An aircraft propulsion assembly includes a power unit, a nacelle positioned around the power unit, and a cleaning device configured to remove insect residue and in order to maintain optimal aerodynamic characteristics. This cleaning device is configured to spread at least a cleaning liquid over an exterior and forward region of the air intake of the nacelle, the cleaning liquid being entrained by a high-speed airflow generated by the power unit and acting as a high-pressure water jet to encourage the removal of the insect residue.

An aircraft propulsion assembly includes a power unit, a nacelle positioned around the power unit, and a cleaning device configured to remove insect residue and in order to maintain optimal aerodynamic characteristics. This cleaning device is configured to spread at least a cleaning liquid over an exterior and forward region of the air intake of the nacelle, the cleaning liquid being entrained by a high-speed airflow generated by the power unit and acting as a high-pressure water jet to encourage the removal of the insect residue.

A deflection measurement assembly according to an example of the present disclosure includes, among other things, a nacelle arranged about an axis to define a flow path, a cable assembly arranged at least partially about the axis, and a transducer coupled to the cable assembly.

A deflection measurement assembly according to an example of the present disclosure includes, among other things, a nacelle arranged about an axis to define a flow path, a cable assembly arranged at least partially about the axis, and a transducer coupled to the cable assembly.

A deflection measurement assembly according to an example of the present disclosure includes, among other things, a nacelle arranged about an axis to define a flow path, a cable assembly arranged at least partially about the axis, and a transducer coupled to the cable assembly.

A thermal insulation support includes a body including a first edge portion and a second edge portion extending generally along a longitudinal axis of the body. A first flange extending a first distance from the first edge portion of the body is coupled to a first wall. A second flange extending a second distance from the second edge portion of the body is coupled to a second wall.

A thermal insulation support includes a body including a first edge portion and a second edge portion extending generally along a longitudinal axis of the body. A first flange extending a first distance from the first edge portion of the body is coupled to a first wall. A second flange extending a second distance from the second edge portion of the body is coupled to a second wall.

For gains in terms of aerodynamic performance levels, an aircraft engine assembly includes a turbomachine, a fastening strut for the turbomachine, and at least one foldable ventilator cover which surrounds the turbomachine and which includes: a first cover sector which includes a first end portion which is mounted so as to be articulated to the fastening strut, along a first articulation axis, and a second cover sector which includes a first end portion which is mounted so as to be articulated to a second end portion of the first cover sector, along a second articulation axis parallel with the first articulation axis. The second end portion is mounted so as to be guided at one side and the other thereof by a thrust inverter cover of the engine assembly and an air inlet structure of this assembly, respectively.

For gains in terms of aerodynamic performance levels, an aircraft engine assembly includes a turbomachine, a fastening strut for the turbomachine, and at least one foldable ventilator cover which surrounds the turbomachine and which includes: a first cover sector which includes a first end portion which is mounted so as to be articulated to the fastening strut, along a first articulation axis, and a second cover sector which includes a first end portion which is mounted so as to be articulated to a second end portion of the first cover sector, along a second articulation axis parallel with the first articulation axis. The second end portion is mounted so as to be guided at one side and the other thereof by a thrust inverter cover of the engine assembly and an air inlet structure of this assembly, respectively.

To surely grasp an unlocked state of a cowl member while suppressing cost and time necessary for measures against forgetting of locking of an engine nacelle. An aircraft according to the present invention includes: an engine (3) that includes an engine main body (4, 5) outputting thrust force and an engine nacelle (7) surrounding the engine main body (4, 5); an engine pylon (2) that supports the engine main body (4, 5) to a main wing (1) and axially supports a cowl member (8) to be openable, the cowl member (8) configuring the engine nacelle (7); a locking part (30) that locks the cowl member (8) of the engine nacelle (7) in a closed state; and one or more light emitting sections (15) that are disposed inside the cowl member (8) and show an unlocked state of the cowl member (8).