Rendezvous in Cis-Lunar Space Near Rectilinear Halo Orbit: Dynamics and Control Issues
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
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. -
The Surface Operations Framework – Transitioning from Early Analogue Experiments to Future Lunar Missions
THE SURFACE OPERATIONS FRAMEWORK – TRANSITIONING FROM EARLY ANALOGUE EXPERIMENTS TO FUTURE LUNAR MISSIONS Sebastian Martin(1), Toril Bye Rinnan(2), Mehran Sarkarati(3), Kim Nergaard(4) (1) ESA/ESOC, Robert-Bosch-Straße 5, 64293 Darmstadt, Germany, Email: [email protected] (2) Solenix Deutschland GmbH, Spreestraße 3, 64295 Darmstadt, Germany, Email: [email protected] (3) ESA/ESOC, Robert-Bosch-Straße 5, 64293 Darmstadt, Germany, Email: [email protected] (4) ESA/ESOC, Robert-Bosch-Straße 5, 64293 Darmstadt, Germany, Email: [email protected] ABSTRACT to assess the financial and technical feasibility of new mission concepts, technologies and studies before This paper provides an overview of a family of possibly advancing them to the next phases of activities performed within the European Space implementation of a mission. Operations Centre (ESOC) to prepare for future robotic As the result of one such concurrent design study in missions on the lunar surface and beyond. 2009, the METERON concept was created. METERON – the Multi-purpose End-To-End Robotics Operations Over the course of nearly a decade, ESOC has been Network – was initiated to prepare for future human and gradually building up expertise for future surface robotic exploration scenarios. These future scenarios operations activities. foresee robotic assets controlled on the surface of Moon This paper describes or Mars, with humans operating those assets from an - the activities and corresponding systems prepared orbiting vehicle or by Earth ground control. The benefit from the ground up before concrete missions were of near real-time remote asset operations is to reduce defined, human risks and cost by not having to land humans and - how we are now covering a range of activities return them from the surface, while still being able to where we have requirements from missions in the control robotic assets with short transmission delays definition phases while continuing to build on from an orbiter. -
ESA Strategy for Science at the Moon
ESA UNCLASSIFIED - Releasable to the Public ESA Strategy for Science at the Moon ESA UNCLASSIFIED - Releasable to the Public EXECUTIVE SUMMARY A new era of space exploration is beginning, with multiple international and private sector actors engaged and with the Moon as its cornerstone. This renaissance in lunar exploration will offer new opportunities for science across a multitude of disciplines from planetary geology to astronomy and astrobiology whilst preparing the knowledge humanity will need to explore further into the Solar System. Recent missions and new analyses of samples retrieved during Apollo have transformed our understanding of the Moon and the science that can be performed there. We now understand the scientific importance of further exploration of the Moon to understand the origins and evolution of Earth and the cosmic context of life’s emergence on Earth and our future in space. ESA’s priorities for scientific activities at the Moon in the next ten years are: • Analysis of new and diverse samples from the Moon. • Detection and characterisation of polar water ice and other lunar volatiles. • Deployment of geophysical instruments and the build up a global geophysical network. • Identification and characterisation of potential resources for future exploration. • Deployment long wavelength radio astronomy receivers on the lunar far side. • Characterisation of the dynamic dust, charge and plasma environment. • Characterisation of biological sensitivity to the lunar environment. ESA UNCLASSIFIED - Releasable to the Public -
Electric Propulsion System Scaling for Asteroid Capture-And-Return Missions
