DOCSLIB.ORG

Project Lyra: Sending a Spacecraft to 1I/'Oumuamua (Former A/2017 U1

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
Project Lyra: Sending a Spacecraft to 1I/'Oumuamua (Former A/2017 U1 Project Lyra: Sending a Spacecraft to 1I/’Oumuamua (former A/2017 U1), the Interstellar Asteroid Andreas M. Hein 1, Nikolaos Perakis 1, T. Marshall Eubanks 1,2 , Adam Hibberd 1, Adam Crowl 1, Kieran Hayward 1, Robert G. Kennedy III 1, Richard Osborne 1 Contact email: [email protected] 1 Initiative for Interstellar Studies, Bone Mill, New Street, Charfield, GL12 8ES, United Kingdom 2 Asteroid Initiatives LLC Abstract The first definitely interstellar object 1I/’Oumuamua (previously A/2017 U1) observed in our solar system provides the opportunity to directly study material from other star systems. Can such objects be intercepted? The challenge of reaching the object within a reasonable timeframe is formidable due to its high heliocentric hyperbolic excess velocity of about 26 km/s; much faster than any vehicle yet launched. This paper presents a high-level analysis of potential near-term options for a mission to 1I/’Oumuamua and potential similar objects. Launching a spacecraft to 1I/’Oumuamua in a reasonable timeframe of 5-10 years requires a hyperbolic solar system excess velocity between 33 to 76 km/s for mission durations between 30 to 5 years. Different mission durations and their velocity requirements are explored with respect to the launch date, assuming direct impulsive transfer to the intercept trajectory. For missions using a powered Jupiter flyby combined with a solar Oberth maneuver using solid rocket boosters and Parker Solar Probe heatshield technology, a Falcon Heavy-class launcher would be able to launch a spacecraft of dozens of kilograms towards 1I/’Oumuamua, if launched in 2021. An additional Saturn flyby would allow for the launch of a New Horizons-class spacecraft. Further technology options are outlined, ranging from electric propulsion, and more advanced options such as laser electric propulsion, and solar and laser sails. To maximize science return decelerating the spacecraft at ’Oumuamua is highly desirable, due to the minimal science return from a hyper-velocity encounter. Electric and magnetic sails could be used for this purpose. It is concluded that although reaching the object is challenging, there seem to be feasible options based on current and near- term technology. 1. Introduction On October 19 th 2017, the University of Hawaii’s Pan-STARRS 1 telescope on Haleakala discovered a fast- moving object near the Earth, initially named A/2017 U1, but now designated as 1I/’Oumuamua [1]. It is likely that this object has its origin outside the solar system [2–9], with a velocity at infinity of 26.33 km/s, an eccentricity of 1.20, and an incoming radiant (direction of motion) near the solar apex in the constellation Lyra [10]. Due to the non-observation of a tail in the proximity of the Sun, the object seems to be an asteroid [11]. However, it has been hypothesized that either a cometary tail was present for a brief moment but was not observed [12], as 1I/’Oumuamua was discovered post perihelion, or that an organically rich surface, resulting in an insulating mantle prevented a cometary tail from forming [13]. Such a mantle could be the result of long-term cosmic ray exposure, although Jackson et al. argue against this possibility [14]. The comet hypothesis has been supported by the observation of non-gravitational acceleration, which can be explained by cometary outgassing [15]. However, the question is still far from resolved [16]. Spectroscopic results [12,13,17–21] indicate that the object is reddish, with a distribution similar to Trans-Neptunian objects [18,19,21]. The rapidly changing albedo has also lead to the assumption that the object is rotating and is highly elongated [19,22,23] with estimated dimensions of 230m x 35m x 35m [21]. The axis ratio of is larger than for any small solar system body [21]. Its orbital features have been analyzed by . ≥ 6.3.: 1 1 [10,24,25]. Hypotheses for its origin range from a star of the Local Association [4] to a more distant origin in the galactic thin disk, with the ejection dating back several billion years [7,20]. Estimates for the abundance of interstellar objects with a similar size are wide-ranging. Feng and Jones [4] estimate an abundance of interstellar objects larger than 100 m as . The steady state population of interstellar objects with a size of the order of 100 m inside6.0 the 10 orbit of Neptune has been estimated as on the order of 10 4 by [21]. As 1I/‘Oumuamua is the nearest macroscopic sample of interstellar material, likely with an isotopic signature distinct from any other object in our solar system, the scientific returns from sampling the object are hard to understate. Detailed in-situ studies of interstellar materials at interstellar distances is likely