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David Mauro, KBR / NASA Ames Research Center [email protected] 1
Space Mission Concept Design
at the NASA Ames Mission Design Center (MDC)
Stanford University
David Mauro, KBR / NASA Ames Research Center
Agenda
2David Mauro, KBR / NASA Ames Research Center [email protected]
• Space Mission Concept Design at NASA Ames• What the Ames MDC is• A framework for space mission ideas – The Concept Maturity Levels• Aeolus: an example of a mission concept study for Mars• Lessons learned and tips
• Overview on how to design a spacecraft telecommunication subsystem• Overview on the main design considerations• The Link Budget
• Summary & Conclusion
Mission Design Center - What is it?
https://www.nasa.gov/centers/ames/engineering/mission-design-center/about
3David Mauro, KBR / NASA Ames Research Center [email protected]
Credit: Amanda Waltz
5David Mauro, KBR / NASA Ames Research Center [email protected]
A framework for space mission ideas
The Concept Maturity Levels
From: Space Mission Concept Development Using Concept Maturity Levels, Wessen et al., 2013
6David Mauro, KBR / NASA Ames Research Center [email protected]
7David Mauro, KBR / NASA Ames Research Center [email protected]
Aeolus: an example of a mission concept study for
Mars
8
CML 1
“Cocktail Napkin”
David Mauro, KBR / NASA Ames Research Center [email protected]
Aeolus: an example of a mission concept study for
Mars
9
CML 1
“Cocktail Napkin”
David Mauro, KBR / NASA Ames Research Center [email protected]
Aeolus: an example of a mission concept study for
Mars
10
CML 1
“Cocktail Napkin”
David Mauro, KBR / NASA Ames Research Center [email protected]
Aeolus: an example of a mission concept study for
Mars
11
CML 1
“Cocktail Napkin”
David Mauro, KBR / NASA Ames Research Center [email protected]
Opportunity December 2011 (Credit NASA)
Aeolus: an example of a mission concept study for
Mars
CML 1: Initial Cartoon
Meaningfulness & Uniqueness
Identify Knowledge Gaps
State Broad Science Objective
One-sentence description of measurement(s)
12David Mauro, KBR / NASA Ames Research Center [email protected]
CML 1
“Cocktail Napkin”
CML 2
Feasibility
Does any
solution
exist?
Aeolus: an example of a mission concept study for
Mars
13David Mauro, KBR / NASA Ames Research Center [email protected]
CML 2: Feasibility Study
Resource CBE
Volume45 x 35 x 52
cm Total Launch Mass 37.6 kg
Total Power 53 W
Spacecraft Delta-V 237.5 m/sSolid State Data Storage (Vol)
8GB
Data Throughput (UHF Downlink)
1Mbps
Draft of Science Traceability Matrix
Mission Architecture – main elements
Environmental driving parameters
Identify required tech development
Launch opportunities
Delta-V calculations
Orbital solutions
Mission ops
Spacecraft CAD model
Rough cost estimate
Rough schedule
Initial risks & mitigation identified
Future trades identified
14David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Link Budget
Orbital Mechanic
Power Budget
Propellant budget
ADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost
15David Mauro, KBR / NASA Ames Research Center [email protected]
Mission Concept
LaunchCruise 15 months
17David Mauro, KBR / NASA Ames Research Center [email protected]
Mission Concept
LaunchCruise 15 months
NeMO LTT10 months
18David Mauro, KBR / NASA Ames Research Center [email protected]
Mission Concept
LaunchAeolus Stowed
Cruise 15 months
NeMO LTT10 months
19David Mauro, KBR / NASA Ames Research Center [email protected]
Mission Concept
AeolusDeploy
LaunchAeolus Stowed
Cruise 15 months
NeMO LTT10 months
20David Mauro, KBR / NASA Ames Research Center [email protected]
Mission Concept
Orbit Transfer
AeolusDeploy
LaunchAeolus Stowed
Cruise 15 months
NeMO LTT10 months
21David Mauro, KBR / NASA Ames Research Center [email protected]
Mission Concept
Orbit Transfer
AeolusDeploy
LaunchAeolus Stowed
Cruise 15 months
