Appendix Q Launch Debris and Staging Impact Locations
|
|
- George Montgomery
- 5 years ago
- Views:
Transcription
1 Appendix Q Launch Debris and Staging Impact Locations K.R. Bohman, Vehicle Systems Division, The Aerospace Corporation, Aerospace Report No. TOR-99 (1103)-2, September, Jettisoned Body Analysis Using ascent trajectory data provided by the contractor, nominal drag impact locations for the launch vehicle jettisoned bodies were determined by trajectory simulation. The solid motor casings, spent core stage, and payload fairing for each Evolved Expendable Launch Vehicle (EELV) configuration were assumed to have similar aerodynamic characteristics as current launch vehicle jettisoned bodies that have similar length to diameter ratios. Thus, tumbling drag coefficients that are used for current launch vehicle range safety analyses (References [1]&[2]) were applied to EELV jettisoned bodies with the appropriate scaling of the aerodynamic reference area and using appropriate jettisoned weights. Separate 3- degree-of-freedom simulations from jettison to surface impact were executed for the Atlas V solid rocket motors (SRMs), the Delta IV solid rocket motors (graphite epoxy motors or GEM 60s), the payload fairings (PLF), and the expended first stages (Stage 1). Note that separation velocities were not modeled. For solid strap-ons and the fairing, the separation velocity is generally of small magnitude and in a lateral direction. Therefore, it would have a very small effect on the calculated impact location. The velocity imparted to the spent core stage could be significant and in the aft direction. If so, the expected impact location would shift uprange by about 10 to 20 nautical miles. The Eastern Range refers to launches from Cape Canaveral Air Force Station and the Western Range refers to launches from Vandenberg Air Force Base. Nominal (No-Wind) Impact Locations for the Atlas V with SRMs and the Delta IV with the larger GEMs: Eastern Range Vehicle Configuration & Mission Jettisoned Body Latitude Longitude Atlas V 511 GTO SRM PLF Stage Atlas V 551 GTO SRMs PLF Stage Atlas V deg Inclined SRMs PLF Stage Delta IV-M+(4,2) GTO GEMs PLF Stage Delta IV-M+(5,4) GTO GEMs PLF Stage SAC/PKG2002.DOC/ DOC Q-1
2 Q-2 SAC/PKG2002.DOC/ DOC
3 SAC/PKG2002.DOC/ DOC Q-3
4 Nominal (No-Wind) Impact Locations for the Atlas V with SRMs and the Delta IV with the larger GEMs: Western Range Vehicle Configuration & Mission Jettisoned Body Latitude Longitude Atlas V 512 Inclined SRM PLF Stage Atlas V 512 Polar SRM PLF Stage Atlas V 552 Inclined SRMs PLF Stage Atlas V 552 Polar SRMs PLF Stage Delta IV-M+(4,2) Inclined GEMs PLF Stage Delta IV-M+(4,2) Polar GEMs PLF Stage Delta IV-M+(5,4) Inclined GEMs PLF Stage Delta IV-M+(5,4) Polar GEMs PLF Stage Q-4 SAC/PKG2002.DOC/ DOC
5 SAC/PKG2002.DOC/ DOC Q-5
6 Q-6 SAC/PKG2002.DOC/ DOC
7 Obviously, the actual jettisoned body impact locations are dependent on the day-of-launch conditions and trajectory. Therefore, jettisoned body impact ellipses are constructed via downrange and crossrange dispersion distances from the nominal impact point. The dispersion distances may be determined by simulating the vehicle performance and wind effects separately and then root sum squaring (RSS) the results together. For this study, notional performance dispersion distances were applied based on experience from other launch vehicles (References [2]&[3]). Wind effects were determined by simulating the jettisoned body s fall through a 99 percent outer profile wind. In each case (headwind, tailwind, left and right crosswinds) the wind was adjusted for azimuth using the appropriate wind rose factor. For this analysis the primary concern was the potential impact region just off the coast, thus, only solid motor jettison ellipses were estimated. The following tables show the estimated dimensions for the SRM/GEM impact ellipses for various EELV configurations involving the use of solid motors. SRM Drag Impact Dispersion Distances from Nominal SRM Impact Locations Atlas V 511 ER GTO Performance dispersions* Wind effects RSSed total Atlas V 551 ER GTO Performance dispersions* Wind effects RSSed total Atlas V 552 ER LEO Inclined Performance dispersions* Wind effects RSSed total *Performance dispersions are estimated based on related studies for other launch vehicles SAC/PKG2002.DOC/ DOC Q-7
8 Estimated Solid Motor Impact Ellipses Atlas V 511 and 551 GTO Launches Estimated Solid Motor Impact Ellipses Atlas V 552 LEO 55 deg Inclined Launch Q-8 SAC/PKG2002.DOC/ DOC
9 SRM Drag Impact Dispersion Distances from Nominal SRM Impact Locations Atlas V 512 WR Inclined Performance dispersions* Wind effects RSSed total Atlas V 512 WR Polar Performance dispersions* Wind effects RSSed total Atlas V 552 WR Inclined Performance dispersions* wind effects RSSed total Atlas V 552 WR Polar Performance dispersions* Wind effects RSSed total *Performance dispersions are estimated based on related studies for other launch vehicles SAC/PKG2002.DOC/ DOC Q-9
10 Current restrictions of over-flight of Channel Islands requires nominal trajectory of IIP west of Santa Rosa Island. All azimuths proposed will be evaluated by Flight Safety Officer to ensure acceptable risk levels for general public are not exceeded. Q-10 SAC/PKG2002.DOC/ DOC
11 GEM Drag Impact Dispersion Distances from Nominal GEM Impact Locations Delta IV-M+ (4,2) ER GTO Performance dispersions* Wind effects RSSed total Delta IV-M+ ( 5,4) ER GTO Performance dispersions* Wind effects RSSed total *Performance dispersions are estimated based on related studies for other launch vehicles Estimated Solid Motor Impact Ellipses Delta IV-M42 and M54 GTO and LEO Launches SAC/PKG2002.DOC/ DOC Q-11
