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The Utilization of Halo Orbit§ in Advanced Lunar Operation§
NASA TECHNICAL NOTE NASA TN 0-6365 VI *o M *o d a THE UTILIZATION OF HALO ORBIT§ IN ADVANCED LUNAR OPERATION§ by Robert W. Fmqcbar Godddrd Spctce Flight Center P Greenbelt, Md. 20771 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON, D. C. JULY 1971 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No. NASA TN D-6365 5. Report Date Jul;v 1971. 6. Performing Organization Code 8. Performing Organization Report No, G-1025 10. Work Unit No. Goddard Space Flight Center 11. Contract or Grant No. Greenbelt, Maryland 20 771 13. Type of Report and Period Covered 2. Sponsoring Agency Name and Address Technical Note J National Aeronautics and Space Administration Washington, D. C. 20546 14. Sponsoring Agency Code 5. Supplementary Notes 6. Abstract Flight mechanics and control problems associated with the stationing of space- craft in halo orbits about the translunar libration point are discussed in some detail. Practical procedures for the implementation of the control techniques are described, and it is shown that these procedures can be carried out with very small AV costs. The possibility of using a relay satellite in.a halo orbit to obtain a continuous com- munications link between the earth and the far side of the moon is also discussed. Several advantages of this type of lunar far-side data link over more conventional relay-satellite systems are cited. It is shown that, with a halo relay satellite, it would be possible to continuously control an unmanned lunar roving vehicle on the moon's far side. Backside tracking of lunar orbiters could also be realized. -
Astrodynamics
Politecnico di Torino SEEDS SpacE Exploration and Development Systems Astrodynamics II Edition 2006 - 07 - Ver. 2.0.1 Author: Guido Colasurdo Dipartimento di Energetica Teacher: Giulio Avanzini Dipartimento di Ingegneria Aeronautica e Spaziale e-mail: [email protected] Contents 1 Two–Body Orbital Mechanics 1 1.1 BirthofAstrodynamics: Kepler’sLaws. ......... 1 1.2 Newton’sLawsofMotion ............................ ... 2 1.3 Newton’s Law of Universal Gravitation . ......... 3 1.4 The n–BodyProblem ................................. 4 1.5 Equation of Motion in the Two-Body Problem . ....... 5 1.6 PotentialEnergy ................................. ... 6 1.7 ConstantsoftheMotion . .. .. .. .. .. .. .. .. .... 7 1.8 TrajectoryEquation .............................. .... 8 1.9 ConicSections ................................... 8 1.10 Relating Energy and Semi-major Axis . ........ 9 2 Two-Dimensional Analysis of Motion 11 2.1 ReferenceFrames................................. 11 2.2 Velocity and acceleration components . ......... 12 2.3 First-Order Scalar Equations of Motion . ......... 12 2.4 PerifocalReferenceFrame . ...... 13 2.5 FlightPathAngle ................................. 14 2.6 EllipticalOrbits................................ ..... 15 2.6.1 Geometry of an Elliptical Orbit . ..... 15 2.6.2 Period of an Elliptical Orbit . ..... 16 2.7 Time–of–Flight on the Elliptical Orbit . .......... 16 2.8 Extensiontohyperbolaandparabola. ........ 18 2.9 Circular and Escape Velocity, Hyperbolic Excess Speed . .............. 18 2.10 CosmicVelocities -
Rendezvous Design in a Cislunar Near Rectilinear Halo Orbit Emmanuel Blazquez, Laurent Beauregard, Stéphanie Lizy-Destrez, Finn Ankersen, Francesco Capolupo
Rendezvous Design in a Cislunar Near Rectilinear Halo Orbit Emmanuel Blazquez, Laurent Beauregard, Stéphanie Lizy-Destrez, Finn Ankersen, Francesco Capolupo To cite this version: Emmanuel Blazquez, Laurent Beauregard, Stéphanie Lizy-Destrez, Finn Ankersen, Francesco Capolupo. Rendezvous Design in a Cislunar Near Rectilinear Halo Orbit. International Symposium on Space Flight Dynamics (ISSFD), Feb 2019, Melbourne, Australia. pp.1408-1413. hal-03200239 HAL Id: hal-03200239 https://hal.archives-ouvertes.fr/hal-03200239 Submitted on 16 Apr 2021 HAL is a multi-disciplinary open access L’archive ouverte pluridisciplinaire HAL, est archive for the deposit and dissemination of sci- destinée au dépôt et à la diffusion de documents entific research documents, whether