Accession Number : AD0258668

Title :   OPTIMUM SOFT LANDING TRAJECTORIES. PART I. ANALYSIS

Corporate Author : MASSACHUSETTS INST OF TECH CAMBRIDGE

Personal Author(s) : BERMAN,LAWRENCE J.

Report Date : 30 MAR 1961

Pagination or Media Count : 1

Abstract : A variational calculus solution is obtained for the thrust program for minimum propellant consumption to achieve landing of a rocket vehicle from a space orbit with zero relative velocity at touchdown, under the simplifying assumptions of no atmospheric forces and a uniform (i.e., flat-earth) gravitational field. These assumptions are appropriate for lunar landing of a moderately high thrust rocket. The results of the variational solution are interpreted to provideAN APPRECIATION OF THE PHYSICAL NATURE OF THE REQUIREMENTS ESTABLISHED BY DIFFERENT INITIAL CONDITIONS, AS SPECIFIED BY INITIAL ALTITUDE AND VELOCITY VECTOR. Representing the initial conditions parametrically by an equivalent energy altitude and the actual altitude, five different regimes are identified and the corresponding thrust programs described. (Author)

Descriptors :   *LANDING IMPACT, *SPACE FLIGHT, CALCULUS OF VARIATIONS, LANDING, LUNAR PROBES, ORBITS, PARTIAL DIFFERENTIAL EQUATIONS

Distribution Statement : APPROVED FOR PUBLIC RELEASE