Army Future Vertical Lift (FVL) Program
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Future Battlefield Rotorcraft Capability (FBRC) – Anno 2035 and Beyond
November 2018 Future Battle eld Rotorcraft Capability Anno 2035 and Beyond Joint Air Power Competence Centre Cover picture © Airbus © This work is copyrighted. No part may be reproduced by any process without prior written permission. Inquiries should be made to: The Editor, Joint Air Power Competence Centre (JAPCC), [email protected] Disclaimer This document is a product of the Joint Air Power Competence Centre (JAPCC). It does not represent the opinions or policies of the North Atlantic Treaty Organization (NATO) and is designed to provide an independent overview, analysis and food for thought regarding possible ways ahead on this subject. Comments and queries on this document should be directed to the Air Operations Support Branch, JAPCC, von-Seydlitz-Kaserne, Römerstraße 140, D-47546 Kalkar. Please visit our website www.japcc.org for the latest information on JAPCC, or e-mail us at [email protected]. Author Cdr Maurizio Modesto (ITA Navy) Release This paper is releasable to the Public. Portions of the document may be quoted without permission, provided a standard source credit is included. Published and distributed by The Joint Air Power Competence Centre von-Seydlitz-Kaserne Römerstraße 140 47546 Kalkar Germany Telephone: +49 (0) 2824 90 2201 Facsimile: +49 (0) 2824 90 2208 E-Mail: [email protected] Website: www.japcc.org Denotes images digitally manipulated JAPCC |Future BattlefieldRotorcraft Capability and – AnnoBeyond 2035 | November 2018 Executive Director, JAPCC Director, Executive DEUAF General, Lieutenant Klaus Habersetzer port Branchviae-mail [email protected]. AirOperationsSup contact to theJAPCC’s free feel thisdocument.Please to withregard have you may comments welcome any We thisstudy. -
Effectiveness of the Compound Helicopter Configuration in Rotorcraft Performance Increase
transactions on aerospace research 4(261) 2020, pp.81-106 DOI: 10.2478/tar-2020-0023 eISSN 2545-2835 effectiveness of the compound helicopter configuration in rotorcraft performance increase Jarosław stanisławski Retired doctor of technical sciences [email protected] • ORCID: 0000-0003-1629-4632 abstract The article presents the results of calculations applied to compare flight envelopes of varying helicopter configurations. Performance of conventional helicopter with the main and tail rotors, in the case of compound helicopter, can be improved by applying wings and pusher propellers which generate an additional lift and horizontal thrust. The simplified model of a helicopter structure, consisting of a stiff fuselage and the main rotor treated as a stiff disk, is applied for evaluation of the rotorcraft performance and the required range of control system deflections. The more detailed model of deformable main rotor blades, applying the Galerkin method, is used to calculate rotor loads and blade deformations in defined flight states. The calculations of simulated flight states are performed considering data of a hypothetical medium class helicopter with the take-off mass of 6,000kg. In the case of both of the helicopter configurations, the articulated main rotor hub is taken under consideration. According to the Galerkin method, the elastic blade model allows to compute blade deformations as a combination of the blade bending and torsional eigen modes. Introduction of additional wing and pusher propellers allows to increase the range of operational speed over 300 km/h. Results of the simulation are presented as time- runs of rotor loads and blade deformations and in a form of disk distribution plots of rotor parameters. -
Micro Coaxial Helicopter Controller Design