decades away. For example, Breakthrough Initiatives’ Project Starshot, which is developing a laser-propelled interstellar probe along with a beaming infrastructure for example, currently aims at a launch date in the 2040s [26]. Hence, an interesting question is if there is a way to exploit this unique opportunity to study interstellar material by sending a spacecraft to 1I/‘Oumuamua to make observations at close range. The Initiative for Interstellar Studies, i4is, has announced Project Lyra on the 30 th of October to answer this question. The goal of the project is to assess the feasibility of a mission to 1I/‘Oumuamua using current and near-term technology and to propose mission concepts for achieving a fly-by or rendezvous. The challenge is formidable. According to current estimates, 1I/‘Oumuamua has a heliocentric hyperbolic excess velocity of 26 km/s. This is considerably faster than any object humanity has ever launched into space. Voyager 1, the fastest object humanity has ever built, has a hyperbolic excess velocity of 16.6 km/s. As 1I/‘Oumuamua is already leaving our solar system, any spacecraft launched in the future would need to chase it. However, besides the scientific interest of getting data back from the object, the challenge to reach the object could stretch the current technological envelope of space exploration. Hence, Project Lyra is not only interesting from a scientific point of view but also in terms of the technological challenge it presents. This paper presents some preliminary results for a mission concept to 1I/‘Oumuamua. 2. Trajectory Analysis In the following, we first provide a first order trajectory analysis assuming one or more impulsive transfers in the vicinity of the earth and a free trajectory to 1I/‘Oumuamua. Subsequently we present results for a more complex trajectory that combines a Jupiter flyby and a solar Oberth maneuver. 2.1 Trajectory Analysis without Gravity Assist Given the hyperbolic excess velocity and its inclination with respect to the solar system ecliptic, the first question to answer is the required velocity increment (DeltaV) to reach the object, a key parameter for designing the propulsion system. The DeltaV for a mission without gravity assist is calculated by determining the transfer hyperbola from Earth orbit with respect to the position of 1I/‘Oumuamua at a certain point in time. Using the vis-viva equation (1), the orbital velocity v of a body on a hyperbolic trajectory can be computed. (1) 2 1 = − Where is the standard gravitational parameter, r is the radial distance of the object from the central body, and a the semi-major axis. With a few arithmetic manipulations, the relationship (2) between the orbital velocity , the escape velocity from the Sun, and the hyperbolic excess velocity ∞ can be obtained. (2) ∞ 2 = + 2 ∞ can be understood as the velocity at infinity with respect to the Sun. Note that the earth’s orbital velocity can be exploited for reducing the required DeltaV. Nevertheless the high inclination of 1I/‘Oumuamua relative to the ecliptic requires significant additional DeltaV. (3) ∞ 2 = − ! " cos & cos ' = + − ! " cos & cos ' Where i is the inclination of the trajectory with respect to the ecliptic and the angle between the velocity vector of the trajectory and the velocity vector of the Earth. ' Obviously, a slower spacecraft will reach the object later than a faster spacecraft, leading to a trade-off between trip duration and required DeltaV. Furthermore, the earlier the spacecraft is launched the shorter the trip duration, as the object is closer. However, a launch date within the next 5 years is likely to be unrealistic, and even 10 years could be challenging, in case new technologies need to be developed. A third trade-off is between launch date and trip time / characteristic energy C3. The characteristic energy is the square of the hyperbolic excess velocity ∞. These trade-offs are captured in Figure 1. The figure plots the characteristic energy for the launch with respect to mission duration and launch date. An impulsive propulsion system with a sufficiently short thrust duration is assumed. No planetary or solar fly-by is assumed, only a direct launch towards the object. It can be seen that a minimum 3 exists, which is about 703 km²/s² (26.5 km/s). However, this minimum value rapidly increases when the launch( date is moved into the future. At the same time, a larger mission duration leads to a decrease of the required 3 but also implies an encounter with the asteroid at a larger distance from the Sun. A realistic launch date (for a probe would be at least 10 years in the future (2027). At that point, the hyperbolic excess velocity with respect to the Earth is already at 37.4km/s (1400 km²/s²) with a mission duration of about 15 years, which makes such an orbital insertion extremely challenging with conventional launches in the absence of a planetary fly-by.
