DOCSLIB.ORG

Modeling of a Tethered Testbed for a VTVL Vehicle

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Modeling of a Tethered Testbed for a VTVL Vehicle Hindawi Modelling and Simulation in Engineering Volume 2020, Article ID 8523514, 13 pages https://doi.org/10.1155/2020/8523514 Research Article Modeling of a Tethered Testbed for a VTVL Vehicle Marco Sagliano ,1 Stephan Theil,1 Johanna Schramm,2 and Matthias Schwarzwald2 1German Aerospace Center, Robert Hooke Straße 7, 28359 Bremen, Germany 2University of Bremen, Bibliothekstraße 1, 28359 Bremen, Germany Correspondence should be addressed to Marco Sagliano; [email protected] Received 8 January 2020; Revised 20 May 2020; Accepted 3 September 2020; Published 1 October 2020 Academic Editor: Mohamed B. Trabia Copyright © 2020 Marco Sagliano et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. This paper proposes an algorithm for modeling a three-dimensional tethered environment for testing vertical-take off, vertical landing vehicles. The method is able to take several geometrical configurations into account and combines the classical catenary model with the elasticity theory to predict the forces acting on the lander in quasistatic conditions, i.e., in conditions of hovering, where the motion of the vehicle is reduced. Numerical results confirm that the method is potentially able to provide real-time solutions, which can be included as feedforward contributions in the design of tethered experiments. 1. Introduction test the hovering capability, one of the first milestones to be achieved towards the development of the full free-flight capa- Recent and future missions involve a precise descent and bility. On the other side, a tethered configuration provides a landing in addition to the ascent phase to reach the target safe environment for the vehicle. It is mitigating the effect orbit. This can be on the one hand the powered descent of failures until the technology under development is mature and landing of a reusable first stage of a launch vehicle as it enough to allow a reliable free flight. Moreover, the use of was demonstrated several times by SpaceX with its Falcon 9 tethered configurations allows for making the test facility a launch system. On the other hand, precise descent and land- protective area for the team of engineers and researchers. ing has been applied to planetary missions and is foreseen for Thus, they can safely and closely track the progress in the many more future missions to Mars and to the Moon. The development of the vehicle. development of guidance, navigation, and control (GNC) This paper addresses the problem of modeling the teth- techniques for these applications remains a challenging task ered testbed during the hovering experiments of the VTVL although several missions have been already successfully vehicle EAGLE (Environment for Autonomous GNC Land- completed. Several ideas to support and accelerate the ing Experiments) developed by the German Aerospace Cen- GNC development using demonstrators have been con- ter (DLR) [9–11]. The modeling focuses on the tethering ceived in the past, for example NASA’s Morpheus lander effects on the vehicle in hovering conditions. It can poten- [1, 2] or the HOMER demonstrator of Airbus Defense and tially be extended to any vehicle where it is needed to include Space [3, 4]. In these and other developments of space sys- the forces generated by the tethers in the design of the tems, a wide variety of tethered experimental setups has been controller. created [1, 2, 5–8]. The modeling starts with the use of the catenary, a well- For vertical-take off, vertical landing (VTVL) vehicles, known concept in the field of structures and mechanics the use of tethered solutions has pros and cons. One of the [12], which physical meaning is the ideal shape that a hang- main drawbacks is the impact of the tethers on the flight ing rope or chain has when subject to its own weight while characteristics of the vehicle. They introduce effects which having its endpoints constrained in two points in the space. do not exist in the final free-flight scenario. A further down- The catenary is slightly different from the parabolic profile, side is that the allowed flight envelope is usually quite small which is the shape that intuition would (erroneously) sug- due to limited tether length. Nevertheless, it is sufficient to gest. The catenary concept is widely used and can be 2 Modelling and Simulation in Engineering �(x , y ) b x y extended to multibody net structures [13]. For instance, it � � ( b, b) can