| 摘要 |
The invention provides an apparatus locatable in a missile tip 56, comprising a turbine impeller 10 operatively connected to an electricity generator 12, and a valve assembly 14 locatable upstream of the impeller 10. In use an induced flow of air passes through a passage 60 defined by the missile tip 56 to drive the turbine 10 and the generator 12. The valve assembly 14 is designed to throttle the flow of air at the maximum flight speeds reached by the missile tip 56. The generator 12 becomes operative again at lower flight speeds to power electronic equipment located in the missile tip 56. <IMAGE> |
