(Mars) Vehicle "2500" - Part 2 - The Plans

Basically if the target planet or object has less gravity than Mars and/or any atmosphere or not at all like Earth's Moon this vehicle should be fine. It differs from the Apollo Lunar Module in those parts which require aerodynamics but is otherwise similar. It can be used with some amount of AB (aero braking) but it can also handle braking with rockets alone. If much gas is available for braking then less fuel is required and that mass can be used for transport purposes if required. So basically our design is a general purpose lander, but fits best to Mars, Moons etc.

Here is the more detailed general plan of the vehicle "2500".

Figure 1. General purpose lander for Mars, Moons, etc.

Mars Vehicle "2500" - Part 1 - Basics

This Mars Vehicle (MV), model "2500" is part of the LEAMOR (Light Extended Apollo Mars Orbit Rendezvous) total mission plan. See the article for general ideas about that Mars mission plan.

Figure 1. Mars Vehicle (MV) "2500" with ablative lower part and heat shield above ablative fuel balls.

LEAMOR Mars Mission - Entry and Return Vehicles (Part 4)

PART 4: Entry and Return Vehicles

Why to have separated Entry and Return Vehicles (EV and RV) for the mission. Basically separating them makes it possible to divide the required consumables and propellants to two smaller amounts. And the one without the astronauts could then be sent using lower speed and less propellant expensive routes. Additionally two return capable vehicles in the LMO add to the safety of the astronauts. If one of the vehicles is broken the other one hopefully still is usable.

Return or Entry Vehicle without the Habitat Module (HM). Service Module (SM) to the left and the Orion re-entry capsule to the right.

LEAMOR Manned Space Craft - Modular Transport Engine (Part 3)

PART 3: Modular Transport Engine (TE)

LEAMOR stabnds for Light Extended Apollo Mars Orbit Rendezvous.

As we already have figured out that the large spacecraft must be modular (since the lift vehicle can only lift a certain amount to the LEO at one time). See the previous part of this article series and we call these about 150 ton (lbs) building blocks as L-modules.

L-Modules about 150 000 lbs each, size about D5 x L11.75

LEAMOR Manned Mars Mission - Why Modular? (Part 2)

PART 2: Why the Manned Mars Mission Must be Modular?

Simply because the launch vehicle can only lift a certain amount at any time - and that size or mass will be the maximum module size - and the only way to get larger masses and structures is to bolt them together in the low Earth's orbit (LEO).

LEAMOR stabnds for Light Extended Apollo Mars Orbit Rendezvous.

SLS can lift about 150 .. 300 tons (lbs) to LEO

LEAMOR Mission - Light Extended Apollo Mars Orbit Rendezvous (Part 1)

PART 1: LEAMOR MISSION BASICS

How to land a man on the Mars and return him safely to the Earth

It looks like the main problem is NOT that we couldn't do it but that we maybe need more time and/or money for it?

I represent here a simple LEAMOR mission plan to Mars and back which just extends the Apollo missions and tries not to do anything more in the first phase than just to get a man on the Mars and return him safely to the Earth. LEAMOR stands for Light Extended Apollo Mars Orbit Rendezvous. (See also LOR).

The following picture shows the basic Mars mission phases.

Typical Mars mission and its main events.