MODIFICATION OF COMMERCIAL ROCKET MOTORS FOR TACTICAL APPLICATIONS
Loading...
Authors
Stuffle, Nathan D.
Subjects
commercial
commercial off-the-shelf
COTS
modification
rocket
rocket motor
ignition
blast tube
forward ignition
head-end ignitor
nozzle
nozzle cap
nozzle plug
head-end ignition
tactical
tactical applications
rapid response
payload delivery
rocket propulsion
rocket propellant
commercial rocket
solid rocket motor
SRM
commercial off-the-shelf
COTS
modification
rocket
rocket motor
ignition
blast tube
forward ignition
head-end ignitor
nozzle
nozzle cap
nozzle plug
head-end ignition
tactical
tactical applications
rapid response
payload delivery
rocket propulsion
rocket propellant
commercial rocket
solid rocket motor
SRM
Advisors
Brophy, Christopher M.
Date of Issue
2022-06
Date
Publisher
Monterey, CA; Naval Postgraduate School
Language
Abstract
Several design modifications to commercial off-the-shelf solid rocket motors have been evaluated in support of the Naval Postgraduate School tactical rapid-response payload delivery vehicle. The modifications include a novel head-end ignition system and a tailorable nozzle end cap designed to provide reliable at-altitude ignition by improving the transient behavior of the initial combustion chamber pressure rise. The nozzle cap also provides the additional benefit of extending the shelf life of the propellant by creating an environmental seal to prevent ambient humidity from affecting the propellant. A preliminary design of a blast tube was proposed to explore how the motor exhaust could be channeled through a smaller-diameter tube before reaching the nozzle throat, thereby accommodating the volume requirements of aft fin control servos without sacrificing the overall rocket diameter or precluding use of larger-diameter rocket motors. Implementation of a blast tube also resulted in a favorable shift of the center of gravity of the rocket, which preserved and enhanced control authority during simulated fly-outs. All of the modifications were designed to be directly interchangeable with the OEM hardware to minimize the cost of implementing the new capabilities. Both the head-end ignition and nozzle enclosure systems were successfully demonstrated during flight testing, and a design process for the future implementation of a blast tube was proposed.
Type
Thesis
Description
Series/Report No
Department
Space Systems Academic Group (SP), Mechanical and Aerospace Engineering (MAE)
Organization
Identifiers
NPS Report Number
Sponsors
ONR/NPS
Funder
Format
Citation
Distribution Statement
Approved for public release. Distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.