1990 Fiscal Year Final Research Report Summary
Control of Flexible Flight Vehicles
| Project/Area Number |
01550047
|
|---|
| Research Category |
Grant-in-Aid for General Scientific Research (C)
|
| Allocation Type | Single-year Grants |
|---|
| Research Field |
Aerospace engineering
|
|---|
| Research Institution | Kyushu University |
|---|
Principal Investigator |
GOTO Norihiro Kyushu University, Department of Aeronautical Engrg., Professor, 工学部, 教授 (60038015)
|
|---|
| Co-Investigator(Kenkyū-buntansha) |
OKAZAKI Hiromitsu Kyushu University, Department of Aeronautical Engrg., Assistant, 工学部, 助手 (10177040)
HOKAMOTO Shinji Saga University, Department of Mechanical Engrg., Assistant, 理工学部, 助手 (80199463)
|
|---|
| Project Period (FY) |
1989 – 1990
|
| Keywords | vibration / control / modal stability / spillover / characteristic equation / root locus method / LAC / HAC |
|---|
| Research Abstract |
Precise attitude and shape control of flexible flight vehicles such as large-sized aircraft and large space structures requires active control of flexural vibrations. This project is concerned with the design of vibration control systems for these flexible flight vehicles. First in the project, the root locus method was extended to be able to deal with distributed parameter systems. Secondly, by applying the perturbation method to the characteristic equation for the root locus analysis modal stability conditions were obtained for general multi-sensor and multi-actuator systems. The modal stability conditions were then utilized to prove mathematically the third result that a non-colocated one-actuator and one-sensor system always has unstable modes. Taking these results into consideration, a new vibration control technique was proposed as the final result of this project. The new technique is referred to as the Time Sharing LAC (Low Authority Control) /HAC (High Authority Control) Technique, in which the HAC part of the LAC/HAC system is turned off at regular intervals so as to minimize the spillover effects on the system stability. This technique was tested in the experiment of controlling transversal vibrations of a cantilever beam to show its effectiveness and practicality.
|