Micro Coaxial Helicopter Controller Design A Thesis Submitted to the Faculty of Drexel University by Zelimir Husnic in partial fulfillment of the requirements for the degree of Doctor of Philosophy December 2014 c Copyright 2014 Zelimir Husnic. All Rights Reserved. ii Dedications To my parents and family. iii Acknowledgments There are many people who need to be acknowledged for their involvement in this research and their support for many years. I would like to dedicate my thankfulness to Dr. Bor-Chin Chang, without whom this work would not have started. As an excellent academic advisor, he has always been a helpful and inspiring mentor. Dr. B. C. Chang provided me with guidance and direction. Special thanks goes to Dr. Mishah Salman and Dr. Humayun Kabir for their mentorship and help. I would like to convey thanks to my entire thesis committee: Dr. Chang, Dr. Kwatny, Dr. Yousuff, Dr. Zhou and Dr. Kabir. Above all, I express my sincere thanks to my family for their unconditional love and support. iv v Table of Contents List of Tables ........................................... viii List of Figures .......................................... ix Abstract .............................................. xiii 1. Introduction .......................................... 1 1.1 Vehicles to be Discussed................................... 1 1.2 Coaxial Benefits ....................................... 2 1.3 Motivation .......................................... 3 2. Helicopter Flight Dynamics ................................ 4 2.1 Introduction ........................................ -
Open Walsh Thesis.Pdf
The Pennsylvania State University The Graduate School College of Engineering A PRELIMINARY ACOUSTIC INVESTIGATION OF A COAXIAL HELICOPTER IN HIGH-SPEED FLIGHT A Thesis in Aerospace Engineering by Gregory Walsh c 2016 Gregory Walsh Submitted in Partial Fulfillment of the Requirements for the Degree of Master of Science August 2016 The thesis of Gregory Walsh was reviewed and approved∗ by the following: Kenneth S. Brentner Professor of Aerospace Engineering Thesis Advisor Jacob W. Langelaan Associate Professor of Aerospace Engineering George A. Lesieutre Professor of Aerospace Engineering Head of the Department of Aerospace Engineering ∗Signatures are on file in the Graduate School. Abstract The desire for a vertical takeoff and landing (VTOL) aircraft capable of high forward flight speeds is very strong. Compound lift-offset coaxial helicopter designs have been proposed and have demonstrated the ability to fulfill this desire. However, with high forward speeds, noise is an important concern that has yet to be thoroughly addressed with this rotorcraft configuration. This work utilizes a coupling between the Rotorcraft Comprehensive Analysis System (RCAS) and PSU-WOPWOP, to computationally explore the acoustics of a lift-offset coaxial rotor sys- tem. Specifically, unique characteristics of lift-offset coaxial rotor system noise are identified, and design features and trim settings specific to a compound lift-offset coaxial helicopter are considered for noise reduction. At some observer locations, there is constructive interference of the coaxial acoustic pressure pulses, such that the two signals add completely. The locations of these constructive interferences can be altered by modifying the upper-lower rotor blade phasing, providing an overall acoustic benefit. -
Future Vertical Lift Gets Closer
The Sikorsky-Boeing Defiant X (Sikorsky-Boeing image) The Sikorsky-Boeing team has continued flying its SB>1 Defiant JMR demonstrator. According to a FlightGlobal article on Jan. 25, Future Vertical the aircraft had made 31 flights for a total of 26 flight hours since its first flight on March 21, 2019. The team had also logged 135 hours on its Propulsion Systems Testbed in West Palm Beach, Lift Gets Closer Florida. Sikorsky-Boeing plans to return to the US Air Force’s National Full-Scale Aerodynamics Complex (NFAC), located at By VFS Staff Moffett Field in Mountain View, California, in March for additional wind tunnel testing of its one-fifth-scale Defiant model. he Future Vertical Lift (FVL) program continues to move forward on multiple fronts for the US Army and US Navy. In January, the Sikorsky-Boeing team unveiled their “Defiant T Initiated by Congressional direction in 2008, FVL is expected X” concept to meet the FLRAA requirements as stated in the to set the capabilities for the rotary-wing fleet of the United States RFP, leveraging their Defiant JMR demonstrator — which was (and its allies) for the rest of the 21st century. More information based on the Army’s 2013 model performance specification. and links to past articles from each issue of Vertiflite can be found Though not specifically stated, the Defiant X is believed to be at www.vtol.org/FVL. slightly larger than the JMR demonstrator to meet the FLRAA range and payload requirements, and to have growth capability US Army’s FLRAA & FARA for future needs. -
