This 1962 instruction manual has been ready as one among a sequence at the layout of ballistic missiles. It provides the equations of movement as utilized to either easy and intricate trajectory stipulations; analyzes the ability part, vacuum section, and re-entry part of missile trajectories together with a few of the corrections which needs to be thought of; and discusses definite particular subject matters similar to pass and go with the flow trajectories, and Coriolis impression. Simplified graphs of required release angles to acquire wanted trajectories from a variety of preliminary latitudes and velocities also are integrated.
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Additional resources for Ordnance Engineering Design Handbook - Ballistic Missile Series - Trajectories (U)
To find the exact range error, the range, T , is first calculated for the desired cutoff velocity vector, v o using the expression I 1 tan \I Next, the range corresponding to the actual velocity vector, va, is determined by substituting va for v o in Equation (4-25). The difference between these two range values is, of course, the range error. Table 4-2 illustrates the range error resulting from velocity errors in the firing plane. This table applies only to optimum conditions. Using the constants, k (sec-I) and f t found in Table 4-2 for Equation that range error due to errors in magnitude and velocity direction obtained k' deg2/ (4-26), velocity can be ORDP 20-284 TABLE 4-3.
Error in time of cutoff 5. computer errors. The magnitude of these errors a t cutoff is reproduced in Table 3-2 for a 1500 n mi and a 5500 n mi missile. An explanation of u used in this table is given in Chapter 6. 1s The range and deflection errors for the 5500 n mi missile are 24,000 feet and 4600 feet respectively. For a radio-guided missile these errors are approximately the same. However, for short range, inertial guidance gives better range accuracy; for the long ranges, radio guidance gives better range accuracy.
MI = mass of everything in the itb stage including structure, plumbing, propellant, propellant tanks, engine, etc. m, = same as MI except mass of propellant is excluded Figure 3-5. 2, the characteristics of the individual steps may be listed as: warhead whose weight is included in m.. 2. 1. x i ; the payload ratio of step i is expressed as 5iM * 3. ti; propellant mass ratio of step i is expressed as mass or propellant in ithstep si = total remaining mass - M i - mi (3-26) n where the payload of ith step = the structural factor of step i is expressed as mi El = Mi (3-27) ei; M, 2M.