Physiological Effects During Aerobatic Flights on Science Astronaut Candidates
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
Ff 89/6 Copy
$3 vol libre • free flight 6/89 Dec - Jan POTPOURRI SAC was informed by Sport Canada on the 10th of July that we are not eligible for funding for 1989-90 and until further notice. Thus we are now totally on our own. The average yearly grant from 1979 to 1988 in 1989 dollars was $14,000, or $16 per person. Perhaps it’s a good thing as planning in an atmosphere of doubt is not conducive to good health and efficient use of funds. The cutback was not unexpected and steps were taken early on to ease the effects of this loss of revenue. Imaginative planning in our small store and a good response from our members through the use of the “Soaring Stuff” inserts resulted in in- creased sales. We will also receive higher than projected invest- ment income essentially due to careful cash management and short-term interest rates, which have remained higher for longer than generally expected. In addition, a small gain in projected receipts from an unexpected increase in membership – now at 1423 – which is the first time since 1982 that we have passed 1400. Total expenditures should come in well below budget projection, primarily as a result of scaling back meetings and travel expenditures. On balance it seems fair to say that a combination of some tight fistedness on the expenditure side and a bit of luck on the revenue side will leave SAC in a financially stronger position than was expected at the beginning of the season, despite the cutting off of govern- ment funding. -
Safety Consideration on Liquid Hydrogen
Safety Considerations on Liquid Hydrogen Karl Verfondern Helmholtz-Gemeinschaft der 5/JULICH Mitglied FORSCHUNGSZENTRUM TABLE OF CONTENTS 1. INTRODUCTION....................................................................................................................................1 2. PROPERTIES OF LIQUID HYDROGEN..........................................................................................3 2.1. Physical and Chemical Characteristics..............................................................................................3 2.1.1. Physical Properties ......................................................................................................................3 2.1.2. Chemical Properties ....................................................................................................................7 2.2. Influence of Cryogenic Hydrogen on Materials..............................................................................9 2.3. Physiological Problems in Connection with Liquid Hydrogen ....................................................10 3. PRODUCTION OF LIQUID HYDROGEN AND SLUSH HYDROGEN................................... 13 3.1. Liquid Hydrogen Production Methods ............................................................................................ 13 3.1.1. Energy Requirement .................................................................................................................. 13 3.1.2. Linde Hampson Process ............................................................................................................15 -
Circular Administration
Advisory US.Depanment 01 Tronsporlolion Federal Aviation Circular Administration Subject: A HAZARD IN AEROBATICS: Date: 2/28/84 At No: 91-61 EFFECTS OF G-FORCES ON PILOTS Initiated by: AFO- 800 ; Change: AAM-500; AAC-100 1. PURPOSE. Because aerobatic flying subjects pilots to gravitational effects (G's) that can impair their ability to safely operate the aircraft, pilots who engage in aerobatics, or those who would take up such activity, should understand G's and some of their physiological effects. This circular provides background information on G's, their effect on the human body, and their role in safe flying. Suggestions are offered for avoiding problems caused by accelerations encountered in aerobatic maneuvers. 