1. No category

Is there Life on M rs
concept of an unmanned sample-return-mission
and the necessary delta-v requirement
by
Toni Engelhardt
14.6.12
Thursday, June 14, 12
Outline
- Introduction - Life on other planets
Follow the water (H2O) & manned missions to Mars
Text
- 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
Thursday, June 14, 12
Follow the water (Introduction)
Vastitas Borealis Crater
•
•
•
•
evidence for life as we know it
North Polor Region
Mars has trenches and rifts maybe originating from fluid water
water ice
Frozen water at poles? liquid water under ground H2O
also important for future manned missions source
to Mars
of life
long-term manned missions
Follow the water
NASA initiative
Thursday, June 14, 12
High Resolution [1m/pixel] mapping
to determine areas of interest for
Rover Missions like Curiosity
e.g. cracks in rocks
Mars Reconnaissance Orbiter
Thursday, June 14, 12
Curi sity [MSL]
Robot arm
up
to
7m
h
ac
re
complete
laboratory
onboard
drilling unit
camera
etc.
search for
organic carbon
(elements of life)
REMOTE
Spectrum analyzer
with
Laser ablation
Thursday, June 14, 12
Land on Mars
to collect 1kg of rock/dust samples and bring them back to Earth
< OBJECTIVE >
>> 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
Mission “Red Dust”
Thursday, June 14, 12
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)
Thursday, June 14, 12
Trajectories of Launch system and Hermes
Aphelion Earth
Matlab
Simulation
focal point of Hohmann Ellipse
Perihelion Mars
duration for transfer
239days 18hrs
(one way)
Orbit: 500 km above surface
>> r_MOrb = 3896.2 km
Thursday, June 14, 12
Ideal delta-v calculation (with Matlab)
Matlab
Simulation
Aphelion Earth
focal point of Hohmann Ellipse
1 Direct Hohmann to Mars
dv1 = v_EarthEscape - v_LaunchSite +
(v_H1 - v_EarthAphelion) =
Perihelion Mars
= 13,594 m/s - v_LaunchSite
1
- definitions -
dv positive in S/C flight direction
dv = v_after - v_before maneuver
Thursday, June 14, 12
total delta-v
dv_total = 13,594 m/s - v_LaunchSite
Ideal delta-v calculation (with Matlab)
Aphelion Earth
Matlab
Simulation
focal point of Hohmann Ellipse
2 Hohmann to LMO
dv2 = v_MarsOrbit - (v_H2 + v_GravityMars
- v_MarsPerihelion) =
Perihelion Mars
= 1,790 m/s
1
2
- definitions -
dv positive in S/C flight direction
dv = v_after - v_before maneuver
Thursday, June 14, 12
total delta-v
dv_total = 15,384 m/s - v_LaunchSite
Ideal delta-v calculation (with Matlab)
Aphelion Earth
Matlab
Simulation
focal point of Hohmann Ellipse
a LMO to parachute
dvMa = 550m/s - v_MarsOrbit
= - 2,766 m/s
Perihelion Mars
1
2
a
- definitions -
dv positive in S/C flight direction
dv = v_after - v_before maneuver
Thursday, June 14, 12
total delta-v
dv_total = 18,150 m/s - v_LaunchSite
Ideal delta-v calculation (with Matlab)
Aphelion Earth
Matlab
Simulation
focal point of Hohmann Ellipse
parachute phase
dvP_Mars = 60m/s - 550m/s
= - 490 m/s (not counting)
Perihelion Mars
1
2
a
- definitions -
dv positive in S/C flight direction
dv = v_after - v_before maneuver
Thursday, June 14, 12
total delta-v
dv_total = 18,150 m/s - v_LaunchSite
Ideal delta-v calculation (with Matlab)
Aphelion Earth
Matlab
Simulation
focal point of Hohmann Ellipse
b Parachute to touchdown
dvMb = 0m/s - 60m/s
= - 60 m/s
Perihelion Mars
1
2
a
- definitions -
b
dv positive in S/C flight direction
dv = v_after - v_before maneuver
Thursday, June 14, 12
total delta-v
dv_total = 18,210 m/s - v_LaunchSite
Ideal delta-v calculation (with Matlab)
Aphelion Earth
Matlab
Simulation
focal point of Hohmann Ellipse
c Relaunch to LMO
dvMc = v_MarsOrbit =
= 3,316 m/s
Perihelion Mars
1
2
a
- definitions -
b
c
dv positive in S/C flight direction
dv = v_after - v_before maneuver
Thursday, June 14, 12
total delta-v
dv_total = 21,526 m/s - v_LaunchSite
Ideal delta-v calculation (with Matlab)
Aphelion Earth
Matlab
Simulation
focal point of Hohmann Ellipse
3 Mars Orbit to Return
dv3 = - v_H2 - ( - v_MarsPerihelion +
v_MarsOrbit - v_MarsEscape500) =
Perihelion Mars
= 1,225 m/s
1
2
a
- definitions -
3
b
c
dv positive in S/C flight direction
