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Morphing Wing Droop Nose with Large Deformation: Ground Tests and Lessons Learned

Vasista, Srinivas and Riemenschneider, Johannes and Keimer, Ralf and Monner, Hans Peter and Nolte, Felix and Horst, Peter (2019) Morphing Wing Droop Nose with Large Deformation: Ground Tests and Lessons Learned. Aerospace, 6 (10), p. 111. Multidisciplinary Digital Publishing Institute (MDPI). doi: 10.3390/aerospace6100111. ISSN 2226-4310.

[img] PDF - Postprint version (accepted manuscript)

Official URL: https://www.mdpi.com/2226-4310/6/10/111


A design for a new high lift system that features a morphing wing leading edge 'droop nose' has the potential to generate high lift coefficients whilst mitigating airframe noise emissions. This seamless, continuous, and stepless flexible droop nose potentially offers improvements to stall and compressor requirements for an internally-blown active Coanda trailing edge flap. A full-scale, span-trimmed three-dimensional droop nose was manufactured and ground-tested based on results obtained from new design synthesis tools. A new component of the droop nose is the hybrid fiberglass-elastomeric skin that is tailored in stiffness to meet morphing curvature requirements and spanwise bending resistance. A manufacturing concept of the novel skin was established that led to an adequate manufacturing quality. The skin was driven and supported by two optimized kinematic ribs and conventional actuators and overall shape results show good agreement apart from the region closest to the leading edge. Kinematic trajectory measurements showed that the kinematics met the target trajectories well, with and without the influence of the skin, and it was deemed that the error in curvature is due to a higher than expected skin stiffness in the hybrid layer. Calculated actuator torque levels and strain measurements corroborate this inference. The lessons learned show that means of adjustment post-assembly are needed, and a reduction of torque, energy and a better curvature distribution may be achieved if the skin at the spar junction is allowed to move relative to the main wing. Careful aerodynamic, structural, actuation and manufacturing trade-off studies would be needed to determine the overall performance benefit.

Item URL in elib:https://elib.dlr.de/129511/
Document Type:Article
Title:Morphing Wing Droop Nose with Large Deformation: Ground Tests and Lessons Learned
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Vasista, SrinivasUNSPECIFIEDhttps://orcid.org/0000-0002-7917-6740UNSPECIFIED
Riemenschneider, JohannesUNSPECIFIEDhttps://orcid.org/0000-0001-5485-8326UNSPECIFIED
Keimer, RalfUNSPECIFIEDhttps://orcid.org/0000-0001-9638-4413UNSPECIFIED
Monner, Hans PeterUNSPECIFIEDhttps://orcid.org/0000-0002-5897-2422UNSPECIFIED
Date:2 October 2019
Journal or Publication Title:Aerospace
Refereed publication:Yes
Open Access:Yes
Gold Open Access:Yes
In ISI Web of Science:Yes
Page Range:p. 111
Publisher:Multidisciplinary Digital Publishing Institute (MDPI)
Keywords:morphing wing; droop nose; high lift; hybrid composites; structural optimization
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:fixed-wing aircraft
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Structures and Materials (old)
Location: Braunschweig
Institutes and Institutions:Institute of Composite Structures and Adaptive Systems > Adaptronics
Deposited By: Vasista, Srinivas
Deposited On:17 Oct 2019 13:42
Last Modified:31 Oct 2023 13:50

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