Technology Risk DSM Analysis for Indian Space Exploration Missions - AIAA SPACE 2013 VPS

1. Complex Project Interface and Technology Risk Assessment
utilizing DSM Methods for Indian Space Exploration Missions
AIAA SPACE 2013 Conference
By
Prasad Sundararajan

2. Indian Space Exploration Missions Technology Risk Assessment
Indian Space Program
 Earth Observation (IRS, INSAT, IRNSS)
 Space Science & Planetary Exploration
Design/Dependency Structure Matrix [DSM]
Chandrayaan-I Mission
 India’s first deep space mission
 Discoveries of the mission
 Interface DSM and Technology Risk DSM
Indian Mars Orbiter (“Mangalyaan”) Mission
 India’s first interplanetary mission to the Red Planet
 Technology Risk DSM
Astrosat-1 Mission
 Multi-wavelength Astronomy Satellite
 Technology Risk DSM

3. Indian Space Exploration Missions Technology Risk Assessment
A PSLV launch by ISRO

4. Indian Space Exploration Missions Technology Risk Assessment
Design/ Dependency Structure Matrix (DSM)
– A Systems Engineering Management Tool for
gaining insights on architectural and Integration
benefits in complex engineering product/ process.
 DSM is an N x N matrix network modeling tool
 Represent the elements/ components in a complex
engineering system and their interactions/ interfaces
in a graphical matrix format.
 Highlight the product system’s architecture, the
principal design and project implementation behavior
in the development of the complex product.

5. Indian Space Exploration Missions Technology Risk Assessment
The Design/ Dependency Structure Matrix (DSM)
A B C D E F G H
A
X
B
C X
X
D
X
X
E X
F
X
X
G
X
X
H X
X
Task A depends
on information
from Task E
Task C and D
must be done
concurrently

6. Indian Space Exploration Missions Technology Risk Assessment
Interface DSM
 Consists of a component interface dependency
section and a section identifying the
dependencies of components on the operational
phases.
 The interface dependency value assigned to the
DSM cell is obtained by summing values
representing the physical, energy and
information interactions that exist between a pair
of elements.
 The purpose of the rating is to identify the
spacecraft component interfaces with high
interdependence and to identify critical
components for the operational phases.

7. Indian Space Exploration Missions Technology Risk Assessment
Matrix Values for Strength of Component Interface Dependencies
Type of Element Interaction
Physical Interface - a direct physical interface exists in the
defined system architecture
Energy Interface - a direct energy transfer exists between
components such as power, propulsion, or thermal loads
Information interface a) direct transfer of information between the components
b) indirect information exchanged between the
components
Points
2
2
2
1
Matrix Values for Strength of Operation's dependence on a Component
Type of component interaction during
critical operations phase
Essential component - a single point or major component
failure can cause failure in the specific operational phase
Critical component - a single point or major component
failure can cause degraded operations during the specific
operational phase
Points
4
2

8. Indian Space Exploration Missions Technology Risk Assessment
TRF
NASA Technology Readiness Level (TRL) Definition
TRL
1
Actual system 'flight proven' through successful mission operations
9
2
2
Actual system completed and "flight qualified" through test and demonstration
System prototype in a space environment
8
7
3
4
4
System/ subsystem model or prototype demonstrated in a relevant environment
Component validation in relevant environment
Component validation in laboratory environment
6
5
4
5
5
5
Analytical and experimental critical function and/ or characteristic proof-of-concept
Technology concept and/or application formulated
Basic principles observed and reported
3
2
1
TRF of
Component
A
X
TRF of
Component
B
X
Interface
dependence
value between
A and B
=
TR-DSM matrix
value for A-B
interface

9. Indian Space Exploration Missions Technology Risk Assessment
Technology Risk DSM
 The technology risk DSM is intended to provide
an overall view of the project’s technological and
operational risk areas
 TR-DSM can be utilized as an analytical tool
throughout a project’s development life cycle for
identifying and communicating high-risk areas in
a single system view.
 The high TRF values identify the components/
subsystems that require a thorough mitigation
strategy during development.

10. Chandrayaan-1 Mission
Objectives:
Place an unmanned spacecraft in polar
orbit around the moon
Conduct mineralogical and chemical
mapping of the entire lunar surface (95%)
Upgrade technological base for future
planetary missions
Orbit: Lunar Polar Orbit at 100 KM Circular
Launched by Indian PSLV XL.
Timeline: Oct 22, 2008 - Aug 29, 2009
Spacecraft:
Basic architecture derived from the IRS
satellite bus, Spacecraft mass 1380 kg.
Single solar panel generated 700 W power.
Onboard liquid engine with 440 N
performed orbit raising maneuvers.
Eleven Science Instruments
(ISRO - 5, NASA - 2, ESA - 3, Bulgaria - 1)
Credit: NASA/ ISRO

11. Credit: ISRO

12. Magmatic Water detected
on Moon’s Surface at
Bullialdus impact crater
by M3 Instrument carried
aboard Chandrayaan-1
- NASA, August 27, 2013
Credit: NASA/APL/ USGS

13. Indian Space Exploration Missions Technology Risk Assessment

14. Indian Space Exploration Missions Technology Risk Assessment

15. Indian Space Exploration Missions Technology Risk Assessment
India’s First Interplanetary Mission to the Red Planet
Credit: ISRO Annual Report 2012-13

16. Indian Space Exploration Missions Technology Risk Assessment
Credit: ISRO

17. Indian Space Exploration Missions Technology Risk Assessment
Science Objectives of
Indian Mars Orbiter Mission:
Exploration of Martian Surface Features
 Morphology
 Topography
 Mineralogy
Study of Martian Upper Atmosphere
 Detect and measure Methane with an
accuracy of ppb
 Explore the Martian Exosphere
(>= 400 km above the surface of Mars)
neutral density and composition
Optical Imaging
 Mars
 Phobos and Deimos
 Context for Science Payloads

18. Indian Space Exploration Missions Technology Risk Assessment
Indian Mars Orbiter
Science Payloads
Payload
Mass
(kg)
Primary Scientific Objective
Lyman Alpha Photometer (LAP)
1.5
Methane Sensor for MARS (MSM)
3.6
Escape processes of Mars upper atmosphere through
Deuterium/Hydrogen
Detect presence of Methane
Martian Exospheric Composition
Explorer (MENCA)
MARS Color Camera (MCC)
4.3
Study the neutral composition of the Martian upper atmosphere
1.4
Optical imaging
TIR imaging spectrometer (TIS)
4.0
Map surface composition and mineralogy

19. Indian Space Exploration Missions Technology Risk Assessment

20. Astrosat-1 Mission
Objectives:
 To carry out simultaneous observations
of cosmic sources for high resolution
timing, spectral and imaging studies.
 High-resolution UV imaging for
morphological studies of galactic and
extragalactic objects
Orbit: Circular near equatorial orbit of
about 650 km altitude with orbital inclination
of 8 degrees
Timeline: 2014 - 2018
Spacecraft:
Basic architecture derived from Cartosat
satellite bus, Spacecraft mass 1600 kg.
Two solar panels generating 1,250 Watts.
Credit: ISRO
Pointing accuracy is < 0.05º and 0.2
arcsec/s drift.
Five Science Instruments (mass: 868 kg)
Single Solid State Recorder: 120 Gb

21. Indian Space Exploration Missions Technology Risk Assessment