) Mark G. Benton, Sr. The Boeing Company. AIAA 2008 Joint Propulsion Conference Hartford, Connecticut July 23, 2008

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Crew and Cargo Landers for Human Exploration of Mars Vehicle System Design (AIAA-2008 2008-5156) The Boeing

1 Crew and Cargo Landers for Human Exploration of Mars Vehicle System Design (AIAA ) The Boeing Company AIAA 2008 Joint Propulsion Conference Hartford, Connecticut July 23, 2008 Slide 1 of 25 Slides 2008

Spaceship Discovery Architecture for Human Solar System Exploration Spaceship Discovery Conceptual design study Four design reference missions DRM 1: Moon high-energy DRM 2: Mars low-energy DRM 3:

Mars orbit Wait time in Mars orbit: 454 d Transfer orbit to Earth: 259 d Propulsive capture into 1854 km (1000 nmi), circular Earth orbit Total mission duration: 972 d Two Types of Mars Landers LM2

System (3) SSD-DRM2-v2 Bimodal Nuclear Thermal Rocket (NTR) Engine (3) Deployable Solar / Thermal Shade (2) Main LH 2 Propellant Core Tank (CT) (4) Very Low Boil-off Cryo. Retention Sys.

2 Spaceship Discovery Architecture for Human Solar System Exploration Spaceship Discovery Conceptual design study Four design reference missions DRM 1: Moon high-energy DRM 2: Mars low-energy DRM 3: Mars high-energy DRM 4: Callisto high-energy DRM 2 Summary Assembly in 556 km (300 nmi) altitude, circular Earth orbit Transfer orbit to Mars: 259 d Propulsive capture into 556 km (300 nmi), circular Mars orbit Wait time in Mars orbit: 454 d Transfer orbit to Earth: 259 d Propulsive capture into 1854 km (1000 nmi), circular Earth orbit Total mission duration: 972 d Two Types of Mars Landers LM2 piloted crew lander LM3 autonomous cargo lander Six landers transported to Mars (3) LM2 and (3) LM3 Engineering Module (EM) Closed Brayton Cycle (CBC) Electrical Gen. System (3) SSD-DRM2-v2 Bimodal Nuclear Thermal Rocket (NTR) Engine (3) Deployable Solar / Thermal Shade (2) Main LH 2 Propellant Core Tank (CT) (4) Very Low Boil-off Cryo. Retention Sys. Abort Propulsion System (APS) Main Engine Main LH 2 Propellant Drop Tank (DT) (6) Spaceship Discovery Side View - Main Ship Artificial Gravity (AG) Centrifuge Galactic Cosmic Ray (GCR) Biological Shield (LH 2 & H 2 O) Spaceship Discovery Side View Cutaway Key Features Service Module (SM) 5-Port Docking Module (DM) Moon & Callisto Lander Module LM1 (DRMs 1, 4) Crew Module (CM) Mars Lander Modules LM2, LM3 (DRMs 2, 3) Reentry Module (RM) Spaceship Discovery with Six LM2/LM3 Landers Attached DRM2 Configuration for Trans-Mars Injection Slide 2 of 25 Slides 2008

Spaceship Discovery DRM 2 Mars Exploration Mission Details Mars

crew on surface at a time: 3 crew per mission 3 crew do science in

(40 kw) Each manned mission (1) LM2: Crew, 0.5 MT cargo (1) LM3: Hab.

Requirements Wait time at Mars = 454 days 7 d in orbit before 1 st

TEI Total surface time = 436 days Endurance for each mission: 218 d

(contingency) Surface rendezvous with LM3 enables full 218 d mission

3 Spaceship Discovery DRM 2 Mars Exploration Mission Details Mars Mission Assumptions 6-person crew Two manned landing attempts 1/2 of crew on surface at a time: 3 crew per mission 3 crew do science in orbit Base camp w/ cargo-only LM3 4.6 MT of cargo 6.0 MT nuclear gen. (40 kw) Each manned mission (1) LM2: Crew, 0.5 MT cargo (1) LM3: Hab., 4.0 MT cargo Extra (6 th ) lander: LM2 dedicated for rescue DRM2 Requirements Wait time at Mars = 454 days 7 d in orbit before 1 st landing 4 d between landing missions 2 nd mission ends 7 d before TEI Total surface time = 436 days Endurance for each mission: 218 d + 10% margin = 240 d LM2 can perform 24 d mission on its own (contingency) Surface rendezvous with LM3 enables full 218 d mission Slide 3 of 25 Slides Trans-Mars Injection (TMI) Burn Mars Orbit Insertion (MOI) Burn 2008

