alternatives concepts white paper ipt 02e
DESCRIPTION
Alternatives Concepts White Paper IPT 02E. Team Eclipse. Project Management. Overview. Phase 2 Seek to establishes team roles Develop two alternative designs Select one design as the final concept to take into Phase 3. Design Concepts Viking Lander, the baseline design - PowerPoint PPT PresentationTRANSCRIPT
![Page 1: Alternatives Concepts White Paper IPT 02E](https://reader036.vdocuments.mx/reader036/viewer/2022062500/56814fcb550346895dbd8c93/html5/thumbnails/1.jpg)
Alternatives Concepts White PaperIPT 02E
![Page 2: Alternatives Concepts White Paper IPT 02E](https://reader036.vdocuments.mx/reader036/viewer/2022062500/56814fcb550346895dbd8c93/html5/thumbnails/2.jpg)
Project ManagementThe University of Alabama Huntsville
Team Leader Eddie Kiessling
Structures Nathan Coffee
Systems Engineer Jay Gala
GN & C Brandon York
GN & C Joseph Sandlin
Operations Brett Guin
Thermal Kathryn Kirsh
Thermal Eddie Kiessling
Payload Operations Brent Newson
Power Christopher Goes
Technical Editor Michael Bryan
![Page 3: Alternatives Concepts White Paper IPT 02E](https://reader036.vdocuments.mx/reader036/viewer/2022062500/56814fcb550346895dbd8c93/html5/thumbnails/3.jpg)
Overview
• Phase 2– Seek to establishes team roles– Develop two alternative designs– Select one design as the final concept to take
into Phase 3.
• Design Concepts– Viking Lander, the baseline design– Lander on Wheels (LOW), final design chosen– Lander + Rover
![Page 4: Alternatives Concepts White Paper IPT 02E](https://reader036.vdocuments.mx/reader036/viewer/2022062500/56814fcb550346895dbd8c93/html5/thumbnails/4.jpg)
Technical Description
• Overview of Phase 2:– Deliverable Items:
• White Paper– Summarizes the strategy for selecting alternative
systems– Qualitative/quantitative information to evaluate each idea– Logical rational for down selecting one concept among
the three concepts
• Oral Presentation– Summarizing information from the White Paper to
present to the review board.
![Page 5: Alternatives Concepts White Paper IPT 02E](https://reader036.vdocuments.mx/reader036/viewer/2022062500/56814fcb550346895dbd8c93/html5/thumbnails/5.jpg)
Technical Description
• Specification Summary– Level 1 Requirements
• Housed within an Atlas V-401 EPF Shroud• Total Landed Mass – 997.4 kg• Launch Date – NLT September 30, 2012• Survivability Time of 1 Year• Attain a slope of 12º• Polar Landing as well as other Lunar Landings• Land Precision +/- 100m 3σ• Maneuverability• SMD to ESMD
![Page 6: Alternatives Concepts White Paper IPT 02E](https://reader036.vdocuments.mx/reader036/viewer/2022062500/56814fcb550346895dbd8c93/html5/thumbnails/6.jpg)
Team Eclipse Approach to Phase 2Baseline CDD
Mobility Trade SpaceViking 1 FOM
Customer
Systems Engineer and Team Lead
Power Payload Thermal Structures Operations GN&C
Analysis
Results
![Page 7: Alternatives Concepts White Paper IPT 02E](https://reader036.vdocuments.mx/reader036/viewer/2022062500/56814fcb550346895dbd8c93/html5/thumbnails/7.jpg)
Description of Concepts
• 3 Concepts– Viking Lander (Baseline Design)– Lander on Wheels (Concept 1)– Lander + Rover (Concept 2)
