Experimental and Numerical Characterization of Polymer Nanocomposites for Solid Rocket Motor Internal Insulation

2009 ◽  
Author(s):  
J. H. Koo ◽  
O. A. Ezekoye ◽  
M. C. Bruns ◽  
J. C. Lee
Keyword(s):  
Polymer Nanocomposites ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Numerical Characterization ◽  
Solid Rocket

Development of a Novel Ablative Composite Tape Layup Technology for Solid Rocket Motor Nozzle and Liquid Engine Liners

2015 ◽  
Vol 830-831 ◽  
pp. 417-420 ◽  
Author(s):  
L. Mohan Kumar ◽  
K.M. Usha ◽  
E.N. Anandapadmanabhan ◽  
P. Chakravarthy
Keyword(s):  
New Technology ◽  
Rocket Motor ◽  
Operating Conditions ◽  
Solid Rocket Motor ◽  
Cylindrical Blank ◽  
Static Test ◽  
Composite Tape ◽  
Good Potential ◽  
Solid Rocket

Solid rocket motor nozzles and liquid engine throats use ablative composite materials to protect the structures from the extremely severe operating conditions of high temperature, pressure and particle impingement. These ablative nozzle liners are processed from carbon phenolic/silica phenolic prepregs using a complex processing cycle. The process starts from impregnating the fibres with phenolic resin followed by either moulding or wrapping/winding prepreg tapes over metallic mandrels followed by polymerization under pressure. Traditionally, prepreg is cut into straight tapes and wound on mandrels to form the divergents. For throats and convergents, prepreg patterns are cut and stacked for curing. Plies of shape conforming to the development of base cone are cut from the prepreg and wound on the mandrel. After polymerization, the final required configuration is machined from this cylindrical blank after the liners are cured. The new method, described in this paper, replaces the straight-cut prepreg tapes by bias-cut prepreg tapes. These can be used for ablative liners in which the plies are at an angle to the direction of the flow. Bias tapes are cut at 45° to the warp and weft directions of the fabric to the required width and formed to the required frustum of cone. Since the cone is formed from straight cut bias tape, the fibre construction will be uniform around the circumference unlike the pattern cut tape. The efficiency of this process depends on the wrapping ratio which is in turn a function of the diameter, ply angle and tape width. To get the best wrapping ratio, shaped mandrels are used which brings down the material wastage and machining allowances. This paper describes the attempts to develop the Bias wrapping technology for angle wound liners. The details of process trials, challenges faced and how they were overcome, advantages of the process over conventional process etc are explained. Exhaustive material characterization of the material was done. Property comparison and validation of performance in subscale tests and a full scale static test are also discussed. The analysis indicates that this new technology has good potential in replacing the traditional tape-winding technology for rocket motor nozzle liners.

Thermal insulation by heat resistant polymers for solid rocket motor insulation

2011 ◽  
Vol 46 (13) ◽  
pp. 1549-1559 ◽  
Author(s):  
Ashraf Fathy Ahmed ◽  
Suong V Hoa
Keyword(s):  
Carbon Fiber ◽  
Flame Retardant ◽  
Rocket Motor ◽  
New Method ◽  
Ethylene Propylene Diene Monomer ◽  
Solid Rocket Motor ◽  
Fabrication And Characterization ◽  
Solid Rocket ◽  
Master Batch

A new method for the development (design, fabrication, and characterization) of asbestos-free rubbers for use as rocket motor insulators is presented. Such insulation is based on chopped carbon fiber (CCF) and aramid fiber in pulp form asreinforcement for ethylene propylene diene monomer (EPDM) along with ammonium polyphosphate (AP) flame retardant agent. Six millimeters long CCFs and/or Kevlar pulp (KP) are dispersed in the EPDM polymeric matrix to obtain a homogenous master batch for curing. The new method involves the development of two types of prepregs andthe lamination of these types of prepregs. The first one consists of CCF/EPDM/AP (50 phr CCF) and the second type of prepreg KP/EPDM/AP (30 phr KP). Laminates composed of six alternative layers of these prepregs have been shown to exhibit better thermal, mechanical, physical, and ablative properties than their non-laminated counterparts.

Design of a Solid Rocket Motor for Characterization of Spinning

2011 ◽  
Vol 63-64 ◽  
pp. 621-626
Author(s):  
Zai Cheng Wang ◽  
Chun Lan Jiang ◽  
Ming Li
Keyword(s):  
Rocket Motor ◽  
Structure Characterization ◽  
Test Results ◽  
Solid Rocket Motor ◽  
Ballistic Performance ◽  
Static Test ◽  
Rocket Propulsion ◽  
Working Performance ◽  
Solid Rocket

Although the rocket propulsion technologies have been used for several decades, the traditional motor can not meet the special rotating requirement. A kind of spinning solid rocket motor (SSRM) which used as power device of some kinds of dispenser was introduced. This kind of motor has the structure characterization for tangential nozzles. Its design scheme and prediction of interior ballistic performance were discussed. And the main factors should to be considered in design were analyzed comprehensively. In order to research working performance of the SSRM static test was carried out. The calculation and test results indicate that the design can satisfy general requirement of its application normally.

Kinetics and Thermophysical Properties of Polymer Nanocomposites for Solid Rocket Motor Insulation

2009 ◽  
Vol 46 (3) ◽  
pp. 526-544 ◽  
Author(s):  
David W. K. Ho ◽  
Joseph H. Koo ◽  
Ofodike A. Ezekoye
Keyword(s):  
Polymer Nanocomposites ◽  
Thermophysical Properties ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Solid Rocket
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