4 Mars Lander Design Challenges Mars Entry, Descent, and Landing (EDL) Aero braking selected as primary deceleration method (to minimize mass) Difficult to decelerate in Mars thin atmosphere, but aeroheating is significant Advantages of Viking shape for aero braking (70-deg. sphere-cone forebody) Low ballistic coefficient, C B = m / C d S Ref (nominal 64 kg/m 2 ) High hypersonic C d, good stability, and tolerable peak deceleration A flight-proven shape, with extensive aerodynamic data Used for every Mars landing to date or planned (But only up to 2.0 MT) Large mass ( T) needed for sufficient cargo for human exploration ~1.0 MT Viking entry vehicles had C B of 64 kg/m 2 with a base diameter of m An 80 MT entry vehicle would need a 32 m dia. heatshield (deemed impractical) Divided 80 MT into four 20 MT landers, each w/ more achievable diameter of 16 m Inflatable heatshield extension (HSE) enables low ballistic coefficient Increases base dia. From 7.5 to 16.0 m (achieves C B of 66 kg/m 2 nominal Viking ) Maximum internal clear diameter of launch fairings assumed to be 8.0 m Inflatable heatshields have been studied for many years and show feasibility Implementation of CG offset needed for Apollo-type steering Not possible to relocate sufficient mass to achieve required 0.28 m CG offset Rigid heatshield/hse asymmetric to vehicle centerline but symmetric to Viking OML Vehicle flies hypersonically at 3 degrees of incidence with forebody = 0 Implementation of parachute deceleration and powered descent (PD) phases Earlier design had 2-stg. parachute system, but insufficient time for 2 nd stage to deploy Parachute sizing trade used to size larger single parachute w/ longer PD phase Parachute based on 19.7 m dia. disk-gap-band (DGB) flight tested in Viking program Parachute diameter increased to 27 m, vehicle total mass increased to 21.5 MT SSD-LM2-v4 Side View with Lander Vertical Axis Normal HSE Attached to Rigid Central Heatshield Scaled Viking Lander OML Side View w/ Vert. Axis at 3 deg. Incidence Front View w/ Lander Vertical Axis Normal Slide 4 of 25 Slides 2008

The need for six landers Two pairs of LM2 & LM3 landers permit two independent, manned landing attempts 3 rd LM3: dedicated cargo/power 3 rd LM2: dedicated rescue veh.

5 The need for six landers Two pairs of LM2 & LM3 landers permit two independent, manned landing attempts 3 rd LM3: dedicated cargo/power 3 rd LM2: dedicated rescue veh. Requirements & Assumptions Mars Landing Mission Design Lander design considerations EDL for elevation 0.0 m or lower ~ 1/2 of equatorial surface 250 km orbit based on a study for Mars sample return mission Two-stg ascent reduces EDL landed mass stress vs SSTO Stable, w/ sufficient altitude to enable rescue of crew Enables LM2 abort-to-orbit during powered descent Able to return to parking orbit from latitude degrees Utilizes Mars 241 m/s rotational speed at equator Booster allocation 120 m/s for 2.0 deg. plane change Orbiter allocation 120 m/s for 2.0 deg. plane change & 32 m/s for orbital maneuvering Entry Interface h = 150 km V Rel = km/s Descent Xfer Orbit h A = 550 km h P = 125 km Deorbit Burn V = km/s a b a LM2/LM3 EDL Mission Profile LM2/LM3 Landing Zones (a, b) EDL Powered Descent V T = km/s Total Orbital Maneuvering, Deorbit, & Powered Descent Burns V T = km/s Orbiter Ascent Burn 2 V 2 = km/s Orbiter Xfer Orbit h A = 556 km h P = 250 km Orbiter Ascent Burn 1 V 1 = km/s LM2 Ascent Mission Profile Booster Ascent Burn V T = km/s Intermediate Circular Orbit V = km/s Parking Orbit H = 556 km V = km/s Slide 5 of 25 Slides 2008