Aviation Week & Space Technology Student Edition
$14.95 JULY 27-AUGUST 16, 2020 FLIGHT PATHS FORWARD CLIMBING OUT OF COVID-19 CEO Interviews Airbus, Boeing and L3Harris U.S. Army’s FVL Plan A Heavy Lift for Industry Pandemic Tests Aviation Week Smallsat Industry Workforce Initiative Supported by: The Wings Club Digital Edition Copyright Notice The content contained in this digital edition (“Digital Material”), as well as its selection and arrangement, is owned by Informa. and its affiliated companies, licensors, and suppliers, and is protected by their respective copyright, trademark and other proprietary rights. Upon payment of the subscription price, if applicable, you are hereby authorized to view, download, copy, and print Digital Material solely for your own personal, non-commercial use, provided that by doing any of the foregoing, you acknowledge that (i) you do not and will not acquire any ownership rights of any kind in the Digital Material or any portion thereof, (ii) you must preserve all copyright and other proprietary notices included in any downloaded Digital Material, and (iii) you must comply in all respects with the use restrictions set forth below and in the Informa Privacy Policy and the Informa Terms of Use (the “Use Restrictions”), each of which is hereby incorporated by reference. Any use not in accordance with, and any failure to comply fully with, the Use Restrictions is expressly prohibited by law, and may result in severe civil and criminal penalties. Violators will be prosecuted to the maximum possible extent. You may not modify, publish, license, transmit (including by way of email, facsimile or other electronic means), transfer, sell, reproduce (including by copying or posting on any network computer), create derivative works from, display, store, or in any way exploit, broadcast, disseminate or distribute, in any format or media of any kind, any of the Digital Material, in whole or in part, without the express prior written consent of Informa. -
Ka-50 Attack Helicopter Acrobatic Flight
24 EUROPEAL'J ROTORCRAFT FORUM Marseilles, France -15th_l i 11 September 1998 ADOS Ka-50 Attack Helicopter Acrobatic Flight Serguey V. Mikheyev, Boris N. Bourtsev, Serguey V. Selemenev Kamov Company, Moscow Region, Russia I. Introduction The Ka-50 attack helicopter is intended to act against both ground and air targets. High maneuverability of the Ka-50 helicopter provides lower own vulnerability in combat. Aerobatic t1ight demonstrates maneuverability of the helicopter. This is effected by validity of the key solution in the helicopter designing. KAMOV Company helicopter experience concentrates in the Ka-50 attack helicopter. The Table No.1 lists basic types of the serial and experimental helicopters which have been developed by K.AJ\10V Company within the 50 years period. This paper consists of presentations on the following subjects: basic technical solutions and aeroelastic phenomena; examination of test t1ight results; maneuverability features; means of aerobatic t1ight monitoring and analysis. 2.Basic technical solutions and aeroelastic phenomena It is very important to have a substantiation of aeromechanical phenomena. This is feasible given adequate mathematical models making possible to explain and forecast : natural frequencies of structures; loads; aeroelastic stability limits ; helicopter performance . KAL'v!OV Company has developed software to simulate a coaxial rotor aeroelasticity [1,2,4,5]. Aeroelastic phenomena to be simulated are shown in the Fig.2 as ( 1-7) lines in the following way: ( 1) - system of equations of rotor blades motion ; (2) - elastic model of coaxial rotor control linkage ; (3) - model of coaxial rotor vortex wake; (4,5,6)- unsteady aerodynamic data of airfoils; (7) - elastic /mass I geometry data of the upper/lower rotor blades and of the hubs. -
