Index
Note: Page numbers with “f” denote figures; “t” tables.
A
Abbreviated injury scale (AIS), ,
832
of Association for Advancement of Automotive Medicine,
3–4
Abrupt hard-over nozzle failures,
104–105
ABS
see American Bureau of Shipping
Acceleration expressions,
618
Accumulated risks,
Active spacecraft charging control,
533
Defense Satellite Communication System-III B-7 satellite,
533–534
Acute Exposure Guideline Level (AEGL),
213–214
Advanced Stirling Radioisotope Generator (ASRG),
260–261
panel wise response analysis,
655
transitional heating calculation,
654
flow regimes
aerodynamic coefficients,
616
energy accommodation coefficient,
617
heat transfer Stanton number,
616–617
non-dimensional Knudsen number,
615–616
Affordable Fission Surface Power System (AFSPS),
264–265
Air
traffic control organizations,
778–779
Air-space traffic interface management,
777
Airborne Surveillance Testbed (AST),
176
alternative approaches
probability of impact
vs. flight azimuth,
789,
790f
catastrophic consequences,
777
computing risk
aircraft areas and motion,
780f
mitigations effectiveness,
782
probability of consequence,
781
potential architecture,
779
debris characteristics,
791
rehearsed procedures,
792
required tools and processes,
790–791
special-purpose system,
791
risk mitigation approach,
784
ballistic coefficient,
786
open-ocean analysis,
787t
two-dimensional polygons,
785
vulnerable potential aircraft,
785
casualty maximum probability,
778
impacting maximum acceptable probability,
778
vulnerability
impacts upon wing flow chart,
783f
significant differences,
782
Aircraft hazard area
US catastrophe aversion criterion,
758f
re-entry vehicle hazards,
24
Risk criteria for national ranges,
24
Aircraft vulnerability model (AVM),
24,
845–847
on commercial passenger transport jet,
846t,
847t
impact probabilities,
846
tier 1 thresholds for aircraft,
846t
air-launched rockets,
251
risk analysis perspective,
251
Allen/Egger analytic analysis
simple re-entry model,
614f
Altitude reservation (ALTRV),
784–785
American National Standard (ANSI),
219
Ammonium perchlorate (AP),
222
Analytical re-entry destruction analysis,
649
calorimetric energy balance,
650
calorimetric survival,
650
demise and survival
solid spherical objects,
651f
for titanium and aluminium spheres,
653f
radiative energy balance,
649
Angle of attack (AOA),
619
Anti-Ballistic Missile defence radars (ABMD radars),
414–416
Apollo 11 Mission Rule
Apollo slidewire system,
52f
Apollo-Soyuz Test Project (ASTP),
475
Application software failures
control and safety limits,
502f
control and thruster management function,
501–502
navigation function failures,
501
rendezvous control software,
501
Ariane 5 Main Cryotechnic Stage,
See EPC
modeling validation
airborne surveillance testbed and sensor,
177f
ARGUS optical bench,
178f
Ariane 5 maiden flight 501 re-entry,
176
AST observation for 503 EPC re-entry,
178f
measurement data and infra-red measure,
179f
third Ariane 5 flight 503 observation,
176–178
re-entry modeling
synthesis
EPC re-entry observation campaigns,
184t
VHF
radar observation system,
180,
181f
Assembly, integration and testing (AIT),
Atmosphere control and supply systems control (ACS control),
395
Atmospheric
dispersion modeling, rocket emissions,
198–199
Atmospheric sound focusing gain (ASFG),
239–240
Atomic Clock Ensemble in Space (ACES),
799
Atomic Energy Commission (AEC),
260
Automated Transfer Vehicle (ATV),
477,
714,
740
fragmentation analysis method
aluminum inter-stage skin panel,
746f
LOX Saturation vapor pressure,
748,
748f
RP1 saturation vapor pressure,
749f
stagnation point heat flux rates,
745–746
consequence and probability,
754
controlled re-entry risk profile data,
754t
fragmentation profile,
753f
RCC 321–07 standard set limits,
750
safety analysis method
primary risk metrics,
744
RRAT program data flow,
745f
ship and aircraft hazard area
US catastrophe aversion criterion,
758f
Autonomous Flight Termination System (AFTS),
102
Autonomous Transfer Vehicle (ATV),
375,
401
Avifauna
residual alumina content,
60
waders and coastal ecosystems,
60
B
Backup control center (BCC),
389–390
Baikonur/Tyuratam (TB),
907
Allen Eggers simple re-entry model,
614f
Allen/Egger entry trajectories,
615,
615f
exponential atmosphere,
614
maximum heating rate,
614
BCC Activation Team (BAT),
390
Bipropellant chemical thrusters,
554–555
Blast
wave propagation conditions,
240,
242f
Blast Danger Area (BDA),
52
blast wave scaling fig,
326f
MMH/NTO propellant combination,
332,
332f
Boeing Space Environments Team,
559–560
Brode energy equation,
74–75
Brute force approach,
448
critical radius and threshold radius,
448f
potential conjunction,
448
threshold radius equation,
448
Building locations,
41–42
Building vulnerability,
839
air blast threshold criteria,
842
air blast wave damage,
841
building damage and injury,
