Structures to limit collision damage for aircraft
Described herein is an aircraft. The aircraft includes a peripheral assembly, such as a sensor probe. The aircraft further includes a release assembly connecting the peripheral assembly to a portion of the aircraft. The release assembly is configured to separate the peripheral assembly and the portion upon receipt of a threshold force. The release assembly may be configured to allow for the quick release, such as via a snap-fit connection, between the peripheral assembly and the portion of the aircraft.
1 . An aircraft comprising:
a portion of the aircraft having a wing assembly and
a peripheral assembly comprising:
a sensor probe; and
a breakaway mechanism connecting the peripheral assembly to the portion of the aircraft having the wing assembly wherein the breakaway mechanism separates from the peripheral assembly and the portion of the aircraft upon receipt of a threshold impact force, the breakaway mechanism comprising:
a connecting feature that facilitates a secure connection between the portion of the aircraft and the peripheral assembly;
wherein the connecting feature is a sacrificial component that is configured to fail in a predetermined manner upon the breakaway mechanism receiving the threshold impact force, permitting separation of the peripheral assembly from the portion of the aircraft.
2 . The aircraft of claim 1 , wherein the sensor probe comprises:
a microphone assembly having a portion configured to receive audio signals; and
a nosecone configured to shield the portion of the microphone assembly from noise generated by direct impact of airflow.
3 . The aircraft of claim 1 , wherein the connecting feature is configured to release from the wing assembly upon receipt of the threshold impact force along a longitudinal direction of the sensor probe and transverse to the connecting feature.
4 . The aircraft of claim 1 , wherein the connecting feature comprises a nylon material, a glass material, a shear pin, magnets, or detents.
5 . The aircraft of claim 1 , wherein the breakaway mechanism further comprises:
a blade attached to the sensor probe; and
a base attached to the portion of the aircraft;
wherein the base and the blade are releasably connected to one another via the sacrificial component.
6 . The aircraft of claim 1 , wherein the breakaway mechanism further comprises:
a coupling node that establishes an electrical coupling between the sensor probe and electrical components of the aircraft.
7 . The aircraft of claim 1 , wherein the breakaway mechanism further comprises:
a thread insert configured for threadable engagement with threads of the connecting feature.
8 . The aircraft of claim 1 , wherein the sacrificial component is configured to fail in the predetermined manner by shearing or severing in a predetermined manner.
9 . A method comprising:
securing a connection between a portion of an aircraft having a wing assembly and a peripheral assembly with a breakaway mechanism, the breakaway mechanism comprising:
a connecting feature that is configured to secure the connection between the portion of the aircraft and the peripheral assembly, wherein the connecting feature is a sacrificial component that is configured to fail in a predetermined manner upon the breakaway mechanism receiving a threshold impact force, permitting separation of the peripheral assembly from the portion of the aircraft;
releasing the peripheral assembly from the wing assembly via the sacrificial component failing in the predetermined manner via receiving the threshold impact force;
wherein the portion remains substantially intact during the releasing of the peripheral assembly.
10 . The method of claim 9 , wherein the peripheral assembly comprises a sensor probe, the sensor probe comprising:
a microphone assembly having a portion configured to receive audio signals; and
a nosecone configured to shield the portion of the microphone assembly from noise generated by direct impact of airflow.
11 . The method of claim 10 , wherein the threshold impact force is along a longitudinal direction of the sensor probe and transverse to the connecting feature.
12 . The method of claim 10 , wherein the connecting feature comprises a nylon material, a glass material, a shear pin, magnets, or detents.
13 . The method of claim 10 , wherein the breakaway mechanism further comprises:
a blade attached to the sensor probe; and
a base attached to the portion of the aircraft;
wherein the base and the blade are releasably connected to one another via the sacrificial component.
14 . The method of claim 13 , wherein the received threshold impact force is associated with a collision of the blade with another object.
15 . The method of claim 10 , wherein the breakaway mechanism further comprises:
a coupling node that establishes an electrical coupling between the sensor probe and electrical components of the aircraft.
16 . The method of claim 9 , wherein the breakaway mechanism further comprises:
a thread insert configured for threadable engagement with threads of the connecting feature.
17 . The method of claim 9 , wherein the sacrificial component fails in the predetermined manner by shearing or severing in a predetermined manner.
18 . The method of claim 9 , wherein following the step of releasing the peripheral assembly, the method further comprises a step of:
landing the aircraft in a controlled manner.