6 Mars Landing Mission Description Launch, Transit, and Landing Preps Launch and Assembly (a) Modular Spaceship Discovery design - Assembled in LEO Modules launched into 556 km (300 nmi) assembly orbit Assembly completed during approximately one year Max. launch dimensions: 32.0 m long x 8.0 m dia. Max. mass 50 MT incl. fairing & airborne support equip. (2) 21.5 MT LM2 / LM3 landers launched together Outbound Transit and Landing Preparations (b - e) (6) landers docked to Spaceship Discovery docking module (3) LM2 crew landers (3) LM3 cargo landers Hibernation mode during transit Capture into Mars parking orbit Lander undocks in Mars orbit HSE inflated and checked out Deorbit burn injects vehicle into descent transfer orbit (a) Notional Launch Configuration Inflatable HSE Stowed Under Fixed Central Heatshield (c) In Transit HSE Stowed (d) Inflate Heatshield Extension (b) Outbound Transit (e) Deorbit Burn Slide 6 of 25 Slides 2008

7 Three Main EDL s Aero Deceleration Mars Landing Mission Description Overview of EDL s Start: 150 km entry interface Deploy parachute M = 3.0 Parachute Deceleration Full inflation M = 2.7 Jettison heatshield, HSE, landing gear doors M = 0.76 Powered Descent Jettison parachute M = 0.74, start rocket engines End: Soft landing MOLA Altitude (km) Axial Velocity vs. Altitude ,000 1,500 2,000 2,500 3,000 3,500 Velocity (m/s) Drag, Lift, and Thrust Forces vs. Time 1, Aero Entry Deceleration Parachute Deceleration Powered Descent Start DGB Deployment M = 3.0, h = 13.9 km Jettison Heatshield, HSE, & Landing Gear Doors M = 0.76, h = 5.5 km Force (kn) Drag Force Lift Force Thrust Force DGB Fully Inflated M = 2.7, h = 13.3 km Jettison Parachute & Start Powered Descent M = 0.74, h = 4.4 km Start Hover h = 25 m Soft Landing h = 0 m Time From Entry Interface (s) EDL Mission Profile Final Descent Slide 7 of 25 Slides 2008

8 Mars Landing Mission Description EDL: Entry & Parachute s Aero Braking (a, b, and c) Aerodynamic deceleration RCS/ offset CG control for Apollo-type lift & steering 4.7 g maximum deceleration DGB parachute deceleration Redundant DGB parachute carried (2 for 1 redundancy) 3.3 g maximum deceleration Jettison heatshield (8) solid motors fire for 5 s for clean separation, drive heatshield 1.3 km downrange Axial Acceleration vs. Time (a) Atmospheric Entry (b) Parachute Deceleration Aero Entry Deceleration Parachute Deceleration Powered Descent Acceleration (Earth g's) Time From Entry Interface (s) (c) Jettison Heatshield and Deploy Landing Gear Slide 8 of 25 Slides 2008

Mars Landing Mission Description EDL: Powered Descent Powered Descent (d, e) Gravity turn and vertical

0 (constant) DS: (8) throttleable descent engines (8 for 6 redundancy) LM2: gimballed main engine x-fed w/

point in powered descent Descent section jettisoned Switch to ascent propellants (d) Gravity Turn: T/W = 2.

) 0.00-10.00-20.00-30.00-40.00-50.00-60.00-70.00-80.

9 Mars Landing Mission Description EDL: Powered Descent Powered Descent (d, e) Gravity turn and vertical descent at T/W = 2.0 (constant) DS: (8) throttleable descent engines (8 for 6 redundancy) LM2: gimballed main engine x-fed w/ descent propellant LM3: (5) gimballed descent engines (same type as DS) LM2 abort-to-orbit during any point in powered descent Descent section jettisoned Switch to ascent propellants (d) Gravity Turn: T/W = 2.0 Flight Path and Thrust Vector Angles vs. Time - Powered Descent Thrust Vector or Flight Path Angle (Deg.) Flight Path Angle Gravity Turn Thrust Vector Angle Vertical Descent Timed Hover Soft Landing Time From Entry Interface (s) (e) Vertical Descent: T/W = 2.0 Slide 9 of 25 Slides 2008

10 Mars Landing Mission Description Powered Descent, Continued Hover & Soft Landing (f, g, h) LM2: Main engine shut down LM3: (5) Central eng. shut down Timed hover: Up to 10 s Determine final trajectory to avoid surface obstacles Descent: 0.74 < T/W < 1.29 Soft landing at vertical velocity less than 2.0 m/s LM2 abort-to-orbit during any point in powered descent Booster engine ignited Descent section jettisoned (f) Hover: T/W = 1.0 T/W and Axial Acceleration vs. Time - Powered Descent T/W (Non-Dim.) or Acceleration (Earth g's) Gravity Turn Vehicle T/W Axial Acceleration Vertical Descent Timed Hover Soft Landing (g) Descent: T/W = Time From Entry Interface (s) (h) Final Braking: T/W = 1.29 Slide 10 of 25 Slides 2008

