Optimization of the propulsion for multistage solid rocket motor launchers

Calabro, Max; Dufour, A.; Macaire, Alexis

doi:10.1016/s0094-5765(01)00164-3

Cited by 13 publications

(12 citation statements)

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“…Air-breathing engine, also known as the duct engine, is the most commonly used engine type for aviation within stratosphere. The principle of duct engine is to entrain and compress air flow, using the energy from igniting the propellant to heat and further accelerate the flow [1]. High speed mass has been exhausted and a reaction force is applied to accelerate the aircraft.…”

Section: Principles and Challengesmentioning

confidence: 99%

“…The most commonly used duct engine is the turbojet engine which plays a significant role in modern day's commercial airlines. However, ramjet engine will be the focusing topic in this subsection because of its decent thrust-to-weight ratio which is 7:1 with Mach number 3 at around 9,144 meters (30,000 feet) above sea level [1]. The thrust-to weight ratio is an important dimensionless group when this term can be used to determine the payload of a rocket vehicle.…”

Section: Principles and Challengesmentioning

confidence: 99%

“…Another limitation of ramjet is its oxidizer choice, all ABEs use the air as oxidizer, many designs even consider the bypass air flow as the main source of thrust and cooling system. Therefore, an aircraft with ABE has a theoretical altitude limitation of 45,000 meters (147,638 feet) above sea level when operating at Mach 12 [1], which is technically feasible, but with no existing application nowadays. The most inconvenient feature of ramjet is that it requires certain initial speed to operate.…”

Section: Principles and Challengesmentioning

confidence: 99%

“…Human activities are severely limited by the earth resources, the developing over population and environmental problems are pushing the limits of both mankind and the earth [1]. October 4, 1957, the Soviet Union launched the first uman activities are severely limited by the earth resources, the developing over population and environmental satellite to the earth orbit.…”

Section: Introductionmentioning

confidence: 99%

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Principles of Multistage Rocket Vehicle and Concepts of Propulsion Methods for Rocket Applications

Liang¹

2022

HSET

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The variety of propulsion methods will reach their peak efficiencies under certain conditions. This paper will focus on the propulsion methods and different propellant choices for certain usage when designing a vehicle or a stage of a rocket with some altitude limitations, their working principles, applications and challenges. The advantages of multistage design for rocket vehicles and the prospects of advanced engine technology using electricity or solar radiation as its main power source will also be discussed. The cost, payload and other attributes such as the thrust-to-weight ratio of every propulsion concept are the main factors for determining the general performance. MRV is the ideal design for rocket vehicles that are launched from the surface of a planet consider the massive amount of energy it requires to get into the orbit or escape the gravity, but the propulsion system can be various depends on the applications under certain conditions of launching and space travel.

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Section: Principles and Challengesmentioning

confidence: 99%

Section: Principles and Challengesmentioning

confidence: 99%

Section: Principles and Challengesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Principles of Multistage Rocket Vehicle and Concepts of Propulsion Methods for Rocket Applications

Liang¹

2022

HSET

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“…Garfi eld and Allen (1995) used integer optimization applied to the configuration of LVs, Johnson (2002) conducted a screening process of booster for hypersonic vehicles, Calabro et al (2002) presented the optimization of the propulsion for multistage LVs, and Bhatnagar et al (2012) solved the mass distribution problem under restrictive condition.…”

Section: Design Constraintsmentioning

confidence: 99%

Small Solid Propellant Launch Vehicle Mixed Design Optimization Approach

Villanueva

He²,

Xu³

2014

J.Aerosp. Technol. Manag.

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For a small country with limited research budget and lack of advanced space technology, it is imperative to find new approaches for the development of low-cost launch vehicles (LV), which is, among all possibilities, an interesting option for rapid access to space, focused on integration of acquired components complemented with indigenously developed subsystems. This approach requires the cooperation of developed countries with huge experience and knowledge in LV development and operations. The main objective is to develop a small three stage solid propellant LV capable of delivering a payload of 100 kg to a circular low earth orbit of 600 km altitude, with the first and second stage solid rocket motors (SRM) hypothetically acquired from different countries and the third one designed and produced domestically in accordance with the production and technological capability. This approach provides main advantages such as: reduction in total time to access the space and to master the basic knowledge of launch operations. For this purpose, an integer continuous genetic algorithm global optimization method was selected and implemented, the SRM characteristics of the first and second stage were considered as integer variables, whereas the design variables of the third stage SRM and the trajectory variable were considered as continuous. A multi discipline feasible (MDF) framework was implemented along with the propulsion, aerodynamic, mass and trajectory models. Despite their particular characteristics and constraints, the results show highly acceptable values, and the approach proved to be reliable for conceptual design level.

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Effect of Variable Selection on Multidisciplinary Design Optimization: a Flight Vehicle Example

Roshanian¹,

Keshavarz²

2007

Chinese Journal of Aeronautics

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Optimization of the propulsion for multistage solid rocket motor launchers

Cited by 13 publications

References 0 publications

Principles of Multistage Rocket Vehicle and Concepts of Propulsion Methods for Rocket Applications

Principles of Multistage Rocket Vehicle and Concepts of Propulsion Methods for Rocket Applications

Small Solid Propellant Launch Vehicle Mixed Design Optimization Approach

Effect of Variable Selection on Multidisciplinary Design Optimization: a Flight Vehicle Example

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