Raven SAR Rotorcraft Advanced Rotor Control Concept

Total Page:16

File Type:pdf, Size:1020Kb

Raven SAR Rotorcraft Advanced Rotor Control Concept Raven SAR Rotorcraft Advanced Rotor Control Concept Alfred Gessow Rotorcraft Center Department of Aerospace Engineering University of Maryland, College Park Maryland, 20742 University of Maryland Alfred Gessow Rotorcraft Center Department of Aerospace Engineering University of Maryland, College Park Maryland, 20742 Raven SAR Rotorcraft In response to the 2001 Annual AHS International Student Design Competition – Graduate Category 21 June 2001 Matthew Tarascio – Team Leader Dr. Inderjit Chopra – Faculty Advisor Marc Gervais Gaurav Gopalan Tim Gowen Kristi Kleinhesselink Jun Ma Kiran Singh Yong-sheng Zhao Acknowledgements The Terp Works design team would like to thank all of the people that assisted us during the 2001 AHS design competition. First and foremost, we would like to express our sincerest thanks to the faculty members that graciously offered their support throughout the entire project, including Dr. Marat Tishchenko, Dr. Alfred Gessow, Dr. V. T. Nagaraj, and Dr. Inderjit Chopra. We would also like to thank our fellow students who offered us their support, particularly Taeoh Lee, Jayanarayanan Sitaraman and Harsha Prahlad. And finally, we would like to send a special thanks to the SAR operators who took the time to respond to our questions, including Philip Hogan (Senior Helicopter Paramedic – Victorian Air Ambulance), Chris Snyder (Director of Coast Guard and Federal Programs – Agusta Westland), Daniel Tyler (SAR/EMS Senior Pilot – Care Flight Services), Lieutenant Strumm (Pilot – NAS Patuxent River SAR), Lieutenant Gancayco (Pilot – NAS Patuxent River SAR), AMHC Robert Mirabal (Crew Chief – NAS Patuxent River SAR), AT1 Jason Van Buren (Rescue Swimmer – NAS Patuxent River SAR), and HM2 Jason Owen (Medical Technician – NAS Patuxent River SAR). 2001 AHS Design Proposal Page i Table of Contents ACKNOWLEDGEMENTS ................................................................................................................................................................... I TABLE OF CONTENTS ...................................................................................................................................................................... II EXECUTIVE SUMMARY ................................................................................................................................................................. VI SECTION 1 – INTRODUCTION .......................................................................................................................................................... 1 SECTION 2 – SAR MISSION RESPONSIVENESS ............................................................................................................................. 1 2.1 – DESIGN PHILOSOPHY ....................................................................................................................................................................................1 2.2 – SAR MISSION STUDY ....................................................................................................................................................................................1 2.2.1 – General SAR Mission Requirements ...................................................................................................................................................................... 2 2.2.2 – Mission Profile (RFP Defined) .............................................................................................................................................................................. 2 2.2.3 – Mission Launch Requirements ............................................................................................................................................................................... 2 2.2.4 – Mission Constraints ................................................................................................................................................................................................ 3 2.2.5 – SAR Operator Suggestions ..................................................................................................................................................................................... 4 2.3 – SAR DESIGN DRIVERS ..................................................................................................................................................................................5 SECTION 3 – CONFIGURATION DESIGN AND DEVELOPMENT ................................................................................................. 6 3.1 – DESIGN METHODOLOGY ...............................................................................................................................................................................6 3.2 – INITIAL CONCEPT SELECTION .......................................................................................................................................................................6 3.2.1 – Candidate Configurations ...................................................................................................................................................................................... 6 3.2.2 – Evaluation Criteria ................................................................................................................................................................................................. 6 3.2.3 – Weighting Factors ................................................................................................................................................................................................... 6 3.2.4 – Concept Evaluation ................................................................................................................................................................................................. 7 3.2.5 – Preliminary Concept Assessment ........................................................................................................................................................................... 7 3.3 – CONFIGURATION TRADE STUDIES ................................................................................................................................................................7 3.3.1 – Historical Database ................................................................................................................................................................................................ 7 3.3.2 – Mission Profile ........................................................................................................................................................................................................ 8 3.3.3 – Methodology ............................................................................................................................................................................................................ 8 3.3.4 – Analysis Limitations ................................................................................................................................................................................................ 9 3.3.5 – Design Parameters & Code Validation ................................................................................................................................................................. 9 3.3.6 – Measures of Effectiveness / Efficiency ................................................................................................................................................................. 10 3.3.7 – Trade Study Results............................................................................................................................................................................................... 11 3.4 – FINAL CONFIGURATION SELECTION ........................................................................................................................................................... 14 SECTION 4 – RAVEN DESIGN FEATURES AND PERFORMANCE SUMMARY ........................................................................ 16 SECTION 5 – MAIN ROTOR AND HUB DESIGN............................................................................................................................ 17 5.1 – BASELINE ROTOR DESIGN .......................................................................................................................................................................... 17 5.1.1 – Diameter ................................................................................................................................................................................................................ 17 5.1.2 – Tip Speed and Tip Shape ...................................................................................................................................................................................... 17 5.1.3 – Solidity ................................................................................................................................................................................................................... 17 5.1.4 – Twist and Taper..................................................................................................................................................................................................... 18 5.1.5 – Number of Blades .................................................................................................................................................................................................
