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Advanced Coastal Navigation Coast Guard Auxiliary Association Inc. Washington, D. C. First Edition..........................................................................1987 Second Edition .....................................................................1990 Third Edition ........................................................................1999 Fourth Edition.......................................................................2002 ii iii iv v vi Advanced Coastal Navigation TABLE OF CONTENTS Introduction...................................................................................................ix Chapter 1 INTRODUCTION TO COASTAL NAVIGATION . .1-1 Chapter 2 THE MARINE MAGNETIC COMPASS . .2-1 Chapter 3 THE NAUTICAL CHART . .3-1 Chapter 4 THE NAVIGATOR’S TOOLS & INSTRUMENTS . .4-1 Chapter 5 DEAD RECKONING . .5-1 Chapter 6 PILOTING . .6-1 Chapter 7 CURRENT SAILING . .7-1 Chapter 8 TIDES AND TIDAL CURRENTS . .8-1 Chapter 9 RADIONAVIGATION . .9-1 Chapter 10 NAVIGATION REFERENCE PUBLICATIONS . .10-1 Chapter 11 FUEL AND VOYAGE PLANNING . .11-1 Chapter 12 REFLECTIONS . .12-1 Appendix A GLOSSARY . .A-1 INDEX . .Index-1 vii Advanced Coastal Navigation viii intRodUction WELCOME ABOARD! Welcome to the exciting world of completed the course. But it does marine navigation! This is the fourth require a professional atti tude, care- edition of the text Advanced Coastal ful attention to classroom presenta- Navigation (ACN), designed to be tions, and diligence in working out used in con cert with the 1210-Tr sample problems. chart in the Public Education (PE) The ACN course has been course of the same name taught by designed to utilize the 1210-Tr nau - the United States Coast Guard tical chart. It is suggested that this Auxiliary (USCGAUX). Portions of chart be readily at hand so that you this text are also used for the Basic can follow along as you read the Coastal Navigation (BCN) PE text. We recognize that students course. -
Soaring Weather
Chapter 16 SOARING WEATHER While horse racing may be the "Sport of Kings," of the craft depends on the weather and the skill soaring may be considered the "King of Sports." of the pilot. Forward thrust comes from gliding Soaring bears the relationship to flying that sailing downward relative to the air the same as thrust bears to power boating. Soaring has made notable is developed in a power-off glide by a conven contributions to meteorology. For example, soar tional aircraft. Therefore, to gain or maintain ing pilots have probed thunderstorms and moun altitude, the soaring pilot must rely on upward tain waves with findings that have made flying motion of the air. safer for all pilots. However, soaring is primarily To a sailplane pilot, "lift" means the rate of recreational. climb he can achieve in an up-current, while "sink" A sailplane must have auxiliary power to be denotes his rate of descent in a downdraft or in come airborne such as a winch, a ground tow, or neutral air. "Zero sink" means that upward cur a tow by a powered aircraft. Once the sailcraft is rents are just strong enough to enable him to hold airborne and the tow cable released, performance altitude but not to climb. Sailplanes are highly 171 r efficient machines; a sink rate of a mere 2 feet per second. There is no point in trying to soar until second provides an airspeed of about 40 knots, and weather conditions favor vertical speeds greater a sink rate of 6 feet per second gives an airspeed than the minimum sink rate of the aircraft. -
Hang Glider: Range Maximization the Problem Is to Compute the flight Inputs to a Hang Glider So As to Provide a Maximum Range flight
