The local distributed criteria method for multidisciplinary optimization of launcher parameters

Paper number

IAC-06-C2.2.08

Author

Dr. Alexander Filatyev, Central Aero-HydroDynamic Institute, Russia

Coauthor

Mr. Alexander Golikov, Central Aero-HydroDynamic Institute, Russia

Coauthor

Dr. Alexander Shanygin, Central Aero-HydroDynamic Institute, Russia

Coauthor

Mr. Vladimir Voityshen, Central Aero-HydroDynamic Institute, Russia

Year

2006

Abstract

The new approach to the complex optimization of launcher parameters by the target criterion are formulated in view of requirements of aerodynamics, strength and control. The approach is based on the local decomposition of the initial problem into monodisciplinary subtasks with special Local Distributed Criteria (LDC). The LDC, on the one hand, give to monodisciplinary subtasks an independent access to the unified target criterion (the maximum payload mass or other for mutual problems), and on the other hand, take into account the specific contribution of all flight phases (Mach numbers, altitudes, etc.). The regular method of LDC formation is described on the basis of sensitivity functions. These functions resulted from transformation of conjugate variables and Lagrange multipliers extracted from the rigorous solution of the launcher trajectory optimization problem by the target criterion with the use of the Pontryagin maximum principle.
 
Advantages of the developed approach:

- natural objective subjection of monodisciplinary variables and parameters to the single general problem - maximization of the payload mass;

- the consideration of nonlinear feature of relation of the target functional from monodisciplinary variables and parameters, including bifurcations;

- possibility to use comprehensive (without simplifications) monodisciplinary methods under control of developers.

The following programs are used: the software ASTER for the thorough optimization of branched trajectories by the Pontryagin maximum principle, and the software for the structural layout optimization and weight analysis based on the finite element method. These programs are developed separately from each other and were intended firstly for the solution of the appropriate monodisciplinary problems. Due to the LDC approach, they have been joined to the unified virtual complex of the multidisciplinary optimization, which capabilities are much higher than the simple sum of capabilities of each separate program.
 
The approach advantages are demonstrated on examples of space launchers started from the Earth surface and aircraft carrier. The qualitatively new solutions are demonstrated both in the field of the multidiscipline optimization, and in separate disciplines. The capability of the launcher layout research by the LDC-shell is exhibited in the case of nonlinear and discontinues (bifurcation) relations of influence functions to layout parameters.

Abstract document

IAC-06-C2.2.08.pdf

Manuscript document

IAC-06-C2.2.08.pdf (🔒 authorized access only).

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