Engineering topics

Maksimovic, V. M.

Publications and source records attributed to Maksimovic, V. M..

3 records

NASA NTRS1982

Black Brant X third stage dispersion dynamics

The successful development of the Black Brant X (BBX) launch vehicle resulted from the application of a gyroscopically stabilized, unguided third stage motor configuration. Design analyses indicated sufficient gyroscopic stability and acceptable impact dispersion could be realized by optimizing second/third stage separation time. By flying an unguided third stage motor, significant program cost savings were realized. One flight test and two operational missions demonstrated the feasibility of utilizing gyroscopic stability to achieve satisfactory trajectory dispersion on a high performance rocket. A detailed assessment of the major dispersion contributors identified for the first three BBX missions is presented, offering important insight into the dispersion sensitivity of unguided, spin-stabilized flight.

Montag, W. H.↗

NASA NTRS1982

Black Brant X - The low cost development of an advanced sounding rocket system

During the late 1970s it became more and more apparent that an investigation of the regions extending above the earth's dayside polar cusp is very important from a scientific point of view. The feasibility of a mission for implementing such an investigation was studied. It was found that a sounding rocket vehicle having the necessary payload throw capability and the required low trajectory dispersion did not exist within the NASA inventory. It was, therefore, decided to develop a suitable sounding rocket, the Black Brant X (BBX), in a cooperative effort including NASA, the Canadian National Research Council, and a number of aerospace companies. Attention is given to a BBX vehicle description, BBX flight results, and the BBX flight capabilities

Lane, J. H.↗

NASA NTRS1979

A parachute system for upper atmospheric studies

The Goddard Space Flight Center's Sounding Rocket Division successfully flight tested a high altitude, low velocity, 63.5 foot cross parachute system. The system was developed to provide a platform for atmospheric studies at altitudes higher than those attainable with balloons. This paper represents the approach taken to determine the necessary conditions for a successful apogee deployment of the parachute. The test flight deployed the parachute system at an apogee altitude of 61 kilometers. Post-flight results of rocket and parachute performance are compared to the preflight analyses.

Maksimovic, V. M.↗