Atmospheric Planetary Probes And
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Onboard Determination of Vehicle Glide Capability for Shuttle Abort Flight Managment (Safm)
Source of Acquisition NASA Johnson Space Center ONBOARD DETERMINATION OF VEHICLE GLIDE CAPABILITY FOR SHUTTLE ABORT FLIGHT MANAGMENT (SAFM) Mark Jackson, Timothy Straube, Thomas Fill, Scott Nemeth, When one or more main engines fail during ascent, the flight crew of the Space Shuttle must make several critical decisions and accurately perform a series of abort procedures. One of the most important decisions for many aborts is the selection ofa landing site. Several factors influence the ability to reach a landing site, including the spacecraft point of atmospheric entry, the energy state at atmospheric entry, the vehicle glide capability from that energy state, and whether one or more suitable landing sites are within the glide capability. Energy assessment is further complicated by the fact that phugoid oscillations in total energy influence glide capability. Once the glide capability is known, the crew must select the "best" site option based upon glide capability and landing site conditions and facilities. Since most of these factors cannot currently be assessed by the crew in flight, extensive planning is required prior to each mission to script a variety of procedures based upon spacecraft velocity at the point of engine failure (or failures). The results of this pre flight planning are expressed in tables and diagrams on mission-specific cockpit checklists. Crew checklist procedures involve leafing through several pages of instructions and navigating a decision tree for site selection and flight procedures - all during a time critical abort situation. With the advent of the Cockpit Avionics Upgrade (CAU), the Shuttle will have increased on-board computational power to help alleviate crew workload during aborts and provide valuable situational awareness during nominal operations. -
Notes on Earth Atmospheric Entry for Mars Sample Return Missions
NASA/TP–2006-213486 Notes on Earth Atmospheric Entry for Mars Sample Return Missions Thomas Rivell Ames Research Center, Moffett Field, California September 2006 The NASA STI Program Office . in Profile Since its founding, NASA has been dedicated to the • CONFERENCE PUBLICATION. Collected advancement of aeronautics and space science. The papers from scientific and technical confer- NASA Scientific and Technical Information (STI) ences, symposia, seminars, or other meetings Program Office plays a key part in helping NASA sponsored or cosponsored by NASA. maintain this important role. • SPECIAL PUBLICATION. Scientific, technical, The NASA STI Program Office is operated by or historical information from NASA programs, Langley Research Center, the Lead Center for projects, and missions, often concerned with NASA’s scientific and technical information. The subjects having substantial public interest. NASA STI Program Office provides access to the NASA STI Database, the largest collection of • TECHNICAL TRANSLATION. English- aeronautical and space science STI in the world. language translations of foreign scientific and The Program Office is also NASA’s institutional technical material pertinent to NASA’s mission. mechanism for disseminating the results of its research and development activities. These results Specialized services that complement the STI are published by NASA in the NASA STI Report Program Office’s diverse offerings include creating Series, which includes the following report types: custom thesauri, building customized databases, organizing and publishing research results . even • TECHNICAL PUBLICATION. Reports of providing videos. completed research or a major significant phase of research that present the results of NASA For more information about the NASA STI programs and include extensive data or theoreti- Program Office, see the following: cal analysis. -
A Comprehensive Entry, Descent, Landing, And