12 GEM Drag Impact Dispersion Distances from Nominal GEM Impact Locations Delta IV-M+ (4,2) WR Inclined Performance dispersions* Wind effects RSSed total Delta IV-M+ (4,2) WR Polar Performance dispersions* Wind effects RSSed total Delta IV-M+ (5,4) WR Inclined Performance dispersions* Wind effects RSSed total Delta IV-M+ ( 5,4) WR Polar Performance dispersions* Wind effects RSSed total *Performance dispersions are estimated based on related studies for other launch vehicles Q-12 SAC/PKG2002.DOC/ DOC
13 Current restrictions of over-flight of Channel Islands requires nominal trajectory of IIP west of Santa Rosa Island. All azimuths proposed will be evaluated by Flight Safety Officer to ensure acceptable risk levels for general public are not exceeded. SAC/PKG2002.DOC/ DOC Q-13
14 Debris Footprint Analysis For any space launch vehicle, there is the possibility of a launch failure early in flight. Hence, there is a risk of vehicle debris impacting the region surrounding the launch site as well as areas downrange of the launch site. The vehicle location, speed, and direction at the time of the explosion as well as the current wind conditions would largely determine a debris footprint from an actual failure. To generate a typical debris footprint that may occur from a launch failure, simulations of fragment trajectories were run using parameters that are consistent with current launch vehicle debris models. The fragments (with ballistic coefficients ranging between 2 and 400 psf) were initialized at some nominal, on-trajectory state, with a randomly selected induced velocity (between 0 and 200 fps in any direction) and then propagated to ground impact in the presence of a mean, annual wind model. Under these assumptions, simulation results show that the debris patterns generally lie on the Air Force Base/Station or just offshore. On the Western Range there is some risk of debris impacting the Point Conception area. More extreme wind conditions could result in debris footprints lying significantly onshore. It should be noted that the Space Wing Safety Offices for both eastern and western ranges adhere to an flight plan approval process for each launch vehicle and mission to ensure that the risks associated with launch vehicle operations do not exceed acceptable limits (Reference [4]). References [1] Sica, D.W., Range Safety Data for Titan IVB-24, Volume III: Trajectory/Jettison Body Data, Lockheed Martin Astronautics, MCR , September [2] Salerno, C.L., Range Safety Data Package For Titan II 23G-7, Lockheed Martin Corporation, MCR , August [3] Delvaux, M.J., Titan IVB-12 TAG Range Safety Data Package, Lockheed Martin Corporation, MCR , December [4] Flight Safety Analyst Training and General Reference Handbook, 30 th Space Wing/ Safety Office, January Q-14 SAC/PKG2002.DOC/ DOC
15 Debris Footprint for On-Trajectory Failure at T + 10 seconds Atlas V 552 LEO 55 deg Inclined Debris Footprint for On-Trajectory Failure at T + 30 seconds Atlas V 552 LEO 55 deg Inclined SAC/PKG2002.DOC/ DOC Q-15
16 Debris Footprint for On-Trajectory Failure at T + 60 seconds Atlas V 552 LEO 55 deg Inclined Debris Footprint for On-Trajectory Failure at T + 20 seconds Delta IV-M+(4,2) GTO Q-16 SAC/PKG2002.DOC/ DOC
17 Debris Footprint for On-Trajectory Failure at T + 30 seconds Delta IV-M+(4,2) GTO Debris Footprint for On-Trajectory Failure at T + 50 seconds Atlas V 512 SAC/PKG2002.DOC/ DOC Q-17
18 Debris Footprint for On-Trajectory Failure at T + 90 seconds Atlas V 512 Debris Footprint for On-Trajectory Failure at T seconds Atlas V 512 Q-18 SAC/PKG2002.DOC/ DOC
19 Debris Footprint for On-Trajectory Failure at T + 30 seconds Delta IV-M+(5,4) Debris Footprint for On-Trajectory Failure at T + 50 seconds Delta IV-M+(5,4) SAC/PKG2002.DOC/ DOC Q-19
20 Debris Footprint for On-Trajectory Failure at T + 70 seconds Delta IV-M+(5,4) Debris Footprint for On-Trajectory Failure at T + 90 seconds Delta IV-M 54 Q-20 SAC/PKG2002.DOC/ DOC
LAUNCH SYSTEMS. Col. John Keesee. 5 September 2003
LAUNCH SYSTEMS Col. John Keesee 5 September 2003 Outline Launch systems characteristics Launch systems selection process Spacecraft design envelope & environments. Each student will Lesson Objectives Understand
More informationCONTROLLED DEORBIT OF THE DELTA IV UPPER STAGE FOR THE DMSP-17 MISSION
CONTROLLED DEORBIT OF THE DELTA IV UPPER STAGE FOR THE DMSP-17 MISSION R. P. Patera (1), K. R. Bohman (2), M. A. Landa (3), C. Pao (4), R. T. Urbano (5), M. A. Weaver (6), Capt. D. C. White (7) (1) The
More informationSuccessful Demonstration for Upper Stage Controlled Re-entry Experiment by H-IIB Launch Vehicle
11 Successful Demonstration for Upper Stage Controlled Re-entry Experiment by H-IIB Launch Vehicle KAZUO TAKASE *1 MASANORI TSUBOI *2 SHIGERU MORI *3 KIYOSHI KOBAYASHI *3 The space debris created by launch
More informationSpace Debris Reentry Hazards
IAASS Space Debris Reentry Hazards William Ailor, Ph.D., The Aerospace Corporation Chair, Space Hazards Technical Committee, International Association for the Advancement of Space Safety (IAASS) Presented
More informationGLAST Mission Overview. Delta II 7920H-10 Cape Canaveral Air Force Station, FL Space Launch Complex-17B
GLAST Mission Overview Delta II 7920H-10 Cape Canaveral Air Force Station, FL Space Launch Complex-17B GLAST United Launch Alliance is proud to launch the Gamma-ray Large Area Space Telescope (GLAST) mission.