be used for the modeling of railway overheads or power lines as in [14] or [15]. In these applications, however, the shape is the most important aspect and is therefore the main factor to be studied. As a consequence, the forces at the sus- pension points are not so emphasized. In [16], the catenary curve and the corresponding equi- librium of forces are discussed in the frame of the develop- ment of a controller for an unmanned vehicle. However, this work focuses on the design of a controller which mini- mizes the tension in the ropes. Richardson focused instead y on the entanglement detection of swarms of robot in urban environments [17]. This paper focuses on the modeling and the analysis of x complex tethered configurations including hanging ropes o x y attached to the vehicle while hovering. In addition, elasticity ( 0, 0) is included in the model. The purpose is to know the forces which act on the VTVL vehicle and can be included as Figure 1: Example of catenary curve. Point a and b are the feed-forward contribution in the design of the EAGLE con- suspension points. Point o is the vertex. troller. We propose an algorithm implementing the afore- mentioned theories of catenary and elasticity that computes the forces acting on EAGLE in an iterative way. y, with a horizontal x-coordinate and a vertical y-coordi- The paper is structured as follows. In Section 2.1, the nate. An example is depicted in Figure 1. modeling of a hanging rope and the related concept of cate- We can derive three equations for three unknown param- r x y nary are introduced. The corresponding forces at the suspen- eters , 0, and 0. We know the position of the two suspen- sion points with and without elasticity are computed. sion points, defined as a = ðxa, yaÞ and b = ðxb, ybÞ. Numerical validations of the proposed modeling are carried Moreover, the length of the rope l is known. out in Section 2.2. In Section 3.1, the specific geometrical test x − x setup for EAGLE is described. The setup includes different a 0 hxðÞa = ya = r cosh + y rope materials and a configuration of three ropes which are r 0, x − x linked to the VTVL vehicle in a triangular configuration. b 0 hxðÞb = y = r cosh + y , In Section 3.2, the iterative solving procedure is illus- b r 0 ð2Þ sffiffiffiffiffiffiffiffiffiffiffiffiffiffiffiffiffiffiffiffiffi trated. It is based on a MATLAB implementation, but it ðx ðx b dh 2 b x − x can be transferred to any other software. Section 4 shows l dx 0 dx: = 1+ dx = cosh r some numerical results obtained with the proposed algo- xa xa rithm. In general, every single point within the test area can be tested. However, for a better characterization of the sce- With this equations, we get the following system: nario involving the EAGLE motion, two specific hovering x − x paths are analyzed, and the accuracy of the computed solu- y y − r a 0 ð Þ tions is discussed. Finally, in Section 5, we draw some conclu- 0 = a cosh r , 3 sions on the work done. xb − x xa − x y = r cosh 0 − r cosh 0 + y ð4Þ 2. Rope Modeling b r r a, xb − x xa − x 2.1. A Brief Review. In this section, a brief introduction about l = r sinh 0 − r sinh 0 : ð5Þ the modeling of a static rope is given, and the computation r r procedure of the forces at the suspension points is explained. For a simplification of the system of equations, the cate- The function describing the shape of a hanging rope sub- nary curve is shifted. The suspension points are moved, such ject to a constant gravity is called catenary [18]. The catenary fi fi that the rst suspension point is on the origin. Thus, a local curve is de ned as coordinate system positioned at the first suspension point is used. x − x Now, Equations (4) and (5) can be used to obtain a for- hxðÞ r 0 y ð Þ = cosh + 0, 1 x r mula for 0: y − y x x x −r b a b + a : ð Þ r x x 0 = artanh + 6 where is the radius in the vertex, 0 is the -coordinate of l 2 y y ff the vertex and 0 is the -o set of the vertex. x y y A two-dimensional - reference frame is used for the Here, 0 is eliminated. Therefore, Equations (5) and (6) – x description of the motion. The gravity is directed towards become a system of two equations for two unknowns 0 Modelling and Simulation in Engineering 3 r y F and , whereas 0 can be computed by evaluating Equation b (3) at point a. x − x y y − r a 0 : ð Þ 0 = a cosh r 7 We can rewrite the condition on the length of the rope represented by Equation (6), which gives hi x − x 2 F b a 2 2 a 2r sinh − l + ðÞyb − ya =0: ð8Þ 2r This is a nonlinear equation, only depending on r, which y cannot be solved analytically.
