1 Space Shuttle Mission SPACE SHUTTLE SYSTEM Operation
2 SPACE SHUTTLE SYSTEM Operation The flight plan and operation of the Space Shuttle differs markedly from that of the now-familiar launch procedures and splashdown of the Apollo missions, which utilized the expendable Saturn-V launch vehicle. The Space Shuttle vehicle provides a relatively comfortable environment for a nominal flight crew of four plus up to three payload specialists. In an emergency, an additional three persons can be provided for. This capability will enable experienced scientists and technicians to accompany their payloads into space. The environmental improvement is a result of the lower levels of launch and entry accelerations and a crew cabin that provides an air environment at shirt-sleeve temperature, pressure and humidity. As illustrated on the left side of the figure, the integrated Shuttle vehicle ascends from the launch pad to an altitude of about 24 nautical miles, at which point the solid rocket boosters are jettisoned. The SRB's fall in an arc back to earth, are decelerated by parachutes, and are recovered from the ocean for reuse. Shortly before orbital injection, the orbiter main propulsion engines are shut down, and the external tank is separated from the orbiter. The orbital maneuver ing system provides thrust to inject the orbiter into orbit while the external tank follows a ballistic trajectory into a remote ocean area for disposal. Fitted for orbiting missions of from 7 to 30 days, the Shuttle has the capability to perform a variety of tasks such as satellite placement and recovery, propulsive stage and satellite delivery and return, manned orbital laboratory operation, and satellite service and repair. At the end of its mission, the Shuttle, with thrust from its orbit-maneuvering engines, leaves its orbit to reenter the earth's atmosphere, decelerating to make an aircrafttype landing on earth. After landing, the crew of scientists, technicians, and astronauts leave the Shuttle with their data and equipment. Recovered payloads are unloaded, and the orbiter is serviced for the next flight. The orbiter, loaded with a new payload, is mated with a new propellant tank and the refurbished solid propellant boosters and is then transported to the launch area where the crew boards for the next mission.
3 SPACE SHUTTLE SYSTEM Missions
4 SPACE SHUTTLE SYSTEM Missions The Space Shuttle has been designed to support a wide variety of space missions, including all those current and planned. This is implicit in the vehicle's capability to orbit 65,000 pounds of payload compared to the current expendable launch vehicle capability of about 30,000 pounds. The Space Shuttle is more than a launch vehicle, however, and can support new missions and operations which will make possible the achievement of higher productivity for the space program and facilitate greater utilization of space resources. The Space Shuttle also has the unique capability to make observations and measurements, particularly those involving real- or short-time opportunities, which can only be accomplished with man-in-the-loop operations. In addition to its ability to provide more cost-effective launch services, the Shuttle has been designed to service and refurbish low-earth-orbit satellites, retrieve and return to earth pay-loads weighing up to 32,000 pounds, perform dedicated experimentation and technology development missions, carry passengers in relative comfort, and, with suitable upper stage propulsion, economically launch from orbit satellites and spacecraft whose missions require the attainment of higher orbital velocities. A group of reusable mission kits to provide special or extended services for payloads will be added when required and will be designed to be quickly installed and easily removed. " The major mission kits are as follows: oxygen and hydrogen for fuel cell usage to generate electrical energy; life support for extended missions; added propellant tanks for special on-orbit mission maneuvers; extra or specialized attachment fittings; airlocks, transfer tunnels, and docking modules; a second remote manipulator cirm; an extra high-gain antenna; fill, vent, drain, purge, and dump lines; additional radiator panels for increased heat rejection; additional storage tanks; and electrical harnesses. These capabilities can be used in many ways, some of which are listed in the facing chart as applications. Some of these applications have already evolved into vital programs. Others await the special operational capabilities of the Space Shuttle, mentioned above, to enable their initiation. With its capabilities, economy, and operational flexibility, the Space Shuttle provides the United States and its partners in space ventures the means to develop space resources for everyone's benefit.
