jinnantonix

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About jinnantonix

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  1. This is true. However an elliptical lunar orbit with Ap at 62,000km this is very close to being outside the Moon SOI, IRL it means that a craft at this altitude can shift the 90 degrees of plane change with delta-V of only ~200m/s. i.e. the plan is for arriving craft to encounter the LOP-G when it is close to Ap, and match velocities. Yes it is somewhat wasteful, but not seriously so, compared to the benefits of attaining NRHO.
  2. Artemis 3 - Lunar Orbital Platform and Advanced Exploration Lander.
  3. Hi @harrisjosh2711, a big thanks for this mod, I am really enjoying it. I have used many of your parts to build a Falcon Heavy as part of my mission log Artemis: To the Moon and Beyond in Real Solar System.
  4. More of the Artemis Program in RSS. SSTU Merlin engines used in the Falcon Heavy, and SSTU lander pod, fuel tanks and SuperDRACO engines used in the Advanced Exploration Lander and transit vehicles.
  5. Artemis 3 The final stage of Artemis phase 1, is initial establishing of the Lunar Orbital Platform - Gateway, and a crewed lunar landing in the darkness of Shackleton Crater at the lunar south pole. The high level plan for Artemis 1, 2 and 3 is as follows: The component craft for the Artemis 3 mission comprises the following: Power and Propulsion Element (PPE), being developed by Maxar Technologies (8.0 tons, including 2t of Xenon propellant) Minimum Habitat Module, being developed by Northrop Grumman - a modified Cygnus standard module (3.75 tons approx) Advanced Exploration Lander, developed by NASA and partners. 3 stage - Ascent, Descent and Transit Vehicles. (14.5 tons approx) Orion with crew of 4 (launch mass 25.8 tons) and lunar surface logistics module (9.8 tons) Design Proposal: The first three components are to be delivered on commercial spacecraft. In order to minimise cost and risk, I propose that the SpaceX Falcon Heavy ($150M per launch) be used, two launches with each launch carrying ~`16 ton payload to lunar insertion, and a single robotic docking procedure in lunar orbit. The final component, Orion with crew of 4 and logistics, will be launched on the Space Launch System (SLS Block 1B), and will rendezvous and manually dock with the LOP-G in lunar orbit. Artemis 3a: integrates and fully tests the PPE and MHM on Earth along with a small expendable hypergolic General Transit Vehicle (GTV) providing 800 m/s delta-V to decelerate the PPE/MHM into NRHO. The GTV is a smaller version of the Lunar Transit Vehicle (stage 1 of the Advanced Exploration Lander), a relatively low cost craft comprising a single SuperDraco engine, fuel tanks and remote control system. Launch Vehicle is the SpaceX Falcon Heavy. Artemis 3b: integrates and fully tests the 3 stages of the Advanced Exploration Lander on Earth. The craft comprises Lunar Ascent Vehicle (crew of 2), Lunar Descent Vehicle (which remains on the lunar surface) and Lunar Transit Vehicle which provides propulsion for entry into NRHO and rendezvous with the LOP-G, transport of LAV and LDV to low lunar orbit, and rendezvous with LAV after surface mission completion, thence return crew to the LOP-G. The prototype AEL craft will be fully expendable, however future AEL craft will have re-usable LAV and LTV components. Launch Vehicle is the SpaceX Falcon Heavy. The AEL will rendezvous with the LOP-G, and will dock with the MHM under robotic control from Earth. Artemis 3: integrates the Orion spacecraft (crew of 4) with a supply module containing lunar surface and transit logistics. Launch Vehicle is the SLS Block 1B. After rendezvous, logistics equipment will be transferred to the Advanced Exploration Lander. 2 crew will remain at the LOP-G. while a pilot and a scientist will transfer to the AEL, and land at the lunar south pole. After 2 weeks on the surface carrying out scientific studies, they will launch in the Lunar Ascent Vehicle and return to the LOP-G with a small payload of moon rocks. The crew of 4 will then board the Orion and return to Earth.
  6. It says: " nearly polar ", it is not exactly polar because NRHO is a 3-body orbit. Otherwise, I entirely agree with you. The video is excellent, though I had to watch it 3 times to understand the whole "slinky" thing. I propose to model the NRHO in KSP as a highly elliptical orbit, with the Ap over the south pole, as this will best allow the proposed telecommunications relay capability from the lunar south pole. I don't fully understand why NASA proposes DRO rather then NRHO, I suspect it may have something to do with safety or recoverability in case of system failure. I am certain there is no intention to ever transition from DRO to NRHO. I will also redo the Artemis 1 mission from scratch showing the Orion burning into DRO, new video is pending. DONE Edit: I figured out why they go to DRO. The Orion stays in DRO for about 6 days or about 1/3 of a lunar orbit before burning retrograde to elliptical orbit. By shifting the position of Pe, this allows a single burn utilising the Oberth effect to attain a trajectory directly back to Earth. (It doesn't explain why they don't go to NRHO and do a proper test ).
