Basic Principles of Satellite
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Analysis of Planetary and Solar-Induced Perturbations on Trans-Martian Trajectory of Mars Missions Before and After Mars Orbit Insertion
Analysis of planetary and solar-induced perturbations on trans-Martian trajectory of Mars missions before and after Mars orbit insertion V U J Nwankwo1 and S K Chakrabarti1,2* 1S N Bose National Centre for Basic Sciences, Kolkata 700 098, West Bengal, India 2Indian Center for Space Physics, Kolkata 700 084, West Bengal, India Abstract: Interplanetary missions are susceptible to gravitational and nongravitational perturbing forces at every tra- jectory phase, assuming, of course, that the man made rockets and thrusters work as expected. These forces are mainly due to planetary and solar-forcing-induced perturbations during geocentric, heliocentric and Martian trajectories, and before orbit insertion. In this study, we review and/or analyze Mars orbiters mission associated perturbing forces and their possible impacts before Mars Orbit Insertion viz Earth’s oblateness, Third body (solar and lunar), solar radiation pressure, solar energetic radiation environment and atmospheric drag forces. We also model the significance of atmospheric drag force on Mangalyaan Mars orbiter mission, as a function of appropriate space environmental parameters during its 28 days in Earth’s orbit (around and during perigee passage), 300 days of heliocentric and 100 days of Martian trajectory. We have found that for a total perigee height boost of about 250 km, the cumulative orbit decay can be approximately 720 m. The approximate altitude variation could be up to 158 m with respect to the sun during 300 days of interplanetary journey toward Mars. After Mars orbit insertion, the total decay experienced by the spacecraft could be up to 701 m with decay rate of up to 9 m/day during 100 days of Martian trajectory, based on Mars–Earth atmosphere density ratio. -
Theoretical and Experimental Investigation of Hall Thruster Miniaturization by Noah Zachary Warner
Theoretical and Experimental Investigation of Hall Thruster Miniaturization by Noah Zachary Warner S.B., Aeronautics and Astronautics, Massachusetts Institute of Technology, 2001 S.M., Aeronautics and Astronautics, Massachusetts Institute of Technology, 2003 SUBMITTED TO THE DEPARTMENT OF AERONAUTICS AND ASTRONAUTICS IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE OF DOCTOR OF PHILOSOPHY AT THE MASSACHUSETTS INSTITUTE OF TECHNOLOGY JUNE 2007 © 2007 Massachusetts Institute of Technology. All rights reserved. Signature of Author . Department of Aeronautics and Astronautics May 25, 2007 Certified by . Manuel Martínez-Sánchez Professor of Aeronautics and Astronautics Thesis Supervisor Certified by . Jack Kerrebrock Professor Emeritus of Aeronautics and Astronautics Certified by . Oleg Batishchev Principal Research Scientist in Aeronautics and Astronautics Certified by . Vladimir Hruby President, Busek Company, Inc. Accepted by . Jaime Peraire Professor of Aeronautics and Astronautics Chair, Committee on Graduate Students 2 Theoretical and Experimental Investigation of Hall Thruster Miniaturization by Noah Zachary Warner Submitted to the Department of Aeronautics and Astronautics on May 25, 2007 in partial fulfillment of the requirements for the degree of Doctor of Philosophy in Aeronautics and Astronautics in the field of Space Propulsion ABSTRACT Interest in small-scale space propulsion continues to grow with the increasing number of small satellite missions, particularly in the area of formation flight. Miniaturized Hall thrusters have been identified as a candidate for lightweight, high specific impulse propul- sion systems that can extend mission lifetime and payload capability. A set of scaling laws was developed that allows the dimensions and operating parameters of a miniaturized Hall thruster to be determined from an existing, technologically mature baseline design. -
Earth to Mars Areostationary Mission Optimization Analysis
