Paper summaries

[NirViaje]

Papers

short URL for this page - https://git.io/fpAk3

Target asteroids #3

1. [ ] https://github.com/ExponentialDeepSpace/exponentialdeepspace.github.io/issues/35#issuecomment-443314506 How to find metal-rich asteroids, 2014, German Aerospace Center
2. [ ] https://www.google.com/search?q=asteroid+delivery+efficiency
3. [ ] #34 https://www.google.com/search?q=asteroid+rotation+axis

Solar funace #5

4. [x] https://github.com/ExponentialDeepSpace/exponentialdeepspace.github.io/issues/35#issuecomment-444948647 Vasile, Solar Deflection
5. [ ] https://github.com/ExponentialDeepSpace/exponentialdeepspace.github.io/issues/35#issuecomment-445857015 film lens: MOIRE/MOD-EnMat, etc
6. [ ] https://github.com/ExponentialDeepSpace/exponentialdeepspace.github.io/issues/35#issuecomment-448868540 Solar pumped laser
7. [ ] DoE Solar

Target probe #25

7. [x] https://github.com/ExponentialDeepSpace/exponentialdeepspace.github.io/issues/35#issuecomment-445441798 MarCO HGA
8. [ ] https://github.com/ExponentialDeepSpace/exponentialdeepspace.github.io/issues/35#issuecomment-445879704 JAXA solar probe
9. [ ] https://github.com/ExponentialDeepSpace/exponentialdeepspace.github.io/issues/35#issuecomment-447696268 Cubesat for deep space
10. [ ] https://github.com/ExponentialDeepSpace/exponentialdeepspace.github.io/issues/35#issuecomment-448755568 Celestial navigation for Cubesat, commercialized cubesat ecology like BCT

Electric propulsion and other methods of propulsion #9

9. [x] https://github.com/ExponentialDeepSpace/eds-archive/issues/3 Pulsed Plasma Thruster (PPT)
10. [ ] https://github.com/ExponentialDeepSpace/eds-archive/issues/2 Magneto Plasma Dynamic (MPD) thruster (MPDT), Pulsed Inductive Thruster (PIT), Electrodeless Lorentz Force Thruster (ELF)
11. [ ] https://github.com/ExponentialDeepSpace/exponentialdeepspace.github.io/issues/35#issuecomment-445876939 MEMS Thruster
12. [ ] https://github.com/ExponentialDeepSpace/exponentialdeepspace.github.io/issues/35#issuecomment-445942591 Cold gas

Other

14. [ ] https://github.com/ExponentialDeepSpace/exponentialdeepspace.github.io/issues/35#issuecomment-445877728 1982Lunar #10
15. [x] film solar cell #21

[NirViaje]

HOW TO FIND METAL-RICH ASTEROIDS

Alan W. Harris and Line Drube German Aerospace Center (DLR) Institute of Planetary Research, Rutherfordstrasse 2, D-12489 Berlin, Germany; alan.harris@dlr.de Received 2014 February 3; accepted 2014 March 8; published 2014 March 24

https://www.researchgate.net/publication/261034084_How_to_find_metal-rich_asteroids

The Near-Earth Asteroid Thermal Model (NEATM; Harris 1998), based on spherical geometry, offers a relatively straightforward means of deriving reasonably accurate diameters and albedos of asteroids and trans-Neptunian objects (in principle all atmosphereless bodies) from thermal-infrared data for objects with unknown physical characteristics. With NEOs in mind, the NEATM was designed to extend the applicability of the thermal model concept described by Lebofsky et al. (1986) to objects with significant thermal inertia and/or rapid rotation. The model incorporates a fitting parameter, η, referred to for historical reasons as the beaming parameter, which allows the model surface temperature distribution to be adjusted to take account of the effects of thermal inertia, spin vector, and surface roughness, thereby giving a better fit of the model fluxes to the measurements.

NEO	Tax.	PHA?	D(km)	pv	η	ηerr	pIR
138359		N	1.09	0.10	2.931	0.105	0.19
1865	S	N	1.61	0.14	2.902	0.036	0.27
152931	Q	N	1.65	0.24	2.884	0.138	0.24
152978	S:	Y	0.53	0.11	2.641	0.116	0.19
365071		Y	0.87	0.15	2.559	0.117	0.28
3554	X, M, D	N	3.05	0.09	2.411	0.072	0.19
215442		N	0.79	0.15	2.328	0.325	0.17
152558	S	N	1.36	0.18	2.284	0.051	0.28
366774	AS	Y	0.86	0.20	2.284	0.059	0.29
250680		Y	0.40	0.15	2.279	0.075	0.30
7822	S	Y	1.21	0.13	2.261	0.049	0.30
163243	S, Q	Y	1.68	0.17	2.191	0.061	0.23
263976	L	Y	0.79	0.13	2.165	0.043	0.18
142464		N	0.89	0.12	2.139	0.044	0.22
2002 NW16		N	0.85	0.16	2.118	0.066	0.26
103067	S	Y	1.28	0.25	2.114	0.056	0.29
363024		Y	0.56	0.10	2.055	0.067	0.24
325102		N	0.36	0.12	2.048	0.063	0.18

