Modular hybrid airframe structure for battery thermal event protection and repair
A replaceable web structure for an aircraft frame is described and includes a plurality of structural members fabricated from a first type of material, the replaceable web structure comprising a plurality of web members fabricated from thin sheets of a second type of material, wherein each of the web members is fastened to a web frame of one of the structural members to replace a web portion of the one of the structural members; wherein the second type of material is stronger than the first type of material such that one of the sheets of the second type of material is lighter weight than a sheet of equal strength of the first type of material.
1. An aircraft frame comprising:
a plurality of structural members fabricated from a first type of material, wherein each of the structural members comprises a web frame and a web portion within the web frame;
a plurality of web members fabricated from sheets of a second type of material, wherein each of the web members is fastened to the web frame of a respective structural member of the plurality of structural members to comprise the web portion of the structural member, wherein each of the web members includes a flange along at least one edge thereof; and
a plurality of fasteners for securing the flange of a first one of the web members to the flange of a second one of the web members to create an airgap to accommodate the fasteners, the airgap further providing thermal protection for a joint between the structural members to which the first and second ones of the web members are attached;
wherein the second type of material is stronger than the first type of material such that one of the sheets of the second type of material is lighter weight than a sheet of equal strength of the first type of material; and
wherein the second type of material is more heat-resistant than the first material.
2. The aircraft frame of claim 1 , wherein the first type of material is at least one of aluminum and aluminum alloy.
3. The aircraft frame of claim 1 , wherein the second type of material is titanium.
4. The aircraft frame of claim 1 , wherein the structural members comprise at least one of keel beams and intercostals.
5. The aircraft frame of claim 1 , wherein the structural members surround a battery compartment.
6. The aircraft frame of claim 1 , wherein the web members are fastened to the structural members with removable fasteners.
7. The aircraft frame of claim 5 , wherein the removable fasteners comprise pairs of nuts and bolts.
8. An aircraft comprising:
a plurality of structural members fabricated from a first type of material, wherein each of the structural members comprises a web frame and a web portion within the web frame;
a plurality of web members fabricated from sheets of a second type of material, wherein each of the web members is fastened to the web frame of a respective structural member of the plurality of structural members to comprise the web portion of the structural member, wherein each of the web members includes a flange along at least one edge thereof; and
a plurality of fasteners for securing the flange of a first one of the web members to the flange of a second one of the web members to create an airgap to accommodate the fasteners, the airgap further providing thermal protection for a joint between the structural members to which the first and second ones of the web members are attached;
wherein the second type of material is stronger than the first type of material such that one of the sheets of the second type of material is lighter weight than a sheet of equal strength of the first type of material; and
wherein the second type of material is more heat-resistant than the first material.
9. The aircraft of claim 8 , wherein the first type of material is at least one of aluminum and aluminum alloy.
10. The aircraft of claim 8 , wherein the second type of material is titanium.
11. The aircraft of claim 8 , wherein the structural members comprise at least one of keel beams and intercostals.
12. The aircraft of claim 8 , wherein the structural members surround a battery compartment.
13. The aircraft of claim 8 , wherein the web members are fastened to the structural members with removable fasteners.
14. An aircraft battery compartment, the aircraft battery compartment comprising:
a plurality of beams fabricated from a first type of metal, wherein a web of each of the beams comprises a web member fabricated from a sheet of a second type of metal, wherein the second type of metal is stronger and more heat resistant than the first type of metal such that the sheet of the second type of material is lighter weight than a sheet of equal strength of the first type of material;
wherein each of the web members includes a flange along at least one edge thereof, the battery compartment further comprising a plurality of fasteners for securing the flange of a first one of the web members the flange of a second one of the web members to create an airgap to accommodate the fasteners, the airgap further providing thermal protection for a joint between the structural members to which the first and second ones of the web members are attached.
15. The aircraft battery compartment of claim 14 , wherein the first type of metal is at least one of aluminum and aluminum alloy and the second type of material is titanium.
16. The aircraft battery compartment of claim 14 , wherein the web members are fastened to the beams using removable fasteners.