More informationCHAPTER 3 PERFORMANCE
PERFORMANCE The launch performance given in this chapter is based on the following assumptions: The LV system parameters being all nominal values; Mass of the LV adapter and the separation system are included
More informationUnited States Active Vertical Launch Success Rates (for the purpose of discussing safety) As of 9 Sept 2016
United States Active Vertical Launch Success Rates (for the purpose of discussing safety) As of 9 Sept 2016 data asof 9/9/2016 (c) 2016, NelsonCFO, Inc., All Rights Reserved 1 Summary Today s US vertical
More informationCHAPTER 3 PERFORMANCE
PERFORMANCE 3.1 Introduction The LM-3A performance figures given in this chapter are based on the following assumptions: Launching from XSLC (Xichang Satellite Launch Center, Sichuan Province, China),
More informationRyan K. Decker * NASA Marshall Space Flight Center, Huntsville, Alabama. Lee Burns Raytheon, Huntsville, Alabama
P.7 THE 006 CAPE CANAVERAL AIR FORCE STATION RANGE REFERENCE ATMOSPHERE MODEL VALIDATION STUDY AND SENSITIVITY ANALYSIS TO THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION'S SPACE SHUTTLE Ryan K. Decker
More informationCHAPTER 3 PERFORMANCE
PERFORMANCE 3.1 Introduction The LM-3B performance figures given in this chapter are based on the following assumptions: Launching from XSLC (Xichang Satellite Launch Center, Sichuan Province, China),
More informationProton Launch System Mission Planner s Guide APPENDIX F. Proton Launch System Options and Enhancements
Proton Launch System Mission Planner s Guide APPENDIX F Proton Launch System Options and Enhancements F. PROTON LAUNCH SYSTEM OPTIONS AND ENHANCEMENTS The missions presented in the previous sections represent
More informationRocket Propulsion Basics Thrust
Rockets 101: A Quick Primer on Propulsion & Launch Vehicle Technologies Steve Heister, Professor School of Aeronautics and Astronautics Purdue University Presentation to AFSAB, 13 January, 2010 Rocket
More informationPlanning, Simulation, and Assessment of Various Missions from Wallops Flight Facility using Satellite Toolkit (STK)
Planning, Simulation, and Assessment of Various Missions from Wallops Flight Facility using Satellite Toolkit (STK) Mitchell 1 Mission Planning Lab, Wallops Flight Facility, Wallops Island, VA, 23337 Satellite
More information1. INTRODUCTION. Gregg Barton Charles Stark Draper Laboratory El Camino Real, Suite 470 Houston, TX
Guided Entry Performance of Low Ballistic Coefficient Vehicles at Mars Ian Meginnis, Zachary Putnam, Ian Clark, Robert Braun Daniel Guggenheim School of Aerospace Engineering Georgia Institute of Technology
More informationSECTION 9 ORBIT DATA - LAUNCH TRAJECTORY
SECTION 9 ORBIT DATA - LAUNCH TRAJECTORY --~'- SECTION 9 LAUNCH TRAJECTORY 9.1 MISSION PROFILE IUE was launched by a three-stage Delta 2914 launch vehicle from Cape Kennedy on January 26, 1978 at l7 h
More informationProton Launch System Mission Planner s Guide SECTION 2. LV Performance
Proton Launch System Mission Planner s Guide SECTION 2 LV Performance 2. LV PERFORMANCE 2.1 OVERVIEW This section provides the information needed to make preliminary performance estimates for the Proton
More informationAEROTHERMODYNAMIC ANALYSIS OF INNOVATIVE HYPERSONIC DEPLOYABLE REENTRY CAPSULES. Raffaele Savino University of Naples Federico II
AEROTHERMODYNAMIC ANALYSIS OF INNOVATIVE HYPERSONIC DEPLOYABLE REENTRY CAPSULES Raffaele Savino University of Naples Federico II Objectives Show the main capabilities of deployable aero-brakes for Earth
More informationInnovative Technologies for Improved Launch Probability Delta IV Day-of-Launch Monitoring
Innovative Technologies for Improved Launch Probability Delta IV Day-of-Launch Monitoring Michael D. Berglund 1 Delta IV Mission Integration Manager michael.d.berglund@boeing.com Kevin Holliday 2 Manager,
More informationLaunch Vehicle Family Album
Launch Vehicle Family Album T he pictures on the next several pages serve as a partial "family album" of NASA launch vehicles. NASA did not develop all of the vehicles shown, but has employed each in its
More informationA Space Debris Alert System for Aviation. US Patent pending Inventor: T. Sgobba - ESA Independent Safety Office
A Space Debris Alert System for Aviation US Patent pending Inventor: T. Sgobba - ESA Independent Safety Office Re-entry breakup basics Space systems in LEO reenter naturally at very shallow angle (
More informationThe Characteristics and Consequences of the Break-up of the Fengyun-1C Spacecraft
The Characteristics and Consequences of the Break-up of the Fengyun-1C Spacecraft N. Johnson, E. Stansbery, J.-C. Liou, M. Horstman, C. Stokely, D. Whitlock NASA Orbital Debris Program Office NASA Johnson
More informationINTER-AGENCY SPACE DEBRIS COORDINATION COMMITTEE (IADC) SPACE DEBRIS ISSUES IN THE GEOSTATIONARY ORBIT AND THE GEOSTATIONARY TRANSFER ORBITS
INTER-AGENCY SPACE DEBRIS COORDINATION COMMITTEE (IADC) SPACE DEBRIS ISSUES IN THE GEOSTATIONARY ORBIT AND THE GEOSTATIONARY TRANSFER ORBITS Presented to: 37-th Session of the SCIENTIFIC AND TECHNICAL
More informationSolid Propellant Autonomous DE-Orbit System [SPADES] Co-authors: T. Soares J. Huesing A. Cotuna I. Carnelli L. Innocenti
Solid Propellant Autonomous DE-Orbit System [SPADES] Co-authors: T. Soares J. Huesing A. Cotuna I. Carnelli L. Innocenti SPADES introduction SPADES is: Cross-cutting system to support the compliance of
More information21 JSTS Vol. 27, No. 2
21 JSTS Vol. 27, No. 2 Technical Challenges and Study on Guided Reentry Flight for Capsule Spacecraft Shuichi MATSUMOTO 1), Yoshinori KONDOH 1), Takane IMADA 1) and Naoki SATO 1) 1) Japan Aerospace Exploration
More informationA METHODOLOGY FOR EVALUATING THE EXPLOSIVE HAZARDS OF LARGE SOLID ROCKET MOTORS. Paul K. Salzman, TRW Strategic Systems Division
A METHODOLOGY FOR EVALUATING THE EXPLOSIVE HAZARDS OF LARGE SOLID ROCKET MOTORS Paul K. Salzman, TRW Strategic Systems Division INTRODUCTION An important part of launch operations (vs. test) of a new large
More informationStatistical methods to address the compliance of GTO with the French Space Operations Act
Statistical methods to address the compliance of GTO with the French Space Operations Act 64 th IAC, 23-27 September 2013, BEIJING, China H.Fraysse and al. Context Space Debris Mitigation is one objective
More informationRocket Science 102 : Energy Analysis, Available vs Required
Rocket Science 102 : Energy Analysis, Available vs Required ΔV Not in Taylor 1 Available Ignoring Aerodynamic Drag. The available Delta V for a Given rocket burn/propellant load is ( ) V = g I ln 1+ P
More informationGuided Entry Performance of Low Ballistic Coefficient Vehicles at Mars
Guided Entry Performance of Low Ballistic Coefficient Vehicles at Mars AE8900 MS Special Problems Report Space Systems Design Lab (SSDL) Guggenheim School of Aerospace Engineering Georgia Institute of
More informationThe Interstellar Boundary Explorer (IBEX) Mission Design: A Pegasus Class Mission to a High Energy Orbit
The Interstellar Boundary Explorer (IBEX) Mission Design: A Pegasus Class Mission to a High Energy Orbit Ryan Tyler, D.J. McComas, Howard Runge, John Scherrer, Mark Tapley 1 IBEX Science Requirements IBEX
More informationSatellite Engineering
Satellite Engineering Universidad de Concepción November 2009 Gaëtan Kerschen Space Structures & Systems Lab University of Liège Satellite Engineering Universidad de Concepción November 2009 Day 3: Satellite
More informationHuman Spaceflight Value Study Was the Shuttle a Good Deal?
