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a aThis lecture discusses in-situ measurements of space debris. It describes missions like LDEF, Hubble, the International Space Station, and Space Shuttle that have enabled the collection of in-situ data on space debris. Examples are provided of impacts on these structures from debris. Estimates of small debris, like micrometer-sized particles, are also presented.
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This lecture discusses the impacts of space debris on spacecraft operations. It provides data on historical close approaches and collision avoidance maneuvers performed by NASA, ESA, CNES, and private company Capella Space spacecraft. The number of close approaches requiring maneuvers has grown over time, particularly following major breakup events. For example, the number of high-risk conjunctions for ESA spacecraft doubled on average after the 2009 Iridium-Cosmos collision. Even small satellites like Capella-1 have performed maneuvers to avoid debris.
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This document provides an overview of four lectures on space debris that will examine the current state of the orbital debris environment. It will look at the number and mass of objects in orbit, as well as their distribution, using data from NASA, ESA and other sources. The lectures will also explore the history of space launches and fragmentations and how the debris population has evolved over time. Current estimates indicate there are over 34,000 pieces of debris larger than 10 cm in size, around 900,000 pieces between 1 cm and 10 cm, and approximately 128 million pieces between 1 mm and 1 cm. The total mass of all orbital debris is around 9,200 tonnes.
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This lecture discusses space debris, focusing on three significant hypervelocity collision events - the Fengyun 1C ASAT test in 2007, the Iridium 33-Cosmos 2251 collision in 2009, and the Microsat-R ASAT test in 2019. The consequences of these events in increasing space debris in low Earth orbit are examined. The lecture also reviews the top 50 debris-producing objects in history and how these high-profile collisions have impacted the space environment.
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as a destination for both robotic and human space exploration
• Multiple nations are now pursuing both robotic exploration programs with spacecraft in
lunar orbit and landers on the lunar surface.
• In addition to these purely robotic exploration programs, NASA has started construction
of the Gateway space station for operations in lunar orbit and development work has
begun on the Human Landing System infrastructure which promises to return humans to
the lunar surface for the first time since the last Apollo missions in the 1970’s.
• Because the Moon has very little atmosphere and no strong intrinsic magnetic field to
protect the surface from meteoroid impacts and charge particles, respectively, the space
environments that need to be considered when designing and operating lunar
exploration missions are essentially the free-field environments used in design of
interplanetary missions
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• Atmosphere
• Lunar regolith and dust
• Illumination and thermal
• Solar UV/EUV
• Ionizing radiation
o GCR
o SPE
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• Space plasma and charging
• Meteoroid environments
o Primary impacts
o Ejecta
• DSNE Lunar Environments
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This document summarizes a lecture on space debris and the increasing risk of collisions. It discusses how the number of predicted close approaches between debris fragments is rising even as the number of fragments decreases over time. Data is presented on close approaches related to debris from the 2007 Fengyun-1C anti-satellite test and the 2009 Iridium-Cosmos collision. While around 27,000 close approaches under 5km were predicted per week in 2019, by 2021 that number had risen to around 46,000 per week. Similarly, close approaches under 1km rose from 1,100 to 2,400 per week. This increasing risk is likely due to the dispersing and expanding cloud of fragments over time.
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This document discusses the growing problem of space debris orbiting Earth. It defines space debris as nonfunctional human-made objects in space including defunct spacecraft and fragments from explosions. The amount of space debris is increasing and will likely be dominated by collision fragments in the future, posing a hazard to operational satellites and human spaceflight. Several proposals for active debris removal are presented, including using nets, lasers, and momentum to capture debris and deorbit them to burn up in Earth's atmosphere. International guidelines call for passive mitigation efforts but active debris removal may be necessary to reduce risks to space activities and prevent the space environment from becoming too polluted.
When did satellite communication become viable, i.e. what timeframe (.pdf
When did satellite communication become viable, i.e. what timeframe (years +-) What are some
of the restrictions in using Satellite communications? Does the mass of a satellite have any effect
on its orbit? What is geostationary orbit? How is it described and what altitude above the earth
are geostationary orbits? Extra Credit:Derive the Keller equations of motion and describe each
step in your calculations
Solution
1. First artificial sattelite launched by sovient union named sputnik 1 in 1957 but that was not
used for communication.Later on first artifical sattelite ballon named echo 1 in 1960 launched
which contained a passive reflector and used for communication.Then America launched a
advanced project named project score in1960 and bring revolution to communication sysytem.
