The original proposal was to use the geometry of a reference aircraft for the Scaled Flight Demonstrator (SFD) design. Due to issues with the release of actual geometry data the decision was taken to develop the geometry for the SFD based on Open Source data and guidance from the reference aircraft OEM (Airbus). The final SFD geometry is assessed by comparing the 3D models and by Computational Fluid Dynamics by a partner within LPA 1.3. In the first period of the SCALAiR project the 3D model of the SFD has been developed, starting with the design of the aerodynamic surfaces. Also the best scaling factor (1:8,5) for the SFD was selected, using a Matlab tool whereby the scaling factor can be optimized given scaling requirements and design constraints. 2D and 3D analysis techniques were used to verify that the SFD geometry can fly given the selected scaling factor. The final SFD geometry was approved within LPA 1.3 to start the further design. These inputs were used to calculate the aerodynamic loads, hinge moments of the control surfaces and basic performance parameters, as drivers for the selection of components, e.g. actuators, engines and the structural design of the SFD. The fact that the SFD will undergo a wind tunnel test puts additional requirements on the structural design of the SFD. The procurement, design and manufacturing of the SFD components and structure has started.
Partially independent of the SFD geometry is the design of the electrical system for the SFD, including the Avionics Rack. Using the operational requirements defined within LPA 1.3 the high level architecture of the electrical system has been defined and the basis autopilot to be used has been selected. Most components of the electrical system, e.g. datalink system, power supply, vehicle control unit, etc. have been procured or are under development.
Two projects in LPA 1.3 provide subsystems that need to be integrated in the SFD; the NOVAIR project that designs the Flight Test Instrumentation system used to monitor and measure specific parameters for the scaling analysis and the analysis of the SFD behaviour. The HyperF project designs the Guidance and Navigation Computer that will initiate and control the specific test maneuvers of the SFD. These systems have a close interface with the SCALAiR project both electrical interfaces and structural interfaces.
In the second half of 2019, financial issues have been identified by NLR. The critical risk as identified in the proposal that adjustments or redesign of the new vehicle is too expensive and time consuming w.r.t. allocated resources has materialized. Discussions were held between WP1.3 partners, PL1 leader and CSJU and a recovery plan was proposed and agreed in Q1 2020. It was agreed that the remaining activities in 2020 and later are funded under the NOVAIR project. The SFD has been tested in the wind tunnel of DNW in April 2021. Qualification and mission flight tests campaigns are planned to be performed in September-October 2021.
