Spaceflight 🚀The first #Starhopper flight was in 📆 2019. First #Starship landing (without #RUD 💥) 📆 2021. First #atmospheric entry 📆 2024. When do you expect the first (uncrewed) Starship #Mars 🔴 landing attempt ? 🤔
2025
2027
2029
> 2030
Poll ended at .
#SpaceX will launch its first #Starships 🚀 to #Mars 🔴 in two years. "These will be uncrewed to test the reliability of landing intact on Mars" https://www.reuters.com/technology/space/musk-says-spacex-launch-first-uncrewed-starships-mars-two-years-2024-09-07/
"Two years down the road it seems feasible.It would be enough for #SpaceX to have a fleet of three launchers, one per pad. The bottleneck may lie in the supply of the thousands of liters of #methane and oxygen needed to maintain a sustained hourly launch rate. Some have proposed building a jetty and a small gas #pipeline so that the fuel can arrive in large methane tankers." https://english.elpais.com/science-tech/2024-11-04/elon-musks-plans-to-go-to-mars-within-two-years.html
The proof of concept shows that at the current achievable flow rates of #CO2 and water, it is possible to meet #NASA’s 16-month deadline for refueling #rockets on #Mars 🔴. It can be scaled further to meet tighter rocket refueling ⛽ deadlines. The use of Martian nighttime temperatures for heat 🌡️ exchange can potentially reduce the dependence on power-hungry cryogenic methods for gas liquefaction. https://pmc.ncbi.nlm.nih.gov/articles/PMC9118664
Thermodynamic modeling of in-situ rocket propellant fabrication on Mars
In-situ resource utilization (ISRU) to refuel rockets on Mars will become critical in the future. The current effort presents a thorough feasibility analysis of a scalable, Matlab-based, integrated ISRU framework from the standpoint of the second ...
For Starship to go to #Mars 🔴, you’ve got to get #Starship tankers ⛽ on orbit and perfect orbital refueling. #SpaceX will have to perfect the #robots 🤖 that will help build spacecraft #LandingPads and human #habitats on the Martian surface, prospect for water 💧 underground, and convert the water and carbon dioxide captured from the atmosphere into vast reservoirs of super-cooled oxygen and methane for the Starships’ return voyage to Earth. https://www.forbes.com/sites/kevinholdenplatt/2025/03/11/spacexs-starship-plan-to-land-first-humans-on-mars-but-not-till-2031
#Reuters - #Starship is set to depart for #Mars at the end of next year, carrying humanoid bot #Optimus. https://www.reuters.com/technology/space/starship-carrying-teslas-bot-set-mars-by-end-2026-elon-musk-2025-03-15
Each #technological breakthrough brings us closer to realizing the goal of living on #Mars 🔴. Mars colonization 👩🚀👨🚀 is within our potential reach. This paper has outlined a feasible timeline⌛
📆 2020s: Continued #robotic exploration
📆 2030s: Test missions for human life-support systems and #ISRU ⚒️ on the Martian surface
https://pmc.ncbi.nlm.nih.gov/articles/PMC10884476
#HumanSpaceflight #SpaceTravel #SpaceExploration #SpaceColonization
Towards sustainable horizons: A comprehensive blueprint for Mars colonization
This paper thoroughly explores the feasibility, challenges, and proposed solutions for establishing a sustainable human colony on Mars. We quantitatively and qualitatively analyze the Martian environment, highlighting key challenges such as ...
"#Musk's timeline will prove a bit optimistic, but even accounting for that, we are on the threshold of a new era.” Despite setbacks, #SpaceX continues pushing boundaries with its rapid iteration approach. The question remains not whether humans will reach #Mars, but when. https://www.forbes.com/sites/luisromero/2025/03/07/spacex-explosion-blasts-mars-timeline-2026-goal-likely-delayed
According to the baseline scenario, a total of four cargo 📦 #Starships and two crewed 👩🚀👨🚀 Starships with a payload capacity of 100 MT each are available until 📆 2029 to bring the required systems to Mars. A power🔋supply system (#PSS) is needed for all activities on Mars. It could be investigated if a refueling ⛽ in #Mars orbit 🌌 scenario would enable return flights. https://www.nature.com/articles/s41598-024-54012-0.pdf
#Starship would take between a mere 80 and 150 days to reach #Mars 🔴, depending on the launch window.
A shorter transfer time comes at the cost of higher fuel ⛽ requirements and less payload mass. Not only is it more difficult to reach the required delta-V, it’s also more difficult to stop. The spacecraft will need to brake harder to match velocities with Mars upon arrival https://www.marssociety.ca/2021/01/22/rocket-physics-how-to-go-to-mars
The time of travel to #Mars can be reduced from nine months ⏳ to about four months. This would reduce #radiation ☢️ doses by over 60% compared to the Hohmann transfer. This trajectory uses 4.62 km/s of deltaV. #SpaceX #Starship is designed for about 6 km/s of deltaV. The return velocity of #Apollo was about 11 km/s https://marspedia.org/Aerobraking
By Giusy Falcone Dec 2021 https://gfalcon2.web.illinois.edu
With a 6 m/s increase in the Delta-V budget, the deep reinforcement learning approach shortened the #aerobraking time by 68.3% 📉. The DRL algorithm does not encounter any thermal violations over 40 episodes compared to the 2.8 average thermal violations experienced by the state-of-the-art heuristic https://arc.aiaa.org/doi/10.2514/6.2022-2497
As the #spacecraft approaches Mars 🔴, it will need to perform a capture burn 🔥 to slow down and be captured by Mars' gravity. This requires a delta-v of about 0.7 to 1.3 km/s to enter Mars' orbit or to land on the planet's surface. #Starship 🚀 will enter #Mars’ atmosphere at 7.7 km/sec and decelerate #aerodynamically https://www.uc.edu/content/dam/refresh/cont-ed-62/olli/fall-23-class-handouts/SpaceX%208%20%20Mars%20%20Vision%20Summary.pdf
Parachute 🪂 is not the only means for descent, as high-mass class vehicles are emerging for human 👩🚀 missions. Shallow entry flight-path angles are preferred in order to achieve a lower terminal velocity to ensure a safe descent phase. Retro-propulsion could be activated at Mach 2 and above https://www.intechopen.com/chapters/72944#
Aerocapture, Aerobraking, and Entry for Robotic and Human Mars Missions
This chapter provides an overview of the aeroassist technologies and performances for Mars missions. We review the current state-of-the-art aeroassist technologies for Mars explorations, including aerocapture, aerobraking, and entry. Then we present a parametric analysis considering key design parameters such as interplanetary trajectory and vehicle design parameters (lift-to-drag ratio, ballistic coefficient, peak g-load, peak heat rate, and total heat load) for aerocapture, aerobraking, and entry. A new perspective on a rapid aerobraking concept will be provided. The analysis will include first-order estimates for thermal loading, thermal protection systems material selection, and vehicle design. Results and discussion focus on both robotic missions and human missions as landed assets and orbiters.