5 Space Shuttle Mission SPACE SHUTTLE SYSTEM Space Shuttle Vehicle
6 SPACE SHUTTLE SYSTEM Space Shuttle Vehicle The Space Shuttle flight system consists of an orbiter with Space Shuttle main engines (SSME's), an external tank (ET), and two solid rocket boosters (SRB's). The orbiter with SSME's and the solid rocket booster are reusable elements; the external tank is expended on each launch. The orbiter normally carries into orbit a crew of four, with provisions for a crew of as many as seven, and payloads. It can remain in orbit nominally for seven days (up to 30 days with special payloads), return to earth with personnel and payload, land like an airplane, be refurbished for a subsequent flight in 14 days, and provide for a rescue mission launch within 24 hours after notification (from standby status). The Space Shuttle main engines, used during ascent, obtain their propellants from the external tank. Smaller orbiter rocket engines provide for maneuvering and attitude control during space flight. Aerodynamic surfaces on the wings and vertical stabilizer control the orbiter during atmospheric flight. The crew occupies a two-level cabin at the forward end of the vehicle. From the upper level flight deck, the crew controls the launch, orbital maneuvering, atmospheric entry, and landing phases of the mission. The crew also performs payload handling. Seating for up to three additional crew members and habitability provisions are provided on the mid deck. The mid deck can be reconfigured to provide an additional three seats in the event of a rescue mission. The load factors experienced by the crew on any of these missions is 3 g's or less. The solid rocket boosters burn in parallel with the SSME's and are separated from the orbiter/external tank at approximately 150,000 feet. The SRB's descend on parachutes and land in the ocean about 150 nautical miles from the launch site. They may be recovered by ships, returned to land, refurbishec and then reused. After SRB separation, the SSME's continue to burn until the orbiter is injected into the required ascent trajectory. The external tank then separates and falls ballistically into the little used areas of the Indian Ocean or the South Pacific Ocean, depending on the launch site and mission. The orbil maneuvering system completes insertion of the orbiter into the final desired orbit.
7 NAVIGATION AND FLIGHT Typical Mission Profile
8 NAVIGATION AND FLIGHT Typical Mission Profile The Shuttle is launched with the three orbiter Space Shuttle main engines (SSME's) burning in parallel with the two solid rocket boosters (SRB's). After approximately two minutes, the SRB propellants are depleted, and the SRB's are staged off to be recovered and returned to the launch site. The orbiter ascent is continued using the three SSME's, which provide thrust vector control until main engine cutoff (MECO) conditions assure a safe disposal of the external tank (ET). The ET is separated immediately after MECO, and the orbital maneuvering system (OMS) engines provide the additional velocity needed to insert the orbiter into an elliptical orbit having a minimum apogee of 150 nautical miles. At first apogee, the orbiter initiates the first of two maneuvers to circularize the orbit at 150 nautical miles. Additional maneuvers may be executed as required for the orbital operations of a specific mission. Following the completion of orbital operations, the orbiter is oriented to a tail-first attitude, and the OMS provides the deceleration thrust necessary for deorbiting. The orbiter is reoriented nose-forward to the proper attitude for entry. The orientation of the orbiter is established and maintained by the reaction control system (RCS) down to the altitude where the atmospheric density is sufficient for the pitch and roll aerodynamic control surfaces to be effective, about the 250,000-foot altitude. The yaw RCS remains active until the vehicle reaches the 80,000-foot altitude, approximately. The orbiter entry trajectory provides lateral flight range to the landing site and energy management for an unpowered landing. The trajectory, lateral range, and heating are controlled through the attitude of the vehicle by angle of attack and bank angle. The orbiter has a lateral or cross-range capability of approximately 1150 nautical miles Terminal Area Energy Management (TAEM) is initiated approximately 50 nautical miles from the landing site and provides the proper vehicle approach to the runway with respect to position, altitude, velocity, and headings Final touch-down occurs at a nominal landing speed of about 210 knots.
