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a aThe document discusses two spacecraft, SOHO and STEREO, that have been used to observe the sun. SOHO was launched in 1995 with a design lifetime of 2 years but remains operational today. It carries several instruments to study the solar interior, corona, and solar wind. SOHO orbits the L1 Lagrange point in a halo orbit. STEREO was launched in 2006 with two spacecraft to observe the sun from the sides. Other solar observing spacecraft mentioned include ACE, SDO, Solar Orbiter, DSCOVR, and Parker Solar Probe.
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ADITYA-L1 MISSION
The Aditya-L1 spacecraft is equipped with seven specialized instruments designed to observe different aspects of the Sun, including its photosphere, chromosphere, and the outermost layer called the corona. These instruments utilize various techniques, including electromagnetic and particle detection, as well as magnetic field measurement.
Exploring the Sun-heliosphere connection with Solar Orbiter
This talk was given to Airdrie Astronomy Association on 22 March 2013. Some of the material was borrowed from Daniel Mueller (ESA) and the Solar Orbiter team. More information on Solar Orbiter can be found at http://sci.esa.int/solarorbiter
Aditya l1
Aditya-L1 is ISRO's second astronomy mission to study the sun. It will be launched into orbit around the Lagrange point L1, approximately 1.5 million km from Earth, to observe the photosphere, chromosphere, and corona of the sun with its seven scientific payloads. Studying the sun is important to understand solar winds, flares, and disturbances that can affect communications on Earth and the orbits and electronics of satellites. Future ISRO missions include exploring the lunar poles in collaboration with Japan and additional satellites in the RISAT series.
aditya-l1-210625152747 (1).pdmmmmmmmmmmmmmmmmmmmmmmmmmf
Aditya-L1 is ISRO's second astronomy mission to study the sun. It contains seven payloads that will provide multi-dimensional observations of the sun's photosphere, chromosphere, and corona. Studying the sun is important because solar activity can interfere with communications on Earth and affect satellites through radiation and magnetic field fluctuations. Future goals beyond Aditya-L1 include collaborating with Japan on exploring the lunar poles and launching new Earth observation and crewed spaceflight missions.
International astronomy from the Moon
International Astronomy from the Moon
Southeast Asia and Beyond
The document discusses conducting astronomy from the moon, including as a shield from the sun/earth, as a stable platform, and for access from a lunar base. It outlines past and current lunar astronomy studies and proposals from agencies like NASA, ESA, China, and opportunities for involvement from Southeast Asian countries. Key points include China's Chang'e lunar telescope capturing over 32,000 images, and potential for commercial communications from the moon to expand coverage. Moon plans from agencies like NASA, JAXA, ISRO, KARI, and CSA are summarized.
Orbit design for exoplanet discovery spacecraft dr dora musielak 1 april 2019
Most exoplanets have been discovered with space telescopes. Starting with an overview of rocket propulsion, this presentation introduces spacecraft trajectories in the Sun-Earth-Moon System, focusing especially on those appropriate for exoplanet detection spacecraft. It reviews past, present, and future exoplanet discovery missions.
Journey of Mangalyaan
Mangalyaan india's first MOM at first attempt,
so over view of MOM, and brief explanation of instruments used in payload spacecraft, and phases of orbital transformation
The Unprecedented Rosetta mission to Comet 67P/Churyumov–Gerasimenko
After almost 11 years in transit and 4 gravitational assists from the Earth and Mars, the European Space Agency’s Rosetta probe has arrived at the Jupiter-family comet 67P/Churyumov–Gerasimenko. Arriving on Wednesday, August 6th, the probe went into a 100 km-high orbit around the comet, both of which are now in common orbit around the sun. Depending on the comet’s activity, Rosetta will come as close as 10 km to the comet’s nucleus over the course of the mission. With a high orbital eccentricity (the orbit’s deviation from a perfect circle) of 0.640, a perihelion of 1.2 AU and an aphelion of 5.68 AU, 67P/Churyumov–Gerasimenko is now in common orbit around the sun with Rosetta.