Electric propulsion system scaling for asteroid capture-and-return missions Justin M. Little⇤ and Edgar Y. Choueiri† Electric Propulsion and Plasma Dynamics Laboratory, Princeton University, Princeton, NJ, 08544 The requirements for an electric propulsion system needed to maximize the return mass of asteroid capture-and-return (ACR) missions are investigated in detail. An analytical model is presented for the mission time and mass balance of an ACR mission based on the propellant requirements of each mission phase. Edelbaum’s approximation is used for the Earth-escape phase. The asteroid rendezvous and return phases of the mission are modeled as a low-thrust optimal control problem with a lunar assist. The numerical solution to this problem is used to derive scaling laws for the propellant requirements based on the maneuver time, asteroid orbit, and propulsion system parameters. Constraining the rendezvous and return phases by the synodic period of the target asteroid, a semi- empirical equation is obtained for the optimum specific impulse and power supply. It was found analytically that the optimum power supply is one such that the mass of the propulsion system and power supply are approximately equal to the total mass of propellant used during the entire mission. Finally, it is shown that ACR missions, in general, are optimized using propulsion systems capable of processing 100 kW – 1 MW of power with specific impulses in the range 5,000 – 10,000 s, and have the potential to return asteroids on the order of 103 104 tons. − Nomenclature -
Aas 11-509 Artemis Lunar Orbit Insertion and Science Orbit Design Through 2013
AAS 11-509 ARTEMIS LUNAR ORBIT INSERTION AND SCIENCE ORBIT DESIGN THROUGH 2013 Stephen B. Broschart,∗ Theodore H. Sweetser,y Vassilis Angelopoulos,z David C. Folta,x and Mark A. Woodard{ As of late-July 2011, the ARTEMIS mission is transferring two spacecraft from Lissajous orbits around Earth-Moon Lagrange Point #1 into highly-eccentric lunar science orbits. This paper presents the trajectory design for the transfer from Lissajous orbit to lunar orbit in- sertion, the period reduction maneuvers, and the science orbits through 2013. The design accommodates large perturbations from Earth’s gravity and restrictive spacecraft capabili- ties to enable opportunities for a range of heliophysics and planetary science measurements. The process used to design the highly-eccentric ARTEMIS science orbits is outlined. The approach may inform the design of future eccentric orbiter missions at planetary moons. INTRODUCTION The Acceleration, Reconnection, Turbulence and Electrodynamics of the Moons Interaction with the Sun (ARTEMIS) mission is currently operating two spacecraft in lunar orbit under funding from the Heliophysics and Planetary Science Divisions with NASA’s Science Missions Directorate. ARTEMIS is an extension to the successful Time History of Events and Macroscale Interactions during Substorms (THEMIS) mission [1] that has relocated two of the THEMIS spacecraft from Earth orbit to the Moon [2, 3, 4]. ARTEMIS plans to conduct a variety of scientific studies at the Moon using the on-board particle and fields instrument package [5, 6]. The final portion of the ARTEMIS transfers involves moving the two ARTEMIS spacecraft, known as P1 and P2, from Lissajous orbits around the Earth-Moon Lagrange Point #1 (EML1) to long-lived, eccentric lunar science orbits with periods of roughly 28 hr. -
Dynamical Analysis of Rendezvous and Docking with Very Large Space Infrastructures in Non-Keplerian Orbits
DYNAMICAL ANALYSIS OF RENDEZVOUS AND DOCKING WITH VERY LARGE SPACE INFRASTRUCTURES IN NON-KEPLERIAN ORBITS Andrea Colagrossi ∗, Michele` Lavagna y, Simone Flavio Rafano Carna` z Politecnico di Milano Department of Aerospace Science and Technology Via La Masa 34 – 20156 Milan (MI) – Italy ABSTRACT the whole mission scenario is the so called Evolvable Deep Space Habitat: a modular space station in lunar vicinity. A space station in the vicinity of the Moon can be exploited At the current level of study, the optimum location for as a gateway for future human and robotic exploration of the space infrastructure of this kind has not yet been determined, Solar System. The natural location for a space system of this but a favorable solution can be about one of the Earth-Moon kind is about one of the Earth-Moon libration points. libration points, such as in a EML2 (Earth-Moon Lagrangian The study addresses the dynamics during rendezvous and Point no 2) Halo orbit. Moreover, the final configuration of docking operations with a very large space infrastructure in a the entire system is still to be defined, but it is already clear EML2 Halo orbit. The model takes into account the coupling that in order to assemble the structure several rendezvous and effects between the orbital and the attitude motion in a Circular docking activities will be carried out, many of which to be Restricted Three-Body Problem environment. The flexibility completely automated. of the system is included, and the interaction between the Unfortunately, the current knowledge about rendezvous in modes of the structure and those related with the orbital motion cis-lunar orbits is minimal and it is usually limited to point- is investigated. -
What Is the Interplanetary Superhighway?