A Comprehensive Entry, Descent, Landing, and Locomotion (EDLL) Vehicle for Planetary Exploration Kevin Schroeder Dissertation submitted to the Faculty of the Virginia Polytechnic Institute and State University in partial fulfillment of the requirements for the degree of Doctor of Philosophy in Mechanical Engineering Javid Bayandor, Chair Jamshid Samareh Sasan Armand Francine Battaglia Walter O’Brien Wayne Scales July 18th, 2017 Blacksburg, Virginia Keywords: Entry Descent Landing (EDL), Tensegrity, Venus Rover, Deployable Heat Shield Copyright 2017, Kevin Schroeder A Comprehensive Entry, Descent, Landing, and Locomotion (EDLL) Vehicle for Planetary Exploration Kevin Schroeder Abstract The 2012 Decadal Survey has stated that there is a critical role for a Venus In-situ Explore (VISE) missions to a variety of important sites, specifically the Tessera terrain. This work aims to answer the Decadal Survey’s call by developing a new comprehensive Entry, Descent, Landing, and Locomotion (EDLL) vehicle for in-situ exploration of Venus, especially in the Tessera regions. TANDEM, the Tension Adjustable Network for Deploying Entry Membrane, is a new planetary probe concept in which all of EDLL is achieved by a single multifunctional tensegrity structure. The concept uses same fundamental concept as the ADEPT (Adaptable Deployable Entry and Placement Technology) deployable heat shield but replaces the standard internal structure with the structure from the tensegrity- actuated rover to provide a combined aeroshell and rover design. The tensegrity system implemented by TANDEM reduces the mass of the overall system while enabling surface locomotion and mitigating risk associated with landing in the rough terrain of Venus’s Tessera regions, which is otherwise nearly inaccessible to surface missions. -
GAS DIVISION NEWSLETTER Official Publication of the BFA Gas Division
GAS DIVISION NEWSLETTER Official Publication of the BFA Gas Division Volume 4, Issue 2 Copyright Peter Cuneo & Barbara Fricke, 2003 August 2003 On Saturday morning, we were greeted with a hotel RACE TO KITTY HAWK message saying the morning launch had been cancelled by Ray Bair but a briefing would take place at 7:00 a.m. The entire day was scrubbed due to substantial thunderstorms just west of Dayton in Indiana. As it turned out, the storms dissipated, and the day was pleasant for visiting the As part of the centennial celebration of powered various museums and city historic sites. That evening, flight, RE/MAX sponsored a Balloon Celebration we were treated to a reception at the Air Force Museum which included both hot air and gas flights for the and a briefing that made a Sunday morning launch seem weekend of the Fourth of July. At least that was the possible. Again the threat of severe weather prevented a plan. While about half the field of hot air balloons Saturday night launch. Later that night I found myself finally flew on Sunday morning, the gas flight was clustered in the main briefing room as the hotel staff totally scrubbed. gathered everyone for a tornado “drill”. The intended gas competition was an accuracy flight Sunday morning we were back on the field and once to the monument marking the first flight of the again prepared the equipment for launch. Another Wright brothers in Kitty Hawk, N.C. This is about couple of hours Sunday morning was only slightly better 500 miles from the launch site at Wright Patterson as the local weather allowed launch of some of the hot AFB in Dayton, Ohio. -
FCC-20-54A1.Pdf
Federal Communications Commission FCC 20-54 Before the Federal Communications Commission Washington, D.C. 20554 In the Matter of ) ) Mitigation of Orbital Debris in the New Space Age ) IB Docket No. 18-313 ) REPORT AND ORDER AND FURTHER NOTICE OF PROPOSED RULEMAKING Adopted: April 23, 2020 Released: April 24, 2020 By the Commission: Chairman Pai and Commissioners O’Rielly, Carr, and Starks issuing separate statements; Commissioner Rosenworcel concurring and issuing a statement. Comment Date: (45 days after date of publication in the Federal Register). Reply Comment Date: (75 days after date of publication in the Federal Register). TABLE OF CONTENTS Heading Paragraph # I. INTRODUCTION .................................................................................................................................. 1 II. BACKGROUND .................................................................................................................................... 3 III. DISCUSSION ...................................................................................................................................... 14 A. Regulatory Approach to Mitigation of Orbital Debris ................................................................... 15 1. FCC Statutory Authority Regarding Orbital Debris ................................................................ 15 2. Relationship with Other U.S. Government Activities ............................................................. 20 3. Economic Considerations ....................................................................................................... -