[NirViaje]

Vasile, Solar Deflection

• Light Touch2 : Effective Solutions to Asteroid Manipulation, ESA General Studies Programme

  • Designs of multi-spacecraft swarms for the deflection of Apophis by solar sublimation , Massimiliano Vasile, 2009

  • Physical limits of solar collectors in deflecting Earth-threatening asteroids

  • On the deflection of asteroids with mirrors, Massimiliano Vasile, Christie Alisa Maddock, ESA, 2011

  • Hazardous asteroid mitigation: Campaign planning and credibility analysis, thesis, Yohei Sugimoto, 2014

• Vasile, Massimiliano and Maddock, Christie (2012) Design of a formation of solar pumped lasers for asteroid deflection
  • LASER BEES: A Concept for Asteroid Deflection & Hazard Mitigation
  • https://en.wikipedia.org/wiki/Solar-pumped_laser

De-Starlite from UCSB

• http://www.deepspace.ucsb.edu/projects/directed-energy-planetary-defense
• [de-starlite] Directed Energy Missions for Planetary Defense, UCSB, 2014
• Effective Planetary Defense using Directed Energy DE-STARLITE, Philip Lubin, UCSB, 2015

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Publication: Massimiliano Vasile https://www.google.com.hk/search?q=Vasile+asteroid https://www.youtube.com/watch?v=mOtIwp86rF0 Vasile-solar-deflection Hazardous asteroid mitigation- Campaign planning and credibility analysis, thesis, Yohei Sugimoto, 2014_2014sugimotophd.pdf

[NirViaje]

Hodges, Richard E. (21 February 2017). "A Deployable High-Gain Antenna Bound for Mars: Developing a New Folded-panel Reflectarray for the First CubeSat Mission to Mars". IEEE Antennas and Propagation Magazine. 59: 39–49. doi:10.1109/MAP.2017.2655561 – via IEEE Xplore Digital Library.

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On board the two CubeSats is an ultra-high frequency (UHF) antenna which is circularly polarized. The EDL information from InSight was transmitted through the UHF band at 8 kbit/s to the CubeSats, and was simultaneously retransmitted at an X band frequency at 8 kbit/s to Earth.[18] MarCO used a deployable solar panel for power, but because of the limitations in solar panel efficiency, the power for the X-band frequency can only be about 5 watts.

In order for the CubeSats to be able to relay information, they need to have a high gain antenna (HGA) which is reliable, meets the mass specs, has low complexity, and is affordable to build. A high gain antenna is one that has a focused, narrow radiowave beam width (directional antenna). Three possible types of antennas were assessed: a standard microstrip patch antenna, a reflectarray, and a mesh reflector. With the small, flat, size required for the CubeSats, the reflectarray antenna type met all of the mission needs. The components of a reflectarray HGA are three folded panels, a root hinge which connects the wings to the body of the CubeSat, four wing hinges, and a burn wire release mechanism. The antenna panels must be able to withstand a varying degree of temperature changes throughout the mission as well as vibrations throughout deployment.[18] MarCO relayed EDL-critical data 8 minutes after the completion of the landing.[19][20]

https://en.wikipedia.org/wiki/Mars_Cube_One#Relay

IRIS Radio

• https://www.jpl.nasa.gov/cubesat/missions/iris.php
  • https://www.sdl.usu.edu/downloads/iris.pdf
  • https://www.jpl.nasa.gov/cubesat/pdf/Brochure_IrisV2.1_201611-URS_Approved_CL16-5469.pdf
• Iris (Deep-space radio for CubeSat missions) for SLS EM-1
  • M. Michael Kobayashi, "Iris Deep-Space Transponder for SLS EM-1 CubeSat Missions," Proceedings of the 31st Annual AIAA/USU Conference on Small Satellites, Logan UT, USA, Aug. 5-10, 2017
  • Courtney B. Duncan, Amy E. Smith, Fernando H. Aguirre, "Iris Transponder – Communications and Navigation for Deep Space," Proceedings of the 28th Annual AIAA/USU Conference on Small Satellites, Logan, Utah, USA, August 2-7, 2014

• https://www.jpl.nasa.gov/cubesat/missions/inspire.php

[NirViaje]

Optical membrane

Membrane optics is a flat lens that employs plastic in place of glass to diffract rather than reflect or refract light. Concentric microscopic grooves etched into the plastic provide the diffraction.[1]

Glass transmits light with 90% efficiency, while membrane efficiencies range from 30-55%. Membrane thickness is on the order of that of plastic wrap.[1]

• https://en.wikipedia.org/wiki/Optical_membrane
• Membrane Optical Imager for Real-Time Exploitation (MOIRE)