What is the InterPlanetary Suppgyerhighway? Kathleen Howell Purdue University Lo and Ross Trajectory Key Space Technology Mission-Enabling Technology Not All Technology is hardware! The InterPlanetary Superhighway (IPS) • LELow Energy ObitfSOrbits for Space Mi Miissions • InterPlanetary Superhighway—“a vast network of winding tunnels in space” that connects the Sun , the planets, their moons, AND many other destinations • Systematic mapping properly known as InterPlanetary Transport Network Simó, Gómez, Masdemont / Lo, Howell, Barden / Howell, Folta / Lo, Ross / Koon, Lo, Marsden, Ross / Marchand, Howell, Lo / Scheeres, Villac/ ……. Originates with Poincaré (1892) Applications to wide range of fields Different View of Problems in N-Bodies • Much more than Kepler and Newton imagined • Computationally challenging Poincaré (1854-1912) “Mathematics is the art of giving the same name to different things” Jules Henri Poincaré NBP Play 3BP Wang 2BP New Era in Celestial Mechanics Pioneering Work: Numerical Exploration by Hand (Breakwell, Farquhar and Dunham) Current Libration Point Missions Goddard Space Flight Center • z WIND SOHO ACE MAPGENESIS NGST Courtesy of D. Folta, GSFC Multi-Body Problem Orbit propagated for 4 conic periods: • Change our perspective 4*19 days = 75.7 days Earth Earth Sun To Sun Inertial View RotatingRotating View View Inertial View (Ro ta tes w ith two b odi es) Aeronautics and Astronautics Multi-Body Problem • Change our perspective • Effects of added gravity fields Earth Earth TSTo Sun Rotating View Inertial View Equilibrium -
Go, No-Go for Apollo Based on Orbital Life Time
https://ntrs.nasa.gov/search.jsp?R=19660014325 2020-03-24T02:45:56+00:00Z I L GO, NO-GO FOR APOLLO BASED ON ORBITAL LIFE TIME I hi 01 GPO PRICE $ Q N66(ACCESSION -2361 NUMBER1 4 ITHRU) Pf - CFSTI PRICE(S) $ > /7 (CODE) IPAGES) 'I 2 < -55494 (CATEGORY) f' (NASA CR OR rwx OR AD NUMBER) Hard copy (HC) /# d-a I Microfiche (M F) I By ff653 Julv65 F. 0. VONBUN NOVEMBER 1965 t GODDARD SPACE FLIGHT CENTER GREENBELT, MARYLAND ABSTRACT A simple expression for the go, no-go criterion is derived in analytical form. This provides a better understanding of the prob- lems involved which is lacking when large computer programs are used. A comparison between "slide rule" results and computer re- sults is indicated on Figure 2. An example is given using a 185 km near circular parking or- bit. It is shown that a 3a speed error of 6 m/s and a 3c~flight path angle error of 4.5 mrad result in a 3c~perigee error of 30 km which is tolerable when a 5 day orbital life time of the Apollo (SIVB + Service + Command Module) is required. iii CONTENTS Page INTRODUCTION ...................................... 1 I. VARLATIONAL EQUATION FOR THE PERIGEE HEIGHT h,. 1 11. THE ERROR IN THE ORBITAL PERIGEE HEIGHT ah,. 5 III. CRITERION FOR GO, NO-GO IN SIMPLE FORM . 5 REFERENCES ....................................... 10 LIST OF ILLUSTRATIONS Figure Page 1 Orbital Insertion Geometry . 2 2 Perigee Error for Apollo Parking Orbits (e 0, h, = 185 km) . 6 3 Height of the Apollo Parking Orbit After Insertion . -
Global Exploration Roadmap
The Global Exploration Roadmap January 2018 What is New in The Global Exploration Roadmap? This new edition of the Global Exploration robotic space exploration. Refinements in important role in sustainable human space Roadmap reaffirms the interest of 14 space this edition include: exploration. Initially, it supports human and agencies to expand human presence into the robotic lunar exploration in a manner which Solar System, with the surface of Mars as • A summary of the benefits stemming from creates opportunities for multiple sectors to a common driving goal. It reflects a coordi- space exploration. Numerous benefits will advance key goals. nated international effort to prepare for space come from this exciting endeavour. It is • The recognition of the growing private exploration missions beginning with the Inter- important that mission objectives reflect this sector interest in space exploration. national Space Station (ISS) and continuing priority when planning exploration missions. Interest from the private sector is already to the lunar vicinity, the lunar surface, then • The important role of science and knowl- transforming the future of low Earth orbit, on to Mars. The expanded group of agencies edge gain. Open interaction with the creating new opportunities as space agen- demonstrates the growing interest in space international science community helped cies look to expand human presence into exploration and the importance of coopera- identify specific scientific opportunities the Solar System. Growing capability and tion to realise individual and common goals created by the presence of humans and interest from the private sector indicate and objectives. their infrastructure as they explore the Solar a future for collaboration not only among System. -
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.