Title:
Maneuver Trim Optimization Techniques for Active Aeroelastic Wings
Maneuver Trim Optimization Techniques for Active Aeroelastic Wings
| dc.contributor.author | Zink, Paul Scott | en_US |
| dc.contributor.author | Mavris, Dimitri N. | en_US |
| dc.contributor.author | Raveh, Daniella E. | en_US |
| dc.contributor.corporatename | American Institute of Aeronautics and Astronautics | |
| dc.contributor.corporatename | Georgia Institute of Technology. Aerospace Systems Design Laboratory | |
| dc.date.accessioned | 2005-05-26T14:04:59Z | |
| dc.date.available | 2005-05-26T14:04:59Z | |
| dc.date.issued | 2000-04 | en_US |
| dc.description | Presented at the 41st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and Exhibit, Atlanta, GA, April 3-6, 2000. | en_US |
| dc.description.abstract | A new method for performing trim optimization of Active Aeroelastic Wing (AAW) technology is presented. The method is based on posing the trim problem as a linear program and solving it with the simplex method. Trim optimization is then integrated with the structural design process in a sequential manner, such that new optimal deflections of the control surfaces are computed for every structural design iteration. The use of the simplex method for trim optimization allowed the elimination of non-physical constraints that had to be imposed when a gradient-based method was used. This resulted in significantly better objectives for the trim optimization. The sequential AAW design process was demonstrated on a lightweight fighter type aircraft performing symmetric and antisymmetric maneuvers at subsonic and supersonic speeds. The concurrent trim and structural optimization resulted in a significantly lighter structure compared to a structure designed with conventional control technology and to a structure employing AAW technology with fixed control surface deflections. | en_US |
| dc.format.extent | 129414 bytes | |
| dc.format.mimetype | application/pdf | |
| dc.identifier.uri | http://hdl.handle.net/1853/6405 | |
| dc.language.iso | en_US | en_US |
| dc.publisher | Georgia Institute of Technology | en_US |
| dc.publisher | Georgia Institute of Technology | |
| dc.publisher.original | American Institute of Aeronautics and Astronautics (AIAA) | |
| dc.relation.ispartofseries | ASDL; AIAA-2000-1330 | en_US |
| dc.relation.ispartofseries | ASDL; AIAA-2000-1330 | |
| dc.subject | Active aeroelastic wings | en_US |
| dc.subject | Optimization | en_US |
| dc.subject | Linear programming | en_US |
| dc.subject | Iterative solution | en_US |
| dc.subject | Control surfaces | en_US |
| dc.subject | Structural design | en_US |
| dc.subject | Aeroelasticity | en_US |
| dc.subject | Simplex method | en_US |
| dc.subject | Wings | en_US |
| dc.subject | Deflection | en_US |
| dc.subject | Weight | en_US |
| dc.subject | Aircraft maneuverability | en_US |
| dc.title | Maneuver Trim Optimization Techniques for Active Aeroelastic Wings | en_US |
| dc.type | Text | |
| dc.type.genre | Paper | |
| dspace.entity.type | Publication | |
| local.contributor.author | Mavris, Dimitri N. | |
| local.contributor.corporatename | Daniel Guggenheim School of Aerospace Engineering | |
| local.contributor.corporatename | Aerospace Systems Design Laboratory (ASDL) | |
| local.contributor.corporatename | College of Engineering | |
| relation.isAuthorOfPublication | d355c865-c3df-4bfe-8328-24541ea04f62 | |
| relation.isOrgUnitOfPublication | a348b767-ea7e-4789-af1f-1f1d5925fb65 | |
| relation.isOrgUnitOfPublication | a8736075-ffb0-4c28-aa40-2160181ead8c | |
| relation.isOrgUnitOfPublication | 7c022d60-21d5-497c-b552-95e489a06569 |
Files
Original bundle
1 - 1 of 1
- Name:
- AIAA-2000-1330.pdf
- Size:
- 126.38 KB
- Format:
- Adobe Portable Document Format
- Description: