Optimal design of hybrid rocket motor powered vehicle for suborbital flight

Cai, Guobiao; Zhu, Hao; Rao, D. M. K. K. Venkateswara; Tian, Hui

doi:10.1016/j.ast.2011.12.014

Cited by 45 publications

(13 citation statements)

References 21 publications

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“…The structure of the HRM powered rocket consists of head (containing payloads), fins, HRM and the linking structures, 8 as shown in Fig. 1.…”

Section: Rocket Structure Designmentioning

confidence: 99%

“…Therefore, an approach to the uncertainty analysis and design optimization of HRM powered vehicles is proposed in this paper, based on our former work about the conceptual design of HRM powered rockets. 8,9 The main problem in UDO is the low efficiency of the uncertainty analysis when the system design model is complicated. The approximate model technology is one of the most popular methods to solve this problem.…”

Section: Introductionmentioning

confidence: 99%

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Uncertainty analysis and design optimization of hybrid rocket motor powered vehicle for suborbital flight

Zhu

Tian

Cai

et al. 2015

Chinese Journal of Aeronautics

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In this paper, we propose an uncertainty analysis and design optimization method and its applications on a hybrid rocket motor (HRM) powered vehicle. The multidisciplinary design model of the rocket system is established and the design uncertainties are quantified. The sensitivity analysis of the uncertainties shows that the uncertainty generated from the error of fuel regression rate model has the most significant effect on the system performances. Then the differences between deterministic design optimization (DDO) and uncertainty-based design optimization (UDO) are discussed. Two newly formed uncertainty analysis methods, including the Kriging-based Monte Carlo simulation (KMCS) and Kriging-based Taylor series approximation (KTSA), are carried out using a global approximation Kriging modeling method. Based on the system design model and the results of design uncertainty analysis, the design optimization of an HRM powered vehicle for suborbital flight is implemented using three design optimization methods: DDO, KMCS and KTSA. The comparisons indicate that the two UDO methods can enhance the design reliability and robustness. The researches and methods proposed in this paper can provide a better way for the general design of HRM powered vehicles.

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“…The structure of the HRM powered rocket consists of head (containing payloads), fins, HRM and the linking structures, 8 as shown in Fig. 1.…”

Section: Rocket Structure Designmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Uncertainty analysis and design optimization of hybrid rocket motor powered vehicle for suborbital flight

Zhu

Tian

Cai

et al. 2015

Chinese Journal of Aeronautics

Self Cite

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“…Many intensive studies have been conducted on key technologies for HRM [4][5][6][7][8] and its applications [9][10][11]. In an interesting demonstration test that was recently conducted in the United States, the ascent, hovering, and soft landing of a craft were accomplished using an HRM as the propulsion system.…”

Section: Introductionmentioning

confidence: 99%

Uncertainty analysis and probabilistic design optimization of hybrid rocket motors for manned lunar landing

Zhu

Tian

Cai

et al. 2015

Sci. China Technol. Sci.

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To obtain a conceptual design for a hybrid rocket motor (HRM) to be used as the Ascent Propulsion System in the Apollo lunar module, the deterministic design optimization (DDO) method is applied to the HRM design. Based on the results of an uncertainty analysis of HRMs, an uncertainty-based design optimization (UDO) method is also adopted to improve the design reliability. The HRM design process, which is a multidisciplinary system, is analyzed, and a mathematical model for the system design is established to compute the motor performance from the input parameters, including the input variables and model parameters. The input parameter uncertainties are quantified, and a sensitivity analysis of the model parameter uncertainties is conducted to identify the most important model parameter uncertainties for HRMs. The DDO and probabilistic UDO methods are applied to conceptual designs for an HRM to be used as a substitute for the liquid rocket motor (LRM) of the Ascent Propulsion System. The conceptual design results show that HRMs have several advantages as an alternative to the LRM of the Ascent Propulsion System, including nontoxic propellant combination, small motor volume, and comparable functions, such as restarting and throating. Comparisons of the DDO and UDO results indicate that the UDO method achieves more robust and reliable optimal designs than the DDO method. The probabilistic UDO method can be used to develop better conceptual designs for HRMs. hybrid rocket motor, deterministic design optimization, uncertainty-based design optimization, sensitivity analysis, manned lunar landing Citation: Zhu H, Tian H, Cai G B, et al. Uncertainty analysis and probabilistic design optimization of hybrid rocket motors for manned lunar landing. Sci

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“…A complex interrelationship between these three subsystems and their proper integration determine the performance of a particular SRM mission [2]. Effort to minimize the pressure and friction losses of internal and external flows may increase the range or payload capacity of SRM.…”

Section: Introductionmentioning

confidence: 99%

Optimization of Potassium Nitrate Based Solid Propellant Grains Formulation Using Response Surface Methodology

Ogunleye¹,

Hammed²,

Alagbe³

2015

Adv. Sci. Technol. Res. J.

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This study was designed to evaluate the effect of propellant formulation and geometry on the solid propellant grains internal ballistic performance using core, bates, rod and tubular and end-burn geometries. Response Surface Methodology (RSM) was used to analyze and optimize the effect of sucrose, potassium nitrate and carbon on the chamber pressure, temperature, thrust and specific impulse of the solid propellant grains through Central Composite Design (CCD) of the experiment. An increase in potassium nitrate increased the specific impulse while an increase in sucrose and carbon decreased specific impulse. The coefficient of determination (R 2 ) for models of chamber pressure, temperature, thrust and specific impulse in terms of composition and geometry were 0.9737, 0.9984, 0.9745 and 0.9589, respectively. The optimum specific impulse of 127.89 s, pressure (462201 Pa), temperature (1618.3 K) and thrust (834.83 N) were obtained using 0.584 kg of sucrose, 1.364 kg of potassium nitrate and 0.052 kg of carbon as well as bate geometry. There was no significant difference between the calculated and experimented ballistic properties at p < 0.05. The bate grain geometry is more efficient for minimizing the oscillatory pressure in the combustion chamber.

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Optimal design of hybrid rocket motor powered vehicle for suborbital flight

Cited by 45 publications

References 21 publications

Uncertainty analysis and design optimization of hybrid rocket motor powered vehicle for suborbital flight

Uncertainty analysis and design optimization of hybrid rocket motor powered vehicle for suborbital flight

Uncertainty analysis and probabilistic design optimization of hybrid rocket motors for manned lunar landing

Optimization of Potassium Nitrate Based Solid Propellant Grains Formulation Using Response Surface Methodology

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