Load more

Recommended publications
  • First Level Design and System Design of Janus Liquid Oxygen-Liquid Methane Lander Jahir Fernandez University of Texas at El Paso, J [email protected]
    University of Texas at El Paso DigitalCommons@UTEP Open Access Theses & Dissertations 2017-01-01 First Level Design And System Design Of Janus Liquid Oxygen-Liquid Methane Lander Jahir Fernandez University of Texas at El Paso, [email protected] Follow this and additional works at: https://digitalcommons.utep.edu/open_etd Part of the Mechanical Engineering Commons Recommended Citation Fernandez, Jahir, "First Level Design And System Design Of Janus Liquid Oxygen-Liquid Methane Lander" (2017). Open Access Theses & Dissertations. 444. https://digitalcommons.utep.edu/open_etd/444 This is brought to you for free and open access by DigitalCommons@UTEP. It has been accepted for inclusion in Open Access Theses & Dissertations by an authorized administrator of DigitalCommons@UTEP. For more information, please contact [email protected]. FIRST LEVEL DESIGN AND SYSTEM DESIGN OF JANUS LIQUID OXYGEN-LIQUID METHANE LANDER JAHIR FERNANDEZ Master’s Program in Mechanical Engineering APPROVED: Ahsan Choudhuri, Ph.D., Chair John F. Chessa, Ph.D., Co-chair Luis Rene Contreras, Ph.D. Charles H. Ambler, Ph.D. Dean of the Graduate School Copyright © By Jahir Fernandez 2017 FIRST LEVEL DESIGN AND SYSTEM DESIGN OF JANUS LIQUID OXYGEN-LIQUID METHANE LANDER By JAHIR FERNANDEZ, B.S. MECHANICAL ENGINEERIN THESIS Presented to the Faculty of the Graduate School of The University of Texas at El Paso in Partial Fulfillment of the Requirements for the Degree of MASTER OF SCIENCE Department of Mechanical Engineering THE UNIVERSITY OF TEXAS AT EL PASO December 2017 Acknowledgements I would like to thank Dr. Ahsan Choudhuri for the opportunity to work at the cSETR. It has been an amazing experience working at the center, where the research has opened many doors for me and through which I was able to intern with NASA at Marshall Space Flight Center.
    [Show full text]
  • 액체로켓 메탄엔진 개발동향 및 시사점 Development Trends of Liquid
    Journal of the Korean Society of Propulsion Engineers Vol. 25, No. 2, pp. 119-143, 2021 119 Technical Paper DOI: https://doi.org/10.6108/KSPE.2021.25.2.119 액체로켓 메탄엔진 개발동향 및 시사점 임병직 a, * ㆍ 김철웅 a⋅ 이금오 a ㆍ 이기주 a ㆍ 박재성 a ㆍ 안규복 b ㆍ 남궁혁준 c ㆍ 윤영빈 d Development Trends of Liquid Methane Rocket Engine and Implications Byoungjik Lim a, * ㆍ Cheulwoong Kim a⋅ Keum-Oh Lee a ㆍ Keejoo Lee a ㆍ Jaesung Park a ㆍ Kyubok Ahn b ㆍ Hyuck-Joon Namkoung c ㆍ Youngbin Yoon d a Future Launcher R&D Program Office, Korea Aerospace Research Institute, Korea b School of Mechanical Engineering, Chungbuk National University, Korea c Guided Munitions Team, Hyundai Rotem, Korea d Department of Aerospace Engineering, Seoul National University, Korea * Corresponding author. E-mail: [email protected] ABSTRACT Selecting liquid methane as fuel is a prevailing trend for recent rocket engine developments around the world, triggered by its affordability, reusability, storability for deep space exploration, and prospect for in-situ resource utilization. Given years of time required for acquiring a new rocket engine, a national-level R&D program to develop a methane engine is highly desirable at the earliest opportunity in order to catch up with this worldwide trend towards reusing launch vehicles for competitiveness and mission flexibility. In light of the monumental cost associated with development, fabrication, and testing of a booster stage engine, it is strategically a prudent choice to start with a low-thrust engine and build up space application cases.
