This paper presents a computerized method of determining the external insulation requirements because of aerodynamic heating during the boost phase of flight on a rocket booster.

The computer program’s aim is to aid in weight estimating during the advanced design phase of engineering in a rapid and accurate fashion. Proficient use or the program does not require an extensive background in heat transfer.

The basic requirement for input to this program has one outside dependent parameter. This parameter is that the vehicle fly a normal trajectory or that the trajectory data be based on a related booster vehicle. The trajectory data required are altitude and Mach number at the desired time interval. These data are generally related to a particular thrust-to-weight ratio.

Calculation of the total heat transfer is done by numerical integration within the computer program. The resultant temperature and heat transfer values derived from the program are used to determine the required thickness of the insulation.

The computed temperature is comparable to a mean booster R & D flight program temperature ± 10%.

The insulation discussed in this paper is based on a cork compound. Other types of insulation may be used by varying the proper input insulation characteristics. The computer program is presented so that it may provide a basis for insulation calculations and may be changed to fit any desired vehicle.