Human Spaceflight Value Study Was the Shuttle a Good Deal? Andy Prince Billy Carson MSFC Engineering Cost Office/CS50 20 October 2016 Purpose Examine the Space Shuttle Program Relative to its Goals and
More informationINNOVATIVE STRATEGY FOR Z9 REENTRY
INNOVATIVE STRATEGY FOR Z9 REENTRY Gregor Martens*, Elena Vellutini**, Irene Cruciani* *ELV, Corso Garibaldi, 34 Colleferro (Italy) **Aizoon, Viale Città d Europa 681, 144, Roma (Italy) Abstract Large
More informationLAUNCH OPTIONS FOR MARS NETWORK MISSIONS USING SMALL SPACECRAFT. Walter K Daniel'
LAUNCH OPTIONS FOR MARS NETWORK MISSIONS USING SMALL SPACECRAFT Walter K Daniel' The currentlyplanned Mars Global Network Mission calls for a Delta II launch to deploy spacecraft that will place small
More informationMission Overview Vandenberg Air Force Base, CA. Delta II Aquarius/SAC-D
Delta II Aquarius/SAC-D Mission Overview Vandenberg Air Force Base, CA United Launch Alliance (ULA) is proud to launch the Aquarius/SAC-D mission. Aquarius/SAC-D will be launched aboard a Delta II 7320-10C
More informationFederal Aviation Administration Optimal Aircraft Rerouting During Commercial Space Launches
Federal Aviation Administration Optimal Aircraft Rerouting During Commercial Space Launches Rachael Tompa Mykel Kochenderfer Stanford University Oct 28, 2015 1 Motivation! Problem: Launch vehicle anomaly
More informationMultidisciplinary Optimization Techniques for Branching Trajectories
Multidisciplinary Optimization Techniques for Branching Trajectories J. R. Olds L. A. Ledsinger Georgia Institute of Technology Atlanta, GA A Companion Paper to an AIAA Young Members Off-the-Drawing-Board
More informationUSA Space Debris Environment, Operations, and Policy Updates
USA Space Debris Environment, Operations, and Policy Updates Presentation to the 48 th Session of the Scientific and Technical Subcommittee Committee on the Peaceful Uses of Outer Space United Nations
More informationCygnus Loop from the NOAO
Cygnus Loop from the NOAO Longmont Astronomy Society Newsletter January 2013 Cover Picture: As an end of the year finale, the National Optical Astronomy Observatory (NOAO) and WIYN partners offer this
More informationSection 8: Getting Things into Space: Rockets and Launch Requirements
Section 8: Getting Things into Space: Rockets and Launch Requirements To place an object in orbit, a rocket must be able to do two things: carry the object to the proper altitude and give it the correct
More informationSolid Propellant Autonomous DE-Orbit System [SPADES]
Solid Propellant Autonomous DE-Orbit System [SPADES] Solid Propellant Rocket Motor development Presented: Rogier Schonenborg Study: T. Soares J. Huesing A. Cotuna W. van Meerbeeck I. Carnelli L. Innocenti
More informationClimate. Annual Temperature (Last 30 Years) January Temperature. July Temperature. Average Precipitation (Last 30 Years)
Climate Annual Temperature (Last 30 Years) Average Annual High Temp. (F)70, (C)21 Average Annual Low Temp. (F)43, (C)6 January Temperature Average January High Temp. (F)48, (C)9 Average January Low Temp.
More informationOptimized Trajectory Shaping Guidance for an Air-to-Ground Missile Launched from a Gunship. Craig Phillips Ernie Ohlmeyer Shane Sorenson
Optimized Trajectory Shaping Guidance for an Air-to-Ground Missile Launched from a Gunship Craig Phillips Ernie Ohlmeyer Shane Sorenson Overview Mission Scenario Notional Munition Concept Guidance Laws
More informationP7.7 A CLIMATOLOGICAL STUDY OF CLOUD TO GROUND LIGHTNING STRIKES IN THE VICINITY OF KENNEDY SPACE CENTER, FLORIDA
P7.7 A CLIMATOLOGICAL STUDY OF CLOUD TO GROUND LIGHTNING STRIKES IN THE VICINITY OF KENNEDY SPACE CENTER, FLORIDA K. Lee Burns* Raytheon, Huntsville, Alabama Ryan K. Decker NASA, Marshall Space Flight
More informationA trendsetting Micro-Launcher for Europe
A trendsetting Micro-Launcher for Europe Farid Gamgami German Aerospace Center (DLR), Space Launcher Systems Analysis (SART) Bremen, Germany Farid.Gamgami@dlr.de ABSTRACT In this paper we analyse a potential,