  7. Hi @Geschosskopf Agree that DRO is equatorial, and according to your video it is circular. So now the infographics make sense, thanks for advising. My assumption was the the test burns were intended to simulate entering NRHO which involves retrograde burn to relative zero velocity, then immediate prograde burn returning to an elliptical orbit . However it could also be that NASA's plan is that the craft prograde burns to circular orbit (DRO), then immediately (the fact that the craft is in orbit for only 6 days suggests this) burns back to an elliptical orbit - consuming a similar amount of fuel. From your video it is clear that NRHO is neither equatorial nor polar, the craft is not actually in orbit around the Moon (in the normal sense). However as there are no Lagrange points in KSP the nearest equivalent is a lunar polar orbit. I have already tested entering polar orbit direct from TLI (Ap=60,000km, Pe = 2,000km) - my Orion has plenty of fuel for this, even carrying a 6 ton payload, with plenty of fuel remaining to return to Earth.
  8. Artemis 2: Orion crewed lunar flyby Proposed launch, July 2022 on the NASA SLS Block 1 launch vehicle with Orion spacecraft. Artemis 2 mission: Lunar flyby with 4 crew and launch of CubeSats.
  9. Hi @Geschosskopf I spent a long time developing the SRBs. I tried to modify maxthrust and fuel capacity in a single booster pair, but ended up with SRBs that are much heavier than the real boosters, or did not burn long enough. I found clipping some SRBs (from the BetterSRB mod) into the bottom of an unmodified Kickback got exactly the right dimensions ,thrust, mass and burn time to match real world. (Stock SRBs SUCK!) The part count (and resultant launch pad explosions) has occasionally been a problem, but judicious autostrutting eventually fixed that. I also switched settings to "Indestructible Buildings" as the SLS and Falcon Heavy are both so large, and boosters so powerful, they destroy the pad at launch. I didn't follow the the infographic, it conflicts with other information I have on the proposed Artemis 1 mission. Firstly the launch goes east from the Cape exactly when in lunar planer alignment so there is no wasteful plane change burn needed. Why would you launch any other way? There is conflicting information on the whether Artemis 1 will go to circular orbit with 4 burns. Future missions will never put the Orion in circular orbit, rather they will involve a single retrograde burn of the engines to go into NRHO, adjust to encounter the Lunar Orbital Platfrom - Gateway, then use thrusters to rendezvous and dock with the LOP-G. Crew then transfer to the LOP-G, and the 3-stage lunar lander. At the end of the mission, the crew reboard the Orion to return to Earth. This is a more accurate infographic : https://www.nasa.gov/image-feature/artemis-1-map/ showing the Orion burning once to going into elliptic orbit, then "Orbital Maintenance " burns while in a Distant Retrograde Orbit (DRO) at Ap= 38,000 nmi which I believe is proposed to be sufficiently similar to NRHO for test purposes. In the video I did similar to this. In the video I did 2 burns for return, (a) prograde to exit lunar SOI, then (b) retrograde with Pe at 70km from Earth's surface. This is different to the intended return manouevre, which is (a) retrograde to low Pe over the moon and (b) utilise Oberth, prograde burn to Earth. The latter is not possible to model accurately in KSP because there are no Lagrange points. However I will attempt to show this in future videos (if it doesn't use too much dV)
  10. More of the Artemis Program in RSS. SSTU components used to create a Space Launch System (SLS) Block 1.
  11. Artemis 1: Orion Lunar Orbital Test Proposed launch, July 2021 on the NASA SLS Block 1 launch vehicle with Orion spacecraft. Artemis 1 mission: Lunar orbital test flight and launch of 13 CubeSats.
  12. More of the Artemis Program in RSS. SSTU components used to create a Atlas V 500 series commercial launch vehicle, using 1st stage RD-180 engine with maxthrust of 4,152 kN, and second stage RL10C-1 with maxthrust of 106kN in vacuum, and a Cygnus ISS resupply module. I also made an Atlas V 300 series suitable for single 1.4 ton payload launch. (not shown).
  13. Commercial Lunar Payload Service - Mission 1 It is proposed that by 2021, NASA will award a contract for the first Commercial Lunar Payload Service, to deliver science equipment and mini rovers to the lunar surface. One contender for the contract is Astrobotic Technology with their Peregrine Lander. This video simulates CLPS Mission 1 assuming Astrobotic wins the contract. It is expected that NASA will utilise CLPS to execute reconnaissance at Artemis program lunar landing sites. Design Notes:
  14. My first video in my mission log Artemis: To the Moon and Beyond in Real Solar System. Many SSTU parts used in building a LAS test vehicle, Delta IV Heavy, Orion and modified Peacekeeper missile.
  15. Testing Phase: 2010 LAS Pad Abort-1 Test [video] 2014 Delta IV Heavy Orion Exploration Flight Test-1 [video] 2019 PeaceKeeper Ascent Abort-2 Test [video]