    [Show full text]
  • Forever Remembered
    July 2015 Vol. 2 No. 7 National Aeronautics and Space Administration KENNEDY SPACE CENTER’S magazine FOREVER REMEMBERED Earth Solar Aeronautics Mars Technology Right ISS System & Research Now Beyond NASA’S National Aeronautics and Space Administration LAUNCH KENNEDY SPACE CENTER’S SCHEDULE SPACEPORT MAGAZINE Date: July 3, 12:55 a.m. EDT Mission: Progress 60P Cargo Craft CONTENTS Description: In early July, the Progress 60P resupply vehicle — 4 �������������������Solemn shuttle exhibit shares enduring lessons an automated, unpiloted version of the Soyuz spacecraft that is used to ����������������Flyby will provide best ever view of Pluto 10 bring supplies and fuel — launches 14 ����������������New Horizons spacecraft hones in on Pluto to the International Space Station. http://go.nasa.gov/1HUAYbO 24 ����������������Firing Room 4 used for RESOLVE mission simulation Date: July 22, 5:02 p.m. EDT 28 ����������������SpaceX, NASA will rebound from CRS-7 loss Mission: Expedition 44 Launch to 29 ����������������Backup docking adapter to replace lost IDA-1 the ISS Description: In late July, Kjell SHUN FUJIMURA 31 ����������������Thermal Protection System Facility keeping up Lindgren of NASA, Kimiya Yui of JAXA and Oleg Kononenko of am an education specialist in the Education Projects and 35 ����������������New crew access tower takes shape at Cape Roscosmos launch aboard a Soyuz I Youth Engagement Office. I work to inspire students to pursue science, technology, engineering, mathematics, or 36 ����������������Innovative thinking converts repair site into garden spacecraft from the Baikonur Cosmodrome, Kazakhstan to the STEM, careers and with teachers to better integrate STEM 38 ����������������Proposals in for new class of launch services space station.
    [Show full text]
  • Foundational Methane Propulsion Related Technology Efforts, and Challenges for Applications to Human Exploration Beyond Earth Orbit
    https://ntrs.nasa.gov/search.jsp?R=20160006983 2019-07-23T15:36:47+00:00Z Foundational Methane Propulsion Related Technology Efforts, and Challenges for Applications to Human Exploration Beyond Earth Orbit SPACE PROPULSION 2016 MARRIOTT PARK HOTEL, ROME, ITALY / 2-6 May 2016 Thomas Brown Mark Klem Patrick McRight NASA Engineering and Safety Center Propulsion Division Propulsion Department NASA Marshall Space Flight Center NASA Glenn Research Center NASA Marshall Space Flight Center Huntsville, AL 35812 Cleveland, Ohio 44135 Huntsville, AL 35812 Agenda • Introduction • Background • Needs for Beyond Earth Orbit (BEO) human exploration • LOX/CH4 Igniters • Reaction Control System (RCS) Thrusters • Large (870 – 1000 lbf) LOX/LH2 and LOX/Ethanol thrusters (TRW & Aerojet) • 100 lbf LOX/CH4 thrusters (Aerojet & Northrop Grumman) • Main Engine Injector Parametric Testing • Pressure Fed Main Engine Efforts • 7500 lbf LOX/CH4 (XCOR & KT Engineering) • 5500 lbf LOX/CH4 (Aerojet) • Additively Manufactured 4K Regeneratively Cooled Engine • Pump Fed Main Engine Efforts • Common Extensible Cryogenic Engine – LOX/LH2 throttle-able engine • 7000 lbf LOX/LH2 (TRW/Northrop Grumman) • 7000 lbf LOX/LH2 two stage injector • Current efforts with the Additive Manufacturing Demonstration engine • Cryogenic Fluid Management (CFM) and Distribution • Integrated Systems Demonstration • Challenges for future Human Exploration • Summary and Conclusions 2 Introduction Background • Human, beyond earth orbit, exploration architecture studies have identified Methane/Oxygen
    [Show full text]
  • Cfd Kinetic Scheme Validation for Liquid Rocket Engine Fuelled by Oxygen/Methane
    DOI: 10.13009/EUCASS2019-680 8TH EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS) CFD KINETIC SCHEME VALIDATION FOR LIQUID ROCKET ENGINE FUELLED BY OXYGEN/METHANE Pasquale Natale*, Guido Saccone** and Francesco Battista*** * Centro Italiano Ricerche Aerospaziali Via Maiorise, 81043 Capua (CE), Italy, [email protected] **Centro Italiano Ricerche Aerospaziali Via Maiorise, 81043 Capua (CE), Italy,[email protected] ***Centro Italiano Ricerche Aerospaziali Via Maiorise, 81043 Capua (CE), Italy,[email protected] Abstract In recent years, greater attention has been paid to green propellants, among those liquid methane is one of the most promising choice. This has also been encouraged by the abolition of hydrazine for its intrinsic human-rating concerns. On the other hand, the adoption of methane as a fuel introduces some issues about modelling. Detailed kinetic schemes are required to properly reconstruct combustion process. This is especially true for rocket propulsion problems, in which the combustion is characterized by high pressure and not stoichiometric mixture ratio. Moreover, detailed scheme may not be feasible for CFD applications, due to high computational cost. For this reason, adoption of reduced schemes is encouraged, even if detailed mechanism description is required. In the present work, a reduced kinetic scheme (HPRB, by CIRA) will be presented for a specific LRE application. Some experimental firing-tests (i.e. FSBB test-campaign) will then be compared with model results, in order to validate the proposed model. 1. Introduction Traditionally, high performance rocket engines have used LOX and hydrogen or LOX and kerosene, while, as such, methane has not yet been used in a commercial launch vehicle.
