PSAD-76-172 Federal Short Takeoff and Landing Transport Programs
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China's Aircraft Carrier Ambitions
CHINA’S AIRCRAFT CARRIER AMBITIONS An Update Nan Li and Christopher Weuve his article will address two major analytical questions. First, what are the T necessary and suffi cient conditions for China to acquire aircraft carriers? Second, what are the major implications if China does acquire aircraft carriers? Existing analyses on China’s aircraft carrier ambitions are quite insightful but also somewhat inadequate and must therefore be updated. Some, for instance, argue that with the advent of the Taiwan issue as China’s top threat priority by late 1996 and the retirement of Liu Huaqing as vice chair of China’s Central Military Commission (CMC) in 1997, aircraft carriers are no longer considered vital.1 In that view, China does not require aircraft carriers to capture sea and air superiority in a war over Taiwan, and China’s most powerful carrier proponent (Liu) can no longer infl uence relevant decision making. Other scholars suggest that China may well acquire small-deck aviation platforms, such as helicopter carriers, to fulfi ll secondary security missions. These missions include naval di- plomacy, humanitarian assistance, disaster relief, and antisubmarine warfare.2 The present authors conclude, however, that China’s aircraft carrier ambitions may be larger than the current literature has predicted. Moreover, the major implications of China’s acquiring aircraft carriers may need to be explored more carefully in order to inform appropriate reactions on the part of the United States and other Asia-Pacifi c naval powers. This article updates major changes in the four major conditions that are necessary and would be largely suffi cient for China to acquire aircraft carriers: leadership endorsement, fi nancial affordability, a relatively concise naval strat- egy that defi nes the missions of carrier operations, and availability of requisite 14 NAVAL WAR COLLEGE REVIEW technologies. -
A Design Study Me T Rop"Ol Itan Air Transit System
NASA CR 73362 A DESIGN STUDY OF A MET R OP"OL ITAN AIR TRANSIT SYSTEM MAT ir 0 ± 0 49 PREPARED UNDER, NASA-ASEE SUMMER FACULTY FELLOWSHIP PROGRAM ,IN Cq ENGINEERING SYSTEMS DESIGN NASA CONTRACT NSR 05-020-151 p STANFORD UNIVERSITY STANFORD CALIFORNIA CL ceoroducedEAR'C-by thEGHOU AUGUST 1969 for Federal Scientific &Va Tec1nical 2 Information Springfied NASA CR 73362 A DESIGN STUDY OF A METROPOLITAN AIR TRANSIT SYSTEM MAT Prepared under NASA Contract NSR 05-020-151 under the NASA-ASEE Summer Faculty Fellowship Program in Engineering Systems Design, 16 June 29 August, 1969. Faculty Fellows Richard X. Andres ........... ......... ..Parks College Roger R. Bate ....... ...... .."... Air Force Academy Clarence A. Bell ....... ......"Kansas State University Paul D. Cribbins .. .... "North Carolina State University William J. Crochetiere .... .. ........ .Tufts University Charles P. Davis . ... California State Polytechnic College J. Gordon Davis . .... Georgia Institute of Technology Curtis W. Dodd ..... ....... .Southern Illinois University Floyd W. Harris .... ....... .... Kansas State University George G. Hespelt ........ ......... .University of Idaho Ronald P. Jetton ...... ............ .Bradley University Kenneth L. Johnson... .. Milwaukee School of Engineering Marshall H. Kaplan ..... .... Pennsylvania State University Roger A. Keech . .... California State Polytechnic College Richard D. Klafter... .. .. Drexel Institute of Technology Richard S. Marleau ....... ..... .University of Wisconsin Robert W. McLaren ..... ....... University'of Missouri James C. Wambold..... .. Pefinsylvania State University Robert E. Wilson..... ..... Oregon State University •Co-Directors Willi'am Bollay ...... .......... Stanford University John V. Foster ...... ........... .Ames Research Center Program Advisors Alfred E. Andreoli . California State Polytechnic College Dean F. Babcock .... ........ Stanford Research Institute SUDAAR NO. 387 September, 1969 i NOT FILMED. ppECEDING PAGE BLANK CONTENTS Page CHAPTER 1--INTRODUCTION ... -
NASA's Real World: Mathematics