841
damage approximations,
844t
inert debris vulnerability modeling,
840t
roof types for building class,
32,
840t
serious injury to occupants,
843f
structural damage to light structures,
842f
Buoyant sources, toxic emissions
air entrainment coefficients,
209,
211f
aluminium oxide particulate size ranges,
200
atmospheric dispersion modeling,
198–199
cloud or plume dispersion,
212
direct measurement of turbulence,
212
duration of exposure,
213
exhaust cloud radius
vs. cloud centroid height,
210f
flight safety toxic dispersion models,
214
Gaussian puffs, or cloud disk elements,
202
hypergol propellant mass calculation,
206
launch pad configurations,
201
normal launch emission source,
199–200
physically-based cloud-rise algorithms,
208
rocket exhaust plumes and fireballs,
208
rocket launch emission evaluation,
198
solid propellant fragments,
206–208
thermal decomposition reaction,
206
Titan 34D-9 launch vehicle,
204,
205f
Titan IVB launch vehicle,
201,
202f
toxic exhaust plumes emission,
207f
C
C-language based Arbitrary Lagrangian-Eulerian/Propellant Energetic Response to Mechanical Stimuli (CALE/PERMS),
321
Canadian Space Agency (CSA),
375,
401
Capsule communicator (CAPCOM),
387
Casualty,
expectation,
failure time and failure mode,
109
Casualty area computations
from blast waves to people in structures,
142f
casualty producing events,
131f
concrete reinforced with steel roof,
140f
debris and projected area,
130
debris impact locations,
135f
maximum casualty areas
vs. fragment weight,
148f
modeling roof/floor penetration,
137f
primary fire effects,
143
roof penetration capability,
134
secondary fire effects,
143
simplification model for casualties,
135f
toxic casualty areas,
147
toxic emitting fragment,
147
unsheltered persons as function of yield,
141f
for vertically falling fragments,
132f
Catastrophe averse requirement,
778
Catastrophic collisions,
584
consequences of future collisions,
585
fragments yield distribution,
585f
3U CubeSat and rocket stage,
584f
Catastrophic extravehicular activity shock hazard,
545
Catastrophic launch failures,
202–203
Catastrophic risk,
Center for Space Standards and Innovation (CSSI),
446
Center of mass (CoM),
653
Certification testing,
101
Change request number (CR number),
406
Chaser capture interfaces,
481
Chemical Propulsion Information Agency (CPIA),
313
Clohessy–Wiltshire (CW) equations,
487
Closed loop trajectories,
497
Cloud-to-ground lightning events
streak camera image,
966f
Coefficient of variation (COV),
245
mitigating
Space Shuttle Forward RCS module,
83f
Space Shuttle OMS/RCS Pod,
83f
spaceflight applications,
79
Collective risk,
Collision danger causes,
482
orbital disturbances,
482
differential accelerations acting,
485–486
drag force of residual atmosphere,
482
trajectory deviation calculation,
486
external disturbances effects,
487–492
Collision protection
active collision protection,
508
control centers of chaser and target,
508
safety responsibilities,
509f
trajectory development,
508
passive trajectory safety,
505
Collision risk
collision probability,
468
one-size-fits-all volume-based box method,
468
Orbital Conjunction Message,
469
prediction
Columbia Accident Investigation Board (CAIB),
22,
681,
811
Columbia public risk analysis
ground risk results,
766t
Columbus module (COL module),
375,
376f
Combined Release and Radiation Effects Satellite (CRRES),
523
chemical equilibrium calculations,
306–307
droplet flame envelope,
309
gaseous reaction products,
307f
propellant burning surface,
310
reaction zone characteristics,
309t
solid propellant plume,
306f
Command and control (C&C),
396
Command control process
Commercial Transport (CT),
757
Committee on Peaceful Uses of Outer Space (COPUOS),
420
Common cause failure modeling (CCF modeling),
807
Communication and data handling (C&DH),
395
Communication failures
manned or unmanned rendezvous missions,
504
satellite navigation,
504
Complementary cumulative distribution function (CCDF),
347
Complex aerodynamic
Composite overwrapped pressure vessel (COPV),
70,
774
Compressed gases
hazards and leakage rate,
76–77
Compressed natural gas (CNG),
74
computer voting and state limits monitoring scheme,
499
failure detection by voting computer output,
500f
Confinement by Ground Surface (CBGS),
326–329
Confinement by Missile configuration (CBM configuration),
329–330
Conical shaped charge (CSC),
358
Conjunction Summary Messages (CSM),
414
Constant bank angle guidance,
633,
633f
Contamination hazard controls,
557–558
design rules and guidelines,
558
contamination transport analysis,
558
thruster plume impact analysis,
558
operational hazard control,
559
vehicle attitude control,
559
Contamination hazard effects,
556
damage to mechanisms,
557
degraded performance
of navigation instruments,
557
of thermal control surfaces,
557
external events impact mitigation,