they are pub- scientifiques de niveau recherche, publiés ou non, lished or not. The documents may come from émanant des établissements d’enseignement et de teaching and research institutions in France or recherche français ou étrangers, des laboratoires abroad, or from public or private research centers. publics ou privés. Open Archive Toulouse Archive Ouverte (OATAO) OATAO is an open access repository that collects the wor of some Toulouse researchers and ma es it freely available over the web where possible. This is an author's version published in: h ttps://oatao.univ-toulouse.fr/22865 To cite this version : Blazquez, Emmanuel and Beauregard, Laurent and Lizy-Destrez, Stéphanie and Ankersen, Finn and Capolupo, Francesco Rendezvous Design in a Cislunar Near Rectilinear Halo Orbit. -
Rideshare and the Orbital Maneuvering Vehicle: the Key to Low-Cost Lagrange-Point Missions
SSC15-II-5 Rideshare and the Orbital Maneuvering Vehicle: the Key to Low-cost Lagrange-point Missions Chris Pearson, Marissa Stender, Christopher Loghry, Joe Maly, Valentin Ivanitski Moog Integrated Systems 1113 Washington Avenue, Suite 300, Golden, CO, 80401; 303 216 9777, extension 204 [email protected] Mina Cappuccio, Darin Foreman, Ken Galal, David Mauro NASA Ames Research Center PO Box 1000, M/S 213-4, Moffett Field, CA 94035-1000; 650 604 1313 [email protected] Keats Wilkie, Paul Speth, Trevor Jackson, Will Scott NASA Langley Research Center 4 West Taylor Street, Mail Stop 230, Hampton, VA, 23681; 757 864 420 [email protected] ABSTRACT Rideshare is a well proven approach, in both LEO and GEO, enabling low-cost space access through splitting of launch charges between multiple passengers. Demand exists from users to operate payloads at Lagrange points, but a lack of regular rides results in a deficiency in rideshare opportunities. As a result, such mission architectures currently rely on a costly dedicated launch. NASA and Moog have jointly studied the technical feasibility, risk and cost of using an Orbital Maneuvering Vehicle (OMV) to offer Lagrange point rideshare opportunities. This OMV would be launched as a secondary passenger on a commercial rocket into Geostationary Transfer Orbit (GTO) and utilize the Moog ESPA secondary launch adapter. The OMV is effectively a free flying spacecraft comprising a full suite of avionics and a propulsion system capable of performing GTO to Lagrange point transfer via a weak stability boundary orbit. In addition to traditional OMV ’tug’ functionality, scenarios using the OMV to host payloads for operation at the Lagrange points have also been analyzed. -
Analysis of Interplanetary Transfers Between the Earth and Mars Halo Orbits
Analysis of Interplanetary Transfers between the Earth and Mars Halo orbits M. Nakamiya (1), H. Yamakawa (2), D. J. Scheeres (3) and M. Yoshikawa (4) (1) Japan Aerospace Exploration Agency, 3-1-1 Sagamihara, Kanagawa 229-8510, Japan. nakamiya,[email protected] (2) University of Colorado, Boulder, Colorado 80309, USA. [email protected] (3) KyotoUniversity, Gokasho, Uji, Kyoto 611-0011, Japan. [email protected] (4) Japan Aerospace Exploration Agency, 3-1-1 Sagamihara, Kanagawa 229-8510, Japan. [email protected] Spacecraft interplanetary transportation systems using Earth and Mars Halo orbits are analyzed. This application is motivated by future proposals to place “deep space ports” at the Earth and Mars Halo orbits as space hub for planetary Mission. First, the feasibility of interplanetary trajectories between Earth Halo orbit and Mars Halo orbit was investigated, and such trajectories were designed with reasonable DV and flight time. Here, we utilize unstable and stable manifolds associated with the Halo orbit to approach the vicinity of the planet’s surface, and assume impulsive maneuver for escape and capture trajectories from/to Halo Orbits. Next, applying to Earth-Mars transportation system using spaceports on Halo orbits, we evaluated the system with respect to the mass of round-trip transfer. As a result, the transfer between the low Earth orbit and the low Mars orbit via the Earth Halo orbit and the Mars Halo orbit could be saved the fuel cost compared with a direct transfer between the low Earth orbit and the low Mars orbit 1. INTRODUCTION These days there has been great interest in the libration points of the circular restricted 3-body problem (CR3BP), where the gravity of the primary and secondary bodies and centrifugal force are balanced. -