Hang Glider: Range Maximization The problem is to compute the flight inputs to a hang glider so as to provide a maximum range flight. This problem first appears in [1]. The hang glider has weight W (glider plus pilot), a lift force L acting perpendicular to its velocity vr relative to the air, and a drag force D acting in a direction opposite to vr. Denote by x the horizontal position of the glider, by vx the horizontal component of the absolute velocity, by y the vertical position, and by vy the vertical component of absolute velocity. The airmass is not static: there is a thermal just 250 meters ahead. The profile of the thermal is given by the following upward wind velocity: 2 2 − x −2.5 x u (x) = u e ( R ) 1 − − 2.5 . a m R We take R = 100 m and um = 2.5 m/s. Note, MKS units are used through- out. The upwind profile is shown in Figure 1. Letting η denote the angle between vr and the horizontal plane, we have the following equations of motion: 1 x˙ = vx, v˙x = m (−L sin η − D cos η), 1 y˙ = vy, v˙y = m (L cos η − D sin η − W ) with q vy − ua(x) 2 2 η = arctan , vr = vx + (vy − ua(x)) , vx 1 1 L = c ρSv2,D = c (c )ρSv2,W = mg. 2 L r 2 D L r The glider is controlled by the lift coefficient cL. The drag coefficient is assumed to depend on the lift coefficient as 2 cD(cL) = c0 + kcL where c0 = 0.034 and k = 0.069662. -
2.1 ANOTHER LOOK at the SIERRA WAVE PROJECT: 50 YEARS LATER Vanda Grubišic and John Lewis Desert Research Institute, Reno, Neva
2.1 ANOTHER LOOK AT THE SIERRA WAVE PROJECT: 50 YEARS LATER Vanda Grubiˇsi´c∗ and John Lewis Desert Research Institute, Reno, Nevada 1. INTRODUCTION aerodynamically-minded Germans found a way to contribute to this field—via the development ofthe In early 20th century, the sport ofmanned bal- glider or sailplane. In the pre-WWI period, glid- loon racing merged with meteorology to explore ers were biplanes whose two wings were held to- the circulation around mid-latitude weather systems gether by struts. But in the early 1920s, Wolfgang (Meisinger 1924; Lewis 1995). The information Klemperer designed and built a cantilever mono- gained was meager, but the consequences grave— plane glider that removed the outside rigging and the death oftwo aeronauts, LeRoy Meisinger and used “...the Junkers principle ofa wing with inter- James Neeley. Their balloon was struck by light- nal bracing” (von Karm´an 1967, p. 98). Theodore ening in a nighttime thunderstorm over central Illi- von Karm´an gives a vivid and lively account of nois in 1924 (Lewis and Moore 1995). After this the technical accomplishments ofthese aerodynam- event, the U.S. Weather Bureau halted studies that icists, many ofthem university students, during the involved manned balloons. The justification for the 1920s and 1930s (von Karm´an 1967). use ofthe freeballoon was its natural tendency Since gliders are non-powered craft, a consider- to move as an air parcel and thereby afford a La- able skill and familiarity with local air currents is grangian view ofthe phenomenon. Just afterthe required to fly them. In his reminiscences, Heinz turn ofmid-20th century, another meteorological ex- Lettau also makes mention ofthe influence that periment, equally dangerous, was accomplished in experiences with these motorless craft, in his case the lee ofthe Sierra Nevada. -
FAA-H-8083-15, Instrument Flying Handbook -- 1 of 2
i ii Preface This Instrument Flying Handbook is designed for use by instrument flight instructors and pilots preparing for instrument rating tests. Instructors may find this handbook a valuable training aid as it includes basic reference material for knowledge testing and instrument flight training. Other Federal Aviation Administration (FAA) publications should be consulted for more detailed information on related topics. This handbook conforms to pilot training and certification concepts established by the FAA. There are different ways of teaching, as well as performing, flight procedures and maneuvers and many variations in the explanations of aerodynamic theories and principles. This handbook adopts selected methods and concepts for instrument flying. The discussion and explanations reflect the most commonly used practices and principles. Occasionally the word “must” or similar language is used where the desired action is deemed critical. The use of such language is not intended to add to, interpret, or relieve a duty imposed by Title 14 of the Code of Federal Regulations (14 CFR). All of the aeronautical knowledge and skills required to operate in instrument meteorological conditions (IMC) are detailed. Chapters are dedicated to human and aerodynamic factors affecting instrument flight, the flight instruments, attitude instrument flying for airplanes, basic flight maneuvers used in IMC, attitude instrument flying for helicopters, navigation systems, the National Airspace System (NAS), the air traffic control (ATC) system, instrument flight rules (IFR) flight procedures, and IFR emergencies. Clearance shorthand and an integrated instrument lesson guide are also included. This handbook supersedes Advisory Circular (AC) 61-27C, Instrument Flying Handbook, which was revised in 1980. -