More informationSTUDY THE SPACE DEBRIS IMPACT IN THE EARLY STAGES OF THE NANO-SATELLITE DESIGN
ARTIFICIAL SATELLITES, Vol. 51, No. 4 2016 DOI: 10.1515/arsa-2016-0014 STUDY THE SPACE DEBRIS IMPACT IN THE EARLY STAGES OF THE NANO-SATELLITE DESIGN Mohammed Chessab Mahdi Al-Furat Al-Awsat Technical
More informationUpper Atmospheric Monitoring for Ares I-X Ascent Loads and Trajectory Evaluation on the Day-of-Launch
1st AIAA Atmospheric and Space Environments Conference 22-25 June 2009, San Antonio, Texas AIAA 2009-3781 Upper Atmospheric Monitoring for Ares I-X Ascent Loads and Trajectory Evaluation on the Day-of-Launch
More informationScience Review Board
Science Review Board Delta IV Initiated UFO Reports C C Paulson (13110) Abstract A recent Delta IV rocket launch from Cape Canaveral Air Force Station produced a multitude of UFO reports. Those reports
More informationLaunch and Deployment Analysis for a Small, MEO, Technology Demonstration Satellite
Launch and Deployment Analysis for a Small, MEO, Technology Demonstration Satellite Tyson Karl Smith 1 Stephen Anthony Whitmore 2 Utah State University, Logan, UT, 84322-4130 A trade study investigation
More informationSpace Debris Re-entries and Aviation Safety
IAASS Space Debris Re-entries and Aviation Safety By Tommaso Sgobba IAASS President (iaass.president@gmail.com) International Association for the Advancement of Space Safety 1 Space debris as re-entry
More informationUSV TEST FLIGHT BY STRATOSPHERIC BALLOON: PRELIMINARY MISSION ANALYSIS
USV TEST FLIGHT BY STRATOSPHERIC BALLOON: PRELIMINARY MISSION ANALYSIS A. Cardillo a, I. Musso a, R. Ibba b, O.Cosentino b a Institute of Information Science and Technologies, National Research Council,
More informationFinal Examination 2015
THE UNIVERSITY OF SYDNEY School of Aerospace, Mechanical and Mechatronic Engineering AERO 2705: Space Engineering 1 Final Examination 2015 READ THESE INSTRUCTIONS CAREFULLY! Answer at least 4 (four of
More informationRAPID GEOSYNCHRONOUS TRANSFER ORBIT ASCENT PLAN GENERATION. Daniel X. Junker (1) Phone: ,
RAPID GEOSYNCHRONOUS TRANSFER ORBIT ASCENT PLAN GENERATION Daniel X. Junker (1) (1) LSE Space GmbH, Argelsrieder Feld 22, 82234 Wessling, Germany, Phone: +49 160 9111 6696, daniel.junker@lsespace.com Abstract:
More informationLAUNCHES AND LAUNCH VEHICLES. Dr. Marwah Ahmed
LAUNCHES AND LAUNCH VEHICLES Dr. Marwah Ahmed Outlines 2 Video (5:06 min) : https://youtu.be/8t2eyedy7p4 Introduction Expendable Launch Vehicles (ELVs) Placing Satellite into GEO Orbit Introduction 3 Introduction
More informationDesign of Orbits and Spacecraft Systems Engineering. Scott Schoneman 13 November 03
Design of Orbits and Spacecraft Systems Engineering Scott Schoneman 13 November 03 Introduction Why did satellites or spacecraft in the space run in this orbit, not in that orbit? How do we design the
More informationMajor fragmentation of Atlas 5 Centaur upper stage B (SSN #40209)
Major fragmentation of Atlas 5 Centaur upper stage 2014 055B (SSN #40209) Vladimir Agapov IAA Space Debris Committee meeting Bremen, 29 Sep 2018 Outline Atlas 5 Centaur overview 30 Aug 2018 anomaly in
More informationGuidance Concept for a Mars Ascent Vehicle First Stage
NASA/TM-2000-210618 Guidance Concept for a Mars Ascent Vehicle First Stage Eric M. Queen Langley Research Center, Hampton, Virginia November 2000 The NASA STI Program Office... in Profile Since its founding,
More informationSmall Satellite Aerocapture for Increased Mass Delivered to Venus and Beyond
Small Satellite Aerocapture for Increased Mass Delivered to Venus and Beyond Adam Nelessen / Alex Austin / Joshua Ravich / Bill Strauss NASA Jet Propulsion Laboratory Ethiraj Venkatapathy / Robin Beck
More informationVariations of Solid Rocket Motor Preliminary Design for Small TSTO launcher
Variations of Solid Rocket Motor Preliminary Design for Small TSTO launcher Etienne Dumont Space Launcher Systems Analysis (SART), DLR, Bremen, Germany Etienne.Dumont@dlr.de Abstract Several combinations
