Target asteroid detect

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Sensor

MIR detector

Observation of ballistic avalanche phenomena in nanoscale vertical InSe/BP heterostructures

• https://www.nature.com/articles/s41565-018-0348-z
  • Observation of ballistic avalanche phenomena in nanoscale vertical InSe-BP heterostructures, NJU, gao2019.pdf
  • https://mp.weixin.qq.com/s/_jhYHnDQz9TVS7uAsMInJw

Land observer

Space observer

Direct probe

Overview #3

Conference

• 15th International Planetary Probe Workshop, IPPW15, 2018
  • Short Course - Small Satellites: An Emerging Paradigm for Bold Planetary Exploration
• Science and Technology Progress Report on Planetary Probes, 14th International Planetary Probe Workshop The Hague, The Netherlands, 2017
• https://icubesat.org/

Web portal

• Small Spacecraft Virtual Institute
• State of the Art of Small Spacecraft Technology

Tools

• Space Mission Design Tools index in Small Spacecraft Virtual Institute, NASA
• NASA Ames Web-based Trajectory Generation Tool
• The Astrogator's Guild, guide on STK for trajectory design
• Evolutionary Mission Trajectory Generator (EMTG), NASA, Goddard

General

• Space Travel on a Shoestring- CubeSat Beyond LEO, Vasile, 2016
  • https://www.stardust2013.eu/

Type of mission

• Space rendezvous
• Flyby
• Landing
• Sample return

Term and technical concept

• Orbital maneuver
• Oberth effect
• Gravity assist, CN, further explain in Chinese

飞掠 伴飞 附着 采样返回

Rosetta and Philae by ESA

Rosetta was a space probe built by the European Space Agency launched on 2 March 2004. Along with Philae, its lander module, Rosetta performed a detailed study of comet 67P/Churyumov–Gerasimenko (67P).[8][9]

• 2.8 × 2.1 × 2.0 m central frame and aluminium honeycomb platform

• ~3,000 kg, which included the 100 kg (220 lb) Philae lander and 165 kg (364 lb) of science instruments

• communications suite

  • 2.2 m steerable high-gain parabolic dish antenna
  • a 0.8 m fixed-position medium-gain antenna
  • two omnidirectional low-gain antennas.[51]

• two solar arrays totalling 64 square metres

  • Each one was subdivided into five solar panels
  • each panel being 2.25 × 2.736 m
    • individual solar cells were made of silicon, 200 μm thick, and 61.95 × 37.75 mm

• maximum of approximately 1,500 watts at perihelion

• minimum of 400 watts in hibernation mode at 5.2 AU

• 850 watts when comet operations begin at 3.4 AU

• a redundant Terma power module also used in the Mars Express spacecraft,[54][55] and was stored in four 10-A·h NiCd batteries supplying 28 volts to the bus.[51]

Main propulsion comprised 24 paired bipropellant 10 N thrusters,[52] with four pairs of thrusters being used for delta-v burns.

• The spacecraft carried 1,719.1 kg (3,790 lb) of propellant at launch:

  • 659.6 kg of monomethylhydrazine fuel
  • 1,059.5 kg of dinitrogen tetroxide oxidiser,
  • contained in two 1,108-litre grade 5 titanium alloy tanks and providing delta-v of at least 2,300 metres per second (7,500 ft/s) over the course of the mission. Propellant pressurisation was provided by two 68-litre (15 imp gal; 18 US gal) high-pressure helium tanks.[56]

• https://en.wikipedia.org/wiki/Rosetta_(spacecraft)

  • https://en.wikipedia.org/wiki/Philae_(spacecraft)

Hayabusa2

• Hayabusa2 section in this page

IKAROS

• Overview of IKAROS in ESA
• Overview of IKAROS in JAXA
• Direct Exploration of Jupiter Trojan Asteroid using Solar Power Sail

Attachments

• Direct Exploration of Jupiter Trojan Asteroid using Solar Power Sail_17087_Slide_Dr. Osamu Mori.pdf

[Uploading Evolutionary Mission Trajectory Generator (EMTG), NASA, Goddard_EMTGv8.zip…]()

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the Hayabusa series from JAXA

Operation Status of Ion Engines of Asteroid Explorer Hayabusa2, JAXA, 2016

Hayabusa

Hayabusa2

• http://www.hayabusa2.jaxa.jp/en/enjoy/material/factsheet/FactSheet_en_v2.31s.pdf

• http://www.issfd.org/ISSFD_2014/ISSFD24_Paper_S12-2_Canalias.pdf

MASCOT

• https://www.colorado.edu/event/ippw2018/sites/default/files/attached-files/20_-_biele_mascot_ippw2018.pdf

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IKAROS

https://en.wikipedia.org/wiki/OKEANOS

• Direct Exploration of Jupiter Trojan Asteroid using Solar Power Sail

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Asteroid Probe Survey

Device	Hayabusa	Hayabusa2	Akatsuki	IKAROS	OKEANOS	OSIRIS-REx	MarCO	Dawn	Stardust
Cost		$144.6M				$800M		$446M
Weight							13.5kg	1,217.7 kg
Propulsion							Cold gas/Reaction	3 of 90mN
Electric								10kW
Vis Cam			LAC
NIR Cam			1, 2um
MIR Cam
LIR Cam			10um
UV Cam			293-365nm
Lidar
Radar
Sampling
Rover
Target			Venus
Aim			Atmosphere

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Basic facts

the minimum radius of turn, while:

• with Pulsed Plasma Thruster (PPT)@10mN
• weight = 10kg
• v = 10km/s

Proposal of target probes

orbit to turn around to target trajectory?

• EP, ~10kg
• Exposive boost to release the rover (?
• cold gas propelle to finally landing

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• Chang'e 2 Flyby of Toutatis, CAS, DC, 2013

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全国空间轨道设计竞赛总结

• 第四届全国空间轨道设计竞赛研讨会”征文通知
• http://www.nssc.cas.cn/wxzygx/weixin/201607/P020160718380097592858.pdf
• http://www.nssc.ac.cn/wxzygx/weixin/201607/P020160718380098022460.pdf

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NEA Scout

• https://www.nasa.gov/content/nea-scout
  • https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20190030404.pdf
  • https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20180003091.pdf

• https://ntrs.nasa.gov/api/citations/20180001124/downloads/20180001124.pdf
  • Solar Torque Management for the Near Earth Asteroid (NEA) Scout CubeSat Using Center of Mass Position Control, AIAA SciTech 2018
• https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20170012413.pdf
• https://ntrs.nasa.gov/api/citations/20140004799/downloads/20140004799.pdf

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Miniaturised Asteroid Remote Geophysical Observer (M-ARGO), ESA

• https://www.esa.int/ESA_Multimedia/Images/2017/06/M_Argo
• https://www.colorado.edu/event/ippw2018/sites/default/files/attached-files/smallprobes_4_ippw_2018_m-argo_a_stand-alone_deep_space_cubesat_system_for_low-cost_science_and_exploration_missions_conference_final.pdf
  • smallprobes_4_ippw_2018_m-argo_a_stand-alone_deep_space_cubesat_system_for_low-cost_science_and_exploration_missions_conference_final.pdf