• Selection Process– Advantages and Disadvantages– Weighting of FOMs– Analysis and Comparison
• Concept Chosen: Lander on Wheels (Concept 1)
![Page 8: Alternatives Concepts White Paper IPT 02E](https://reader036.vdocuments.mx/reader036/viewer/2022062500/56814fcb550346895dbd8c93/html5/thumbnails/8.jpg)
Boost Matrix for Project 02Baseline Alternative Concepts
02-BL 02E-ALT1 02E-ALT2
Configuration Category
State Viking Lander on
Wheels Lander +
Rover
Power
RTG Lithium
NiCd Fuel Cell
RTG 2 RTGs
RTG & Rechargeable
Rover
RTG Radiation
Heater Regenerative
Thermal
Radiation
RTG (Heating)
Radiation (Cooling)
RTG (Heating)
Radiation (Cooling)
RTG (Heating)
Radiation (Cooling)
Composite Alloys
Titanium Structure
Aluminum
Aluminum And
Titanium Titanium
Titanium (Lander)
Composite (Rover)
LRO Payload Bay Sample/ Data
Acq./Transmissions Operations
Data Storage
Single Site Science
Multiple Site Science and
Samples
Single Site Science and Multiple Site
Samples
Travel to Sites GN&C
Landing Landing
Landing + Travel to Sites
Landing + Travel to Sites
Shroud (4 m) Payload Bay for
Samples Payload
SRV
N/A Shroud (4m)
SRV Shroud (4m)
SRV
![Page 9: Alternatives Concepts White Paper IPT 02E](https://reader036.vdocuments.mx/reader036/viewer/2022062500/56814fcb550346895dbd8c93/html5/thumbnails/9.jpg)
02-BL “Viking”• Availability of Data• Martian Surface• Single Site Science Mission• Subsystems
– Thermal• Active & Passive
– Structural• Parachute, Bio-shield, & Aero-decelerator
– Redundant Communications– Power
• RTGs & Nickel-Cadmium Batteries– Guidance, Navigation, and Controls
• Three Axis Gyros and Accelerometer & Redundant x-axis system.
![Page 10: Alternatives Concepts White Paper IPT 02E](https://reader036.vdocuments.mx/reader036/viewer/2022062500/56814fcb550346895dbd8c93/html5/thumbnails/10.jpg)
02E-ALT1 “Lander on Wheels”• Power System
– RTGs/ASRGs– Thermal Systems– Heating – Excess energy from RTG– Cooling – Moon’s environment
• Structure– Titanium– 8 Wheel Rocker Bogey Configuration
• Operations– Communicate with LRO & Earth at Direct LOS
• GN & C– Landing Hazard Avoidance– Travel to Scientific Sites
• Payload– Scientific Equipment– SRV
![Page 11: Alternatives Concepts White Paper IPT 02E](https://reader036.vdocuments.mx/reader036/viewer/2022062500/56814fcb550346895dbd8c93/html5/thumbnails/11.jpg)
02E-ALT2 “Lander + Rover”• Power System
– Lander: RTG/ASRG– Rover: Rechargeable battery system
• Thermal Systems– Lander: Heating – Excess energy from RTG– Rover: Heating – Energy from battery system– Lander and Rover: Cooling – Moon’s environment
• Structure– Lander: Titanium– Rover: Composite
• Operations– Communicate with LRO & Earth at Direct LOS
• GN & C– Lander: Landing Hazard Avoidance– Rover: Travel to and from Scientific Sites
• Payload– Scientific Equipment– Rover– SRV
![Page 12: Alternatives Concepts White Paper IPT 02E](https://reader036.vdocuments.mx/reader036/viewer/2022062500/56814fcb550346895dbd8c93/html5/thumbnails/12.jpg)
Selection of Final Concept
• Criteria selection (in order of importance)– Technology Ratio– ConOps– Objectives Completed– Percent Payload– Surface Objectives Completed– Percent Power System
• Chosen Concept– Lander on Wheels (Alternative Concept 01)
