Fundamentals of Space Systems
Fundamentals of Space Systems was developed to satisfy two objectives: the first is to provide a text suitable for use in an advanced undergraduate or beginning graduate course in both space systems engineering and space system design. The second is to be a primer and reference book for space professionals wishing to broaden their capabilities to develop, manage the development, or operate space systems. The authors of the individual chapters are practicing engineers that have had extensive experience in developing sophisticated experimental and operational spacecraft systems in addition to having experience teaching the subject material. The text presents the fundamentals of all the subsystems of a spacecraft missions and includes illustrative examples drawn from actual experience to enhance the learning experience. It includes a chapter on each of the relevant major disciplines and subsystems including space systems engineering, space environment, astrodynamics, propulsion and flight mechanics, attitude determination and control, power systems, thermal control, configuration management and structures, communications, command and telemetry, data processing, embedded flight software, survuvability and reliability, integration and test, mission operations, and the initial conceptual design of a typical small spacecraft mission.
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Systems Engineering and Management
The Space Environment
Spacecraft Propulsion Launch Systems and Launch Mechanics 1 71
Spacecraft Attitude Determination and Control
Space Power Systems
Spacecraft Thermal Control
Spacecraft Configuration and Structural Design
Spacecraft Command and Telemetry
activity analysis angular antenna atmosphere attitude control attitude determination battery bits charge circuit command components configuration constant cycle defined density device discharge dynamic Earth effects electrical electrons elements energy engineering environment equation error estimate Euler angles example exospheric flight flux frequency function hardware heat inertia input instrument integrated circuits integration interface ionosphere latchup launch vehicle lithium load magnetic field magnetosphere mass material matrix maximum mission operations modulation momentum momentum wheel motion node nozzle orbit parameters particle payload performance phase plasma pressure processor propellant protons radiation radius ratio requirements result right ascension rocket rotation satellite schedule semimajor axis sensor shown in figure solar array solar cell solar wind space spacecraft specific specific impulse spin stress structure subsystem surface telemetry temperature thermal thrust thrusters torque true anomaly typically vector velocity voltage
Page 795 - Units length meter* (m) mass* kilogram (kg) time second (s) electric current ampere (A) thermodynamic temperature* kelvin (K) amount of substance mole (mol) luminous intensity candela (cd) Supplementary Units plane angle radian (rad) solid angle steradian (sr) The spellings "metre" and "litre" are preferred by ASTM; however, "-er