Info

Sines, law of (in spherical triangles)

33, 731-732

Single-axis attitude 343-346

Single-axis attitude determination— Accuracy 373-409

Methods 362-409

Single-degree-ol-1 reedom g; roscope 1%

Single-spin spacecraft 503-504

Singular matrix 749

Singularities, in attitude solutions 403

Singularity conditions in attitude determination 406-407

Table of 407

Sinter, Use in thermistor flake 171

SIRIO (Italian experimental communications satellite)— Application of block averaging to attitude solutions 371 Attitude accuracy constraints on launch window 399-401

Attitude determination accuracy 397

Attitude software structure 698

Attitude system of 794-795

Correlation among measurement types 480 Slit horizon sensor/Sun sensor 178-179 Spin rate change due to orbit maneuvers 582 Sun sensor analysis 717-718

Use of body-mounted horizon sensor 173 Use of carbon dioxide band horizon sensor 92

Skew-symmetric matrix 750

Attitude control system 197. 201

Disturbance torques due to crew motion 579 Spacecraft configuration 579

SKYMAP. star catalog 147

SKYNET (U.K. Communications satellite)— Attitude system of 794-795 Skywave (in radio broadcasts) 301

Slave station (time signals) 300

Slew maneuvers 601,655-661

Slit horizon/Sun sensor 178-179

As possible standard coarse sensor 721

Math, model for misalignment 219

Slit sensors. Analysis of alternative designs 717-718

Slit star sensor, mathematical model 254-256 SI.P ephemeris files 140

Subroutine for reading (SUN RD) 693

Slug (unit of mass) 808

SM (San Marco satellite)

Attitude system of 794-795

Small circle (spherical geometry) 22, 32

Area formulas 729-730

Construction of on global geometry plot

739, 742-743

Equations for 727

Smithsonian Astrophysfcal Observatory, star catalog 143-144,(46-147

SMM (Solar Maximum Mission) (See also MMS)— Attitude acquisition 672

Attitude control law for 659

Attitude system 718-720, 794-795

Control system 608

Data collection Tor bias determination 475 Fine Sun sensor 166-167

Inertial reference assembly 187

Onboard computer 210

Smoothing, of attitude data and ■ results .

Applications of 316

Guidelines for 317-318

SMPOS (subroutine) 693

Analytic basis 141 -142

SMS (Synchronous Meteorological Satellite)— Application of block averaging to attitude solutions 371

Attitude acquisition 661

Attitude determination accuracy 397-399 Attitude software structure 698

Attitude solutions from 373

Attitude system of 794-795

Behavior of single-frame solutions 403-405. Correlation among measurement types

478,480-482

Data collection for bias determination 474 Earth-width data 233-234

Horizon sensor electronics modeling 244-249

Launch of 5

Pagoda effect 336-339

Sensor package characteristics 721

State vector for bias determination 440 Sun sensor analysis 717-718

Telemetry data errors 311

Use of body-mounted horizon sensor 173 Use of carbon dioxide band horizon sensor 92

Use of open-loop control 663

View of Earth by 84,91

Snapshot, of star sensor data 706

Sneirs law 223

Software—

Avoidance of errors in 682-683,685

Development of 681 -713

Example of attitude support software structure 700-703

For multimission support 686,721-722 General structure for attitude support 696-700

Goddard Space Flight Center

- environment 682

Safeguards for mission support 681-686 Standardization of 686,721-722

Systems, general structure for 696-700

Test procedures for state estimators 471-473 Utility subroutines 690-695

Solar eclipse 72

Solar heating, effect on flexible spacecraft

549,550

Solar mass ratio, for planets 827-828

Solar parallax 31

Solar radiation— Flux 130

Pressure, effect on orbit 64-65

—Effect on flexible spacecraft 550-551 Stabilization 19

Torque 17,570-573

Solar sail 64

Solar System—

Orbits 48-52

Properties 814-825 Solar time 798,799-801 Solar wind 120,129-132

Sectors 131-132

Solid angle 23

Formulas 729-730

Units and conversion factors 810

Solid spherical harmonics 775

Sounding rocket 52 Smith Atlantic Anomaly (See Brazilian Anomaly)

Soviet Space Program 3

Launch sites 3

Tracking and data acquisition 290

Space cone 491-492 Space Mission, profile of—

Future changes in 8-12

Representative 3-12

Space navigation I Space Precision Attitude Reference

System (SPARS) 708

Space shuttle 3,8-9 Effect on attitude determination and control 714,724

Orbit ephemeris 134

Payload mass as a function of altitude 9

Star tracker for .190

Thrust 53 Space Telescope—

Attitude system of 794-795

Onboard computer 211

Pointing accuracy 714

Reaction wheels 604

Stability requirements 604 Spacecraft—

Data generation and handling onboard 278-283

Effects of flexibility on dynamics 548-556 Gyroscope measurement of angular velocity 267-268 Magnitude of when viewed from a distance 79

Names and international designations 52 Stabilization and control, methods of 18-19 Stabilization, methods of (See also

A ttitude stabilization) 3 Spacecraft attitude control (See Attitude control)

Spacecraft attitude determination and control systems 787-797 Spacecraft attitude dynamics {See

Attitude dynamics) Spacecraft attitude motion—

Example of Apollo 15 subsatellite 495-497

Introduction to 487-502

Spacecraft axes, alternative systems 487-489

Spacecraft-centered celestial sphere 22-24

Spacecraft-centered coordinates 26-29

Spacecraft docks 298-299 Spacecraft ephemerides—

Definitive subroutines 693

Two-body orbit generator (ORBGEN) 692 Spacecraft fixed coordinates 26

Spacecraft orbits 32-62, 132-138

As function of injection conditions 60-62 Multipurpose ephemeris subroutine

(EPHEMX) 693

Spacecraft stability (See also Attitude dynamics; Disturbance torques; Nutation; Flexible spacecraft dynamics) 523 Apollo 15 subsatellite 495-497

With respect to libration (GEOS

example) 674

Spaceflight Tracking and Data Network

(STDN) 283-290

Time-tagging by 299-301

Spacelab, onboard computer 211

SPARS (See Space Precision Altitude

Reference System) Special perturbations, method of (orbit analysis) 139

Specular reflection 84

Torque due to 572

SPHCNV (subroutine) 694

Sphere, illumination of as function of phase, distance 78-79,89

Sphere of influence— For spacecraft orbits 69-71

Table of for planets 69-71

Spherical coordinate systems 24-31,760

Advantages relative to rectangular 25-26 Properties of 24-26

Transformations between 765-766

Spherical excess 32

Spherical geometry 31-35

Construction of global geometry plots

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