Earth to Mars areostationary mission optimization analysis M. M. Sánchez-García, G. Barderas and P. Romero Instituto de Matemática Interdisciplinar. U. D. Astronomía y Geodesia, Facultad de Ciencias Matemáticas, Universidad Complutense de Madrid, Madrid, Spain ([email protected], [email protected], [email protected]) Abstract Mars has become one of the priorities in the planetary exploration programs. The analysis of space mission costs has become a key factor in mission planning. The determination of optimal trajectories aiming to lower costs in terms of impulses allows for more massive payloads to be transported at a minimum energy cost. Areostationary satellites are considered the most efficient and robust candidates to satisfy the control needs of the missions to Mars. Mars Areostationary Relay Satellites providing continuous coverage of a specific region of Mars are being considered for a near future. In this work, we analyze the optimization of an areostationary mission. We first determine the launch and arrival dates for an optimal minimum energy Earth-Mars transfer trajectory. Then, the minimum thrust maneuvers to capture the spacecraft from the hyperbolic arrival trajectory to Mars and place it in the areostationary orbit are analyzed. XIV.0 Reunión Científica 13-15 julio 2020 Context of the research: Previous studies The number of missions to Mars has increased over the last years, particularly robotic missions which need to be tele- commanded from the Earth. The need to control the different missions in Mars in almost real time with a relay system that provides continuous coverage of a specific region has been proposed by several authors such as Edwards et al. -
The Annual Compendium of Commercial Space Transportation: 2017
Federal Aviation Administration The Annual Compendium of Commercial Space Transportation: 2017 January 2017 Annual Compendium of Commercial Space Transportation: 2017 i Contents About the FAA Office of Commercial Space Transportation The Federal Aviation Administration’s Office of Commercial Space Transportation (FAA AST) licenses and regulates U.S. commercial space launch and reentry activity, as well as the operation of non-federal launch and reentry sites, as authorized by Executive Order 12465 and Title 51 United States Code, Subtitle V, Chapter 509 (formerly the Commercial Space Launch Act). FAA AST’s mission is to ensure public health and safety and the safety of property while protecting the national security and foreign policy interests of the United States during commercial launch and reentry operations. In addition, FAA AST is directed to encourage, facilitate, and promote commercial space launches and reentries. Additional information concerning commercial space transportation can be found on FAA AST’s website: http://www.faa.gov/go/ast Cover art: Phil Smith, The Tauri Group (2017) Publication produced for FAA AST by The Tauri Group under contract. NOTICE Use of trade names or names of manufacturers in this document does not constitute an official endorsement of such products or manufacturers, either expressed or implied, by the Federal Aviation Administration. ii Annual Compendium of Commercial Space Transportation: 2017 GENERAL CONTENTS Executive Summary 1 Introduction 5 Launch Vehicles 9 Launch and Reentry Sites 21 Payloads 35 2016 Launch Events 39 2017 Annual Commercial Space Transportation Forecast 45 Space Transportation Law and Policy 83 Appendices 89 Orbital Launch Vehicle Fact Sheets 100 iii Contents DETAILED CONTENTS EXECUTIVE SUMMARY . -
ON FORMING the MOON in GEOCENTRIC ORBIT Herbert, F., Et Al
ON FORMING ME MOON IN GEOCENTRIC ORBIT; DYNAMICAL EVOLUTION OF A CIRCUMTERRESTRIAL PLANETESIMAL SWARM; Floyd Herbert, University of Arizona, Tucson, and D.R. Davis and S.J. Weidenschilling, Planetary Science Institute, Tucson, AZ. The wclassicalv theories of lunar origin all have major difficulties that have prevented any of them from beinq generally accepted: the capture hypo- thesis is quite improbable, while the fission hypothesis suffers a larqe anqular momentum problem. New theories have, of course, sprouted to replace these -- tidal disruption/capture, accretion in geocentric orbit, and the qiant impact hypothesis. At a recent conference on the oriqin of the moon (October, 1984, Kona, HI), the qiant impact hypothesis, which holds that the moon formed as the result of a large (Mercury-to-Mars-sized) planetesimal impactinq the proto-Earth, emerqed as the current favored hypothesis, with co-formation in geocentric orbit a possible alternative. The latter model, which suqgests that the moon formed from planetesimals captured from helio- centric orbit and forminq a circumterrestrial disk, was criticized also as suffering an angular momentum deficit, based on our preliminary results (1). We present here additional results of studies of anqular momen-tum input to a circumterrestrial swarm by planetesimals arriving from heliocentric orbits. Such a target swarm could have formed initially by collisions among heliocentric planetesimals passing within Earth's sphere of influence. Such collisions have a siqnificant probability (tens of $1 of yieldinq capture into qeocentric orbit (2). We assume that the swarm is evolvinq due to collisions with the heliocentric planetesimal population as they pass close to the Earth. -