Load more

Recommended publications
  • Mission to Jupiter
    This book attempts to convey the creativity, Project A History of the Galileo Jupiter: To Mission The Galileo mission to Jupiter explored leadership, and vision that were necessary for the an exciting new frontier, had a major impact mission’s success. It is a book about dedicated people on planetary science, and provided invaluable and their scientific and engineering achievements. lessons for the design of spacecraft. This The Galileo mission faced many significant problems. mission amassed so many scientific firsts and Some of the most brilliant accomplishments and key discoveries that it can truly be called one of “work-arounds” of the Galileo staff occurred the most impressive feats of exploration of the precisely when these challenges arose. Throughout 20th century. In the words of John Casani, the the mission, engineers and scientists found ways to original project manager of the mission, “Galileo keep the spacecraft operational from a distance of was a way of demonstrating . just what U.S. nearly half a billion miles, enabling one of the most technology was capable of doing.” An engineer impressive voyages of scientific discovery. on the Galileo team expressed more personal * * * * * sentiments when she said, “I had never been a Michael Meltzer is an environmental part of something with such great scope . To scientist who has been writing about science know that the whole world was watching and and technology for nearly 30 years. His books hoping with us that this would work. We were and articles have investigated topics that include doing something for all mankind.” designing solar houses, preventing pollution in When Galileo lifted off from Kennedy electroplating shops, catching salmon with sonar and Space Center on 18 October 1989, it began an radar, and developing a sensor for examining Space interplanetary voyage that took it to Venus, to Michael Meltzer Michael Shuttle engines.
    [Show full text]
  • Arxiv:2006.00776V1 [Physics.Space-Ph] 1 Jun 2020
    manuscript submitted to Geophysical Research Letters Dust impact voltage signatures on Parker Solar Probe: influence of spacecraft floating potential S. D. Bale1,2, K. Goetz3, J. W. Bonnell1, A. W. Case4, C. H. K. Chen5,T. Dudok de Wit6, L. C. Gasque1,2, P. R. Harvey1, J. C. Kasper 7,4, P. J. Kellogg3, R. J. MacDowall8, M. Maksimovic9, D. M. Malaspina10, B. F. Page1,2, M. Pulupa1, M. L. Stevens4, J. R. Szalay11, A. Zaslavsky9 1Space Sciences Laboratory, University of California, Berkeley, CA 94720-7450, USA 2Physics Department, University of California, Berkeley, CA 94720-7300, USA 3School of Physics and Astronomy, University of Minnesota, Minneapolis, 55455, USA 4Smithsonian Astrophysical Observatory, Cambridge, MA 02138 USA 5School of Physics and Astronomy, Queen Mary University of London, London E1 4NS, UK 6LPC2E, CNRS and University of Orleans,´ Orleans,´ France 7Climate and Space Sciences and Engineering, University of Michigan, Ann Arbor, MI 48109, USA 8Solar System Exploration Division, NASA/Goddard Space Flight Center, Greenbelt, MD, 20771 9LESIA, Observatoire de Paris, Universit PSL, CNRS, Sorbonne Universit, Universit de Paris, 5 place Jules Janssen, 92195 Meudon, France 10Laboratory for Atmospheric and Space Physics, University of Colorado, Boulder, CO, 80303, USA 11Department of Astrophysical Sciences, Princeton University, Princeton, NJ, 08544, USA Key Points: • The Parker Solar Probe (PSP) FIELDS instrument measures millisecond volt- ages impulses associated with dust impacts • The sign of the largest monopole voltage response is a function of the spacecraft floating potential • These measurements are consistent with models of dynamic charge balance following dust impacts Submitted : June 2, 2020 arXiv:2006.00776v1 [physics.space-ph] 1 Jun 2020 Corresponding author: Stuart D.