2. BACKGROUND. Aerobatic flying demands the best of both aircraft and pilot. The aircraft must be highly maneuverable, yet tolerant of G-loads. The pilot must possess skill and physiological stamina. He or she must be daring, yet mindful of the aircraft's limitations as well as his or her own. Federal Aviation Administration (FAA) Advisory Circular No. 91-48, "Acrobatics-Precision Flying with a Purpose," dated June 29, 1977, discusses some of the airworthiness and operational aspects of aerobatics, but does not consider biomedical factors. The most important of these biomedical factors is the pilot's response to accelerations (or G-loading). The major physiological effects of G-loaaing vary from reduced vision to loss of consciousness. The pilot who understands these effects will be better able to cope with them so that he or she can continue the sport of aerobatic flying. J. -
Stearman Aerobatics
( SFA'OUIFI" OCIOBEF1990 3 AEROBATICS U.S.NAVY Fep ntedlbm: U.S.NAVY PRIMARY FLIGHT TFAINING MANUAL 1 Juy, I945 NAVALAIF TRAINING COMMAND CHIEFOF NAVALAIB PRIMAFYIFAINING o sFA 'OUrFrr'. @TOAEB1990 5 AEROBATICS Import it Regsrdl6 oI sherhd o! not . part.llar manelver lsdecrib€d in th€ lollowlngp!s.i you aE to prc. Youare now !e.dy lor rhar shse in yrlr tEinlnsas a Nav.l dc. only thosemaneuveB d€m6nst6i.d .nd p@scdbedby Aviarlor rowad {hlch you have been lookins loMad wlrh you LndrucrorIn rh2 oda preserr€dby ih€ syllabus keenanricLp,rion, p€rhars nor unmix€dwih 5omeI€€tinqs ot AII .ercb.ric d|l be comDl.r..l !r lad 2,0lr0 f€€r missrvlns.Uk€ manybclore you, 9ou are piobably wondelhg sherhff or nor you can \ak€ i1" ai dre same6me |rboilng Tl ! L nor h.nated .ldtud€ trt .cr!.I .ldtude uider rhedelusionrhanh?maitolasood pilor b hcsktllh aeob.hca $e aE,e'. ol .ou6e. is rhai you qtn be .bl. to "rake ",bu|h? querion$ltbe lnethsornoryouon "h-ue I Yourel€ry b€ll lr sh@ld b. lan.ned snugly.bur mr b Ll" T@ rony c.d?a helore ylo hde (fie ro Ei.t in C r.se, rsh& d ro inrerl€e s h yor les @€m€nis. Ah. simplybea u.e rheyrs'e tanied aky" birthdr entolnenr ol ch4* rh€ shouldq h.66 aerob.rt and r d6n€ ro bercm€ aerbaric expds Tiey 2 Be €@ nor akn in l@kjns lor dhq airEft in your nesleded rh€ prc.kion ert iirrodlc€d i. -
National Transportation Safety Board Aviation Accident Final Report
National Transportation Safety Board Aviation Accident Final Report Location: RANCHO MURIETA, CA Accident Number: LAX88FA015 Date & Time: 10/15/1987, 1528 PDT Registration: N121FJ Aircraft: DASSAULT-BREGUET DA 10 Aircraft Damage: Destroyed Defining Event: Injuries: 3 Fatal Flight Conducted Under: Part 91: General Aviation - Positioning Analysis THE ACFT FLEW TO THE ARPT FOR A SALES DEMO FLT. THE CREW BOARDED THE ACFT AND TAXIED OUT FOR DEP. WITNESSES, INCLUDING TWO PLTS WITH AEROBATIC EXP, WATCHED THE ACFT DEP, MAKE A LEFT TRAFFIC PATTERN AND DO A LOW FLY-BY DOWN THE RWY. AT THE DEP END OF THE RWY, THE ACFT PITCHED UP INTO A STEEP CLIMB. AT 600 FT AGL, THE ACFT ENTERED A LEFT AILERON ROLL, WHICH THE WITNESSES SAID WAS 'SMOOTH, COORDINATED AND WITH THE NOSE ON THE POINT.' AT THE INVERTED POINT OF THE ROLL, THE ROLL CHANGED FROM AN AILERON TO A BARREL ROLL. ONE PILOT WITNESS SAID THAT IT APPEARED THE 'CREW LOST IT AT THE TOP' AND THAT THE CREW 'HELD THE BACK PRESSURE TOO LONG AT THE TOP.' AT THE 270 DEG POINT OF THE ROLL, THE ACFT WAS SEEN TO 'FALL OUT' OR 'DISH OUT' OF THE ROLL; IT RECOVERED TO WINGS LEVEL FLT AT ABOUT 100 FT AGL IN A VERY NOSE HIGH ATTITUDE SETTLING INTO THE GROUND WITH A HIGH VERTICAL DESCENT RATE. NO PREIMPACT ENG OR CONTROL SYSTEM MALFUNCTIONS WERE FOUND. Probable Cause and Findings The National Transportation Safety Board determines the probable cause(s) of this accident to be: IN FLIGHT LOSS OF CONTROL BY THE PILOT FLYING WHILE PERFORMING AN INTENTIONAL LOW LEVEL AEROBATIC MANEUVER. -
Sportsman Sequence but Sequence