![Page 13: Alternatives Concepts White Paper IPT 02E](https://reader036.vdocuments.mx/reader036/viewer/2022062500/56814fcb550346895dbd8c93/html5/thumbnails/13.jpg)
Illustrations02-BL “Viking”
![Page 14: Alternatives Concepts White Paper IPT 02E](https://reader036.vdocuments.mx/reader036/viewer/2022062500/56814fcb550346895dbd8c93/html5/thumbnails/14.jpg)
Illustrations02E-ALT1 “Lander on Wheels”
![Page 15: Alternatives Concepts White Paper IPT 02E](https://reader036.vdocuments.mx/reader036/viewer/2022062500/56814fcb550346895dbd8c93/html5/thumbnails/15.jpg)
IllustrationsShroud Configuration
![Page 16: Alternatives Concepts White Paper IPT 02E](https://reader036.vdocuments.mx/reader036/viewer/2022062500/56814fcb550346895dbd8c93/html5/thumbnails/16.jpg)
Video
![Page 17: Alternatives Concepts White Paper IPT 02E](https://reader036.vdocuments.mx/reader036/viewer/2022062500/56814fcb550346895dbd8c93/html5/thumbnails/17.jpg)
Illustrations02E-ALT2 “Lander + Rover”
![Page 18: Alternatives Concepts White Paper IPT 02E](https://reader036.vdocuments.mx/reader036/viewer/2022062500/56814fcb550346895dbd8c93/html5/thumbnails/18.jpg)
Engineering Summary
• 02E-ALT 1 Lander on Wheels – 700 kg allocated with 300kg or 30% mass to be distributed
• 02E-ALT 2 Lander + Rover– 750 kg allocated with 250 kg or 25% mass to be distributed
02E-BL 02E-ALT1
02E-ALT2
Viking1 Lander
on Wheels
Lander +
Rover NAME Units
1. Lunar Lander Data a) Width m 2 3.5 3.5
b) Length m 3 8 3.5 d) Height m 2 3.5 8
c) Dry Mass kg 576 997.4 997.4 1- Structure kg 90 115
2- Propulsion Dry Mass kg 64.6 64.6 3- Mobility System kg 150 n/a 4- Communications kg 50 70
5- Power kg 15.4 40 20 6- SRV kg 200 200
7- Science Equipment kg 91 120 100 8- Rover kg n/a 200
1 United States. National Aeronautics & Space Administration. Viking.
![Page 19: Alternatives Concepts White Paper IPT 02E](https://reader036.vdocuments.mx/reader036/viewer/2022062500/56814fcb550346895dbd8c93/html5/thumbnails/19.jpg)
Concept Evaluation MatrixScoring Legend
Not Analyzed
N/A
Does Not Meet
0
Meets 5
Exceeds 10
02E-BL 02E-ALT1 02E-ALT2 CDD Figures
Of Merit
Score Weight Viking
Lander on Wheels
Lander + Rover
Goals
Number of Surface
Objectives Completed
2 0 10 10 20
Sites
Percent Payload
2 10 10 5 Maximize Science
SMD to ESMD Ratio
2 10 10 5 2:1
ConOps 3 5 10 5 Efficiency
Percent Power System
2 10 10 10
Minimize Weight
Of Power System
Ratio Of
Off Shelf To
New Technology
3 5 5 10 High Ratio
With TRL Level 9
TOTAL 90.00 125.00 105.00
![Page 20: Alternatives Concepts White Paper IPT 02E](https://reader036.vdocuments.mx/reader036/viewer/2022062500/56814fcb550346895dbd8c93/html5/thumbnails/20.jpg)
Phase 3 Plan
• Key Issues– Power Supply– Single Site Goals Issue– Finalize Mobility Concerns
• Tasks for Partner Universities– Southern University
• Suspension System• CAD Model of Mobility System
– ESTACA University• Design of SRV Propulsion System• CAD Model of SRV
![Page 21: Alternatives Concepts White Paper IPT 02E](https://reader036.vdocuments.mx/reader036/viewer/2022062500/56814fcb550346895dbd8c93/html5/thumbnails/21.jpg)
Review
• Technical Description
• Description of Concepts
• Selection of Final Concept
• Phase 3 Plan