THRUST NOZZLE FOR THRUST VECTOR CONTROL IN AIRCRAFT FITTED WITH JET ENGINES

摘要

PCT No. PCT/DE90/00226 Sec. 371 Date Nov. 1, 1991 Sec. 102(e) Date Nov. 1, 1991 PCT Filed Mar. 21, 1990 PCT Pub. No. WO90/11222 PCT Pub. Date Oct. 4, 1990.The proposal is for a thrust nozzle for aircraft fitted with jet engines especially for lateral thrust vector control, in which the upstream ends of at least two flaps (8, 12) actuated via lever-like adjusters are arranged to pivot simultaneously at different angles of rotation about spindles running across the nozzle axis (20) and between walls (22, 23) running substantially parallel to the nozzle axis of a square nozzle housing in such a way that, with a permanently convergent nozzle contour, a narrowest cross-section is formed between the flaps (8, 12) at the outlet side; one end of each lever-like adjuster (28, 29) is to engage in downstream ends of the flaps, said adjusters being arranged at their movably mutually coupled other ends to travel in a guide path (30) which is curved so as to produce continuously different flap rotation angles; one or more narrowest cross-sections can either be kept continuously constant or change dependently upon the jet deflection angle.