SPORT MARCH 2011 OFFICIALFICIAL MAGAZINEMA NENE ofof thet INTERNATIONALN TION AEROBATIC CLUB • First Japanese How to Fly the Contest SPORTSMAN •Cheap Acro SEQUENCE Drive one. 2011 Ford Mustang All Legend, No Compromise The Privilege of Partnership The legendary 5.0L V8 returns to the Mustang GT, delivering 412 HP EAA members are eligible for special pricing on Ford Motor Company and 26 MPG. The 3.7L V6 boasts 305 HP and 31 MPG – new standards vehicles through Ford’s Partner Recognition Program. To learn more in the class! on this exclusive opportunity for EAA members to save on a new Ford vehicle, please visit www.eaa.org/ford. State-of-the-art technology includes: Twin-Independent Variable Cam Timing (Ti-VCT), SYNC in-car connectivity, and AdvanceTrac electronic stability control. VEHICLE PURCHASE PLAN OFFICIAL MAGAZINE of the INTERNATIONAL AEROBATIC CLUB Vol. 40 No.3 March 2011 A PUBLICATION OF THE INTERNATIONAL AEROBATIC CLUB CONTENTS “Somebody said, “Well, they met a black bear when they were making the corner markers. Maybe it’s true. ” Yuichi Tagaki FEATURES 06 Flying the 2011 Sportsman Known John Morrisey 18 Full Circle Dave Watson 22 Cheap Acro Will Tyron 28 Japan’s First Contest Cutting acro out of the jungle Yuichi Takagi COLUMNS 03 / President’s Page Doug Bartlett DEPARTMENTS 02 / Letter From the Editor 04 / Sun ‘n Fun Speakers 26 / 2010 Regional Results THE COVER 30 / Contest Calendar and Advertisers Index Photo by Laurie Zaleski. 31 / FlyMart and Classifieds PHOTOGRAPHY COURTESY YUICHI TAGAKI REGGIE PAULK COMMENTARY / EDITOR’S LOG OFFICIAL MAGAZINE of the INTERNATIONAL AEROBATIC CLUB PUBLISHER: Doug Bartlett IAC MANAGER: Trish Deimer EDITOR: Reggie Paulk SENIOR ART DIRECTOR: Phil Norton DIRECTOR OF PUBLICATIONS: Mary Jones COPY EDITOR: Colleen Walsh CONTRIBUTING AUTHORS: Doug Bartlett John Morrissey Reggie Paulk Yuichi Tagaki Will Tyron Dave Watson IAC CORRESPONDENCE International Aerobatic Club, P.O. -
DCS: Su-27 Flanker Flight Manual
[SU-27] DCS DCS: Su-27 Flanker Eagle Dynamics i Flight Manual DCS [SU-27] DCS: Su-27 for DCS World The Su-27, NATO codename Flanker, is one of the pillars of modern-day Russian combat aviation. Built to counter the American F-15 Eagle, the Flanker is a twin-engine, supersonic, highly manoeuvrable air superiority fighter. The Flanker is equally capable of engaging targets well beyond visual range as it is in a dogfight given its amazing slow speed and high angle attack manoeuvrability. Using its radar and stealthy infrared search and track system, the Flanker can employ a wide array of radar and infrared guided missiles. The Flanker also includes a helmet-mounted sight that allows you to simply look at a target to lock it up! In addition to its powerful air-to-air capabilities, the Flanker can also be armed with bombs and unguided rockets to fulfil a secondary ground attack role. Su-27 for DCS World focuses on ease of use without complicated cockpit interaction, significantly reducing the learning curve. As such, Su-27 for DCS World features keyboard and joystick cockpit commands with a focus on the most mission critical of cockpit systems. General discussion forum: http://forums.eagle.ru ii [SU-27] DCS Table of Contents INTRODUCTION ........................................................................................................... VI SU-27 HISTORY ............................................................................................................. 2 ADVANCED FRONTLINE FIGHTER PROGRAMME ......................................................................... -
Chris Larson Soaring Over Michigan the “Remote” Instructor Bronze Badge Process Nutmeg Open House Ad
