Review on Typical Ingredients for Ammonium Perchlorate Based Solid Propellant

Aziz, Azrina Abd; Mamat, Rizalman; Ali, Wan Khairuddin Wan; Perang, Mohd Rozi Mohd

doi:10.4028/www.scientific.net/amm.773-774.470

Cited by 25 publications

(20 citation statements)

References 30 publications

(31 reference statements)

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“…In general, KNSu consists of a mixture of 65 wt% of potassium nitrate and 35 wt% of sucrose.Additives in the basic formulation of KNSu are commonly used to increase the specific thrust of this propellant. Additives such as metal oxides and metals are widely used (Chaturvedi and Dave, 2015;Aziz et al, 2015). The oxides used are iron oxide and also magnesium oxide.…”

Section: Introductionmentioning

confidence: 99%

“…The oxides used are iron oxide and also magnesium oxide. Several metallic additives can be used, such as, beryllium, magnesium, zirconium and aluminum (Aziz et al, 2015;Zhou et al, 2019). When compared to other metallic additives aluminum is vastly used due to the high energy released during its combustion, low cost and low toxicity (Aziz et al, 2015).…”

Section: Introductionmentioning

confidence: 99%

“…Several metallic additives can be used, such as, beryllium, magnesium, zirconium and aluminum (Aziz et al, 2015;Zhou et al, 2019). When compared to other metallic additives aluminum is vastly used due to the high energy released during its combustion, low cost and low toxicity (Aziz et al, 2015). However, some disadvantages with the use of this additive are also reported in the literature, such as the formation of particle agglomerates (Xiao, et al, 2019) and the formation of an oxide layer on the metal surface (Griego, Yimaz and Atmanli, 2019), both factors reduce additive performance when incorporated into rocket propellants.Thus, the present work aims to evaluate the effect of the incorporation of different loadings of aluminum wastes on the performance of KNSu.…”

Section: Introductionmentioning

confidence: 99%

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Evaluation of use waste aluminum on the burning of solid rocket propellant

Baldissera¹,

Khün²,

Telöken³

et al. 2019

IJASTR

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Solid propellants based on potassium nitrate (KNO 3) and sucrose are widely used in rocketry, because they are inexpensive and easily obtainable compounds and also generate high specific thrust. In this study, the performance of propellants based on a mixture of 65 wt% KNO 3 and 35 wt% sucrose, named KNSu, was evaluated.Aluminum waste particles were loading at 2.5 wt%, 5 wt% and 7.5 wt%. Aluminum was used as a powder with an average particle size of 35 μm. Rocket engines were developed and the thrust versus time curves obtained for the samples studied. The results showed that the utilization of 5 wt% caused a 30% increase in both the specific impulse and the average gas ejection velocity when compared to KNSu. The incorporation of 2.5 wt% and 7.5 wt% caused a reduction in the specific impulse and other properties evaluated when compared to KNSu. Based on the results obtained, it is possible to state that the insertion of aluminum waste from the metalworking industry may contribute to the increase of the performance of rockets that use KNSu as a solid propellant.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Evaluation of use waste aluminum on the burning of solid rocket propellant

Baldissera¹,

Khün²,

Telöken³

et al. 2019

IJASTR

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“…Solid propellants are mainly used in gun and rocket propulsion applications [1,2]. The choice of a propellant is the main decision of any solid rocket motor design.…”

Section: Introductionmentioning

confidence: 99%

Solid Propellants for Rockets: A Methodology to Obtain High Purity Kno3 From an Inexpensive Source

.¹

2018

IJRET

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Solid propellants are mainly used in rocket propulsion applications. The performance of a rocket is directly affected by the design of the solid propellant used. The presence of impurities in the propellant formulation can reduce the average thrust, specific impulse and characteristic velocity of a rocket. Oxidizers are the main compounds in propellants formulation, which produce the high energy on combustion. One the most commonly used oxidizers in amateur rocketry is potassium nitrate. KNO 3 is normally used because of its good characteristics that include compatibility with others ingredients and availability at low cost in fertilizer formulation. The main objective of this work is to propose a methodology to obtain higher purity potassium nitrate from a fertilizer, an available and inexpensive source that can be used as oxidizer in a solid rocket propellant formulation. The KNO 3 crystals were obtained by recrystallization process using a commercial fertilizer. The properties of purified fertilizer were compared with the properties of KNO 3 analytical. The fertilizer, purified and analytical grade KNO 3 samples were evaluated by means of morphology, pH of saturated solution, Fourier transform infrared (FTIR) spectroscopy, and differential scanning calorimetry (DSC). The results demonstrated that recrystallization process effectively remove impurities from the fertilizer. The purified KNO 3 crystals were optically transparent with a planar shape, similar to higher purity KNO 3. The FTIR and DSC results showed that some impurities, such as, sulfur and alkaline compounds were removed after recrystallization and the purified KNO 3 presented a similar behavior than higher purity KNO 3. The recrystallization process used in this work can successfully used to obtain KNO 3 crystals with high purity that can be used as oxidizer in solid propellants for rockets.

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“…In our experiment, the size of AP particles range from 63 -125 µm. This was obtained using the electromagnetic sieve shaker [7] [8] [9].…”

Section: Experimental Analysismentioning

confidence: 99%

Studies on the Internal Ballistics of Composite Solid Rocket Propellants Incorporating Nano-Structured Catalysts

Mukesh¹,

Sivasubramaniyam²,

Elangovan³

et al. 2017

AAST

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This paper deals with the analysis of burn rate using various catalysts of Iron Oxide and determining which gives the higher burn rate with low pressure variation. The Ammonium Perchlorate (AP) was obtained and ground into fine powder with the particle size ranging from 63 to 125 µm. The propellant strands were prepared with proportions by mixing AP with the binder (Hydroxyl Terminated Polybutadiene), the catalyst (Iron Oxide), curing agent (Isophorone diisocyanate) and the plasticizer (Dioctyladipate). The prepared propellant mixture was cured at around 63 deg C to get various propellant strands. The first strand was prepared with the absence of a catalyst to set an initial base of comparison with other Iron Oxide catalysts, namely, Flower Shaped, Micro and Nano, based on the size of the particles. The combustion process was carried out in a strand burner, which was in turn connected to a data acquisition system. The obtained output was analysed in the form of graphs. The burn rate was achieved by calculating the slope of the graph i.e. by calculating the difference between the highest and the lowest peak of the graph and dividing the total time by the answer. The experiment was repeated with the different catalyst types, as mentioned above, at different pressures. It was observed that the Nano shaped Iron Oxide exhibits better burning characteristics when compared to the rest with the pressure index of 0.792. In this paper, the various experiments carried out along with their procedures are explained in detail. The results obtained and the techniques used are also elaborately described in this paper.

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Review on Typical Ingredients for Ammonium Perchlorate Based Solid Propellant

Cited by 25 publications

References 30 publications

Evaluation of use waste aluminum on the burning of solid rocket propellant

Evaluation of use waste aluminum on the burning of solid rocket propellant

Solid Propellants for Rockets: A Methodology to Obtain High Purity Kno3 From an Inexpensive Source

Studies on the Internal Ballistics of Composite Solid Rocket Propellants Incorporating Nano-Structured Catalysts

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