1. Aerodynamics
Project Olympus

2. Ballute Material Ballute material is Kapton
Filled with Helium Gas to Mars surface Pressure for landing and 100 Pa for Aerocapture
Tethers are PBO
By Richard O’Connor

3. Mars Thermal Protection System (TPS)
Low Heating Rates with Ballutes
Non-Ablators Carbon phenolic
If a Ballute is usable than this Heat shield will work
TPS
Mass
3.0 t

4. Aerobrake Maneuver for Earth Propulsion (EP) Tug
Prior to Aerobrake Maneuver:
EET Location/Altitude: km (at Highest Energy Ellipse Orbit)
Initial Aerobrake Parameters:
Atmospheric Entry Velocity: km/s
Constant Atmospheric Entry & Exit Altitude: 150 km (at LEO)
Perigee radius (Rp) for all Aerobrake runs: fixed at 115 km
EP Parameters:
Maximum Diameter: 10 m
EET Mass: 29.1 t
Tankage Mass & Size will vary per crew

5. Total Energy Dissipated (J)
Aerobrake Maneuver Options:
Aerobrake #1= 3 Runs, Aerobrake # 2 = 7 Runs
Ablative Heat Shield Required:
Material: AVOCAT H/CG
Heat Shield Mass Calculations:
TOFD (days)
Aerobrake # 1
Aerobrake # 2
≈ 5
≈ 10
Aerobrake Maneuver
Total Energy Dissipated (J)
Aerobrake # 1
1.49 x 108 J
Aerobrake # 2
9.40 x 107 J
Heat Shield Mass (t)
Aerobrake # 1
Aerobrake # 2
4.32
2.01

6. Earth - Aerobraking Tug

7. Mars -Aerocapture
Using the Atmospheric Drag to do a ΔV for entering into an Orbit
Crew 3
Total Mass t
Velocity
6.4 km/s
Ballute Mass
3.07 t
TPS Mass
3 t
Max g’s
2.67g

8. Mars -Crew Landing From MLO
Crews 1-7
Mass
100t
Velocity
3.5 km/s
TPS Mass
3.0 t
Ballute Mass
2.93 t
Max gs
4.07
Working on pinpoint landing
Working on last 14km and handing over to hovering

9. Mars -Cargo Entry
Cargo
Mass
68t – 91t
Velocity
6.0 km/s
TPS Mass
3.0 t
Ballute Mass
4.89 t
Some of the Cargo Missions will be Aerocaptured to LMO
Increased Mass gives a better ballute efficiency

10. Earth Descent Vehicle (EDV)
Direct Re-entry into Earth
Use of Capsule with Subsonic Parachutes similar to Apollo/Orion
PICA-X ablator
Conditions
Initial Velocity
12.6 km/s
Flight Path Angle
-7.1o
Max gs
6.6 g
Heat Shield Mass
0.64 t

11. Earth Re-entry Trajectory
Landed Mass
Entry velocity (h = 150 km)
6 metric tons
12.57 km/s
Interface flight path angle
-7.065
Allowable variation
+0.1/-0.2
max deceleration
6.58g
4g+ period
230 sec
Duration
486 sec (8m 6s)
Total stag point heating
56.3 kJ/cm2
Required TPS mass
0.61 t
Ending velocity (h = 4 km)
75.6 m/s

12. Earth Entry Capsule - Geometry
Heat shield: 3 m radius, 3 m nose radius, 3.6 cm thickness
Capsule total mass: 6.6 t
Crew compartment: cylindrical pressure vessel, 2.25 m tall x 3 m diameter
Docking/crew entry port on top side (for attaching to Transit Hab)