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Mars Scout Mission 2011: 

Mars Scout Mission 2011 Daedalus Final Presentation April 27, 2005

Presentation Outline: 

Presentation Outline I. Team Organization II. Science Objectives and Measurement III. Baseline Mission Architecture 1. Mission Summary 2. Flight System Baseline 3. Mass and Power Budgets 4. Descope Options 5. Cost

Team Roles and Specializations: 

Team Roles and Specializations Project Manager: Shae Williams Project Systems Engineer: Clifford May Science Payload Engineer: Michael Thomas Flight Systems Engineer: Kevin Diggs Mission Systems Engineer: Michael Sullivan Principal Investigator: Alexander Bazilevskiy Traj/Performance: Michael Sullivan Mass & Structures: Clifford May Prop/Power: Kevin Diggs CAD: Shae Williams Cost: Michael Thomas

Scientific Philosophy: 

Scientific Philosophy Group Objective: Advance understanding of Martian geology. Deep cores a favored location for learning about Martian geology… Why not use the large hole on Mars naturally present?

Science Traceability Matrix: 

Science Traceability Matrix


Mission Baseline Architecture


Mission Summary Launch Vehicle Delta II 2925-10 provides Earth escape energy (C3) of 9.7 km2/s2 Cruise Stage Cruise stage separation from aeroshell 25 minutes prior to entry Daedalus Glider Data acquisition begins 4000 m above mean datum 4 rocket boosts are performed to regain altitude during flight 67 minutes of flight time

Entry, Descent & Deployment: 

Entry, Descent & Deployment


Mission Profile

Daedalus Glider: 

Daedalus Glider

Flight System Baseline: 

Flight System Baseline Science Platform Baseline: 1 Monopropellant Boosted Autonomous Glider Power: Lithium Thionyl Chloride Batteries - 175 W*hr/kg Propulsion: 1 Aerojet MR-107P 90N engine Communications (Electra System): 1 UHF Antenna Transceiver Guidance Navigation: 1 Honeywell HG 8500 series radar altimeter 1 Honeywell MIMU Navigation Computer integrated with Command & Data Handling System Thermal Control: Aluminum Honeycomb/Graphite-Epoxy Aeroshell MLI Thermal Control Blankets Aerodynamic Characteristics Span - 7 m Aspect Ratio - 7 Average L/D - 16 Aircraft Lift Coefficient - 0.83

Contingencies (for aircraft except where indicated): 

Contingencies (for aircraft except where indicated)

Weight Breakdown Structure: 

Weight Breakdown Structure Aircraft Weight Breakdown

Weight Breakdown Structure, cont’d: 

Weight Breakdown Structure, cont’d Cruise Stage Weight Breakdown

Power Budget: 

Power Budget Cruise Stage Power Budget Aircraft Power Budget Aircraft has 88% Energy Margin

Descope Options: 

Descope Options


Cost $433,365,823.05 30% cost reserves applied to instruments, aircraft/spacecraft, and Phase E


Questions. “That’s sexy.” – Dr. Karen McBride, Mars Scout Director


Deployment Site Entry targeted for the ‘mouth’ of the southern Coprates Chasma, a site of scientific interest Roughly 430 kilometer flight distance allows in depth scientific investigation

Cruise Stage Trajectory: 

Cruise Stage Trajectory

Cruise System Baseline Architecture: 

Cruise System Baseline Architecture Cruise Stage Spacecraft Baseline: Power: Multijunction GaInP/GaAs Solar Cells - 5.5 m^2 Communications: Hi-Gain Parabolic Dish - 1 m (dia) X-band, 8 GHz 2 Alcatel Transponders WR90 waveguide Guidance Navigation & Control: 12 Aerojet MR-50S monopropellant thrusters 3 Goodrich HD-1003 Wide FOV Star Trackers 4 Vectronic Aerospace Reaction Control Wheels type RW-01 Thermal Control: Passive Thermal Control System Structures & Materials: Aluminum Alloys

Internal Packaging: 

Internal Packaging

High-level Trade Studies: 

High-level Trade Studies

Systems Trade Studies: 

Systems Trade Studies

Design Drivers: 

Design Drivers

Key Risks/Mitigations: 

Key Risks/Mitigations

Planetary Protection: 

Planetary Protection Category IVa mission Assembly and packaging of glider and aeroshell in clean room Entire airframe cleaned with alcohol Dry heat microbial reduction used to sterilize glider inside and out $14 million allocated for planetary protection


Project Schedule




Spacecraft Velocity Budget Change this

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