    [Show full text]
  • JUICE Red Book
    ESA/SRE(2014)1 September 2014 JUICE JUpiter ICy moons Explorer Exploring the emergence of habitable worlds around gas giants Definition Study Report European Space Agency 1 This page left intentionally blank 2 Mission Description Jupiter Icy Moons Explorer Key science goals The emergence of habitable worlds around gas giants Characterise Ganymede, Europa and Callisto as planetary objects and potential habitats Explore the Jupiter system as an archetype for gas giants Payload Ten instruments Laser Altimeter Radio Science Experiment Ice Penetrating Radar Visible-Infrared Hyperspectral Imaging Spectrometer Ultraviolet Imaging Spectrograph Imaging System Magnetometer Particle Package Submillimetre Wave Instrument Radio and Plasma Wave Instrument Overall mission profile 06/2022 - Launch by Ariane-5 ECA + EVEE Cruise 01/2030 - Jupiter orbit insertion Jupiter tour Transfer to Callisto (11 months) Europa phase: 2 Europa and 3 Callisto flybys (1 month) Jupiter High Latitude Phase: 9 Callisto flybys (9 months) Transfer to Ganymede (11 months) 09/2032 – Ganymede orbit insertion Ganymede tour Elliptical and high altitude circular phases (5 months) Low altitude (500 km) circular orbit (4 months) 06/2033 – End of nominal mission Spacecraft 3-axis stabilised Power: solar panels: ~900 W HGA: ~3 m, body fixed X and Ka bands Downlink ≥ 1.4 Gbit/day High Δv capability (2700 m/s) Radiation tolerance: 50 krad at equipment level Dry mass: ~1800 kg Ground TM stations ESTRAC network Key mission drivers Radiation tolerance and technology Power budget and solar arrays challenges Mass budget Responsibilities ESA: manufacturing, launch, operations of the spacecraft and data archiving PI Teams: science payload provision, operations, and data analysis 3 Foreword The JUICE (JUpiter ICy moon Explorer) mission, selected by ESA in May 2012 to be the first large mission within the Cosmic Vision Program 2015–2025, will provide the most comprehensive exploration to date of the Jovian system in all its complexity, with particular emphasis on Ganymede as a planetary body and potential habitat.
    [Show full text]
  • Reduction of Saturn Orbit Insertion Impulse Using Deep-Space Low Thrust
    Reduction of Saturn Orbit Insertion Impulse using Deep-Space Low Thrust Elena Fantino ∗† Khalifa University of Science and Technology, Abu Dhabi, United Arab Emirates. Roberto Flores‡ International Center for Numerical Methods in Engineering, 08034 Barcelona, Spain. Jesús Peláez§ and Virginia Raposo-Pulido¶ Technical University of Madrid, 28040 Madrid, Spain. Orbit insertion at Saturn requires a large impulsive manoeuver due to the velocity difference between the spacecraft and the planet. This paper presents a strategy to reduce dramatically the hyperbolic excess speed at Saturn by means of deep-space electric propulsion. The inter- planetary trajectory includes a gravity assist at Jupiter, combined with low-thrust maneuvers. The thrust arc from Earth to Jupiter lowers the launch energy requirement, while an ad hoc steering law applied after the Jupiter flyby reduces the hyperbolic excess speed upon arrival at Saturn. This lowers the orbit insertion impulse to the point where capture is possible even with a gravity assist with Titan. The control-law algorithm, the benefits to the mass budget and the main technological aspects are presented and discussed. The simple steering law is compared with a trajectory optimizer to evaluate the quality of the results and possibilities for improvement. I. Introduction he giant planets have a special place in our quest for learning about the origins of our planetary system and Tour search for life, and robotic missions are essential tools for this scientific goal. Missions to the outer planets arXiv:2001.04357v1 [astro-ph.EP] 8 Jan 2020 have been prioritized by NASA and ESA, and this has resulted in important space projects for the exploration of the Jupiter system (NASA’s Europa Clipper [1] and ESA’s Jupiter Icy Moons Explorer [2]), and studies are underway to launch a follow-up of Cassini/Huygens called Titan Saturn System Mission (TSSM) [3], a joint ESA-NASA project.
