Foot Launching with Power (This Article Appeared in Hang Gliding Magazine - Oct, 2001) “ 2001 Richard Cobb
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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. -
Download the BHPA Training Guide
VERSION 1.7 JOE SCHOFIELD, EDITOR body, and it has for many years been recognised and respected by the Fédération Aeronautique Internationale, the Royal Aero Club and the Civil Aviation Authority. The BHPA runs, with the help of a small number of paid staff, a pilot rating scheme, airworthiness schemes for the aircraft we fly, a school registration scheme, an instructor assessment and rating scheme and training courses for instructors and coaches. Within your membership fee is also provided third party insurance and, for full annual or three-month training members, a monthly subscription to this highly-regarded magazine. The Elementary Pilot Training Guide exists to answer all those basic questions you have such as: ‘Is it difficult to learn to fly?' and ‘Will it take me long to learn?' In answer to those two questions, I should say that it is no more difficult to learn to fly than to learn to drive a car; probably somewhat easier. We were all beginners once and are well aware that the main requirement, if you want much more than a ‘taster', is commitment. Keep at it and you will succeed. In answer to the second question I can only say that in spite of our best efforts we still cannot control the weather, and that, no matter how long you continue to fly for, you will never stop learning. Welcome to free flying and to the BHPA’s Elementary Pilot Training Guide, You are about to enter a world where you will regularly enjoy sights and designed to help new pilots under training to progress to their first milestone - experiences which only a few people ever witness. -
Gliding Flight
Gliding Flight Whenever an airplane is flying such that the power required is larger than the power available, it will descend rather than climb. In the ultimate situation, there is no power at all; in this case, the airplane will be in gliding. This will occur for a conventional airplane when the engine quits during flight (e.g., engine failure). Also, this is the case for gliders and sailplanes. The force diagram is the higher the L/D, the shallower the glide angle. The smallest equilibrium glide angle occurs at (L/D)max. The equilibrium glide angle does not depend on altitude or wing loading, it simply depends on the lift-to-drag ratio. However, to achieve a given L/D at a given altitude, the aircraft must fly at a specified velocity V, called the equilibrium glide velocity, and this value of V, does depend on the altitude and wing loading, as follows: it depends on altitude (through rho) and wing loading. The value of CL and L/D are aerodynamic characteristics of the aircraft that vary with angle of attack. A specific value of L/D, corresponds to a specific angle of attack which in turn dictates the lift coefficient (CL). If L/ D is held constant throughout the glide path, then CL is constant along the glide path. However, the equilibrium velocity along this glide path will change with altitude, decreasing with decreasing altitude (because rho increases). SERVICE AND ABSOLUTE CEILINGS The highest altitude achievable is the altitude where (R/C)max=0. It is defined as the absolute ceiling that altitude where the maximum rate of climb is zero is in steady, level flight. -
Government of India Office of Director General of Civil Aviation
GOVERNMENT OF INDIA OFFICE OF DIRECTOR GENERAL OF CIVIL AVIATION TECHNICAL CENTRE, OPPOSITE SAFDARJUNG AIRPORT, NEW DELHI CIVIL AVIATION REQUIREMENTS DRAFT SECTION 2 – AIRWORTHINESS SERIES 'O', PART VI F No.11-690/CAR/O-VI/2006/AI (2) ISSUE II DATED __________APRIL 2016 EFFECTIVE: FORTHWITH Subject Manufacture, Registration and Operation of Powered Hang Gliders 1 INTRODUCTION This part of the Civil Airworthiness Requirements specifies requirements relating to, manufacture, registration, maintenance operation and security of powered hang gliders. 1.1 For the purpose of this CAR, a powered hang glider is a vehicle that is used or intended to be used for manual operation in the air by a single occupant/ double 1.1.1 occupant. is used or intended to be used for recreation, sport, or any other purpose approved by 1.1.2 DGCA in writing. 1.1.3 has the maximum AUW less than 275 kgs for a single seater. 1.1.4 has the maximum AUW less than 375 kgs for a double seater. 1.1.5 is not capable of more than 70 knots calibrated air speed at full power in level flight, and 1.1.6 has a power-off stall speed which does not exceed 30 knots calibrated air speed. 2 DEFINITION 2.1 "Acrobatic flight" means manoeuvres intentionally performed by an aircraft involving an abrupt change in its attitude, an abnormal attitude or abnormal variation in speed. 2.2 "Air Traffic Control Clearance" means authorisation by an Air Traffic Control unit for an aircraft to proceed within controlled airspace under specified conditions. 2.3 "Controlled Airport” means an airport at which an Air Traffic Control unit is provided. -