389–390
CORIOLIS acceleration,
618
Coupled Aero-heating and Thermal Network Solver (CATNS),
742–743
Cumulative risk analysis procedure,
107f
D
Danger zones
launch site perimeter,
34
computer voting and state limits monitoring scheme,
499
failure detection by voting computer output,
500f
Data line coding standard,
858,
858t
Data transfer error detection,
395
Database queries
database input form,
857f
de minimis threshold,
Debris
mitigation practices,
581
Debris avoidance maneuver (DAM),
511–512
planning and execution,
472
flight dynamics team,
472
ISS trajectory teams,
473
large prediction errors,
472
Russian and NASA operations teams,
472
Debris avoidance operation process,
469
ISS trajectory operations,
470
late notification conjunctions,
471
Soyuz emergency escape vehicles,
471
strategy for ISS collision avoidance,
469t
Debris data development,
124
breakup state vector,
124
Expendable Launch Vehicles,
127
fragment characteristics,
124
fragment grouping speed calculations,
125–126
fragment mean ballistic coefficient calculations,
126
guidelines for ballistic coefficient uncertainty,
125t
ranges of maximum velocities computation,
129t
sources in vehicle explosions,
127–129
three sigma low and high limits,
126
breakup state vectors development,
108
casualty expectation computation,
109
cumulative procedure to risk computation,
109–110
debris characteristics,
108
debris to impact propagation,
108
failure probabilities development,
107
fault trees and event trees,
107
hazard identification,
107
impact probability
Debris-generating events,
11
Decision authority,
Deep dielectric charging
affecting insulators and discharge,
523
spacecraft materials,
523
internal or deep dielectric charging,
523
no hard and fast distinction,
523
Deep space missions, innovative,
431
Defence Priority Facility (IDP),
32
Defense Satellite Communication System-III B-7 satellite,
533–534
Deflagration-to-detonation transition (DDT),
317,
318f
Delayed Detonation Transition (XDT),
317,
318f
Delta II 7925 launch vehicle failure,
203f
impact locations of debris items,
671t
pressure sphere dimensions and dry weights,
670t
propellant system pressurization,
670
propellant tank dimensions and weight,
670t
wind data for Texas Delta II re-entry,
671t
initial state and impact location,
675
laboratory analysis results,
675–676
maximum temperature ranges,
678–679
motor casing
recovered in Thailand,
678f
remains recovered in Argentina,
679f
Star-48B rocket motor,
674f
Thailand Star 48B motor case,
676–678
Delta launch vehicle (DLT launch vehicle),
906
Department of Defense Explosives Safety Board (DDESB),
222–223
Design for Demise (D4D),
771
Destructive re-entry analysis,
638–639
demands on explosion model,
665
destruction analysis for SC,
639–640
destruction events during re-entry,
639,
639f
material properties effect,
640
materials and mass specific heat storage,
642f
melting temperatures of materials,
641,
641f
multidisciplinary process,
640
object analysis methods,
644
re-entry vehicles differences,
638t
specific heat capacity,
640
system inputs and outputs,
665,
666t
tool interaction sequence,
666f
blast wave propagation conditions,
240,
242f
building yield histogram,
231
large ELV yield histogram,
233f
simulation of vehicle accidents,
231f
solid propellants impact,
232f
vehicle trajectories,
231
defining exposed population and window inventory,
233
assigning population centers,
235f
sample of window inventory link,
235f
structure, window, population data determination,
234f
description of phenomenology
atmospheric condition,
220
atmospheric focusing of blast waves,
219f
far-field overpressure levels,
220
far-field overpressure propagation conditions,
221f
launch accident scenarios,
218
safe design of launch operations,
222
weather balloon observation,
221–222
detailed DFO approach result,
248
detailed DFO risk analysis,
227–228
Monte Carlo simulations,
229
Monte Carlo simulations,
229
overpressure attenuation relationships,
240–243
amplified overpressure in caustic focusing region,
243–244
gradient and inversion relationships,
243
simplified screening models,
222
maximum credible yield screening analysis,
222–223
simplified risk-based screening analysis,
223–227
terrain type and elevation irregularities,
234,
236f
2D ray tracing performance,
236–237
hemispherical symmetric isotropic blast wave propagation,
238f
ray path direction change according,
239f
ray tracing on flat terrain,
240f
two dimensional model,
238f
window breakage model,
244
duration-dependent behavior,
244–245
high fidelity modeling tool,
244
physics-basedmodeling approach,
244
Distant focusing overpressure (DFO),
222,
830
maximum credible yield screening analysis
no damage limits for surface explosions,
223f
screening procedures,
222
simplified risk-based screening analysis,
223–224
acceptable risk levels,
227