    [Show full text]
  • Parallel LOX-Methane Engine Development
    https://ntrs.nasa.gov/search.jsp?R=20110014012 2019-08-30T16:17:05+00:00Z View metadata, citation and similar papers at core.ac.uk brought to you by CORE provided by NASA Technical Reports Server Project Morpheus Main Engine Development and Preliminary Flight Testing Robert L. Morehead1 NASA/Johnson Space Center, Houston, TX, 77058 A LOX/Methane rocket engine was developed for a prototype terrestrial lander and then used to fly the lander at Johnson Space Center. The development path of this engine is outlined, including unique items such as variable acoustic damping and variable film cooling. Nomenclature ALHAT = Autonomous Landing and Hazard Avoidance Technology Hz = Hertz ISP = Specific Impulse lbf = Pound-force GNC = Guidance, Navigation, and Control JSC = Johnson Space Center RCS = Reaction Control System VTB = Vertical Test Bed VTOL = Vertical Take Off and Landing I. Introduction he NASA/Johnson Space Center Vertical Test Bed (VTB, a.k.a. Morpheus) is an integrated testing platform capable of short VTOL flights using liquid oxygen and liquid methane propellants for both the main engine and T 2 RCS systems . This paper outlines the development of the main engine for the VTB. Morpheus main engine requirements: 4,200 lbf thrust, 215 sec ISP, a 4:1 throttle range, and a minimum run time of 210 seconds. The VTB is designed to operate with or without active propellant pressurization, so the engines must also be able to operate under stable pressure or blowdown operation. Additionally, the engine must be able to respond to changes in desired thrust very quickly and be insensitive to rapid engine rotation due to gimballing.
    [Show full text]
  • SARGE Users Guide
    EXOS Aerospace Systems & Technologies, Inc. PAYLOAD USER GUIDE (PUG) 1 SARGE – Payload User Guide – Rev. 3 SARGE FAMILY OF VEHICLES INDEX 1. INTRODUCTION 1.1. Corporate Information Page 3 1.2. Purpose & The NASA Flight Opportunities Program Page 3 2. THE SARGE VEHICLE 2.1. Heritage Page 4 2.2. Description Page 4 2 SARGE – Payload User Guide – Rev. 3 2.3. Mission Profile Page 6 2.4. Launch Site(s) Page 7 2.5. Launch Windows Page 7 2.6. Reusability & Frequency Page 8 3. EXOS FACILITIES 3.1. Headquarters Page 8 3.2. R&D Center Page 8 4. PAYLOAD PROVIDER INFORMATION 4.1. Payload Mass & Physical Size Page 8 4.2. Payload Environment Page 9 4.3. Standard Integration Services Page 10 4.4. Non-Standard Integration Services (Optional) Page 10 5. PAYLOAD INTEGRATION 5.1. Procedure for Approval Page 11 5.2. FAA /AST Payload Approval Page 11 5.3. Combined Systems Test Page 11 5.4. Physical Integration Page 11 5.5. Launch Operations Page 11 6. ITAR 6.1. Introduction Page 12 6.2. ITAR Integration & Launch Protocol, Telemetry Data Page 12 7. REVISION HISTORY Page 13 3 SARGE – Payload User Guide – Rev. 3 1. INTRODUCTION 1.1. EXOS Aerospace Systems & Technologies, Inc. (hereinafter EXOS or (E.A.S.T. for legal purposes)) is the successor company to Armadillo Aerospace LLC. (Hereinafter AA (the EXOS team)). EXOS acquired AA’s mission critical physical assets in early 2015 to take this technology commercial with the development of the SARGE platform. AA was a leading developer of reusable rocket powered vehicles and continuing the tradition EXOS is immediately focused on suborbital research rockets, with the vision of launching microsatellites and, eventually progressing to autonomous spaceflight.