Graduation Project September 2020
ISTANBUL TECHNICAL UNIVERSITY FACULTY OF AERONAUTICS AND ASTRONAUTICS PERFORMANCE CALCULATION FOR HELICOPTER BLADE UNDER HOVER CONDITION GRADUATION PROJECT Hüseyin DİKEL Department of Aeronautical Engineering Thesis Advisor: Assis. Prof. Dr. Özge ÖZDEMİR SEPTEMBER 2020 i ISTANBUL TECHNICAL UNIVERSITY FACULTY OF AERONAUTICS AND ASTRONAUTICS PERFORMANCE CALCULATION FOR HELICOPTER BLADE UNDER HOVER CONDITION GRADUATION PROJECT Hüseyin DİKEL (110150005) Department of Aeronautıcal Engineering Thesis Advisor: Assis. Prof. Dr. Özge ÖZDEMİR SEPTEMBER 2020 iii Hüseyin DİKEL, student of ITU Faculty of Aeronautics and Astronautics student ID 110150005, successfully defended the graduation entitled “PERFORMANCE CALCULATION FOR HELICOPTER BLADE UNDER HOVER CONDITION” which he prepared after fulfilling the requirements specified in the associated legislations, before the jury whose signatures are below. Thesis Advisor: Assis. Prof. Dr. Özge ÖZDEMİR .............................. İstanbul Technical University Jury Members: Prof. Dr. Metin Orhan KAYA ............................... İstanbul Technical University Prof. Dr. Zahit MECİTOĞLU ............................... İstanbul Technical University Date of Submission : 07 September 2020 Date of Defense : 14 September 2020 v To my big family, iii iv FOREWORD Önsöz bölümünün içerisindeki metinler 1 satır aralıklı yazılır. Tezin ilk sayfası niteliğinde yazılan önsöz ikisayfayı geçmez. Tezi destekleyen kurumlara ve yardımcı olan kişilere bu kısımdateşekkür edilir. Önsöz metninin altında sağa dayalı olarak -
Identification of Coaxial-Rotors Dynamic Wake Inflow for Flight Dynamics and Aeroelastic Applications
42st European Rotorcraft Forum 2016 IDENTIFICATION OF COAXIAL-ROTORS DYNAMIC WAKE INFLOW FOR FLIGHT DYNAMICS AND AEROELASTIC APPLICATIONS Felice Cardito, Riccardo Gori, Giovanni Bernardini Jacopo Serafini, Massimo Gennaretti Department of Engineering, University Roma Tre, Rome, Italy Abstract This paper presents the development of a linear, finite-state, dynamic perturbation model for wake inflow of coaxial rotors in arbitrary steady flight, based on high-accuracy radial and azimuthal representations. It might conveniently applied in combination with blade element formulations for rotor aeroelastic mod- elling, where three-dimensional, unsteady multiharmonic and localized aerodynamic effects may play a crucial role. The proposed model is extracted from responses provided by an arbitrary high-fidelity CFD solver to perturbations of rotor degrees of freedom and controls. The transfer functions of the multihar- monic responses are then approximated through a rational-matrix approach, which returns a constant coefficient differential operator relating the inflow multiharmonic coefficients to the inputs. The accuracy of the model is tested both for hovering and forward flight by comparison with the wake inflow directly evaluated by the high-fidelity CFD tool for arbitrary inputs. 1. INTRODUCTION ing the need for a tail rotor and its associated shafting and gearboxes. Due to the improved performance they may provide, coaxial rotors are expected to become a common solu- While coaxial rotors have been investigated since the tion for next-generation rotorcraft. -
Future Vertical Lift Takes Off
National Aeronautics Museum of Argentina Future Vertical Lift Takes Off The Sikorsky-Boeing SB>1 Defiant made its first flight on March 21. (Sikorsky-Boeing photo) With FARA underway, the Defiant taking flight, the release of the Pentagon’s FVL budget and a request for information for joint-service FLRAA missions, FVL is accelerating to full speed. By Alan Graham he Sikorsky-Boeing SB>1 Defiant high-speed compound Congress added $75M to the fiscal 2019 budget to kick off the helicopter demonstrator flew for the first time on March FARA program. It also added $20M for the JMR program (as a result T21, just days before the US Army released a request for of lobbying by VFS), a portion of which will be used to expand information (referred to here as a “Sources Sought Notice”) on the flight envelopes