2. There are various limitation of sattellite communication .some of are as:-
a) the main problem is with power to operate them at a distant,as now days solar enery has
developed but yet there is limitd power available.
b) receiver sensitivity-a lot of signal loss occur due to many reason like bad
weather,interface,noise which effects the signal.
c)signal by sattellite communication can be easilly traceable.
d)availability-sometime receiver cannot find the sattellite transmitter and unable to receive
signals.
3.No,mass of sattellite doent effect orbit of satteliite baecause as compared to earths mass mass
of sattellite become negligible.
4.Geo stationary orbit is a geosynchronous orbit in the plane of earths equator with a radius of
approx 42000km maesured from centre of earth.It has an orbital period of one sidereal day(23hrs
56 min 4 sec),thus it appers to be in same position as observed from eath.
5.A sattellite in geostationary orbit is approx at a height of 35000 km.
6. The square of the orbital period of a planet is proportional to the cube of the semimajor axis of
the ellipse.
T^2=KA^3
T=TIME PERIOD OF ORBIT
A=SEMI MAJOR AXIS OF ELLIPSE.
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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of the restrictions in using Satellite communications? Does the mass of a satellite have any effect
on its orbit? What is geostationary orbit? How is it described and what altitude above the earth
are geostationary orbits? Extra Credit:Derive the Keller equations of motion and describe each
step in your calculations
Solution
1. First artificial sattelite launched by sovient union named sputnik 1 in 1957 but that was not
used for communication.Later on first artifical sattelite ballon named echo 1 in 1960 launched
which contained a passive reflector and used for communication.Then America launched a
advanced project named project score in1960 and bring revolution to communication sysytem.
2. There are various limitation of sattellite communication .some of are as:-
a) the main problem is with power to operate them at a distant,as now days solar enery has
developed but yet there is limitd power available.
b) receiver sensitivity-a lot of signal loss occur due to many reason like bad
weather,interface,noise which effects the signal.
c)signal by sattellite communication can be easilly traceable.
d)availability-sometime receiver cannot find the sattellite transmitter and unable to receive
signals.
3.No,mass of sattellite doent effect orbit of satteliite baecause as compared to earths mass mass
of sattellite become negligible.
4.Geo stationary orbit is a geosynchronous orbit in the plane of earths equator with a radius of
approx 42000km maesured from centre of earth.It has an orbital period of one sidereal day(23hrs
56 min 4 sec),thus it appers to be in same position as observed from eath.
5.A sattellite in geostationary orbit is approx at a height of 35000 km.
6. The square of the orbital period of a planet is proportional to the cube of the semimajor axis of
the ellipse.
T^2=KA^3
T=TIME PERIOD OF ORBIT
A=SEMI MAJOR AXIS OF ELLIPSE.
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如果你回国在学历认证方面有以下难题请联系我们我们将竭诚为你解决认证瓶颈
1所有材料真实但资料不全无法提供完全齐整的原件。【如：成绩单丶毕业证丶回国证明等材料中有遗失的。】
2获得真实的国外最终学历学位但国外本科学历就读经历存在问题或缺陷。【如：国外本科是教育部不承认的或者是联合办学项目教育部没有备案的或者外本科没有正常毕业的。】
3学分转移联合办学等情况复杂不知道怎么整理材料的。时间紧迫自己不清楚递交流程的。
如果你是以上情况之一请联系我们我们将在第一时间内给你免费咨询相关信息。我们将帮助你整理认证所需的各种材料.帮你解决国外学历认证难题。
国外波士顿学院波士顿学院本科学位证成绩单办理方法：
1客户提供办理信息：姓名生日专业学位毕业时间等（如信息不确定可以咨询顾问：我们有专业老师帮你查询波士顿学院波士顿学院本科学位证成绩单）；
2开始安排制作波士顿学院毕业证成绩单电子图；
3波士顿学院毕业证成绩单电子版做好以后发送给您确认；
4波士顿学院毕业证成绩单电子版您确认信息无误之后安排制作成品；
5波士顿学院成品做好拍照或者视频给您确认；