National Aeronautics and Space Administration NASA’s Real World: Mathematics Educator Guide “Preparing for a Soft Landing” Educational Product Educators & Students Grades 6-8 www.nasa.gov NP-2008-09-106-LaRC Preparing For A Soft Landing Grade Level: 6-8 Lesson Overview: Students are introduced to the Orion Subjects: Crew Exploration Vehicle (CEV) and NASA’s plans Middle School Mathematics to return to the Moon in this lesson. Thinking and acting like Physical Science engineers, they design and build models representing Orion, calculating the speed and acceleration of the models. Teacher Preparation Time: 1 hour This lesson is developed using a 5E model of learning. This model is based upon constructivism, a philosophical framework or theory of learning that helps students con- Lesson Duration: nect new knowledge to prior experience. In the ENGAGE section of the lesson, students Five 55-minute class meetings learn about the Orion space capsule through the use of a NASA eClips video segment. Teams of students design their own model of Orion to be used as a flight test model in the Time Management: EXPLORE section. Students record the distance and time the models fall and make sug- gestions to redesign and improve the models. Class time can be reduced to three 55-minute time blocks During the EXPLAIN section, students answer questions about speed, velocity and if some work is completed at acceleration after calculating the flight test model’s speed and acceleration. home. Working in teams, students redesign the flight test models to slow the models by National Standards increasing air resistance in the EXTEND section of this lesson. -
The SKYLON Spaceplane
The SKYLON Spaceplane Borg K.⇤ and Matula E.⇤ University of Colorado, Boulder, CO, 80309, USA This report outlines the major technical aspects of the SKYLON spaceplane as a final project for the ASEN 5053 class. The SKYLON spaceplane is designed as a single stage to orbit vehicle capable of lifting 15 mT to LEO from a 5.5 km runway and returning to land at the same location. It is powered by a unique engine design that combines an air- breathing and rocket mode into a single engine. This is achieved through the use of a novel lightweight heat exchanger that has been demonstrated on a reduced scale. The program has received funding from the UK government and ESA to build a full scale prototype of the engine as it’s next step. The project is technically feasible but will need to overcome some manufacturing issues and high start-up costs. This report is not intended for publication or commercial use. Nomenclature SSTO Single Stage To Orbit REL Reaction Engines Ltd UK United Kingdom LEO Low Earth Orbit SABRE Synergetic Air-Breathing Rocket Engine SOMA SKYLON Orbital Maneuvering Assembly HOTOL Horizontal Take-O↵and Landing NASP National Aerospace Program GT OW Gross Take-O↵Weight MECO Main Engine Cut-O↵ LACE Liquid Air Cooled Engine RCS Reaction Control System MLI Multi-Layer Insulation mT Tonne I. Introduction The SKYLON spaceplane is a single stage to orbit concept vehicle being developed by Reaction Engines Ltd in the United Kingdom. It is designed to take o↵and land on a runway delivering 15 mT of payload into LEO, in the current D-1 configuration. -
ICAO Safety Report |2020
SAFETY Safety Report 2020 Edition Foreword A Coordinated, Risk-based Approach to Improving Global Aviation Safety The air transport industry plays a major role in global economic activity and development. One of the key elements to maintaining the vitality of civil aviation is to ensure safe, secure, efficient and environmentally sustainable operations at the global, regional and national levels. A specialized agency of the United Nations, the International Civil Aviation Organization (ICAO) was established in 1944 to promote the safe and orderly development of international civil aviation throughout the world. ICAO promulgates Standards and Recommended Practices (SARPs) to facilitate harmonized regulations in aviation safety, security, efficiency and environmental protection on a global basis. Today, ICAO manages over 12 000 SARPs across the 19 Annexes and five Procedures for Air Navigation Services (PANS) to the Convention on International Civil Aviation (Chicago Convention), many of which are constantly evolving in tandem with latest developments and innovations. ICAO serves as the primary forum for co-operation in all fields of civil aviation among its 193 Member States. Improving the safety of the global