atmospheric focus factor probability distribution,
225f
casualties risk equation,
227
conservative rule-of-thumb,
226–227
probability of breakage for average window panes,
226f
simplified DFO risk analysis results,
228f
simplified power law relationship,
224–225
vulnerable community building inventory,
225
Document configuration
ATV approach profile,
407f
ATV RANGE RATE profile,
408f
flight director responsibility,
406–407
flight rule designation,
406
Hazard Control indication,
406
technical or functional areas,
406
Down conductor system,
971
Draft environmental impact statement (DEIS),
353–354
Drag-thru risk
caution and warning capability,
823
for JEM temporary crew quarters,
823f
mobile transporter risk comparison,
821f
DTMBARLIER + CIRA88 model,
613
Dynamic pressure limit,
628
E
Early Ammonia Servicer (EAS),
513
Earth orbit
objects distribution
inclination distribution,
433f
non-uniform distribution,
431
perturbations complicate mission planning,
431–432
semi-synchronous regime,
432
Electrical connectors,
69
occurrence probability
lightning flash density,
965
lightning location systems,
965
Electro explosive device (EED),
70
explosive circuits,
70–71
Electro-optical sensors,
413
Electromagnetic environment,
34
Electromagnetic pump (EM pump),
265–266
Electrostatic discharge (ESD),
71
Emergency Escape System (EES),
50–51
constellation program rail,
53f
design safety factors,
52–53
Emergency Response Planning Guideline (ERPG),
213–214
End of mission (EOM),
374
End-of-life debris mitigation measurement
debris in Earth orbit,
572
mitigation measure guidelines,
575
aforementioned measures,
576
communications and electrical systems,
576
long-term preservation,
576
passivation measures,
575
mitigation measure practices,
577
batteries and heat pipes,
578
designing spacecraft and launch vehicle,
578
drag-augmentation devices,
579
Globalstar constellation,
579
higher altitude spacecraft,
578–579
LEO commercial communications networks,
579
liquid or gaseous propulsion systems,
577
multi-national Sea Launch organization,
580
Proton Block-DM and Briz stages,
581
Proton Briz-M stages,
577
post-mission fragmentations,
572
End-states are Evacuation (EVAC),
813–814
Energydispersive X-ray spectrometer (EDXS),
672
Environment protection
action plans and results,
56–61
physico-chemical quality,
59
communication of results,
60
geographical and ecological context
final assembly building,
62f
Guiana Space Center,
56,
57f
integrated environmental approach,
56
methodology
modeling and dispersion calculations,
57–58
simulation input data,
58
regulatory context
Environmental Assessment (EA),
353
Environmental impact statement (EIS),
353,
987–988
Environmental protection,
32
Environmental Protection Agency (EPA),
985
Equilibrium hypothesis,
620
atmospheric density modelling,
621
azimuth of velocity vector,
621–622
weight and centrifugal force relationship,
620
Equilibrium trajectory,
627
lift ceiling altitude equation,
628
Europe’s Ariane launch vehicles,
574
European Space Agency (ESA),
401,
740
operational development phase,
419
preliminary activities,
419
preparatory phase elements,
419
European Space Agency SPENVIS (ESA SPENVIS),
530
European Technology Exposure Facility (EuTEF),
376,
376f
Expected Fatalities (EF),
736
Explosions
ascent phase explosions
ballistic trajectory,
314
early
vs. later flight impacts,
315f
computer modeling
Titan upper segments,
323
Cassini Titan IV SRMU segment,
319f
fallback secondary explosions
impact crater delta II explosion,
316f
pre-launch to flight phase explosions,
313
Chinese long march 3B launch accident,
314f
VLS-1 pre-launch accident,
313f
solid propellant experimental testing
critical diameter test apparatus,
322f
propellant testing data,
321t
Explosive destruction during re-entry,
659
destructive re-entry analysis of fragments
analysis system inputs and outputs,
665,
666t
analysis tool interaction sequence,
666f
demands on explosion model,
665
explosion likelihood development,
660,
660f
explosive environment generation,
659
fragment length number of fragments
A/M distribution density,
665
probabilistic explosive destruction process,
662
Lc and A/M correlation,
663f
NASA explosion model,
662
re-entry explosion phenomenology,
660–661
explosive detonation,
662
explosive flow field generation,
661f
relation for shock speed and position,
662
transient gas dynamics,
661f
Exponential charging law,
525
Exposure Response Function (ERF),
215
External disturbance effects
solar pressure in GEO,
488
floating-potential measurement unit data,
549
negative and positive floating-potential,
549–550
positive floating-potential hazard,
549
U.S. extravehicular mobility unit,
549
toxic propellant residue hazard
crew extravehicular activity suits,
561
fuel-oxidizer reaction products,
560
NASA Johnson Space Center Toxicology Group,
561
