Comparison of Return to Launch Site Options for a Reusable Booster Stage
|
|
- Cynthia Simpson
- 6 years ago
- Views:
Transcription
1 Comparison of Return to Launch Site Options for a Reusable Booster Stage Barry Mark Hellman Space System Design Lab (SSDL) School of Aerospace Engineering USAF ASC/XRE barry.hellman@wpafb.af.mil Advisor Dr. John R. Olds In Partial Fulfillment of the Requirements for the Degree of Master of Science in Aerospace Engineering p. 1
2 Presentation Overview Motivation of Study Historical Background Study Conclusions Technical Approach Staging Point Comparison Results of Trajectory and Vehicle Sizing Future Plans p. 2
3 Study Motivation Current desire to develop reusable booster Study uses expendable upper stage (ARES) Booster recovery options Return to Launch Site (RTLS) Land at a site downrange RTLS Requirements Velocity direction must be reversed Staging occurs in near vacuum Enough margin to land safely 15,000 ft over launch site (KSC) p. 3
4 Booster RTLS Methods Glideback Re-enter at high alpha, aerodynamic turn, and glide to launch site Completely unpowered after staging Flyback Re-enter at high alpha, aerodynamic turn Glide to subsonic cruising altitude Use airbreathing engine to cruise back to launch site Currently felt to be the proper solution Boostback Pitch booster around after staging Fire ascent engine until booster s velocity vector points towards launch site Unpowered re-entry and glide to launch site Compare methods based on gross and dry weight 15,000 lb payload direct insertion into 100 nmi circular Boostback Shows Significant Potential p. 4
5 Historical Look at Reusable Boosters Glideback Future Space Transportation System (early 80 s) Flyback Liquid Flyback Space Shuttle Boosters (80 s 90 s) Tokyo University Flyback vs. Glideback Study ( 03) Boostback Kistler K-1 (late 90 s - present ) Which is Best for a Hybrid System? p. 5
6 Technical Approach Baseline Configuration (Hybrid) LOX Tank RP Tank LOX/RP Engines 110 ft 28 ft LOX Tank RP Tank 165 ft p. 6
7 Technical Approach Branching Trajectories Three branches of flight Ascent Orbital RTLS Requires an MDO method handle growth of booster due to RTLS Orbital Branch Ascent Branch RTLS Branch p. 7
8 Technical Approach Design Structure Matrix Configuration Aerodynamics (APAS) Rocket Propulsion (REDTOP-2) Airbreathing Propulsion (PARA) (If Needed) Ascent Trajectory (3D POST) RTLS Trajectory (3D POST) Avionics Weights (SESAW) Weights & Sizing (EXCEL and Solver) p. 8
9 250 Trajectories Minimum Dry Mass Vehicles 200 Return to Launch Site Altitude (nmi) Ascent Glideback (Stage at 3.2) Flyback (Stage 6.4) Boostback (Stage at 5.2) Downrange (nmi) p. 9
10 RTLS Booster Required MRs 3.5 Ascent Required Mass Ratio Minimum Dry Weight Points RTLS Mass MR = Mass initial final Flyback RTLS MR Boostback RTLS MR Flyback Ascent MR Boostback Ascent MR Staging Mach p. 10
11 Gross Mass Comparison 1,000,000 Points are Lowest Dry Mass Design Total Gross Weight (lbm) 950, , , % 6.02% Flyback Glideback Boostback Minimum Dry Weight Points 800, Staging Mach Gross Mass is not a Direct Indicator of Cost p. 11
12 Dry Mass Comparison 105, ,000 Total Dry Weight (lbm) 95,000 90,000 85, % Flyback Glideback Boostback 80,000 75, % Staging Mach Minimum Dry Weight Points Unfortunately Dry Mass is not a Direct Indicator of Hybrid System Cost A Cost Trade will be Needed p. 12
13 Optimal Staging Points Parameters from Optimal Staging Point Glideback Flyback (Lowest Dry Mass) Boostback (Lowest Dry Mass) Staging Ideal V (ft/sec) 7,248 11,200 10,200 Staging Mach Number Staging Altitude (ft) 106, , ,224 Staging FPA (deg) Max Re-Entry Mach Total Gross Mass (lbm) 822, , ,300 Upper Stage Dry Weight (lbm) 20,100 17,200 18,600 Total Dry Mass (lbm) 78,100 95,800 81,000 Booster Length (ft) Upper Stage Length (ft) RTLS Time (sec) Too Close to Call: Need Cost Study p. 13