11 Mars Landing Mission Description Mars Surface Operations Mars Surface Ops (a, b, & c) (2) LM3s land before LM2 LM3 w/ nuclear generator and 4.6 MT cargo (LM3-GEN) LM3 w/ crew habitat and 4.0 MT cargo (LM3-HAB) (2) LM3s traverse the surface Up to 1.0 km/d Rendezvous & wait for LM2 LM2 lands near LM3 site Homes on LM3 beacons Lands within 10 km Waits for LM3s, up to 24 d LM3s traverse the surface Up to 1.0 km/d Rendezvous w/ LM2 Base camp setup LM3s unload cargo LM3 GEN moves ~500 m (connected w/ power cable) LM3 HAB docks w/ LM2 Three-level LM3 crew habitat 58 m 3 pressurized volume Protection from radiation and dust storms Ultraflex 5.5 m dia., Steerable Solar Array (2 places) 5.0 kw Tot. (a) LM3 Landed Configuration Surface Docking Adaptor (2 places) Surface Docking System (b) LM2 Landed Configuration 5 cm H 2 O Radiation Shield HAB LSS Supercritical LO 2 Tk. (6 pl) HAB LSS H 2 O Tank (Toroidal) Slide 11 of 25 Slides (c) LM2 and LM3 HAB Docked on Surface for Long-Term Mission 2008

12 Mars Landing Mission Description Mars Surface Ops., Continued Mars Surface Ops (d and e) Base camp inventory LM3-HAB docked w/ LM2 LM3-GEN provides power Cargo: Rover, inflatable habitat, scientific and communications gear Preparations for LM2 ascent Crew stores samples in LM2 Crew leave PLSS units behind, use ELSS for suits LM3-HAB undocks and moves a safe distance away Preparations for 2 nd mission LM3s on surface wait for 2 nd landing mission (LM2 & LM3) Surface rendezvous as before Optional Capabilities 2 nd landing mission could utilize both LM3-HABs (shown) 3 rd LM3 could carry ISRU plant, enabling entire crew of 6 to land LM2 contingency mission 24 day duration Small rover and science equipment (500 kg cargo) Slide 12 of 25 Slides (d) LM2 (Center) Docked w/ Two LM3 Habitat/ Cargo Landers (2 nd LM3 Optional) Top View of Notional Mars Base Camp 2008 (e) LM3 w/ 40 kw Nuclear Generator and Cargo Power Cable

13 Mars Landing Mission Description Ascent, Rendezvous, & Docking s Booster Ascent (a, b, and c) Two-stage LM2 launches from descent section Ascent to 250 km intermediate orbit using booster propellants Same configuration for abort to orbit in powered descent Main ship could rescue crew in intermediate orbit if required Booster jettisoned in orbit Orbiter Ascent (d, e) Orbiter maneuvers for correct orbital alignment Orbiter uses Hohmann transfer to raise orbit to 556 km orbit Orbiter performs rendezvous and docking w/ main ship Crew transfers to main ship Orbiter jettisoned in orbit Preparations for 2 nd manned landing or return to earth (a) Ascent to Intermediate Orbit (b) Ascent to Intermediate Orbit End of 1 st Mission (c) Jettison Booster in Intermed. Orbit (d) Orbiter Ascent to Parking Orbit End of 2 nd Mission (e) Rendezvous and Docking Slide 13 of 25 Slides 2008

14 Vehicle Systems (a through d) Key Enabling Technologies LM2 / LM3 Mars Exploration Landers Larger diameter Viking heritage, DGB parachutes (up to 30 m) Inflatable, lightweight, damagetolerant, ablative heatshield Long-term, low-loss storage systems for cryogenic liquids Precision GN&C for EDL LM3 initial targeting LM2 landing near LM3 Exploration Systems Exploration equipment Life support systems Power generation systems Rugged space suits Inflatable habitats Rover vehicles Avionics & communications Scientific equipment In-Situ Resource Utilization to Reduce consumables Increase scientific returns (a) DGB Parachutes (b) Inflatables for HSE (b) Cryo Consumable Storage Slide 14 of 25 Slides (d) Precision GN&C for Entry, Descent, and Landing 2008