Station-Keeping and Momentum-Management on Halo Orbits Around L2: Linear-Quadratic Feedback and Model Predictive Control Approaches
MITSUBISHI ELECTRIC RESEARCH LABORATORIES http://www.merl.com Station-keeping and momentum-management on halo orbits around L2: Linear-quadratic feedback and model predictive control approaches Kalabi´c,U.; Weiss, A.; Di Cairano, S.; Kolmanovsky, I.V. TR2015-002 January 11, 2015 Abstract The control of station-keeping and momentum-management is considered while tracking a halo orbit centered at the second Earth-Moon Lagrangian point. Multiple schemes based on linear-quadratic feedback control and model predictive control (MPC) are considered and it is shown that the method based on periodic MPC performs best for position tracking. The scheme is then extended to incorporate attitude control requirements and numerical simulations are presented demonstrating that the scheme is able to achieve simultaneous tracking of a halo orbit and dumping of momentum while enforcing tight constraints on pointing error. AAS/AIAA Space Flight Mechanics Meeting This work may not be copied or reproduced in whole or in part for any commercial purpose. Permission to copy in whole or in part without payment of fee is granted for nonprofit educational and research purposes provided that all such whole or partial copies include the following: a notice that such copying is by permission of Mitsubishi Electric Research Laboratories, Inc.; an acknowledgment of the authors and individual contributions to the work; and all applicable portions of the copyright notice. Copying, reproduction, or republishing for any other purpose shall require a license with payment of -
Utilizing the Deep Space Gateway As a Platform for Deploying Cubesats Into Lunar Orbit
Deep Space Gateway Science Workshop 2018 (LPI Contrib. No. 2063) 3138.pdf UTILIZING THE DEEP SPACE GATEWAY AS A PLATFORM FOR DEPLOYING CUBESATS INTO LUNAR ORBIT. Fisher, Kenton R.1; NASA Johnson Space Center 2101 E NASA Pkwy, Houston TX 77508. [email protected] Introduction: The capability to deploy CubeSats from the Deep Space Gateway (DSG) may significantly increase access to the Moon for lower- cost science missions. CubeSats are beginning to demonstrate high science return for reduced cost. The DSG could utilize an existing ISS deployment method, assuming certain capabilities that are present at the ISS are also available at the DSG. Science and Technology Applications: There are many interesting potential applications for lunar CubeSat missions. A constellation of CubeSats Figure 1: Nanoracks CubeSat Deployer (NRCSD) being could provide a lunar GPS system for support of positioned by the Japanese Remote Manipulator System surface exploration missions. CubeSats could be used (JRMS) for deployment on ISS [4]. to provide communications relays for missions to the Present Lunar CubeSat Architecture: lunar far side. Potential science applications include While there are many opportunities for deploying using a CubeSat to produce mapping of the magnetic CubeSats into Earth orbits, the current options for fields of lunar swirls or to further map lunar surface deployment to lunar orbits are limited. Propulsive volatiles. requirements for trans-lunar injection (TLI) from International Space Station CubeSats: The Earth-orbit and lunar orbital insertion (LOI) International Space Station (ISS) has been a major significantly increase the cost, mass, and complexity platform for deploying CubeSats in recent years. -
Aas 19-266 Designing Low-Thrust Enabled Trajectories for A
