Abstract
A gas generating propellants are used as initiators of liquid rocket propellants turbopumps and have as desired characteristic a high-volume production of low-temperature gas. In this context, some formulations of composite propellant containing polyurethane (based on liquid hydroxyl-terminated polybutadiene), guanidine nitrate, ammonium perchlorate, and additives were evaluated and characterized in order to verify their potential as gas generator propellant, as well as to evaluate the influence of additives on mechanical properties. The formulations were prepared, analyzed, and tested for mechanical properties.
Highlights
The composition of solid propellants consists basically of a binder such as polyurethanes based on liquid hydroxyl-terminated polybutadiene (HTPB), an oxidizer such as ammonium perchlorate, curing agent, plasticizer, metallic additives, ballistic modifiers, among others (Kishore and Sridhara 1999)
The propellant samples were prepared based on the composition described in Table 1, using HTPB (Liquiflex – batch 19/90) as a binder; as solid load: ammonium perchlorate (IAE – batch 002/2014) and guanidine nitrate (GUNI, Chemical Point – batch CP4139) as oxidizers, and copper acetylacetonate (CuAA), synthesized according to Cardoso et al (2019), as a catalyst for thermal degradation of HTPB
An essential requirement for a gas generator propellant for aerospace application is the temperature of the gases exiting the nozzle throat, which has to be lower than 1100 °C (Almeida and Pagliuco 2014)
Summary
The composition of solid propellants consists basically of a binder such as polyurethanes based on liquid hydroxyl-terminated polybutadiene (HTPB), an oxidizer such as ammonium perchlorate, curing agent, plasticizer, metallic additives, ballistic modifiers, among others (Kishore and Sridhara 1999). The gas generator propellant, in turn, can have a wide range of applications: in-car safety systems (airbags), fire extinguishers (Puccio et al 2011), or even as a liquid rocket-motor turbopump initiator (Salgansky et al 2019; Harikrishnan et al 2018). This type of material has as its main characteristic the production of a large volume of gases in a small-time interval (Puccio et al 2011). The low adiabatic flame temperature imposes a challenge for this type of propellant to ignite and maintain a self-sustaining burning
Sign-in/Register to view highlights & summary Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