Rosetta is a cornerstone mission of the European Space Agency (ESA). It is an unprecedented landmark achievement in human history and the history of science. Humankind has placed a sophisticated instrument of science in orbit around a comet's nucleus and has placed a robotic lander in the surface of that nucleus! Rosetta will chase down, go into orbit around, and land on the object of interest. It will study 67P/Churyumov-Gerasimenko with a combination of remote sensing and in situ measurements. The mission has 2 phases, the ongoing orbital phase and the landing phase. During the ongoing orbital phase, the spacecraft will examine the comet up close with its suite of 11 instruments. During the landing phase, the orbiter will release the Philae lander which carries an onboard suite of 10 instruments for imaging and sampling the comet’s nucleus. The mission will track the comet through perihelion, its closest approach to the sun, examining its behavior before, during and after.
Providing an introductory retrospective of comets, sometimes regarded as harbingers of doom, Prof. Madigan discusses this historic mission, a mission that includes study of the comet from the surface of its nucleus!
This public event was hosted at the Ross School (East Hampton, NY) by the Montauk Observatory on September 18th, 2014.
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ADITYA-L1 MISSION
The Aditya-L1 spacecraft is equipped with seven specialized instruments designed to observe different aspects of the Sun, including its photosphere, chromosphere, and the outermost layer called the corona. These instruments utilize various techniques, including electromagnetic and particle detection, as well as magnetic field measurement.
Exploring the Sun-heliosphere connection with Solar Orbiter
This talk was given to Airdrie Astronomy Association on 22 March 2013. Some of the material was borrowed from Daniel Mueller (ESA) and the Solar Orbiter team. More information on Solar Orbiter can be found at http://sci.esa.int/solarorbiter
Aditya l1
Aditya-L1 is ISRO's second astronomy mission to study the sun. It will be launched into orbit around the Lagrange point L1, approximately 1.5 million km from Earth, to observe the photosphere, chromosphere, and corona of the sun with its seven scientific payloads. Studying the sun is important to understand solar winds, flares, and disturbances that can affect communications on Earth and the orbits and electronics of satellites. Future ISRO missions include exploring the lunar poles in collaboration with Japan and additional satellites in the RISAT series.
aditya-l1-210625152747 (1).pdmmmmmmmmmmmmmmmmmmmmmmmmmf
Aditya-L1 is ISRO's second astronomy mission to study the sun. It contains seven payloads that will provide multi-dimensional observations of the sun's photosphere, chromosphere, and corona. Studying the sun is important because solar activity can interfere with communications on Earth and affect satellites through radiation and magnetic field fluctuations. Future goals beyond Aditya-L1 include collaborating with Japan on exploring the lunar poles and launching new Earth observation and crewed spaceflight missions.
International astronomy from the Moon
International Astronomy from the Moon
Southeast Asia and Beyond
The document discusses conducting astronomy from the moon, including as a shield from the sun/earth, as a stable platform, and for access from a lunar base. It outlines past and current lunar astronomy studies and proposals from agencies like NASA, ESA, China, and opportunities for involvement from Southeast Asian countries. Key points include China's Chang'e lunar telescope capturing over 32,000 images, and potential for commercial communications from the moon to expand coverage. Moon plans from agencies like NASA, JAXA, ISRO, KARI, and CSA are summarized.
Orbit design for exoplanet discovery spacecraft dr dora musielak 1 april 2019
Most exoplanets have been discovered with space telescopes. Starting with an overview of rocket propulsion, this presentation introduces spacecraft trajectories in the Sun-Earth-Moon System, focusing especially on those appropriate for exoplanet detection spacecraft. It reviews past, present, and future exoplanet discovery missions.
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Mangalyaan india's first MOM at first attempt,
so over view of MOM, and brief explanation of instruments used in payload spacecraft, and phases of orbital transformation
The Unprecedented Rosetta mission to Comet 67P/Churyumov–Gerasimenko
After almost 11 years in transit and 4 gravitational assists from the Earth and Mars, the European Space Agency’s Rosetta probe has arrived at the Jupiter-family comet 67P/Churyumov–Gerasimenko. Arriving on Wednesday, August 6th, the probe went into a 100 km-high orbit around the comet, both of which are now in common orbit around the sun. Depending on the comet’s activity, Rosetta will come as close as 10 km to the comet’s nucleus over the course of the mission. With a high orbital eccentricity (the orbit’s deviation from a perfect circle) of 0.640, a perihelion of 1.2 AU and an aphelion of 5.68 AU, 67P/Churyumov–Gerasimenko is now in common orbit around the sun with Rosetta.