NeMO LTT10 months
Commiss. 3 months
22David Mauro, KBR / NASA Ames Research Center [email protected]
Mission Concept
Orbit Transfer
AeolusDeploy
LaunchAeolus Stowed
Cruise 15 months
NeMO LTT10 months
Science24 months
Commiss. 3 months
23David Mauro, KBR / NASA Ames Research Center [email protected]
Mission Concept
Science24 months
Orbit Transfer
AeolusDeploy
LaunchAeolus Stowed
Cruise 15 months
NeMO LTT10 months
Commiss. 3 months
Decommission
Total Mission Duration
52 months
24David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
25David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
26David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
27David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
28David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
29David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
30David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
31David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
32David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
33David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
34David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
35David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
36David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
37David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
38David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
39David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
40David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
41David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
42David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
43David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
44David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
45David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
46David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
47David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
48David Mauro, KBR / NASA Ames Research Center [email protected]
Develop Feasible Mission Architecture
Orbital Mechanic
Power BudgetADCS
CAD Visualization
Mass Budget
Data Budget
Concept of Operations
Science
Risks & Tech Dev
Cost Link Budget 𝐸𝑏
𝑁𝑜𝑑𝐵 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 𝑆𝑝𝑎𝑐𝑒, 𝑝𝑜𝑖𝑛𝑡𝑖𝑛𝑔, 𝑐𝑎𝑏𝑙𝑒𝑠 +
G
T− dataratedB + 228.6
Propellant budget
∆𝑉 = 𝑔 ∙ 𝐼𝑠𝑝 ∙ ln𝑀𝑓𝑖𝑛𝑎𝑙
𝑀𝑖𝑛𝑖𝑡𝑖𝑎𝑙
49David Mauro, KBR / NASA Ames Research Center [email protected]
50
CML 1
“Cocktail Napkin”
CML 2
FeasibilityCML 3
Expanded Trade
SpaceDoes any
solution
exist?
What other
solutions
exist?
Aeolus: an example of a mission concept study for
Mars
50David Mauro, KBR / NASA Ames Research Center [email protected]
CML 3: Expanded Trade Space
Divergent Phase:
Explore different mission architectures
primary vs. secondary
launch options
number of spacecrafts
et cetera
Convergent Phase:
Identify rejection criteria & pick
architectures to pursue.
Iteration:
Repeat CML 2 as needed on
selected architectures
51David Mauro, KBR / NASA Ames Research Center [email protected]
52
CML 1
“Cocktail Napkin”
CML 2
FeasibilityCML 3
Expanded Trade
Space
CML 4
Point Design
Does any
solution
exist?
What other
solutions
exist?
What is a good
approach, given our
circumstances?
Aeolus: an example of a mission concept study for
Mars
52David Mauro, KBR / NASA Ames Research Center [email protected]
CML 4: Point Design
53
Power analysis
Thermal analysis
Schedule
Science Traceability Matrix
Mission Architecture
Driving environmental parameters
Launch vehicle
Delta-V calculations
Orbital solution
Radiation Analysis
Mission ops
Identify required tech development
Spacecraft CAD model
Power Analysis
Thermal Analysis
Better Cost Estimate
Refined Schedule
Risks Matrix & Mitigation
53David Mauro, KBR / NASA Ames Research Center [email protected]
CML 4: Point Design
54
Science Traceability Matrix
Mission Architecture
