Launch Vehicle Design Features for Minimum Cost

Portz, Ron

doi:10.2514/6.2004-3562

Cited by 12 publications

(8 citation statements)

References 4 publications

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“…Using this GA and the objective function, in 2003 and 2006, Burkhalter, Jenkins, and Hartfield took the design optimization of missile systems further [3][4][5]. Significant research has been performed in rocket-based vehicle design optimization using various evolutionary techniques [6][7][8][9][10][11][12][13][14][15][16]. Cost has also been considered in some studies [17][18][19] [20].…”

Section: Recent Launch Vehicle Optimization Workmentioning

confidence: 99%

Multidisciplinary design optimization of an expendable launch vehicle

Hosseini

Toloie

Nosratollahi

et al. 2011

Proceedings of 5th International Conference on Recent Advances in Space Technologies - RAST2011

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This paper describes an effort to optimize the design of an expendable launch vehicle (ELV) to low-Earth orbit, consisting of multiple stages with the goal of minimizing total vehicle weight and ultimately vehicle cost. The disciplines of weight & sizing, propulsion characteristics, aerodynamics and flight dynamics have been integrated to produce a system model of the entire vehicle. One multilevel multidisciplinary optimization techniques -Collaborative -is applied to the design of a launch vehicle. The results inclusive designed launch vehicle data has been validated by existing launch vehicle data. Keywords-Launch vehicle (LV), System design, Optimization, MDO, Design framework. I. NOMENCLATURE R = Earth radius E ω = Earth rotational velocity φ = Launch point latitude Hp = Orbit perigee altitude Ha = Orbit apogee altitude i = Orbit inclination ei μ = proportion of empty mass to total mass for (i)th stage ei M = empty mass for (i)th stage i M 0 = total mass for (i)th stage i n = load factor for (i)th stage MDO = multidisciplinary design optimization a, b, c = coefficient of mass & energy PL μ = proportion of payload mass to total mass CD = coefficient of drag D L = proportion of length to diameter N = number of stages ELV = Expendable Launch Vehicle LV = Launch Vehicle FPI = Fixed Point Iteration BLISS = Bi-level integrated system synthesis CO = Collaborative Optimization CAs = contributing analyses

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Section: Recent Launch Vehicle Optimization Workmentioning

confidence: 99%

Multidisciplinary design optimization of an expendable launch vehicle

Hosseini

Toloie

Nosratollahi

et al. 2011

Proceedings of 5th International Conference on Recent Advances in Space Technologies - RAST2011

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“…The importance of turnaround operations on total cost is aptly captured 17 : "Meeting the cost goal depends less on technical innovation than commercial demand and operational cost reduction." Shuttle turnaround activities are summarized as follows: Criticisms: 1.…”

Section: H Turnaround Operationsmentioning

confidence: 99%

An In-Line Reusable Launch Vehicle Concept Using Confined Load-Bearing Frozen Propellants

Baran

Anderson

Auxt

2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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This paper addresses the problem of the high cost of space vehicles evidenced by actual program lifetime-averaged costs of ~$1.5B per flight (Space Shuttle). Launch vehicles are complex and require high performance engineering design driven significantly by vehicle mass; a large fraction being propellant mass. The work described here investigates a novel concept towards more affordable launch vehicles and is primarily theoretical along with development of computational analyses. The concept involves the storage of propellant as a frozen monolithic mass, phase change to fluid during flight and fluid delivery to a rocket engine; i.e., solid-storage/fluid-delivery (SSFD). The approach is applicable to all propulsion systems (bipropellant, monopropellant, chemical, electric, nuclear, solar, beamed) and a variety of missions. We focus on a launch mission from Earth-surface to Earth-orbit and we focus on chemical bi-propellant propulsion in this paper. A reduction of operational cost is expected for such a vehicle concept from: increased functionality per unit mass, reduced complexity, and engine reusability. Frozen propellants can serve load-bearing/heat-sink roles prior to consumption. Innovative storage and delivery concepts reduce complexity and offer engine reusability. Improvements can be realized with existing rocket engine technology. Further improvements can be realized with development of a novel rocket engine. These will be discussed. We investigate feasibility and show results in terms of design: balance of heat rate necessary for melting with required propellant consumption for thrust and mechanical load-bearing capability with frozen propellant material yield strength and ultimate strength. We also investigate overall vehicle operation and show results in terms of propulsion performance, discuss costs, discuss technical challenges that remain and future research direction.

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“…[2][3][4] Significant research has been performed in rocket-based vehicle design optimization using various evolutionary techniques. [5][6][7][8][9][10][11][12][13][14][15][16] Cost has also been considered in some studies; [17][18][19] however, this paper represents an effort to minimize launch vehicle cost, for liquid-fueled launch vehicles, at the preliminary design stage using a GA.…”

Section: Introductionmentioning

confidence: 99%

Design Optimization of Space Launch Vehicles for Minimum Cost Using a Genetic Algorithm

Bayley¹,

Hartfield²

2007

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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This paper describes an effort to optimize liquid-fueled space launch vehicles for minimum cost. The entire launch vehicle is modeled to achieve a low-Earth (circular) orbit using multiple stages. The optimization scheme employs a genetic algorithm (GA) with the goals of minimizing both vehicle weight and vehicle cost per launch. Two and three-stage liquid propellant launch vehicles have been analyzed. In addition, results from an air-launched, two-stage liquid propellant launch vehicle are presented. The vehicle performance modeling requires that analysis from four separate disciplines be integrated into the design optimization process. Modeling of propulsion systems, aerodynamics, mass properties and flight dynamics have been integrated to produce a high fidelity system model of the entire vehicle. An existing, two-stage liquid propellant launch vehicle has been used to validate the two-stage liquid propellant system model. The cost model is mass-based and uses extensive historical data to produce a cost estimating relationship for a liquid propellant vehicle. For the design optimization, the primary goal is for the GA to minimize the differences between the desired and actual orbital parameters. This ensures the payload achieves the desired orbit. The third goal is to minimize total launch vehicle mass and system cost per launch.

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Launch Vehicle Design Features for Minimum Cost

Cited by 12 publications

References 4 publications

Multidisciplinary design optimization of an expendable launch vehicle

Multidisciplinary design optimization of an expendable launch vehicle

An In-Line Reusable Launch Vehicle Concept Using Confined Load-Bearing Frozen Propellants

Design Optimization of Space Launch Vehicles for Minimum Cost Using a Genetic Algorithm

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