    [Show full text]
  • JSC LOX/Methane Regen Engine Development Project Plan
    Combustion Instability in the Project Morpheus Liquid Oxygen/Liquid Methane Main Engine John. C. Melcher, Ph.D., Robert L. Morehead, Chris Radke, Eric A. Hurlbert NASA Johnson Space Center, Houston, TX AIAA Houston 2013 Annual Technical Symposium (ATS) May 17, 2013 Acknowledgements • John Olansen/Morpheus Project Manager • John Applewhite, John Brewer, Michael Baine, Jennifer Devolites (JSC) • Andy Guymon, Gary Taylor, Craig Chandler (SSC) • Jim Hulka, Gregg Jones, Jeremy Kenny, Chris Protz (MSFC) • Jeffrey Muss (Sierra Engineering) • Ben Stiegemeier (GRC) • Dave Vaughn (JPL) 2 Agenda • Executive summary • Project Morpheus Propulsion Overview • Morpheus Main Engine Overview • Combustion Instability background • Overview of Instability signatures and spectral analysis • Overview of Instability Working Theory • Discussion on vehicle applicability, redline JSC HD4-LT in test at SSC SSC Stennis Stand E-3 3 Executive Summary • The Project Morpheus Liquid Oxygen (LOX)/Liquid Methane HD4-LT and HD5 demonstrated acoustic-coupled combustion instabilities during testing at Stennis Space Center (SSC). • The instabilities have two causes and signatures – Overchilled CH4 with high CH4 injection velocity causes a high-amplitude, 1T, 1R, 1T1R (and higher order R harmonics). This instability usually manifests during low-throttle startup conditions and can propagate through mainstage throttle-up. It has never been shown to start after mainstage throtte-up. – Warm LOX causes transient, self-limiting instabilities that appear as 1T-1L or 1R (with harmonics).
    [Show full text]
  • Design & Analysis of a 500 Lbf Liquid Oxygen and Liquid Methane Rocket
    University of Texas at El Paso DigitalCommons@UTEP Open Access Theses & Dissertations 2017-01-01 Design & Analysis of a 500 lbf Liquid Oxygen and Liquid Methane Rocket Engine Daniel Eduardo Vargas University of Texas at El Paso, [email protected] Follow this and additional works at: https://digitalcommons.utep.edu/open_etd Part of the Mechanical Engineering Commons Recommended Citation Vargas, Daniel Eduardo, "Design & Analysis of a 500 lbf Liquid Oxygen and Liquid Methane Rocket Engine" (2017). Open Access Theses & Dissertations. 571. https://digitalcommons.utep.edu/open_etd/571 This is brought to you for free and open access by DigitalCommons@UTEP. It has been accepted for inclusion in Open Access Theses & Dissertations by an authorized administrator of DigitalCommons@UTEP. For more information, please contact [email protected]. DESIGN & ANALYSIS OF A 500 LBF LIQUID OXYGEN AND LIQUID METHANE ROCKET ENGINE DANIEL VARGAS FRANCO Master’s Program in Mechanical Engineering APPROVED: Ahsan Choudhuri, Ph.D., Chair Jack Chessa, Ph.D. Luis Rene Contreras, Ph.D. Charles H. Ambler, Ph.D. Dean of the Graduate School Copyright © by Daniel Vargas Franco 2017 DESIGN & ANALYSIS OF A 500 LBF LIQUID OXYGEN AND LIQUID METHANE ROCKET ENGINE by DANIEL VARGAS FRANCO, B.S.ME THESIS Presented to the Faculty of the Graduate School of The University of Texas at El Paso in Partial Fulfillment of the Requirements for the Degree of MASTER OF SCIENCE Department of Mechanical Engineering THE UNIVERSITY OF TEXAS AT EL PASO December 2017 Acknowledgements Foremost, I would like to express my gratitude to my advisor Dr. Ahsan Choudhuri for the useful comments, engagement, and continuous support of my Master’s study and for giving me the opportunity to conduct research at the UTEP Center for Space Exploration and Technology Research (cSETR).