14 Results Glideback Lowest dry and gross mass Low Complexity Requires No TPS (Re-entry Mach 1.8) Probably not lowest cost due to large expendable upper stage Flyback Very low RTLS propellant required Flyback requires turbofan and installation hardware Highest dry mass Powered landing and go-around capability Long Return TOF ~ 78 min Requires Significant TPS (Re-entry Mach 6.9) Boostback Requires Minimal TPS (Re-entry Mach 2.7) Short Return TOF ~ 13 Boostback requires more return propellant Unpowered landing Boostback Deserves Consideration Cost Study Needed p. 14
15 Future Work Need to pick staging point based on cost for hybrid system Booster cost is amortized over flights New upper stage for each launch Staging concerns Rocket relight vs. continuous burn Separation More in depth look at TPS requirements Compare maintenance requirements between Boostback and Flyback p. 15
16 Backup p. 16
17 Previously Studied RTLS Boosters Future Space Transportation System (Glideback) Space Shuttle Replacement (80 s Design) Stage at Mach 3 Liquid Flyback Space Shuttle Boosters (Flyback) Stage at Mach 5.2 at 163,000 ft Coast to apogee of 270,000 ft Cruise at 18,500 ft and Mach 0.48 p. 17
18 Previously Studied RTLS Boosters Kistler K-1 (Boostback) Mach kft Parachute Landing 12 min after liftoff p. 18
19 Technical Approach Contributing Analyses Aerodynamics APAS Airbreathing Propulsion Isp ~ 3600 sec SFC ~ 1/hr Rocket Propulsion Spaceworks Engineering Inc. s REDTOP 2 LOX/RP, Gas-Generator, 2500 psi Weights & Sizing Booster weights based on MER from Dr. Ted Talay NASA LARC Trajectory POST 3D p. 19
20 Glideback Final Altitude 50,000 45,000 Final Altitude Over Launch Site (ft) 40,000 35,000 30,000 25,000 20,000 15,000 10,000 5, Staging Mach Number p. 20
21 Ground Track p. 21
22 Boostback Booster and Upper 100,000 Total Dry Weight (lbm) 90,000 80,000 70,000 60,000 50,000 40,000 30,000 Booster Upper Total 20,000 10, Staging Mach Number p. 22
Multidisciplinary 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 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 informationSOLAR ROCKET PROPULSION Ground and Space Technology Demonstration. Dr. Michael Holmes, AFRL/PRSS
SOLAR ROCKET PROPULSION Ground and Space Technology Demonstration Dr. Michael Holmes, AFRL/PRSS Solar Thermal Propulsion Concept Parabolic Mirror Sun Create thrust by collecting and focusing sunlight to
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 informationMass Estimating Relationships MARYLAND. Review of iterative design approach Mass Estimating Relationships (MERs) Sample vehicle design analysis
Mass Estimating Relationships Review of iterative design approach Mass Estimating Relationships (MERs) Sample vehicle design analysis 2006 David L. Akin - All rights reserved http://spacecraft.ssl.umd.edu
More informationAnalysis of the Staging Maneuver and Booster Glideback Guidance for a Two-Stage, Winged, Fully Reusable Launch Vehicle
NASA Technical Paper 3335 April 1993 Analysis of the Staging Maneuver and Booster Glideback Guidance for a Two-Stage, Winged, Fully Reusable Launch Vehicle J. Christopher Naftel and Richard W. Powell NASA
More informationDEPARTMENT OF AEROSPACE ENGINEERING, IIT MADRAS M.Tech. Curriculum
DEPARTMENT OF AEROSPACE ENGINEERING, IIT MADRAS M.Tech. Curriculum SEMESTER I AS5010 Engg. Aerodyn. & Flt. Mech. 3 0 0 3 AS5020 Elements of Gas Dyn. & Propln. 3 0 0 3 AS5030 Aircraft and Aerospace Structures
More informationA little more about costing Review of iterative design approach Mass Estimating Relationships (MERs) Sample vehicle design analysis
A little more about costing Review of iterative design approach (MERs) Sample vehicle design analysis 2004 David L. Akin - All rights reserved http://spacecraft.ssl. umd.edu Internal Rate of Return Discount
More informationParametric Design MARYLAND. The Design Process Regression Analysis Level I Design Example: Project Diana U N I V E R S I T Y O F.
