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Parachute systems can be used to control the reentry trajectory of launcher upper stages, in order to lower the risks to the population or facilitate the retrieval of the stage. Several types of parachutes deployed at subsonic, supersonic and hypersonic speeds are analyzed, modeled as single and multistage systems. The performance of deceleration parachutes depends on their drag area and deployment conditions, while gliding parachutes are configured to achieve stable flight with a high glide ratio. Gliding parachutes can be autonomously guided to a low risk landing area. Sizing the canopy is shown to be an effective method to reduce parachute sensitivity to wind. The reentry trajectory of a launcher upper stage is simulated for each parachute system configuration and the results are compared to the nominal reentry case.

The prediction of Darrieus wind turbine aerodynamic performances provides the necessarydesign and operational data base related to the wind potential. In this sense it provides the type ofturbine suitable to the area where it is to be installed. Two calculation methods are analyzed for arotor with straight blades. The first one is a global method that allows an assessment of the turbinenominal power by a brief calculation. This method leads to an overestimation of performances. Thesecond is the calculation method of the gust factor and momentum which deals with the pale as beingcomposed of different elements that don’t influence each other. This method, developed based on thetheory of the turbine blades, leads to values close to the statistical data obtained experimentally. Thevalues obtained by the calculation method of gust factor - momentum led to the concept of a Darrieusturbine, which will be tested for different wind values in the INCAS subsonic wind tunnel.

The specific developments of Dutch roll mode have shown a number of flight dynamics deficiencies, prevailing in aircraft with fixed (non-assisted) controls in which the damping factor is at level 2.The project deals with the lateral motion damping (damper of gyration) issue according to the flight regulations, for an envelope as wide as possible, but mainly referring to missions involving the Dutch roll type developments. The undertaken analysis takes as a reference the school and training aircraft IAR – 99. The execution equipment, an actuator assisted by a servo valve, ensures the system efficiency of self-stabilization system SAS providing low execution times and high precision. The relationship between the flight quality parameters related to characteristics of lateral-directional motion modes, depending on gravimetric-inertial and aerodynamic parameters of the airplane is envisaged to meet the regular levels of flying qualities. The proposed calculation method can be used both for flight qualitative analysis and for defining the overall conditions for meeting the quality flight regulations. These conditions can serve as a basis for assessing the possibilities to remedy the above-mentioned deficiencies mater.

The low frequency damper is an autonomous equipment for damping vibrations with the 1-20Hz range.Its autonomy enables the equipment to be located in various mechanical systems, without requiring special hydraulic installations.The low frequency damper was designed for damping the low frequency oscillations occurring in the circuit controls of the upgraded IAR-99 Aircraft.The low frequency damper is a novelty in the aerospace field ,with applicability in several areas as it can be built up in an appropriate range of dimensions meeting the requirements of different beneficiaries. On this line an equipment able to damp an extended frequency range was performed for damping oscillations in the pipes of the nuclear power plants.This damper, tested in INCAS laboratories matched the requirements of the beneficiary.The low frequency damper is patented – the patent no. 114583C1/2000 is held by INCAS.