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Energetic Opportunities of Solid Composite Propellants Containing Some Hypothetic Furazano-[3,4-d]-pyridazine-based Derivatives

LEMPERT David B.1，DOROFEENKO Ekaterina M.1，SHU Yuan-jie2，JIANG Wei-dong3，WU Zong-kai2，WANG Ke2，LIU Xiao-qiang3

(1. Institute of Problems of Chemical Physics, Russian Academy of Sciences (IPCP RAS), Moscow 142432, Russia;2. Xi′an Modern Chemistry Research Institute, Xi′an 710065, China;3. School of Chemistry and Environmental Engineering, Sichuan University of Science and Engineering, Zigong Sichuan 643000, China)

Six furazano-[3,4-d]-pyridazine-based derivatives as main compounds in solid composite propellants have been investigated. It was shown that the use of some furazano-[3,4-d]-pyridazine-based derivatives as main compounds in solid composite propellants can considerably increase ballistic parameters compared with HMX if the compounds under consideration contain difluoramine groups. And the use of the compounds under consideration may be successful only in the presence of an active binder and 10%-30% of AP or ADN as additional oxidizers.

solid composite propellant; furazano-[3,4-d]-pyridazine-based derivative; energetic specific impulse

Introduction

The search of new energetic materials is an important topic worldwide[1]. In recent years, much attention is riveted on N-heterocycles, because they have high densities and high standard enthalpies of formation. High-enthalpy propellants require a bit or no aluminum in the formulation, because the energy contained in high-enthalpy N-heterocyclic ring is often enough to warm up the gaseous combustion products to high temperatures (3500K and even higher)[2].

Currently underway is not only an experimental search for new N-heterocycles, but also a lot of investigations on the theoretical search for new high-energy compounds of this class[3], that is rather natural, since such studies facilitate a targeted search of new compounds[4].

In this study, the estimations of properties (densities, standard enthalpies of formation, detonation parameters) of new compounds, some furazano-[3,4-d]-pyridazine-based derivatives, that are not obtained yet, have been carried out.

1 Statement of the problem and research methodology

Ief(1)=Isp+100·(ρ-1.9);

Ief(2)=Isp+50·(ρ-1.8);

Ief(3)=Isp+25·(ρ-1.7) ;

We have considered the propellant formulations containing about 19 volume percents of AB, because at lower volume percentage it is almost impossible to create a formulation having satisfactory rheologic properties of uncured mass and physico-mechanical properties of the cured propellant. Aluminum mass fraction was varied from 0 to 18 %.

Table 1 Properties of hypotetic furazano-[3,4-d]-pyridazine-based derivatives, that were used at calculations.

2 Results and discussion

2.1 Formulations with AP as additional inorganic oxidizers

2.1.1 Formulations with S1 + Al + AP + AB (19% volume fraction) (Fig.1)

Fig.

2.1.2 Formulations with S2 + Al + AP + AB (19% volume fraction) (Fig.2)

Fig.

2.1.3 Formulations with S3 + Al + AP + AB (19% volume fraction) (Fig.3)

Fig.

2.1.4 Formulations with S4 + Al + AP + AB (19% volume fraction) (Fig.4)

Fig.

2.1.5 Formulations with S5 + Al + AP + AB (19% volume fraction) (Fig.5)

Fig.

2.1.6 Formulations with S6 + Al + AP + AB (19% volume fraction) (Fig.6)

Fig.

2.1.7 Formulations with HMX + Al + AP + AB (19% volume fraction)

Fig.

However, at HMX content higher than 50%-60% compositions with Al, HMX and active binders become dangerous and one always uses a bit of AP to provide the necessary combustion law and to reduce the risk of combustion to detonation transfer. So, a real estimation of energetic characteristics of SCP based on HMX has be compared with compo- sitions containing at least 10% AP.

Table 2 Ballistic parameters of the optimal formulations at optimal content of Al and AP

2.2 Formulations with ADN as additional inorganic oxidizers

Fig.

3 Conclusions

(2)The use of the compounds under consideration may be successful only in the presence of an active binder and 10%-30% of AP or ADN as additional oxidizers.

Acknowledge

The investigation was supported by the Russian Ministry of Education and Science accordingly the agreement No.14.613.21.0043 from 10.11.2015, the unique identifier RFMEFI61315X0043.

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10.14077/j.issn.1007-7812.2016.05.004

TJ55;TQ560 Document Code：A Article ID：1007-7812(2016)05-0028-07

Received date:2016-07-25； Revised date:2016-08-20

Foundation:Ministry of Education and Science of the Russian Federation (14.613.21.0043)

Biography:LEMPERT David B.(1946-), male, Ph.D, Professor. Researcher field: Aerospace propulsion. E-mail:lempert@icp.ac.ru