| 摘要 |
1,036,033. Controlling aircraft. BOLKOW, G.m.b.H. March 19, 1964 [March 26, 1963], No. 11658/64. Heading B7G. An aerodynamic control device for the control of missiles comprises spoilers which are rotatable by air flow and which can be braked and have axes of rotation parallel to aerodynamic surfaces of the missile and transverse to the direction of airflow, and have blades which are arranged to enter recesses in the aerodynamic surfaces of the missile. A wing 1 (Fig. 1, not shown) having opposed surfaces 2 and 3 has mountings for freely rotatable vaned members 6 and 7 respectively, so positioned in cut-outs 4 and 5 that their axes lie substantially in the plane of the respective surfaces. The upper member comprises a plurality of vanes 10 attached to circular end plates 12, 13 carried by pivots 8, 9 and the lower member is similarly constructed with end plates 14, 15. An electromagnetic device, comprising an armature 24 mounted on a pivot 34 and stabilized in a central position by a tension spring 38, is provided to retard one vaned member or the other, brake pads 36, 37 being arranged to bear against end plate 12 or 14 when the appropriate coil 28 or 29 is energized. A solenoid 17 is positioned at the other end of the vaned members to attract an armature 42 against the action of a spring 45 to apply simultaneously brake pads 43, 44 against end plates 13, 15. By this means either or both of the vaned members may be held against free rotation to act as control spoilers. Other embodiments are described in which two planar vanes are geared together for free rotation in opposite directions with the planes of the vanes mutually at right angles, solenoidoperated sprags being provided to engage the gear teeth to hold the vanes so that one is in the plane of the corresponding wing surface and the other is normal to its corresponding surface. |