Parametric Design The Design Process Regression Analysis Level I Design Example: U N I V E R S I T Y O F MARYLAND 2003 David L. Akin - All rights reserved http://spacecraft.ssl.umd.edu Parametric Design
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 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 informationMARYLAND. The Design Process Regression Analysis Level I Design Example: UMd Exploration Initiative U N I V E R S I T Y O F.
Parametric Design The Design Process Regression Analysis Level I Design Example: UMd Exploration Initiative U N I V E R S I T Y O F MARYLAND 2004 David L. Akin - All rights reserved http://spacecraft.ssl.
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 informationRocket Performance MARYLAND U N I V E R S I T Y O F. Rocket Performance. ENAE Launch and Entry Vehicle Design
The rest of orbital mechanics The rocket equation Mass ratio and performance Structural and payload mass fractions Regression analysis Multistaging Optimal ΔV distribution between stages Trade-off ratios
More informationHow Small Can a Launch Vehicle Be?
UCRL-CONF-213232 LAWRENCE LIVERMORE NATIONAL LABORATORY How Small Can a Launch Vehicle Be? John C. Whitehead July 10, 2005 41 st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit Tucson, AZ Paper
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 informationRocket Performance MARYLAND U N I V E R S I T Y O F. Rocket Performance. ENAE Launch and Entry Vehicle Design
The rocket equation Mass ratio and performance Structural and payload mass fractions Regression analysis Multistaging Optimal ΔV distribution between stages Trade-off ratios Parallel staging Modular staging
More informationPropulsion Systems Design MARYLAND. Rocket engine basics Survey of the technologies Propellant feed systems Propulsion systems design
Propulsion Systems Design Rocket engine basics Survey of the technologies Propellant feed systems Propulsion systems design 2008 David L. Akin - All rights reserved http://spacecraft.ssl.umd.edu 1 Propulsion
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 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 informationRocket Performance MARYLAND U N I V E R S I T Y O F. Rocket Performance. ENAE 483/788D - Principles of Space Systems Design
Lecture #03 September 5, 2017 The rocket equation Mass ratio and performance Structural and payload mass fractions Regression analysis Multistaging Optimal ΔV distribution between stages Trade-off ratios
More informationMultistage Rockets. Chapter Notation
Chapter 8 Multistage Rockets 8.1 Notation With current technology and fuels, and without greatly increasing the e ective I sp by air-breathing, a single stage rocket to Earth orbit is still not possible.
More informationRocket Performance MARYLAND U N I V E R S I T Y O F. Rocket Performance. ENAE 483/788D - Principles of Space Systems Design
Lecture #06 September 17, 2015 The rocket equation Mass ratio and performance Structural and payload mass fractions Regression analysis Multistaging Optimal ΔV distribution between stages Trade-off ratios
More informationComparison of Return to Launch Site Options for a Reusable Booster Stage
Comparison of Return to Launh Site Options for a Reusable Booster Stage AE8900 MS Speial Problems Report Spae Systems Design Lab (SSDL) Shool of Aerospae Engineering Georgia Institute of Tehnology Atlanta,
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 informationRocket Performance MARYLAND U N I V E R S I T Y O F. Rocket Performance. ENAE 483/788D - Principles of Space Systems Design
Lecture #06 September 18, 2014 The rocket equation Mass ratio and performance Structural and payload mass fractions Regression analysis Multistaging Optimal ΔV distribution between stages Trade-off ratios