Flight Instruments - Rev
Flight Instruments - rev. 9/12/07 Ground Lesson: Flight Instruments Objectives: 1. to understand the flight instruments, and the systems that drive them 2. to understand the pitot static system, and possible erroneous behavior 3. to understand the gyroscopic instruments 4. to understand the magnetic instrument, and the short comings of the instrument Justification: 1. understanding of flight instruments is critical to evaluating proper response in case of failure 2. knowledge of flight instruments is required for the private pilot checkride. Schedule: Activity Est. Time Ground 1.0 Total 1.0 Elements Ground: • overview • pitot-static instruments • gyroscopic instruments • magnetic instrument Completion Standards: 1. when the student exhibits knowledge relating to flight instruments including their failure symptoms 1 of 3 Flight Instruments - rev. 9/12/07 Presentation Ground: pitot-static system 1. overview (1) pitot-static system uses ram- air and static air measurements to produce readings. (2) pressure and temperature effect the altimeter i. remember - “Higher temp or pressure = Higher altitude” ii. altimeters are usually adjustable for non-standard temperatures via a window in the instrument (i) 1” of pressure difference is equal to approximately 1000’ of altitude difference 2. components (1) static ports (2) pitot tube (3) pitot heat (4) alternate static ports (5) instruments - altimeter, airspeed, VSI gyroscopic system 1. overview (1) vacuum :system to allow high-speed air to spin certain gyroscopic instruments (2) typically vacuum engine-driven for some instruments, AND electrically driven for other instruments, to allow back-up in case of system failure (3) gyroscopic principles: i. rigidity in space - gyroscopes remains in a fixed position in the plane in which it is spinning ii. -
TOTAL ENERGY COMPENSATION in PRACTICE by Rudolph Brozel ILEC Gmbh Bayreuth, Germany, September 1985 Edited by Thomas Knauff, & Dave Nadler April, 2002
TOTAL ENERGY COMPENSATION IN PRACTICE by Rudolph Brozel ILEC GmbH Bayreuth, Germany, September 1985 Edited by Thomas Knauff, & Dave Nadler April, 2002 This article is copyright protected © ILEC GmbH, all rights reserved. Reproduction with the approval of ILEC GmbH only. FORWARD Rudolf Brozel and Juergen Schindler founded ILEC in 1981. Rudolf Brozel was the original designer of ILEC variometer systems and total energy probes. Sadly, Rudolph Brozel passed away in 1998. ILEC instruments and probes are the result of extensive testing over many years. More than 6,000 pilots around the world now use ILEC total energy probes. ILEC variometers are the variometer of choice of many pilots, for both competition and club use. Current ILEC variometers include the SC7 basic variometer, the SB9 backup variometer, and the SN10 flight computer. INTRODUCTION The following article is a summary of conclusions drawn from theoretical work over several years, including wind tunnel experiments and in-flight measurements. This research helps to explain the differences between the real response of a total energy variometer and what a soaring pilot would prefer, or the ideal behaviour. This article will help glider pilots better understand the response of the variometer, and also aid in improving an existing system. You will understand the semi-technical information better after you read the following article the second or third time. THE INFLUENCE OF ACCELERATION ON THE SINK RATE OF A SAILPLANE AND ON THE INDICATION OF THE VARIOMETER. Astute pilots may have noticed when they perform a normal pull-up manoeuvre, as they might to enter a thermal; the TE (total energy) variometer first indicates a down reading, whereas the non-compensated variometer would rapidly go to the positive stop. -
ASA Ch 3 the Instrument - Workbook Questions