9 Space Shuttle Mission NAVIGATION AND FLIGHT Typical Trajectory Profiles
10 NAVIGATION AND FLIGHT Typical Trajectory Profiles Ascent Trajectory. The ascent traiectory reaches a maximum dynamic pressure (Q) of 650 pounds per square foot approximatey 60 seconds after launch at an altitude of feet. At 108 seconds, the total load factor reaches the first stage maximum value of 2.6 g's. SRB separation occurs at approximately 126 seconds at an altitude of 148,500 feet, 28 nautical miles downrange from the launch site. After SKB separation, the orbiter continues to ascend, using the three SSME's. The total load factor reaches a maximum value of 3.0 g's (longitudinal) at 415 seconds. It remains at that value until 470 seconds, when the main engine cutoff (MECO) sequence is initiated. MECO takes place 478 seconds after lift-off, when the orbiter has reached an altitude of 361,400 feet. The external tank (ET) separation occurs at MECO. After a short coasting period, the orbital maneuving system (OMS) engines are fired at 514 seconds to provide the additional velocity needed to insert the orbiter into an elliptical orbit having a minimum apogee of 150 nautical miles. The OMS engine cutoff occurs 648 seconds after launch at an altitude of 407,000 feet, when the orbiter is 1350 nautical miles from the launch site. Additional OMS burn at apogee is required to circularize or increase orbit altitude. Descent Trajectory. The orbiter descent or entry trajectory provides lateral flight range to the landing site and energy management for an unpowered landing. Entry is initiated by a deorbit maneuver and retrofinng the 0MS nominally 28 minutes prior to entry interface. The trajectory, lateral range, and heating are con trolled through the attitude of the vehicle by angle of attack and bank angle. The angle of attack is established at 40 degrees for the theoretical entry interface of 400,000 feet altitude. The entry flight path angle is l.l8 degrees. The 40- degree angle of attack is held until the speed is reduced to 11,000 feet per second (about 170,000 feet altitude), then is reduced gradually to 13.5 degrees at 2500 feet per second (about 85,000 feet altitude). Tactical Air Navigation (TACAN) acquisition is accomplished at approximately 190,000 feet altitude and 650 nautical miles from the landing site. During the final phases of descent, flight path control is maintained by using the aerodynamic surfaces Terminal Area Energy Management (TAEM) is initiated to provide the proper vehicle approach to the runway with respect to position, energy, and heading. Final touchdown occurs at an angle of attack of about 8 degrees, with a nominal touch speed of 210 knots. The maximum landing speed for a 32,000- pound payload, including dispersions for hot day effects and tailwinds, is about 225 knots.
11 GN&C CHALLANGES Take-Off Get all rocket motors firing: must be timed properly relative to SSME ignition to reduce vehicle loads solid rocket booster (SRB) ignition causes vehicle to "twang" twang can cause software to think rate gyros are failing => teach software Clear launch support structure & tower: winds cause drifts mismatch of thrust (cause unwanted moments): in magnitude in direction failures: engine thrust thrust vector control system (TVCS)
12 GN&C CHALLANGES Ascent through the Atmosphere Overall shuttle vehicle is four big elements three thrusting elements tied together through one relatively weak element take care not to put too heavy loads on this configuration What causes loads: "lift" due to wings winds (steady state & gusts) failures (engine out, GN&C failures) Solution: pick angle of attack (alpha) profile sense lateral accelerations due to winds and control vehicle to relieve wind loads pick new flight profiles when an engine goes out & design GN&C to minimize failure transients More loads problems: elevons and wings no fixed setting of elevon that is OK for both elevon & wing cannot predict a variable setting that is accurate enough Solution: pick basic flight profile to keep wing happy, sense elevon loads (via resulting hydraulic pressures) & move elevons to alleviate loads
13 GN&C CHALLANGES Ascent through Atmosphere (continued) Total axial acceleration: basic design is for 3 gs or less near the end of ascent the vehicle is lighter & acceleration increases over 3 g s solution is to sense actual acceleration & reduce engine thrust to limit g's Solid rocket booster separation: avoid recontact during separation cannot turn off SRB s => just let them burn out but they do not burn out at quite the same time => vehicle wants to become a pinwheel must limit external tank (ET) yaw motion for thermal reasons also time to phase-in orbiter as main source of thrust vector control Solution: sophisticated moding & sequencing of separation events technique of flight control during separation etc.
