Is there Life on Mars? a Sample Return Mission Concept

Is there Life on M rsconcept of an unmanned sample-return-mission and the necessary delta-v requirement

Toni Engelhardtby

14.6.12

Text- Introduction - Life on other planets Follow the water (H2O) & manned missions to Mars

- Related Missions - Quick Overview Mars Reconnaissance Orbiter & Curiosity (Mars Science Laboratory)

- Mission “Red Dust” - Sample Return from Mars Surface * Trajectories * Delta-v Requirement * Loss & m0 estimation * Available Launchers / in development

- Aurora Joint ESA & NASA Mars program, ExoMars, Sample Return

Outline

Follow the water (Introduction)

• evidence for life as we know it

• Mars has trenches and rifts maybe originating from fluid water

• Frozen water at poles? liquid water under ground

• also important for future manned missions to Mars

Follow the water

Vastitas Borealis Crater North Polor Region

NASA initiative

water ice H2O

source of lifelong-term manned missions

Mars Reconnaissance Orbiter

High Resolution [1m/pixel] mapping to determine areas of interest for Rover Missions like Curiosity e.g. cracks in rocks

REMOTESpectrum analyzer with

Curi sity [MSL]

up to 7m reach

Laser ablation

Robot arm drilling unit camera etc.

complete laboratory onboard

search fororganic carbon

(elements of life)

Land on Mars to collect 1kg of rock/dust samples and bring them back to Earth < OBJECTIVE >

Mission “Red Dust”

>> Launch System (to be determined) will carry the following components to Mars

>> Lander Wimble Xs

will descent from Low Mars Orbit (LMO) to Mars surface with drilling unit to collect dust/rock and a Mars Launcher Brimo to return the samples to LMO

>> Orbiter Hermes remains with propellant for return and a docking unit in LMO will have a rendeveuz with Brimo to bring its cargo safely back to Earth

Land on Mars to collect 1kg of rock/dust samples and bring them back to Earth < OBJECTIVE >

>> Assumptions for the Matlab simulations

most efficient direct transfer to Mars > Hohmann

* Earth & Mars Orbit around the sun in a plane (actually di=1.85°)

* tilt of equatorial plane neglected

* assumptions for air drag, steering and gravity loss (g0, gT, gM and gM500 are constant during burn phase)

* typical propellant for all vehicles with Isp=300s

* no influence from moon, planets or any other celestial body besides mars, sun & earth

* re-entry and landing on earth without steering, just by aerobrake and parachute (see apollo missions)

* parachute on mars from 550m/s to 60m/s (taken from curiosity mission)

Orbit: 500 km above surface >> r_MOrb = 3896.2 km

Trajectories of Launch system and HermesAphelion Earth

Perihelion Mars

focal point of Hohmann Ellipseduration for transfer

239days 18hrs(one way)

Matlab Simulation

Perihelion Mars

focal point of Hohmann Ellipse

Aphelion Earth

1

1 Direct Hohmann to Marsdv1 = v_EarthEscape - v_LaunchSite + (v_H1 - v_EarthAphelion) =

= 13,594 m/s - v_LaunchSite

total delta-v dv_total = 13,594 m/s - v_LaunchSite

Ideal delta-v calculation (with Matlab)

Matlab Simulation

- definitions -dv positive in S/C flight direction dv = v_after - v_before maneuver


Perihelion Mars


Aphelion Earth

1

2 Hohmann to LMOdv2 = v_MarsOrbit - (v_H2 + v_GravityMars - v_MarsPerihelion) =

= 1,790 m/s

2


Matlab Simulation



Perihelion Mars


Aphelion Earth

1

a LMO to parachutedvMa = 550m/s - v_MarsOrbit

= - 2,766 m/s

2


a

Matlab Simulation



Perihelion Mars


Aphelion Earth

1

parachute phasedvP_Mars = 60m/s - 550m/s

= - 490 m/s (not counting)

2


a

Matlab Simulation



Perihelion Mars


Aphelion Earth

1

b Parachute to touchdowndvMb = 0m/s - 60m/s

= - 60 m/s

2


a b

Matlab Simulation



Perihelion Mars


Aphelion Earth

1

Relaunch to LMOdvMc = v_MarsOrbit =

= 3,316 m/s

2


a bc

cMatlab Simulation



Perihelion Mars


Aphelion Earth

1

3 Mars Orbit to Returndv3 = - v_H2 - ( - v_MarsPerihelion + v_MarsOrbit - v_MarsEscape500) =

= 1,225 m/s

2


3a b

c

Matlab Simulation




Perihelion Mars


Aphelion Earth

1

2


3a b

c

aerobrake + parachute

> aerobrake (with heat shield)