Successful Demonstration for Upper Stage Controlled Re-Entry Experiment by H-IIB Launch Vehicle
Mitsubishi Heavy Industries Technical Review Vol. 48 No. 4 (December 2011) 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 vehicles after orbital injections can be hazardous. A piece of debris can collide with artificial satellites or cause a casualty when it falls back to earth, which is an ongoing problem among countries that utilize outer space. This paper reports on a Japanese controlled re-entry disposal method that brings the upper stage of a launch vehicle down in a safe ocean area after the mission has been completed. The method was successfully demonstrated on the H-IIB launch vehicle during Flight No. 2, and provides a means of reducing the amount of space debris and the risk of ground casualty. |1. Introduction The H-IIB launch vehicle was jointly developed by the Japan Aerospace Exploration Agency (JAXA) and Mitsubishi Heavy Industries, Ltd., to launch the Kounotori (‘Stork’) H-II Transfer Vehicle (HTV), which carries supply goods to the International Space Station (ISS). The H-IIB launch vehicle has the largest launch capability of the H-IIA launch vehicle family: it can inject a 16.5-ton HTV into a low earth orbit (ISS transfer orbit). Figure 1 shows an overview of the H-IIB launch vehicle. Figure 1 Overview of the H-IIB launch vehicle The changes introduced in the H-IIB launch vehicle are as follows: ・ Enhanced first stage relative to the H-IIA: tank diameter extension, cluster system for two main engines, and four solid rocket boosters (SRB-A) ・ Reinforced upper stage (second stage) relative to the H-IIA to launch the HTV ・ 5S-H fairing (newly developed to launch the HTV) H-IIB Test Flight No. -
'.';King Navigation
1980012912 -' JPL PUBLICATION 78-38 '.';king Navigation W. J. O'Neil, R. P. Rudd, D. L. Farless, C. E. Hildebrand, R. T. Mitchell, K. H. Rourke, et al. Jet Propulsion Laboratory E. A. Euler Martin Marietta Aerospace (N,%SA-C[_-l_,2517) VIklt_G ._AVIGA'IION (Jet t, u0-213_-_ : Pcopulsio[, L,_c.) 322 p _lC Alq/MF A01 _:d[,U CSCL Z2.t; hd0-_|4dj •_ [J_;c ]. a_ GJ/15 l,t7 5 'JJ ± November 15, 1979 _',r:.'> ;Y/l&_',,/I_cC7.'/',_/, : < X* ",t ,'" t National Aeronautics and Space Administration Jet Propulsion Laboratory California Institute of Technology Pasadena, California # 1980012912-002 JPL PUBLICATION 78-38 Viking Navigation W. J. O'Neil, R. P. Rudd, D. L. Farless, C. E. Hildebrand, R. T. Mitchell, K. H. Rourke, et al. Jet Propulsion Laboratory E. A. Euler Martin Marietta Aerospace November 15, 1979 National Aeronautics and Space Administration Jet Propulsion Laboratory : California Institute of Technology Pasadena, California 1980012912-003 The research descnbed bnth_s pubhcat_onwas camed out by the Jet Propulsion Laboratory, Cahforn_aInstitute of Technology, under NASA Contract No NAS7-100 i 1980012912-004 Abstract NASA soft-landed two Viking spacecraft on Mars in the summer t,f 1976. These were the free world's first landings on another planet. This report provides a final, comprehensive description of the navigation of the Viking spacecraft throughout their flight from Earth launch to Mars landing. The flight path design, actual int]lght control, and postflight reconstruction ale discussed in detail. The report Is comprised of an introductory chapter followed by five Olapters which essenually correspond to the organization of the Viking navigation operations, namely, Trajectory Descriptton, Interplanetary Orbit Determination, Satellite Orbit Determination, ._haneuver Analysis, and Lander Flight Path Analysis. -
Orbital Aggregation & Space Infrastructure Systems (OASIS)