Diffractive Fresnel Lens

• nautilus-array,
• Multiple Order Diffractive Fresnel Lens (MOD-DFL) for Atmospheric Transit Surveying of Earthlike Exoplanets, 2017
• 微结构薄膜望远镜研究进展分析, CAS, 2017

[NirViaje]

• https://github.com/ExponentialDeepSpace/eds-archive/issues/3

[NirViaje]

• https://github.com/ExponentialDeepSpace/eds-archive/issues/2

[NirViaje]

MEMS Thruster

• MEMS Mega-pixel Micro-thruster Arrays for Small Satellite Stationkeeping, EPPDyL, 2000

• In-Orbit Demonstration of a MEMS-based Micropropulsion System for Cubesats, Sweden and CAS, 2015

• https://alfven.princeton.edu/research/past/mems

• [Catalytic Porous Microchannel for Hydrogen Peroxide MEMS Thruster, Koji Takahashi, Kyushu University, 2006](http://www.aero.kyushu-u.ac.jp/aml/MEMS/article4.pdf

• https://www.google.com/search?q=mems+thruster

[NirViaje]

NASA Lunar 1982

[NirViaje]

IKAROS

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

• Direct Exploration of Jupiter Trojan Asteroid using Solar Power Sail

[NirViaje]

Propellant: R134a and R236fa

• CubeSat High Impulse Propulsion System (CHIPS) July 2018

• https://ssed.gsfc.nasa.gov/pcsi/docs/2017/presentations/013-2017-Presentation-SoA-for-Small-Sat-Prop-Systems.pdf

[NirViaje]

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[NirViaje]

Cubesat for deep space

Cubesat for the moon

• CubeSat Lunar Mission Using a Miniature Ion Thruster, MiXI, 2011
• Interplanetary High Reliability CubeSat Software with SPARK/Ada
• http://wirzresearchgroup.com/plasma
• Interplanetary High Reliability CubeSat Software with SPARK/Ada, Vermont Technical College, 2013
• http://www.cubesatlab.org/

Lunar IceCube

• https://en.wikipedia.org/wiki/Lunar_IceCube

• Broadband InfraRed Compact High-resolution Exploration Spectrometer: Lunar Volatile Dynamics for the Lunar Ice Cube Mission, JPL, 2016
• https://cubesats.gsfc.nasa.gov/

Xe

液体密度：3057kg·m⁻³(-108.10℃，101.325kpa) 储罐压力：30MPa

Nanosat fleet proposed to 300 asteroids

• http://www.europlanet-society.org/nanosat-fleet-proposed-to-300-asteroids/

• Flyby of 300 main belt asteroids by nanosat fleet using singletether electric sails, Finland, 2017
• https://presentations.copernicus.org/EPSC2017-215_presentation.pdf
• http://www.electric-sailing.fi/

• Asteroid Touring Nanosatellite Fleet, MIT, 2018

Mission details

• The reference mission contains 50 identical CubeSats
• Estimated total cost <100 million USD
• Each to visit 6 targets on average
• 100 km – 1000 km flybys
• Total of 300 visits during 3.2 years
• Even if 50% are successful, number of visited asteroids would increase by a factor of 10
• First published concept from Finnish Meteorological Institute (Pekka Janhunen et al, “Asteroid touring nanosat fleet with single-tether Esails”, 2017)

A single MAT nanospacecraft

• Multispectral telescope
  • ~230 mm focal length
  • Coaxial Startracker/framing camera
  • Visual FPA + MIR FPA
  • 1-5 μm TACHYON 6400 Uncooled PbS
  • 0.3-1 μm IMX264 as reference
• Solar cell array
  • ~40 W peak at 1 AU
  • Contains E-sail module and remote unit
  • Reaction wheels
• Remote unit ~1 kg Deployed spacecraft
  • Independent propulsion
• Main spacecraft ~4 kg
  • Electrospray propulsion (Accion Systems TILE as reference)
  • for spin-up and course correction
  • Electron guns for charging
  • Centrifugally deployed aluminum tether,
  • 20 km long (0.2 kg), charged to 20 kV
• Mass: 5-6 kg

• Nanospacecraft Fleet for Multi-asteroid Touring with Electric Solar Wind Sails, Finland, MIT, JHU, 2018

[NirViaje]

Celestial navigation and deep space orbit for Cubesat

• https://scienceandtechnology.jpl.nasa.gov/research/research-topics-list/communications-computing-software/deep-space-navigation
• https://descanso.jpl.nasa.gov/evolution/evolution.html

Commercialized CubeSat ecology

BCT

• https://www.colorado.edu/event/ippw2018/sites/default/files/attached-files/15_-_ippw_adcs_-_dan_hegel.pdf
• https://www.sprsa.org/sites/default/files/presentations/Hegel%20-%20Spacecraft%20Design%20and%20Enablers%20for%20Express-class%20Missions.pdf
• https://cubesats.gsfc.nasa.gov/symposiums/2018/presentations/Day2/1115_Hegel.pdf

[NirViaje]

Solar-pumped laser

• https://github.com/ExponentialDeepSpace/eds-archive/issues/15