Summary Spaceship Discovery LM2 & LM3 Mars Exploration Landers Conclusion LM2 & LM3: Proposed solution for landing humans on Mars Part of Spaceship Discovery -or- Architectures utilizing MOR Build on

15 Summary Spaceship Discovery LM2 & LM3 Mars Exploration Landers Conclusion LM2 & LM3: Proposed solution for landing humans on Mars Part of Spaceship Discovery -or- Architectures utilizing MOR Build on a successful heritage Viking geometry EDL concept for multiple Mars unmanned landers Flight tested parachutes Inflatable HSE enables a low C B in a reasonable fairing size Extensively studies & tests show concept is feasible Designed for crew safety Descent abort-to-orbit Rescue on surface Rescue in orbit Dual mission sets of landers Enhance mission redundancy Design & CONOPS minimizes developmental risk and cost Flight-tested HW & methods LM2 & LM3 commonality Slide 15 of 25 Slides Trans-Earth Injection (TEI) Burn LM2 Ascent to Orbit (Booster) Burn 2008

16 Backup: LM2/LM3 Design Data LM2 Crew Lander Elevation Views Abbreviations and Acronyms ADM Array Drive Mechanism AS Ascent Section ASB Ascent Booster ASO Ascent Orbiter DGB Disk-Gap-Band DOT Deorbit Thruster DS Descent Section FDE Fixed Descent Engine GDE Gimballed Descent Eng. HAB Crew Habitat HS - Heatshield HSE Heatshield Extension HSM HS Separation Motor LGR Landing Gear LSS Life Support System ME Main Engine OML Outer Moldline PRP Propellant PRS Pressurization RCS Reaction Control System SCR Supercritical SDA Surface Docking Adaptor SDS Surface Docking System VDW Vehicle Drive Wheel VDM Vehicle Drive Motor Slide 16 of 25 Slides SSD-LM2-v4 ASO: Crew Cabin Tunnel to Air Lock in DS Air Lock in DS DS DOT (8 pl) & RCS Fuel Cell Cutaway: AS, Airlock, & Cargo Bay Descent / Ascent ME AS w/ DS Cutaway: Fuel Cell Bays 2008 ASB: PRP and PRS Tanks & ME SDA (2 pl) AS RCS Thruster Quad HSM (8 pl) DS Fuel Cell /LSS SCR LH 2 Tks. (2 pl) DS Fuel Cell /LSS SCR LO 2 Tks. (2 pl) FDE (8 pl) Avionics Bay DS PRP & PRS Tanks DS Thrust Cylinder Structure Pri. Struc. Cutaway: PRP/LGR Bays (LGR Stowed) Landed CG Landing Pad Cutaway: PRP/LGR Bays (LGR Depl.) Deploy w/ Pyros, Spring & Gravity Assist LGR Door (Jett. w/ HS) DS PRP & PRS Tanks m Stroke, & m Leveling Strut

17 Backup: LM2/LM3 Design Data LM2 Crew Lander Section Views LM2-Specific Design Features Two-way transport of crews between Mars orbit and surface Single-stage Descent Section (DS) Two-stage Ascent Section (AS) 1 st stg: Ascent Booster (ASB) 2 nd stg: Ascent Orbiter (ASO) Gimballed, fixed thrust, ME for descent and ascent: 98.2 kn Crew: 3 (4 for rescue) Payload: 500 / 140 kg (DS/AS) Endurance:27 / 3 d (DS/AS) DS power: LH 2 / LO 2 fuel cells AS power: Batteries Airlock for surface egress Surface docking adaptors (2) Cargo bay for contingency mission payload (500 kg) Designed for abort to orbit during descent and landing Coverage during all phases of the powered descent SSD-LM2-v4 DS DOT (8 pl) DS Avionics Bay DS RCS Crew Cabin LSS SCR LO 2 Tanks Tunnel to Airlock in DS Tunnel to Airlock in DS RCS Thruster Quad Ascent Orbiter Upper Level Crew Seat LSS H 2 O Tanks Tunnel to SDA in DS AS Orbiter ME (6 pl) DS DGB Parachute Mortar (2 pl) ASO PRP Tank (8 pl) DS Surface Access Door Pair (2 pl) ASB PRP and PRS Tanks & ME DS RCS Thruster (8 pl) Fuel Cell Fixed DE (8 pl) Airlock in DS SDA in DS (2 pl) ASB & DS Mid-Level (LGR Stowed) Cargo Bay DS Fuel Cell/ LSS SCR LH2 Tanks (2 pl) DS-AS Pyro Sep. Bolts (6 pl) Fuel Cell / LSS SCR LO2 Tks. (2 pl) PRP/ PRS Tks. ASO Lower Level and DS Upper Level DS Lower Level (LGR Depl.) Air Lock Slide 17 of 25 Slides 2008