14 ASCENT TO ORBIT Dynamic Pressure Limiting
15 ASCENT TO ORBIT Acceleration Limiting
16 ASCENT TO ORBIT Propulsion System Constraints
17 ABORT MANEUVERS Abort Characteristics
18 RE-ENTRY Deorbit To Landing
19 RE-ENTRY Re-Entry Events
20 RE-ENTRY Runway Approach
21 RE-ENTRY Landing
22 WEIGHT SUMMARY Weight Summary
23 SPACE SHUTTLE SYSTEM Weight Summary The Space Shuttle is designed to satisfy three payload missions. Mission 1 is to be launched from KSC, while Missions 3A and 4 are to be launched from VAFB. Mission 1 requires placing the maximum payload (65,000 pounds) into the minimum inclination (28-1/2 deg), 150-nmi circular orbit and return a 32,000-pound payload. Mission 3A deploys a 32,000-pound payload into a 104-degree inclination at first apogee, with a minimum altitude of 100-nmi. The orbiter lands nearly empty at the launch/landing site at end of the first revolution. Mission 4 calls for the vehicle to launch a 32,000-pound payload into a 98-degree inclination, 150-nmi circular orbit within two revolutions after lift-off and to capture, retrieve, and return a 25,000-pound payload to VAFB. The weight summary chart shows the breakdown of the pre-lift-off weights for the required missions. The gross weight of the Shuttle Transportationj System for Mission 1 is the heaviest at 4.5 million pounds; the gross weights of the other missions are slightly smaller. The variations in the gross weights are due to differences in payloads, crew size, and propellants for OMS, RCS, and electrical power as required for mission altitude, rendezvous/maneuver, and duration. The lift-off weights are slightly less (about 7500 pounds) than the pre-liftoff weights shown, due to the use of about 6300 pounds of ET propellants in engine ignition and increasing thrust level, and about 1200 pounds of propellant in the SRB's from ignition to lift-off thrust level.
SpaceLoft XL Sub-Orbital Launch Vehicle The SpaceLoft XL is UP Aerospace s workhorse space launch vehicle -- ideal for significant-size payloads and multiple, simultaneous-customer operations. SpaceLoft
9210-228 Level 7 Post Graduate Diploma in Mechanical Engineering Aerospace engineering You should have the following for this examination one answer book non-programmable calculator pen, pencil, drawing
Overview of the Orbiting Carbon Observatory (OCO) Mishap Investigation Results For Public Release SUMMARY The Orbiting Carbon Observatory was a National Aeronautics and Space Administration satellite mission
Shuttle Variations And Derivatives That Never Happened - An Historical Review Carl F. Ehrlich, Jr. * Consultant, Calabasas, CA 91302 James A. Martin The Boeing Company, Huntington Beach, CA 92647 While
The Space Shuttle: Teacher s Guide Grade Level: 6-8 Curriculum Focus: Astronomy/Space Lesson Duration: Two class periods Program Description This video, divided into four segments, explores scientists'
Can Hubble be Moved to the International Space Station? 1 On January 16, NASA Administrator Sean O Keefe informed scientists and engineers at the Goddard Space Flight Center (GSFC) that plans to service
Technologies for Re-entry Vehicles SHEFEX and REX FreeFlyer, DLR s Re-Entry Program Hendrik Weihs Folie 1 DLR`s Re-Entry Program, Why? Re-entry or return technology respectively, is a strategic key competence
China Space Station Project Zhou Jianping Chief Designer of China Manned Space Program September 2013 Beijing Contents Introduction Overview of China space station Unique features of China space station
How Rockets Work Whether flying a small model rocket or launching a giant cargo rocket to Mars, the principles of how rockets work are exactly the same. Understanding and applying these principles means
Forces on a Model Rocket This pamphlet was developed using information for the Glenn Learning Technologies Project. For more information, visit their web site at: http://www.grc.nasa.gov/www/k-12/aboutltp/educationaltechnologyapplications.html
Teacher s Guide Grade Level: 9 12 Curriculum Focus: Physical Science Lesson Duration: Three class periods Program Description Examine Isaac Newton's laws of motion, the four fundamental forces of the universe,
TYPES OF AIRCRAFT CLASSIFICATION OF AIRCRAFT AND SPACECRAFT Aircraft can be classified into various types based on the mode of classification. In the following slide, a general classification of aircraft
General aviation & Business System Level Applications and Requirements Electrical Technologies for the Aviation of the Future Europe-Japan Symposium 26 March 2015 2015 MITSUBISHI HEAVY INDUSTRIES, LTD.