Rosetta is a cornerstone mission of the European Space Agency (ESA). It is an unprecedented landmark achievement in human history and the history of science. Humankind has placed a sophisticated instrument of science in orbit around a comet's nucleus and has placed a robotic lander in the surface of that nucleus! Rosetta will chase down, go into orbit around, and land on the object of interest. It will study 67P/Churyumov-Gerasimenko with a combination of remote sensing and in situ measurements. The mission has 2 phases, the ongoing orbital phase and the landing phase. During the ongoing orbital phase, the spacecraft will examine the comet up close with its suite of 11 instruments. During the landing phase, the orbiter will release the Philae lander which carries an onboard suite of 10 instruments for imaging and sampling the comet’s nucleus. The mission will track the comet through perihelion, its closest approach to the sun, examining its behavior before, during and after.
Providing an introductory retrospective of comets, sometimes regarded as harbingers of doom, Prof. Madigan discusses this historic mission, a mission that includes study of the comet from the surface of its nucleus!
This public event was hosted at the Ross School (East Hampton, NY) by the Montauk Observatory on September 18th, 2014.
F3-Sc-C9.pptx
The document discusses the structure and composition of the Sun. It describes the three main layers of the Sun - the photosphere, chromosphere, and corona. The photosphere is the visible surface and is about 400km thick with a temperature of 6000°C. The chromosphere is about 9600km thick and has a temperature of 15,000°C. The corona has a temperature of over 2,000,000°C. The core of the Sun is over 15,000,000°C and is where hydrogen is fused into helium, releasing energy that powers the Sun.
Jupiter info.ppt
Jupiter is the largest planet in the Solar System and is over 11 times the diameter of Earth. It has been extensively studied by spacecraft such as Pioneer, Voyager, Galileo, and Cassini. These missions have provided insights into Jupiter's atmosphere, internal structure, and climate. A notable event was the collision of Comet Shoemaker-Levy 9 with Jupiter in 1994, which was observed by Galileo and provided an opportunity to study Jupiter's atmosphere.
Sofia astronomy
NASA operates SOFIA, the Stratospheric Observatory for Infrared Astronomy, which is a modified Boeing 747SP aircraft carrying a 106-inch infrared telescope. Astronomers use SOFIA to study star birth and death, planet formation, molecules in space, planets and asteroids in our solar system, galaxies, black holes, and more. SOFIA builds on a history of airborne astronomy at NASA dating back to 1965, allowing astronomers to make observations above the atmosphere and upgrade instruments.
ADITYA-L1 MISSION THE FIRST OBSERVATORY-CLASS SPACE-BASED SOLAR MISSION FROM ...
Our Sun is the nearest star and the
largest object in the solar system. The
estimated age of sun is about 4.5 billion
years. It is a hot glowing ball of hydrogen
and helium gases. The distance to the
sun from the earth is about 150 million
kilometres, and is the source of energy
for our solar system. Without the solar
energy the life on earth, as we know, can
not exist. The gravity of the sun holds all
the objects of the solar system together.
At the central region of the sun, known
as ‘core’, the temperature can reach as
high as 15 million degree Celsius. At this
temperature, a process called nuclear
fusion takes place in the core which
powers the sun. The visible surface of the
sun known as photosphere is relatively
cool and has temperature of about
5,500°C.
Solar Dynamics Observatory_June 2010
The document summarizes information about NASA's Solar Dynamics Observatory (SDO) satellite mission to study the sun. SDO was launched in 2010 and uses high-resolution instruments to observe the sun's atmosphere, magnetic field, and irradiance. It aims to improve understanding of the sun's influence on space weather and the solar cycle. SDO provides images every minute that are 10 times clearer than previous satellites and help scientists monitor solar activity and eruptions.
Orion
The document summarizes NASA's Orion spacecraft and its Exploration Mission-1 (EM-1) test flight. Some key points:
- Orion will take astronauts farther into space than ever before, including to asteroids and Mars. It is designed to transport crew to and from the International Space Station and facilitate deep space exploration for decades.
- EM-1 will launch Orion on NASA's new Space Launch System rocket and send it around the moon without crew to test the spacecraft. The mission will deploy several small satellites and help check Orion's performance.