More informationNATIONAL TRANSPORTATION SAFETY BOARD WASHINGTON, D.C.
DOCKET NO. SA-516 EXHIBIT NO. 22A NATIONAL TRANSPORTATION SAFETY BOARD WASHINGTON, D.C. TRAJECTORY STUDY (16 Pages) NATIONAL TRANSPORTATION SAFETY BOARD Office of Research and Engineering Washington, DC
More informationMAE 180A: Spacecraft Guidance I, Summer 2009 Homework 4 Due Thursday, July 30.
MAE 180A: Spacecraft Guidance I, Summer 2009 Homework 4 Due Thursday, July 30. Guidelines: Please turn in a neat and clean homework that gives all the formulae that you have used as well as details that
More informationLaunch strategy for Indian lunar mission and precision injection to the Moon using genetic algorithm
Launch strategy for Indian lunar mission and precision injection to the Moon using genetic algorithm VAdimurthy, R V Ramanan, S R Tandon and C Ravikumar Aeronautics Entity, Vikram Sarabhai Space Centre,
More informationOrbit Design Marcelo Suárez. 6th Science Meeting; Seattle, WA, USA July 2010
Orbit Design Marcelo Suárez Orbit Design Requirements The following Science Requirements provided drivers for Orbit Design: Global Coverage: the entire extent (100%) of the ice-free ocean surface to at
More informationInformation furnished in conformity with General Assembly resolution 1721 B (XVI) by States launching objects into orbit or beyond
United Nations General Assembly Distr.: General 23 October 2007 English Original: French Committee on the Peaceful Uses of Outer Space Information furnished in conformity with General Assembly resolution
More informationUnmanned Aircraft Hurricane Reconnaissance. Pat Fitzpatrick GeoSystems Research Institute Mississippi State University Stennis Space Center branch
Unmanned Aircraft Hurricane Reconnaissance Pat Fitzpatrick GeoSystems Research Institute Mississippi State University Stennis Space Center branch Outline Motivation Unmanned Aircraft Systems (UAS) [also
More informationEffects of Mitigation Measures on the Space Debris Environment
Effects of Mitigation Measures on the Space Debris Environment Carsten Wiedemann 1, Sven Flegel 1, Johannes Gelhaus 1, Heiner Klinkrad 2, Detlef Alwes 3, Peter Vörsmann 1 1 Institute of Aerospace Systems,
More informationOrbital Debris Mitigation
Orbital Debris Mitigation R. L. Kelley 1, D. R. Jarkey 2, G. Stansbery 3 1. Jacobs, NASA Johnson Space Center, Houston, TX 77058, USA 2. HX5 - Jacobs JETS Contract, NASA Johnson Space Center, Houston,
More informationUSA Space Debris Environment, Operations, and Modeling Updates
USA Space Debris Environment, Operations, and Modeling Updates Presentation to the 51 st Session of the Scientific and Technical Subcommittee Committee on the Peaceful Uses of Outer Space United Nations
More informationSAILING THE PLANETS: PLANETARY EXPLORATION FROM GUIDED BALLOONS. 7 th Annual Meeting of the NASA Institute for Advanced Concepts
SAILING THE PLANETS: PLANETARY EXPLORATION FROM GUIDED BALLOONS 7 th Annual Meeting of the NASA Institute for Advanced Concepts DR. ALEXEY PANKINE GLOBAL AEROSPACE CORPORATION SAILING THE PLANETS 1 MARS
More informationFormation Flying and Rendezvous and Docking Simulator for Exploration Missions (FAMOS-V2)
Formation Flying and Rendezvous and Docking Simulator for Exploration Missions (FAMOS-V2) Galder Bengoa, F. Alonso, D. García, M. Graziano (GMV S.A.) Dr. Guillermo Ortega (ESA/ESTEC) 2nd ESA Workshop on
More informationUniversal Space Vehicle Design Concept to Defend the Earth against Asteroidal-Cometary Danger
Universal Space Vehicle Design Concept to Defend the Earth against Asteroidal-Cometary Danger Abstract V.A. Volkov, V.A. Danilkin, V.G. Degtyar, G.G. Sytyi State Rocket Centre "Makeyev Design Bureau",
More informationMULTI-STAGE SUBORBITAL LAUNCHER MODAL AND DYNAMIC TEST PROGRAM
Review of the Air Force Academy No 3 (30) 2015 MULTI-STAGE SUBORBITAL LAUNCHER MODAL AND DYNAMIC TEST PROGRAM Mihai MIHAILA-ANDRES*, Flore LICA*, Paul-Virgil ROSU** * Institute for Theoretical & Experimental
More informationBall Aerospace & Technologies Corp. & L Garde Inc.
