Abstract
Solid propellants are composite materials with complex microstructure. In a generic form, the material consists of polymeric binder, ceramic oxidizer, and fuel particles (e.g. aluminum). Damage induced by severe stress and extreme temperatures is manifested in particle cracking, decohesion along particle/polymer interfaces, and void opening. In this work, the effect of damage due to particle dewetting on the material macroscopic response is investigated by accounting for large deformations. First, issues pertaining to the constitutive behavior of the individual components in the absence of damage are reviewed. Next, with the use of rigorous composite homogenization theory, a macroscopic constitutive law is devised that accounts for continuous void nucleation and growth upon straining. The standard relaxation and uniaxial tension tests are used to calibrate the model parameters. The model is implemented in our Center's finite element code Rocsolid to study damage evolution in the propellant grain of the Titan IV SRMU PQM-1 rocket motor.
| Original language | English |
|---|---|
| Publication status | Published - Dec 1 2005 |
| Externally published | Yes |
| Event | 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit - Tucson, AZ, United States Duration: Jul 10 2005 → Jul 13 2005 |
Other
| Other | 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit |
|---|---|
| Country | United States |
| City | Tucson, AZ |
| Period | 7/10/05 → 7/13/05 |
Fingerprint
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Control and Systems Engineering
- Electrical and Electronic Engineering
Cite this
Constitutive response and damage in solid propellants. / Aravas, N.; Xu, F.; Sofronis, P.; Namazifard, A.; Fiedler, R.
2005. Paper presented at 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Tucson, AZ, United States.Research output: Contribution to conference › Paper
}
TY - CONF
T1 - Constitutive response and damage in solid propellants
AU - Aravas, N.
AU - Xu, F.
AU - Sofronis, P.
AU - Namazifard, A.
AU - Fiedler, R.
PY - 2005/12/1
Y1 - 2005/12/1
N2 - Solid propellants are composite materials with complex microstructure. In a generic form, the material consists of polymeric binder, ceramic oxidizer, and fuel particles (e.g. aluminum). Damage induced by severe stress and extreme temperatures is manifested in particle cracking, decohesion along particle/polymer interfaces, and void opening. In this work, the effect of damage due to particle dewetting on the material macroscopic response is investigated by accounting for large deformations. First, issues pertaining to the constitutive behavior of the individual components in the absence of damage are reviewed. Next, with the use of rigorous composite homogenization theory, a macroscopic constitutive law is devised that accounts for continuous void nucleation and growth upon straining. The standard relaxation and uniaxial tension tests are used to calibrate the model parameters. The model is implemented in our Center's finite element code Rocsolid to study damage evolution in the propellant grain of the Titan IV SRMU PQM-1 rocket motor.
AB - Solid propellants are composite materials with complex microstructure. In a generic form, the material consists of polymeric binder, ceramic oxidizer, and fuel particles (e.g. aluminum). Damage induced by severe stress and extreme temperatures is manifested in particle cracking, decohesion along particle/polymer interfaces, and void opening. In this work, the effect of damage due to particle dewetting on the material macroscopic response is investigated by accounting for large deformations. First, issues pertaining to the constitutive behavior of the individual components in the absence of damage are reviewed. Next, with the use of rigorous composite homogenization theory, a macroscopic constitutive law is devised that accounts for continuous void nucleation and growth upon straining. The standard relaxation and uniaxial tension tests are used to calibrate the model parameters. The model is implemented in our Center's finite element code Rocsolid to study damage evolution in the propellant grain of the Titan IV SRMU PQM-1 rocket motor.
UR - http://www.scopus.com/inward/record.url?scp=77957856690&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=77957856690&partnerID=8YFLogxK
M3 - Paper
AN - SCOPUS:77957856690
ER -