NASA White Sands Test Facility laboratory tests,
561
Service Module surfaces,
560
thruster-induced contamination,
559–560
Extravehicular Mobility Unit (EMU),
825–826
location of potentially exposed surfaces,
827f
F
Facilities Classified for Protection of The Environment (ICPE),
32,
56
Failure detection isolation and recovery system (FDIR),
503
Failure modes and effects analysis (FMEA),
107,
392,
806
Failure probability development
casualty area computations
from blast waves to people in structures,
142f
casualty producing events,
131f
concrete reinforced with steel roof,
140f
debris and projected area,
130
hazard area and hazard areas,
130
maximum casualty areas
vs. fragment weight,
148f
modeling roof/floor penetration,
137f
primary fire effects,
143
roof construction and debris impact locations,
135f
roof penetration capability,
134
secondary fire effects,
143
simplification model for casualties,
135f
toxic casualty areas,
147
toxic emitting fragment,
147
unsheltered persons as function of yield,
141f
for vertically falling fragments,
132f
trajectory input data development,
120
aerodynamic breakup criteria,
124
dispersion effect of normal trajectories,
123f
flight safety analyses,
120
performance variations,
121
pre-failure trajectory dispersions,
121
6DOF flight dynamics computer program,
122
trajectory, subvehicle point and IIP,
121f
Failure tolerance requirements,
497
functional redundancy,
498
malfunction and robustness,
498
rendezvous operations,
498
Federal Aviation Administration (FAA),
22,
784–785
Federal Tort Claims Act (FTCA),
Figures of Merit (FOM),
812
characteristics of satellite orbits,
451
series of iterations,
451
using Taylor-series approach,
451
Final environmental impact statement (FEIS),
353–354
Final Safety Analysis Report (FSAR),
264
Finding Of No Significant Impact (FONSI),
353
Finite difference (FD),
244
Fire protection
Firmware controllers (FWC),
395
First flight tests
ATV-2 supply vehicle,
703
altitude-time history for,
705f
REBR
First-order risk assessment,
445–446
brute force approach,
448
critical radius and threshold radius,
448f
potential conjunction,
448
threshold radius equation,
448
conjunction analysis,
446
satellite positions and velocities,
446
TLEs and state-vector propagation,
446–447
USSTRATCOM and CelesTrak,
447
Fleet Satellite Communications satellite (FltSatCom satellite),
964
Flight Control Operations Handbook (FCOH),
399,
409–410
Flight control team (FCT),
383
Flight director
Flight dynamic analysis,
653
Flight environment effects
charging by auroral electrons,
525
exponential capacitor charging equation,
525
spacecraft capacitance effects,
527t
current balance models
spacecraft surface interactions,
524–525
structural charging interactions,
524–525
international space station,
527
solar array floating potential,
528
spacecraft charging, analysis tools for
department of defense,
530
European Space Agency,
531
handbooks and standards,
530
modeling and analysis tools,
530
Flight hardware (F/H),
65,
71
Flight path angle (FPA),
620
Flight risk control,
accidentological analysis,
34
danger zones
launch site perimeter,
34
flight safety mission,
35
flight termination system
launch vehicle’s propulsion,
35
liquid propellant motor,
35
solid propellant motor,
35
ground support facilities,
35
intervention criteria,
35
Flight rules
Apollo 11 Mission Rule
document configuration
ATV approach profile,
407f
ATV range rate profile,
408f
flight director responsibility,
406–407
flight rule designation,
406
Hazard Control indication,
406
technical or functional areas,
406
flight-specific books,
405
technical and programmatic aspects,
405–406
flight-specific decisions,
403
ISS Joint Flight Rule
B1–2 Flight Rule Purpose,
402f
B1–3 Real-time Operating Policy,
404f
B1–4 Mission Management Team,
402f
B2–1 Power Connector Inhibits,
403f
E2–31 MSU Management,
404f
mission requirements,
401
pre-planned decisions,
403,
405
flight rules changes,
409
rules requirring concurrence,
409
pre-coordinated operations products,
399
Flight safety risk management,
90
Flight safety system malfunctions,
107
Flight termination system (FTS),
98–99,
218
flight termination actions,
102
launch vehicle’s propulsion,
35
liquid propellant motor,
35
solid propellant motor,
35
typical flight safety system,
100f
Floating Potential Measurement Unit (FPMU),
535–536,
536f
Fluid dumping
feathering constraints,
567
Space Shuttle Orbiter water dump damage mitigation
constraints development,
570
feathering angle α/β pair combinations,
568
U.S. Laboratory water dump damage mitigation,
567
β gimbal assembly β-rotations,
568
feathering angles for solar array wings,
567–568
solar array feathering angles,
570f
U.S. Laboratory water venting,
568f
Fluid venting
feathering constraints,
567
Space Shuttle Orbiter water dump damage mitigation
constraints development,
570
