Burning, solid propellant composite

Scanning Electron Microscopy in the Study of Solid Propellant Combustion. Part 111. The Surface Structure and Profile Characteristics of Burning Composite Solid Propellants , NavWeps-Cent r TP 5142-Part 3 (1971) 48) B.T. 

Composition Variables on Acceleration-Induced Burning-Rate Augmentation of Solid Propellants , NASA TND-6923 (1972) 13) G.W. 

Steinz, J. A., Stang, P. L., and Summer-field, M., The Burning Mechanism of Ammonium Perchlorate-Based Composite Solid Propellants, Aerospace and Mechanical Sciences Report No. 830, Princeton University, 1969. 

Ramohalli, K. N. R., Steady-State Burning of Composite Propellants, Fundamentals of Solid-Propellant Combustion (Eds. Kuo, K. K., and Summerfield, M.), Progress in Astronautics and Aeronautics, Vol. 90, Chapter 8, AIAA, New York (1984). 

K. Yamazaki K. Kishi, Composite Solid Propellant Containing Preshaped Oxidizer Salt-Metallic Fuel-Burning Rate Controller Particles , USP 3454437 (1969) CA71, 161... 

Figure 2. Pressure dependence of burning rate of a composite solid propellant with 75% AP + 25% polyester resin (99)...

CA 48, 11061(1954) (Erosive burning of some composite solid propellants) 37) H.H. Abram, T. Williams K.F. Allen, Examination of Six QF 17-pr Gun Barrels Used in Ballistic and Erosion Trials of Propellants of Various Compositions and Flame Temperatures , Armament Research Establishment Metallurgy Report No 8/54, Woolwich,... 

NTO is being developed in many areas these include i) a substitute for ammonium perchlorate or ammonium nitrate in solid rocket propellants, since it does not liberate undesirable products such as HC1 and has quite a high burn rate compared to ammonium perchlorate and ammonium nitrate, ii) used as a burning rate modifier for composite propellants, iii) replacing RDX and HMX in composite solid propel-... 

Solid propellants may be classified as monopropellants or composite propellants. Monopropellants are substances in which the fuel and oxidizer are both contained within the same molecule or at least in a single phase. These materials may either burn slowly at subsonic rates or may decompose rapidly in detonation. Depending on the use to which this type of material is put, it may be classified either as propellant or high explosive. In general, useful monopropellants are difficult to detonate. The typical example of a monopropellant is the so-called double-base propellant. This substance consists of nitrocellulose which has been colloidized by nitroglycerine along with various minor constituents which have been added to... 

PATR 2488(1958)(New formulas for rapid calcn of linear burning rates of solid proplnts) 32)J. Delacarte et al, MP 41, 223 65(1959)(Contribution to study of rates of burning and other props of composite proplnts) 33)J Taylor, "Solid Propellant and Exothermic Compositions , Interscience, NY(1959), 55-6 34)C.Napoly, MP 42, 229-46(1960)(4 refs)(Relations between linear rate of burning, apparent potential and pressures for proplnts consisting of only NC, NG and Centralite) 35)Anon, "Ordnance Proof Manual , Aberdeen Proving Ground, Md,7-24 36)L.Shulman et al, PATR FRL-TR 41(1961)... 

Princeton Univ Press, Princeton, NJ(1956),pp 470-513(70 refs) 24)C.Hugget, "Combustion of Solid Propellants , in the above book by Lewis et al,pp 514-74(98 refs) 25)F.A.Warren, "Rocket Propellants , Reinhold, NY(1958), 88-107 l37-40(Burning and burning rate of rocket propellants) 26)J.Taylor, "Solid Propellant and Exothermic Compositions , Interscience, NY(1959), 100-4(Burning rate of rocket proplnts) 27)J. 

Burning rate of composite proplnts) l4a)F.J.Hendel, "Chemical Rocket Propulsion Systems", ChemEngrg 68, No 3, 107-10 (1961) (Solid proplnts) l4b)L.Nadaud, "Die Verbrennug der Metallhaltigen Festen Treib-stoffe , Explosivst 1962, 186-93 (The combustion of metal-contg solid proplnts) 15)M. J.Zucrow, "Propulsion and Propellants ,... 

L.H. Caveny et al, Evaluation of Additives to Reduce Solid Propellant Flammability in Ambient Air , BRL Contract Rept 278, Princeton Univ, Princeton, Contract DAAD05-72-C-0135) (1975) (ADA-019108), 15,17, 73 [The authors expts show that addn of 10% tritotyl phosphate is the most effective means of lowering the mass burning rate and reducing flammability limits of a control HMX composite pro-pint. The proplnt compn consisted of HMX/-3,3 -bitolylene 4,4 -diisocyanate, hydroxyl-terminated polyethylene oxide of 400 mw, trime-thylolpropane trimethacrylate and ferric acetyl-acetonate (75/25%)] 62) N. Kubota T. 

W. Nachbar and G. B. Cline, Jr., The Effects of Nonstoichiometric Composition and Particle Size on the Burning Rates of Composite Solid Propellants, Tech. Note 3-64-62-1, Contract No. AF 49 638)-4I2, Lockheed Missiles and Space Company, Palo Alto (1962) presented at Fifth AGARD Combustion and Propulsion Colloquium, Braunschweig (1962). 

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