초록 ▼

The invention relates to an aircraft comprising a device, for example an optical device, for detection and/or measurement of atmospheric disturbances in the path of the aircraft. This measurement device is placed in the pressurized zone between the aircraft nose and the compartment of the landing ge

The invention relates to an aircraft comprising a device, for example an optical device, for detection and/or measurement of atmospheric disturbances in the path of the aircraft. This measurement device is placed in the pressurized zone between the aircraft nose and the compartment of the landing gear. It comprises: a structure box (18) designed to resist pressurization forces, aerodynamic fairing (13).

대표청구항 ▼

The invention claimed is: 1. An aircraft system comprising: a detection device connected to an aircraft and configured to detect atmospheric disturbances in the path of the aircraft, the connection between the detection device and the aircraft being disposed between a nose of the aircraft and landi

The invention claimed is: 1. An aircraft system comprising: a detection device connected to an aircraft and configured to detect atmospheric disturbances in the path of the aircraft, the connection between the detection device and the aircraft being disposed between a nose of the aircraft and landing gear of the aircraft; a structure box configured to resist pressurization forces while the aircraft is in flight and to separate the pressurized zone from the detection device, said structure box covering the detection device and located in the pressurized zone external and adjacent to the aircraft; and an aerodynamic fairing, which is a component distinct from the structure box, that covers the structure box with respect to an environment external to the aircraft, wherein the detection device is an “L” shaped light imaging detection and ranging (lidar) device, a vertical part of the L shape being located inside the aircraft, and a horizontal part of the L shape being located outside the aircraft and inside the structure box, wherein the structure box includes a flat glass portion on a front part of the structure box with respect to a longitudinal axis of the aircraft extending from the nose of the aircraft rearward, and wherein the structure box is a caisson. 2. The aircraft system according to claim 1, wherein the light imaging detection and ranging device is installed so as to be accessible via an avionics door of the aircraft. 3. The aircraft system according to claim 1, wherein the flat glass is disposed at an angle of less than 45° with respect to a vertical plane perpendicular to a horizontal plane formed by a longitudinal axis of the aircraft extending from the nose of the aircraft rearward and a transverse axis extending from one wing of the aircraft to another. 4. The aircraft system according to claim 1, wherein the fairing is disposed in contact with the structure box only on a side of the structure box opposite the aircraft. 5. The aircraft system according to claim 4, wherein the fairing extends farther toward a front of the aircraft than the light imaging detection and ranging device extends. 6. The aircraft system according to claim 5, wherein the fairing extends farther toward a rear of the aircraft than the light imaging detection and ranging device extends. 7. An aircraft system comprising: an “L” shaped light imaging detection and ranging device configured to detect atmospheric disturbances in the path of an aircraft and connected to the aircraft, a vertical part of the L shape being disposed within the aircraft, and a horizontal part of the L shape being disposed external to the aircraft; a structure box configured to resist pressurization forces, said structure box covering the device with respect to an environment external to the aircraft, said structure box connected to an external area of the aircraft; and an aerodynamic fairing, distinct from the structure box, covering the structure box to separate the structure box from the environment external to the aircraft, wherein the structure box includes a flat glass portion on a front part of the structure box with respect to a longitudinal axis of the aircraft extending from the nose of the aircraft rearward, and wherein the structure box is a caisson. 8. The aircraft system according to claim 7, wherein the flat glass is disposed at an angle of less than 45° with respect to a vertical plane perpendicular to a horizontal plane formed by a longitudinal axis of the aircraft extending from the nose of the aircraft rearward and a transverse axis extending from one wing of the aircraft to another. 9. The aircraft system according to claim 7, wherein the fairing is disposed in contact with the structure box only on a side of the structure box opposite the aircraft. 10. The aircraft system according to claim 9, wherein the fairing extends farther toward a front of the aircraft than the light imaging detection and ranging device extends. 11. The aircraft system according to claim 10, wherein the fairing extends farther toward a rear of the aircraft than the light imaging detection and ranging device extends.