Analysis of the Aerodynamic Orbital Transfer Capabilities of a Winged Re-Entry Vehicle
Abstract
The ability to perform an inclination change maximizes the maneuverability of an orbiting space vehicle. Most maneuvers utilize a combined plane change and orbital transfer to the new orbit. This costs more in terms of energy and fuel than an in-plane change of orbits. The amount of DeltaV and fuel required for such an energy-intensive inclination change exceeds the benefit of performing the maneuver. However, this paper demonstrates that a winged re-entry vehicle, based on the currently proposed X-3 7, has the necessary thrust to change planes and then perform an in-plane transfer to achieve a new orbit. Using SIMULINKTM and LABVIEW simulation tools, this research found that the use of the aerodynamic lift of a winged re-entry vehicle produced more than 120 of inclination change with the minimal DeltaV achievable. Through small orbital maneuvers and atmospheric re-entry, the aerodynamics of the lift vector demonstrated that the spacecraft retained sufficient energy to prevent perigee collapse using an orbital regulation code to control throttle selling.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 2002
- Accession Number
- ADA407161
Entities
People
- John P. Pienkowski
Organizations
- Naval Postgraduate School