Modeling of dispersion and ignition processes of finely dispersed particles of aluminum using a solid propellant gas generator

Turbocharged solid propellant ramjet (TSPR) is the combination of solid propellant gas generator air turbo ramjet (ATR)with solid ramjet, is cycle of augmented ATR, the parametric performance calculation were carried out for TSPR, The effects of independent design parameters including parameters of compressor and turbine and propellants were studied and the preferred compressor, turbine and propellants were obtained for TSPR; The operation envelop of TSPR and ATR were obtain under the preferred component limitation, the results shows that TSPR offers wide speed-altitude operation envelope, high specific thrust, high specific impulse, it is combining the advantages of the ATR and solid ramjet, and suitable for tactical missiles application meets potential requirements for boosting and cruising.

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Design of a Solid Propellant Air Turbo Rocket for a Tactical Air-Launched Missile

Volume 1: Turbo Expo 2007 ◽

10.1115/gt2007-27826 ◽

2007 ◽

Cited By ~ 1

Author(s):

Fredrik Haglind ◽

Henrik Edefur ◽

Stefan Olsson

Keyword(s):

Solid Propellant ◽

Combined Cycle ◽

Rocket Motor ◽

Solid Rocket Motor ◽

Gas Generator ◽

Number Range ◽

Solid Propellant Rocket ◽

Solid Rocket ◽

Novel Concept ◽

Propellant Rocket

Traditionally, air-launched missiles are powered by a turbojet engine, rocket motor or a ramjet engine. A novel concept that may offer advantages over these concepts is the Air Turbo Rocket (ATR), which is a combined cycle engine, featuring a cycle where the turbine is isolated from the core engine flow entirely and powered by a separate gas generator. This paper is aimed at assessing the suitability of the solid propellant ATR as power source for a tactical air-launched missile. The ATR cycle is designed to achieve optimum performance, and a suitable solid propellant is selected. In addition, a turbojet and a solid rocket motor are designed for the same requirements, and the performances of these three engine concepts are compared. The ATR offers high thrust to weight and thrust to frontal area weight ratios, throttleability, and a wide speed-altitude operating envelope. The calculations suggest that, provided that the afterburning cooling issues can be solved, it would be reasonable to design the ATR such that a stoichiometric fuel/air mixture is obtained in the afterburner. For the Mach number range evaluated here, the ATR may offer advantages over the turbojet and the solid propellant rocket motor.

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RESEARCH OF THE TEMPERATURE CONDITION OF THE GAS GENERATOR OF SOLID PROPELLANT AT THE STAND TEST BY THE METHOD OF THERMAL IMAGING

Perm National Research Polytechnic University Aerospace Engineering Bulletin ◽

10.15593/2224-9982/2020.60.03 ◽

2020 ◽

pp. 26-33

Author(s):

Roman Mormul ◽

◽

Sergey Merzlyakov ◽

Keyword(s):

Temperature Field ◽

Experimental Design ◽

Thermal Imaging ◽

Solid Propellant ◽

Thermal State ◽

Experimental Studies ◽

Operating Characteristics ◽

Gas Generator ◽

Rocket Motors ◽

Emergency Rescue

In this article, the authors described in detail the methodology for conducting fire bench tests for the reusable experimental design of a solid propellant (SP) gas generator, specially designed to study the complex laws of heat and mass transfer under conditions of unsteady combustion of SP during operation of the installation and in the after-treatment mode. The developed technique allows us to study the nonlinear dynamics of temperature field changes, fuel and generator gas consumption, as well as its composition. The paper presents the chronology of the research, describes the used measuring equipment. Based on the carried out thermodynamic analysis of working processes in the combustion chamber of the gas generator under study, an algorithm for the optimal determination of its operating characteristics is proposed. The methodology of experimental studies of the thermal state of the design of the TT gas generator is universal and can be successfully used in working out other gas generating solid fuels with various energy characteristics during the optimal design of special technical systems such as solid propellant rocket motors (the approbation of the methodology is given on the example of an experimental design with a rotating nozzle), emergency rescue systems and aircraft engines. The results of studies of the thermal state of the elements of the TT gas generator by thermal imaging are well verified with the readings of temperature field sensors.

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