FSI of high performance high-lift devices with circulation control via conditioned coandã-jets

Current transport aircraft are limited to airports with comparatively long runways for take-off and landing. An aircraft with short take-off and landing capabilities is under investigation at the Collaborative Research Center 880. The aircraft employs circulation controlled high lift devices where high velocity air is blown through a slot in front of the flap. These high performance high-lift devices allow take-off and landing of the aircraft at runways of 800 m length. The curved flap leading edge induces a Coandˇa effect with the jet resulting in an attached flow up to the tip of the flap even at high deflection angles of up to 85 . Examination of the aeroelasticity of the wing is of high importance because of the sensitivity of the Coandˇa effect to perturbation through deformation and consequential change in flow. The large pressure gradients can play a significant role in the effective use of this jet system. Preliminary studies have shown an influence on aerodynamic performance due to slot deformation. Small changes in the aerodynamic characteristics can have adverse effects on the stall behavior. A flap section model of the wing is used to analyze the performance for several flight states. This high detail model allows capturing fine effects over the whole wing chord and on the slot region while still including wing deformations. The aerodynamic performance of the aeroelastic flap section model is compared to the characteristics of the rigid airfoil. The analyzed flight states give an insight into the influence of the deformation on the flow. Additionally the effects of jet momentum variation on aerodynamics is shown and the dominant stall phenomena presented. The local relative change in pressure can reach values between 10 and 20 % and has an influence on the stall behavior of the section. The change in aerodynamic performance illustrates the influence of small deformations on the sensitive circulation control

Traffic Optimization for Signalized Corridors (TOSCo) Phase 2 Project

DTFH6114H00002This report provides a roadmap to details contained in four TOSCo Phase 2 detailed reports that focus on specific aspects of the four key technical objectives undertaken in the TOSCo Phase 2 Project. The four key technical objectives that the project team focused their efforts on in the project were: 1. Implement TOSCo vehicle algorithm in vehicles 2. Implement TOSCo infrastructure algorithm in infrastructure components 3. Verify and refine TOSCo system in a closed course setting then exporting it onto an actual corridor 4. Assess TOSCo functional safety and performance using real-world observations and actual on-road dat

Design and modelling of a support and stabilizing cylinder for a very large stable membrane antenna

The Institute of Composite Structures and Adaptive Systems of the German Aerospace Center (DLR) is developing in cooperation with the European Space Agency (ESA) a large, light weight, stable membrane antenna, which can be packed in a small volume and deployed in space. This work comprised the design of a scalable prototype which needs to be engineered in a way to increase the packing efficiency which can be archived by rolling up the membranes and their stabilizing booms on a core structure. Previous projects have advanced the development of the main structure aiming on the dynamic stability and the characteristics of the booms. The central task of this student project was the design of the aforementioned core structure and all its sub-elements to facilitate an easy storage, deployment as well as operation. For this purpose the construction focused on lightweight design with attention to the limitation of stress to the core itself, the booms and especially the thin membranes. The process constituted a conceptual approach to match the preceding design activities, a discussion during the design phase and a final concept which will be manufactured and implemented with the existing components

DESIGN AND TEST OF TAPE SPRING HINGES FOR THE DEPLOYMENT OF SOLAR ARRAYS FOR SPACECRAFTS

Reliable deployment and locking of structures like booms, panels and antennae is a key moment at the beginning of spacecraft missions. Classical approaches for the deployment of fixed structures employ spring powered hinges. Curved thin strips, known as tape springs, are self-powered, self-locking mechanism with low complexity. The tape spring dimensions and its material determine the deployment characteristics and its unlocking resistance. Various variables of the behaviour of composite hinges are identified in this work. Regression analysis is used to derive simplified formulas allowing for quick design of hinges based on the desired deployment parameters like deployed stiffness, deployment time and solar panel accelerations

FSI of high performance high-lift devices with circulation control via conditioned coandã-jets

Current transport aircraft are limited to airports with comparatively long runways for take-off and landing. An aircraft with short take-off and landing capabilities is under investigation at the Collaborative Research Center 880. The aircraft employs circulation controlled high lift devices where high velocity air is blown through a slot in front of the flap. These high performance high-lift devices allow take-off and landing of the aircraft at runways of 800 m length. The curved flap leading edge induces a Coandˇa effect with the jet resulting in an attached flow up to the tip of the flap even at high deflection angles of up to 85 . Examination of the aeroelasticity of the wing is of high importance because of the sensitivity of the Coandˇa effect to perturbation through deformation and consequential change in flow. The large pressure gradients can play a significant role in the effective use of this jet system. Preliminary studies have shown an influence on aerodynamic performance due to slot deformation. Small changes in the aerodynamic characteristics can have adverse effects on the stall behavior. A flap section model of the wing is used to analyze the performance for several flight states. This high detail model allows capturing fine effects over the whole wing chord and on the slot region while still including wing deformations. The aerodynamic performance of the aeroelastic flap section model is compared to the characteristics of the rigid airfoil. The analyzed flight states give an insight into the influence of the deformation on the flow. Additionally the effects of jet momentum variation on aerodynamics is shown and the dominant stall phenomena presented. The local relative change in pressure can reach values between 10 and 20 % and has an influence on the stall behavior of the section. The change in aerodynamic performance illustrates the influence of small deformations on the sensitive circulation control

SFB880: FLIGHT DYNAMICS

The paper summarizes approaches and first results on flight dynamics of the Collaborative Research Centre SFB 880 - "Fundamentals of High Lift for Future Commercial Aircraft" - , i.e. high fidelity solutions of dynamics in aerodynamics, aeroelasticity and flight control