air transport system is ICAO’s guiding and most fundamental strategic objective. The Organization works constantly to address and enhance global aviation safety through the following coordinated activities: • Policy and Standardization; • Monitoring of key safety trends and indicators; • Safety Analysis; and • Implementing programmes to address safety issues. The ICAO Global Aviation Safety Plan (GASP) presents the strategy in support of the prioritization and continuous improvement of aviation safety. The GASP sets the goals and targets and outlines key safety enhancement initiatives (SEIs) aimed at improving safety at the international, regional and national levels. -
Constraints for STOL Operations in South Florida Conurbation Cedric Y
Constraints for STOL Operations in South Florida Conurbation Cedric Y. Justin June 2021 Based on research previously published: Development of a Methodology for Parametric Analysis of STOL Airpark Geo-Density, Robinson et al. AIAA AVIATION 2018 Door-to-Door Travel Time Comparative Assessment for Conventional Transportation Methods and Short Takeoff and Landing On Demand Mobility Concepts, Wei et al. AIAA AVIATION 2018 Wind and Obstacles Impact on Airpark Placement for STOL-based Sub-Urban Air Mobility, Somers et al., AIAA AVIATION 2019 Optimal Siting of Sub-Urban Air Mobility (sUAM) Ground Architectures using Network Flow Formulation, Venkatesh et al, AIAA AVIATION 2020 Comparative Assessment of STOL-based Sub-Urban Air Mobility Operations in Massachusetts and South Florida, Justin et al. AIAA AVIATION 2020 Current Market Segmentation ? VTOL CTOL CTOL CTOL CTOL Capacity ? 200-400+ pax Twin Aisle Are there 120-210 pax scenarios where Single Aisle an intermediate solution using 50-90 pax STOL vehicles and Regional Aircraft sitting in- Design range below 300 nm Commuters between UAM 9-50 pax Flight time below 1.5 hours Thin-Haul and thin-haul 9 to 50 seat capacity operations exists? 4-9 pax Sub-Urban Missions 50-150 nm Air Mobility 4 to 9 revenue-seats Missions below 50 nm Urban Air Mobility 1-4 pax 1 to 4 revenue-seats 50 nm 300 nm 500 nm 3000 nm 6000+ nm Artwork Credit Uber Design Range 2 Introduction • Population, urbanization, and congestion Atlanta, GA Miami, FL Dallas, TX Los Angeles, CA have increased steadily over the past several decades • Increasing delays damage the environment and substantially impact the economy Driving time: 8 min. -
Off Airport Ops Guide
Off Airport Ops Guide TECHNIQUES FOR OFF AIRPORT OPERATIONS weight and balance limitations for your aircraft. Always file a flight plan detailing the specific locations you intend Note: This document suggests techniques and proce- to explore. Make at least 3 recon passes at different levels dures to improve the safety of off-airport operations. before attempting a landing and don’t land unless you’re It assumes that pilots have received training on those sure you have enough room to take off. techniques and procedures and is not meant to replace instruction from a qualified and experienced flight instruc- High Level: Circle the area from different directions to de- tor. termine the best possible landing site in the vicinity. Check the wind direction and speed using pools of water, drift General Considerations: Off-airport operations can be of the plane, branches, grass, dust, etc. Observe the land- extremely rewarding; transporting people and gear to lo- ing approach and departure zone for obstructions such as cations that would be difficult or impossible to reach in trees or high terrain. any other way. Operating off-airport requires high perfor- mance from pilot and aircraft and acquiring the knowledge Intermediate: Level: Make a pass in both directions along and experience to conduct these operations safely takes either side of the runway to check for obstructions and time. Learning and practicing off-airport techniques under runway length. Check for rock size. Note the location of the supervision of an experienced flight instructor will not the touchdown area and roll-out area. Associate land- only make you safer, but also save you time and expense. -
Lockheed Martin F-35 Lightning II Incorporates Many Significant Technological Enhancements Derived from Predecessor Development Programs