Revolutionary Aerospace Systems Concepts Orbital Aggregation & Space Infrastructure Systems (OASIS) Preliminary Architecture and Operations Analysis FY2001 Final Report June 10, 2002 This page intentionally left blank. Foreword Just as the early American settlers pushed west beyond the original thirteen colonies, the world today is on the verge of expanding the realm of humanity beyond its terrestrial bounds. The next great frontier lies ahead in low-Earth orbit and beyond. Commercialization of space has recently been mostly limited to communications and remote sensing applications, but materials processing, manufacturing, tourism and servicing opportunities will undoubtedly increase during the first part of the new millennium. Discoveries hinting at the existence of water on Mars and Europa offer additional motivation for establishing a space-based infrastructure that supports extended human exploration of the solar system. If this space-based infrastructure were also utilized to stimulate and support space commercialization, permanent human occupation of low-Earth orbit and beyond could be achieved sooner and more cost effectively. The purpose of this study is to identify synergistic opportunities and concepts among human exploration initiatives and space commercialization activities while taking into account technology assumptions and mission viability in an Orbital Aggregation & Space Infrastructure Systems (OASIS) framework. OASIS is a set of concepts that provide a common infrastructure for enabling a large class of space missions. The concepts include communication, navigation and power systems, propellant modules, tank farms, habitats, and transfer systems using several propulsion technologies. OASIS features in-space aggregation of systems and resources in support of mission objectives. The concepts feature a high level of reusability and are supported by inexpensive launch of propellant and logistics payloads. -
Deep Space Network Ission Suppo
870-14, Rev. AF Deep Space Network ission Suppo Jet Propulsion Laboratory California institute of Technology JPL 0-0787,Rev. AF 870-14, Rev. AF October 1991 Deep Space Network ission Support Re uirements Reviewed by: L.M. McKinley TDA Mission Support Off ice Approved by: R.J. Amorose Manager, TDA Mission Support Jet Propulsion Laboratory California Institute of Technology JPL 0-0787, Rev. AF 870.14. Rev . AF CONTENTS INTRODUCTION............................................................ 1-1 A . PURPOSE AND SCOPE ................................................. 1-1 B . REVISION AND CONTROL .............................................. 1-1 C . ORGANIZATION OF DOCUMENT 870-14 ................................... 1-1 D . ABBREVIATIONS ..................................................... 1-1 ASTRO-D ................................................................. 2-1 BROADCASTING SATELLITE-3A AND -3B (BS-3A AND -3B) ....................... 3-1 CRAF/CASSINI (c/c)...................................................... 4-1 COSMIC BACKGROUND EXPLORER (COBE)....................................... 5-1 DYNAMICS EXPLORER-1 (DE-1).............................................. 6-1 EARTH RADIATION BUDGET SATELLITE (ERBS)................................. 7-1 ENGINEERING TEST SATELLITE-VI (ETS-VI).................................. 8-1 EUROPEAN TELECOMMUNICATIONS SATELLITE I1 (EUTELSAT 11) .................. 9-1 EXTREME ULTRAVIOLET EXPLORER (EWE)..................................... 10-1 FRENCH DIRECT TV BROADCAST SATELLITE (TDF-1 AND -2) .................... -
Orbital Mechanics Joe Spier, K6WAO – AMSAT Director for Education ARRL 100Th Centennial Educational Forum 1 History
Orbital Mechanics Joe Spier, K6WAO – AMSAT Director for Education ARRL 100th Centennial Educational Forum 1 History Astrology » Pseudoscience based on several systems of divination based on the premise that there is a relationship between astronomical phenomena and events in the human world. » Many cultures have attached importance to astronomical events, and the Indians, Chinese, and Mayans developed elaborate systems for predicting terrestrial events from celestial observations. » In the West, astrology most often consists of a system of horoscopes purporting to explain aspects of a person's personality and predict future events in their life based on the positions of the sun, moon, and other celestial objects at the time of their birth. » The majority of professional astrologers rely on such systems. 