| 摘要 |
The present invention is a missile-helicopter device which is capable of a projected, nose up ascent and a helicopter nose up descent. The device has an elongated missile body, fins, a latch release for the fins, bias mechanism for the fins and propulsion. The fins have relatively long lengths and short widths and are hingedly connected to the upper half of the missile body. The fins have a first position which is a substantially vertical position along their lengths parallel to the elongated missile body such that the fins protrude along their widths radially outwardly from the missile body at least at the lower half of the missile body so as to function as flight stabilizing fins during ascent. They also have a second position which is at approximately right angles or larger to the missile body such that the fins protrude radially outwardly along their lengths away from the upper half of the missile body so as to create a nose up helicopter type rotation during descent.
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