AIAA AVIATION Forum 10.2514/6.2018-3368 June 25-29, 2018, Atlanta, Georgia 2018 Aviation Technology, Integration, and Operations Conference F-35 Air Vehicle Technology Overview Chris Wiegand,1 Bruce A. Bullick,2 Jeffrey A. Catt,3 Jeffrey W. Hamstra,4 Greg P. Walker,5 and Steve Wurth6 Lockheed Martin Aeronautics Company, Fort Worth, TX, 76109, United States of America The Lockheed Martin F-35 Lightning II incorporates many significant technological enhancements derived from predecessor development programs. The X-35 concept demonstrator program incorporated some that were deemed critical to establish the technical credibility and readiness to enter the System Development and Demonstration (SDD) program. Key among them were the elements of the F-35B short takeoff and vertical landing propulsion system using the revolutionary shaft-driven LiftFan® system. However, due to X- 35 schedule constraints and technical risks, the incorporation of some technologies was deferred to the SDD program. This paper provides insight into several of the key air vehicle and propulsion systems technologies selected for incorporation into the F-35. It describes the transition from several highly successful technology development projects to their incorporation into the production aircraft. I. Introduction HE F-35 Lightning II is a true 5th Generation trivariant, multiservice air system. It provides outstanding fighter T class aerodynamic performance, supersonic speed, all-aspect stealth with weapons, and highly integrated and networked avionics. The F-35 aircraft -
Splashdown and Post-Impact Dynamics of the Huygens Probe : Model Studies
SPLASHDOWN AND POST-IMPACT DYNAMICS OF THE HUYGENS PROBE : MODEL STUDIES Ralph D Lorenz(1,2) (1)Lunar and Planetary Lab, University of Arizona, Tucson, AZ 85721-0092, USA email: [email protected] (2)Planetary Science Research Institute, The Open University, Milton Keynes, UK ABSTRACT Computer simulations and scale model drop tests are performed to evaluate the splashdown loads of a capsule in nonaqueous liquids, in anticipation of the descent of the ESA Huygens probe on Saturn's moon Titan which may have lakes and seas of liquid hydrocarbons. Deceleration profiles in liquids of low and high viscosity are explored, and how the deceleration record may be inverted to recover fluid physical properties is studied. 1. INTRODUCTION Fig.1 Impression of the Huygens probe descending to a splashdown in a hydrocarbon lake under Titan’s ruddy sky. While the splashdown scenario may be realistic, Saturn's moon Titan appears to be partly covered by the vista is not – Saturn will be on the other side of lakes and seas of organic liquids [1]. The short Titan during Huygens’ descent. Artwork by Mark photochemical lifetime of methane in the atmosphere, Robertson-Tessi and Ralph Lorenz. See which is close to its triple point just as water is on http:://www.lpl.arizona.edu/~rlorenz/titanart/titan1.html Earth, suggests that its continued presence in the atmosphere requires replenishment from a surface or subsurface reservoir. Furthermore, the dominant Little work, however, has been published on spacecraft product of methane photolysis is ethane, which is also splashdown dynamics since the Apollo era ; one a liquid at Titan's 94K surface temperature, and models notable exception being a study of the impact of the predict that an equivalent of several hundred meters Challenger crew module after its disintegration after global depth of ethane should have accumulated over launch. -
Aircraft Requirements for Sustainable Regional Aviation
aerospace Article Aircraft Requirements for Sustainable Regional Aviation Dominik Eisenhut 1,*,† , Nicolas Moebs 1,† , Evert Windels 2, Dominique Bergmann 1, Ingmar Geiß 1, Ricardo Reis 3 and Andreas Strohmayer 1 1 Institute of Aircraft Design, University of Stuttgart, 70569 Stuttgart, Germany; [email protected] (N.M.); [email protected] (D.B.); [email protected] (I.G.); [email protected] (A.S.) 2 Aircraft Development and Systems Engineering (ADSE) BV, 2132 LR Hoofddorp, The Netherlands; [email protected] 3 Embraer Research and Technology Europe—Airholding S.A., 2615–315 Alverca do Ribatejo, Portugal; [email protected] * Correspondence: [email protected] † These authors contributed equally to this work. Abstract: Recently, the new Green Deal policy initiative was presented by the European Union. The EU aims to achieve a sustainable future and