18 Backup: LM2/LM3 Design Data LM3 Cargo Lander Elevation Views LM3-Specific Design Features One-way autonomous transport of cargo to surface of Mars Design commonality with LM2: Descent section (DS) Overall geometry Mass properties Engines & subsystems EDL flight profile Surface power: Solar arrays (5 kw) and batteries Surface mobility: 90 m/hr during daylight conditions (~ 1 km/day) Surface docking system (to mate to an LM2 or another LM3) Surface Docking Adaptor (1) Crew Habitat (HAB) In place of LM2 AS Net landed cargo: 10.6 T LSS consum./ food (6.6 T) Exploration equip. (4.0 T) Mission endurance: 240 d LM2 maximum (30 d) LM3 maximum (210 d) 218 d + 10% margin SSD-LM3-v4 5 cm H 2 O Radiation Shield SDA HAB LSS SCR LO 2 Tk. (6 pl) Air Lock DS DOT (8 pl) & RCS DS RCS Thruster (8 pl) DS Batteries 3-Level HAB Cutaway: HAB, Airlock, & Cargo Bay 3-Level HAB RCS Thruster Pair SDS (Stowed) LSS H 2 O Toroidal Tank DS DGB Chute Mortar (2 pl) DS ADM (2 pl) DS Solar Array (Stowed) (2 pl) GDE (5 pl) FDE (8 pl) HAB w/ DS Cutaway: Cargo Bays Avionics Bay DS PRP & PRS Tanks DS Thrust Cylinder Structure Pri. Struc. Steerable VDW/ VDM Bogey Cutaway: PRP/LGR Bays (LGR Stowed) Landed CG Cutaway: PRP/LGR Bays (LGR Depl.) Bogey Link Folds for LGR Stowage LGR Door (Jett. w/ HS) DS PRP & PRS Tanks Bogey Link Extends to Land, Folds to Traverse Slide 18 of 25 Slides 2008

19 Backup: LM2/LM3 Design Data LM3 Cargo Lander Section Views LM2/LM3 Common Features Heatshield OML scaled from Viking 70-degree sphere-cone EDL flight profile Apollo steering: CG offset and lifting for precision guidance Lightweight composite structures Storable MMH & N 2 O 4 propellants 6-axis reaction control system 3 yr service life (DRM 2) SSD-LM3-v4 Dining Area Kitchen Area Computer Station and Bookshelves Ladder to HAB Mid- Level Lounge w/ Entertainment Center DS Surface Access Door Pair HAB LSS Toroidal H 2 O Storage Tk. DS RCS Thruster (8 pl) HAB Lower Level Food Storage Bay SDS (Stowed) Solar Array (Stowed) & ADM (2 pl) HAB LSS SCR LO 2 Tks. (6 pl) SDA in DS LM2/LM3 Common DS Primary structure Descent propellant system Descent engines (8) Deorbit thrusters (8) RCS thrusters (16) HS, HSE, and thermal protection DGB Parachutes (2) Primary & redundant Landing gear Air lock & cargo bay LM3 has (2) cargo bays in place of LM2 fuel cell bays DS Avionics Bay HAB Upper Level, Crew Living Space DS DOT (8 pl) DS RCS HAB: Berthing, Medical, Shower, & Toilet HAB Mid-Level & DS Upper Level Tunnel to SDS in DS Bunk (Stowed) Ladder to HAB Lower Level Tunnel to Air Lock in DS Battery HAB Lower Level & DS Mid-Level (LGR Stowed) DS PRP & PRS Tks. Cargo Bay Air Lock SDS (Stowed) Cargo Bay DS Lower Level (LGR Depl.) Solar Array Stowed (2 pl) Slide 19 of 25 Slides 2008

