Multistage rocket preliminary design and trajectory optimization using a multidisciplinary approach

Morgado, F. M. P.; Marta, André C.; Gil, P. J. S.

doi:10.1007/s00158-022-03285-y

Cited by 6 publications

(1 citation statement)

References 53 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The methods for solving trajectory optimization problems can be classified as direct or indirect [28]. In the context of concurrent design and trajectory optimization, the usage of an indirect method would imply an optimization architecture with multi-level optimizers in which the trajectory optimization would be nested inside the design optimizer, thus implying considerable computational cost [29]. As such, this work uses a direct collocation method (also known as a direct transcription method), which is an implicit direct trajectory optimization based methodology that uses the control and state variables as optimization variables and the numerically integrated differential equations of motion as constraints.…”

Section: Trajectory Optimization Methodsmentioning

confidence: 99%

Concurrent Trajectory Optimization and Aircraft Design for the Air Cargo Challenge Competition

Matos

Marta

2022

Aerospace

Self Cite

View full text Add to dashboard Cite

A coupled aerostructural aircraft design and trajectory optimization framework is developed for the Air Cargo Challenge competition to maximize the expected score based on cargo carried, altitude achieved and distance traveled. Its modular architecture makes it easily adaptable to any problem where the performance depends not only on the design of the aircraft but also on its flight trajectory. It is based on OpenAeroStruct, an aerostructural solver that uses analytic derivatives for efficient gradient-based optimization. A trajectory optimization module using a collocation method is coupled with the option of using b-splines to increase computational efficiency together with an experimentally-based power decay model that accurately determines the aircraft propulsive response to control input depending on the battery discharge level. The optimization problem totaled 206 variables and 283 constraints and was solved in less than 7 h on a standard computer with 12% reduction when using b-splines for trajectory control variables. The results revealed the need to consider the multi-objective total score to account for the different score components and highlighted the importance of the payload level and chosen trajectory. The wing area should be increased within allowable limits to maximize payload capacity, climb to maximum target height should be the focus of the first 60 s of flight and full throttle should be avoided in cruise to reduce losses and extend flight distance. The framework proved to be a valuable tool for students to easily obtain guidelines for both the model aircraft design and control to maximize the competition score.

show abstract

Section: Trajectory Optimization Methodsmentioning

confidence: 99%