    [Show full text]
  • A Perspective on the Design and Development of the Spacex Dragon Spacecraft Heatshield
    A Perspective on the Design and Development of the SpaceX Dragon Spacecraft Heatshield by Daniel J. Rasky, PhD Senior Scientist, NASA Ames Research Center Director, Space Portal, NASA Research Park Moffett Field, CA 94035 (650) 604-1098 / [email protected] February 28, 2012 2 How Did SpaceX Do This? Recovered Dragon Spacecraft! After a “picture perfect” first flight, December 8, 2010 ! 3 Beginning Here? SpaceX Thermal Protection Systems Laboratory, Hawthorne, CA! “Empty Floor Space” December, 2007! 4 Some Necessary Background: Re-entry Physics • Entry Physics Elements – Ballistic Coefficient – Blunt vs sharp nose tip – Entry angle/heating profile – Precision landing reqr. – Ablation effects – Entry G’loads » Blunt vs Lifting shapes – Lifting Shapes » Volumetric Constraints » Structure » Roll Control » Landing Precision – Vehicle flight and turn-around requirements Re-entry requires specialized design and expertise for the Thermal Protection Systems (TPS), and is critical for a successful space vehicle 5 Reusable vs. Ablative Materials 6 Historical Perspective on TPS: The Beginnings • Discipline of TPS began during World War II (1940’s) – German scientists discovered V2 rocket was detonating early due to re-entry heating – Plywood heatshields improvised on the vehicle to EDL solve the heating problem • X-15 Era (1950’s, 60’s) – Vehicle Inconel and Titanium metallic structure protected from hypersonic heating AVCOAT » Spray-on silicone based ablator for acreage » Asbestos/silicone moldable TPS for leading edges – Spray-on silicone ablator
    [Show full text]
  • 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
    [Show full text]
  • The Blurring Distinction Between Asteroids and Comets
    Answers Research Journal 8 (2015):203–208. www.answersingenesis.org/arj/v8/asteroids-and-comets.pdf The Blurring Distinction between Asteroids and Comets Danny R. Faulkner, Answers in Genesis, PO Box 510, Hebron, Kentucky, 41048. Abstract Asteroids and comets long had been viewed as distinct objects with regards to orbits and composition. However, discoveries made in recent years have blurred those distinctions. Whether there is a continuum on which our older conception of asteroids and comets are extremes or if there still is a gap between them is not entirely clear yet. Some of the newer views of comets and asteroids may challenge the evolutionary theory of the solar system. Additionally, the new information may challenge the idea that the solar system is billions of years old. For readers not versed in nomenclature of small solar system bodies, I discuss that in the appendix. Keywords: small solar system objects, comets, asteroids (minor planets) Introduction the sun, and their orbits frequently are inclined The differences between asteroids and comets considerably to the orbits of the planets. Because of At one time, we thought of asteroids and comets as their highly elliptical orbits, most comets alternately being two very different groups of objects. Comets and are very close to the sun when near perihelion and asteroids certainly looked different. Comets can be very far from the sun when near aphelion. Comets visible to the naked eye, and have been known since spend most of the time near aphelion far from the ancient times. They have a hazy, fuzzy appearance. sun, so that their ices remain frozen.