feathering angle α/β pair combinations,
568
U.S. Laboratory water dump damage mitigation,
567
β gimbal assembly β-rotations,
568
feathering angles for solar array wings,
567–568
solar array feathering angles,
570f
U.S. Laboratory water venting,
568f
Fragment length number
A/M distribution density,
665
Fragment penetration vulnerability,
843–844
by mechanical fracture of joint,
656f
SC model before fragmentation event,
655f
Fragmentation analysis method,
644
aluminum inter-stage skin panel,
746f
LOX Saturation vapor pressure,
748,
748f
RP1 saturation vapor pressure,
749f
stagnation point heat flux rates,
745–746
emitting and receiving antennas,
416,
418f
Free Piston Stirling Engine (FPSE),
264–265
Fuel-oxidizer reaction products,
560
Full stack intact impact (FSII),
359
Functional hazard analysis (FHA),
392
G
Gases storage and handling safety
gas during ground operations,
75
minimizing effective time under pressure,
80
mitigating collateral damage
Space Shuttle Forward RCS module,
83f
Space Shuttle OMS/RCS Pod,
83f
operating in ground facilities
ground operation schedules,
80
pressurized components,
79
shrapnel and fragmentation analysis,
75–76
spherical gas expansion,
75
stored energy considerations
Brode energy equation,
74–75
potential effects of explosion energy,
75
stored gas energy equation,
75
Gaussian dispersion models,
195
Gaussian modeling assumption,
195
General Perturbations (GP),
414
General Purpose Heat Source (GPHS),
337
Geostationary Earth Orbit (GEO),
420,
477,
482
coordinated station-keeping
using orbital parameters,
425
seven Astra satellites,
425f
coordination with operators,
427
drift orbit
with high eccentricity,
426f
with low eccentricity,
426f
longitudes and frequencies management
orbital position and frequency slot,
424
solar pressure, predominant in,
484f
space surveillance data,
423
Geostationary orbits,
984
Geostationary transfer orbits (GTO),
416,
580
Geosynchronous orbits,
984
Global Precipitation Measurement (GPM),
772–773
Globalstar constellation,
579
Grand Réseau Adapté à la Veille Spatiale system (GRAVES system),
416
emitting and receiving antennas,
416,
418f
Gross Domestic Product (GDP),
730–731
Ground risk control,
electromagnetic environment,
34
GROUND support facilities,
33
requirements
Range Space Safety Regulations,
32
space vehicle integration,
33
profession’s capitalization,
33
Ground support equipment (GSE),
66
design details
biomedical systems and materials,
68–69
design practices
fluid servicing cart,
67–68
payload processing flows,
68
processing of flight hardware,
67
sources of information,
67
ground support hazards,
66
safety documentation,
66–67
environmental hazards,
73
launch and possible return phases,
73
mechanical and electromechanical devices
Guidance, Navigation and Control (GNC),
406,
475,
481
Guidance system failures,
113
H
guidance system failures,
113
staging/jettison failures,
114
hazard thresholds for debris
building classes, uses and roof types,
750t
impacts on waterborne vessels,
724
penetration threshold values,
757
on people and buildings,
722
threshold values for roof penetration,
754t
tier 1 thresholds for aircraft,
766t
typical injury thresholds,
731t
used in US for building structures,
722
sample abort mode event tree,
120f
sample top level RLV event tree,
116f
Hazardous command identification,
391–392
system safety
Hazardous command implementation
Hazardous effect zones,
blast and flying fragment zones,
38
pyrotechnic regulations,
38
specialist literature,
38–41
toxic fallout calculation results,
37f
Heat flux density thermochemical model,
291–292
Heavy lift space launch boosters,
197–198
Heuristic International Space Station charging model,
528f
High Elliptical Orbits (HEO),
416
Higher fidelity models,
failure comparison
altitude-time history for,
705f
Hubble Space Telescope (HST),
379
Human Reliability Assessment modeling (HRA modeling),
807
Human vulnerability
injury severity
body part sensitivity,
837t
injury consequences,
836t
non-toxic propellants,
837t
penetrating injuries,
836t
severity levels for toxic injuries,
833t
toxic propellants and by-products,
837t
Hybrid verified interval propagation,
464
Hydrocarbon rubber binder-aluminum fuel-ammonium perchlorate oxidizer (HC/Al/AP),
320–321
Hydrological phenomena,
30
Hypergolic liquid propellants,
192
Hypergolic oxidizers,
193
I
Immediate breakup failures,
112
Immediately Dangerous to Life and Health (IDLH),
92–93
Immersion heat probes,
310
Impact covariance matrix,
157
Impact probability computation
failure time and failure mode,
109
fragment and population center,
108
impact covariance matrix,
108
one-or-more fragment impacts,
109
Impact probability distributions,
108
In-orbit collision risk,
427
annual collision risk,
427t
Iridium 33 and Cosmos 2251 satellites,
427
ISS and launch trajectory,
429f
monitoring procedure,
428
using space surveillance data,