HELICOPTERS (Air-Cushion Vehicles B60V)
CPC - B64C - 2020.02 B64C AEROPLANES; HELICOPTERS (air-cushion vehicles B60V) Special rules of classification The use of the available Indexing Codes under B64C 1/00- B64C 2230/00 is mandatory for classifying additional information. B64C 1/00 Fuselages; Constructional features common to fuselages, wings, stabilising surfaces and the like (aerodynamical features common to fuselages, wings, stabilising surfaces, and the like B64C 23/00; flight-deck installations B64D) Definition statement This place covers: • Overall fuselage shapes and concepts (only documents relating thereto are attributed the symbol B64C 1/00, when the emphasis is on aerodynamic aspects the symbol B64C 1/0009 is attributed). • Structural features (including frames, stringers, longerons, bulkheads, skin panels and interior liners). • Windows and doors (including hatch covers, access panels, drain masts, canopies and windscreens). • Fuselage structures adapted for mounting power plants, floors, integral loading means (such as steps). • Attachment of wing or tail units or stabilising surfaces to the fuselage; • Relatively movable fuselage parts (for improving pilot's view or for reducing size for storage). • Severable/jettisonable parts for facilitating emergency escape. • Inflatable fuselage components. • Fuselage adaptations for receiving aerials or radomes. • Passive cooling of fuselage structures and sound/heat insulation (including isolation mats, and clips for mounting such mats and components such as pipes or cables). References Limiting references This place does not cover: Structural features and concepts are attributed the relevant symbol(s) in B64C 1/06 - B64C 1/12 Aerodynamical features common to fuselages, wings, stabilising B64C 23/00 surfaces, and the like Flight-deck installations B64D Special rules of classification Structures and components for helicopters falling within this main group and/or appended subgroups are additionally attributed the symbol B64C 27/04. -
FAA Regulations of Ultralight Vehicles Sudie Thompson
Journal of Air Law and Commerce Volume 49 | Issue 3 Article 4 1984 FAA Regulations of Ultralight Vehicles Sudie Thompson Follow this and additional works at: https://scholar.smu.edu/jalc Recommended Citation Sudie Thompson, FAA Regulations of Ultralight Vehicles, 49 J. Air L. & Com. 591 (1984) https://scholar.smu.edu/jalc/vol49/iss3/4 This Comment is brought to you for free and open access by the Law Journals at SMU Scholar. It has been accepted for inclusion in Journal of Air Law and Commerce by an authorized administrator of SMU Scholar. For more information, please visit http://digitalrepository.smu.edu. Comments FAA REGULATION OF ULTRALIGHT VEHICLES SUDIE THOMPSON A RELATIVELY NEW form of sport and recreational avi- ation has swept the aviation industry - ultralights. Ul- tralights are the first airplanes to have been developed and marketed as "air recreational vehicle[s]." ' Powered ul- tralights are featherweight planes which cost between $2,800 and $7,000.2 Unpowered ultralights are most frequently called hang gliders.' It is estimated that the worldwide total of powered and unpowered ultralights of all types is 25,000,' and one source predicts that the world total of 20,000, pow- ered ultralights will soon double.5 An October, 1981, article places the Federal Aviation Administration's (FAA) estimate of the number of powered ultralights flying in the United States alone at about 2,500.6 Less than one year later the Experimental Aircraft Association (EAA) and the FAA in- creased their estimates of the number of operational powered and unpowered ultralights (excluding true hang gliders) to 7 10,000. -
Robot Dynamics - Fixed Wing UAS Exercise 1: Aircraft Aerodynamics & Flight Mechanics
Robot Dynamics - Fixed Wing UAS Exercise 1: Aircraft Aerodynamics & Flight Mechanics Thomas Stastny ([email protected]) 2016.11.30 Abstract This exercise analyzes the performance of the Techpod UAV during steady-level and gliding flight con- ditions. A decoupled longitudinal model is further derived from its full six-degrees-of-freedom represen- tation, and the necessary assumptions leading to said model are elaborated. 