Aerospace & Aviation

Hypothesis on tektite origin by comet impact with earth

Near-ultraviolet, visible and infrared spectroscopy of sodium and potassium thiocyanate

Low pressure rocket extinction

Microspectrophotometry

Longitudinal aerodynamic characteristics of semispan v/stol tilt-wing configuration with single rotating propeller

Constrained turbulent shear flows of newtonian fluid solvents with polymer solutes - elastic viscous fluids

Nasa aerospace nuclear radiation safety philosophy

Equatorial electrojet investigation by sounding rockets with magnetometer

Steam rankine cycle solar power system

Digital computer approximation of automatic control piecewise linear systems by integral equations

Attenuation of solar flares by aluminum shields of slab and spherical-shell geometries of varying thickness

Electron emission test of uranium carbide compatibility with tungsten alloys for nuclear fuel elements

Parts 2 and 3 present tabulations of trajectory data for scheduling flights to and from Venus and Mars during the period 1960-2000. Part 2 contains information for outbound flights to these planets; Part 3 contains information for trajectories returning from the planets to Earth. Each Part contains data for single-plane transfers, as well as for broken-plane transfers which employ a midcourse plane-change to eliminate the high speed "ridges." The mathematical analyses employed for all calculations are described in Part 1 of this handbook. To facilitate the construction of round-trip trajectories, the date at the target planet is held fixed while the trip duration is varied in 10-day increments from zero days to the length of that planet's synodic period with Earth. Dates of arrival at the target planet are presented in the extreme right-hand column of Part 2, and dates of departure from the target planet are presented in the extreme left-hand column of Part 3. Thus, by holding Part 2 directly to the left of Part 3, the analyst may easily and rapidly scan all trip possibilities which involve any desired stopover time at the target planet. Within approximately 200 days of each conjunction or opposition, data are presented in 10-day increments at the target planet. Only those trips are listed for which the hyperbolic excess speeds at either or both ends of the trajectory do not exceed 0.6 EMOS (Earth Mean Orbital Speed). For the remaining mission regions, the requirements are so smoothly varying that a 50-day interval in dates at the target planet may be employed; the 10-day interval in trip times is, however, preserved here. In these regions, only those trips are listed for which either or both speeds do not exceed 0.3 EMOS.

Ranger vi probe launching - lunar photographic mission