be the first climate-neutral continent by 2050. It targets all of the continent’s industries, meaning aviation must contribute to these changes as well. By employing a systems engineering approach, this high-level task can be split into different levels to get from the vision to the relevant system or product itself. Part of this iterative process involves the aircraft requirements, which make the goals more achievable on the system level and allow validation of whether the designed systems fulfill these requirements. Within this work, the top-level aircraft requirements (TLARs) for a hybrid-electric regional aircraft for up to 50 passengers are presented. Apart from performance requirements, other requirements, like environmental ones, Citation: Eisenhut, D.; Moebs, N.; are also included. -
Planetary Basalt Construction Field Project of a Lunar Launch/Landing Pad – PISCES/NASA KSC Project Update R. P. Mueller1 and R
47th Lunar and Planetary Science Conference (2016) 1009.pdf Planetary Basalt Construction Field Project of a Lunar Launch/Landing Pad – PISCES/NASA KSC Project Update R. P. Mueller1 and R. M. Kelso2, R. Romo2, C. Andersen2 1 National Aeronautics & Space Administration (NASA), Kennedy Space Center (KSC), Swamp Works Labora- tory, ) Mail Stop: UB-R, KSC, Florida, 32899, PH (321)867-2557; email: [email protected] 2 Pacific International Space Center for Exploration System (PISCES), 99 Aupuni St, Hilo, HI 96720, PH (808)935-8270; email: [email protected], [email protected], [email protected]. Introduction: odologies for constructing infrastructure and facilities Recently, NASA Headquarters invited PISCES to on the Moon and Mars using in situ materials such as become a strategic partner in a new project called “Ad- planetary basalt material. By using the indigenous ditive Construction with Mobile Emplacement” regolith materials on extra-terrestrial bodies, then the (ACME). The goal of this project is to investigate high mass and corresponding high cost of transporting technologies and methodologies for constructing facili- construction materials (e.g. concrete) can be avoided. ties and surface systems infrastructure on the Moon and At approximately $10,000 per kg launched to Low Mars using planetary basalt material. The first phase of Earth Orbit (LEO) this is a significant cost savings this project is to robotically-build a 20 meter (65-ft) which will make the future expansion of human civili- diameter vertical takeoff, vertical landing (VTVL) zation into space more achievable. Part of the first pad out of local basalt material on the Big Island of phase of the ACME project is to robotically-build a 20 Hawaii. -
Modeling and Analysis of Disc Rotor Wing
© 2020 JETIR March 2020, Volume 7, Issue 3 www.jetir.org (ISSN-2349-5162) MODELING AND ANALYSIS OF DISC ROTOR WING 1 2 3 G. MANJULA , L. BALASUBRAMANYAM , S. JITHENDRA NAIK 1PG scholor, 2Asso.Professor, 3Asso.Professor Mechanical Engineering Department 1P.V.K.K Engineering College, Anantapur, AP, INDIA. Abstract-Disc rotor configuration may be a conceptual design. the aim of the Project is to guage the merits of the DiscRotor concept that combine the features of a retractable rotor system for vertical take-off and landing (VTOL) with an integral, circular wing for high-speed flight. The primary objective of this project is to style such a configuration using the planning software Unigraphics and afterward analyzing the designed structure for its structural strength in analysis software ANSYS. This project deals with the all the required aerodynamic requirements of the rotor configuration. In today’s world most the vtol/stol largely depends upon the thrust vectoring that needs huge amounts of fuel and separate devices like nozzles etc., whose production is extremely much tedious and dear. this is often an effort to use a rotor as within the case of helicopters for vtol/stol thus reducing the foremost of the value though weight would be considered as a hindrance to the project. Keywords: Disc rotor wing, vertical take-off and landing (VTOL), UNIGRAPHICS, ANSYS software, Force, Coefficients, Wall and Wing. I. INTRODUCTION A circular wing, or disc, is that the primary lifting surface of the Disc Rotor aircraft during high-speed flight (approx. 400knots). During the high-speed flight, the disc are going to be fixed (i.e.