Rocket, propulsion

The momentum equation at the nozzle exit is represented by thg du = -A dp,., and dthg = Ofor a steady-state flow at the nozzle. Thus, from Eq. (1.64), one obtains the 

The maximum thrust is obtained atp = p , i. e., when the pressure at the nozzle exit is equal to the ambient pressure. 

However, it must be noted that Eq. (1.62) is applicable for ramjet propulsion, as in ducted rockets and solid-fuel ramjets, because in these cases air enters through the inlet and a pressure difference between the inlet and the exit is set up. The mass flow rate from the inlet m plays a significant role in the generation of thmst in the case of ramjet propulsion. 

If one can assume that (1) the flow is one-dimensional and in a steady-state, (2) the flow is an isentropic process, and (3) the combustion gas is an ideal gas and the specific heat ratio is constant, the plots of p vs. v and of h vs. s are uniquely determined, The enthalpy change due to the combustion of the propellant is given by 

---

J. G. Baet2, Characterisation of Advanced Solid Pocket No ffe Materials (SAMSO-TR-75-301), Air Eorce Rocket Propulsion Laboratories, Edwards AEB, Calif., Dec. 1975. 

J. E. Tormey, "Processing and Manufactuie of Composite Propellants," Proceedings of the AGARD Colloquim, Advances in Tactical Rocket Propulsion, CIRA Pub., Pelham, New York, 1968. 

M. H. Smith, "The Literature of Rocket Propulsion," ia The Eiterature of Chemical Technology, Mdvances in Chemisty, Series No. 74, American Chemical Society, Washington, D.C., 1968, p. 581. 

G. P. Sutton, Rocket Propulsion Elements, 5th ed., John Wiley Sons, Inc., New York, 1986. 

S. S. Peimer, Chemical Rocket Propulsion and Combustion Research, Gordon and Breach Science PubHshers, New York, 1962. 

L. A. Dee, Analysis of Nitrogen Trifluoride, AERPL-TR-76-20 (AD-A022887), Air Eorce Rocket Propulsion Laboratory, Edward Air Eorce Base,... 

Rakete,/. rocket (leas often) firecracker. Raketen-antrieb, m. rocket propulsion, -bombe, /. rocket bomb, -leuchtgeschoss, n. rocket flare fire, -satz, m. rocket composition rocket attachment, -verfahren, n., -vortrieb, m. rocket propulsion, -wurf-maschine, /. rocket laimcher, rocket projector. -zeichen, n. rocket signal. 

Y. M. Timnat, Advanced Chemical Rocket Propulsion, Academic, New York (1987). 

Solid Rocket Propulsion Technology, (A. Devenas, ed.), Pergamon, Oxford (1993). 

The first experiments with the thermal electric engine were conducted in Russia in 1929 by its inventor, Valentin P. Glushko, who later became a world-famous authority in rocket propulsion. For more than forty years, the United States and Russia have devoted many resources to research and development of various kinds of EREs. First tested in space by the Russians in 1964, these engines have found some limited applications in modern space technology. For more than two decades Russian weather and communication satellites have regularly used electric rocket engines for orbital stabilization. The first spacecraft to employ ERE for main propulsion was the American asteroid exploration probe Deep Space 1, launched in 1998. The performance of... 

Hydrazine, N2H4, can be burned with oxygen to provide energy for rocket propulsion. The energy released is 150 kcal per mole of hydrazine burned. 

C.F. Callis, Tarticle Size , J. Wiley, NY (1963). 27) C.H. Johnson, J.E. Christian A.W. Tiede-mann, Jr, Bulletin Nineteenth Meeting Inter agency Chemical Rocket Propulsion Group-Working Group on Analytical Chemistry, St. Paul, Minnesota, 265-269 (1963) 28) H.L. 

Air Force Rocket Propulsion Laboratory Scientific and Engineering Seminar Abstracts—... 

S.S. Penner, Chemical Rocket Propulsion Combustion Research , Gordon Breach,... 

Composite proplnts, which are used almost entirely in rocket propulsion, normally contain a solid phase oxidizer combined with a polymeric fuel binder with a -CH2—CH2— structure. Practically speaking AP is the only oxidizer which has achieved high volume production, although ammonium nitrate (AN) has limited special uses such as in gas generators. Other oxidizers which have been studied more or less as curiosities include hydrazinium nitrate, nitronium perchlorate, lithium perchlorate, lithium nitrate, potassium perchlorate and others. Among binders, the most used are polyurethanes, polybutadiene/acrylonitrile/acrylic acid terpolymers and hydroxy-terminated polybutadienes... 

For the reader interested in more elaborate treatments of the influence of mechanical properties upon rocket motor service life, the meeting papers of the Interagency Chemical Rocket Propulsion Group, Mechanical Behavior Working Group, as published by the Chemical Propulsion Information Agency are recommended... 

J.W. Jones, APL Bull Meeting, Interagency Chem Rocket Propulsion Group, Working Group Mech Behavior, 3rd, 1, 371—94 (1964)... 

Many of these substances have been investigated in the context of rocket propulsion technology, since, chemically, the combustion of rocket fuels is related to the combustion of incendiary agents. Though by-products of rocket research may be theoretically of interest as potential incendiary agents, it remains to be seen whether they are feasible economically (Ref 7.n 103)... 

A6. Anderson, R., and Brown, R. S., paper presented at ICRPG (Interagency Chem. Rocket Propulsion Group) Combust. Instability Con/., 1st, Orlando, Florida, 1964. 

H8. Hightower, J. D., and Price, E. W., presented at ICRPG Interagency Chem. Rocket Propulsion Group) Combust. Conf, 2nd, Los Angeles, California, 1965. 

Despite the fact that thermo-acoustic instabilihes have been studied for more than a century, their control and elimination in practical combustion devices is still a problem that is difficult to master, particularly in devices with a high energy density such as aero-engines and rocket propulsion systems [24-28]. 

Polymers which give mouldable propellants are mixed with the oxidiser in a similar manner, but the product is usually worked mechanically between rolls and evacuated to remove air bubbles. The powder is then moulded by pressure into the metal casing. Alternatively, such plastics can give a propellant which can be extruded into charges which are afterwards cut and machined to suitable shape. The Rocket Propulsion Establishment at Westcott has used ammonium perchlorate and polyisobutene to produce a propellant of putty-like consistency. 

The design of propellants for solid fuel rockets differs considerably from that for ordnance, because of the lower operating pressures, usually below 15 MPa. To understand the principles involved it is first necessary to give a brief account of rocket propulsion. In this account considerations will be restricted to motors based on solid propellants. Motors based on liquid fuels, such as petroleum fractions and liquid oxygen, depend on combustion processes of non-explosive type. 

Table 19.3 Missiles with Solid-fuel Rocket Propulsion... 

Barrere, M., Jaumotte, A.,de Veubeke, B. F., and Vandenkerckhove, J., Rocket Propulsion. Elsevier, Amsterdam, 1960. 

Corner, J., Theory of the Interior Ballistics of Guns. Chapman Hall, London, 1950. Daboo, J. E., Solid-fuel Rocket Propulsion. Temple Press, London, 1962. 

Injection of oxygen is used to initiate the metal-water reaction in rocket propulsion systems. 

Mixtures with triethylaluminium have been used as hypergolic igniters in rocket propulsion systems. 

---