    [Show full text]
  • Science: Planetary Science Outyears Are Notional
    Science: Planetary Science Outyears are notional ($M) 2019 2020 2021 2022 2023 Planetary Science $2,235 $2,200 $2,181 $2,162 $2,143 Ø Creates a robotic Lunar Discovery and Exploration program, that supports commercial partnerships and innovative approaches to achieving human and science exploration goals. Ø Continues development of Mars 2020 and Europa Clipper. Ø Establishes a Planetary Defense program, including the Double Asteroid Redirection Test (DART) and Near-Earth Object Observations. Ø Studies a potential Mars Sample Return mission incorporating commercial partnerships. Ø Formulates the Lucy and Psyche missions. Ø Selects the next New Frontiers mission. Ø Invests in CubeSats/SmallSats that can achieve entirely new science at lower cost. Ø Operates 10 Planetary missions. § OSIRIS-REx will map asteroid Bennu. § New Horizons will fly by its Kuiper belt target. Dawn Image of Ceres on January 13, 2015 20 Science: Astrophysics Outyears are notional ($M) 2019 2020 2021 2022 2023 Astrophysics $1,185 $1,185 $1,185 $1,185 $1,185 Ø Launches the James Webb Space Telescope. Ø Moves Webb into the Cosmic Origins Program within the Astrophysics Account. Ø Terminates WFIRST due to its significant cost and higher priorities elsewhere within NASA. Increases funding for future competed missions and research. Ø Supports the TESS exoplanet mission following launch by June 2018. Ø Formulates or develops, IXPE, GUSTO, XARM, Euclid, and a new MIDEX mission to be selected in FY 2019. Ø Operates ten missions and the balloon project. Ø Invests in CubeSats/SmallSats that can achieve entirely new science at lower cost. Ø All Astrophysics missions beyond prime operations (including SOFIA) will be subject to senior review in 2019.
    [Show full text]
  • 1. Some of the Definitions of the Different Types of Objects in the Solar
    1. Some of the definitions of the different types of objects in has the greatest orbital inclination (orbit at the the solar system overlap. Which one of the greatest angle to that of Earth)? following pairs does not overlap? That is, if an A) Mercury object can be described by one of the labels, it B) Mars cannot be described by the other. C) Jupiter A) dwarf planet and asteroid D) Pluto B) dwarf planet and Kuiper belt object C) satellite and Kuiper belt object D) meteoroid and planet 10. Of the following objects in the solar system, which one has the greatest orbital eccentricity and therefore the most elliptical orbit? 2. Which one of the following is a small solar system body? A) Mercury A) Rhea, a moon of Saturn B) Mars B) Pluto C) Earth C) Ceres (an asteroid) D) Pluto D) Mathilde (an asteroid) 11. What is the largest moon of the dwarf planet Pluto 3. Which of the following objects was discovered in the called? twentieth century? A) Chiron A) Pluto B) Callisto B) Uranus C) Charon C) Neptune D) Triton D) Ceres 12. If you were standing on Pluto, how often would you see 4. Pluto was discovered in the satellite Charon rise above the horizon each A) 1930. day? B) 1846. A) once each 6-hour day as Pluto rotates on its axis C) 1609. B) twice each 6-hour day because Charon is in a retrograde D) 1781. orbit C) once every 2 days because Charon orbits in the same direction Pluto rotates but more slowly 5.
    [Show full text]
  • On Parker Solar Probe, NASA Leaves the Driving to Aerojet Rocketdyne
    On Parker Solar Probe, NASA Leaves the Driving to Aerojet Rocketdyne August 12, 2018 KENNEDY SPACE CENTER, Fla., Aug. 12, 2018 (GLOBE NEWSWIRE) -- With a big assist from Aerojet Rocketdyne, NASA’s Parker Solar Probe is now on its way to humankind’s closest encounter ever with a star – in this case our solar system’s sun. Parker Solar Probe NASA image Aerojet Rocketdyne provided the full propulsion system on NASA’s Parker Solar Probe, which will venture eight times closer to the Sun than the previous record holderCredit: NASA/Johns Hopkins APL In addition to the RS-68A main engines for the United Launch Alliance Delta IV Heavy rocket that launched the Parker Probe into space, Aerojet Rocketdyne also supplied the RL10B-2 second stage engine and 12 MR-106 reaction control thrusters on the Delta Cryogenic Second Stage, as well as the full propulsion system on the Parker Solar Probe. The nearly 7-year journey will bring the probe to within 6.2 million kilometers of the Sun’s surface. That’s well within the orbit of the Sun’s nearest planet, Mercury, and eight times closer than the previous record holder, the U.S.-German Helios B probe, which made its closest approach in 1976. “Surviving a years-long journey to the corona of the Sun while operating in autonomous mode requires an incredibly high level of reliability,” said Aerojet Rocketdyne CEO and President Eileen Drake. “Aerojet Rocketdyne propulsion plays a critical role in all aspects of the Parker Solar Probe mission, from launch on the Delta IV, to the probe’s safe cruise through space and approach of the Sun’s atmosphere.” The Parker Solar Probe ultimately will dip into the Sun’s corona, carrying instruments to observe and measure the movement and interaction of phenomena including electric and magnetic fields, energetic particles and solar wind.
