Aircraft structure dynamic loading testing device

A dynamic loading testing device, for dynamic load testing of an aircraft structure, the device comprising:

• a nozzle with a fluid inlet and a fluid outlet, and defining a nozzle force direction extending from the fluid outlet to the fluid inlet;
• an attachment mechanism for attaching the nozzle to the aircraft structure, the attachment mechanism comprising:
• a first portion attached to the nozzle such that the nozzle force direction is constrained at a set orientation with respect to the first portion;
• and
• a second portion for attaching to the aircraft structure, wherein the second portion is rigidly connected to the first portion and configured to be constrained at a given orientation with respect to the aircraft structure;
• a fluid flow rate controller;
• and
• a length of conduit for connecting at a first end to a fluid supply and connected at a second end to the nozzle inlet;
• wherein, in use, the nozzle force direction is constrained at a desired orientation with respect to the aircraft structure, and fluid is supplied along the length of conduit to the nozzle inlet and ejected from the nozzle outlet such that the nozzle exerts a dynamic force on the aircraft structure, in a direction of the nozzle force direction.

A kit of parts for forming a dynamic loading testing device, for dynamic load testing of an aircraft structure, comprising:

• a nozzle with a fluid inlet and a fluid outlet, and defining a nozzle force direction extending from the fluid outlet to the fluid inlet;
• an attachment mechanism for attaching the nozzle to the aircraft structure, the attachment mechanism comprising:
• a first portion for attaching to the nozzle such that the nozzle force direction is constrained at a set orientation with respect to the first portion;
• and
• a second portion for attaching to the aircraft structure, wherein the second portion is configured to be rigidly connected to the first portion and configured to be constrained at a given orientation with respect to the aircraft structure;
• a fluid flow rate controller;
• and
• a length of conduit for connecting at a first end to a fluid supply and for connecting at a second end to the nozzle inlet;
• wherein, in use, the nozzle force direction is constrained at a desired orientation with respect to the aircraft structure, and fluid is supplied along the length of conduit to the nozzle inlet and ejected from the nozzle outlet such that the nozzle exerts a dynamic force on the aircraft structure in a direction of the nozzle force direction.

A dynamic loading testing device, for dynamic load testing of an aircraft structure, the device comprising:

• a nozzle having an outlet for ejecting fluid in a first direction along a nozzle axis;
• an attachment mechanism for attaching the nozzle to the aircraft structure so that the nozzle axis is constrained to a set orientation with respect to the aircraft structure;
• a fluid flow rate controller;
• and
• a length of conduit for supplying fluid to the nozzle;
• wherein, in use, when fluid is supplied along the length of conduit to the nozzle and ejected from the nozzle outlet in the first direction, the nozzle exerts a dynamic force on the aircraft structure in a second direction along the nozzle axis, the second direction being opposite to the first direction.