Driving environmental parameters
Launch vehicle
Delta-V calculations
Orbital solution
Radiation Analysis
Mission ops
Identify required tech development
Spacecraft CAD model
Power Analysis
Thermal Analysis
Better Cost Estimate
Refined Schedule
Risks Matrix & Mitigation
2 weeks operational cycle
54David Mauro, KBR / NASA Ames Research Center [email protected]
CML 4: Point Design
55
Refined orbit design
Science Traceability Matrix
Mission Architecture
Driving environmental parameters
Launch vehicle
Delta-V calculations
Orbital solution
Radiation Analysis
Mission ops
Identify required tech development
Spacecraft CAD model
Power Analysis
Thermal Analysis
Better Cost Estimate
Refined Schedule
Risks Matrix & Mitigation
55David Mauro, KBR / NASA Ames Research Center [email protected]
CML 4: Point Design
56
Refined Flight system capabilitiesScience Traceability Matrix
Mission Architecture
Driving environmental parameters
Launch vehicle
Delta-V calculations
Orbital solution
Radiation Analysis
Mission ops
Identify required tech development
Spacecraft CAD model
Power Analysis
Thermal Analysis
Better Cost Estimate
Refined Schedule
Risks Matrix & Mitigation
+X (along track)
-Y (cross-track)
+Z (Zenith)
56David Mauro, KBR / NASA Ames Research Center [email protected]
Maturation of a Concept from CML 1 to CML 4
CML 1
CML 2
CML 4
57David Mauro, KBR / NASA Ames Research Center [email protected]
Science & Engineering
Lessons learned
59David Mauro, KBR / NASA Ames Research Center [email protected]
Science & Engineering
Programmatic Constraints
Lessons learned
60David Mauro, KBR / NASA Ames Research Center [email protected]
Science & Engineering Team Dynamics
Programmatic Constraints
Lessons learned
61David Mauro, KBR / NASA Ames Research Center [email protected]
Science & Engineering Team Dynamics
Programmatic Constraints
Life
Lessons learned
62David Mauro, KBR / NASA Ames Research Center [email protected]
• Meeting Ground Rules
Practical tips and best practices
63David Mauro, KBR / NASA Ames Research Center [email protected]
• Meeting Ground Rules
• Check out smartphone/tablet/pc at the door unless working session
Practical tips and best practices
64David Mauro, KBR / NASA Ames Research Center [email protected]
• Meeting Ground Rules
• Check out smartphone/tablet/pc at the door unless working session
• Prepare meeting in advance:
• Agenda & expected outcome
• Assign preliminary work
Practical tips and best practices
65David Mauro, KBR / NASA Ames Research Center [email protected]
• Meeting Ground Rules
• Check out smartphone/tablet/pc at the door unless working session
• Prepare meeting in advance:
• Agenda & expected outcome
• Assign preliminary work
• Brainstorming: use diverse options
Practical tips and best practices
66David Mauro, KBR / NASA Ames Research Center [email protected]
• Meeting Ground Rules
• Check out smartphone/tablet/pc at the door unless working session
• Prepare meeting in advance:
• Agenda & expected outcome
• Assign preliminary work
• Brainstorming: use diverse options
• Action Items: assign & review
Practical tips and best practices
67David Mauro, KBR / NASA Ames Research Center [email protected]
• Meeting Ground Rules
• Check out smartphone/tablet/pc at the door unless working session
• Prepare meeting in advance:
• Agenda & expected outcome
• Assign preliminary work
• Brainstorming: use diverse options
• Action Items: assign & review
• Do meetings only if needed
Practical tips and best practices
68David Mauro, KBR / NASA Ames Research Center [email protected]
• Meeting Ground Rules
• Check out smartphone/tablet/pc at the door unless working session
• Prepare meeting in advance:
• Agenda & expected outcome
• Assign preliminary work
• Brainstorming: use diverse options
• Action Items: assign & review
• Do meetings only if needed
• Scrum Wall
