By Wren Software, Inc. C. Brown
This article discusses the conceptual phases of undertaking layout, structures engineering, and orbital mechanics, delivering a foundation for realizing the layout method for various parts and services of a spacecraft. assurance comprises propulsion and gear structures, buildings, angle regulate, thermal keep watch over, command and information structures, and telecommunications. labored examples and routines are integrated, as well as appendices on acronyms and abbreviations and spacecraft layout info. The booklet can be utilized for self-study or for a direction in spacecraft layout. Brown directed the staff that produced the Magellan spacecraft, and has taught spacecraft layout on the college of Colorado.
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Additional info for Elements of Spacecraft Design (2002)(1st ed.)(en)(610s)
Unplanned maneuvers. Propellant margin can be reduced late in the program if necessary. Propellant temperatures. and hardware in contact with propellant. should be . maintained >IO:C above propellant freezing temperature. Propellant upper temperature must be controlled with substantial margin. Serious failures have occurred by overheating propellant. 13 Spacecraft subsystem power budget Subsystem Thennal control Attitude control Power C&DH Communications Propulsion Mechanisms Tow/ Allocation. lk Power.
4) Determine the total allowable on-orbit dry mass. 5) Establish the total allowable payload weight (usually specified by the customer). 6) Evaluate the mass margin to be set aside. The AIAA guidelines I I are very useful in this step. 7) Allocate mass budgets to each subsystem. The less obvious of these steps are discussed in the following sections. 5. 1 Maximum spacecraft launch mass. The maximum spacecraft launch mass is derived directly from the launch vehicle capability. which in tum is a function of the mission design.
Once the design process starts. the mass properties activity changes from budget allocation to monitoring progress and estimating what the actual launch weight will be. For mass monitoring. it is customary to tabulate detailed weights along with the maturity of each element. 7 '. ; ,I d Iwn as I , 'I the Subsystem mass allocation Structure Thermal ACS Power Cabling Propulsion Telecom (Comsat) CDS Budget total Mass margin Max bus ma~s Max payload mass Max on-orbit dry Percent of total Allocated mass.