Appendix 1: Venus Missions
Appendix 1: Venus Missions Sputnik 7 (USSR) Launch 02/04/1961 First attempted Venus atmosphere craft; upper stage failed to leave Earth orbit Venera 1 (USSR) Launch 02/12/1961 First attempted flyby; contact lost en route Mariner 1 (US) Launch 07/22/1961 Attempted flyby; launch failure Sputnik 19 (USSR) Launch 08/25/1962 Attempted flyby, stranded in Earth orbit Mariner 2 (US) Launch 08/27/1962 First successful Venus flyby Sputnik 20 (USSR) Launch 09/01/1962 Attempted flyby, upper stage failure Sputnik 21 (USSR) Launch 09/12/1962 Attempted flyby, upper stage failure Cosmos 21 (USSR) Launch 11/11/1963 Possible Venera engineering test flight or attempted flyby Venera 1964A (USSR) Launch 02/19/1964 Attempted flyby, launch failure Venera 1964B (USSR) Launch 03/01/1964 Attempted flyby, launch failure Cosmos 27 (USSR) Launch 03/27/1964 Attempted flyby, upper stage failure Zond 1 (USSR) Launch 04/02/1964 Venus flyby, contact lost May 14; flyby July 14 Venera 2 (USSR) Launch 11/12/1965 Venus flyby, contact lost en route Venera 3 (USSR) Launch 11/16/1965 Venus lander, contact lost en route, first Venus impact March 1, 1966 Cosmos 96 (USSR) Launch 11/23/1965 Possible attempted landing, craft fragmented in Earth orbit Venera 1965A (USSR) Launch 11/23/1965 Flyby attempt (launch failure) Venera 4 (USSR) Launch 06/12/1967 Successful atmospheric probe, arrived at Venus 10/18/1967 Mariner 5 (US) Launch 06/14/1967 Successful flyby 10/19/1967 Cosmos 167 (USSR) Launch 06/17/1967 Attempted atmospheric probe, stranded in Earth orbit Venera 5 (USSR) Launch 01/05/1969 Returned atmospheric data for 53 min on 05/16/1969 M. -
Catherinesaunders
The Utility of Robot Sensory Devices in a Collaborative Autonomic Environment Catherine Saunders, Roy Sterritt, George Wilkie School of Computing and Mathematics University of Ulster Northern Ireland [email protected], [email protected], [email protected] Abstract –-This paper proposes an Autonomic architecture that environment and relay meaningful information to each will enable mobile robots to self-manage and collaborate by other. using control loops to monitor their internal state and external environment. The Autonomic Computing MAPE-K control In this paper we discuss the sensor capabilities of the Dr loop is used to design a Robot Autonomic Element and a Robot X80-H platform that will be used for the research. A Mapping Autonomic Element; each can exchange data and collaborate to find an object located within a room. A review of design of the proposed system is included and explained. A the sensor capabilities of the X80-H mobile robot platform is brief literature review of robotic collaborative systems is undertaken with emphasis on how useful each sensor will be to also included. The Research Background section looks at the proposed research. A literature review of other projects why self-managing software systems are needed. that feature robot collaboration is also included. Keywords - autonomic computing; mobile robot; Dr Robot II. ROBOT SENSORY DEVICES X80-H; collaboration; MAPE-K This section gives an overview of the sensors that the Dr Robot X80-H is equipped with. We assess how reliable they are and how useful they will be for our research. We will be I. -
EDL – Lessons Learned and Recommendations