20 Backup: LM2/LM3 Design Data DGB Parachute Sizing Trade Mach Number for Heatshield Separation, DGB Jettison, & Start of Powered Descent Mach Number m DGB Simulation Did Not Close Increasing Risk for HS Sep & Start of PD Selected 27 m DGB Parachute Diameter Increasing Risk in Technology Developmt. PD Start w/ M > 0.9 Not Considered Feasible DGB Parachute Diameter (m) Mass (kg) Mach Number for HS Separation, DGB Jettison, & Start of PD m DGB Simulation Did Not Close PD Start w/ M > 0.9 Not Considered Feasible Increasing Mass Penalty for Smaller DGB Dia. Parachute Sizing Parametric Selected 27 m DGB Parachute Diameter Decreasing Mass Benefit for Larger DGB Dia. Propellant, DGB, & Structures Mass Propellant Consumed for Soft Landing Installed DGB Parachute Mass Delta Descent Sect. Structures Mass DGB Parachute Diameter (m) Data for Parachute Sizing Parametric: DGB Parachute Diameter (m) = DGB parachute Area (m 2 ) = DGB Parachute Installed Mass (kg) = Mach No. for Jettisoning DGBs and Start of PD (Non-d.) = Velocity for Jettisoning DGBs and Start of PD (m/s) = Altitude for Jettisoning DGBs and Start of PD (m) = 8,322 6,516 5,719 5,200 4,770 4,423 4,089 3,836 3,249 Total Propellant Mass Consumed for Soft Landing (kg) = 3, , , , , , , , ,353.3 Max. Axial Force During DGB Deploymt. (kn) = Axial Force Normalized to a 22.0 m DGB Parachute = Upper Descent Section DGB B/U Structure Mass (kg) = Descent Section Propellant Tank Structural Mass (kg) = Descent Section Structural Mass Changes (kg) = Delta Struct. Mass Normalized to a 22 m DGB (Non-d.) = Delta Descent Section Structure Mass (kg) = Total Mass of DGBs, Propellant, & Structure (kg) = Slide 20 of 25 Slides 2008

21 Backup: LM2/LM3 Design Data Descent Flight Performance Axial Velocity vs. Altitude Lander and Heatshield Trajectories ,000 5,000 Heatshield Traject. Lander Trajectory MOLA Altitude (km) 10 MOLA Altitude (m) 4,000 3,000 2, , ,000 Velocity (m/s) Distance from Separation (m) Lander and Heatshield Altitudes vs. Time 6,000 5,000 Heatshield Traject. Lander Trajectory MOLA Altitude (m) 4,000 3,000 2,000 1, Time from Separation (s) Slide 21 of 25 Slides 2008

22 Backup: LM2/LM3 Design Data LM2 Ascent Flight Performance Altitude vs. Inertial Velocity Components Flight Path and Thrust Vector Angles vs. Time Burnout MOLA Altitude (km) Vertical Velocity Burnout Horizontal Velocity - Includes m/s Equatorial Rotation Angle from Horizontal (Degrees) Thrust Vector Angle Flight Path Angle ,000 1,500 2,000 2,500 3,000 3,500 4,000 Velocity (m/s) Elapsed Time From Ignition (s) Altitude vs. Acceleration Components Axial Thrust and Drag Forces vs. Time Burnout Thrust Force MOLA Altitude (km) Vertical Acceleration Horizontal Acceleration Burnout Axial Force (kn) Drag Force Acceleration (m/s 2 ) Elapsed Time From Ignition (s) Slide 22 of 25 Slides 2008

23 Backup: LM2/LM3 Design Data LM2 Abort-to to-orbit Flight Performance (a) Altitude vs. Time for Abort Scenarios 250 MOLA Altitude (km) Abort Scenario 1 Abort Scenario 2 Abort Scenario 3 Abort Scenario 4 Abort Scenario Elapsed Time From Abort (s) Altitude vs. Time for Abort Scenarios 5,000 4,000 MOLA Altitude (m) 3,000 2,000 Abort Scenario 1 Abort Scenario 2 Abort Scenario 3 Abort Scenario 4 Abort Scenario 5 1, Elapsed Time from Abort (s) Slide 23 of 25 Slides 2008

