The Phoenix Hybrid Sounding Rocket Program: A Progress Report

Geneviève, Bernard; Chowdhury, Seffat; Brooks, Michael J.; Pitot, Jean; Veale, Kirsty L.; Roberts, Lance W.

doi:10.2514/6.2011-6104

Cited by 6 publications

(5 citation statements)

References 3 publications

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“…7) Phoenix-2A preliminary design with propulsion trade studies. Figure 1 shows a CAD representation of Phoenix-1A 1 . This paper explains the methodology used to model various key design parameters of the Phoenix-2A vehicle, using HYROPS, for improved performance and the structural analysis of a large scale grain.…”

Section: Introductionmentioning

confidence: 99%

“…he Phoenix Hybrid Sounding Rocket Program commenced in 2010 with the design and development towards Phoenix-1A, a small scale hybrid sounding rocket capable of reaching 10 km in altitude 1 . The main objective of the program is to develop reusable large scale hybrid rockets for the African scientific community due to the lack of launch services in the country 2 .…”

Section: Introductionmentioning

confidence: 99%

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Performance Modeling of the Phoenix-2A Hybrid Sounding Rocket using the HYROPS Software

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Brooks

Pitot

et al. 2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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The University of KwaZulu-Natal's Phoenix Hybrid Sounding Rocket Program aims to develop a hybrid sounding rocket, called Phoenix-2A that is capable of reaching a 100 km apogee with a 5 kg payload. The rocket must be safe, reusable and designed for scientific research. The program has been under way since 2010 with the design and development of Phoenix-1A, a small scale hybrid rocket capable of reaching an altitude of 10 km. Nitrous oxide and Sasol 0907 paraffin wax are the selected propellants for Phoenix-2A. The design phase incorporates the use of a UKZN-developed motor performance and flight dynamics simulation tool, HYROPS (Hybrid Rocket Performance Simulator). The design methodology implemented for the preliminary design is discussed and illustrates the architecture of the HYROPS software. Parametric trade studies have been conducted to determine the sensitivity of varying key propulsion and aerodynamic design parameters. Propulsion parameters included are chamber pressure, O/F ratio, and design atmospheric pressure. These studies act as a platform for the development of large scale hybrid rockets. The structural integrity of large scale fuel grains is also being investigated. NomenclatureA t = nozzle throat area C F = thrust coefficient C * = characteristic velocity F D = design thrust mdot n = nozzle mass flow rate O/F = oxidizer to fuel ratio P atm = atmospheric pressure P c = chamber pressure P e = exit pressure ∆P inj = pressure drop across injector η = combustion efficiency

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Performance Modeling of the Phoenix-2A Hybrid Sounding Rocket using the HYROPS Software

Leverone

Brooks

Pitot

et al. 2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

View full text Add to dashboard Cite

show abstract

“…This goal forms part of a longer-term vision to produce sounding rockets for the South African scientific community. Since inception at the start of 2010, the Phoenix Program has seen the development of a laboratory-scale hybrid rocket motor and test facility, codes for the modeling of hybrid rocket motor performance 2 and hybrid sounding rocket flight dynamics 3 , and the design of the program"s first vehicle, the Phoenix-1A 4 (Fig. 1), which has been designed with the capacity to deliver a 1 kg payload to an altitude of 10 km.…”

Section: Introductionmentioning

confidence: 99%

The Phoenix Hybrid Sounding Rocket Program: A Progress Report 2012

Geneviève¹,

Chowdhury²,

Brooks³

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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The University of KwaZulu-Natal's Phoenix Program aims to develop a hybrid sounding rocket capable of reaching 100 km apogee by 2016. The first stage of the program is the development of the Phoenix-1A low altitude vehicle, capable of delivering a 1 kg payload to an altitude of 10 km. Following intensive structural design and computational analysis work, manufacture of the vehicle is nearing completion. To date, the flight oxidizer tank and motor have been developed, pressure tested, and integrated together by means of four high strength stainless steel struts. The aluminum stabilizing fins have been fabricated and the manufacture of composite airframe components is ongoing. A cold flow test of Phoenix-1A flight motor has been performed. Two hot-fire ignition failures are described and the possible causes discussed. The next immediate objectives of the program are to successfully hot-fire the flight motor by the end of August 2012, and to fly the vehicle by the end of 2012.

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“…HE University of KwaZulu-Natal's Hybrid Sounding Rocket Program was initiated in 2010, with the design and development of a lab scale paraffin wax\nitrous oxide motor, combustion and trajectory performance software (HYROPS) 2 and their first launch vehicle, the Phoenix-1A 3 . Further program development included the paper design of the Phoenix-2A vehicle 4 , which according to simulations, should be capable of reaching an altitude of 100 km and the design and construction of the Phoenix-1B low altitude demonstrator.…”

Section: Introductionmentioning

confidence: 99%

Structural Performance of Large Scale Paraffin Wax Based Fuel Grains

Veale¹,

Brooks²,

Pitot³

2015

51st AIAA/SAE/ASEE Joint Propulsion Conference

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Paraffin wax has been identified as a high regression rate, liquefying fuel that can be used with nitrous oxide and other oxidizers as the solid component of a hybrid rocket propellant combination. The low viscosity and low surface tension of certain liquefying fuels allows for the development of small surface wave formations, and droplet entrainment into the oxidizer stream during the combustion process. This is the main contributing factor to the increased regression rate when compared to commonly used hybrid fuels such as HTPB and HDPE 1 . Although significant work has been conducted in the field of combustion analysis of liquefying fuels, little investigation has been done on the structural performance of large scale grains. This paper investigates the structural performance of a pure paraffin wax fuel grain on the Phoenix-1A hybrid rocket and the proposed grain design of the larger Phoenix-2A vehicle. UKZN's in-house Hybrid Rocket Performance Simulator software, HYROPS, is used to facilitate loading and regression rate predictions. Flight data from the Phoenix-1A launch is also considered along with an analysis of unconsumed grain that remained after motor burnout.

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The Phoenix Hybrid Sounding Rocket Program: A Progress Report

Cited by 6 publications

References 3 publications

Performance Modeling of the Phoenix-2A Hybrid Sounding Rocket using the HYROPS Software

Performance Modeling of the Phoenix-2A Hybrid Sounding Rocket using the HYROPS Software

The Phoenix Hybrid Sounding Rocket Program: A Progress Report 2012

Structural Performance of Large Scale Paraffin Wax Based Fuel Grains

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