."#!(*"# 0 1(%"##" !)"#!(*"#* 0 1"!#"("#"#(-$" ."!##("""*#!#$*#( "" !#!#0 1%"#"! /!##"*!###"#" #"#!$#!##!("""-"!"##&!%%!%&# $!!# %"##"*!%#'##(#!"##"#!$$# /25-!&""$!)# %"##!""*&""#!$#$! !$# $##"##%#(# ! "#"-! *#"!,021 ""# !"$!+031 !" )!%+041 #!( !"!# #$!"+051 # #$! !%#-" $##"!#""#$#$! %"##"#!#(- IPPW Enabled International Collaborations in EDL – Lessons Learned and Recommendations: Ethiraj Venkatapathy1, Chief Technologist, Entry Systems and Technology Division, NASA ARC, 2 Ali Gülhan , Department Head, Supersonic and Hypersonic Technologies Department, DLR, Cologne, and Michelle Munk3, Principal Technologist, EDL, Space Technology Mission Directorate, NASA. 1 NASA Ames Research Center, Moffett Field, CA [email protected]. 2 Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR), German Aerospace Center, [email protected] 3 NASA Langley Research Center, Hampron, VA. [email protected] Abstract of the Proposed Talk: One of the goals of IPPW has been to bring about international collaboration. Establishing collaboration, especially in the area of EDL, can present numerous frustrating challenges. IPPW presents opportunities to present advances in various technology areas. It allows for opportunity for general discussion. Evaluating collaboration potential requires open dialogue as to the needs of the parties and what critical capabilities each party possesses. Understanding opportunities for collaboration as well as the rules and regulations that govern collaboration are essential. The authors of this proposed talk have explored and established collaboration in multiple areas of interest to IPPW community. The authors will present examples that illustrate the motivations for the partnership, our common goals, and the unique capabilities of each party. The first example involves earth entry of a large asteroid and break-up. NASA Ames is leading an effort for the agency to assess and estimate the threat posed by large asteroids under the Asteroid Threat Assessment Project (ATAP). -
THE LANDSCAPE of COMET HALLEY Hungarian Academy of Sciences CENTRAL RESEARCH INSTITUTE for PHYSICS
KFKI 1939-35/C E. MERÉNYI L. FÖLDY K. SZEGŐ I. TÓTH A. KONDOR THE LANDSCAPE OF COMET HALLEY Hungarian Academy of Sciences CENTRAL RESEARCH INSTITUTE FOR PHYSICS BUDAPEST KFKI-1989-35/C PREPRINT THE LANDSCAPE OF COMET HALLEY E. MERÉNYI, L. FÖLDY, K. SZEGŐ. I. TÓTH', A. KONDOR Central Research Institute for Physics H-1626 Budapest 114, P.O.B. 49 'Konkoly Thege Observatory H-1625 Budapest, P.O.B. 67 Comets in Post Hal ley area Bamberg (FRG). 24 28 April 1989 HU ISSN 0368 6330 E. Merényi, L. Földy. К. Szegő, I. Tóth. A. Kondor: The landscape of cornel Halley KFKM989 35/C ABSTRACT In this paper the three dimensional model of P/Halley's nucleus is constructed based on the results of the imaging experiments It has the following major characteristics: the overai' sizes are 7 2 km, 722 km, 15.3 km, its volume is 365 km3, the ratios of the inertfal momenta are 34:33:1, the longest Inorttal axis is siiyhlly inclined to the geometrical axis of the body. 3 3° in latitude and 1.1° In longitude if the geometrical axis is at zero latitude and longitude The shape is very irregular, it is not close to any regular body e g to a tri axial ellipsoid Several features on the images are interpreted as local slope variations of the nucleus. Э. Мерени; Л. Фёлди, К. Сегё, И. Тот, Л. Кондор: Форма и поверхность ядра кометы Галлея. КГКТ-198<?-35/С АННОТАЦИЯ Описывается трехмерная модель ядра кометы Галлея, основывающаяся на резуль татах телевизионного эксперимента КА "Вега". -
A Systematic Concept Exploration Methodology Applied to Venus in Situ Explorer
Session III: Probe Missions to the Giant Planets, Titan and Venus A Systematic Concept Exploration Methodology Applied to Venus In Situ Explorer Jarret M. Lafleur *, Gregory Lantoine *, Andrew L. Hensley *, Ghislain J. Retaureau *, Kara M. Kranzusch *, Joseph W. Hickman *, Marc N. Wilson *, and Daniel P. Schrage † Georgia Institute of Technology Atlanta, Georgia 30332 ABSTRACT One of the most critical tasks in the design of a complex system is the initial conversion of mission or program objectives into a baseline system architecture. Presented in this paper is a methodology to aid in this process that is frequently used for aerospace problems at the Georgia Institute of Technology. In this paper, the methodology is applied to initial concept formulation for the Venus In Situ Explorer (VISE) mission. Five primary steps are outlined which encompass program objective definition through evaluation of candidate designs. Tools covered include the Analytic Hierarchy Process (AHP), Technique for Order Preference by Similarity to Ideal Solution (TOPSIS), and morphological matrices. Direction is given for the application of modeling and simulation as well as for subsequent iterations of the process. The paper covers both theoretical and practical aspects of the tools and process in the context of the VISE example, and it is hoped that this methodology may find future use in interplanetary probe design. 