24 Backup: LM2/LM3 Design Data Dimensions and Mass Properties Ascent Orbiter Lander Module 2 (LM2) Ascent Booster Total Ascent Descent Section Overall Vehicle Lander Module 3 (LM3) Payload Carrier Descent Section Overall Vehicle Dimensions (m) Length Overall Diameter * Mass (kg) Dry Payload (Incl. Crew) ** , ,000 4,000 Structure, Tanks, Insulation ,213 1,547 2,760 2,197 1,897 4,094 ECLSS & Avionics Parachute System Main Engine (Installed) Reaction Control System Dry Mass Margin (15%) Life Support Consumables , ,615 RCS Propellant (Usable) Main Propellant (Usable) 231 9,950 10,181 3,461 13, ,461 3,461 Total Mass 2,050 11,150 13,200 8,300 21,500 9,790 11,710 21,500 Dry Mass Fraction *** * Diameters for LM2 and LM3 in the Overall Vehicle columns shows dimensions with inflatable HSE inflated. ** For LM3, Includes 500 kg allocation for module-module surface docking system. *** = (Payload + Structure/Insulation/Shielding + Engines & Subsystems (Including Propellant Residuals)) / Total Mass Slide 24 of 25 Slides Ascent Orbiter* Descent Section Overall Vehicle * Ascent Orbiter consumables are reserved for ascent and contingency and are not included in surface endurance calculations Lander Module 2 (LM2) Lander Module 3 (LM3) Total Payload Carrier Descent Section Overall Vehicle Usable on Surface* Design Assumptions (kg/man-day) Breathing Oxygen Water Dried & Condensed Food Endurance on Surface of Mars Total (man-days) Crewmembers (days) Consumables Mass (kg) Breathing Oxygen Water ,725 4,725 5,339 Dry Food ,260 1,260 1,422 Total ,615 6,615 7,540

25 Backup: LM2/LM3 Design Data Nominal and Abort Performance Major Propulsive Burns Ascent Orbiter Orbit Raising Lander Module 2 (LM2) Ascent Booster Total Ascent Booster Ascent Descent Section Overall Vehicle Deorbit & Braking Lander Module 3 (LM3) Payload Carrier Descent Section Overall Vehicle Deorbit & Braking Req'd. Delta Velocity (km/s) V - Ideal, Req'd. for Burn V - Maneuvers & Losses V - Subtotal V - Total Incl. 1% FPR * Performance Parameters ** Specific Impulse (I SP ) Mass Ratio (M i / M f ) Burn Propellant Fraction Initial Thrust / Weight *** Final Thrust / Weight *** Mass (kg) Operating Empty Mass 1,819 1,200 3,019 4,839 7,858 9,790 8,249 18,039 Main Propellant for Burn 231 9,950 10,181 3,461 13, ,461 3,461 Total Mass 2,050 11,150 13,200 8,300 21,500 9,790 11,710 21,500 * FPR = Flight Performance Reserve ** Heat shield (772 kg) jettisoned before landing braking. *** For AS Booster & Orbiter, Referenced to Mars' gravity (g M = m/s 2 ); For DS During Powered Descent. Orbit Requirements, Abort 250 km Baseline Scenarios 1, 2 ATO 1 ATO 2 ATO 3 ATO 4 ATO 5, & Baseline Ascent Orbit Ascent Initial Conditions Initiation Altitude (m) 4,423 3,015 2,010 1, Initial Flight Path Angle (deg.) Initial Horiz. Relative Velocity (m/s) Initial Vertical Relative Velocity (m/s) Results Altitude Minimum in Trajectory (m) 1, Altitude Required / Achieved (km) Velocity Required / Achieved 3 (m/s) 3,553 3,417 3,349 3,348 3,391 3,482 3,553 Add'l. V Req'd. for Inter. Orb. (m/s) Ascent Orbiter V Available 4 (m/s) V Deficit for Orbit Raising (m/s) Abort Scenario 1 initiated from the start of powered descent. 2 Abort Scenario 5 initiated from a low-altitude hover. 3 Velocity required for 250 km intermed. orbit includes allocation of 6 m/s for up to 12.5 degrees of launch latitude (equatorial ascent would need 6 m/s less V) plus an allocation of 120 m/s for 2.0 deg. plane change during ascent. 4 Ascent Orbiter delta velocity available to augment booster performance includes an allocation of 120 m/s for a Slide 25 of 25 Slides 2.0 degree plane change during orbit raising plus 32 m/s for rendezvous and docking for a total of 182 m/s. 2008

Loads, Structures, and Mechanisms. Team C5 Matthew Marcus Chris O'Hare Alex Slafkosky Scott Wingate

Loads, Structures, and Mechanisms Matthew Marcus Chris O'Hare Alex Slafkosky Scott Wingate Presentation Overview Design requirements Initial crew capsule design choice Pressure vessel design Pressure loads