- Orion consists of crew, service, and launch abort modules and can carry more astronauts than Apollo. Its first uncrewed test flight was successful in 2014. Future missions will
Mercury
Mercury is the planet closest to the Sun. It has a diameter of 4,878 km and rotates slowly, completing one rotation every 58.65 days. Mercury has a very thin atmosphere composed primarily of oxygen, sodium, potassium, and hydrogen. The MESSENGER spacecraft orbited Mercury from 2011-2015, obtaining high-resolution images and measurements of the planet's composition, geology, gravity field, magnetic field, and exosphere. MESSENGER's observations revealed that Mercury has an iron-rich core making up about 75% of the planet's radius and a complex geological history marked by volcanic activity and planetary contraction.
29sept03 notes
This document discusses different types of spacecraft and space missions used to explore the solar system. It describes flyby missions like Voyager that pass by planets to study them without entering orbit. Orbiter spacecraft like Galileo are designed to enter a planet's orbit to study it up close for an extended period. Atmospheric probes and landers allow studying a planet's surface and atmosphere. Future technologies like ion propulsion could enable slower but more fuel efficient missions. Successfully exploring the solar system requires careful planning of spacecraft design, trajectories, and within budget constraints that can exceed $100 million per mission.
What Is ISRO Mission - Google Docs.pdf
The first Solar Mission, Aditya-L1, was successfully launched by the Indian Space Research Organization (ISRO) recently.PSLV-C57 rocket was used for the launch. A first in ISRO’s history, the fourth stage of the PSLV was fired twice to perfectly place the spacecraft into its elliptical orbit.
Spp sweap nes_osa_oct2011
The document discusses the Solar Wind Electrons, Alphas, and Protons (SWEAP) instrument suite aboard the Solar Probe Plus mission. SWEAP will make detailed measurements of solar wind particles to help solve mysteries like why the solar corona is so much hotter than the surface and how the solar wind is accelerated. Key measurements include particle velocities, densities, temperatures, and anisotropies to better understand kinetic physics processes and trace the flow of energy in the solar atmosphere.
webb bhaiya.pptx
The document provides information about the James Webb Space Telescope (JWST). It discusses that JWST is the largest and most powerful space telescope ever built, allowing scientists to observe the first galaxies formed after the Big Bang. It also notes that JWST had to fold up origami-style to fit inside the rocket during launch. Additionally, the document summarizes that JWST operates at the Sun-Earth L2 Lagrange point to keep its temperature stable for infrared observations.
AAS National Conference 2008: Andy Cheng
Session 2: Space Science – the Next Decade
18 November 2008, Pasadena California
http://www.astronautical.org/conference/conference-2008
Determination of Solar Rotation
Hello, I am Subhajit Pramanick. I and my classmate, Shivani Gupta, both presented this ppt in seminar of our university, Banaras Hindu University. Here it is the experiment how to determine Synodic and Sidereal time period of rotation of the Sun by tracing Sun spots. This presentation consists both the theory as well as experiment part. We hope you will all enjoy by reading this presentation. Thank you.
Galaxy forum vienna_2018_cv1
This document discusses the history and potential future of astronomy from the Moon. It outlines how the Moon provides opportunities for astronomy due to its lack of atmosphere and long lunar days. Telescopes on the Apollo missions and Chang'e 3 lander took some early ultraviolet images from the Moon. The document argues that an observatory on the far side of the Moon could benefit from radio quiet skies and that the low gravity would allow for lighter telescope structures. It compares this to how satellites revolutionized astronomy and suggests space-based interferometry and gravitational wave detection as potential future areas for lunar astronomy.
Artsun02hi
The document is a collection of images from NASA's Solar and Heliospheric Observatory (SOHO) spacecraft, along with brief captions describing each image. The images show various phenomena on the sun's surface and atmosphere such as solar prominences, the corona, coronal mass ejections, sunspots, and oscillations within the sun's interior. They demonstrate what the sun looks like in different wavelengths of light beyond the visible spectrum.
ADITYA-L1 MISSION
Aditya-L1 is the first space-based observatory-class Indian
solar mission to study the Sun. The spacecraft is planned to be
placed in a halo orbit around the Lagrangian point1 (L1) of the
Sun-Earth system, which is about 1.5 million km from the Earth.
A satellite placed in the halo orbit around the L1 point has
the major advantage of continuously viewing the Sun without any
occultation/eclipse. This will provide a greater advantage of
observing the solar activities continuously.
The spacecraft will carry seven payloads to observe the
photosphere, chromosphere, and the outermost layers of the Sun
(the corona) using electromagnetic and particle detectors.