ASA Ch 3 The Instrument - Workbook Questions 1. The flight instruments are commonly grouped into basic categories based on the a. physical properties they rely on to work. b. whether they are used on the ground or in flight. c. Library of Congress catalog system, Dewey Decimal. 2. The basis of a conventional attitude indicator is a self-erecting a. vertical card mounted on a swivel. b. attitude flag arranged on a diagonal. c. gyroscope spinning on a vertical axis. 3. If the spin axis of the attitude indicator gyroscope moves off the vertical for some reason, the internal mechanism will realign it at a rate of approximately a. 3 degrees per second. b. 3 degrees per minute. c. 3 degrees per hour. 4. Occasionally, the miniature airplane on the attitude indicator may require repositioning while in level flight, due to changes in a. altitude (and corresponding air density). b. pitch attitude (associated with airspeed changes). c. the Earth’s gravitational forces. 5. If the attitude indicator experiences a failure of the power source, it will a. be unusable. b. continue to function if you maintain the same heading. c. still be a valid source of bank attitude. 6. Acceleration of the aircraft may cause the gyroscope to move off vertical, moving the horizon line a. toward the pilot. b. in the direction of the turn. c. to an incorrect position. 7. During a rapid acceleration, the horizon line will move down and the attitude indicator will indicate a false climb. a. True b. False 8. To avoid false indications when speeding up or slowing down, a pilot should increase the instrument scan rate a. -
Finish Your Private Pilot License
THE PRIVATE PILOT LEARNING GUIDE STOPPING A TURN CARDINAL DIRECTIONS Coordinated aileron and rudder pressure in the direction opposite When referencing the magnetic compass or heading indicator, always TURNS the bank will return the airplane to a level attitude. As with the associate one of the eight cardinal directions with the number on roll in the roll out of a bank attitude requires rudder deflection to the indicator. This will assist you in keeping spatially oriented and overcome adverse yaw. Relax elevator back pressure to return to a will be very important later in your training when you must visualize Rolling the airplane into a banked attitude results in a turn. Since the flight path is now curved there is an level pitch attitude as the bank attitude decreases. Neutralize the runway directions and while doing cross country navigation. controls when reaching a level sight picture. acceleration force. The increased force is directly related to the bank attitude used for the turn. A shallow As an aircraft rotates about its longitudinal axis, the lifting force bank attitude results in a slowly changing flight path, creating only a small increase in load factor. also rotates remaining perpendicular to the wingspan. When the airplane is in a bank, this redirected lift causes the airplane to turn. 60o As discussed earlier in this chapter, turning results in a curved flight path and additional load. The increase in load is due to centrifugal 40o force and is present anytime the airplane is turning. The centrifugal force combines with the airplane’s weight resulting in “load” opposite to lift. -
Soaring Forecasts: Digging for Data at NWS Web Sites by Dan Shoemaker, NWS Fort Worth, TX
December 2003 National Weather Service Volume 2, Number 3 Soaring Forecasts: Digging For Data at NWS Web Sites by Dan Shoemaker, NWS Fort Worth, TX The National Weather Service (NWS) sphere alone work to keep their refuge from In this Issue: serves a broad base of aviation users that the everyday world aloft. include soaring pilots. The main sources The soaring community is extensive. Soaring Forecasts: of information are TAFs, from Weather One estimate puts the number around Digging For Data Forecast Offices “WFOs”, numerous 20,000 pilots flying sailplanes, hang gliders, products from the Aviation Weather Cen- and paragliders. As a group, these pilots have at NWS Web Sites ter “AWC” and the computer generated had to hone good meteorological sense to Surface Analysis 1 guidance from the National Centers for maximize their soaring experience. It’s worth Environmental Prediction “NCEP”. noting that sailplanes have soared past the Specific NWS Forecast for soaring are tropopause, and hang gliders and paragliders Volcanic Ash: mainly throughout the southwestern por- have reached altitudes above 18,000 ft. Hang Significant Aviation tion of the US. But but we’ll discuss gliders and paragliders routinely make Hazard 5 weather products and information that unpowered cross country trips of more than assist making soaring forecast for other 100 miles. The current hang glider cross locations, as savvy, resourceful soaring pi- country record is over 400 miles. All by tap- lots, hangliders, and paragliders enjoy im- ping the resources of the free air without a mensely the thrill of letting the atmo- powered assist after release. -
