Development and Flight Demonstration of 5 kN Thrust Class CAMUI Type Hybrid Rocket

Nagata, Harunori; Wakita, Masashi; Totani, Tsuyoshi; Uematsu, Tsutomu

doi:10.2322/tastj.12.ta_1

Cited by 9 publications

(9 citation statements)

References 1 publication

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“…This is true for the hybrid rockets reported by Kobald et al, Gamal et al, and Zilliac et al in [11,14,16]. In a 5 kN thrust-class sounding rocket launch reported by Nagata et al, the former strategy was employed with great success using a high-density polyethylene (HDPE) fuel of the Cascaded Multistage Impinging-jet (CAMUI) design and liquid oxygen as the oxidizer [17]. With a characteristic exhaust velocity, c * , efficiency, η * , of 99% and a sustained acceleration during launch of 4 G to 5 G, the major concern of this development project shifted to nozzle thermochemical erosion.…”

Section: Introductionmentioning

confidence: 99%

Comprehensive Data Reduction for N2O/HDPE Hybrid Rocket Motor Performance Evaluation

et al. 2019

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Static firing tests of a hybrid rocket motor using liquid nitrous oxide (N2O) as the oxidizer and high-density polyethylene (HPDE) as the fuel are analyzed using a novel approach to data reduction that allows histories for fuel mass consumption, nozzle throat erosion, characteristic exhaust velocity (c*) efficiency, and nozzle throat wall temperature to be determined experimentally. This is done by firing a motor under the same conditions six times, varying only the burn time. Results show that fuel mass consumption was nearly perfectly repeatable, whereas the magnitude and timing of nozzle throat erosion was not. Correlations of the fuel regression rate result in oxidizer port mass flux exponents of 0.62 and 0.76. There is a transient time in the c* efficiency histories of around 2.5 s, after which c* efficiency remains relatively constant, even in the case of excessive nozzle throat erosion. Although nozzle erosion was not repeatable, the erosion onset factors were similar between tests, and greater than values in previous research in which oxygen was used as the oxidizer. Lastly, nozzle erosion rates exceed 0.15 mm/s for chamber pressures of 4 to 5 MPa.

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Section: Introductionmentioning

confidence: 99%

Comprehensive Data Reduction for N2O/HDPE Hybrid Rocket Motor Performance Evaluation

et al. 2019

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“…By Yuji SAITO, 1) Tsutomu UEMATSU, 2) Hikaru ISOCHI, 2) Masashi WAKITA, 1) Tsuyoshi TOTANI 1) and Harunori NAGATA 1) 1) Hokkaido University, Sapporo, Japan 2) Uematsu Electronic Corporation, Hokkaido, Japan (Received July 31st, 2015)…”

Section: Estimation Of Hybrid Rocket Nozzle Throat Erosion Historymentioning

confidence: 99%

“…On the other hand, ξ is necessary to calculate the temporal nozzle throat area by Eq. (1). A key of the present study is to solve the specific heat ratio and the nozzle throat area simultaneously.…”

Section: Introductionmentioning

confidence: 99%

“…We have been developing CAMUI-type hybrid rocket based on this motivation. 1) Nozzle throat erosion problem occurs in developing a 15 kN-thrust class motor. Figure 1 shows histories of chamber pressure and thrust in a static firing test of the motor.…”

Section: Introductionmentioning

confidence: 99%

“…A nichrome wire ignites an igniter fuel by electrical heating. The motor is a CAMUI-type 1) and high density polyethylene was used as a solid fuel. A video camera monitors the exit of the exhaust nozzle.…”

Section: Introductionmentioning

confidence: 99%

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Estimation of Hybrid Rocket Nozzle Throat Erosion History

Saito

Uematsu²,

Isochi³

et al. 2016

AEROSPACE TECHNOLOGY JAPAN

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A nozzle throat erosion problem occurs in developing a 15 kN-thrust class motor. To obtain a history of the nozzle throat area in a hybrid rocket static firing test, a new method is developed. Although the specific heat ratio of the combustion gas, which depends on the oxidizer to fuel ratio ξ, is necessary to calculate a nozzle throat area, it is difficult to obtain temporal ξ in hybrid rockets. A reconstruction technique, which estimates temporal ξ, needs chamber pressure, oxidizer flow rate, and nozzle throat area as input data. These two equations are solved simultaneously to acquire two convergence calculations for nozzle throat area and ξ. The new method was applied to a static firing test. The results show a typical erosion history, showing the validity of this method.

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Evaluation of Regression Rate Enhancing Concepts and Techniques for Hybrid Rocket Engines

Glaser

Hijlkema

Anthoine

2022

Aerotec. Missili Spaz.

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The low regression rate of Hybrid Rocket Engines (HREs) is one prominent characteristic that is addressed in most abstracts concerning hybrid propulsion. Over the years, researchers developed and investigated numerous ways to tackle the low regression rate problem of HREs. This article is a collection and assessment of these diverse methods and designs. It allows for a quick overview of the different mechanisms that are being employed and can serve both as information and inspiration. The enhancement ideas are grouped together as (a) adjustments to the solid fuel chemical properties, (b) advanced injection methods and concepts and (c) improving the combustion chamber design. These different techniques are discussed and their individual impact on the regression rate is assessed both qualitatively and quantitatively. All methods that are presented come with a different set of advantages and disadvantages, making the regression rate enhancement a trade-off problem. In our view, the most promising designs and methods are those that only call for minor adjustments to the HRE design, as they can be also added to already existing engines. Above all, it is to be said that regression rate enhancing techniques that change the unique features of HREs (namely safety, simplicity and low cost) are to be employed with caution. Only if the achievable regression rate increase is justifying the implications for the HRE in the envisioned use-case, these concepts represent promising alternatives to the status quo.

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Development and Flight Demonstration of 5 kN Thrust Class CAMUI Type Hybrid Rocket

Cited by 9 publications

References 1 publication

Comprehensive Data Reduction for N2O/HDPE Hybrid Rocket Motor Performance Evaluation

Comprehensive Data Reduction for N2O/HDPE Hybrid Rocket Motor Performance Evaluation

Estimation of Hybrid Rocket Nozzle Throat Erosion History

Evaluation of Regression Rate Enhancing Concepts and Techniques for Hybrid Rocket Engines

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