A Multiobjective, Multidisciplinary Design Optimization of Solid Propellant Based Space Launch Vehicle

Abstract

This paper proposes an approach for the multidisciplinary design & optimization of space launch vehicle, wherein the structure/mass, aerodynamics, propulsion and the trajectory system design are performed simultaneously using non-dominated sorting based genetic algorithm. The design problem is posed as an optimization problem in which all the discipline parameters constitute the design variables, which are used to optimize the multi-objective function, thereby resulting in an optimal overall design. The approach is demonstrated by application to the integrated design of a four stage solid launch vehicle. The mission is to deliver predefined payload to the low earth (circular) orbit. An existing, real world system has been used to validate the multistage launch vehicle system model. Nomenclature E a = ratio of thrust in vacuum to thrust in ground D = solid rocket motor diameter, m cr d = throat diameter, m ex d = exit diameter, m o G = vehicle liftoff mass, kg I G = mass of guidance system, steering system and instrument section, kg prop G = mass of propulsion system, kg noz G = mass of nozzle, kg case G = mass of motor case, kg shell G = mass of combustion chamber shell, kg coating G = mass of coating inside, kg silver G = mass of grain silver, kg red G = mass of redundancy of grain, kg aux G = mass of auxiliary parts, kg E spo I = ground effective specific impulse, sec c p = combustion chamber pressure, N/m 2 m p = ratio of total mass to x-sectional area, kg/m 2 k t = running time of ith stage solid rocket motor, sec ε = expansion ratio 1 Doctoral student, School of Astronautics, Student member AIAA, zafar6909@yahoo.com 2 Professor, School of Astronautics, helinshu@sina.com 3 Associate Professor, School of Astronautics, xdj@buaa.edu.cn Downloaded by ROKETSAN MISSLES INC. on February 4, 2015 | http://arc.aiaa.org | 2 gn λ = fineness of grain k µ = ratio of dry mass to total mass o ν = mass to thrust ratio

Optimization of a small satellite tridyne propulsion system

“…The development of heuristic multi-objective optimization techniques over the past decade has alleviated many of the problems present in single objective techniques as well as gradient based methods. These techniques have been used widely in the past in aerospace systems [19], including integrated launch vehicle design [20,21], UAY propulsion systems [22], and solid rocket motor design. [23] To the authors' knowledge, there has been no previous literature presented on the integrated modeling and multi objective optimization of small satellite propUlsion systems.…”

Integrated Optimization of First-Stage SRM and Ascent Trajectory of Multistage Launch Vehicles

“…The maximum permissible values for the quantities in Eqs. (16)(17)(18)(19)(20) are reported in Table 2. The launcher and the payload are subjected, during the flight, to both static and dynamic axial loads.…”

“…A few attempts have been made to perform an integrated design and optimization of a complete SRM-based aerospace system, such as an air-launched satellite vehicle [14], a ground-launched intercep-tor [15] or a four-stage launcher [16], by simultaneously considering solid motors, launcher flight mechanics, and mass configuration. Also, a multidisciplinary optimization approach involving both structural and internal ballistic performance constraints has been recently applied to the design of slotted propellant grains for an SRM [17].…”

Multidisciplinary integrated design of long-range ballistic missile using PSO algorithm

“…Zeeshan et al [15] proposed an MDO strategy for the conceptual design of a multistage interceptor by applying a hybrid optimization method composed of the genetic algorithm (GA) and sequential quadratic programming (SQP), which provides designers with an original and impressive approach. Zafar [16,17] developed a hybrid algorithm with a switch to a local search algorithm for multidisciplinary design of the solid launch vehicle at the conceptual level. In [18,19], an effort was presented to optimize the multidisciplinary design of an entire space launch vehicle to the low earth orbit, consisting of multiple stages by using the GA with the goal of minimizing vehicle weight.…”