# US 7,607,617 B2 · Wing unit, in particular spar box, for forming aerodynamically active surfaces of an aircraft, in particular airfoils, horizontal tail units or rudder units of a plane > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 7,607,617 B2 - Document ID: US7607617B2 - Status: Granted - Kind: B2 - Application number: 11/316,126 - Filed: 2005-12-22 - Published: 2006-10-12 - Granted: 2009-10-27 - Earliest claimed: 2004-12-22 - Assignees: Airbus Deutschland GmbH - Inventors: Barnaby Law - Web page: https://patentgrep.com/patent/US7607617B2 ## CPC - B64C 3/18: Spars; Ribs; Stringers - B64C 3/42: Adjusting about chordwise axes - B64C 3/44: Varying camber - B64C 3/52: Warping - B64C 2003/142: {with variable camber along the airfoil chord} - Y02T 50/10: Drag reduction - B64C: AEROPLANES; HELICOPTERS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract The invention relates to a wing unit, in particular a spar box for forming aerodynamically active surfaces of an aircraft, in particular airfoils, horizontal tail units, or rudder units of a plane. Aerodynamic improvements can be obtained due to a surface geometry of the aerodynamically active surfaces, which surface geometry is adapted to the respective operating state of the plane by using the actuating members and/or weight savings due to minimizing of structural mechanical loads of the wing unit. ## Claims ### Claim 1 A wing unit, in particular a spar box, for forming an aerodynamically active surface of an aircraft, in particular airfoils, horizontal tail units, or rudder units of a plane, comprising: an upper shell and a lower shell, the upper shell and the lower shell forming the aerodynamically active surface; at least two ribs; at least two actuating members; and at least two spars; wherein in a region between the upper shell and the lower shell the at least two actuating members are arranged for modifying the surface geometry of the aerodynamically active surface or the mechanical properties of the wing unit, or both the surface geometry of the aerodynamically active surface and the mechanical properties of the wing unit; wherein between the at least two ribs, the at least two actuating members are arranged crosswise for forming a tension shear; and wherein the at least two actuating members are arranged substantially in parallel to the at least two spars. ### Claim 2 (depends on 1) The wing unit according to claim 1, wherein the at least two actuating members are adapted in such a way that a surface geometry of an aerodynamically active surface is changeable by using a control and regulation device, depending on loading states prevailing in the wing unit. ### Claim 3 (depends on 2) The wing unit according to claim 2 further comprising a control and regulation device associated with at least one of the at least two actuating members to change the surface geometry at the aerodynamically active surface depending on loading status prevailing in the wing unit. ### Claim 4 (depends on 3) The wing unit according to claim 3 further comprising a bending/torsion coupling associated with at least one of the at least two actuating members. ### Claim 5 (depends on 1) The wing unit according to claim 1, wherein the at least two actuating members are adapted in such a way that a bending/torsion coupling of the wing unit is changeable by a control and regulation device, depending on the loading states prevailing in the wing unit. ### Claim 6 (depends on 1) The wing unit according to claim 1, wherein at least one spar is arranged between the upper shell and the lower shell. ### Claim 7 (depends on 6) The wing unit according to claim 6, wherein the at least one spar is shear flexible in the region of at least one of the at least two actuating members. ### Claim 8 (depends on 1) The wing unit according to claim 1, wherein at least one rib is arranged between the upper shell and the lower shell. ### Claim 9 (depends on 8) The wing unit according to claim 8, wherein the at least one rib is transverse force flexible in the region of at least one of the at least two actuating members. ### Claim 10 (depends on 1) The wing unit according to claim 1, wherein a dimension of the at least two actuating members is variable by a control and regulation device. ### Claim 11 (depends on 1) The wing unit according to claim 1, further comprising two ribs and a spar, wherein the two ribs are arranged between the upper shell and the lower shell, wherein the spar is arranged between the upper shell and the lower shell, wherein between the two ribs at least one of the at least two actuating members is arranged, and wherein at least one of the at least two actuating members is arranged substantially in parallel to the spar. ### Claim 12 (depends on 1) The wing unit according to claim 1, further comprising: a rib, wherein the rib is arranged between the upper shell and the lower shell, wherein that at least one actuating member is arranged substantially parallel to the rib in the region between the upper shell and the lower shell. ### Claim 13 (depends on 1) The wing unit according to claim 1, further comprising: at least two actuating members; and at least one rib; wherein the rib is arranged between the upper shell and the lower shell; and wherein the at least two actuating members are arranged crosswise to each other substantially in parallel to the at least one rib for forming a tension shear field. ### Claim 14 (depends on 1) The wing unit according to claim 1, wherein at least one of the at least two actuating members is rod-shaped. ### Claim 15 (depends on 1) The wing unit according to claim 1, wherein at least one of the at least two actuating members comprise at least one actuator, wherein the at least one actuator is adapted to vary a length of the at least one actuating