    [Show full text]
  • Morpheus Lander Testing Campaign
    Morpheus Lander Testing Campaign Jeremy J. Hart Jennifer D. Mitchell NASA Johnson Space Center NASA Johnson Space Center 2101 NASA Parkway / EG6 2101 NASA Parkway / EA34 Houston TX, 77062 Houston TX, 77062 281-483-0001 281-483-8300 [email protected] [email protected] Abstract— NASA’s Morpheus Project has developed and impulse during space flight of up to 321 seconds; it is clean- tested a prototype planetary lander capable of vertical takeoff burning, non-toxic, and cryogenic, but space-storable. and landing designed to serve as a testbed for advanced Additionally, for future space missions the methane could spacecraft technologies. The Morpheus vehicle has successfully be produced in situ on Mars, and the oxygen is compatible performed a set of integrated vehicle test flights including hot- on-board with life support systems or power generation. fire and tether tests, ultimately culminating in an un-tethered “free-flight.” This development and testing campaign was These attributes make LOX/methane an attractive conducted on-site at the Johnson Space Center (JSC), less than propulsion technology for a lander of this scale. one year after project start. Designed, developed, manufactured and operated in-house by engineers at JSC, the The second technology is autonomous landing and hazard Morpheus Project represents an unprecedented departure avoidance. When landing autonomously on any planetary or from recent NASA programs and projects that traditionally other surface, the vehicle must be able to determine a safe require longer development lifecycles and testing at remote, landing site that is free of large boulders, rocks, craters, or dedicated testing facilities.
    [Show full text]
  • Spaceport News John F
    April 6, 2012 Vol. 52, No. 7 Spaceport News John F. Kennedy Space Center - America’s gateway to the universe Inside . SLF offers Morpheus realistic, rocky road 'Rocket University' By Cheryl Mansfield Project Morpheus, one of 20 inspires engineers Spaceport News small projects comprising the Advanced Exploration n area near Ken- Systems (AES) program in nedy Space Center's NASA's Human Explora- Shuttle Land- A tion and Operations Mission ing Facility (SLF) will Directorate. AES projects be turned into a field of pioneer new approaches for hazards as part of the next rapidly developing proto- phase of tests for the Project Morpheus lander. This type systems, demonstrating next step, which integrates key capabilities and validat- Page 2 technologies, hopefully will ing operational concepts for future human missions Trajectory Team someday be used to build beyond Earth orbit. keeps eye on target future spacecraft destined for asteroids, Mars or the Although the first test moon. at Kennedy has not been The lander has been un- scheduled, it could take dergoing testing at NASA's place as early as June, with Johnson Space Center in the series scheduled to wrap up by Sept. 30. The testing Houston for almost a year in CLICK ON PHOTO NASA/JSC preparation for its first free The Project Morpheus lander fires its liquid oxygen- and methane-fueled engine schedule is dynamic and flight. During that flight test- for a tethered test on May 4, 2011, at NASA's Johnson Space Center. With the changes as the vehicle and ing, it will rise almost 100 vehicle suspended from a crane, the tethered tests allowed engineers to test their weather dictate.
    [Show full text]
  • 2013 Spaceport News Summary
    2013 Spaceport News Summary The 2013 Spaceport News used the above banner for the year. Introduction The first issue of the Spaceport News was December 13, 1962. The 1963, 1964 and 1965 Spaceport News were issued weekly. The Spaceport News was issued every two weeks, starting July 7, 1966, until the last issue on February 24, 2014. Spaceport Magazine, a monthly issue, superseded the Spaceport News in April 2014, until the final issue, Jan./Feb. 2020. The two 1962 Spaceport News issues and the issues from 1996 until the final Spaceport Magazine issue, are available for viewing at this website. The Spaceport News issues from 1963 through 1995 are currently not available online. In this Summary, black font is original Spaceport News text, blue font is something I added or someone else/some other source provided, and purple font is a hot link. All links were working at the time I completed this Spaceport News Summary. The Spaceport News writer is acknowledged, if noted in the Spaceport News article. From The January 11, 2013, Spaceport News On page 2, “Kennedy's future bright with full plate for 2013”. Part of the feature, by Bob Cabana, states: “During the past year, Kennedy Space Center made great strides in transitioning from a historically government-only launch facility to an affordable, sustainable, multiuser spaceport for both government and commercial customers… We have a great future ahead, including a full plate for 2013… Coming up later this month is the launch of a TDRS satellite scheduled to lift off from Cape Canaveral Air Force Station… Page 1 We also are moving ahead with plans for NASA's Commercial Crew Program.
    [Show full text]