Performance- Page 67 AIRCRAFT PERFORMANCE Pressure Altitude And Density Altitude Pressure altitude is indicated altitude corrected for nonstandard pressure. It is determined by setting 29.92 in the altimeter
Furze Platt Senior School Does currently available technology have the capacity to facilitate a manned mission to Mars? Daniel Messias Date: 8/03/2015 Candidate Number: 7158 Centre Number: 51519 Contents
A MONTE CARLO DISPERSION ANALYSIS OF A ROCKET FLIGHT SIMULATION SOFTWARE F. SAGHAFI, M. KHALILIDELSHAD Department of Aerospace Engineering Sharif University of Technology E-mail: firstname.lastname@example.org Tel/Fax:
Basic Principles of Inertial Navigation Seminar on inertial navigation systems Tampere University of Technology 1 The five basic forms of navigation Pilotage, which essentially relies on recognizing landmarks
Cessna 172SP & NAV III Maneuvers Checklist Introduction Power Settings This document is intended to introduce to you the standard method of performing maneuvers in Sunair Aviation s Cessna 172SP and NAV
Performance 15. Takeoff and Landing The takeoff distance consists of two parts, the ground run, and the distance from where the vehicle leaves the ground to until it reaches 50 ft (or 15 m). The sum of
APPENDIX 3-B Airplane Upset Recovery Briefing Industry Solutions for Large Swept-Wing Turbofan Airplanes Typically Seating More Than 100 Passengers Briefing Figure 3-B.1 Revision 1_August 2004 Airplane
Section 4: The Basics of Satellite Orbits MOTION IN SPACE VS. MOTION IN THE ATMOSPHERE The motion of objects in the atmosphere differs in three important ways from the motion of objects in space. First,
Newton's Laws of Motion in Motion Objectives: Students will use simple techniques to demonstrate Newton's 1 st and 3 rd Laws of Motion. Students will demonstrate their understanding of thrust, drag, lift,
Aerospace Engineering 3521: Flight Dynamics Prof. Eric Feron Homework 6 due October 20, 2014 1 Problem 1: Lateral-directional stability of Navion With the help of Chapter 2 of Nelson s textbook, we established
Revision history Version Date Action 1.0 Oct 1, 2015 Initial release Moonspike - Feasibility Study - October 2015 - Page 1 of 35 1 Table of Contents 1 Table of Contents... 2 2 Acronyms & Terms... 3 3 Document
Fleet Ballistic Missile Eastern Range Operations Supporting Navy Testing and Deployment Lockheed Martin Space Systems Company Test & Support Systems Engineering Pier Road, Hanger Y Mail Drop: MRL 156 Cape
What Do Engineers Do? Engineers apply the theories and principles of science and mathematics to the economical solution of practical technical problems. I.e. To solve problems Often their work is the link
ROYAL CANADIAN AIR CADETS PROFICIENCY LEVEL TWO INSTRUCTIONAL GUIDE SECTION 6 EO C240.03 IDENTIFY PARTS OF A ROCKET Total Time: 30 min PREPARATION PRE-LESSON INSTRUCTIONS Resources needed for the delivery
ENGINE FIRE / SEVERE DAMAGE / SEPARATION ON TAKEOFF According to RYANAIR Procedures PF PM REMARKS Control the aircraft (FULL T/O thrust can be manually selected) Announce «ENGINE FAILURE» or «ENGINE FIRE»
History of the Titan Centaur Launch Vehicle The Centaur program began in 1958 with its first successful flight on 27 November 1963. The unique Centaur design is the first liquid oxygen and liquid hydrogen
