Contents include the following: Capability Description, Benefits, Current State-of-the-Art. Capability Requirements and Assumptions. Maturity Level - Capabilities. Maturity Level - Technologies. Metrics. Roadmap for Capability

Manning, Rob

NASA Technical Reports Server

1Section 9:
A-Prior Observations
Rob Manning
https://ntrs.nasa.gov/search.jsp?R=20050205030 2019-08-29T19:19:01+00:00Z
2Agenda
Capability Description, Benefits, Current State-of-the-Art•
Capability Requirements and Assumptions•
Maturity Level - Capabilities •
Maturity Level - Technologies•
Metrics•
Roadmap for Capability•
3Capability Breakdown Structure
Human Planetary
Landing Systems
CRM # 7
AEDL Human
Mission Drivers
1.0
AEDL Systems
Engineering
2.0
AEDL
Communication
& Navigation
3.0
Hypersonic
Systems
4.0
Supersonic
Decelerators
5.0
Terminal
Descent
& Landing
6.0
A Priori
Observations
9.0
AEDL Analysis
& Validation
Infrastructure
10.0
9.1 Orbital reconnaissance 
requirements for surface site 
characterization.
9.2 Orbital reconnaissance 
requirements for atmospheric 
characterization
9.3 Robotic EDL measurements
49.1 Orbital Reconnaissance for Lunar and Mars site characterization
Utilize existing and planned orbital and terrestrial-based surface –
observations to characterize and develop the surface site landing 
models & requirements for Lunar & Mars AEDL systems.
9.2 Orbital reconnaissance for Mars atmospheric characterization.
Utilize existing and planned orbital and terrestrial-based Mars –
atmosphere observations to characterize and develop the atmosphere 
models & requirements for Mars AEDL systems. (Earth atmospheric 
characterization is not required for Lunar and Mars return)
9.3 Robotic EDL measurements
Utilize existing and planned in-situ EDL reconstruction data to –
Validate current and future atmosphere models •
Validate vehicle aerodynamic & aeroheating modeling process•
Develop the in-situ measurement systems (a.k.a. EDL instrumentation) –
that acquire above reconstruction data.
A Priori Observations Capability 
Description
5Benefits
Ultimately the benefits from this roadmap are ones of human safety 
and AEDL system design efficacy. Specifically:
9.1 Orbital Reconnaissance for Lunar and Mars site characterization
For Lunar & Mars Landing: Acquisition of site images with <1 m –
resolution from orbit enables safe site selection and use of imagery for 
terrain-relative navigation for pin point landing.
9.2 Orbital reconnaissance for Mars atmospheric characterization.
Characterization of the relevant variation of the Mars atmosphere (over –
multi-year timescales) will enable the design of a safe Human Scale 
AEDL system.
We do not know if we are under-designing or over-designing our AEDL •
systems.
9.3 Robotic EDL measurements
In-situ measurements taken during EDL (and after) will validate the –
models that are created based on long term atmosphere observations.
In-situ measurements taken during EDL will validate the processes –
used to construct AEDL system aero-database and aeroheating models 
that are created based on long term observations.
6State of the Art
9.1 Orbital Reconnaissance for Lunar and Mars site characterization
Lunar state of the art: –
100 - 200 m resolution, global coverage (Clementine).•
Mars state of the art: –
100 - 200 m resolution (Viking, MGS, Odyssey, Mar Express)•
global coverage, small % with 3 m coverage•
100 m global topographic elevation data.•
9.2 Orbital reconnaissance for Mars atmospheric characterization.
2-3 km vertical resolution thermal (density) profiles at 100 km centers at 2 –
pm local solar time (MGS TES)
Minimal data on vertical dust distribution and its diurnal, seasonal and –
long term variability. 
Minimal wind data in 2 - 70 km range (some reconstructed data from 5 –
landings), however unvalidated Mesoscale wind models exist at 2 sites.
9.3 Robotic EDL measurements
Partial aero-reconstruction performed for Viking,MPF & MER based on –
IMU data.
Aerothermal (TPS) reconstruction performed for Viking and some for MPF.–
No external pressure data.–
7Assumptions
Lunar reconnaissance orbiter before 2014•
Mars reconnaissance orbiter before 2009•
Acquires 0.3 m resolution imagery of key landing sites.–
Assume that the first human scale landings on Mars will be at locations •
that have been well characterized by MRO.
2-3 km vertical resolution thermal (density) atmosphere profiles at –
100 km centers. 
Future Mars orbiter mission(s) between 2013-2020 will have •
characterized the long term variability of the Mars atmosphere 
to enable detailed design of Human Scale AEDL system.
Better than 0.1 km resolution vertical thermal (density) atmosphere –
profiles at 10 km centers - all times of day.
Dust transport measurements between 2 - 100 km.–
Better than 0.1 km resolution vertical wind profiles at 2 km centers.–
Future Mars landers will be instrumented to measure •
atmosphere pressure, temp, dynamic pressure, aeroheating.
8Technology Maturity Level
9.1 Orbital Reconnaissance for Lunar and Mars site characterization
Sub meter optical resolution technology is at TRL 6, just need to do it.–
Global assessment at submeter resolution is difficult due to large data –
volumes - > could take many years at today’s communication 
capabilities.