Using the special vantage point of L1, four payloads will directly
view the Sun and the remaining three payloads will carry out
in-situ studies of particles and fields at the Lagrange point L1.
The suit of Aditya L1 payloads are expected to provide most
crucial information to understand the problems of coronal heating,
Coronal Mass Ejection, pre-flare and flare activities, and their
characteristics, dynamics of space weather, study of the
propagation of particles, fields in the interplanetary medium, etc
Astronomy NC 2014
The document provides information about astronomy and the study of stars and space. It begins with an introduction to the Big Bang theory, including that all matter was once condensed in a single point about 13.8 billion years ago. It then discusses evidence for the Big Bang, including the cosmic background radiation and composition of matter in the universe. The document also covers topics like the expansion of the universe, the electromagnetic spectrum, spectroscopy, and the Doppler effect. It provides summaries of the geocentric and heliocentric models of the universe, Kepler's laws of planetary motion, and Newton's laws of gravity. Additional sections describe the structure of the sun, life cycles of stars, Earth's place in the universe, and properties of the
STEREO Science Writer's Guide
The document provides information about NASA's STEREO mission to study the sun and solar phenomena like coronal mass ejections. It includes an overview of the STEREO mission objectives, the two spacecraft and their instruments, and frequently asked questions about the mission. The goal is to obtain the first 3D stereoscopic views of the sun to better understand solar eruptions and aid in space weather forecasting, which can impact satellites, power systems and astronauts. The twin STEREO observatories will be placed in orbit on opposite sides of Earth to view the sun from different vantage points and gather data over a planned two-year mission.
MISSION TO PLANETS (CHANDRAYAAN,MAVEN,CURIOSITY,MANGALYAAN,CASSINI SOLSTICE M...
This document summarizes several planetary exploration missions. It discusses Chandrayaan-1, India's first lunar orbiter mission, and its objectives to map lunar minerals and terrain. It also discusses NASA's MAVEN and Curiosity missions to Mars, with MAVEN studying the Martian atmosphere and Curiosity analyzing samples to search for evidence of past life. Additionally, it summarizes Cassini's ongoing mission in orbit around Saturn, making discoveries about the rings and moons like Titan and Enceladus.
"""Space Science and Exploration Activities of ISAS/JAXA"" The UK-Japan 150 y...
"""Space Science and Exploration Activities of ISAS/JAXA"" The UK-Japan 150 y...ISAS_Director_Tsuneta
"""Space Science and Exploration Activities of ISAS/JAXA""
The UK-Japan 150 year anniversary Science, Technology and Innovation Symposium - Astronomy & Space Science, The Embassy of Japan in the UK, 6 December 2013"12 Perterbations.pdf
This document provides an overview of orbital perturbations and methods for modeling them. It introduces Cowell's method and Encke's method for numerically integrating the equations of motion with perturbations. It then discusses atmospheric drag as a perturbation, describing how drag causes orbits to decay over time. It provides the US Standard Atmosphere 1976 model for atmospheric density with altitude.
4 3d orbits.pdf
This document discusses coordinate systems for describing orbits in three dimensions. It introduces the geocentric equatorial frame, which uses a right-handed Cartesian coordinate system centered on Earth with axes defined by the vernal equinox and Earth's rotation. The state vector specifies an object's position and velocity in this frame using six components. Orbital elements also uniquely define orbits using six parameters and the location of the object. Coordinate transformations allow changing between the state vector and orbital element representations.
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Hello, I am Subhajit Pramanick. I and my classmate, Shivani Gupta, both presented this ppt in seminar of our university, Banaras Hindu University. Here it is the experiment how to determine Synodic and Sidereal time period of rotation of the Sun by tracing Sun spots. This presentation consists both the theory as well as experiment part. We hope you will all enjoy by reading this presentation. Thank you.
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solar mission to study the Sun. The spacecraft is planned to be
placed in a halo orbit around the Lagrangian point1 (L1) of the
Sun-Earth system, which is about 1.5 million km from the Earth.
A satellite placed in the halo orbit around the L1 point has
the major advantage of continuously viewing the Sun without any
occultation/eclipse. This will provide a greater advantage of
observing the solar activities continuously.
The spacecraft will carry seven payloads to observe the
photosphere, chromosphere, and the outermost layers of the Sun
(the corona) using electromagnetic and particle detectors.