6快递给客户（国内顺丰国外DHLUPS等快读邮寄）。疯一把山娃算了算这一次足足花了老爸元够他挣上半个月的山娃很不解一向节俭的父亲啥时变得如此阔绰大方大把大把掏钱时居然连眉头也不皱一下车票早买好了直达卧铺车得经过山娃老家门口山娃拒绝父亲送说往车上一躺就等着下车决无丢失的道理有手机在身联系也方便再说他都岁了还有大半车的小伙伴相伴他不怕在父亲千叮咛万嘱咐中山娃依依不舍地爬上车朝窗外不住地挥手别了父亲别了父亲的城别了我的暑假生活我的城市生活望着窗外挥舞的房
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26.pdf
- 1. Space Environment Lecture 26 – Space Debris (Vol. 1) In-situ measurements Professor Hugh Lewis SESA3038 Space Environment
- 2. Overview of lecture 26 • In this lecture we complete our look at space debris measurements, focusing on in-situ measurements – We look at how in-situ measurements help to complete our understanding of the space debris population – We look at space missions that have enabled us to gather in-situ data: – LDEF, Hubble, ISS, Space Shuttle – We also look briefly at the undesirable nature of in-situ measurements: impacts on parts of the ISS and on an ESA satellite – Finally, we see estimates of the small-size (microscopic) space debris populations Space Environment – Space Debris (Vol. 1)
- 3. Space Environment – Space Debris (Vol. 1) SSA coverage From NASA presentation to the UN COPUOS STSC Jan 2018 https://www.unoosa.org/documents/pdf/copuos/stsc/2018/tech-14E.pdf
- 4. In-situ measurements • LDEF • Hubble solar array • Sentinel 1A Space Environment – Space Debris (Vol. 1)
- 5. Space Environment – Space Debris (Vol. 1)
- 6. Space Environment – Space Debris (Vol. 1) STS-114 High Velocity Impacts on Windows
- 7. Space Environment – Space Debris (Vol. 1) Impacts on the ISS: Multi-Purpose Logistics Module
- 8. Space Environment – Space Debris (Vol. 1) Impacts on the ISS:
- 9. Space Environment – Space Debris (Vol. 1) Impacts on the ISS: https://twitter.com/cmdr_hadfield/status/328920180241596417?lang=en
- 10. Impacts on the ISS • Battery charger on the P6 truss segment of the ISS https://twitter.com/SWGlassPit/status/1228431095525519361 Space Environment – Space Debris (Vol. 1)
- 11. In-situ measurements: Space Debris Sensor • SpaceX-13, carrying resupply and NASA’s SDS, was launched to the ISS on 15 December 2017 • The SDS mission aimed to mature NASA’s in-situ measurement technologies and collect data on the sub-millimetre debris population at the ISS altitude. It failed shortly after deployment • NASA is aiming to deploy SDS above 600 km altitude to fill the data gap on the millimetre- sized debris Space Environment – Space Debris (Vol. 1)
- 12. Impacts on spacecraft • Sentinel 1A • Solar panel impact on 23 August 2016 • Affected area is ~ 40 cm in diameter • Impact on the back of the panel • Sudden small power reduction at 17:07 GMT • Small changes in orientation and orbit • Debris particle few millimetres in size • No impact on satellite operation • See: http://www.esa.int/Our_Activities/Observing_t he_Earth/Copernicus/Sentinel- 1/Copernicus_Sentinel- 1A_satellite_hit_by_space_particle Space Environment – Space Debris (Vol. 1)
- 13. Space Environment – Space Debris (Vol. 1) Potential Shuttle Damage
- 14. Size distribution Space Environment – Space Debris (Vol. 1) Graphic from “Orbital Debris: A Technical Assessment” (1995)
- 15. Overview of lectures 20 to 26 • In these lectures we have focused on the current state of the environment and how this state has emerged from historical space activity and fragmentation events. • We have introduced the space surveillance network and new commercial networks of sensors (radar and optical) • We have seen how the different sensing technologies can be used to characterise space objects (i.e. not just count them) – This characterisation provides space situational/domain awareness • Finally, we looked at how in-situ measurements help to complete our understanding of the space debris population Space Environment – Space Debris (Vol. 1)