Recommended publications
  • 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.
    [Show full text]
  • NASA Mars Helicopter Team Striving for a “Kitty Hawk” Moment
    NASA Mars Helicopter Team Striving for a “Kitty Hawk” Moment NASA’s next Mars exploration ground vehicle, Mars 2020 Rover, will carry along what could become the first aircraft to fly on another planet. By Richard Whittle he world altitude record for a helicopter was set on June 12, 1972, when Aérospatiale chief test pilot Jean Boulet coaxed T his company’s first SA 315 Lama to a hair-raising 12,442 m (40,820 ft) above sea level at Aérodrome d’Istres, northwest of Marseille, France. Roughly a year from now, NASA hopes to fly an electric helicopter at altitudes equivalent to two and a half times Boulet’s enduring record. But NASA’s small, unmanned machine actually will fly only about five meters above the surface where it is to take off and land — the planet Mars. Members of NASA’s Mars Helicopter team prepare the flight model (the actual vehicle going to Mars) for a test in the JPL The NASA Mars Helicopter is to make a seven-month trip to its Space Simulator on Jan. 18, 2019. (NASA photo) destination folded up and attached to the underbelly of the Mars 2020 Rover, “Perseverance,” a 10-foot-long (3 m), 9-foot-wide (2.7 The atmosphere of Mars — 95% carbon dioxide — is about one m), 7-foot-tall (2.13 m), 2,260-lb (1,025-kg) ground exploration percent as dense as the atmosphere of Earth. That makes flying at vehicle. The Rover is scheduled for launch from Cape Canaveral five meters on Mars “equal to about 100,000 feet [30,480 m] above this July on a United Launch Alliance Atlas V rocket and targeted sea level here on Earth,” noted Balaram.
    [Show full text]
  • Design, Modelling and Control of a Space UAV for Mars Exploration
    Design, Modelling and Control of a Space UAV for Mars Exploration Akash Patel Space Engineering, master's level (120 credits) 2021 Luleå University of Technology Department of Computer Science, Electrical and Space Engineering Design, Modelling and Control of a Space UAV for Mars Exploration Akash Patel Department of Computer Science, Electrical and Space Engineering Faculty of Space Science and Technology Luleå University of Technology Submitted in partial satisfaction of the requirements for the Degree of Masters in Space Science and Technology Supervisor Dr George Nikolakopoulos January 2021 Acknowledgements I would like to take this opportunity to thank my thesis supervisor Dr. George Nikolakopoulos who has laid a concrete foundation for me to learn and apply the concepts of robotics and automation for this project. I would be forever grateful to George Nikolakopoulos for believing in me and for supporting me in making this master thesis a success through tough times. I am thankful to him for putting me in loop with different personnel from the robotics group of LTU to get guidance on various topics. I would like to thank Christoforos Kanellakis for guiding me in the control part of this thesis. I would also like to thank Björn Lindquist for providing me with additional research material and for explaining low level and high level controllers for UAV. I am grateful to have been a part of the robotics group at Luleå University of Technology and I thank the members of the robotics group for their time, support and considerations for my master thesis. I would also like to thank Professor Lars-Göran Westerberg from LTU for his guidance in develop- ment of fluid simulations for this master thesis project.