Using the special vantage point of L1, four payloads will directly
view the Sun and the remaining three payloads will carry out
in-situ studies of particles and fields at the Lagrange point L1.
The suit of Aditya L1 payloads are expected to provide most
crucial information to understand the problems of coronal heating,
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characteristics, dynamics of space weather, study of the
propagation of particles, fields in the interplanetary medium, etc
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12 Perterbations.pdf
This document provides an overview of orbital perturbations and methods for modeling them. It introduces Cowell's method and Encke's method for numerically integrating the equations of motion with perturbations. It then discusses atmospheric drag as a perturbation, describing how drag causes orbits to decay over time. It provides the US Standard Atmosphere 1976 model for atmospheric density with altitude.
4 3d orbits.pdf
This document discusses coordinate systems for describing orbits in three dimensions. It introduces the geocentric equatorial frame, which uses a right-handed Cartesian coordinate system centered on Earth with axes defined by the vernal equinox and Earth's rotation. The state vector specifies an object's position and velocity in this frame using six components. Orbital elements also uniquely define orbits using six parameters and the location of the object. Coordinate transformations allow changing between the state vector and orbital element representations.
9 rigid body dynamics.pdf
This chapter discusses rigid body dynamics and provides the foundation for developing equations of satellite attitude dynamics. It first covers the kinematics of rigid bodies using Chasles' theorem, which states that rigid body motion can be described by the displacement of any point plus a rotation about a unique axis through that point. It then discusses the equations of translational and rotational motion by analyzing the interaction between rigid body motion and applied forces. Key concepts covered include moments of inertia, Euler's equations, kinetic energy, and different methods for describing rigid body orientation including Euler angles, yaw/pitch/roll angles, and quaternions. The chapter serves as a basis for understanding satellite attitude dynamics.
10 Sat attitude.pdf
This document discusses the torque-free motion of satellites. It shows that a spinning satellite will have stable motion only if it is oblate in shape, with the equatorial radius greater than the polar radius. Oblate spinners will have prograde precession and spin, while prolate spinners will have retrograde precession and spin. The components of angular velocity and angular momentum are derived in terms of the satellite's principal moments of inertia and Euler angles.
8 Interplanetary traj.pdf
This document discusses interplanetary trajectories and Hohmann transfers between planets. It begins by outlining Hohmann transfers, which provide the most energy-efficient method of transferring between nearly circular, coplanar orbits. It then discusses the timing of opportunities for planetary rendezvous using Hohmann transfers, which depend on the relative positions and velocities of the planets. The document covers methods for calculating delta-v requirements at planetary departure and arrival points to achieve the Hohmann transfer orbit. It also introduces non-Hohmann transfer trajectories when planetary orbits are not coplanar.
6 maneuvres.pdf
This document discusses orbital maneuvers, beginning with an introduction to impulsive maneuvers where brief rocket firings instantaneously change a spacecraft's velocity vector. It then focuses on the Hohmann transfer, the most energy-efficient maneuver for transferring between two coplanar circular orbits. A Hohmann transfer uses an elliptical orbit tangent to the two circles, requiring burns at periapsis and apoapsis to place the spacecraft onto the transfer orbit and then the target orbit. An equation is provided for calculating the angular momentum of the Hohmann transfer ellipse based on the radii of the source and target orbits.
7 relative motion.pdf
This document discusses relative motion between two orbiting spacecraft, a target and chaser. It defines a local vertical/local horizontal (LVLH) coordinate frame attached to the target spacecraft, with axes along the radial direction, local horizontal, and angular momentum direction. Equations are provided to calculate the relative position, velocity, and acceleration of the chaser in this frame based on the states of both spacecraft in an inertial frame. An example problem applies these equations to calculate the relative motion between two spacecraft in slightly different elliptical orbits.
3 position by time.pdf
This document discusses how to determine the position of an orbiting body as a function of time for different orbit types. It introduces Kepler's equation, which relates the true anomaly to time through integrals that must be solved iteratively. For elliptical orbits, Kepler's equation leads to the definition of mean anomaly as a function of true anomaly. The mean anomaly is directly proportional to time through the mean motion. Eccentric anomaly is also introduced to simplify expressions relating true anomaly to time.
5 prelim determination.pdf
- The Gibbs method determines orbital elements from three position vectors of an object.
- It utilizes the fact that the position vectors must lie in the same orbital plane, defined by the angular momentum vector.
