Document Type

Conference Paper

Journal/Book Title/Conference

AIAA SCITECH 2025 Forum

Publisher

Aerospace Research Central

Location

Orlando, FL

Publication Date

1-3-2025

First Page

1

Last Page

21

Creative Commons License

Creative Commons Attribution 4.0 License
This work is licensed under a Creative Commons Attribution 4.0 License.

Abstract

Aircraft with non-traditional actuators tend to have multiple or infinite trim solutions for a single flight condition. For a given flight condition the bio-inspired rotating empennage fighter aircraft has multiple distinct trim solutions with varying tail rotation angles. In the present work these trim solutions are evaluated from various perspectives including: minimum drag, dynamic stability, controllability, and degree of controllability. The results of these analyses can be used to further constrain a trim solver routine such that a trim solution is found meeting a desired criterion. The purpose of the present paper is to evaluate the multiple trim solutions for the BIRE aircraft in order to confirm an appropriate constraint for a trim solution routine. It is found in a steady coordinated turn that the minimum drag, minimum throttle solution is the negative tail rotation solution. It is also found that the near-zero tail rotation solution has the least positive eigenvalue in comparative linearized analysis. Similar findings are noticed in steady-heading sideslip trim solutions.

Comments

AIAA-2025-0662

The authors of this work would like to thank Dr. James J. Joo for his encouragement in studying the alternate trim solutions of the BIRE aircraft. This work was funded by the Air Force Office of Scientific Research (AFOSR) Lab Task 23RQCOR006 with Dr. Les Lee as the program manager. This paper has been cleared for public release, Case Number: AFRL-2024-6307

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