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 informationBifrost: A 4 th Generation Launch Architecture Concept
Bifrost: A 4 th Generation Launch Architecture Concept Rohrschneider, R.R., Young, D., St.Germain, B., Brown, N., Crowley, J., Maatsch, J., Olds, J.R. (Advisor) Abstract Space Systems Design Lab School
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 informationInvestigation of Combined Airbreathing/Rocket. Air Launch of Micro-Satellites from a Combat Aircraft
6th Responsive Space Conference AIAA-RS6-008-5003 Investigation of Combined Airbreathing/Rocket Propulsion for Air Launch of Micro-Satellites from a Combat Aircraft Avichai Socher and Alon Gany Faculty
More informationTechnology of Rocket
Technology of Rocket Parts of Rocket There are four major parts of rocket Structural system Propulsion system Guidance system Payload system Structural system The structural system of a rocket includes
More informationThe Journey Back into Space: Orbiter Processing at the Kennedy Space Center
The Journey Back into Space: Orbiter Processing at the Kennedy Space Center written by Angie Smibert (copyright NASA) FADE IN: EXT - COLUMBIA ORBIT AND RE-ENTRY Columbia re-enters the Earth's atmosphere
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 informationSystem Design and Optimization of a Hypersonic Launch Vehicle
System Design and Optimization of a Hypersonic Launch Vehicle A project present to The Faculty of the Department of Aerospace Engineering San Jose State University in partial fulfillment of the requirements
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 informationParametric Design MARYLAND. The Design Process Level I Design Example: Low-Cost Lunar Exploration U N I V E R S I T Y O F
Parametric Design The Design Process Level I Design Example: Low-Cost Lunar Exploration U N I V E R S I T Y O F MARYLAND 2005 David L. Akin - All rights reserved http://spacecraft.ssl.umd.edu Parametric
More informationOpportunities for Small Satellites and Space Research Using the K-1 Vehicle
SSC99-X-5 Opportunities for Small Satellites and Space Research Using the K-1 Vehicle Debra Facktor Lepore, Gary Lai, and Tom Taylor Kistler Aerospace Corporation 3760 Carillon Point, Kirkland, Washington
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 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 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 informationMissile Interceptor EXTROVERT ADVANCED CONCEPT EXPLORATION ADL P Ryan Donnan, Herman Ryals
EXTROVERT ADVANCED CONCEPT EXPLORATION ADL P- 2011121203 Ryan Donnan, Herman Ryals Georgia Institute of Technology School of Aerospace Engineering Missile Interceptor December 12, 2011 EXTROVERT ADVANCED
More informationRocket Performance Analysis Using Electrodynamic Launch Assist
Rocket Performance Analysis Using Electrodynamic Launch Assist Alejandra Uranga *, Daniel R. Kirk, and Hector Gutierrez Florida Institute of Technology, Melbourne, Florida, 32901 Rainer B. Meinke Advanced
More informationEngineering Sciences and Technology. Trip to Mars
PART 2: Launch vehicle 1) Introduction : A) Open this file and save it in your directory, follow the instructions below. B) Watch this video (0 to 1min03s) and answer to questions. Give the words for each
More informationIV. Rocket Propulsion Systems. A. Overview
IV. Rocket Propulsion Systems A. Overview by J. M. Seitzman for AE 4451 Jet and Rocket Propulsion Seitzman Rocket Overview-1 Rocket Definition Rocket Device that provides thrust to a vehicle by accelerating
More informationMIKE HAWES VICE PRESIDENT & ORION PROGRAM MANAGER
MIKE HAWES VICE PRESIDENT & ORION PROGRAM MANAGER NASA S EXPLORATION SYSTEM EXPLORATION DESTINATIONS 100s of Miles 1,000s of Miles 10,000s of Miles 100,000s of Miles 1,000,000s of Miles 10,000,000s of