- Equations relating the position vectors and angular momentum allow solving for the angular momentum magnitude.
- Knowing the angular momentum vector and magnitude allows determining the velocities at the three observation times from the position vectors using basic orbital mechanics equations.
11 rocket dyanmics.pdf
This document discusses rocket vehicle dynamics and performance. It begins with the equations of motion for a rocket during powered ascent, accounting for thrust, drag, and gravity. It then derives the thrust equation from momentum considerations, relating thrust to propellant mass flow rate and exhaust velocity. Finally, it combines the thrust equation and equations of motion to obtain the rocket equation, which relates propellant expenditure to changes in rocket velocity (delta-v).
3 EDL.pdf
The document discusses entry, descent, and landing (EDL) for spacecraft. It covers:
1) The dynamics of atmospheric entry and re-entry, including key equations of motion.
2) Issues during EDL like deceleration, heating, and communication blackouts.
3) Methods for testing and simulating EDL, including ground and simulation testing.
The document aims to explain the EDL phase and prepare the reader to understand and analyze challenges of atmospheric entry for spacecraft.
1 Power Sys.pdf
1. The power requirements of the spacecraft loads and batteries that need to be supplied by the solar array.
2. The effects of the orbital parameters on the intensity and duration of sunlight, such as eclipse periods.
3. The degradation of the solar cell efficiency over time due to radiation damage and high temperatures in space. Accounting for this ensures the array can still produce enough power at the end of the mission lifetime.
2 Thermal Control.pdf
The document provides an overview of thermal control systems for spacecraft. It discusses passive and active thermal control systems, with passive relying on components like surface coatings and active using powered mechanisms. The document covers thermal analysis methods like conduction, convection, and radiation. It describes modeling the thermal environment from heat sources like solar radiation, planetary radiation, and albedo. Design of passive thermal control uses appropriate surface coatings to control absorptance and emittance.
59.pdf
This document discusses a lecture on space sustainability given by Professor Hugh Lewis at the University of Southampton. The lecture focuses on taking a long term view of ensuring the space environment remains usable by future generations. It includes repeated tags asking the reader to connect with the university and view a film about being connected.
48.pdf
This lecture discusses hypervelocity impacts in space. It focuses on the impact process, computational models used to simulate impacts, and ensuring the accuracy of models. Experimental facilities like light gas guns are used to test impacts and calibrate models. Results from experiments help develop empirical break-up models to better understand and predict how objects break apart during high-speed collisions in space.
50.pdf
This lecture discusses three experiments - SOCIT, DebriSat, and DebrisLV - that studied the effects of hypervelocity impacts on satellites using the light gas gun at Arnold Air Force Base. SOCIT targeted a Navy Transit satellite bus with an aluminum sphere projectile traveling at 6.1 km/s. DebriSat used a custom-built satellite and aluminum cylinder projectile impacting at 6.8 km/s. DebrisLV represented a launch vehicle stage. Diagnostic equipment measured the impact effects, and the results will be used to develop models of hypervelocity impact damage to satellites.
52.pdf
This lecture discusses re-entry predictions and risks from space debris. It covers:
1) How uncertainties in satellite characteristics and the atmosphere lead to uncertainties in re-entry predictions. Predictions are most accurate within 10 days and least accurate beyond that.
2) Methods for calculating risks to humans, including equivalent casualty cross-section and modeling debris footprint as a 2D Gaussian.
3) Long-term risks are low, estimated at 1 casualty every 45 years based on historical re-entries.
56.pdf
The lecture discusses common misconceptions about the Kessler Syndrome, a concept developed by NASA scientist Donald Kessler warning of the risk of increasing amounts of space debris. Some of the misconceptions addressed are that it would be a quick collision chain reaction, that there would be no way to stop it once started, and that it would mean an end to all space travel. The lecture presents examples of these misconceptions in media reports and research articles and aims to explain in upcoming lectures why these ideas are likely incorrect.
57.pdf
This lecture discusses techniques for calculating probabilities using combinatorics, and applies them to scenarios involving satellite collisions and drawing playing cards. Two scenarios are presented:
1) Calculating probabilities of different outcomes from 10 satellite conjunctions each with a 5% chance of collision.
2) Drawing 10 cards from a deck and calculating probabilities of different numbers of hearts. The chance of a heart on each draw is 1/4. Probabilities are calculated using combinations, multiplication of probabilities, and subtraction of complementary events.