ACTIVITY Learning objectives To: describe how we can use the Sun to generate electricity give examples of where solar power is used design and build a solar powered vehicle explore how gears can convert
Regolith-Derived Heat Shield for Planetary Body Entry and Descent System with In-Situ Fabrication Michael D. Hogue, NASA Kennedy Space Center Robert P. Mueller, NASA Kennedy Space Center Laurent Sibille,
ISS Live! was developed at NASA s Johnson Space Center (JSC) under NASA Contracts NNJ14RA02C and NNJ11HA14C wherein the U.S. Government retains certain rights. Console Handbook TOPO Trajectory Operations
SpaceX Overview Tom Markusic Director, McGregor Rocket Development Facility 27 July, 2010 SpaceX Vehicles Falcon 1 Falcon 9 Dragon Spacecraft 2 SpaceX Overview Founded in mid-2002 with the singular goal
Foundations and Mathematical Application of the Water Rocket Students Utilize 2-Liter Bottle Rocket Launcher will help students to explore the science of rocketry. Students build &propel 2-liter bottle
WikiLeaks Document Release February 2, 2009 Congressional Research Service Report RS21606 NASAs Space Shuttle Columbia: Synopsis of the Report of the Columbia Accident Investigation Board Marcia S. Smith,
Atmospheric Reentry Introduction, Mathematical Model and Simulation Julian Köllermeier Theodor-Heuss Akademie, August 23rd 2014 A short history of human spaceflight 1944 V2 is first rocket in space 1957
COPYRIGHT 20. ALL RIGHTS RESERVED FED. SUPPLY CLASS NONE TEAM AMERICA ROCKETRY CHALLENGE 2016 RULES DATE. www.aia-nas.org ISSUE DATE: SEPTEMBER 2002 DATE: MAY 9, 20 THIRD ANGLE PROJECTION CUSTODIAN NATIONAL
S. Widnall, J. Peraire 16.07 Dynamics Fall 008 Version.0 Lecture L17 - Orbit Transfers and Interplanetary Trajectories In this lecture, we will consider how to transfer from one orbit, to another or to
APPENDIX G. (WBS) Space Flight Project Work Breakdown Structure G.1 Introduction G.1.1 The Project Work Breakdown Structure (WBS) is a key element of project management. The purpose of a WBS is to divide
J. Peraire, S. Widnall 16.07 Dynamics Fall 2008 Version 2.0 Lecture L14 - Variable Mass Systems: The Rocket Equation In this lecture, we consider the problem in which the mass of the body changes during
Rocketry for Kids Science Level 4 Newton s Laws Victorian Space Science Education Centre 400 Pascoe Vale Road Strathmore, Vic 3041 www.vssec.vic.edu.au Some material for this program has been derived from
A VALUE PROPOSITION FOR LUNAR ARCHITECTURES UTILIZING ON-ORBIT PROPELLANT REFUELING By James Jay Young In Partial Fulfillment of the Requirements for the Degree of Doctor of Philosophy in the School of
G U I D E T O A P P L I E D O R B I T A L M E C H A N I C S F O R K E R B A L S P A C E P R O G R A M CONTENTS Foreword... 2 Forces... 3 Circular Orbits... 8 Energy... 10 Angular Momentum... 13 FOREWORD
RS platforms Platform vs. instrument Sensor Platform Instrument The remote sensor can be ideally represented as an instrument carried by a platform Platforms Remote Sensing: Ground-based air-borne space-borne
LOGOTYPE TONS MONOCHROME 294C June 2015 VV 05 LOGOTYPE COMPLET (SYMBOLE ET TYPOGRAPHIE) FIFTH VEGA LAUNCH FROM THE GUIANA SPACE CENTER, AT THE SERVICE OF EUROPE'S COPERNICUS PROGRAM On the fifth Vega mission
Student Pilot Training Basic Flight Training Phase I Task #1 Ground support equipment, engine starting, & taxi training Perform aircraft preparation and inspection. Perform engine start and radio checks.
