Turbojet engine thrust reverser and exhaust nozzle assembly

An exhaust assembly for a jet powerplant of a supersonic airplane, the assembly comprising:

• a primary multi-flap nozzle of variable cross-section situated downstream of a primary duct (5), the primary nozzle having a primary exhaust orifice (7) from which a primary gas flow (F1) will be exhausted during operation of the jet powerplant;
• a secondary multi-flap nozzle of variable cross-section situated downstream of a secondary duct (9) enclosing the primary duct (5), the secondary nozzle having a secondary exhaust orifice (12) from which a secondary gas flow (F2) will be exhausted during operation so of the jet powerplant, the secondary nozzle extending rearward beyond the primary exhaust orifice (7), the primary gas flow (F1) and the secondary gas flow (F2) comprising a gas jet flowing through the exhaust assembly downstream of the secondary exhaust orifice (12);
• a fairing (11) enclosing the secondary duct (9) and fitted with a throat (13) downstream of the exhaust orifice (12) of the secondary nozzle, the throat (13) being followed by a diverging portion (14);
• a thrust reverser (15) comprising two eyelids (16, 17) affixed in a pivotable manner to the fairing (11), one on each side of an axial plane of symmetry (P1), the eyelids (16, 17) being movable between an active, thrust-reversal position wherein the eyelids (16, 17) project transversely into the gas jet downstream of the fairing (11) to deflect the gas jet in a forward direction for thrust-reversal and an inactive, forward-thrust position wherein the eyelids (16, 17) are situated in an extension of the fairing (11), the two eyelids (16, 17) each being mounted on the fairing (11) by two lateral linkrods (60) which are freely pivotable relative to the fairing (11) about a transverse axis (61) in the vicinity of the axial plane of symmetry (P1);
• at least two inner actuators (63) anchored on the fairing (11), each of the two inner actuators (63) being connected to an inner point (66) on a respective one of the eyelids (16, 17), the inner point (66) being relatively near axial plane of symmetry (P1);
• and
• at least two outer actuators (64) anchored on the fairing (11), each of the two outer actuators (64) being connected to an outer point (68) on a respective one of the eyelids (16, 17), the outer point (68) being relatively remote from the axial plane of symmetry (P1);
• wherein the two eyelids (16, 17) are retained by the respective inner and outer actuators (63, 64) such that the inner and outer actuators (63, 64) comprise a driving mechanism for the two eyelids (16, 17).