    [Show full text]
  • Real-Time Helicopter Flight Control: Modelling and Control by Linearization and Neural Networks
    Purdue University Purdue e-Pubs Department of Electrical and Computer Department of Electrical and Computer Engineering Technical Reports Engineering August 1991 Real-Time Helicopter Flight Control: Modelling and Control by Linearization and Neural Networks Tobias J. Pallett Purdue University School of Electrical Engineering Shaheen Ahmad Purdue University School of Electrical Engineering Follow this and additional works at: https://docs.lib.purdue.edu/ecetr Pallett, Tobias J. and Ahmad, Shaheen, "Real-Time Helicopter Flight Control: Modelling and Control by Linearization and Neural Networks" (1991). Department of Electrical and Computer Engineering Technical Reports. Paper 317. https://docs.lib.purdue.edu/ecetr/317 This document has been made available through Purdue e-Pubs, a service of the Purdue University Libraries. Please contact [email protected] for additional information. Real-Time Helicopter Flight Control: Modelling and Control by Linearization and Neural Networks Tobias J. Pallett Shaheen Ahmad TR-EE 91-35 August 1991 Real-Time Helicopter Flight Control: Modelling and Control by Lineal-ization and Neural Networks Tobias J. Pallett and Shaheen Ahmad Real-Time Robot Control Laboratory, School of Electrical Engineering, Purdue University West Lafayette, IN 47907 USA ABSTRACT In this report we determine the dynamic model of a miniature helicopter in hovering flight. Identification procedures for the nonlinear terms are also described. The model is then used to design several linearized control laws and a neural network controller. The controllers were then flight tested on a miniature helicopter flight control test bed the details of which are also presented in this report. Experimental performance of the linearized and neural network controllers are discussed.
    [Show full text]
  • National Rappel Operations Guide
    National Rappel Operations Guide 2019 NATIONAL RAPPEL OPERATIONS GUIDE USDA FOREST SERVICE National Rappel Operations Guide i Page Intentionally Left Blank National Rappel Operations Guide ii Table of Contents Table of Contents ..........................................................................................................................ii USDA Forest Service - National Rappel Operations Guide Approval .............................................. iv USDA Forest Service - National Rappel Operations Guide Overview ............................................... vi USDA Forest Service Helicopter Rappel Mission Statement ........................................................ viii NROG Revision Summary ............................................................................................................... x Introduction ...................................................................................................... 1—1 Administration .................................................................................................. 2—1 Rappel Position Standards ................................................................................. 2—6 Rappel and Cargo Letdown Equipment .............................................................. 4—1 Rappel and Cargo Letdown Operations .............................................................. 5—1 Rappel and Cargo Operations Emergency Procedures ........................................ 6—1 Documentation ................................................................................................
    [Show full text]
  • Adventures in Low Disk Loading VTOL Design
    NASA/TP—2018–219981 Adventures in Low Disk Loading VTOL Design Mike Scully Ames Research Center Moffett Field, California Click here: Press F1 key (Windows) or Help key (Mac) for help September 2018 This page is required and contains approved text that cannot be changed. NASA STI Program ... in Profile Since its founding, NASA has been dedicated • CONFERENCE PUBLICATION. to the advancement of aeronautics and space Collected papers from scientific and science. The NASA scientific and technical technical conferences, symposia, seminars, information (STI) program plays a key part in or other meetings sponsored or co- helping NASA maintain this important role. sponsored by NASA. The NASA STI program operates under the • SPECIAL PUBLICATION. Scientific, auspices of the Agency Chief Information technical, or historical information from Officer. It collects, organizes, provides for NASA programs, projects, and missions, archiving, and disseminates NASA’s STI. The often concerned with subjects having NASA STI program provides access to the NTRS substantial public interest. Registered and its public interface, the NASA Technical Reports Server, thus providing one of • TECHNICAL TRANSLATION. the largest collections of aeronautical and space English-language translations of foreign science STI in the world. Results are published in scientific and technical material pertinent to both non-NASA channels and by NASA in the NASA’s mission. NASA STI Report Series, which includes the following report types: Specialized services also include organizing and publishing research results, distributing • TECHNICAL PUBLICATION. Reports of specialized research announcements and feeds, completed research or a major significant providing information desk and personal search phase of research that present the results of support, and enabling data exchange services.