of the two demonstrators. The Army expects the Future Long-Range Assault Aircraft (FLRAA). shortly to put the teams under contract for the additional flying. Originally expected by the end of 2017 but delayed by Meanwhile, the Army has added just over $10M to its fiscal 2020 manufacturing challenges and ground-test glitches, the Defiant’s budget request to accelerate FLRAA. Because it is a joint program, 30-minute first flight also came just weeks after the Army released the service will have to seek approval from the Office of the its fiscal 2020 budget request that seeks increased funding for Secretary of Defense to accelerate the program schedule. the medium-utility FLRAA and the armed-scout Future Attack Reconnaissance Aircraft (FARA). -
Rotor Diameter
Scaling Up Success The SB>1 Defiant Joint Multi-Role Technology Demonstrator challenges Sikorsky and Boeing to grow the integrated X2 technologies By Frank Colucci peed and range improvements The SB>1 Defiant JMR Technology Demonstrator scales up Sikorsky X2 rigid coaxial rotor sought by US Army Aviation drove compound helicopter technologies to achieve speed, range and agility far better than SSikorsky, Boeing and their Defiant conventional helicopters. (Sikorsky graphic) team to scale up technologies flown on the 6,000 lb (3 t) X2 and 11,400 lb The MPS summary of FVL-M teams, Sikorsky Innovations vice (5.2 t) S-97 to the 30,000 lb (14 t) class performance includes cruising president Chris Van Buiten previously SB>1 Joint Multi-Role Technology speeds greater than 230 kt (426 stated, “Raider is risk-reduction for JMR.” Demonstrator (JMR-TD). A Systems km/h), vertical takeoff at 6,000 ft/95˚F Sikorsky and Boeing teamed Integration Laboratory (SIL) for Defiant (1,800 m/35˚C) density altitude and up on the SB>1 Defiant in January came on line in December and a a combat radius of 229 nm (424 km) 2013. Boeing program co-director Transmission System Test Bed will run with four crew and 12 troops. The 250 Pat Donnelly said, “When we put in 2016. The JMR-TD due to fly in 2017 is kt (463 km/h) Defiant answers the this together, we were certainly very based on a 2013 Mission Performance specification with rigid coaxial rotors, sensitive to the scaling issues of the Specification (MPS) for a medium-size an integrated tail propeller, optimized X2 technology. -
Assessing the Affordability of the Army's Future Vertical Lift Portfolio
NOVEMBER 2019 Assessing the Affordability of the Army’s Future Vertical Lift Portfolio AUTHORS Rhys McCormick Gregory Sanders Andrew P. Hunter A Report of the CSIS DEFENSE-INDUSTRIAL INITIATIVES GROUP DEFENSE-INDUSTRIAL INITIATIVES GROUP November 2019 Assessing the Affordability of the Army’s Future Vertical Lift Portfolio AUTHORS Rhys McCormick Gregory Sanders Andrew P. Hunter A Report of the CSIS DEFENSE-INDUSTRIAL INITIATIVES GROUP About CSIS Established in Washington, D.C., over 50 years ago, the Center for Strategic and International Studies (CSIS) is a bipartisan, nonprofit policy research organization dedicated to providing strategic in sights and policy solutions to help decisionmakers chart a course toward a better world. In late 2015, Thomas J. Pritzker was named chairman of the CSIS Board of Trustees. Mr. Pritzker succeeded former U.S. senator Sam Nunn (D-GA), who chaired the CSIS Board of Trustees from 1999 to 2015. CSIS is led by John J. Hamre, who has served as president and chief executive officer since 2000. Founded in 1962 by David M. Abshire and Admiral Arleigh Burke, CSIS is one of the world’s preeminent international policy in stitutions focused on defense and security; regional study; and transnational challenges ranging from energy and trade to global development and economic integration. For eight consecutive years, CSIS has been named the world’s number one think tank for defense and national security by the University of Pennsylvania’s “Go To Think Tank Index.” The Center’s over 220 full-time staff and large network of affiliated schol- ars conduct research and analysis and develop policy initiatives that look to Assessing the Affordability of Army’s Future Vertical Lift Portfolio the future and anticipate change.