The Inertial Navigation Unit: Teaching Navigation Principles Using a Custom Designed Sensor Package
AC 2008-755: THE INERTIAL NAVIGATION UNIT: TEACHING NAVIGATION PRINCIPLES USING A CUSTOM DESIGNED SENSOR PACKAGE Joe Bradshaw, U.S. Naval Academy Electronics Technician at the US Naval Academy for the Weapons and Systems Engineering Department for 7 years. Design special hardware and develop software for projects and labs. Jack Nicholson, U.S. Naval Academy Page 13.1241.1 Page © American Society for Engineering Education, 2008 The Inertial Navigation Unit: Teaching Navigation Principles using a Custom Designed Sensor Package Abstract This paper describes the application and design of a small, inexpensive inertial navigation unit (INU) created to introduce systems engineering students at the United States Naval Academy (USNA) to the principles of navigation systems and to act as a navigation sensor for robotic and autonomous vehicle projects. The INU has been used in place of a multitude of standard navigation sensors such as an inertial measurement unit (IMU), magnetic compass module, and Global Positioning System (GPS) receiver. Its integrated design simplifies mechanical mounting, reduces navigation system weight and size, simplifies data interfacing with a control computer, and provides great flexibility for reconfiguring to meet a variety of engineering education objectives. The INU is capable of firmware upgrades and algorithm enhancements in the field via in-circuit programming, enhancing its longevity as a useful educational tool. In addition, a variety of controllers or a personal computer (PC) can communicate with the INU board through a standard RS-232C serial interface. This compact unit provides good system performance at a reasonable cost compared to most commercially available units. These features enable hands-on education techniques in the navigation aspects of robotics, examples of which are presented. -
1 Altimeter and Compass Watch Instruction Manual Overview Features • Hour, Minute, Second, Year, Month, Day, Day of Week •
Altimeter and Compass Watch Instruction Manual Overview Figure 1 LCD display description Features • Hour, minute, second, year, • Auto calendar • 12/24 hour format display month, day, day of week • Daily alarm • Dual time • Stopwatch • Difference measurement of • Countdown timer • Altimeter – Barometer Use Altimeter and Barometer • 24 hour memory in • Logbook and logbook • 4 day memory in Barometer Altimeter history • Current absolute • Sea level pressure • Temperature display atmospheric • Electro – luminescent back • Compass • Low battery indicator lighted LCD • Diagnostics (System Reset) Care and Maintenance • Protect your watch from shocks, extreme heat and directly exposure to sunlight. • Don’t try to remove the housing or button of the watch. • Don’t insert any object into the watch. • Always put the watch in a clear, dry and room temperature environment when the watch is not used. • Follow the procedure discussed in the manual only. • Make sure the area around the sensors is free of dust or strong chemical. 1 Quick Reference Guide Figure 2 Quick Reference Guide 2 Time Time Main Mode Path Press (S1) until the mode indicator points to the “TIME” Field 1 Day of week, barometer trend indicator Field 2 Hour, Minute, Second Field 3 Month, day Second animation Outer Circumference Adjust o Hold (S2) for 1 second, the second digit will begin to flash o Press (S2) to select second minute hour 12/24hour year month day o Press (S3) or (S4) to set the function o Press (S1) to accept the setting Daily Alarm Path Press (S2) ×1 from Time Main Mode Field 1 “ON” or “OFF” Field 2 Time of a particular alarm Current time Field 3 Adjust o Press (S3) or (S4) to select the alarm number o Hold (S2) for 1 second, the “ON” or “OFF” will begin to flash o Press (S2) to select “ON” or “OFF” hour minute o Press (S3) or (S4) to set the function o Press (S1) to accept the setting Note “ ” will be displayed when any alarm is enabled.