    [Show full text]
  • Measurement of Blade Deflection of an Unmanned Intermeshing Rotor Helicopter
    Measurement of Blade Deflection of an Unmanned Intermeshing Rotor Helicopter Andreas E. Voigt Johann C. Dauer Florian Knaak Research scientist Research scientist Graduate student DLR DLR DLR Braunschweig, Germany Braunschweig, Germany Braunschweig, Germany ABSTRACT The dynamic behavior of intermeshing rotor blades is complex and subjected to rotor-rotor-interactions like oblique blade-vortex and blade-wake interactions. To gain a better understanding of these effects a blade deflection measurement method is proposed in this paper. The method is based on a single camera per rotor blade depicting the rotor blade from a position fixed to the rotor head. Due to the mounting position of the camera close to the rotational plane the method is called In-Plane Blade Deflection Measurement (IBDM). The basic principles, data processing and measurement accuracy are presented in the paper. The major advantages of the proposed method are the applicability to both, flight and wind tunnel trials, as well as the usability for multi-rotor configurations having a significant rotor overlap. Furthermore comparisons to other blade deflection measurement methods are presented. Finally, experimental data of a flight test of an unmanned intermeshing helicopter is presented. conventional rotor configurations such data is even NOTATION rarer and only wind tunnel measurements of a coaxial rotor configuration are published in [5]. These non- A Rotor area, A=R², m² conventional rotor configurations like coaxial or c Profile chord length, m intermeshing rotors exhibit an inherent rotor-rotor- interaction as well as oblique blade-vortex interactions. CT Thrust coefficient, CT = P/(A(R)²) These dynamic effects lead to more complex and NB Number of blades dynamic air loads compared to conventional configurations and could significantly influence the P Power, W blade deflection.
    [Show full text]
  • 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 ........................................
    [Show full text]
  • Sikorsky S70i CAL FIRE HAWK Fact Sheet
    SIKORSKY S70i CAL FIRE HAWK CALIFORNIA DEPARTMENT OF FORESTRY & FIRE PROTECTION AVIATION PROGRAM MANUFACTURER CREW Sikorsky Aircraft, Stratford, Connecticut (Built in Mielec, Poland) One pilot, two Helitack Captains, an operations supervisor, and up to AIRCRAFT FIRE BUILD-UP nine personnel. United Rotorcraft, Englewood, Colorado PAYLOAD ORIGINAL OWNER Fixed tank - 1000 gallons of water/foam with pilot controlled drop volumes. CAL FIRE, 2019 ACQUIRED BY CAL FIRE SPECIFICATIONS Gross Weight: Internal 22,000 lbs./ In 2018 CAL FIRE received approval from the Governor’s Office to purchase External 23,500 lbs. up to 12 new Sikorsky S70i firefighting helicopters from United Rotorcraft. Cruise Speed: 160 mph These new generation helicopters will replace CAL FIRE’s aging fleet of Night Vision Capable 12 Super Huey Helicopters. The new generation of S70i CAL FIRE HAWK Range: 250 miles helicopters will bring enhanced capabilities including flight safety, higher Endurance: 2.5 hours payloads, increased power margins, and night flying capabilities. Rotor Diameter: 53 feet and 8 inches Engines: Twin turbine engine, T700-GE701D MISSION The CAL FIRE HAWK’s primary mission is responding to initial attack wildfires and rescue missions. When responding to wildfires, the helicopter can quickly deliver up to a 9-person Helitack Crew for ground firefighting operations and quickly transition into water/foam dropping missions. The helicopters are also used for firing operations using either a Helitorch or a Chemical Ignition Device System (CIDS) on wildland fires or prescribed burns, transporting internal cargo loads, mapping, medical evacuations and numerous non-fire emergency missions. The CAL FIRE HAWK is also equipped with an external hoist for rescue missions.
    [Show full text]
  • Over Thirty Years After the Wright Brothers
    ver thirty years after the Wright Brothers absolutely right in terms of a so-called “pure” helicop- attained powered, heavier-than-air, fixed-wing ter. However, the quest for speed in rotary-wing flight Oflight in the United States, Germany astounded drove designers to consider another option: the com- the world in 1936 with demonstrations of the vertical pound helicopter. flight capabilities of the side-by-side rotor Focke Fw 61, The definition of a “compound helicopter” is open to which eclipsed all previous attempts at controlled verti- debate (see sidebar). Although many contend that aug- cal flight. However, even its overall performance was mented forward propulsion is all that is necessary to modest, particularly with regards to forward speed. Even place a helicopter in the “compound” category, others after Igor Sikorsky perfected the now-classic configura- insist that it need only possess some form of augment- tion of a large single main rotor and a smaller anti- ed lift, or that it must have both. Focusing on what torque tail rotor a few years later, speed was still limited could be called “propulsive compounds,” the following in comparison to that of the helicopter’s fixed-wing pages provide a broad overview of the different helicop- brethren. Although Sikorsky’s basic design withstood ters that have been flown over the years with some sort the test of time and became the dominant helicopter of auxiliary propulsion unit: one or more propellers or configuration worldwide (approximately 95% today), jet engines. This survey also gives a brief look at the all helicopters currently in service suffer from one pri- ways in which different manufacturers have chosen to mary limitation: the inability to achieve forward speeds approach the problem of increased forward speed while much greater than 200 kt (230 mph).