Ball Aerospace & Technologies Corp. & L Garde Inc. Rapid De-Orbit of LEO Space Vehicles Using Towed owed Rigidizable Inflatable nflatable Structure tructure (TRIS) Technology: Concept and Feasibility Assessment
More informationMars Entry, Descent, and Landing Parametric Sizing and Design Space Visualization Trades
Mars Entry, Descent, and Landing Parametric Sizing and Design Space Visualization Trades Kristina Alemany 1, Grant Wells 1, John Theisinger 1, Ian Clark 1, Dr. Robert Braun 2 Space Systems Design Laboratory
More informationPlanetary Protection Trajectory Analysis for the Juno Mission
AIAA/AAS Astrodynamics Specialist Conference and Exhibit 18-21 August 2008, Honolulu, Hawaii AIAA 2008-7368 Planetary Protection Trajectory Analysis for the Juno Mission Try Lam 1, Jennie R. Johannesen
More informationMars 2020 Atmospheric Modeling for Flight Mechanics Simulations
Mars 2020 Atmospheric Modeling for Flight Mechanics Simulations Soumyo Dutta, David Way, and Carlie Zumwalt NASA Langley Research Center Gregorio Villar Jet Propulsion Laboratory International Planetary
More informationDescribe Define Explain Identify Identify Explain Identify Describe Define Describe Define Describe Describe Name Describe
In this chapter, we will look at what happens when rocketry is used to send payloads into orbit or to destinations in space. Velocity is one major factor in this process. The other major factor is the
More informationLaunch abort trajectory optimisation for reusable launch vehicles
Launch abort trajectory optimisation for reusable launch vehicles Federico Toso and Christie Alisa Maddock Centre for Future Air Space Transportation Technologies University of Strathclyde, Glasgow, G1
More informationAnalysis of Throw Distance Produced by a Sub-detonative Munition Response
Analysis of Throw Distance Produced by a Sub-detonative Munition Response E.L. Baker, J. Grau, J.A. Cordes, Status E. Update Vazquez, T. 08 August 2007 Madsen, D. Suarez, Y. Wu, D. Carlucci and D. Carra
More informationOrbital Anomaly Detection and Application of Space Object
Orbital Anomaly Detection and Application of Space Object Lei CHEN *, Xianzong BAI, Taotao ZHANG College of Aerospace and Materials Engineering, National University of Defense Technology, Changsha 473,China
More informationLIMITING ORBITAL DEBRIS
BY ORDER OF THE COMMANDER SMC Tailoring SMC-T-003 19 March 2010 ------------------------ Supersedes: New issue Air Force Space Command SPACE AND MISSILE SYSTEMS CENTER TAILORING LIMITING ORBITAL DEBRIS
More informationEXPANDING KNOWLEDGE ON REAL SITUATION AT HIGH NEAR-EARTH ORBITS
EXPANDING KNOWLEDGE ON REAL SITUATION AT HIGH NEAR-EARTH ORBITS Vladimir Agapov (1,2), Denis Zelenov (1), Alexander Lapshin (3), Zakhary Khutorovsky (4) (1) TsNIIMash, 4 Pionerskay Str., Korolev, Moscow
More informationDevelopment and Flight Testing of Energy Management Algorithms for Small-Scale Sounding Rockets
Development and Flight Testing of Energy Management Algorithms for Small-Scale Sounding Rockets and Shane Robinson The development, implementation, and ight results for a navigation algorithm and an energy
More informationMars Sample Return (MSR) Mission BY: ABHISHEK KUMAR SINHA
Mars Sample Return (MSR) Mission BY: ABHISHEK KUMAR SINHA Samples returned to terrestrial laboratories by MSR Mission would be analyzed with state-of the-art instrumentation providing unprecedented insight
More information2024 Mars Sample Return Design Overview
2024 Mars Sample Return Design Overview Andrew Hoffman sentinel72@gmail.com Abstract Scheduled for two launches set during two consecutive launch windows with the first launch occurring in 2024, the landmark
More informationFin design mission. Team Members
Fin design mission Team Members Mission: Your team will determine the best fin design for a model rocket. You will compare highest altitude, flight characteristics, and weathercocking. You will report
More informationTUNDRA DISPOSAL ORBIT STUDY
TUNDRA DISPOSAL ORBIT STUDY Al an B. Jenki n (1 ), John P. McVey (2 ), James R. Wi l son (3 ), Marl on E. Sorge (4) (1) The Aerospace Corporation, P.O. Box 92957, Los Angeles, CA 90009-2957, USA, Email:
