Addressing emerging tactical missile propulsion challenges with the Solid Propellant Air-Turbo-Rocket

Thomas, Melanie; Bossard, John A.; Ostrander, Mark J.

doi:10.2514/6.2000-3309

Cited by 4 publications

(4 citation statements)

References 4 publications

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“…In Japan, the solid propellant ATR was test successfully with GAP which is low heating value propellant [3] . CFD research corporation focus on developing the turbo machinery [4] and designing throttling valve for proper propellants control [5][6] , solid propellant ATR demonstration engine has been developed [7] , ATR is constrained as the application of in long duration missile for undeveloped solid propellant. In this paper, the TSPR which is combination the solid propellant ATR and solid ramjet has been studied as new propulsion for tactical missile with complex ballistic trajectory.…”

Section: Introductionmentioning

confidence: 99%

Turbocharged Solid Propellant Ramjet for Tactical Missile

Yang

et al. 2012

AMM

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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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Section: Introductionmentioning

confidence: 99%

Turbocharged Solid Propellant Ramjet for Tactical Missile

Yang

et al. 2012

AMM

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“…A combustion experiment with a variable gas flow rate was designed, and the upper limit of the excess air coefficient was obtained under the condition of cold inflow. W ITH the development of air-breathing engine technology, such as the solid rocket ramjet [1,2], air-turbo rocket (ATR) [3,4], and solid-fuel scramjet [5,6], new requirements for solid propellants have been introduced. A solid-propellant air-turbo rocket (SP-ATR) is a type of air-breathing engine that uses an independent solid gas generator to drive the turbines and pressurize the intake air for combustion.…”

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confidence: 99%

“…They have a wide working range and perform well in self-accelerating and maneuvering. Figure 1 shows the structure of a typical SP-ATR [3]. The main components of ATRs generally include an air inlet, gas generator, compressor, turbine, secondary combustion chamber, and nozzle.…”

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confidence: 99%

Combustion Characteristics Experimental Study of Solid Hydrocarbon Propellant for Air-Turbo Rocket

Liu

Gao

et al. 2018

Journal of Propulsion and Power

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“…[1] Especially, under the regulation of turbomachinary, the working range was enlarged greatly, so that the engine's task type was expanded, for which the engine could be used for multi-task operation. [2,3,4] Therefore a series of studies on the engine were carried out.…”

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confidence: 99%

Influence on TSPR's flight envelope by turbocharger

Liu¹,

Jiang²,

Yang³

et al. 2017

Proceedings of the 2nd Annual International Conference on Electronics, Electrical Engineering and Information Science (EEEIS 20

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In this article, the influence on the flight envelope of turbocharged solid propellant ramjet (TSPR) by turbocharger was studied by TSPR's performance prediction program. By those studies, some conclusions were obtained as follows: (1) to increase the compressor's pressure ratio could only expand the flight envelope in low altitude and low Mach number area, while the key factor to limit the maximum flight altitude and flight Mach number was the temperature limit of compressor impeller material; (2) when the temperature limit of compressor impeller raised from 800K to 1000K, TSPR's maximum latitude and Mach number could be raised from 25.5km and Ma3.57 to 30.7km and Ma 4.1; (3) when the actual turbocharger was introduced, the controlling factors for the maximum latitude and the maximum Mach number would be changed with the raise of the temperature and pressure of the turbocharger's design point, when low pressure and temperature were chosen as the design point the compressor's operating range would be the key factor, and when the high ones were chosen, the temperature limit would be the key factor.

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Addressing emerging tactical missile propulsion challenges with the Solid Propellant Air-Turbo-Rocket

Cited by 4 publications

References 4 publications

Turbocharged Solid Propellant Ramjet for Tactical Missile

Turbocharged Solid Propellant Ramjet for Tactical Missile

Combustion Characteristics Experimental Study of Solid Hydrocarbon Propellant for Air-Turbo Rocket

Influence on TSPR's flight envelope by turbocharger

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