1. INTRODUCTION One of the most critical tasks in the design of a complex engineering system is the initial conversion of mission or program objectives and requirements into a baseline system architecture. In completing this task, the challenge exists to comprehensively but efficiently explore the global trade space of potential designs. -
Jjmonl 1603.Pmd
alactic Observer GJohn J. McCarthy Observatory Volume 9, No. 3 March 2016 GRAIL - On the Trail of the Moon's Missing Mass GRAIL (Gravity Recovery and Interior Laboratory) was a NASA scientific mission in 2011/12 to map the surface of the moon and collect data on gravitational anomalies. The image here is an artist's impres- sion of the twin satellites (Ebb and Flow) orbiting in tandem above a gravitational image of the moon. See inside, page 4 for information on gravitational anomalies (mascons) or visit http://solarsystem. nasa.gov/grail. The John J. McCarthy Observatory Galactic Observer New Milford High School Editorial Committee 388 Danbury Road Managing Editor New Milford, CT 06776 Bill Cloutier Phone/Voice: (860) 210-4117 Production & Design Phone/Fax: (860) 354-1595 www.mccarthyobservatory.org Allan Ostergren Website Development JJMO Staff Marc Polansky It is through their efforts that the McCarthy Observatory Technical Support has established itself as a significant educational and Bob Lambert recreational resource within the western Connecticut Dr. Parker Moreland community. Steve Barone Jim Johnstone Colin Campbell Carly KleinStern Dennis Cartolano Bob Lambert Mike Chiarella Roger Moore Route Jeff Chodak Parker Moreland, PhD Bill Cloutier Allan Ostergren Cecilia Dietrich Marc Polansky Dirk Feather Joe Privitera Randy Fender Monty Robson Randy Finden Don Ross John Gebauer Gene Schilling Elaine Green Katie Shusdock Tina Hartzell Paul Woodell Tom Heydenburg Amy Ziffer In This Issue "OUT THE WINDOW ON YOUR LEFT" ............................... 4 SUNRISE AND SUNSET ...................................................... 13 MARE HUMBOLDTIANIUM AND THE NORTHEAST LIMB ......... 5 JUPITER AND ITS MOONS ................................................. 13 ONE YEAR IN SPACE ....................................................... 6 TRANSIT OF JUPITER'S RED SPOT .................................... -
+ New Horizons
Media Contacts NASA Headquarters Policy/Program Management Dwayne Brown New Horizons Nuclear Safety (202) 358-1726 [email protected] The Johns Hopkins University Mission Management Applied Physics Laboratory Spacecraft Operations Michael Buckley (240) 228-7536 or (443) 778-7536 [email protected] Southwest Research Institute Principal Investigator Institution Maria Martinez (210) 522-3305 [email protected] NASA Kennedy Space Center Launch Operations George Diller (321) 867-2468 [email protected] Lockheed Martin Space Systems Launch Vehicle Julie Andrews (321) 853-1567 [email protected] International Launch Services Launch Vehicle Fran Slimmer (571) 633-7462 [email protected] NEW HORIZONS Table of Contents Media Services Information ................................................................................................ 2 Quick Facts .............................................................................................................................. 3 Pluto at a Glance ...................................................................................................................... 5 Why Pluto and the Kuiper Belt? The Science of New Horizons ............................... 7 NASA’s New Frontiers Program ........................................................................................14 The Spacecraft ........................................................................................................................15 Science Payload ...............................................................................................................16