427
In-sky-laser safety
hot air balloons and hang-gliders,
800–802
laser beam diameter,
801f
Independent plant evaluation (IPE),
806
Individual risk,
Inertial measurement units,
96
Inhibited red fuming nitric acid (IRFNA),
193,
573
Insult environment characterization,
340
launch vehicle and spacecraft accidents,
341
testing and computational simulation programs,
340–341
environmental hazards,
73
launch and possible return phases,
73
Integrated medical model (IMM),
816
Inter-Agency Space Debris Coordination Committee (IADC),
576–577
Interagency Nuclear Safety Review Panel (INSRP),
260,
355–356
Internal charging
affecting insulators and discharge,
523
internal or deep dielectric charging,
523
no hard and fast distinction,
523
spacecraft materials,
523
International Association of Geodesy (IAG),
798–799
International Commission on Radiological Protection (ICRP),
346
International Laser Ranging Service (ILRS),
796,
798–799
International protocols,
348
using space nuclear systems,
348–349
international treaties,
349
liability and compensation,
351
settlement of disputes,
351
UN principles are non-binding,
352
U.S. environmental process for launch
launch radiological impact analysis,
354–355
NEPA compliance process,
354f
U.S. launch approval process,
355
International Scientific Optical Network (ISON),
416
United States Space Surveillance Network,
416
International Sea Launch platform,
899
International space station (ISS),
10,
74,
375,
441,
511,
535,
535f,
717–718,
740–741,
802,
805
ATV-2 supply vehicle,
703
contamination/erosion planes,
566
erosion plane plot for Russian vehicle approach,
566,
566f
robotic camera assets,
567
truss-mounted robotic cameras,
566
visiting vehicle proximity operations,
567
charging instrumentation and measurements
Boeing’s Langmuir probe reduction process,
538–539
floating-potential probe,
538
ionospheric temperature and density,
540f
charging model development
historical probability,
542
International Reference Ionosphere,
542
plasma density and temperature,
541
collision avoidance maneuvers
collision risk determination,
468–469
ISS debris avoidance operations process,
469–473
command software architecture,
396f
catalogued space debris objects,
443f
LEO and GEO environment,
444
real situation in space,
444
distribution of facilities,
378f
first-order risk assessment,
442
TLEs and state-vector propagation,
446–447
HTV2 supply vehicle for,
703
integrated flight control team,
387–388
mitigation strategies,
559
national space agencies,
401
partner’s control rooms,
386f
plasma and spacecraft diagnostics package,
537
shock risk
magnetically induced voltages,
826f
nominal EVA risk
vs. positive potential,
827f
solar and geomagnetic activity,
538
bipropellant thruster particles,
562–563
Boeing Space Environments Team,
562
operational constraints,
565
station attitude control thruster,
563f
thruster-induced erosion events,
564
spacecraft charging hazards,
544
electromagnetic compatibility effects,
545–546
electromagnetic interference,
545–546
extravehicular activity touch-temperature violations,
545
plasma contactor unit tiger team,
544–545
spacecraft charging processes,
535
sun tracking photovoltaic arrays,
535
International Space Station PRA model (ISS PRA model),
813
driver or top contributor,
816
ISS PRA end state relationships,
814f
Monte Carlo simulation,
818
probabilistic results,
815
risk analyst or engineer,
818
International Space Station software,
395
ISS command software architecture,
396f
PCA/ACS system
“must work” function,
396
International Telecommunication Union (ITU),
424
Ion Beam Shepherd (IBS),
596
Iridium-Cosmos collision,
445
Irreversible Effects Thresholds (SEI),
38
Isolated lightning protection systems,
47
ISS Mission Management Team (IMMT),
375,
401
J
Japan Aerospace Exploration Agency (JAXA),
401,
593,
824
Japanese Experimental Module (JEM),
822–823
Joint Flight Rules Control Board (JFRCB),
409
Joint Space Operations Center (JSPOC),
517–518
K
Keldish Institute of Applied Mathematics (KIAM),
416
Kernel density estimation (KDE),
167–168
L
L/D impact dispersion model,
156f
Lagrange Planetary Equations,
447
LAser GEOdynamics Satellite (LAGEOS),
795–796
Launch Abort System (LAS),
51
Launch chronology
abbreviations and acronyms,
851t
database element definitions,
855,
855t
reference documents and sources,
854,
854t
Launch Control Center (LCC),
372
safety risk on launch site,
372–374
Launch Emergency Operations Center (LEOC),
361
Launch Escape System (LES),
51
Launch pad escape system design
Apollo and shuttle program EESs,
51
Apollo slidewire system,
52f
key design safety factors,
52–53
NASA’s Constellation Program,
53
final protection tier,
11
flight termination criteria,
11
launch hazard areas identification,
10
malfunction trajectory,
11
Launch site processing issues,
358–359
flight risk controls,
