AAE 450 Spring 2010 AAE 450 2/11/2010 Kathy Brumbaugh Chris Spreen

AAE 450 Spring 2010

Agenda AAE 450 Spring 2010 TimeTask 9:30am-9:55amPeer Review 1 9:55am-10:10amPDR Presentation 10:10am-10:15amReminders & Concerns

AAE 450 Spring 2010 Project timeline

AAE 450 Spring 2010

Design Stages - Description StageDescription Mission Design Requirements (MDR) Identification of all subsystems for each group’s tasks. Tasks and steps that need to be accomplished for the subsystems identified Preliminary Design Review (PDR) Exploring all the options for each aspect of the design Generating numbers for each option Communicating these numbers between groups **At end of PDR => Mission architecture possibilities have been identified. Critical Design Review (CDR) Project Managers and Group Leaders will meet to discuss all options and make decision based upon group input and calculations. Choose one option for each aspect of the design (ex. Lake Lander = sub or boat) Investigate and generate numbers for options on that design aspect (ex. What type of propulsion for the Lake Lander?) Work numbers in great detail Communicate between groups with detailed analysis and numbers for each option **At end of CDR => Mission architecture is chosen (ex. Specific engines, propellants, launch vehicle and numbers, fly-by or no fly-by, lake lander & airship configuration) Final Design Review (FDR) Project Managers and Group Leaders meet to incorporate all group discussions into choosing the best overall design including specifics for each category and aspect. Numbers and analysis are now completed in great detail. AAE 450 Spring 2010 Project Managers

Preliminary Design Review  Launch Vehicle = Atlas V Heavy  Launch configuration = all together  Titan Entry configuration = all together  Airship = Blimp  Lake Lander = Floater – raft/pontoon  Option for Ballute w/ Orbiter+Airship+Lake Lander configuration AAE 450 Spring 2010

Launch Vehicle Atlas V HLV  29400kg to LEO(185k m, 28.5deg)  21918kg remaining for 3 rd stage Group Name (i.e.Trajectory Optimization) Source: e/img_lau/atlas-5- hlv__1.jpg e/img_lau/atlas-5- hlv__1.jpg Source: ages/content/161979m ain_dIVhpad.jpg ages/content/161979m ain_dIVhpad.jpg Delta IV Heavy  22977kg to 407km, 28.7deg  15495kg remaining for 3 rd stage  Payload increase for lower orbit

Choices & Other Considerations Atlas V best option  2 nd stage engine has more flights  Has lower acceptable frequency – less s/c structure (Andrew), easier to attach 3 rd stage Group Name (i.e.Trajectory Optimization) AAE 450 Spring rd staging  P&W RL-10 engines  With current payload mass estimates, possible to reach v- inf of 4.7km/s with Atlas V HLV and a sized 3 rd stage

AAE 450 Spring 2010 Collin Morgan Launch Configurations  Single Launch –Pros Allows all vehicles to reach Titan together (good if using ballute) –Cons Payload mass too large to reach required trajectory with only two stages –Propellant mass: kg  Multiple Launches (Launch orbiter separately) –Pros Reduces amount of propellant (per vehicle) to leave LEO Requires only two stages –Cons Cost Unable to have vehicles enter Titan together –Propellant mass: 8785 kg, 7275 kg

Entry Configurations  All three vehicles together –Pros Most efficient way to utilize ballute Very little increase in mass for material and structure of airship (7 kg) –Cons Larger heat shield Possibly more demand on airship propulsion system  Separate Entry –Pros Airship not required to carry lake lander (saves approx. 110 kg from airship propulsion system) Less heat shield mass (only if ballute is not used) –Cons Unable to efficiently utilize ballute AAE 450 Spring 2010 Collin Morgan

Selections  Single Launch –Now must design third stage –Mass of third stage must be less than 20,000 kg  Single Entry –Benefits aerocapture maneuver with ballute and reduces total mass AAE 450 Spring 2010 Collin Morgan

AAE 450 Spring 2010 Adam Coulon Airship Vehicle Options  Hot Air Balloon –Standard Balloon Shape –Science Payload Stored beneath  Hybrid Ballon/Blimp –The Shape of a Blimp –Maintained like a Balloon  UAV type aircraft –Aircraft Design –Must Maintain Flight for 6 th Months

Hybrid Blimp/Balloon  Shaped like a blimp, but maintained like a hot air balloon  ASRG would heat incoming air which would be blown into the envelope  Equipment would be stored below  Considering a ducted fan for propulsion  Controlled mainly by control surfaces and not ballast adjustments Currently Working On… Time required to inflate and become able to fly freely Finalizing overall masses/power/dimensions Detailed design for CAD modeling Finalizing performance capabilities AAE 450 Spring 2010 Adam Coulon

Lake Lander Vehicle Choice  Floater Configuration of Pontoon/Raft Qualities –Failure Contingency –Compartmentalized Structure –Communications Availability –Undesirable Submersible Features Complex Ballast Control Autonomous Subsurface Vehicle Navigation Propulsive Failure AAE 450 Spring 2010 Brandon Kan

Next Objectives  Attitude Controls – Surface stability and probe control  Power – Electric and Thermal Power Output, Budgeting  Propulsion – Distance and Time Requirements  Hydrodynamics – Drag and Shape  Communication – Antenna Size, Storage, Location  Structures – Winch system, Hull and Spars  Trajectory – Airship and Lake Lander combined drop, reduced entry and descent complexities  Science – Probe design AAE 450 Spring 2010 Brandon Kan

Reminders & Concerns  Subgroup spreadsheet – UPDATE! PMW1nRzRrZ0E&hl=en  Presentation feedback: –Buffer/Margin = 20% (Detail numbers before and after including this margin) –Include your past weeks’ research on the title slide –Consider the end of the mission => what does that mean for your portion of the project? –If want to know what to work on…read feedback! Ask PM, GLs. –Make conclusions/recommendations –Use updated numbers (spreadsheet) – response is CRUCIAL! –USE OUR RESOURCES!!! –Ballute analysis; Aerocapture simulation (simulations in general)  Additional tasks – who needs more to do?  Section 1 – Critical Design slides due Sun. 5pm AAE 450 Spring 2010