Delimitation and Commercial Use of Outer Space Sang-Myon Rhee Seoul National University March 28, 2011 Where to Delimit? Problems & Issues Problems in Traditional Delimitation Air Space Outer Space Necessity
CHAPTER 1 INTRODUCTION 1.1 Background of the Research Agile and precise maneuverability of helicopters makes them useful for many critical tasks ranging from rescue and law enforcement task to inspection
This file contains the full script of the corresponding video, published on YouTube. November 2014: http://youtu.be/wbu6x0hsnby Background papers and links to formal FAA and EASA Aviation Regulations and
The Logistical Challenges of the SpaceLiner Concept Arnold van Foreest, Martin Sippel Arnold.vanForeest@dlr.de Tel. +49 (0)421 24420-153, Fax. +49 (0)421 24420-150 Space Launcher Systems Analysis (SART),
Atlas Emergency Detection System (EDS) Jeff A. Patton 1 United Launch Alliance, Littleton, Colorado, 80127-7005 [Abstract] The Atlas Expendable Launch Vehicle Program has been studying safe abort requirements
Analysis on the Long-term Orbital Evolution and Maintenance of KOMPSAT-2 Ok-Chul Jung 1 Korea Aerospace Research Institute (KARI), 45 Eoeun-dong, Daejeon, South Korea, 305-333 Jung-Hoon Shin 2 Korea Advanced
TS-124 May 1993 General Schedule Position Classification Flysheet AEROSPACE ENGINEERING SERIES, GS-0861 Theodore Roosevelt Building 1900 E Street, NW Washington, DC 20415-8330 Classification Programs Division
ME 239: Rocket Propulsion Introductory Remarks 1 Propulsion Propulsion: The act of changing a body s motion from mechanisms providing force to that body Jet Propulsion: Reaction force imparted to device
National Aeronautics and Space Administration CCTS Certification Requirements Commercial Crew Transportation System Certification Requirements for NASA Low Earth Orbit Missions ESMD-CCTSCR-12.10 Revision-Basic
Mars Sample Return Campaign: An Overview Dr. Firouz Naderi Associate Director NASA s JPL 1 Why Sample Return? Why Now? Compelling Science Informed Landing Site Selection International Interest Good Engineering
ExpressJet Airlines Pilot Job Knowledge Test Outline The job knowledge test administered as part of the pilot interview process consists of questions in four major knowledge areas essential to piloting
Rocket Dynamics orces on the Rockets - Drag Rocket Stability Rocket Equation Specific Impulse Rocket otors Thrust orces on the Rocket Equation of otion: = a orces at through the Center of ass Center of
AIAA SPACE 21 Conference & Exposition 3 August - 2 September 21, Anaheim, California AIAA 21-864 Modular Approach to Launch Vehicle Design Based on a Common Core Element Dennis M. Creech 1 Jacobs Engineering
Space Shuttle Propulsion PROPULSION SYSTEM Space Shuttle Main Engine (SSME) Space Shuttle Main Engine (SSME) PROPULSION SYSTEM Mounted in a triangular pattern in the orbiter's aft fuselage, the three Space
THE FUTURE OF WORLD PEACE AND OUTER SPACE Edward R. Finch* I. INTRODUCTION... 389 II. CATEGORY I MEASURES... 390 III. CATEGORY II MEASURES... 391 IV. OUTLOOK TO THE FUTURE... 391 V. MAGNA CHARTA OF OUTER
The information provided in this document is to be used during simulated flight only and is not intended to be used in real life. Attention VA's - you may post this file on your site for download. Please
SOYUZ TO LAUNCH METOP-A This new Starsem's flight will boost the Eumetsat Organization's MetOp-A meteorological spacecraft, the Europe's first polarorbiting satellite dedicated to operational meteorology.
Understanding the motion of the Universe Motion, Force, and Gravity Laws of Motion Stationary objects do not begin moving on their own. In the same way, moving objects don t change their movement spontaneously.
