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.p023 Musk wanted for NASA Mars plan .p025 Bezos wanted NASA Moon plan |
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.p026 Musk taunts Bezos, Blue Origin not moving fast enough . uh ... Gradatim Ferociter .p026 2013 SpaceX granted right to lease Launch Complex 39A .p027 Musk mantra focus on customers, not competitors .yet it seems Davenport focuses on a "competition" with SpaceX already the winner .p027 Amazon "Get Big Fast", compares 2016 Blue Origin 700 to (NASA funded) SpaceX with 5500 .p028 Blue Origin before 2016 bid as subcontractor, "from now go after SpaceX bids" .p029 [[ https://science.jpl.nasa.gov/people/cemiller/ | Charles Miller ]] "What can you do relative to the moon by 2020?" .p029 [[ https://afcea-la.org/wp-content/uploads/Brett-Alexander-Blue-Origin.pdf | Brett Alexander ]] .p029 "Landing on the moon was far more difficult than landing on Earth" . no, different, but easier with proper infrastructure. Earth escape energy is 63 MJ/kg, lunar escape velocity energy is 2.8 MJ/kg ... 22 times less energy to dissipate, with no atmosphere to constrain the solution. An "inverse launch loop" track could shed that lunar arrival kinetic energy in d=E/a distance; for acceleration a=20 m/s², d=140 km, time =. Decelerating a few incoming vehicles wouldn't pay for the track, but one per minute is half a million per year. <<nbsp>><<nbsp>> <<nbsp>> <<nbsp>> <<nbsp>> In detail, a Hohmann transfer orbit ellipse from Earth radius perigee 6500 km (122 km equatorial altitude) to lunar orbit radius apogee ( r = 385000 km equatorial altitude). Estimate perigee launch velocity as approximately Earth escape velocity 11.2 km/s; from conservation of angular momentum the apogee velocity is approximately (6500 km / 385000 km )*11200 m/s ≈ 190 m/s . That is not much energy difference compared to lunar escape energy. |
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Rocket Dreams
Musk, Bezos, and the Inside Story of the New, Trillion Dollar Space Race
Christian Davenport . Multco . 919.904 D2471r . 2025
- p001 Introduction
Part I: Earth, 2016-2018
p011 Ch.01 - "I Get This Angry Twice in a Year"
- p011 2017 March 1 Oscar - Manchester by the Sea
- p012 "study hall", 6 page document, 30 minutes reading
p014 Moon not cold dead rock, instead potential oasis, water in shadowed south pole craters
wp hydrates, est. 10 to 1000 ppm, 2025 PRIME-1 mission
- actually IM-2 mission, PRIME-1 payload of a drill and mass spectrometer ... failed landing, no useful data
p015 Pence National Space Council
p017 Shenzhou "Divine" capsule
p017 Shenzhou 5 mission claimed flawless, actually injurous gees
- p017 cleanup, fake second hatch opening
p018 Chang'e-1 mapped lunar surface
p018 Chang'e 3 lander 2023/12
- p023 Musk wanted for NASA Mars plan
- p025 Bezos wanted NASA Moon plan
p026 Ch.02 - Elon's Real Superpower
- p026 Musk taunts Bezos, Blue Origin not moving fast enough
- uh ... Gradatim Ferociter
- p026 2013 SpaceX granted right to lease Launch Complex 39A
- p027 Musk mantra focus on customers, not competitors
- yet it seems Davenport focuses on a "competition" with SpaceX already the winner
- p027 Amazon "Get Big Fast", compares 2016 Blue Origin 700 to (NASA funded) SpaceX with 5500
- p028 Blue Origin before 2016 bid as subcontractor, "from now go after SpaceX bids"
p029 Charles Miller "What can you do relative to the moon by 2020?"
p029 Brett Alexander
- p029 "Landing on the moon was far more difficult than landing on Earth"
no, different, but easier with proper infrastructure. Earth escape energy is 63 MJ/kg, lunar escape velocity energy is 2.8 MJ/kg ... 22 times less energy to dissipate, with no atmosphere to constrain the solution. An "inverse launch loop" track could shed that lunar arrival kinetic energy in d=E/a distance; for acceleration a=20 m/s², d=140 km, time =. Decelerating a few incoming vehicles wouldn't pay for the track, but one per minute is half a million per year. <<nbsp>><<nbsp>> <<nbsp>> <<nbsp>> <<nbsp>> In detail, a Hohmann transfer orbit ellipse from Earth radius perigee 6500 km (122 km equatorial altitude) to lunar orbit radius apogee ( r = 385000 km equatorial altitude). Estimate perigee launch velocity as approximately Earth escape velocity 11.2 km/s; from conservation of angular momentum the apogee velocity is approximately (6500 km / 385000 km )*11200 m/s ≈ 190 m/s . That is not much energy difference compared to lunar escape energy.
p038 Ch.03 - Converting the Impossible to Late
p054 Ch.04 - On a Jihad
p070 Ch.05 - The Dark Side of Space
p083 Ch.06 - "I'll Say You're Fired in Two Minutes"
Part II: Earth Orbit, 2018-2020
p101 Ch.07 - Starman
p113 Ch.08 - Flying by Swipe
p128 Ch.09 - Question Everything
p144 Ch.10 - By Amy Means Necessary
p160 Ch.11 - Artemis
p177 Ch.12 - "We Just Blew It to Smithereens"
p195 Ch.13 - "Thank You for Flying SpaceX"
Part III: Beyond, 2020-2025
p215 Ch.14 - Super Hardcore
p231 Ch.15 - A Chinese Flag in the Lunar Soil
p246 Ch.16 - Can't Get it Up (to Orbit)
p265 Ch.17 - The Gremlins of Unknown Unknowns
p279 Ch.18 - Toxic, Limping, Abysmal
p296 Ch.19 - Corporate Alchemy
p319 Epilogue - Plant the Flag