    [Show full text]
  • The Active Region Source of a Type III Radio Storm Observed by Parker Solar Probe During Encounter 2 Log-Spaced Chunks, Each of 2.56 Mhz Wide
    Astronomy & Astrophysics manuscript no. ISSI_E2_Hinode-final ©ESO 2021 February 10, 2021 The active region source of a type III radio storm observed by Parker Solar Probe during Encounter 2 L. Harra1, 2, D. H. Brooks3, S. D. Bale4, C. H. Mandrini5, 6, K. Barczynski1, 2, R. Sharma7, S. T. Badman4, S. Vargas Domínguez8, and M. Pulupa4 1 PMOD/WRC, Dorfstrasse 33 CH-7260 Davos Dorf, Switzerland e-mail: [email protected] e-mail: [email protected] 2 ETH-Zurich, Hönggerberg campus, HIT building, Zürich, Switzerland 3 College of Science, George Mason University, 4400 University Drive, Fairfax, VA 22030 USA e-mail: [email protected] 4 Physics Department and Space Sciences Laboratory, University of California, Berkeley, USA. 94720-7450 e-mail: [email protected] 5 Instituto de Astronomía y Física del Espacio (IAFE), CONICET-UBA, Buenos Aires, Argentina 6 Facultad de Ciencias Exactas y Naturales (FCEN), UBA, Buenos Aires, Argentina e-mail: [email protected] 7 Fachhochschule Nordwestschweiz (FHNW), Bahnhofstrasse 6, 5210 Windisch, Switzerland e-mail: [email protected] 8 Universidad Nacional de Colombia, Observatorio Astronómico Nacional, Bogotá, Colombia e-mail: [email protected] Received September 2020 ABSTRACT Context. To investigate the source of a type III radio burst storm during encounter 2 of NASA’s Parker Solar Probe (PSP) mission. Aims. It was observed that in encounter 2 of NASA’s Parker Solar Probe mission there was a large amount of radio activity, and in particular a noise storm of frequent, small type III bursts from 31st March to 6th April 2019. Our aim is to investigate the source of these small and frequent bursts.
    [Show full text]
  • Determination of Optimal Earth-Mars Trajectories to Target the Moons Of
    The Pennsylvania State University The Graduate School Department of Aerospace Engineering DETERMINATION OF OPTIMAL EARTH-MARS TRAJECTORIES TO TARGET THE MOONS OF MARS A Thesis in Aerospace Engineering by Davide Conte 2014 Davide Conte Submitted in Partial Fulfillment of the Requirements for the Degree of Master of Science May 2014 ii The thesis of Davide Conte was reviewed and approved* by the following: David B. Spencer Professor of Aerospace Engineering Thesis Advisor Robert G. Melton Professor of Aerospace Engineering Director of Undergraduate Studies George A. Lesieutre Professor of Aerospace Engineering Head of the Department of Aerospace Engineering *Signatures are on file in the Graduate School iii ABSTRACT The focus of this thesis is to analyze interplanetary transfer maneuvers from Earth to Mars in order to target the Martian moons, Phobos and Deimos. Such analysis is done by solving Lambert’s Problem and investigating the necessary targeting upon Mars arrival. Additionally, the orbital parameters of the arrival trajectory as well as the relative required ΔVs and times of flights were determined in order to define the optimal departure and arrival windows for a given range of date. The first step in solving Lambert’s Problem consists in finding the positions and velocities of the departure (Earth) and arrival (Mars) planets for a given range of dates. Then, by solving Lambert’s problem for various combinations of departure and arrival dates, porkchop plots can be created and examined. Some of the key parameters that are plotted on porkchop plots and used to investigate possible transfer orbits are the departure characteristic energy, C3, and the arrival v∞.
    [Show full text]