More informationFAHLLS. Frequent Access Heavy Lift Launch System EXTROVERT ADVANCED CONCEPT EXPLORATION ADL P Josh Sandler, Mark Lieberbaum
EXTROVERT ADVANCED CONCEPT EXPLORATION ADL P- 2013043001 Josh Sandler, Mark Lieberbaum Georgia Institute of Technology School of Aerospace Engineering FAHLLS Frequent Access Heavy Lift Launch System May
More informationPROPULSIONE SPAZIALE. Chemical Rocket Propellant Performance Analysis
Chemical Rocket Propellant Performance Analysis Sapienza Activity in ISP-1 Program 15/01/10 Pagina 1 REAL NOZZLES Compared to an ideal nozzle, the real nozzle has energy losses and energy that is unavailable
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 informationThe Design Process Level I Design Example: Low-Cost Lunar Exploration Amplification on Initial Concept Review
Parametric Design The Design Process Level I Design Example: Low-Cost Lunar Exploration Amplification on Initial Concept Review U N I V E R S I T Y O F MARYLAND 2008 David L. Akin - All rights reserved
More informationModel Rocketry. The Science Behind the Fun
Model Rocketry The Science Behind the Fun Topics History of Rockets Sir Isaac Newton Laws of Motion Rocket Principles Flight of a Model Rocket Rocket Propulsion Forces at Work History Rockets and rocket
More informationAerosciences Considerations in the Design of a Powered Descent Phase for Human-Scale Mars Lander Vehicles
Aerosciences Considerations in the Design of a Powered Descent Phase for Human-Scale Mars Lander Vehicles Ashley Korzun, Karl Edquist, Alicia Dwyer Cianciolo NASA Langley Research Center Jake Tynis Analytical
More informationRocket Propulsion Overview
Rocket Propulsion Overview Seitzman Rocket Overview-1 Rocket Definition Rocket Device that provides thrust to a vehicle by accelerating some matter (the propellant) and exhausting it from the rocket Most
More informationElectrically Propelled Cargo Spacecraft for Sustained Lunar Supply Operations
42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 9-12 July 2006, Sacramento, California AIAA 2006-4435 Electrically Propelled Cargo Spacecraft for Sustained Lunar Supply Operations Christian
More informationRocket Performance MARYLAND U N I V E R S I T Y O F. Ballistic Entry ENAE Launch and Entry Vehicle Design
Rocket Performance Parallel staging Modular staging Standard atmospheres Orbital decay due to drag Straight-line (no gravity) entry based on atmospheric density 1 2014 David L. Akin - All rights reserved
More informationConcurrent Trajectory and Vehicle Optimization for an Orbit Transfer. Christine Taylor May 5, 2004
Concurrent Trajectory and Vehicle Optimization for an Orbit Transfer Christine Taylor May 5, 2004 Presentation Overview Motivation Single Objective Optimization Problem Description Mathematical Formulation
More informationENAE 791 Course Overview
ENAE 791 Challenges of launch and entry Course goals Web-based Content Syllabus Policies Project Content 1 2016 David L. Akin - All rights reserved http://spacecraft.ssl.umd.edu Space Transportation System
More informationLAUNCH 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 informationInitial Trajectory and Atmospheric Effects
Initial Trajectory and Atmospheric Effects G. Flanagan Alna Space Program July 13, 2011 Introduction A major consideration for an earth-based accelerator is atmospheric drag. Drag loses mean that the gun
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 informationBasic Ascent Performance Analyses
Basic Ascent Performance Analyses Ascent Mission Requirements Ideal Burnout Solution Constant & Average Gravity Models Gravity Loss Concept Effect of Drag on Ascent Performance Drag Profile Approximation
More informationDesign And Analysis Of Thrust Chamber Of A Cryogenic Rocket Engine S. Senthilkumar 1, Dr. P. Maniiarasan 2,Christy Oomman Jacob 2, T.
