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Pearl-Like Coating Enhances Lightweight Armor

  • Magazine Article
  • TBMG-35453
Published 2019-11-01 by Tech Briefs Media Group in United States

By mimicking the outer coating of pearls (nacre or mother of pearl), researchers created a lightweight plastic that is 14 times stronger and eight times lighter (less dense) than steel. It could be applicable to vests, helmets, and other types of body armor as well as protective armor for ships, helicopters, and other vehicles.

Unmanned Helicopter Drone

  • Magazine Article
  • TBMG-35358
Published 2019-10-01 by Tech Briefs Media Group in United States

UAVOS Inc. Mountain View, CA 650-584-3176 www.UAVOS.com

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Low Cost Reconfigurable Jig Tooling and In-Process Metrology for High Accuracy Prototype Rotorcraft Wing Assembly

University of Nottingham-Richard J. Crossley, Svetan Ratchev
Published 2019-09-16 by SAE International in United States
Reconfigurable tooling frames consisting of steel box sections and bolted friction clamps offer an opportunity to replace traditional expensive welded steel tooling. This well publicized reconfigurable reusable jig tooling has been investigated for use in the assembly of a prototype compound helicopter wing.Due to the aircraft configuration, the wing design is pinned at both ends and therefore requires a higher degree of end to end accuracy, over the 4m length, than conventional wings. During the investigation some fundamental issues are approached, including:Potential cost savings and variables which effect the business case.Achievable Jig accuracy.Potential sources of instability that may affect accuracy over time.Repeatability of measurements with various features and methods.Typical jig stability over 24hrs including effects of small temperature fluctuations.Deflections that occur due to loading.The cost benefit of reusable tooling in a low volume prototype scenario is examined followed by the design of the jig and location features to enable the accurate build and certification documentation to be completed. A prototype 4m test jig comprising of commercially available components and bespoke machined ‘pick-ups’ is presented.Hardware and…
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Advanced Assembly Solutions for the Airbus RACER Joined-Wing Configuration

University of Nottingham-David Bainbridge, Konstantinos Bacharoudis, Andrea Cini, Alison Turner, Atanas Popov, Svetan Ratchev
Published 2019-09-16 by SAE International in United States
The Rapid And Cost Effective Rotorcraft (RACER) is being developed by Airbus Helicopters (AH) to demonstrate a new Vertical Take-Off and Landing configuration to fill the mobility gap between conventional helicopters and aeroplanes. RACER is a compound rotorcraft featuring wings and multiple rotors. The wing arrangement suggested by AH is defined as a staggered bi-plane joined configuration with an upper and a lower straight wing, either side of the fuselage, connected at their outboard extent to form a triangular structure. The ASTRAL consortium, consisting of the University of Nottingham and GE Aviation Systems, are responsible for the design, manufacture, assembly and testing of the wings. Producing an optimised strategy to assemble a joined-wing configuration for a passenger carrying rotorcraft is challenging and novel. The objective of this work concerns all aspects of assembling the joined-wing structure.The joined-wing and fuselage structures will be produced independently and mated together during the final RACER assembly. A multi-stage process will deliver the joined-wing assembly and ensure it will fit to the fuselage. Producing the individual wing structures requires a…
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Ultra-Light Rocket Launchers

  • Magazine Article
  • TBMG-35110
Published 2019-09-01 by Tech Briefs Media Group in United States

Arnold Defense Arnold, MO 636-296-5417

Hybrid Ultra-Low VOC and Non-HAP Rain Erosion Coatings

  • Magazine Article
  • TBMG-34877
Published 2019-08-01 by Tech Briefs Media Group in United States

Numerous military aircraft and shipboard surfaces, such as radomes, antennas, gun shields, wing leading edges, and helicopter blade leading edges, are coated with a specialized erosion-resistant protective coating possessing strict performance requirements. These protective coatings must provide excellent rain erosion resistance, superior mechanical properties, good adhesion to the substrate and meet a host of other metrics outlined in MIL-PRF-32239 and SAE AMS-C- 83231A.

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An Ice Shedding Model for Rotating Components

ANSYS Inc.-Shezad Nilamdeen, Yue Zhang, Isik Ozcer, Guido S. Baruzzi
Published 2019-06-10 by SAE International in United States
A CFD simulation methodology is presented to evaluate the ice that sheds from rotating components. The shedding detection is handled by coupling the ice accretion and stress analysis solvers to periodically check for the propagation of crack fronts and possible detachment. A novel approach for crack propagation is highlighted where no change in mesh topology is required. The entire computation from flow to impingement, ice accretion and crack analysis only requires a single mesh. The accretion and stress module are validated individually with published data. The analysis is extended to demonstrate potential shedding scenarios on three complex industrially-relevant 3D cases: a helicopter blade, an engine fan blade and a turboprop propeller. The largest shed fragment will be analyzed in the context of FOD damage to neighboring aircraft/component surfaces.
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Numerical Optimisation of a Helicopter Engine Inlet Electrothermal Ice Protection System

AeroTex UK-Richard Moser, Ian Roberts
Published 2019-06-10 by SAE International in United States
This paper details the process involved in the numerical optimisation of a helicopter engine inlet electrothermal ice protection system. Although the process was developed using a production aircraft, it is demonstrated here using a generic intake and flight conditions, due to confidentiality of the actual design. The process includes adherence to the overall system design objectives (maximum power demand), including tolerances required to account for an industrial system (aircraft voltage variation, manufacturing tolerances). The numerical optimisation was performed using a combination of 2D and 3D methods to define the required heated area, power density, locations and settings for temperature control sensors. The use of 2D design tools allows a rapid iteration process to be performed, leading to the possibility of a higher level of optimisation within the allowable time-frame compared to the use of full 3D methods. Different flight settings (different Angle of Attack and Angle of Sideslip) were analysed, for two different droplet diameters (MVD values of 20 microns and 40 microns, coherent with the requirements of the CS-29 Appendix C icing envelope). An…
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Helicopter Load Sensor

  • Magazine Article
  • TBMG-34532
Published 2019-06-01 by Tech Briefs Media Group in United States

Sensor Technology Ltd. Banbury, Oxon, UK 01869 238400

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Evaluation of Aeronautical Design Standard - 33 Using a UH-60A Black Hawk

Aerospace & Defense Technology: February 2019

  • Magazine Article
  • 19AERP02_09
Published 2019-02-01 by SAE International in United States

Flight tests determine whether performance standards developed for scout and attack class rotorcraft can be applied to utility helicopters.

In 1982, the U.S. Army Aeroflightdynamics Directorate (AFDD), then assigned under the U.S. Army Aviation Systems Command (AVSCOM), began development of a new handling qualities specification for military rotorcraft. This effort resulted in the U.S. Army's initial Aeronautical Design Standard-33 (ADS-33A), “Handling Qualities Requirements for Military Rotorcraft,” published in May 1987. It was initially applied to the RAH-66 Comanche Helicopter program, meaning the handling qualities requirements generally related more to scout and attack classes of rotorcraft. As more data became available and lessons learned emerged from using ADS-33A, refinements were implemented into ADS-33B and ADS-33C).

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