeroelasticity;
- Airframes;
- Equations Of Motion;
- Launch Vehicles;
- Structural Stability;
- Bending Moments;
- Liquid Sloshing;
- Propellant Storage;
- Stress Analysis;
- Launch Vehicles and Space Vehicles