> parachute phase to splashdown

( similar to Apollo Missions )

Matlab Simulation

KourouFrench Guiana 5.15925° N 52.64966° W

vKourou = 463 m/S

Kennedy Space CenterUnited States

vKSC = 406 m/S

- Ariane V - Soyuz-2

28.521494° N 80.682392 W

- Ares I-X & V - Delta IV - Atlas V

- Falcon Heavy - Falcon XX

Velocity gain from Earth rotation

BaikonurKazakhstan

45.61908° N 63.313179° E

vKourou = 325 m/S

- Proton-M

Loss estimation + Real delta-v calculation

# air-drag

dv1 (Launcher)Launch to direct

Hohmann140 m/s *

dv2 (Launcher)Hohmann to LMO

-

dvMa (Wimble Xs)LMO to parachute

-

dvMb (Wimble Xs)parachute to touchdown

dvMc (Brimo)Mars surface to LMO

-

nozzle loss steering loss burning time gravity loss additional dv

80 m/s * 20 m/s * 600s 1590 m/s 1830 m/s

30 m/s 100 m/s 100s 76 m/s 206 m/s

20 m/s 50 m/s 250s 190 m/s 260 m/s

included in estimation

0

20 m/s 100 m/s 350s 350 m/s 470 m/s

dv3 (Hermes)LMO to direct Hohmann

- 30 m/s 100 m/s 400s 304 m/s 434 m/s

* from lecture notes - launch to LEOAdditional dv due to losses: 3200 m/sReal total dv requirement: 25951 m/s

Gravity loss = T * g0 / 3.7 ( to adapt to real values [ sample from Ariane V ] )

integration into matlab chain

payload to Mars [LMO] calculation mL, Mars = m0, WimbleXs + m0, Hermes >> planning backward!

weight of dust/rock samples + container + equipment >> Brimo Mars Launcher >> Wimble Xs Mars Lander >> Hermes Return Carrier

total payload to Mars Orbit LMO

source: book - Astronautics I ( Walter Ulrich ) [ page 48 ]

source: lecture notes Prof. Rott ( Spacecraft Technology I )

source: book - Astronautics I ( Walter Ulrich ) [ page 54 ]

from payload mL to total mass m0

from dv calculation

given values

optimal number of stages

optimal payload ratio

ratiopayload to total mass

total payload to Mars [LMO]

Wimble Xs ( payload: Brimo + 50kg )

Brimo ( payload: 72kg )

*Container Unit

*Dust & Rock samples

1kg

*Electronics *Navigation

9kg 24kg

RIG

*Drilling Unit*Embarking Mechanism*Scientific Equipment

196kg

*Parachute22kg

Hermes ( payload: 182kg )

*Brimo Payload(Samples + Container + Nav)

34kg

*Heat Shield58kg

Components > Minimum Weight Estimationintegration into matlab chain

*Power

20kg

*Docking Mechanism 18kg

*Power

20kg*Docking Mechanism 32kg

*Parachute18kg

*Solar Panels

40kg

just wildly guessed

single stage>> m0 = 2.04 mT

Wimble Xsdv = -2766 m/s

λ

dv [m/s]

dv = 3786 m/ssingle stage

>> m0 = 454 kg

Brimo

ε - structural factor

ε = 0.12

ε = 0.14

Isp [ typical ] = 300s

Hermesdv = 1660 m/s

Isp [ typical ] = 300sλ

dv [m/s]

ε - structural factor

single stage>> m0 = 1.65 mT

ε = 0.1

total payload to LMO

3.69 mT

Falcon XX

STATUS

MANUFACTURER

TYPE

CONFIG

CAPACITY

TRANSFER ORBITLMO

SUITABLE

Ares I Ares VFalcon 9Delta IVAtlas VAriane V

HeavyHLVECA

canceled canceledavailableavailableavailable in development proposed

TBD TBD

9.04 mT (esc) 9.31 mT (esc)4.3 mT (esc) ~53,3 mT (esc)25.5 mT (LEO)~53 mT (LEO) ?

?3.67 mT 3.78 mT1.76 mT ~6.0 mT ~21.40 mT2.22 mT

transfer orbit to LMOkick stage with 60kg adapter

Isp = 320s & ε = 0.1

availableavailable

ProtonSoyuz-2

7.9 mT (esc)

NO YESNONONO NO YES YES

20.7 mT (LEO)1.8 mT

M XHeavy

Energia Khrunichev

692 kg

Aurora

ExoMars Mars Lander & Orbiter

NEXTSample Return

far future Manned Mission

thank you

@ toni88x.bplaced.net/LifeOnMars

presentation + matlab simulationare available online

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