An experimental and simulation flight test has been carried out to evaluate the longitudinal gliding characteristics of a lifting body with blunted half-cone geometry. The novelty here is the lifting body's pitch control mechanism, which consists of a pair of leading-edge rotating cylinders. Flight simulation uses aerodynamic data from computational fluid dynamics supported by wind-tunnel test....

Shape control of adaptive wings has the potential to enhance wing aerodynamic performance during cruise and high-speed off-design conditions. A possible way to attain this objective is to develop specific technologies for trailing edge morphing, aimed at variating the airfoil camber. In the framework of SARISTU project (EU-FP7), an innovative structural system incorporating a gapless deformable...

The scientific objective of the Mars Surveyor Program 2005 mission is to return Mars rock, soil, and atmospheric samples to Earth for detailed analysis. The present investigation focuses on design of Mars Ascent Vehicle for this mission. Aerodynamic, aerothermodynamic, and trajectory design considerations are addressed to assess the ascent configuration, determine aerodynamic stability, charact...

Characterization of an off-the-shelf small tailless aircraft with a wing span of 1.3m is presented. Mentioned aircraft is being used in several scientific measurement projects by authors, whereas the flight performance and quality such as endurance, and stability plays an important role on the measurement quality. Hence the main objective is to use the extracted and fine tuned aerodynamic and f...

This paper investigates the use of structured H∞ control for aerodynamic descent phase a reusable rocket. A unified strategy attitude and position is proposed verified. The architecture controller, together with observed performance are discussed. Results presented CALLISTO, rocket demonstrator jointly developed by DLR, JAXA CNES.

This thesis focuses on deriving algorithmic frameworks for the control of Aerodynamic Phenomena. The application of one such control law to the control of Flutter is discussed in detail. Flutter is an aero-structural instability that arises due to the adverse transfer of energy between the airplane structure and the surrounding fluid. CFD is now a mature technology and can be used as a design t...

Flapping wing vehicles, or ornithopters, have proven difficult to control due to the unsteady flow generated by the high-speed flapping surfaces. To-date, research has focused on computational models from which fixed flapping strokes are optimized. These strokes are then fixed and executed open-loop in practice with flapping speed as the primary control output for climb and descent. This paper ...

This paper reviews the formulation and application of optimization techniques based on control theory for aerodynamic shape design in both inviscid and viscous compressible ow. The theory is applied to a system de ned by the partial di erential equations of the ow, with the boundary shape acting as the control. The Frechet derivative of the cost function is determined via the solution of an adj...