2 History Astronomy » Astronomy is a natural science which is the study of celestial objects (such as stars, galaxies, planets, moons, and nebulae), the physics, chemistry, and evolution of such objects, and phenomena that originate outside the atmosphere of Earth, including supernovae explosions, gamma ray bursts, and cosmic microwave background radiation. » Astronomy is one of the oldest sciences. » Prehistoric cultures have left astronomical artifacts such as the Egyptian monuments and Nubian monuments, and early civilizations such as the Babylonians, Greeks, Chinese, Indians, Iranians and Maya performed methodical observations of the night sky. » The invention of the telescope was required before astronomy was able to develop into a modern science. » Historically, astronomy has included disciplines as diverse as astrometry, celestial navigation, observational astronomy and the making of calendars, but professional astronomy is nowadays often considered to be synonymous with astrophysics. -
Experimental Analysis of Low Earth Orbit Satellites Due to Atmospheric Perturbations
IAETSD JOURNAL FOR ADVANCED RESEARCH IN APPLIED SCIENCES ISSN NO: 2394-8442 Experimental Analysis of Low Earth Orbit Satellites due to Atmospheric Perturbations Aman Saluja#1, Manish Bansal#2, M Raja#3, Mohd Maaz#4 #Aerospace Department, University of Petroleum and Energy Studies, Dehradun [email protected], [email protected], [email protected], [email protected] Abstract— A satellite is expected to move in the orbit until its life is over. This would have been true if the earth was a true sphere and gravity was the only force acting on the satellite. However, a satellite is deviated from its normal path due to several forces. This deviation is termed as orbital perturbation. The perturbation can be generated due to many known and unknown sources such as Sun and Moon, Solar pressure, etc. This paper discusses the study of perturbation of a Low Earth satellite orbit due to the presence of aerodynamic drag. Numerical method (Runge - Kutta fourth order) is used to solve the Cowell’s equation of perturbation, which consists of ordinary differential equation. Keywords— Low Earth Orbit (LEO), Cowell’s method, atmospheric perturbation, orbital elements, numerical method (RK4) I. INTRODUCTION Satellite is a space vehicle which is used for different purposes like communication, weather forecasting, surveillance, etc. so, for each purpose the design, working and the altitude the satellite to be placed, is different for different types of satellites which depends on the purpose of the satellite. A perturbation is actually a deviation from real or expected motion. It can be small or large depending upon the type of perturbation and the type of orbit the satellite is in. -
Order-Of-Magnitude Estimation Earth Orbiter (Level 1)
Order-of-Magnitude Estimation Earth Orbiter (Level 1) The Question A geostationary satellite orbits the Earth once each day. About how fast is it traveling in miles per hour? Background Geostationary satellites are designed to remain above the same point on the Earth’s surface, orbiting the Earth exactly once per day. It is possible to expand this question to an expert- level question by determining the exact distance to a satellite with an orbital period of 24 hours. Or, as an alternative starting point, most people can be guided to estimate that a satellite orbits at “a few times the Earth’s radius”. Guiding Questions Here are some things you may need to consider: Always have an initial guess at the answer without any OoM estimation! • Newton’s Law of Gravity is F = GMm/r2 for a body of mass (M) exerting a gravi- • tational force on a second mass m at a distance r. G is the Gravitational Constant. Newton’s Second Law in angular form is F = ma = mrω2 = mr(4π2)/T 2 for a mass • m moving in a circle of radius r that takes a period T to orbit once. How can we estimate the distance to geostationary orbit? • How can we estimate the circumference of geostationary orbit? • How are speed and distance related to velocity? • The Solution To determine the distance r to geostationary orbit (from the center of the Earth), equate Newton’s Second Law and Newton’s Law of Gravity 1 2 GMm mr(4π ) 3 GM F = = r = T 2 (1) r2 T 2 ⇒ r 4π2 remembering that the time for one orbit of a geostationary satellite is 24 hours or 24 60 60 s, which is about (100/4) 36 100 105 and that π2 10: × × × × ∼ ∼ −11 24 13 3 (6.7 10 )(6 10 ) 3 (40 10 ) r = × × (105)2 × 1010 r 40 ∼ r 40 (2) 3 3 3 √1023 3 1021(100) √100√1021 4.5 107 m ∼ ∼ p ∼ ∼ × Thus we have calculated that geocentric orbit is 45,000km or 25,000 miles.