This paper presents study of control and the static stability of a rocket plane. The vehicle is been designed for a suborbital space tourism. The concept of the rocket plane control assumes two types of control surfaces. The first involves two segmented elevons. The second involves rotating side plates on the wing tips. The presented results are focused on the longitudinal static stability and the control of a pitching channel. CFD calculations were conducted by ANSYS Flunet 14.0 and MGAERO software. The paper presents diagrams of lift versus drag coefficient for trim conditions for subsonic and supersonic speeds. Derivatives of lift and pitching coefficients in respect to control surfaces deflection are also included.
|Name||29th Congress of the International Council of the Aeronautical Sciences, ICAS 2014|
|Conference||29th Congress of the International Council of the Aeronautical Sciences, ICAS 2014|
|Period||7/09/14 → 12/09/14|
- Pitching channel control
- Rocket plane
- Static stability