Practical tips and best practices
69David Mauro, KBR / NASA Ames Research Center [email protected]
• Meeting Ground Rules
• Check out smartphone/tablet/pc at the door unless working session
• Prepare meeting in advance:
• Agenda & expected outcome
• Assign preliminary work
• Brainstorming: use diverse options
• Action Items: assign & review
• Do meetings only if needed
• Scrum Wall
Practical tips and best practices
70David Mauro, KBR / NASA Ames Research Center [email protected]
• Meeting Ground Rules
• Check out smartphone/tablet/pc at the door unless working session
• Prepare meeting in advance:
• Agenda & expected outcome
• Assign preliminary work
• Brainstorming: use diverse options
• Action Items: assign & review
• Do meetings only if needed
• Scrum Wall
• Include Cost & Schedule early in the process
Practical tips and best practices
71David Mauro, KBR / NASA Ames Research Center [email protected]
• Meeting Ground Rules
• Check out smartphone/tablet/pc at the door unless working session
• Prepare meeting in advance:
• Agenda & expected outcome
• Assign preliminary work
• Brainstorming: use diverse options
• Action Items: assign & review
• Do meetings only if needed
• Scrum Wall
• Include Cost & Schedule early in the process
• No to “NO” and the power of positive language
Practical tips and best practices
72David Mauro, KBR / NASA Ames Research Center [email protected]
• Meeting Ground Rules
• Check out smartphone/tablet/pc at the door unless working session
• Prepare meeting in advance:
• Agenda & expected outcome
• Assign preliminary work
• Brainstorming: use diverse options
• Action Items: assign & review
• Do meetings only if needed
• Scrum Wall
• Include Cost & Schedule early in the process
• No to “NO” and the power of positive language
• Awareness of Team Dynamics & Life
Practical tips and best practices
73David Mauro, KBR / NASA Ames Research Center [email protected]
Spacecraft Telecomm Sub-System
76David Mauro, KBR / NASA Ames Research Center [email protected]
Uplink / Command
Spacecraft Telecomm Sub-System
77David Mauro, KBR / NASA Ames Research Center [email protected]
Uplink / Command
Downlink / Telemetry
Spacecraft Telecomm Sub-System
78David Mauro, KBR / NASA Ames Research Center [email protected]
RadioTx / Rx
TX
RX
Uplink / Command
Downlink / Telemetry
Spacecraft Telecomm Sub-System
79David Mauro, KBR / NASA Ames Research Center [email protected]
RadioTx / Rx
TX
RX
Uplink / Command
Downlink / Telemetry
Link Margin = 𝐸𝑏
𝑁𝑜𝑑𝐵 received -
𝐸𝑏
𝑁𝑜𝑑𝐵 required
Spacecraft Telecomm Sub-System
80David Mauro, KBR / NASA Ames Research Center [email protected]
RadioTx / Rx
TX
RX
Uplink / Command
Downlink / Telemetry
Link Margin = 𝐸𝑏
𝑁𝑜𝑑𝐵 received -
𝐸𝑏
𝑁𝑜𝑑𝐵 required
• Aim to a value of 6dB or 10 dB for early concept
•𝐸𝑏
𝑁𝑜𝑑𝐵 required is a function of channel coding/modulation. It is the
threshold value of energy in order for the bit to be received.
• BPSK modulation with no channel coding has a Eb/No required ~ 9.6 dB for example
Spacecraft Telecomm Sub-System
81David Mauro, KBR / NASA Ames Research Center [email protected]
RadioTx / Rx
TX
RX
Uplink / Command
Downlink / Telemetry
𝐸𝑏
𝑁𝑜𝑑𝐵 𝑟𝑒𝑐𝑒𝑖𝑣𝑒𝑑 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 +
G
T− dataratedB + 228.6
Link Margin = 𝐸𝑏
𝑁𝑜𝑑𝐵 received -
𝐸𝑏
𝑁𝑜𝑑𝐵 required
Spacecraft Telecomm Sub-System
82David Mauro, KBR / NASA Ames Research Center [email protected]
RadioTx / Rx
TX
RX
Uplink / Command
Downlink / Telemetry
𝑆𝑝𝑎𝑐𝑒 𝐿𝑜𝑠𝑠 𝑑𝐵 = 147.55 − 20log(𝑅𝑎𝑛𝑔𝑒,𝑚) − 20log(𝐹𝑟𝑒𝑞, 𝐻𝑧)
𝐸𝑏
𝑁𝑜𝑑𝐵 𝑟𝑒𝑐𝑒𝑖𝑣𝑒𝑑 = 𝐸𝐼𝑅𝑃 + 𝐿𝑜𝑠𝑠𝑒𝑠 +
G
T− dataratedB + 228.6
Link Margin = 𝐸𝑏
𝑁𝑜𝑑𝐵 received -
𝐸𝑏
𝑁𝑜𝑑𝐵 required
How to do a Link Budget
𝑆𝑝𝑎𝑐𝑒 𝐿𝑜𝑠𝑠 𝑑𝐵 = 147.55 − 20log(𝑅𝑎𝑛𝑔𝑒,𝑚) − 20log(𝐹𝑟𝑒𝑞, 𝐻𝑧)
Link Margin = 𝐸𝑏
𝑁𝑜𝑑𝐵 received -
𝐸𝑏
𝑁𝑜𝑑𝐵 required
EIRP = W RF Out dB + Antenna Gain dB – Cable Loss dB
83David Mauro, KBR / NASA Ames Research Center [email protected]
