Airframe attachments
Disclosed here are airframe component assemblies including example embodiments with a root connected to an aircraft fuselage, a free section with a connection portion with holes, a slidable attachment section formed to fit between the root and the free section, and an elastomeric retention device coupled to the root and the slidable attachment section, the elastomeric retention device configured to exert a force to pull the slidable attachment toward the root.
1 . A wing assembly, comprising:
a wing root connected to an aircraft fuselage, the wing root having a leading edge, a trailing edge, a protrusion forming a cut out space, the protrusion having at least two holes;
a free wing section with a bracket, the bracket formed to fit into the wing root cut out space, the free wing section bracket including at least two holes;
a slidable wing attachment section formed to fit between the wing root and the free wing section;
an elastomeric retention device coupled to the wing root and the slidable wing attachment section, the elastomeric retention device configured to exert a force to pull the slidable wing attachment section toward the wing root;
wherein the slidable wing attachment section includes at least one rigid engagement member configured to engage the at least two holes of the wing root and the at least two holes of the free wing section bracket;
wherein the bracket includes a cam surface configured to engage a guide member of the slidable wing attachment section during insertion of the bracket into the cut out space; and
wherein engagement of the cam surface with the guide member displaces the slidable wing attachment section away from a locking position against the force of the elastomeric retention device during insertion of the bracket into the cut out space.
2 . The wing assembly of claim 1 wherein the elastomeric retention device is a coiled tension spring disposed within a cavity formed in at least one of the wing root and the slidable wing attachment section.
3 . The wing assembly of claim 1 wherein the wing root includes a button protrusion and the free wing section includes a button cavity configured to mate with the button protrusion to provide supplemental structural support when assembled.
4 . The wing assembly of claim 1 wherein the slidable wing attachment section includes a plurality of rigid engagement members including two rods formed to fit into the wing root holes and the free wing section bracket holes.
5 . The wing assembly of claim 1 wherein the elastomeric retention device comprises a piston system including a hydraulic piston, the piston system configured to pull the slidable wing attachment section toward the wing root.
6 . The wing assembly of claim 1 wherein the elastomeric retention device is configured to exert the force in a direction toward the leading edge of the wing root.
7 . The wing assembly of claim 1 wherein the force the elastomeric retention device is configured to exert the force in a direction toward the trailing edge of the wing root.
8 . The wing assembly of claim 4 wherein the free wing section includes a bracket with a wedge, configured to force the slidable wing attachment section away from the wing root to engage the two rods into the free wing section bracket holes, wherein the wedge includes a notch configured to receive the guide member.
9 . A wing assembly comprising:
a wing root defining a cavity;
a free wing section including a bracket receivable within the cavity;
a slidable locking member disposed within the cavity;
a plurality of rigid engagement members coupled to the slidable locking member;
a biasing member configured to bias the slidable locking member toward a locking position;
wherein insertion of the bracket into the cavity causes a cam surface of the bracket to engage a guide member of the slidable locking member and translate the slidable locking member away from the locking position.
10 . The wing assembly of claim 9 , wherein the plurality of rigid engagement members extend in parallel.
11 . The wing assembly of claim 9 , wherein the plurality of rigid engagement members are spaced apart to resist torsional movement of the free wing section relative to the wing root.
12 . The wing assembly of claim 9 , wherein the guide member comprises a guide post configured to slide within a guide channel formed in the wing root.
13 . The wing assembly of claim 9 , wherein the cam surface comprises a curved surface configured to convert insertion force into translational movement of the slidable locking member.
14 . An aircraft wing connection system comprising:
a first wing portion;
a second wing portion;
a translational locking block positioned between the first and second wing portions;
at least one rigid locking member coupled to the translational locking block;
a biasing device configured to bias the translational locking block toward a locked configuration;
wherein engagement of a wedge-shaped surface on the second wing portion with a guide feature on the translational locking block displaces the translational locking block against the biasing device during assembly.
15 . The system of claim 14 , wherein the wedge-shaped surface includes a notch configured to receive the guide feature.
16 . The system of claim 14 , wherein the biasing device comprises a coiled spring, elastic band, piston, pulley system, or magnet.
17 . The system of claim 14 , wherein the translational locking block includes a cavity housing the biasing device.
18 . The system of claim 14 , wherein the at least one rigid locking member comprises two rods configured to engage aligned openings in both wing portions.
19 . The system of claim 14 , wherein respective electrical connectors are positioned on the first and second wing portions and automatically engage one another upon locking.
20 . The system of claim 14 , wherein the first and second wing portions include, respectively, a protrusion and matching cavity configured to provide supplemental structural engagement.