Burning rate characteristics

The burning rate of the NC-NG propellant is higher than that of the NC-TM ETN propellant in the pressure range between 0.1 MPa and 10 MPa. However, the pres- 

Combustion products mole fraction mole fraction 

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It can be concluded that if axial combustion instability is observed it can be eliminated by simple ballistic design changes such as propint burning rate characteristics, motor operating pressure decrease, or a reduction in grain length... 

From these many considerations, the propellant formulator is often faced with preparing a propellant with rather precise 7sp and burning-rate characteristics. As a result, there is considerable interest in understanding the basic propellant combustion and ignition processes and in developing the capability to prepare from theory propellants with the desired burning-rate and 7sp characteristics. 

The prediction of burning-rate characteristics, on the other hand, has not been possible. This has caused rocket designers to adopt a trial-and-error approach to the development of specific propellants to meet specific mission requirements. In an effort to reduce the large development effort required for each new propulsion system, considerable basic research effort has been directed toward the definition and quantitative characterization of propellant combustion mechanisms. The ultimate objective of this effort is to provide methods for predicting the burning-rate characteristics of particular propellant formulations. 

Horton and Price (H11) have obtained acoustic-admittance data for a series of double-base and composite propellants with different burning-rate characteristics. They examined the effects of pressure at various frequencies... 

Komai, L, Kobayashi, K., and Kato, K., Burning Rate Characteristics of Glycidyl Azide Polymer (GAP) Fuels and Propellants, Solid Propellant Chemistry, Combustion, and Motor Interior Ballistics (Ed. Yang, V, Brill, T. B., and Ren, W.-Z.J, Progress in Astronautics and Aeronautics, Vol. 185, Chapter 2.9, AlAA, Virginia, 2000. 

Fig. 6.5 Calculated burning rate characteristics of a double-base propellant.

Fig. 6.6 shows burning rate characteristics as a function of KNOj). The burning rates are seen to increase linearly with increasing pressure in In r versus In p plots... 

Burning Rate Characteristics 7.1.2.1 Effect of AP Particle Size... 

Fig. 7.46 Burning rate characteristics of non-catalyzed and catalyzed HMX composite propellants.

Fig. 7.51 Burning rate characteristics of AP composite propellants composed of coarse AP and fine AP particles.

Fig. 7.52 Burning rate characteristics of RDX composite propellants composed of coarse RDX and fine RDX particles.

Fig. 7.57 Effect of binder on the burning rate characteristics of RDX composite propellants (HTPB and HTPE).

Fig. 7.58 Burning rate characteristics of AP, AP-RDX, and RDX composite propellants (HTPE).

Fig. 7.66 Burning rate characteristics of composite propellants composed of HNIW, AP, or HMX, with BAMO/NIMO as a binder.

Kubota, N., and Masamoto, T., Flame Structures and Burning Rate Characteristics of CMDB Propellants, 16th Symposium (International) on Combustion, The Combustion Instimte, Pittsburgh, PA, 1976, pp. 1201-1209. 

Aoki, I., Burning Rate Characteristics of Double-Base and CMDB Propellants, Ph.D. Thesis, Department of Aeronautics, University of Tokyo, Tokyo, 1998. 

Fig. 11.4 Burning rate characteristics of Mg-Tf pyrolants as a function of adiabatic flame temperature.

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