Abstract
In order to analyze the effect of disturbance rejection rate on stability of the guidance system, the conception of seeker disturbance rejection rate parasitical loop was presented. A model of parasitical loop of seeker disturbance rejection rate was established based on the phase lag of seeker disturbance rejection rate. When the parasitical loop is feedforward and feedback, the stability zone of the parasitical loop is obtained based on the Routh criteria and the normalized model. The effect of phase lag on stability zone was analyzed in complex frequency domain. Simulation results show that the phase lag of seeker disturbance rejection rate reduces the stability zone. The smallest stability zone occurs at about -140° phase lag instead of -180°. As a result , it is helpful for the engineers at the preliminary stage of missile design.
| Original language | English |
|---|---|
| Pages (from-to) | 28-32 |
| Number of pages | 5 |
| Journal | Binggong Xuebao/Acta Armamentarii |
| Volume | 32 |
| Issue number | 1 |
| Publication status | Published - Jan 2011 |
Keywords
- Disturbance rejection rate parasitical loop
- Disturbance rejection rate with phase lag
- Seeker disturbance rejection rate
- Spacecraft structure and design
- Stability