55.pdf
(1) Donald Kessler introduced the idea of a "critical population density" of space debris in 1978 and 1991, where above this density collisions would produce debris faster than it decays.
(2) In 2001, Kessler introduced the concept of a "critical number of objects" and applied a stability model showing regions of low Earth orbit have exceeded the critical level and become unstable.
(3) Kessler's work showed the space debris population could exponentially increase without further launches if the critical threshold is surpassed, known as the "Kessler Syndrome," though this was sometimes misunderstood to mean an immediate effect rather than gradual increase.
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11
- 1. Space Environment Lecture 11 – Space Weather Observing the Sun Professor Hugh Lewis SESA3038 Space Environment
- 2. Overview of lecture 11 • In this lecture we will take a brief look at some of the spacecraft that have been used to observe the Sun. These include: – The SOHO spacecraft – The STEREO spacecraft • I am not expecting you to learn the information in this lecture, but some familiarity with the types of instruments and the types of orbit used for these space missions will be useful. Space Environment – Space Weather
- 3. Understanding the Sun Space Environment – Space Weather Solar and Heliospheric Observatory (SOHO) • Launched 2 December 1995 (2 year design lifetime) • 1850 kg mass at launch, built by Matra Marconi - now Airbus Defence & Space – at a cost of 1 billion euro • Science objectives: • What is the structure and dynamics of the solar interior? • Why does the solar corona exist and how is it heated (to ~1,000,000 °C) • Where is the solar wind produced and how is it accelerated?
- 4. Understanding the Sun Space Environment – Space Weather Solar and Heliospheric Observatory (SOHO) • Coronal Diagnostic Spectrometer (CDS) • Charge, Element and Isotope Analysis System (CELIAS) • Comprehensive Suprathermal and Energetic Particle Analyzer (COSTEP) • Extreme ultraviolet Imaging Telescope (EIT) • Energetic and Relativistic Nuclei and Electron experiment (ERNE) • Global Oscillations at Low Frequencies (GOLF) • Large Angle and Spectrometric Coronograph (LASCO)
- 5. Understanding the Sun Space Environment – Space Weather Solar and Heliospheric Observatory (SOHO) • Michelson Doppler Imager/Solar Oscillations Investigation (MDI/DOI) • Solar Ultraviolet Measurements of Emitted Radiation (SUMER) • Solar Wind Anisotropies (SWAN) • UltraViolet Coronograph Spectrometer (UVCS) • Variability of Solar Irradiance and Gravity Oscillations (VIRGO)
- 6. Understanding the Sun Space Environment – Space Weather SOHO orbit: HALO orbit: periodic, three- dimensional orbit near the L1, L2 or L3 Lagrange points
- 7. Understanding the Sun Space Environment – Space Weather SOHO: latest imagery (3rd February 2021) LASCO C2 LASCO C3 https://www.spaceweatherlive.com/en/solar-activity/solar-images/soho.html
- 8. Solar Terrestrial Relations Observatory Launched October 2006 Understanding the Sun Space Environment – Space Weather
- 9. Understanding the Sun Space Environment – Space Weather Solar Terrestrial Relations Observatory
- 10. Understanding the Sun Space Environment – Space Weather Other solar observatories • ACE: Advanced Composition Explorer • Launch: 25 August 1997 • Sufficient propellant to maintain orbit at L1 until ~2024 • SDO: Solar Dynamics Observatory • Launch: 11 February 2010 • 3000 kg (1400 kg propellant) • Solar Orbiter • Launch: 6 February 2020 • 0.28 AU closest perihelion • 7-year nominal mission duration
- 11. Understanding the Sun Space Environment – Space Weather Other solar observatories • DSCOVR: Deep Space Climate Observatory • Launch: 11 February 2015 • Real-time solar wind monitoring • 570 kg launch mass • Three primary instruments
- 12. Understanding the Sun Space Environment – Space Weather Other solar observatories • Parker Solar Probe • Launch: 18 August 2018 • Understanding the Sun’s atmosphere: – How energy and heat move through the solar corona – How the solar wind is accelerated • 685 kg launch mass • Cost $1.5 billion • Four primary instruments behind a 11.3 cm thick carbon composite shield • 4th solar encounter January 2020 at 37.3 million km (will get as close as 6.1 million km)