This 1962 guide has been ready as certainly one of a chain at the layout of ballistic missiles. It offers the equations of movement as utilized to either uncomplicated and complicated trajectory stipulations; analyzes the facility section, vacuum part, and re-entry section of missile trajectories together with some of the corrections which needs to be thought of; and discusses sure precise subject matters comparable to pass and go with the flow trajectories, and Coriolis influence. Simplified graphs of required release angles to procure wanted trajectories from numerous preliminary latitudes and velocities also are integrated.

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Extra resources for Ordnance Engineering Design Handbook - Ballistic Missile Series - Trajectories (U)

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For calculation purposes, it is also assumed that a standard atmosphere exists, and that the drag and the lift characteristics of the missile are known. Then the variations from the standard conditions are considered, and new impact points are found and compared to the impact point determined under standard conditions. After this, the warhead shape giving minimum dispersion of impact point or other desirable characteristics can be selected. * Boost-glide vehicles discussed later in this chapter are ballistic vehicles which employ lift in reentry and may travel appreciable distances in the low density fringes of the atmosphere.

M. W. , Great Britain, August 1954. , Missile Systems Div. , 15 January 1957. (Secret) Lapp, P. , Trajectory Studies, Vol. I, (Dr. of Sc. Thesis), MZT/T-63, Massachusetts Institute of Technology, 1955. A S T Z A Document No. A D 4 6 102. Fried, B. J. and Richardson, J. , “Optimum Rocket Trajectories,” Journal of Applied Physics, Vol. 27, No. 8, PP. 955-61, August 1956. Culler, G. , and Fried, B. --. of Applied Physics, Vol. 28, No. 6. pp. 11. 12. 13. 14. 15. 16. 17. 18. 672-6, June 1957. , “A Calculation of Variations Solutions to Goddard’s Problem,” Astronautica Acta, Vol.

For these, the vacuum phase may be ignored since the missile proceeds directly from the power phase to the reentry phase. The major purposes of this chapter are (1) to present the equations of motion for a missile in free flight assuming no atmosphere, and (2) to demonstrate the effects of variations in cutoff conditions upon the point of re-entry into the atmosphere. The equations of motion presented are with respect to a homogeneous sphere. The effects of the earth’s nonsphericity, the slight atmosphere above the reference sphere, the earth’s revolution about the sun, the precession of the earth’s axis, the gravitational effects of heavenly bodies, and other variations of the actual from the ideal are examined.

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