May, 2017 THE OFFICIAL PUBLICATION OF THE WOMEN SOARING PILOTS ASSOC. www.womensoaring.org IN THIS ISSUE PAGE 2 Badges June is WSPA dues’ renewal month President’s note Please pay on time From the Editor PAGE 4 Welcome new members Meet Chris Larson Virginia Gallenberger PAGE 5 My first solo WSPA committees PAGE 6 Famous women pilots: Melitta Schiller PAGE 7 100 years old woman celebrates her 100th birthday.. PAGE 8 Winter Soaring..Arizona Winter Soaing...Namibia This and That PAGE 9 NSM letter Shattered Dream A POH cannot be read too many times PAGE 10 Chris Larson soaring over Michigan The “remote” instructor Bronze Badge Process Nutmeg Open House ad PAGE 11 2017 WSPA Seminar page 2 May 2017 THE WOMEN SOARING PILOTS Badges ASSOCIATION (WSPA) WAS (reported through May 2017 A Badge FOUNDED IN 1986 AND IS Coleen Cameron, CO AFFILIATED WITH THE SOARING C Badge Maryam Ali, VA SOCIETY OF AMERICA Coleen Cameron, CO BOARD B Badge Mary Rust ,President Coleen Cameron, CO From the Editor 26630 Garret Ryan Ct. Recently, I got an e-mail from one of our members inquir- Hermet, CA 92544-6733 President’s Note ing why we need separate Charlotte Taylor, Vice President women contests or listing women Your newly elected WSPA Board Mem- 4206 JuniataSt. records separately. This also falls bers are off to a great start working on a St. Louis, MO 63116 into the category ‘why are there variety of projects! Though we have been so few women in aviation and in working on line together for 4 months, Joan Burn, Secretary soaring especially?’ WSPA and many of us have not met each other face 212 Marian Ct. -
Selig-2014-Jofac-Fli
JOURNAL OF AIRCRAFT Vol. 51, No. 6, November–December 2014 Real-Time Flight Simulation of Highly Maneuverable Unmanned Aerial Vehicles Michael S. Selig∗ University of Illinois at Urbana–Champaign, Urbana, Illinois 61801 DOI: 10.2514/1.C032370 This paper focuses on full six degree-of-freedom aerodynamic modeling of small unmanned aerial vehicles at high angles of attack and high sideslip in maneuvers performed using large control surfaces at large deflections for aircraft with high thrust-to-weight ratios. Configurations, such as this, include many of the currently available propeller- driven radio-controlled model airplanes that have control surfaces as large as 50% chord, deflections as high as 50 deg, and thrust-to-weight ratios near 2∶1. Airplanes with these capabilities are extremely maneuverable and aerobatic, and modeling their aerodynamic behavior requires new thinking because using traditional stability- derivative methods is not practical with highly nonlinear aerodynamic behavior and coupling in the presence of high prop-wash effects. The method described outlines a component-based approach capable of modeling these extremely maneuverable small unmanned aerial vehicles in a full six degree-of-freedom real-time environment over the full 180 deg range in angle of attack and sideslip. Piloted flight-simulation results for four radio-controlled/unmanned- aerial-vehicle configurations having wingspans in the range from 826 mm (32.5 in.) to 2540 mm (100 in.) are presented to highlight the results of the high-angle aerodynamic modeling approach. Maneuvers simulated include tailslides, knife-edge flight, high-angle upright and inverted flight, rolling maneuvers at high angle, and an inverted spin of a biplane. -
Increasing Launch Rate and Payload Capabilities
Aerial Launch Vehicles: Increasing Launch Rate and Payload Capabilities Yves Tscheuschner1 and Alec B. Devereaux2 University of Colorado, Boulder, Colorado Two of man's greatest achievements have been the first flight at Kitty Hawk and pushing into the final frontier that is space. Air launch systems aim to combine these great achievements into a revolutionary way to deliver satellites, cargo and eventually people into space. Launching from an aircraft has many advantages, including the ability to launch at any inclination and from above bad weather, which could delay ground launches. While many concepts for launching rockets from an airplane have been developed, very few have made it past the drawing board. Only the Pegasus and, to a lesser extent, SpaceShipOne have truly shown the feasibility of such a system. However, a recent push for rapid, small payload to orbit launches by the military and a general need for cheaper, heavy lift options are leading to an increasing interest in air launch methods. In order for the efficiency and flexibility of the system to be realized, however, additional funding and research are necessary. Nomenclature ALASA = airborne launch assist space access ALS = air launch system DARPA = defense advanced research project agency LEO = low Earth orbit LOX = liquid oxygen RP-1 = rocket propellant 1 MAKS = Russian air launch system MECO = main engine cutoff SS1 = space ship one SS2 = space ship two I. Introduction W hat typically comes to mind when considering launching people or satellites to space are the towering rocket poised on the launch pad. These images are engraved in the minds of both the public and scientists alike. -
