This 1960 guide has been ready as one in all a chain on ballistic missiles. It offers info at the primary working rules of propulsion platforms as present in ballistic missiles, with discussions of propellants which were came upon attainable or that have theoretically beautiful probabilities. standards are provided wherein the functionality of propulsion structures will be judged.

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**Extra info for Ordnance Engineering Design Handbook - Ballistic Missile Series - Propulsion and Propellants**

**Example text**

1740 ft/sec2). If I, is defined by F/m, as is sometimes done, then its dimensions are (ML/T*)/(M/T)= L/T. 174 ft/sec2. (4 29 PROPULSION AND PROPELLANTS ORDP 20-282 F = THRUST TO INFINITY TO INFINITY I I-% I '1 r A----F-------h 1 / I I Figure 3-2. Application of the Momentum Theorem of Fluid Mechanics to an Arbitrary Propulsion System Y Figure 3-3. Free Body Diagram for a Rocket Propelied Ballistic Missile 30 CRITERIA OF ROCKET ENGINE PERFORMANCE ORDP 20-282 From equations (3-7) and (3-11) it follows that if the exhaust nozzle operates with complete expansion ( p , = p,,), then Equation (3-8) is, however, the most widely used definition for I,.

3. Calculation of Thrust by Momentum Theorem. The momentum theorem of fluid mechanics states that the time rate of change of a bounded mass system of discrete particles ( a body of Jluid for example) in any direction i s equal to the resultant of the external forces acting on the boundaries in the speciJied direction and i s independent of the internal forces. (2) The mathematical statement of this principle is where AM = ORDP 20-282 the change in momentum of the body of fluid. Fez1dr= the time impulse of the external force = 'v F = % 90 V, + (pe-po)Ae (3-74 EZL.

Values of the theoretical specific impulse 1: for several liquid propellant combinations based on frozen composition, are presented in Chapter 5. Table 6 presents the enthalpies of formation of fuels, Table 7 the enthalpies of formation of oxidizers, and Table 8 the enthalpies of formation of reaction products. The calculation of the isentropic exit velocity V,' involves determining the enthalpies h, and h: (see equation 4-1). It has been pointed out that h, is determined from the composition of the equilibrium gas mixture at the entrance to the exhaust nozzle, and the combustion temperature t,.