AAS 19-266 DESIGNING LOW-THRUST ENABLED TRAJECTORIES FOR A HELIOPHYSICS SMALLSAT MISSION TO SUN-EARTH L5 Ian Elliott,∗ Christoper Sullivan Jr.,∗ Natasha Bosanac,y Jeffrey R. Stuart,z and Farah Alibayx A small satellite deployed to Sun-Earth L5 could serve as a low-cost platform to observe solar phenomena such as coronal mass ejections. However, the small satellite platform introduces significant challenges into the trajectory design pro- cess via limited thrusting capabilities, power and operational constraints, and fixed deployment conditions. To address these challenges, a strategy employing dynam- ical systems theory is used to design a low-thrust-enabled trajectory for a small satellite to reach the Sun-Earth L5 region. This procedure is demonstrated for a small satellite that launches as a secondary payload with a larger spacecraft des- tined for a Sun-Earth L2 halo orbit. INTRODUCTION Low-thrust spacecraft trajectory design has the potential to enable targeted science missions for small satellites to explore solar processes. In fact, the Sun-Earth (SE) L5 equilibrium point, located at the vertex of an equilateral triangle formed with the Sun and the Earth, is a candidate for locating a SmallSat for a heliophysics mission. At SE L5, a spacecraft would have a currently unavailable perspective of the three-dimensional structure of the coronal mass ejections off the Sun-Earth line.1 Additionally, due to the rotation of the Sun, early warning of solar storms is possible from SE L5.2 This equilibrium point has previously been visited by the Solar TErrestrial RElations Observatory B (STEREO-B) spacecraft which drifted through the SE L5 region, but did not maintain long- term bounded motion.3;4 With the increasing availability of rideshare opportunities and the recent demonstration of CubeSats operations in deep space during the Mars Cube One (MarCO) mission,5 small satellites may soon have the potential to be deployed to SE L5 to perform heliophysics-based science objectives. -
Technologies for Exploration
SP-1254 SP-1254 TTechnologiesechnologies forfor ExplorationExploration T echnologies forExploration AuroraAurora ProgrammeProgramme Proposal:Proposal: Annex Annex DD Contact: ESA Publications Division c/o ESTEC, PO Box 299, 2200 AG Noordwijk, The Netherlands Tel. (31) 71 565 3400 - Fax (31) 71 565 5433 SP-1254 November 2001 Technologies for Exploration Aurora Programme Proposal: Annex D This report was written by the staff of ESA’s Directorate of Technical and Operational Support. Published by: ESA Publications Division ESTEC, PO Box 299 2200 AG Noordwijk The Netherlands Editor/layout: Andrew Wilson Copyright: © 2001 European Space Agency ISBN: 92-9092-616-3 ISSN: 0379-6566 Printed in: The Netherlands Price: €30 / 70 DFl technologies for exploration Technologies for Exploration Contents 1 Introduction 3 2 Exploration Milestones 3 3 Explorations Missions 3 4Technology Development and Associated Cost 5 5 Conclusion 6 Annex 1: Automated Guidance, Navigation & Control A1.1 and Mission Analysis Annex 2: Micro-Avionics A2.1 Annex 3: Data Processing and Communication Technologies A3.1 Annex 4: Entry, Descent and Landing A4.1 Annex 5: Crew Aspects of Exploration A5.1 Annex 6: In Situ Resource Utilisation A6.1 Annex 7: Power A7.1 Annex 8: Propulsion A8.1 Annex 9: Robotics and Mechanisms A9.1 Annex 10: Structures, Materials and Thermal Control A10.1 1 Table 1. Exploration Milestones for the Definition of Technology Readiness Requirements. 2005-2010 In situ resource utilisation/life support (ground demonstration) Decision on development of alternative -
Commercial Spacecraft Mission Model Update
Commercial Space Transportation Advisory Committee (COMSTAC) Report of the COMSTAC Technology & Innovation Working Group Commercial Spacecraft Mission Model Update May 1998 Associate Administrator for Commercial Space Transportation Federal Aviation Administration U.S. Department of Transportation M5528/98ml Printed for DOT/FAA/AST by Rocketdyne Propulsion & Power, Boeing North American, Inc. Report of the COMSTAC Technology & Innovation Working Group COMMERCIAL SPACECRAFT MISSION MODEL UPDATE May 1998 Paul Fuller, Chairman Technology & Innovation Working Group Commercial Space Transportation Advisory Committee (COMSTAC) Associative Administrator for Commercial Space Transportation Federal Aviation Administration U.S. Department of Transportation TABLE OF CONTENTS COMMERCIAL MISSION MODEL UPDATE........................................................................ 