Design And Analysis Of Thrust Chamber Of A Cryogenic Rocket Engine S. Senthilkumar 1, Dr. P. Maniiarasan 2,Christy Oomman Jacob 2, T. Vinitha 2 1 Research Scholar, Department of Mechanical Engineering,
More informationPropulsion and Energy Systems. Kimiya KOMURASAKI, Professor, Dept. Aeronautics & Astronautics, The University of Tokyo
Propulsion and Energy Systems Kimiya KOMURASAKI, Professor, Dept. Aeronautics & Astronautics, The University of Tokyo Schedule Space propulsion with non-chemical technologies 10/5 1) Space Propulsion Fundamentals
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 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 informationOPEN THALES ALENIA SPACE
ISSUE : 01 Page : 2/11 CHANGE RECORDS ISSUE DATE CHANGE RECORDS AUTHOR 01 First Issue F. Cogo ISSUE : 01 Page : 3/11 TABLE OF CONTENTS 1. INTRODUCTION...4 2. RADFLIGHT MISSION OVERVIEW...5 3. INSTRUMENTATION
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 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 informationDARE Dynamic Abort Risk Evaluator Analysis Process Document
DARE Dynamic Abort Risk Evaluator Analysis Process Document Version 3.0 2/28/07 Safety & Risk Section 350 Broadway 8 th Floor New York, NY 10013 SAIC PROPRIETARY INFORMATION. The information contained
More informationToward the Final Frontier of Manned Space Flight
Toward the Final Frontier of Manned Space Flight Image: Milky Way NASA Ryann Fame Luke Bruneaux Emily Russell Toward the Final Frontier of Manned Space Flight Part I: How we got here: Background and challenges
More informationPerformance Characterization of Supersonic Retropropulsion for Application to High-Mass Mars Entry, Descent, and Landing
Performance Characterization of Supersonic Retropropulsion for Application to High-Mass Mars Entry, Descent, and Landing Ashley M. Korzun 1 and Robert D. Braun 2 Georgia Institute of Technology, Atlanta,
More informationPower, Propulsion, and Thermal Preliminary Design Review James Black Matt Marcus Grant McLaughlin Michelle Sultzman
Power, Propulsion, and Thermal Preliminary Design Review James Black Matt Marcus Grant McLaughlin Michelle Sultzman Outline 1. Crew Systems Design Selection 2. Thermal Requirements and Design 3. Power
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 informationThe Role of Zero Dynamics in Aerospace Systems
The Role of Zero Dynamics in Aerospace Systems A Case Study in Control of Hypersonic Vehicles Andrea Serrani Department of Electrical and Computer Engineering The Ohio State University Outline q Issues
More informationDevelopment, Structure, and Application of MAST: A Generic Mission Architecture Sizing Tool
47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Confere 1-4 May 2006, Newport, Rhode Island AIAA 2006-1717 Development, Structure, and Application of MAST: A Generic Mission
More informationMARS DROP. Matthew A. Eby Mechanical Systems Department. Vehicle Systems Division/ETG The Aerospace Corporation May 25, 2013
MARS DROP Matthew A. Eby Mechanical Systems Department Vehicle Systems Division/ETG The Aerospace Corporation May 25, 2013 The Aerospace Corporation 2013 The Aerospace Corporation (Aerospace), a California
More informationOptimization and Design for Heavy Lift Launch Vehicles
University of Tennessee, Knoxville Trace: Tennessee Research and Creative Exchange Masters Theses Graduate School 5-2012 Optimization and Design for Heavy Lift Launch Vehicles Paul Andreas Ritter University
More informationThank you for your purchase!
Thank you for your purchase! Please be sure to save a copy this document to your local computer. This activity is copyrighted by the AIMS Education Foundation. All rights reserved. No part of this work
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 informationTechnology and Space Exploration
Technology and Space Exploration When did people first become interested in learning about Space and the Universe? Records from the earliest civilizations show that people studied and asked questions about
More informationEntry, Descent and Landing Technology Advancement
Entry, Descent and Landing Technology Advancement Dr. Robert D. Braun May 2, 2017 EDL Technology Investments Have Enabled Seven Increasingly-Complex Successful U.S. Landings on Mars Sojourner: 25 kg, 1997
More informationX-34 HIGH PRESSURE NITROGEN REACTION CONTROL SYSTEM DESIGN AND ANALYSIS
X-34 HIGH PRESSURE NITROGEN REACTION CONTROL SYSTEM DESIGN AND ANALYSIS BRIAN A. WINTERS, P.E. * TREY WALTERS, P.E. Orbital Sciences Corporation Applied Flow Technology Dulles, Virginia Woodland Park,
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 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 informationCalifornia State Science Fair
California State Science Fair Working Model for Model Rocket Altitude Prediction Edward Ruth drruth@ix.netcom.com This is a complete model of all the forces acting on a model rocket in flight. It calculates
More informationIntro Physics (Each individual student will complete his or her own lab report)
Intro Physics May/June 2016 Name (Each individual student will complete his or her own lab report) Bottle Rocket Lab - Target Launch Date: Group Members: Post Prototype Launch questions (max 8 points)
More informationMinimum-Fuel Optimal Trajectory for Reusable First-Stage Rocket Landing Using Particle Swarm Optimization
Minimum-Fuel Optimal Trajectory for Reusable First-Stage Rocket Landing Using Particle Swarm Optimization Kevin Spencer G. Anglim, Zhenyu Zhang, Qingbin Gao Abstract Reusable launch vehicles (RLVs) present
More informationIntroduction to Aerospace Engineering
Introduction to Aerospace Engineering 5. Aircraft Performance 5.1 Equilibrium Flight In order to discuss performance, stability, and control, we must first establish the concept of equilibrium flight.
