Abstract
The disturbance effect of random wind on missile is analyzed. A proportional navigation guidance system model with random wind disturbance is built and then simplified. The analytic solution is obtained by using adjoint method. Finally, the original proportional navigation guidance system is analyzed in detail. The analytic solution of the simplified model demonstrates that the miss distance caused by random wind varies as the standard deviation of random wind velocity and trends towards a constant value with the guidance time increase. Simulation results show that the increase of proportion navigation coefficient is beneficial to inhibit the harmful influence of random wind on the guidance precision, either improving autopilot response or reducing the damping coefficient have the same effect.
| Original language | English |
|---|---|
| Pages (from-to) | 1481-1485 |
| Number of pages | 5 |
| Journal | Binggong Xuebao/Acta Armamentarii |
| Volume | 32 |
| Issue number | 12 |
| Publication status | Published - Dec 2011 |
Keywords
- Adjoint method
- Control and navigation technology of aerocraft
- Guidance precision
- Proportional navigation
- Random wind