9.2 Orbital reconnaissance for Mars atmospheric characterization.
For sub km density, thermal technology is at TRL 4-5.–
For sub km dust profiling, technology is at TRL 1-2.–
For sub km wind profiling, technology is at TRL 1-2.–
9.3 Robotic EDL measurements
Aerothermal measurement technology is at TRL4-6–
Aerodynamic (IMU) measurement technology is at TRL 6–
Pressure / wind measurement technology is at TRL 2-4–
9Technology Gaps
9.1 Orbital Reconnaissance for Lunar and Mars site 
characterization
If global high resolution optical imagery is required for site –
selection (not obvious that it is), then higher data volume 
orbiter data delivery systems are required.
9.2 Orbital reconnaissance for Mars atmospheric 
characterization.
Need to develop Doppler (LIDAR-like) limb sounding of dust for –
dust distribution and large scale wind.
Other than “spotty” multiple landers (equivalent terrestrial –
weather balloon measurements), there are few options for 
higher resolution wind and density measurements. 
9.3 Robotic EDL measurements
Need to develop small pressure/temp transducers for –
aerosurfaces (thermal & mass challenge).
Need high rate IMU (inertial measurement) data.–
10
Metrics
9.1 Orbital Reconnaissance for Lunar and Mars site 
characterization
Percent coverage at sub-meter spatial resolution.–
9.2 Orbital reconnaissance for Mars atmospheric 
characterization.
The extent that high resolution (sub km) global “mesosphere” –
atmosphere models have been validated with actual 
measurements.
9.3 Robotic EDL measurements
The extent that an EDL landing’s reconstructed atmosphere –
validates the corresponding atmosphere as measured from 
orbit.
The extent that the reconstructed EDL trajectories can be –
explained by the atmosphere and aerodynamic models. 
The extent that the reconstructed EDL aerothermal profiles –
can be explained by the atmosphere and EDL trajectories.
2005 2010 2015
Launch orbiter-based Mars Atmosphere Recon.
Capability 
Roadmap 
#7: HPLS
2017 Human Lunar 
Missions
7.9 A Priori Measurements
Key Assumptions:
Team 7.9: A Priori Measurements  Roadmap 
Begin AEDL 
System 
Design 
Modeling 
Major Event / Accomplishment / Milestone
Ready to Use
Ensemble of 
Evaluation 
Architectures 
Selected
AEDLA System 
Architecture 
Down select 
Capability to begin 
scaled Fly-off Tests 
(Earth) for System 
downselect
2006 MRO 
Surface site 
Characterization
Pin point landing at Mars (MSL)
Project Start of 
Sub Scaled 
Mars Flight 
Model Validation 
Test. (phase A)
AEDL Subscale 
System at CRL 3
0.3 m Mars (MRO)  
Site Characterization
TRL 5 Sub Scale CRL 1
Decision Point
7.9.1 Orbital Reconnaissance for Site Characterization
7.9.2 Orbital Reconnaissance for Atm. Characterization
7.9.3 Robotic EDL Measurements
Coverage of Human 
Scale Landing Sites 
Complete.
0.3 m Lunar Site 
Characterization
Coverage of Human 
Scale Landing Sites 
Complete.
Acquire 1 km vert. resolution density data (MRO)
Develop orb. wind/dust measurement technology
TRL 3 TRL 6 Acquire 0.1 km vert. resolution density data 
Develop aeroshell transducer technology
TRL 3 TRL 6
Incorporate EDL reconstruction data into models
Reconstruct PHX EDL 
data into models
Reconstruct MSL 
EDL data into models
Reconstruct MSL 
EDL data into models
Incorporate reconstruction data into 
models
Incorporate MRO  data into models
Capability Roadmap 7: 
HLPS
Key Assumptions:
Begin Full Scale 
(Earth) 
Development
Major Event / Accomplishment / Milestone
Ready to Use
Sub Scale AEDL 
Capability Exists: System 
Model validated at Mars
2020 2025 2030
Sub Scaled Mars 
Flight Model 
Validation Project 
PDR
PDR Full scale 
Flight Tests 
(Earth)
Project start of First 
Mars Human Mission
PDR
AEDL Human Scale Sys Capability  
Qualified for Flt (CRL 5)
Launch Landing
AEDL Human Scale 
System at  (CRL  1)
Launch First Human 
Mission to Mars
CRL 5 AEDL Human 
Scale 
Operational 
(CRL 7)
AEDL Human Scale 
System at  (CRL  3)
Subscale AEDL Model 
Validation Mission Launch
Launch
Decision Point
7.9 A Priori Measurements
7.9.1 Orbital Reconnaissance for Site Characterization
7.9.2 Orbital Reconnaissance for Atm. Characterization
7.9.3 Robotic EDL Measurements
Acquire 0.1 km vert. resolution density, 
dust & wind data 
Incorporate orbital data into models
Validate  Scaled EDL 
with measurement 
model
Team 7.9: A Priori Measurements  Roadmap 
Mars Human 
Landing Site 
Selection
Complete 3 Mars Year Atm. 
Characterization
Validated 
Wind/Density 
Model
Updated 
Density, Dust & 
Wind Models
13
A Priori Observation Summary
In order to design high reliability Human Scale •
AEDL systems for Mars, the models of the Mars 
atmosphere we use today need to be validated 
with actual data.
Measurements of dust, dust storms and its affects on –
density needs to be understood (especially variance).
Measurements winds, wind shears in the range of 2-70 –
km needs to be gathered.
A multi-year global weather observer orbiter is needed.–
Measurements of actual AEDL performance must •
be made to validate the modeling methodologies 
used to design today’s robotic EDL systems so 
that these same methodologies may be used to 
design the Human Scale AEDL systems for Mars.


A-Prior Observations

Abstract

Similar works

Full text

Available Versions

NASA Technical Reports Server