More informationThe Analysis of Dispersion for Trajectories of Fire-extinguishing Rocket
The Analysis of Dispersion for Trajectories of Fire-extinguishing Rocket CRISTINA MIHAILESCU Electromecanica Ploiesti SA Soseaua Ploiesti-Tirgoviste, Km 8 ROMANIA crismihailescu@yahoo.com http://www.elmec.ro
More informationTrajectory Optimization for a Mars Ascent Vehicle
AIAA SPACE Forum 13-16 September 216, Long Beach, California AIAA/AAS Astrodynamics Specialist Conference 216. All rights reserved 1.2514/6.216-5441 Trajectory Optimization for a Mars Ascent Vehicle Joel
More informationThe Launch of Gorizont 45 on the First Proton K /Breeze M
The Launch of Gorizont 45 on the First Proton K / Fred D. Rosenberg, Ph.D. Space Control Conference 3 April 2001 FDR -01 1 This work is sponsored by the Air Force under Air Force Contract F19628-00-C-0002
More informationThe 2013 MAVEN Mission To Mars. Bruce Jakosky MAVEN Principal Investigator University of Colorado
The 2013 MAVEN Mission To Mars Bruce Jakosky MAVEN Principal Investigator University of Colorado Summary of MAVEN Status We ve been developing MAVEN since 2003; now under 3 months to launch! All science
More informationIAC-16.A Jason A. Reiter a *, David B. Spencer b
IAC-16.A6.7.5 Trading Spacecraft Propellant Use and Mission Performance to Determine the Optimal Collision Probability in Emergency Collision Avoidance Scenarios Jason A. Reiter a *, David B. Spencer b
More information4.0 Detailed Design g Payload Vehicle Overview
Project Bellerophon 32 4.0 Detailed Design 4.1 200g Payload 4.1.1 Vehicle Overview The launch vehicle carrying the 200 g payload (Fig. 4.1.1.1) hitches a ride on a balloon up to an altitude of 30 km where
More informationSCIENCE WITH DIRECTED AERIAL DR. ALEXEY PANKINE GLOBAL AEROSPACE CORPORATION SAILING THE PLANETS
: SCIENCE WITH DIRECTED AERIAL ROBOT EXPLORERS (DARE) DR. ALEXEY PANKINE GLOBAL AEROSPACE CORPORATION 1 NEW ARCHITECTURE FOR PLANETARY EXPLORATION KEY ELEMENTS: Long-Duration Planetary Balloon Platforms
More informationPREDICTING THE ATMOSPHERIC RE-ENTRY OF SPACE DEBRIS THROUGH THE QB50 ENTRYSAT MISSION
PREDICTING THE ATMOSPHERIC RE-ENTRY OF SPACE DEBRIS THROUGH THE QB50 ENTRYSAT MISSION Y. Prevereaud (1), F. Sourgen (2), D. Mimoun (3), A.Gaboriaud (4), J-L. Verant (5), and J-M. Moschetta (6) (1) ONERA
More informationLRO Lunar Reconnaissance Orbiter
LRO Lunar Reconnaissance Orbiter Launch Date: June 18, 2009 Destination: Earth s moon Reached Moon: June 23, 2009 Type of craft: Orbiter Intended purpose: to map the moon like never before, add additional
More informationEUROPE ARIANE 1 ARIANE 1
. IDENTIFICATION. Name ARIANE.2 Classification Family : ARIANE Series : Version : ARIANE Category : SPACE LAUNCH VEHICLE Class : Medium Launch Vehicle (MLV) Type : Expendable Launch Vehicle (ELV).3 Manufacturer
More informationCase Studies for Uncertainty Quantification of a High-fidelity Spacecraft Oriented Break-up Tool. Bent Fritsche, HTG Stijn Lemmens, ESA
Case Studies for Uncertainty Quantification of a High-fidelity Spacecraft Oriented Break-up Tool Bent Fritsche, HTG Stijn Lemmens, ESA 8th European Symposium on Aerothermodynamics for Space Vehicles Lisbon,
More informationSLR-based orbit determination and orbit prediction of space debris objects
Geodätische Woche Congress Center Essen, 8.- 10. Oktober 2013 SLR-based orbit determination and orbit prediction of space debris objects Harald Wirnsberger, Oliver Baur, Georg Kirchner Space Research Institute
More informationInterim Access to the International Space Station
Utah State University DigitalCommons@USU All Graduate Theses and Dissertations Graduate Studies 12-2009 Interim Access to the International Space Station Tyson Karl Smith Utah State University Follow this
More informationAnalysis of the Briz-M Propellant Tank (35698) Fragmentation Using the Velocity Perturbations of the Fragments
Advances in Aerospace Science and Applications. Volume 4, Number 1 (14), pp. 11-19 Research India Publications http://www.ripublication.com Analysis of the Briz-M Propellant Tank (35698) Fragmentation
More information