Round Trip to Orbit: Human Spaceflight Alternatives
Round Trip to Orbit: Human Spaceflight Alternatives August 1989 NTIS order #PB89-224661 Recommended Citation: U.S. Congress, Office of Technology Assessment, Round Trip to Orbit: Human Spaceflight Alternatives Special Report, OTA-ISC-419 (Washington, DC: U.S. Government Printing Office, August 1989). Library of Congress Catalog Card Number 89-600744 For sale by the Superintendent of Documents U.S. Government Printing Office, Washington, DC 20402-9325 (order form can be found in the back of this special report) Foreword In the 20 years since the first Apollo moon landing, the Nation has moved well beyond the Saturn 5 expendable launch vehicle that put men on the moon. First launched in 1981, the Space Shuttle, the world’s first partially reusable launch system, has made possible an array of space achievements, including the recovery and repair of ailing satellites, and shirtsleeve research in Spacelab. However, the tragic loss of the orbiter Challenger and its crew three and a half years ago reminded us that space travel also carries with it a high element of risk-both to spacecraft and to people. Continued human exploration and exploitation of space will depend on a fleet of versatile and reliable launch vehicles. As this special report points out, the United States can look forward to continued improvements in safety, reliability, and performance of the Shuttle system. Yet, early in the next century, the Nation will need a replacement for the Shuttle. To prepare for that eventuality, NASA and the Air Force have begun to explore the potential for advanced launch systems, such as the Advanced Manned Launch System and the National Aerospace Plane, which could revolutionize human access to space. -
Re-Usable Launch and Payload Delivery System MDDP 2012/3
Group 2 Re-usable Launch and Payload Delivery System MDDP 2012/3 Re-usable Launch and Payload Delivery System MDDP Group 2 James Dobberson Robert Taylor Matthew Chapman Timothy West Mukudzei Muchengeti William Wou Group 2 Re-usable Launch and Payload Delivery System MDDP 2012/3 1. Contents 1. Contents ..................................................................................................................................... i 2. Executive Summary .................................................................................................................. ii 3. Introduction .............................................................................................................................. 1 4. Down Selection and Integration Methodology ......................................................................... 2 5. Presentation of System Concept and Operations ...................................................................... 5 6. System Investment Plan ......................................................................................................... 20 7. Numerical Analysis and Statement of Feasibility .................................................................. 23 8. Conclusions and Future Work ................................................................................................ 29 9. Launch Philosophy ................................................................................................................. 31 10. Propulsion ..............................................................................................................................