1 1. Introduction................................................................................................................ 1 2. 1998 Mission Model Update Methodology.................................................................. 1 3. Conclusions ................................................................................................................ 2 4. Recommendations....................................................................................................... 3 5. References .................................................................................................................. 3 APPENDIX A – 1998 DISCUSSION AND RESULTS........................................................ -
Rendezvous in Cis-Lunar Space Near Rectilinear Halo Orbit: Dynamics and Control Issues
aerospace Article Rendezvous in Cis-Lunar Space near Rectilinear Halo Orbit: Dynamics and Control Issues Giordana Bucchioni † and Mario Innocenti *,† Department of Information Engineering, University of Pisa, 56126 Pisa, Italy; [email protected] * Correspondence: [email protected] † These authors contributed equally to this work. Abstract: The paper presents the development of a fully-safe, automatic rendezvous strategy between a passive vehicle and an active one orbiting around the Earth–Moon L2 Lagrangian point. This is one of the critical phases of future missions to permanently return to the Moon, which are of interest to the majority of space organizations. The first step in the study is the derivation of a suitable full 6-DOF relative motion model in the Local Vertical Local Horizontal reference frame, most suitable for the design of the guidance. The main dynamic model is approximated using both the elliptic and circular three-body motion, due to the contribution of Earth and Moon gravity. A rather detailed set of sensors and actuator dynamics was also implemented in order to ensure the reliability of the guidance algorithms. The selection of guidance and control is presented, and evaluated using a sample scenario as described by ESA’s HERACLES program. The safety, in particular the passive safety, concept is introduced and different techniques to guarantee it are discussed that exploit the ideas of stable and unstable manifolds to intrinsically guarantee some properties at each hold-point, in which the rendezvous trajectory is divided. Finally, the rendezvous dynamics are validated using available Ephemeris models in order to verify the validity of the results and their limitations for Citation: Bucchioni, G.; Innocenti, M. -
Council Drafts New Ordinance to Spread Pump Station Costs
• •*» Read the Herald Read the Herald For Local News For Local News Serving Summit tor $7 Ytcn ERALD Serving Summit for 67 Year a * mi Summit Record MMtW U tfca r»tt«rtie* N. J., THURSDAY, OCTOHR *» lt$S KfttaM* M I lfc. Act *f Mm^b I. lilt. $4 A YEAR 10 Uniteo lamwian GOP Cites City's Council Drafts New Ordinance To List Donors Progress Under To Spread Pump Station Costs Common Council Tuesday night continued hearing on Of 518 or More Republican Ride an ordinance authorizinK eQptruetion of a new $74,550 At a meeting Saturday evening A multipoint propara ef tht pumping station in the Canoe'Brook area with a portion at the home of Mr. and Mrs. John present city administration, out-i of the "costs-to be levienl against area landowners. How-- I_ c. Madden, vice chairmen for lining its accomplishments mi ev«r, on the heels of the resolution to continue the hearing', general solicitation, the 'Honor future plans, has received a Council introduced a now orcli- i;.,ll" plan to be adopted this year nance appropriating $75,000 .for IJY the United Campaign was ex- hearty stamp of approval from the construction of the station as jiLained to the division chairmen. the city Republican Committee. Canoe Brook Civic a general improvement. Under In announcing this plan, Roger M. The report was submitted in a this measure the assessment Spalding, Campaign .chairman, letter from Ogden D. CJensemer, would be city wide. ) Mated: / - president of the Common Coun- Group Votes 'No' Hearings on both ordinances - :For years many of our citi- cil, to Hugh A.