#AMAT allows the user to simulate #atmospheric entry trajectories, compute deceleration and heating🌡️loads, compute aerocapture entry corridors and simulate aerocapture trajectories. AMAT supports analysis for all #atmosphere-bearing destinations in the #SolarSystem: #Venus, #Earth, #Mars, #Jupiter, #Saturn, #Titan, #Uranus, and #Neptune https://amat.readthedocs.io/en/master
Khleedril@spaceflight We move closer to the Flash Gordon future every day, don't we?
From Earth to #Mars lasts about 200 days. To safely go from those speeds down to zero in that short amount of time requires “slamming on the brakes”. Successful #aerobraking depends upon precise navigation, knowledge of weather, and a solid understanding of the forces the craft can withstand. https://science.nasa.gov/planetary-science/programs/mars-exploration/mission-timeline
It makes sense to use the Martian #atmosphere to help with deceleration and save on propellant. https://www.youtube.com/watch?v=5seefpjMQJI This method has been tested and validated on Earth, using #SpaceX #Falcon9 first stages in the high atmosphere to simulate #Martian conditions https://marspedia.org/Landing_on_Mars#Powered_landing
Vehicle Landing
Supersonic retropropulsion 🔥: Beginning in 📆 2014, #NASA and #SpaceX formed a three-year public-private partnership. The F9 boosters were outfitted with special instruments to collect data specifically on portions of the entry burn that fell within the range of Mach numbers and dynamic pressures expected on #Mars 🔴. To everyone's surprise and delight, it worked 👍 https://phys.org/news/2024-11-mars-approach-large-payloads-red.html
The new Mars landing approach: How we'll land large payloads on the Red Planet
Back in 2007, I talked with Rob Manning, engineer extraordinaire at the Jet Propulsion Laboratory, and he told me something shocking. Even though he had successfully led the entry, descent, and landing (EDL) teams for three Mars rover missions, he said the prospect of landing a human mission on the Red Planet might be impossible.
Thermal protection systems and #atmospheric friction have been used #historically 👴 to reduce most of the kinetic energy that needs to be lost prior to landing. #NASA is carrying out thermal imaging infrared sensor data-gathering studies of the SpaceX booster controlled-descent tests that are currently, as of 📆 2014, underway https://en.wikipedia.org/wiki/Mars_atmospheric_entry
April 📆 2016 #SpaceX has quietly been conducting the first flight tests of a technology known as supersonic #retropropulsion—in #Mars 🔴 -like conditions. #NASA had tested supersonic retropropulsion in small-scale air-in-air wind tunnel tests, but not live flights. If NASA were to try to conduct that kind of test on its own, the cost would probably exceed $3 billion 💰. "The stability was manageable, and while there are still some issues, there are no showstoppers." https://arstechnica.com/science/2016/04/spacex-has-already-demonstrated-its-key-mars-landing-tech-with-the-falcon-9
July 📆 2024 The outlook for slowing incoming vehicles has improved, compared to a decade ago. #NASA’s #LEO Flight Test of an Inflatable Decelerator (#LOFTID) took place in 📆 2022, successfully inflating a 6-meter- (20-foot-) diameter aerodynamic decelerator system in Earth’s stratosphere, which has a density similar to #Mars’ 🔴 atmosphere. Additionally, engineers now are optimistic about using thrusters for what is called supersonic #retropropulsion https://www.planetary.org/articles/challenges-facing-the-human-exploration-of-mars
#SpaceX and #NASA have proposed supersonic retro-propulsive landing as a method to land large payloads on #Mars 🔴. This method has been tested and validated on Earth, using SpaceX Falcon 9 first stages in the high atmosphere to simulate Martian conditions. #Retropropulsion in the supersonic flight regime is used to slow the vehicle during part of the flight path. This element of the flight path compensates for the low Martian #atmospheric density https://marspedia.org/Landing_on_Mars#Supersonic_retro-propulsion_landing
Chad - x 
@spaceflight you're comparing an aerobraking maneuver to a true rendezvous mission, opening the crew up to incredible risk. If it's a NASA crew there's no way they'd ever approve it and there's a snowball's chance in hell I'd ever personally participate in a mission that might skip across the atmosphere of Mars with no chance of return in the time my life is sustained.
Capturing into a Mars orbit is the only safe way to get to the Martian surface.
@chad so you propose to go slower, increasing the #radiation exposure time ? 🤔
@spaceflight Mars doesn't have a heliosphere.
@chad that's not an answer
@spaceflight in fact it is.