    [Show full text]
  • Drone-Acharya
    Drone-acharya Submitted in Response to the Real World Design Challenge Submitted by Samaritan Aerospace Incorporated Submitted on 3 April 2020 Team Members’ Names Name Grade Age Email ID Phone number Aditya Swaminathan 10 15 [email protected] +992 937543494 Advitya Singhal 10 16 [email protected] +91 8527076270 Ashvin Verma 10 16 [email protected] +91 9650737950 ​ Karan Handa 12 17 [email protected] +91 9717096675 Siddhansh Narang 10 16 [email protected] +91 9650411440 Om Gupta 12 18 [email protected] +91 9810419992 Zohaib Ehtesham 11 17 [email protected] +91 8791002411 Delhi Public School, R.K. Puram Kaifi Azmi Marg, Sector 12, R.K. Puram, New Delhi, India Q.S.I. International School of Dushanbe Sovetskaya 26, Dushanbe, Tajikistan Coach: Mr. Ajay Goel: [email protected]; affiliated with D.P.S. R.K. Puram ​ ​ ​ ​ Team/Coach Validating Signatures: Participating students/team members completed Formative Surveys: Mr. Ajay Goel Advitya Singhal (Coach) Karan Handa Ashvin Verma Aditya Swaminathan Zohaib Ehtesham Om Gupta Siddhansh Narang FY20 State Real World Design Challenge Page 2 Table of Contents Executive Summary 6 Specification Sheet 7 1. Team Engagement 7 1.1 Team Formation and Project Operation 7 ​ 1.2 Acquiring and Engaging Mentors 9 ​ 1.3 State the Project Goal 10 ​ 1.4 Tool Set-up/Learning/Validation 11 ​ 1.5 Impact on STEM 12 ​ 2. Document the System Design 13 ​ 2.1 Conceptual, Preliminary, and Detailed Design 13 ​ ​ 2.2 Selection of System Components 38 ​ 2.3 Component Placement and Complete Flight Vehicle Weight and Balance 47 ​ 2.4 Operational Maneuver Analysis 48 ​ 2.5 Three View of Final Design 57 ​ 3.
    [Show full text]
  • Mamala Bay Study Infectious Disease Public
    MAMALA BAY STUDY INFECTIOUS DISEASE PUBLIC HEALTH RISK ASSESSMENT PROJECT MB—b Principal Investigators: Robert C. Cooper, Ph.D. Adam W. Olivieri, Dr. P.H., P.E. EOA, Inc. 1410 Jackson Street Oakland, California 94612 AUGUST 31, 1995 (Revision of report dated June 12, 1995) EXECUTIVE SUMMARY The Mamala Bay Study Commission is conducting a comprehensive study of the sources and effects of point and non-point pollution in Mamala Bay. The study will result in recommendations for strategies to reduce pollution levels in Mamala Bay to protect human health and the marine environment. EOA, Inc. (EOA) was retained by PRC Environmental Management, Inc. (PRC) to perform an assessment of the public health risk associated with accidental exposure to microbial pathogens during recreational use of Mamala Bay waters. The primary objectives of this project were to: 1) apply an existing quantitative microbial risk assessment model to estimate the level of microbial risk associated with recreational exposure to Mamala Bay waters; 2) evaluate how public health risk could change with order of magnitude variations in contribution of pathogen to the swimming/surfing area from sources other than shedding by swimmers/surfers; 3) identify important parameters that impact the risk assessment results. The risk assessment model used for this project is based closely on models used in infectious disease epidemiology. Advantages of this type of model include that it can be used to integrate and organize diverse data bearing on disease risk, account for immunity to disease, model aspects of the transmission dynamics of the agent in the environment and explicitly acknowledge the uncertainty and variability in the many parameter values characteristic of comprehensive models.
    [Show full text]