1 Aircraft Flight Performance Use the parameters given in Table3 and the following environmental and platform specific information to answer the following questions. Do not interpolate, simply take the closest value. Assume the aircraft is in steady conditions (i.e. Bv_ = B! = 0) at all times, and level (i.e. γ = 0), if powered. Enivronment: density ρ = 1:225kg=m3 (assume sea-level values) Aircraft specs: wing area S = 0:39m2, mass m = 2:65kg a) Calculate the minimum level flight speed of the Techpod UAV. Is this a good choice of operating airspeed? As we are assuming steady-level flight conditions, we may equate the lifting force with the force 2 of gravity, i.e. L = 0:5ρV ScL = mg. Solving this equation for airspeed, we see that maximizing cL, i.e. cL = cLmax = 1:125 (from Table3), minimizes speed. s 2mg Vmin = = 9:83m=s ρScLmax As this operating speed would be directly at the stall point of the aircraft, this is a highly dangerous condition. For sure not recommended as an operating speed. b) Suppose the motor fails. What maximum glide ratio can be reached? And at what speed is this maximum achieved? Conveniently, an aircraft's lift-to-drag ratio is numerically equivalent to its glide ratio, whether assuming steady-level (powered) or steady (un-powered / gliding) flight. -
Near-Optimal Guidance Method for Maximizing the Reachable Domain of Gliding Aircraft
Trans. Japan Soc. Aero. Space Sci. Vol. 49, No. 165, pp. 137–145, 2006 Near-Optimal Guidance Method for Maximizing the Reachable Domain of Gliding Aircraft By Takeshi TSUCHIYA Department of Aeronautics and Astronautics, The University of Tokyo, Tokyo, Japan (Received November 16th, 2005) This paper proposes a guidance method for gliding aircraft by using onboard computers to calculate a near-optimal trajectory in real-time, and thereby expanding the reachable domain. The results are applicable to advanced aircraft and future space transportation systems that require high safety. The calculation load of the optimal control problem that is used to maximize the reachable domain is too large for current computers to calculate in real-time. Thus the optimal control problem is divided into two problems: a gliding distance maximization problem in which the aircraft motion is limited to a vertical plane, and an optimal turning flight problem in a horizontal direction. First, the former problem is solved using a shooting method. It can be solved easily because its scale is smaller than that of the original problem, and because some of the features of the optimal solution are obtained in the first part of this paper. Next, in the latter problem, the optimal bank angle is computed from the solution of the former; this is an analytical computation, rather than an iterative computation. Finally, the reachable domain obtained from the proposed near-optimal guidance method is compared with that obtained from the original optimal control problem. Key Words: -
Global Phase Space Structures in a Model of Passive Descent
Global phase space structures in a model of passive descent Gary K. Nave, Jr., Shane D. Ross Engineering Mechanics Program, Virginia Tech Blacksburg, VA, 24061 Abstract Even the most simplified models of falling and gliding bodies exhibit rich nonlinear dy- namical behavior. Taking a global view of the dynamics of one such model, we find an attracting invariant manifold that acts as the dominant organizing feature of trajectories in velocity space. This attracting manifold captures the final, slowly changing phase of every passive descent, providing a higher-dimensional analogue to the concept of terminal velocity, the terminal velocity manifold. Within the terminal velocity manifold in extended phase space, there is an equilibrium submanifold with equilibria of alternating stability type, with different stability basins. In this work, we present theoretical and numerical methods for approximating the terminal velocity manifold and discuss ways to approximate falling and gliding motion in terms of these underlying phase space structures. Keywords: Gliding animals, Invariant manifolds, Gliding flight, Reduced order models, Passive aerodynamics 1. Introduction A wide variety of natural and engineered systems rely on aerodynamic forces for locomo- tion. Arboreal animals use gliding flight to catch prey or escape predators [1], while plant seeds may slowly follow the breeze to increase dispersion [2]. To compare different gliding animals with different morphologies, a variety of studies have resolved detailed motion of animals' glides from videos or other tracking methods [3{7]. Throughout their glide, animals may approach an equilibrium glide, but typically spend at least half of the glide between the initial ballistic descent, where aerodynamic forces are small, and the final equilibrium state when aerodynamic forces completely balance weight [5{7]. -
Flight and Rocketry 139 © Delta Education LLC
