Accession Number:

ADA222624

Title:

Analysis of the Flight Performance of the 155 mm M864 Base Burn Projectile

Descriptive Note:

Technical rept.

Corporate Author:

ARMY BALLISTIC RESEARCH LAB ABERDEEN PROVING GROUND MD

Personal Author(s):

Report Date:

1990-04-01

Pagination or Media Count:

58.0

Abstract:

An engineering model has been developed to compute the flight performance of the M864 base burn projectile. This model includes the coupled performance of the gas generator, effects of injected mass flow on the aerodynamics, and a modified point mass trajectory simulation. The gas generator model is based on measured burn rates and basic fluid dynamics. The discharge rate of the generator is calibrated against laboratory experiments. Effects of spin on burn rate are deduced from comparison of analysis with spin fixture tests. Linear and first order nonlinear effects of mass injection on base pressure are the basis for evaluation of base drag. Navier-Stokes solutions near the base with air injection provides essential data. Correlation equations predict base pressure as a function of Mach number, injection rate, and propellant gas temperature. Temperature effects on base pressure are a unique feature of the analysis. Keywords Injection of combustion products, Base burn, Base bleed, Spin, Trajectory, Navier-Stokes computations, Solid propellant.

Subject Categories:

  • Ammunition and Explosives

Distribution Statement:

APPROVED FOR PUBLIC RELEASE