NASTAR CENTER SPACE TRAINING PROGRAMS Public o Intro to Space Passengers o Basic Suborbital Space Training o Advanced Space Training o Space Payload Specialist Training o Space Suits and Systems Training
Astrodynamics (AERO0024) 6. Interplanetary Trajectories Gaëtan Kerschen Space Structures & Systems Lab (S3L) Course Outline THEMATIC UNIT 1: ORBITAL DYNAMICS Lecture 02: The Two-Body Problem Lecture 03:
Congresso della SAIT Museo della Scienza e della Tecnologia di Milano 15 Maggio 2014 Francesca Esposito INAF Osservatorio Astronomico di Capodimonte (Napoli) ExoMars Mission The ExoMars Program is carried
Lunar Program Industry Briefing Altair Overview Clinton Dorris Deputy Manager, Altair Project Office Altair Lunar Lander 4 crew to and from the surface Seven days on the surface Lunar outpost crew rotation
Fluid Mechanics Prof. S. K. Som Department of Mechanical Engineering Indian Institute of Technology, Kharagpur Lecture - 20 Conservation Equations in Fluid Flow Part VIII Good morning. I welcome you all
How Long Do You Need To Achieve Your Scientific Objectives? Time seconds minutes days/weeks months Drop Towers/Drop Tubes KC-135 Parabolic Flights Balloons* Sounding Rockets Alternate Carriers* Shuttle
Position Descriptions Aerospace Aerospace Engineering? Aeromechanics / Flight Control / Flight Qualities Engineer Predict, analyze, and verify air vehicle flight dynamics including aircraft aerodynamics,
A Taxonomy for Space Curricula Arthur W. Draut, Ph.D. College of Aviation Embry-Riddle Aeronautical University Abstract Many universities have added courses and curricula related to satellites and space.
Scientific balloons Fort Hays State University November 22, 2013 Paul Adams and Jack Maseberg (N8VRN) (K1AMO) Things that fly Sky lanterns (~300 B.C.), 575 K = 575 F = 302 C Disney s Tangled (2010) theskylantern.com
Light Sport West Standard Flight Training Procedures for N110GX (Remos GX, 100 H.P.) Welcome to Light Sport West! Thank you for giving us the opportunity to provide all of your flight training needs. Our
Challenges and Opportunities Related to Landing the Dream Chaser Reusable Space Vehicle at a Public-Use Airport Frank W. Taylor 1, Christopher J. Allison 2, and Cassie L. Lee 3 Sierra Nevada Corporation
Location/Time Aircraft Registration Number: Most Critical Injury: Minor Investigated By: NTSB N911BL Nearest /Place Zip Code Local Time Time Zone Las Vegas NV 89032 1600 PDT Airport Proximity: On Airport/Airstrip
CRITICAL EVENTS OF THE INAUGURAL LAUNCH OF THE BOEING DELTA IV EXPENDABLE LAUNCH VEHICLE Michael D. Berglund * email@example.com Mark Wilkins Chief Engineer The Boeing Company Huntington Beach,
SIX DEGREE-OF-FREEDOM MODELING OF AN UNINHABITED AERIAL VEHICLE A thesis presented to the faculty of the Russ College of Engineering and Technology of Ohio University In partial fulfillment of the requirement
Flight Safety Foundation Approach-and-landing Accident Reduction Tool Kit FSF ALAR Briefing Note 4.2 Energy Management The flight crew s inability to assess or to manage the aircraft s energy condition
Diana Space Weather And Its Effects on Spacecraft By William Zinicola - Space weather interaction with early forms of technology date back to 1847 and the 8 th sun cycle - Anomalous currents in telegraph
PRACTICE NO. PD-ED-1263 PAGE 1 OF 6 PREFERRED RELIABILITY PRACTICES CONTAMINATION CONTROL OF SPACE OPTICAL SYSTEMS Practice: Contamination of space optical systems is controlled through the use of proper
Physics 2A, Sec B00: Mechanics -- Winter 2011 Instructor: B. Grinstein Final Exam INSTRUCTIONS: Use a pencil #2 to fill your scantron. Write your code number and bubble it in under "EXAM NUMBER;" an entry