Delta Science Reader FFllightight andand RocketryRocketry Delta Science Readers are nonfiction student books that provide science background and support the experiences of hands-on activities. Every Delta Science Reader has three main sections: Think About . , People in Science, and Did You Know? Be sure to preview the reader Overview Chart on page 4, the reader itself, and the teaching suggestions on the following pages. This information will help you determine how to plan your schedule for reader selections and activity sessions. Reading for information is a key literacy skill. Use the following ideas as appropriate for your teaching style and the needs of your students. The After Reading section includes an assessment and writing links. Students will OVERVIEW read about gliding flight, true flight, flying In the Delta Science Reader Flight and vehicles, and rocketry Rocketry, students read about the two types identify the forces in flight—weight, lift, of flight—gliding flight and true flight. They thrust, and drag—and how they act on an learn about both lighter-than-air flight and object in flight heavier-than-air flight and about different types of flying machines, from parachutes read about the history of flight and airships to jets and spacecraft. They examine nonfiction text elements such as find out about the forces at work in flight table of contents, headings, and glossary and how Bernoulli’s principle explains lift. They are also introduced to the Wright interpret photographs and diagrams to brothers, who made the airplane that flew answer questions the first powered, controlled flight. Finally, complete a KWL chart students learn about milestones in the history of flight. -
Vehicle Registration Application Form
Vehicle Registration Application Form NAME_______________________________________________________________________________________________________ last first middle ADDRESS__________________________________________________________________________________________________ CITY ________________________________________________________ STATE ________ ZIP Phone (______) ______________ Date of Birth ____/____/_____ USUA Member # (REQUIRED FOR REGISTRATION) A _______________ This is a ❏new address ❏ new phone number. Please update my records. Instructions for Vehicle Registration 1. Complete and sign the application. Except for signatures, all data should be typewritten or printed legibly. 2. Send completed application and processing fee to USUA. I AM APPLYING FOR: Vehicle Make & Model To Be Registered ❏ New Vehicle Registration ___________________________________________ (Valid only with current USUA membership) Vehicle Manufacturer Name ❏ Custom Numbers (Available only with New Vehicle Registration) ___________________________________________ Vehicle Model Name ❏ Transfer Of Existing Registration (Valid only with current USUA membership) _______________________ _________________ Engine Make/Model Airframe Serial # (if any) Vehicle Description Vehicle Registration Transfer * If Applicable Check items below as applicable: TO NEW OWNER Registration may be transferred to a new owner when the following statement from the previous owner is completed indicating ❏ SINGLE PLACE forfeiture of the registration number. The new owner may then apply ❏ TWO -
Aerodynamics and Flight Dynamics
Aerodynamics The shuttle vehicle was uniquely winged so it could reenter Earth’s atmosphere and fly to assigned nominal or abort landing strips. and Flight The wings allowed the spacecraft to glide and bank like an airplane Dynamics during much of the return flight phase. This versatility, however, did not come without cost. The combined ascent and re-entry capabilities required a major government investment in new design, development, Introduction verification facilities, and analytical tools. The aerodynamic and Aldo Bordano flight control engineering disciplines needed new aerodynamic and Aeroscience Challenges Gerald LeBeau aerothermodynamic physical and analytical models. The shuttle required Pieter Buning new adaptive guidance and flight control techniques during ascent and Peter Gnoffo re-entry. Engineers developed and verified complex analysis simulations Paul Romere that could predict flight environments and vehicle interactions. Reynaldo Gomez Forrest Lumpkin The shuttle design architectures were unprecedented and a significant Fred Martin challenge to government laboratories, academic centers, and the Benjamin Kirk aerospace industry. These new technologies, facilities, and tools would Steve Brown Darby Vicker also become a necessary foundation for all post-shuttle spacecraft Ascent Flight Design developments. The following section describes a US legacy unmatched Aldo Bordano in capability and its contribution to future spaceflight endeavors. Lee Bryant Richard Ulrich Richard Rohan Re-entry Flight Design Michael Tigges Richard Rohan Boundary Layer Transition Charles Campbell Thomas Horvath 226 Engineering Innovations Aeroscience Challenges One of the first challenges in the development of the Space Shuttle was its aerodynamic design, which had to satisfy the conflicting requirements of a spacecraft-like re-entry into the Earth’s atmosphere where blunt objects have certain advantages, but it needed wings that would allow it to achieve an aircraft-like runway landing.