Multistage Liquid Rocket Weight Estimation and Optimization for Early Design Stages

Shu, Jung-Il; Lee, Jae Woo; Kim, Sangho; Lee, Jae‐Lyun; Wang, Yi

doi:10.1061/(asce)as.1943-5525.0001181

Cited by 4 publications

(4 citation statements)

References 12 publications

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“…The theoretical altitude limit of a ramjet engine with Mach number 5 is 30,000 meters (98,425 feet). With low air pressure at high altitude, the total pressure on an aircraft can be expressed by the follow equation [3]:…”

Section: Principles and Challengesmentioning

confidence: 99%

“…Although these technologies were invented due to the tensions from the cold war, they still play a significant role in the modern space travel. The history of multistage rocket can be traced back to the beginning of human's astronautic travel, the multistage design is still considered as the most practical approach for rocket vehicles [3]. This paper will explain the principles and limitations of various propulsion methods, and how to apply each methods and technologies in different stages of a rocket to achieve a higher speed, better performance or lower cost.…”

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: Introductionmentioning

confidence: 99%

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

Liang¹

2022

HSET

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“…To pursue better GNC performance of advanced flying vehicles, the improvement of current design approaches is investigated [2]. Traditionally, once the main-body design optimization, where the objective is restricted to flight performance [3−6], is finalized, the GNC system is then designed and optimized around a frozen missile configuration [7−10].…”

Section: Introductionmentioning

confidence: 99%

“…Traditionally, once the main-body design optimization, where the objective is restricted to flight performance [3−6], is finalized, the GNC system is then designed and optimized around a frozen missile configuration [7−10]. Due to the strong subsystem interaction, the application of the traditional approach to the design of advanced flying vehicles, including MMs, incurs not only subsequent and expensive redesign efforts [2] but also a suboptimal configuration with the limited potentiality of the improvement of GNC performance [11].…”

Section: Introductionmentioning

confidence: 99%

Design Methodology of a Mini-Missile Considering Flight Performance and Guidance Precision

Zhang,

Gong,

et al. 2024

J. of Syst. Eng. Electron.

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The design of mini-missiles (MMs) presents several novel challenges. The stringent mission requirement to reach a target with a certain precision imposes a high guidance precision. The miniaturization of the size of MMs makes the design of the guidance, navigation, and control (GNC) have a larger-thanbefore impact on the main-body design (shape, motor, and layout design) and its design objective, i.e., flight performance. Pursuing a trade-off between flight performance and guidance precision, all the relevant interactions have to be accounted for in the design of the main body and the GNC system. Herein, a multi-objective and multidisciplinary design optimization (MDO) is proposed. Disciplines pertinent to motor, aerodynamics, layout, trajectory, flight dynamics, control, and guidance are included in the proposed MDO framework. The optimization problem seeks to maximize the range and minimize the guidance error. The problem is solved by using the nondominated sorting genetic algorithm II. An optimum design that balances a longer range with a smaller guidance error is obtained. Finally, lessons learned about the design of the MM and insights into the trade-off between flight performance and guidance precision are given by comparing the optimum design to a design provided by the traditional approach.

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Multistage low-earth-orbit solid rocket conceptual design based on MERS

Piedra

Flores-Espinosa

2022

CEAS Space J

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Multistage Liquid Rocket Weight Estimation and Optimization for Early Design Stages

Cited by 4 publications

References 12 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

Design Methodology of a Mini-Missile Considering Flight Performance and Guidance Precision

Multistage low-earth-orbit solid rocket conceptual design based on MERS

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