Rocket performance

RocketPropella.nts, Liquid propellants have long been used to obtain maximum controUabiUty of rocket performance and, where required, maximum impulse. Three classes of rocket monopropellants exist that differ ia the chemical reactions that release energy (/) those consisting of, eg, hydrogen peroxide, ethylene oxide, C2H4O and nitroethane, CH2CH2NO2 that can undergo internal oxidation—reduction reactions (2) those... 

S. Gordon and B. J. McBride, "Computer Program for Calculation of Complex Chemical Equilibrium Composition, Rocket Performance, Incident and Reflected Shocks, and Chapman-Jouget Detonations," NASA SP-273, Interim Revision, NTIS, Springfield, Va., Mar. 1976. 

Solid rocket performance during rapid pressure increases differs greatly from predictions based on steady-state burning rate data, Rapid pressurization (150—250kpsi/ sec) following a sudden throat-area decrease in... 

It can be shown that if the pressure index of the propellant exceeds 1 the rate of gas increase by factor 2 exceeds the rate of gas loss by factor 1, so that the pressure builds up in the motor, which finally explodes. Quite apart from such an extreme case, a low pressure index in the propellant is desirable so that irregularities in burning are quickly smoothed out with the least effect on rocket performance. It is for this reason that platonising agents mentioned on p. 181 are important, because they enable a very low pressure index to be achieved at ordinary operating pressures of the order of 14 MPa. 

Gordon, S., and McBride, B. J., computer program for calculation of complex chemical equilibrium compositions, rocket performance, incident and reflected shocks and Chapman-Jougonet detonations, NASA SP-273 (1976). 

With these simplifications typical computed values of LP rocket performance (according to Ref 12, pp 453—64) are given in Table 4... 

Additional computational results are given in Table 2 which also shows major exhaust gas products. Parametric charts of rocket performance for specific missions are given by Jortner (Ref 17, p 471). Further data on rocket performance from the point of view of weight and volume limited systems are presented by Mellish Gibb (Ref 17,... 

Gordon, S., and Bride, B.Mc (1976) Computer Programme for Calculation of Complex Chemical Equilibrium Compositions Rocket Performance, Incident and Reflected Shock and Chapman-Jouguet Detonations, NASA 20-273. 

With respect to the structure of this monograph one finds that the purpose of the second chapter is to develop by ideal rocket theory, and to discuss, the rocket performance parameters and, in particular, the significance of these parameters. The third chapter is a review of the pertinent chemical thermodynamics. Of importance are the thermochemical nomenclature, the discussion of the equiUbrium constant and the handling of condensed phases, the methods of determining the combustor... 

Cox, J. D. and Pilcher, G. Thermochemistry of Organic and Organo-metallic Compounds, Academic Press, London 1970 Huff, V. N Gordon, S. and Morell, V. . General method and thermodynamic Tables for Computational of Equilibrium Composition and Temperature of Chemical Reactions, NASA Report 1073 (1973) Gordon, S. and Bride, B. J. Computer Program for Calculation of Complex Chemical Equilibrium Compositions, Rocket Performance, Incident and Reflected Shocks and Chapman-Jouguet Detonations, NASA Report SP-273 (1971)... 

Figure 2.11 schematically shows the pressure profile which is one factor that influences rocket performance. The length of the arrows shows the contribution of the pressure from inside and outside the walls. While the atmospheric pressure outside is constant, the inside pressure of the combustion chamber is at its largest and decreases in the direction of the nozzle end. The pressure term is proportional to the diameter Ae ... 

The theoretical characteristics of the rocket motor propellant may be derived from the analysis of the expansion of the combustion products through the nozzle. The first step in the calculation of the theoretical rocket performance is to calculate the parameters in the combustion chamber, and the next step is to calculate the expansion through the nozzle (see Fig. 4.3). The expansion through the nozzle is assumed to be isentropic (AS = 0). The EXPL05 and ICT program code provide the following options ... 

Does the Kelvin statement apply to rocket performance Or to engines operating on a single stroke ... 

Coefficients for equations which express the dependence of heat capacity, enthalpy, and entropy on temperature, in the range 150-6000 K have also been computed [801] for the purpose of obtaining equilibrium compositions and theoretical rocket performance of propellants the form of the equations are given below (the actual coefficients are too dated to be worth quoting) ... 

Calculating theoretical rocket performance for finite- or infinite-area combustion chambers. 

The program produces different output including tables of thermodynamic and equilibrium data and information about the iteration procedures. The report provides particular information on rocket performance, detonation, and shock parameters that helps to decide the appropriate rocket design in the engineering process. 

---