dv = v_after - v_before maneuver
Thursday, June 14, 12
total delta-v
dv_total = 22,751 m/s - v_LaunchSite
Ideal delta-v calculation (with Matlab)
Aphelion Earth
Matlab
Simulation
focal point of Hohmann Ellipse
aerobrake + parachute
> aerobrake (with heat shield)
> parachute phase to splashdown
Perihelion Mars
( similar to Apollo Missions )
1
2
a
- definitions -
3
b
c
dv positive in S/C flight direction
dv = v_after - v_before maneuver
Thursday, June 14, 12
total delta-v
dv_total = 22,751 m/s - v_LaunchSite
Loss estimation + Real delta-v calculation
#
integration into matlab
chain
air-drag
nozzle loss
steering loss
burning time
gravity loss
additional dv
140 m/s *
80 m/s *
20 m/s *
600s
1590 m/s
1830 m/s
dv2 (Launcher)
-
30 m/s
100 m/s
100s
76 m/s
206 m/s
dvMa (Wimble Xs)
-
20 m/s
50 m/s
250s
190 m/s
260 m/s
dv1 (Launcher)
Launch to direct
Hohmann
Hohmann to LMO
LMO to parachute
dvMb (Wimble Xs)
included in
estimation
parachute to
touchdown
0
dvMc (Brimo)
-
20 m/s
100 m/s
350s
350 m/s
470 m/s
dv3 (Hermes)
-
30 m/s
100 m/s
400s
304 m/s
434 m/s
Mars surface to LMO
LMO to direct Hohmann
Gravity loss = T * g0 / 3.7 ( to adapt to real values [ sample from Ariane V ] )
* from lecture notes - launch to LEO
Thursday, June 14, 12
Additional dv due to losses:
Real total dv requirement:
3200 m/s
25951 m/s
- Proton-M
- Falcon Heavy
- Falcon XX
- Ares I-X & V
- Delta IV
- Atlas V
Kennedy Space Center
United States
28.521494° N 80.682392 W
vKSC = 406 m/S
Velocity gain from
Earth rotation
Thursday, June 14, 12
Kourou
Baikonur
French Guiana
- Ariane V
- Soyuz-2
5.15925° N 52.64966° W
vKourou = 463
m/
S
Kazakhstan
45.61908° N 63.313179° E
vKourou = 325 m/S
payload to Mars [LMO] calculation
mL, Mars = m0, WimbleXs + m0, Hermes
weight of dust/rock samples
+ container + equipment >> Brimo Mars Launcher >>
>> Hermes Return Carrier
>> planning backward!
Wimble Xs Mars Lander
total payload to Mars Orbit LMO
Thursday, June 14, 12
from payload mL to
total mass m0
optimal
payload ratio
from dv calculation
optimal
number of stages
source: book - Astronautics I
( Walter Ulrich ) [ page 54 ]
ratio
payload to total mass
source: book - Astronautics I
( Walter Ulrich ) [ page 48 ]
source: lecture notes Prof. Rott
( Spacecraft Technology I )
Thursday, June 14, 12
given
values
Components > Minimum Weight Estimation
integration into matlab
chain
total payload to Mars [LMO]
Wimble Xs
*Power
( payload: Brimo + 50kg )
20kg
*Docking
Mechanism 18kg
Brimo
( payload: 72kg )
*Dust & Rock
samples
20kg
*Electronics
*Navigation
1kg
*Parachute
9kg
24kg
40kg
RIG
*Drilling Unit
*Embarking Mechanism
*Scientific Equipment
196kg
just wildly guessed
Thursday, June 14, 12
*Solar
Panels
22kg
*Power
*Container Unit
Hermes
( payload: 36kg )
*Docking
Mechanism 32kg
*Parachute
*Heat Shield
18kg
58kg
*Brimo Payload
(Samples + Container + Nav)
34kg
λ
Isp [ typical ] = 300s
ε - structural factor
Wimble Xs
ε = 0.12
single stage
dv = -2766 m/s >> m0 = 2.04 mT
Brimo
dv = 3786 m/s
ε = 0.14
single stage
>> m0 = 454 kg
dv
Thursday, June 14, 12
[m/s]
λ
ε - structural factor
Isp [ typical ] = 300s
Hermes
ε = 0.1
single stage
dv = 1660 m/s >> m0 = 1.65 mT
total payload
to LMO
3.69 mT
dv
Thursday, June 14, 12
[m/s]
available
Energia
Soyuz-2
available
available
available
available
STATUS
in development
proposed
MANUFACTURER
Khrunichev
Proton
Ariane V
Atlas V
Delta IV
TYPE
Falcon 9
M
ECA
HLV
Heavy
CONFIG
Heavy
Falcon XX
canceled
canceled
TBD
TBD
Ares I
Ares V
X
transfer orbit to LMO
kick stage with 60kg adapter
Isp = 320s & ε = 0.1
CAPACITY
7.9 mT (esc)
692 kg
NO
Thursday, June 14, 12
20.7 mT (LEO)
1.8 mT
NO
4.3 mT (esc)
1.76 mT
NO
9.04 mT (esc)
3.67 mT
NO
9.31 mT (esc)
3.78 mT
YES
TRANSFER ORBIT
LMO
~53 mT (LEO)
~6.0 mT
SUITABLE
YES
?
?
25.5 mT (LEO)
2.22 mT
~53,3 mT (esc)
~21.40 mT
NO
YES
ExoMars
NEXT
Sample Return
far future
Manned Mission
Mars Lander & Orbiter
Aurora
Thursday, June 14, 12
thank you
presentation + matlab
simulation
are available online
@
toni88x.bplaced.net/LifeOnMars
QR code
> Download
Thursday, June 14, 12
Info on ExoMars
exploration.esa.int