Verification of scale model in the design of a new SJA

The new scale model will be used to enable the design of the next generation SJA. The verification of the scale model will be performed in close cooperation between the application and the topic manger by designing and characterizing a new actuator based on the findings using the model. The characterization of the actuator will give a first feedback on the accuracy of the model.

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3. Major deliverables/ Milestones and schedule (estimate)

Ref. Nr.

Deliverable Title -

Type

Due date

D1 Analysis of numerical results of SJA in quiescent air condition. Report M10 D2 Analysis of experimental results of SJA in quiescent air condition. Report M12

D3 Model of SJA in quiescent air condition Report M15

D4 Analysis of numerical results of SJA in cross flow condition. Report M18 D5 Analysis of experimental results of SJA in quiescent air condition. Report M20

D6 Model of SJA in cross flow condition Report M24

D7 Scaled model for SJA Report M30

D8 SJA scaled model verification Report M36

Ref. Nr.

Milestone Title

Type

Due date

M1 Lab test finished M12

M2 SJA model (quiescent air condition) validated M15

M3 Wind tunnel test finished M20

M4 SJA model (cross flow condition) validated M24

M5 Verification of scale model successful M34

4. Special skills, Capabilities, Certification expected from the Applicant(s)

The applicant should have profound knowledge in flow control actuator design for aircraft applications. The actuator design must be based on pulsed air blowing without net mass flux.

 The applicant should have expertise in the area of CFD

 The applicant should have expertise in the area of flow measurements and characterization of fluidic devices

 The applicant should have the possibility to prepare and perform lab tests and WT tests to verify the simulation results

o This includes: selection of test geometry, integration of sensors, definition of boundary conditions, data acquisition and data handling

An Implementation agreement will be proposed to manage the IPR and the relation between the Topic

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 Task 1 D1 Task 2 D2 Task 3 D3 Task 4 D4 Task 5 D5 Task 6 D6 Task 7 D7 Task 8 D8 Milestones M1 M2 M3 M4 M5

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XI.

Divergent Aircraft Configurations

Type of action (RIA or IA) RIA

Programme Area LPA, Platform 1, WP1.6.1.4

Joint Technical Programme (JTP) Ref. JTP V5

Indicative Funding Topic Value (in k€) 1 500 k€ Type of agreement Implementation Agreement Duration of the action (in Months) 30 months Indicative Start

Date12

Q2 2017

12 _{The start date corresponds to actual start date with all legal documents in place.}

Identification Title

JTI-CS2-2016-CFP04-LPA-01-28 Divergent Aircraft Configurations Short description (3 lines)

Requested is the delivery of analysis models, of a design platform and of design support for an aircraft design exercise in the field of novel (hybrid) propulsion architectures. The requested know- how comprises system, airframe and operation modelling as well as optimization expertise.

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1. Background

Work Package 1.6 of the Large Passenger Aircraft (LPA) IADP is aimed at the Demonstration of Radical Aircraft Configurations. One main topic in this work package is the aircraft configuration development for alternative propulsion concepts. This work is mainly performed in Work Package 1.6.1.4, “Divergent Aircraft Configurations”. Here, advanced aircraft concepts shall be developed based upon a design strategy targeting a perfect synthesis between innovative airframe concepts and a novel propulsion architecture and its comprising individual technologies. The plan is to open a new design and validation space and offer through this approach a set of efficiently developed (time, cost) and validated airframe and propulsion concepts to overcome the threshold to full game-changing aircraft design. To fulfil the intention of work package 1.6, a very high integration level between airframe and propulsion system is required.

Focus of the work in WP 1.6.1.4 is on integration concepts for Hybrid Propulsion, thus going beyond the UHBR and the CROR. The optimal hybrid propulsion architecture with respect to flight mission profiles, based on synergies and opportunities, has to be defined. An investigation of the interactions and limitations of radical aircraft configurations and of projected hybrid energy technologies shall lead to a sound concept.

The existing consortium drives the development of advanced aircraft concepts based upon a team-centred design strategy. The work is performed by two design teams, with a potential third team joining in 2016. These teams each cover the complete range of aircraft conceptual design and will concentrate on different aircraft configurations, respectively. Two common reference aircraft, one with classical turbofan engines, one with turboprop engines, will be a common baseline for all teams. While each team will concentrate on exploring different design regions of novel propulsion and innovative airframe concepts, the investigations are linked by common evaluation criteria. Tools used by all partners include conceptual design tools, preliminary design tools, as well as high fidelity design tools where necessary. Investigations are, by necessity, multi-disciplinary. A crucial point for the cooperation of the design teams is the availability of common know-how and modelling approaches for aircraft systems, including the blocks for hybrid propulsion systems and for aircraft structures, as well as the availability of a common modelling framework (design platform), for system integration and multidisciplinary analysis and optimisation. The expected level of detail is a conceptual and preliminary design level. This expertise is expected to be contributed by the applicant. The contributions of the applicant shall thus be available for all design teams. Each design team will specify the interfaces of its existing design chains to be supported by the applicant at the start of the activity.

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2. Scope of work