More informationPlanning for a Supersonic Retropropulsion Test in the NASA Langley Unitary Plan Wind Tunnel
National Aeronautics and Space Administration Planning for a Supersonic Retropropulsion Test in the NASA Langley Unitary Plan Wind Tunnel Karl Edquist (Karl.T.Edquist@nasa.gov) and Ashley Korzun NASA Langley
More informationAdvanced drop tests from stratospheric balloons
Advanced drop tests from stratospheric balloons Mr Mikael Töyrä SSC, Esrange, P.O. Box 802, SE-981 28 Kiruna, Sweden Stratospheric balloons are used for scientific measurements, drop tests of aerospace
More informationAMSAT Phase IV Propulsion and Attitude Control Systems Conceptual Design Doug May Thiokol Corporation
AMSAT Phase V Propulsion and Attitude Control Systems Conceptual Design Doug May Thiokol Corporation Amateur Radio Satellite Corporation (AMSAT) is developing a satellite designated Phase V for operation
More informationspace shuttle nasa 06201DA27B68A94CCD9D0B70CE4EF216 Space Shuttle Nasa 1 / 6
Space Shuttle Nasa 1 / 6 2 / 6 3 / 6 Space Shuttle Nasa NASA's space shuttle fleet began setting records with its first launch on April 12, 1981 and continued to set high marks of achievement and endurance
More informationMultidisciplinary Design Optimization of a Two-Stage-to-Orbit Reusable Launch Vehicle with Ethanol-Fueled Rocket-Based Combined Cycle Engines *
Trans. Japan Soc. Aero. Space Sci. Vol. 6, No. 5, pp. 265 275, 217 Multidisciplinary Design Optimization of a Two-Stage-to-Orbit Reusable Launch Vehicle with Ethanol-Fueled Rocket-Based Combined Cycle
More informationIntro Physics (Each individual student will complete his or her own lab report)
Intro Physics May/June 204 Name (Each individual student will complete his or her own lab report) Bottle Rocket Lab - Target Launch Date: Group Members: Pre Launch questions (max 26 points) - Due date:
More informationCharacteristics of some monopropellants (Reprinted from H. Koelle, Handbook of Astronautical Engineering, McGraw-Hill, 1961.)
16.522, Space Propulsion Prof. Manuel Martinez-Sanchez Lecture 7: Bipropellant Chemical Thrusters and Chemical Propulsion Systems Considerations (Valving, tanks, etc) Characteristics of some monopropellants
More informationDevelopment of Multi-Disciplinary Simulation Codes and their Application for the Study of Future Space Transport Systems
24 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES Development of Multi-Disciplinary Simulation Codes and their Application for the Study of Future Space Transport Systems Yukimitsu. Yamamoto JAPAN
More informationTrajectory Optimization for Ascent and Glide Phases Using Gauss Pseudospectral Method
Trajectory Optimization for Ascent and Glide Phases Using Gauss Pseudospectral Method Abdel Mageed Mahmoud, Chen Wanchun, Zhou Hao, and Liang Yang Abstract The trajectory optimization method for ascent
More information7th AIAA/ASME Joint Thermophysics and Heat Transfer Conference June 15-18, 1998 / Albuquerque, NM
AIAA 98-285 Mars Ascent Vehicle Flight Analysis P. N. Desai R. D. Braun W. C. Engelund F. M. Cheatwood NASA Langley Research Center Hampton, VA J. A. Kangas Jet Propulsion Laboratory, California Institute
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 informationApplied Thermodynamics - II
Gas Turbines Sudheer Siddapureddy sudheer@iitp.ac.in Department of Mechanical Engineering Jet Propulsion - Classification 1. A heated and compressed atmospheric air, mixed with products of combustion,
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 information