Study of High Thrust Ratio Approaches for Single-Chamber Dual-Thrust Solid Rocket Motors

Hu, Keke; Zhang, Y.; Cai, Xiaobing; Ma, Z.; Zhang, P.

doi:10.2514/6.1994-3333

Cited by 5 publications

(8 citation statements)

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“…The performance parameters achieved by the GASA strategy are well within the range. All these values were achieved by adhering to and obeying the bounds of design variables, propellant properties, and nozzle parameters given in Table 1 and Table 2, and constraints imposed by Equation (10).…”

Section: Resultsmentioning

confidence: 99%

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Design and Optimization of 3D Wagon Wheel Grain for Dual Thrust Solid Rocket Motors

Wang

2012

Propellants Explo Pyrotec

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The combination of various design and performance parameters in dual thrust solid rocket motors coupled with constraints may lead to a multitude of configurations. It is difficult to initially determine a suitable design without optimization. In this article, a methodology for the design of a 3D wagon wheel that provides two levels of thrust, namely boost phase thrust and sustain phase thrust, is investigated. The proposed framework consists of an integrated approach of grain design, computer aided design and hybrid optimization. A hybrid genetic algorithm and simulated annealing are used for optimization due to their robustness and capability to find global optimal solution. Several benchmark test functions are used to validate the performance of the optimization algorithm and solution. Maximization of the average thrust ratio and the total impulse are the objective functions under the given constraints.

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Section: Resultsmentioning

confidence: 99%

“…Literature on dual thrust design and optimization, however, is scarce. Hu et al presented a design study on high thrust ratio approach using a single chamber dual-thrust solid rocket motor [10]. Dunn described a dual thrust approach using a dual propellant [11].…”

Section: Introductionmentioning

confidence: 99%

Design and Optimization of 3D Wagon Wheel Grain for Dual Thrust Solid Rocket Motors

Wang

2012

Propellants Explo Pyrotec

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“…Accordingly, a high thrust ratio can be achieved by optimizing the different parameters, such as motor performance, propellant combustion characteristics, grain design and structure of chamber and nozzle, etc. [12]. To realize dual thrust, the following equations can be derived from the internal ballistics of motors [13]:…”

Section: Approaches For Achieving a High Thrust Ratiomentioning

confidence: 99%

“…Also, the major disadvantage of this technique is that the presence of an additional nozzle increases the inert weight of the motor and thus decreases the overall performance [14]. Efforts were made to counter the inert weight by allowing the first stage to be jettisoned, however, this causes a change in the external shape of the missile resulting in aerodynamic instability and control problems [12].…”

Section: Figure 1 Dual Chamber or Partitioned Motormentioning

confidence: 99%

Experimental Approaches to Develop a High Thrust Ratio in a Single Chamber Dual Thrust Motor Using a Composite Propellant Formulation Based on HTPB/AP/Al

Kurva

Ukey

Modgi

et al. 2017

Cent. Eur. J. Energ. Mater.

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Abstract:A high thrust ratio in a single chamber dual thrust motor is required to reach a peak velocity very quickly. To achieve a high thrust ratio in a single chamber dual thrust motor, a composite propellant grain, which acts both as booster and sustainer, based on HTPB/AP/Al (84% solid loading) with low aluminum content and having a burning rate of 25±0.5 mm/s at 7 MPa, was successfully developed. This was studied for viscosity build-up, mechanical and ballistic properties, followed by casting and curing as a single type propellant grain. The high burning surface area was created by making grooves of 3 mm width and 60 mm depth over the surface of the nozzle side of the grain while casting and a prototype, thus obtained, was static tested. The data revealed that a grain with one groove demonstrated a thrust ratio of 8, while two grooves, realized a thrust ratio of 30. The experimental thrust ratio values achieved are also in agreement with the predicted values of the thrust ratio of the same composition.

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“…Literature on dual grain geometry optimisation and design however is scarce. Hu et al (1994) presented a design study on high thrust ratio approach using single chamber dual-thrust solid rocket motor. Dunn and Coats (1997) described dual-thrust approach using dual propellant.…”

Section: Introductionmentioning

confidence: 99%

Uncertainty-based computational robust design optimisation of dual-thrust propulsion system

Wang

2011

Journal of Engineering Design

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2012) Uncertainty-based computational robust design optimisation of dual-thrust propulsion system, Journal of Engineering Design, 23:8, 618-634, This paper proposes a robust design optimisation methodology for performance evaluation of high-fidelity propulsion systems under both aleatory and epistemic uncertainties. In this paper, uncertainty-based robust design methodology is applied using first-order orthogonal design to estimate worst case of the uncertainties. The effectiveness and computational efficiency of proposed formulation is obtained by decoupling computation of both types of uncertainties in the optimisation process loop. The system robustness is measured by directly minimising the variance of target mean and standard deviation and adhering to performance constraints. A parametric sensitivity analysis of performance parameters due to input parameters variations is also performed to identify the most significant design variables. A hybrid genetic algorithm and simulated annealing approach are used as an optimiser. By using the proposed method, the objective function to maximise the booster phase to sustain phase thrust ratio and total impulse could be achieved while adhering to the motor performance constraints to provide an insensitive solution.

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Study of High Thrust Ratio Approaches for Single-Chamber Dual-Thrust Solid Rocket Motors

Cited by 5 publications

References 0 publications

Design and Optimization of 3D Wagon Wheel Grain for Dual Thrust Solid Rocket Motors

Design and Optimization of 3D Wagon Wheel Grain for Dual Thrust Solid Rocket Motors

Experimental Approaches to Develop a High Thrust Ratio in a Single Chamber Dual Thrust Motor Using a Composite Propellant Formulation Based on HTPB/AP/Al

Uncertainty-based computational robust design optimisation of dual-thrust propulsion system

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