ground risk control concepts,
mission and flight hardware designers,
liquid and solid propellants,
276
propellant pros and cons,
277,
278t
Lawrence Livermore National Laboratory (LLNL),
321,
323
Lethal Effects Thresholds (SEL),
38
Liability Convention,
349,
714
Lift to drag ratio (L/D ratio),
622,
634
follow up of drag reference profile,
637f
reference trajectory in deceleration/velocity,
635f
trajectory characteristics,
634–635
Light Weight Radioisotope Heater Unit (LWRHU),
310,
336–337
Lighting Launch/flight Commit Criteria (LLCC),
973
cloud-to-ground discharges,
962–963
cloud-to-ground flashes,
963f
Lightning protection systems (LPS),
961
command control process
external and internal protection measures,
45
down conductor system,
971
external protection schemes,
45
fire protection
handling and lifting
pyrotechnic stage transfers,
49
interception efficacy,
45
launch pads
aerial interconnections,
47
protection schemes,
45,
46f
theoretical analysis,
47–48
parameters
thunderclouds
tripole charge structure,
962
vehicle triggered lightning
control and guidance system,
964
Delta II second stage thrust chamber body,
672
optical photograph of as-received debris,
672,
672f
Lightweight Directory Access Protocol (LDAP),
384
Lincoln Experimental Satellites (LES),
268–272
Linear shaped charge (LSC),
332–333
Liquid Cooling and Ventilation Garment (LCVG),
825–826
safety considerations,
71
Long Duration Exposure Facility (LDEF),
442–443
Los Alamos National Laboratory (LANL),
266
Loss of Crew and Vehicle (LOCV),
812–814
Loss of Mission (LOM),
812
Loss of Signal point (LOS point),
683–684
constellation management
analytical model for,
611
DTMBARLIER + CIRA88 model,
613
satellite with characteristics,
612–613
solar and geomagnetic activity effect,
613f
terrestrial atmosphere,
610
lethal debris objects in,
582t
operational orbit protection,
421
during end-of-life maneuvers,
423
sequence of operations,
423
Lunar Exploration Analysis Group (LEAG),
260
M
Manned mission scenarios,
478
Mars Exploration Program Analysis Group (MEPAG),
260
Mars Exploration Rover (MER),
266–267
Marshall Space Flight Center (MSFC),
266
Material Safety Data Sheets (MSDS),
68
Maximum Expected Operating Pressure (MEOP),
79,
577–578
Maximum permissible energy (MPE),
802
Maximum Probable Loss (MPL),
714
Micro-meteoroid and orbital debris (MM/OD),
816
Midcourse Space Experiment satellite (MSX satellite),
413
Minimum Equipment List (MEL),
397
Mir Electrodynamic Tether System (METS),
593
Mishap response systems,
25
Mission and Vehicle Management (MVM),
501
Mission characterization
decision making process,
112
guidance system failures,
113
staging/jettison failures,
114
Flight Termination System,
111
sample abort mode event tree,
120f
sample top level RLV event tree,
116f
ground infrastructure,
381
management control structure,
375
mission personnel
operations control rooms
back room controllers,
388
ISS partner’s control rooms,
386f
redundancy and fault tolerant,
388
structure from flight director,
385,
387f
safety consideration,
379
spaceflight mission project,
379
design concept phase,
380
Mission Control Center Houston (MCC-H),
375
flight controllers in,
380f
Mission Control Center–Moscow (MCC-M),
375
Mission Flight Control Officers (MFCOs),
359
Mission personnel
Mixed oxides of nitrogen (MON),
193
Mobile servicing system (MSS),
820
Mobile transporter (MT),
820
TUS risk
mitigating risk factors,
821
translation operations,
822
Modified equinoctial element (MEE),
455–456
Modular Auxiliary Data System (MADS),
712
Moment of inertia (MoI),
653
Monomethyl hydrazine (MMH),
193,
332
Monte-Carlo analysis,
459
angular velocity calculation,
459
collision-detection methods,
460
normal or uniform distribution,
460
solution space generation,
460f
Multi-Mission Radioisotope Thermoelectric Generator (MMRTG),
260,
268–272
Multi-Purpose Crewed Vehicle (MPCV),
812
Multiplexer/demultiplexer (MDM),
395
N
N-nitrosodimethylamine (NDMA),
560
NASA Advisory Council (NAC),
260
ESA Hubble Space Telescope,
376f
National Environmental Policy Act (NEPA),
352,
987–988
National Highway Traffic Safety Administration (NHTSA),
Natural Zones of Interest for Ecology, Flora and Fauna (ZNIEFF),
56
Navigation errors effects,
493
on trajectory evolution
Nitrogen dioxide (NO
2),
193,
213
Non-buoyant sources, toxic emissions,
192
atmospheric dispersion models,
197
atmospheric stability classes,
195
cloud cover and ceiling factors,
194
downwind concentration analysis,
193
Gaussian dispersion models,
195
Gaussian modeling assumption,
195
heat transfer and evaporation,
194
hypergolic
standard Gaussian models,
197
theoretical evaporation model,
195
turbulence
Non-nominal trajectories,
482
Normal crossrange probability distribution,
164f
Normal launch source,
202
Notice of Availability (NOA),
353–354
Notices to Mariners (NOTMARs),
88,
92