Abstract
Strap-on launch vehicle attitude control is a complex nonlinear problem that is compounded by several factors such as aerodynamics modeling uncertainties, internal/external disturbance and elastic frequency perturbation. An attitude controller of strap-on launch vehicle based on dynamic compensation linearization theory and elastic frequency identification is presented. The controller contains a rigid body attitude controller and a adaptive elasticity filter. The rigid body attitude controller that augments differential compensator which is used to estimate and compensate impact of parametric uncertainties, movement coupling and disturbances by taking advantage of the information of gyros and attitude sensors, to a fractional-order PDμ controller is implemented. Considering the frequency difference between rigid body motion and elastic vibration, sample signals of controller and attitude sensor output are utilized to identify elastic frequency. The adaptive elasticity filter dynamically adjusts the center frequency of notch filter according to the identification result to suppress elastic vibration. Validation of the design is done by numerical simulation. Simulation results show that the controller exhibits better dynamic performance, stronger robustness and elasticity restrain ability.
| Original language | English |
|---|---|
| Pages (from-to) | 578-585 |
| Number of pages | 8 |
| Journal | Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University |
| Volume | 35 |
| Issue number | 4 |
| State | Published - 1 Aug 2017 |
Keywords
- Angle of attack
- Attitude control
- Controllers
- Differentiator
- Elastic frequency identification
- Fractional-order
- Launch vehicles