Combustion of metallized propellants for ducted rockets

Mitsuno, M.; Kuwahara, Taishi; Kosaka, Katsuaki; Kubota, Naminosuke

doi:10.2514/6.1987-1724

Cited by 14 publications

(5 citation statements)

References 4 publications

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“…At the same time, the specific properties of boron make it difficult to realize the potential of boron-containing SPs [4][5][6][7][8][9].…”

Section: Introductionmentioning

confidence: 99%

“…a solid boron particle leads to the formation of a molten film B 2 O 3 on its surface (T melt ≈ 723 K), which prevents oxidation. According to estimates [4], the combustion efficiency of boron-containing propellants does not exceed 0.7. The primary products of combustion of boron-containing SPs in the gas-generator chamber contain components that are more thermally stable and more difficult to ignite than boron (boron carbide C 4 C, boron nitride BN, etc.)…”

Section: Introductionmentioning

confidence: 99%

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Modeling of Ignition and Combustion of Boron-Containing Solid Propellants

Архипов

Basalaev

Kuznetsov

et al. 2021

Combust Explos Shock Waves

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This paper presents the results of an experimental study of the ignition and slagging characteristics for combustion of boron-containing solid propellants with ammonium perchlorate as an oxidizer under conditions modeling the operation of the gas generator and afterburner of a rocket-ramjet engine. It is shown that the introduction of fluorine-containing additives into the propellant reduces the content and adhesion capacity of primary condensed combustion products (slags). The dependences of the ignition delay on the radiant heat flux density in the range 20-180 W/cm 2 are obtained for model solid propellants containing boron, carbon, boron carbide, and slag particles collected in the gas generator.

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“…At the same time, the specific properties of boron make it difficult to realize the potential of boron-containing SPs [4][5][6][7][8][9].…”

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Modeling of Ignition and Combustion of Boron-Containing Solid Propellants

Архипов

Basalaev

Kuznetsov

et al. 2021

Combust Explos Shock Waves

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“…[1][2][3][4][5] Combustion performance is a critical issue in the efficient operation of SPDRs 1) because it directly affects mission performance. In the past few decades, many studies focused on the combustion performance of SPDRs, accounting for propellant type, [6][7][8][9] gas injection device, 7,[10][11][12][13] inlet type 10,[14][15][16][17] and chamber configuration. [18][19][20][21][22] However, most of these studies are forced on SPDRs with four inlets or two inlets, combustion characteristics of SPDRs with chin inlets are not found in open literature.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation of a Solid Propellant Ducted Rocket with a Chin Type Inlet

Chen

Xia

Huang

et al. 2019

Trans. Japan Soc. Aero. S Sci.

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In this study we report an experimental research on the characteristics of combustion chamber in a solid propellant ducted rocket (SPDR) with a chin type inlet. Two kinds of propellants are tested, including boron-based solid propellant and hydrocarbon solid propellant. A new configuration of the SPDR with swirling flow is proposed. Effects on combustion characteristic of swirling flow, chamber length, propellant type and equivalence ratio are conducted. Results show that combustion efficiency based on temperature rise of the SPDR with swirling flow can reach 95%, which is 7% higher than the one without swirling flow. Furthermore, the swirler used in this study offers a significant effect on thermal protection. The combustion efficiency of hydrocarbon fuel-rich propellant is lower than that of boron-based fuel-rich propellant, and the SPDR using hydrocarbon propellant suffers from an ignition delay problem. When equivalence ratio decreases, combustion efficiency of the SPDR without swirling flow remains the same, whereas combustion efficiency of the SPDR with swirling flow increases first and then decreases.

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“…Polymeric fuel binder and metal particle can have a significant effect on the combustion characteristics of composite propellants. Recently, there has been a renewal of interest in the use of boron as a fuel, because of the high heat of boron oxidation (1)(2)(3)(4)(5). Fluorocarbon is also used as an energetic and a heat-resistant polymeric fuel binder.…”

Section: Introduction 21 Propellant Samplementioning

confidence: 99%

Combustion Behavior of Fluorocarbon/Boron/AP Propellant at high pressure

Oyumi¹,

Nagayama²

1995

Propellants Explo Pyrotec

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Thermal decomposition and the burning properties of fluorocarbon/boron/AP propellant granule have been investigated. The fluoro‐carbon binder (FBDR) was oxidized by the decomposition products of admixed ammonium perchlorate (AP) and its decomposition region was 150°C lowered in the slow thermolysis. The boron particles, however reacted with neither FBDR nor AP at 550°C. In the micro‐motor tests, the boron particles completely burnt at a pressure range of from 30 MPa to 80 MPa in a short period of time (one millisecond) even at a low characteristic exhaust velocity. Minimum free volume, however, was needed to complete the combustion reaction in the chamber case. The characteristic exhaust velocity significantly decreased at below the characteristic chamber length of 11 cm. The boronized propellant showed low temperature sensitivity between −30°C and 60°C.

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Combustion of metallized propellants for ducted rockets

Cited by 14 publications

References 4 publications

Modeling of Ignition and Combustion of Boron-Containing Solid Propellants

Modeling of Ignition and Combustion of Boron-Containing Solid Propellants

Experimental Investigation of a Solid Propellant Ducted Rocket with a Chin Type Inlet

Combustion Behavior of Fluorocarbon/Boron/AP Propellant at high pressure

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