The effects of propellant inertia and of internal pressurization on the structural response of solid propellant rocket motors subjected to transverse air blast loading have been investigated, both analytically and numerically. The numerical predictions were accomplished using the BRL versions of the PETROS 3.5 computer program, which employs the finite difference method to solve the equations governing finite amplitude elastoplastic response of thin shells. The response of a typical rocket motor configuration was calculated for the limiting situations of the bare motor case and of the motor case containing the complete propellant grain, each with no internal pressurization and with the pressurization resulting from propellant combustion. These calculations showed that the unpressurized motors experience a much larger deformation than the pressurized motors for the same blast loading. The most significant result is the quantification of the greater vulnerability of rocket motors prior to their ignition, whether on the launcher or as upper stages of in-flight missiles. (Author)
Response of a Rocket Motor to Transverse Blast Loading
1979
54 pages
Report
No indication
English
Rocket Engines & Motors , Rocket Propellants , Solid propellant rocket engines , Blast loads , Rocket propellant grains , Pressurization , Structural response , Vulnerability , Deformation , Transverse , Internal pressure , Computer programs , Finite difference theory , Rocket engine cases , Shells(Structural forms) , Thin walls , Solid rocket propellants , Guided missile components , PETROS computer program , Airburst
Response of a rocket motor to transverse blast loading
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