Showing papers on "Liquid-propellant rocket published in 1984"
TL;DR: In this article, the influence of radiation scattering on the infrared radiation signature of representative plumes from four types of tactical rocket motors is investigated using the recently developed JANNAF Standardized Infrared Radiation Model (SIRRM) numerical code.
Abstract: The influence of radiation scattering on the infrared radiation signature of representative plumes from four types of tactical rocket motors is investigated using the recently developed JANNAF Standardized Infrared Radiation Model (SIRRM) numerical code. The plumes are modeled as isothermal cylinders with gas and particle compositions representative of 1) advanced liquid rocket exhausts (HC1, HF/carbon); 2) low-temperatu re metal fuel solid rocket exhausts (H2O, HC1, CO/aluminum oxide); 3) reduced smoke low visibility solid rocket exhausts (H2O, HC1, CO, CO2/aluminum oxide); and 4) advanced minimum smoke solid rocket exhausts (CO, CO2, H2O/zirconium oxide). The signatures of the plumes containing carbon particles are sensitive to the amount of carbon present, but insensitive to the carbon particle size. The signatures of the plumes containing aluminum oxide particles are sensitive to both the particle size and the amount of aluminum oxide present. The emission from the advanced minimum smoke plume becomes increasingly sensitive to particle size and concentration as the particle loading increases.
56 citations
01 Jan 1984
TL;DR: In this article, the Star 48 solid rocket engine was used to study the lateral stability problem associated with the rocket engine and it was shown that the shape of the combustion chamber could have a significant effect on the vertical stability of the rocket; specifically, a short and wide combustion chamber is destabilizing, while a long and narrow chamber is stabilizing.
Abstract: Existing methods for the derivation of equations of motion of variable mass systems are reviewed and compared, the end product being a system of general dynamical equations for variable mass systems. These equations are used to study the lateral stability problem associated with the Star 48 solid rocket engine. It is shown that the shape of the combustion chamber could have a significant effect on the lateral stability of the rocket; specifically, a short and wide combustion chamber is destabilizing, while a long and narrow chamber is stabilizing.
13 citations
TL;DR: In this article, the state-space method was applied to the analysis of the dynamic characteristics of a variable thrust liquid propellant rocket engine and presented a set of state equations for describing the dynamic process of the engine.
10 citations
TL;DR: In this article, a digital program simulating the unsteady behavior of a liquid-propellant rocket engine is presented, based on the measurement of the light scattered by illuminated drops, which can be validated and calibrated by considering high concentrations and the rather great diameters of concern.
7 citations
11 Jun 1984
5 citations
01 Jan 1984
1 citations
01 Nov 1984
TL;DR: In this article, the authors developed a model to describe the transport and diffusion of airborne combustion products and unreacted vapors from an accident involving hypergolic liquid rocket propellants.
Abstract: : Titan II weapons systems are charged with hypergolic liquid rocket propellants (hydrazine fuel and nitrogen tetroxide oxidizer). These same propellants are used in support of other systems, including the MX missile and the space shuttle. This effort was designed to characterize the interactions of hypergolic liquid rocket propellants and to provide information pertinent to the development of a model to describe the transport and diffusion of airborne combustion products and unreacted vapors from an accident involving these propellants. This report is prepared in two volumes. Volume II discusses the chemical and physical interactions of the combustion products with air, and the dispersion of these products in the environment. Originator supplied keywords include: Atmospheric dispersion modeling; Hydrazine; Hypergolic fuels; Nitrogen tetroxide; Toxic hazard corridor.
1 citations
01 Nov 1984
TL;DR: In this paper, the authors describe the reactions between nitrogen tetroxide and hydrazine, including the reaction products and the heat released, and determine the combustion time and the height of the resulting fireball before it cools and disperses with the air.
Abstract: : Titan II weapons systems are charged with hypergolic liquid rocket propellants (hydrazine fuel and nitrogen tetroxide oxidizer). These same propellents are used in support of other systems, including the MX missile and the space shuttle. This effort was designed to characterize the interactions of hypergolic liquid rocket propellants and to provide information pertinent to the development of a model to describe the transport and diffusion of airborne combustion products and unreacted vapors from an accident involving these propellants. This report is prepared in two volumes. Volume I addresses the reactions between nitrogen tetroxide and hydrazine, including the reaction products and the heat released. This information was used to determine the combustion time and the height of the resulting fireball before it cools and disperses with the air. Volume II discusses the chemical and physical interactions of the combustion products with air, and the dispersion of these products in the environment.
1 citations
TL;DR: In this paper, the authors present the principles of acoustic emission leak detection, describes the sensors and signal conditioning, discusses acoustic signal transmission and isolation techniques, as well as experimental data, and shows how these data can be applied to identify internally leaking parallel redundant components in all-welded feed systems.
Abstract: Acoustic emission techniques have been used for over a decade to locate leaks in petrochemical operations. This approach was refined for locating low-level leaks in spacecraft liquid rocket propellant and pressurant feed systems. This paper presents the principles of acoustic emission leak detection, describes the sensors and signal conditioning, discusses acoustic signal transmission and isolation techniques, as well as experimental data, and shows how these data can be applied to identify internally leaking parallel redundant components in all-welded feed systems.