Active Control for Aircraft Landing Gear
Abstract
The purpose of the thesis is to investigate the use of active control on aircraft landing gear. The problem of vibration isolation is considered using the optimal control approach to establish the control force necessary to minimize runway imposed vibration. A two degree of freedom linear landing gear model is considered, and both the (1-cos wt) bump and an equivalent deterministic input derived from runway spectra, are used as vertical forcing function inputs to the model. An integral square cost function is formed with the integrand consisting of the absolute acceleration of the aircraft squared, plus a weighting factor times the actuator control force squared. The conjugate gradient technique is used for numerical solution of the problem. Results indicate that considerable improvement in vibration isolation could be gained with the active control landing gear system over the present passive systems for most paved runway surfaces. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1970
- Accession Number
- AD0875535
Entities
People
- Ronald A. De Yoe
Organizations
- Air Force Institute of Technology