member. ### Claim 16 (depends on 15) The wing unit according to claim 15, wherein the at least one actuator is formed with at least one piezoelectric element selected from the group consisting of particular piezoelectric stacks, piezoelectric plates, and piezoelectric filaments with at least one shape memory element, wherein the at least one piezoelectric element is adapted in such a way that it is operateable through control signals generated by a control and regulation device. ### Claim 17 (depends on 16) The wing unit according to claim 16, wherein the control signals for the at least one actuator are electrical voltages or electrical currents, or both electrical voltages and electrical currents. ### Claim 18 (depends on 1) The wing unit according to claim 1, wherein at least one of the at least two actuating members comprises at least one sensor, wherein the at least one sensor is adapted to detect loading states in the at least one actuating member or a length variation of the at least one actuating member, or both loading states in the at least one actuating member and a length variation of the at least one actuating member. ### Claim 19 (depends on 1) The wing unit according to claim 1, further comprising at least one sensor, wherein the at least one sensor is arranged in a region of the upper shell, the lower shell, at least one of the at least two spars, as well as at least one of the at least two ribs, wherein the at least one sensor is adapted to detect at least one loading state or at least one length variation, or both at least one loading state and at least one length variation in the region of the upper shell, the lower shell, or at least one of the at least two spars, as well as of at least one of the at least two ribs. ### Claim 20 (depends on 19) The wing unit according to claim 19, wherein the at least one sensor is formed with at least one piezoelectric element, in particular piezoelectric stacks, piezoelectric plates, piezoelectric filaments, or strain gauges. ### Claim 21 A wing unit, in particular a spar box, for forming aerodynamically active surfaces of an aircraft, in particular airfoils, horizontal tail units, or rudder units of a plane, comprising: an upper shell and a lower shell, the upper shell and the lower shell forming the aerodynamically active surface; a first rib having a lower rib foot and an upper rib foot; a second rib having a lower rib foot and an upper rib foot; and at least two actuating members; wherein the at least two actuating members are arranged in a region between the upper shell and the lower shell for modifying the surface geometry of the aerodynamically active surface or the mechanical properties of the wing unit or both the surface geometry of the aerodynamically active surface and the mechanical properties of the wing unit; wherein the at least two actuating members are arranged crosswise; wherein one of the at least two actuating members is arranged between the lower rib foot of the first rib and the upper rib foot of the second rib; and wherein the other one of the at least two actuating members is arranged between the upper rib foot of the first rib and the lower rib foot of the second rib. ### Claim 22 (depends on 21) The wing unit according to claim 21, wherein the at least two actuating members are adapted in such a way that a surface geometry of an aerodynamically active surface is changeable by using a control and regulation device, depending on loading states prevailing in the wing unit. ### Claim 23 (depends on 22) The wing unit according to claim 22 further comprising a control and regulation device associated with at least one of the at least two actuating members to change the surface geometry at the aerodynamically active surface depending on loading status prevailing in the wing unit. ### Claim 24 (depends on 23) The wing unit according to claim 23 further comprising a bending/torsion coupling associated with at least one of the at least two actuating members. ### Claim 25 (depends on 21) The wing unit according to claim 21, wherein the at least two actuating members are adapted in such a way that a bending/torsion coupling of the wing unit is changeable by a control and regulation device, depending on the loading states prevailing in the wing unit. ### Claim 26 (depends on 21) The wing unit according to claim 21, wherein at least one spar is arranged between the upper shell and the lower shell. ### Claim 27 (depends on 26) The wing unit according to claim 26, wherein the at least one spar is shear flexible in the region of at least one of the at least two actuating members. ### Claim 28 (depends on 21) The wing unit according to claim 21, wherein at least one rib is arranged between the upper shell and the lower shell. ### Claim 29 (depends on 28) The wing unit according to claim 28, wherein the at least one rib is transverse force flexible in the region of at least one of the at least two actuating members. ### Claim 30 (depends on 21) The wing unit according to claim 21, wherein a dimension of the at least two actuating members is variable by a control and regulation device. ### Claim 31 (depends on 21) The wing unit according to claim 21, further comprising two ribs and a spar, wherein the two ribs are arranged between the upper shell and the lower shell, wherein the spar is arranged between the upper shell and the lower shell, wherein between the two ribs at least one of the at least two actuating members is arranged, and wherein at least one of the at least two actuating members is arranged substantially in parallel to the spar. ### Claim 32 (depends on 21) The wing unit according to claim 21, wherein at least one of the first or second ribs is arranged between the upper shell and the lower shell, and wherein at least one of the at least two actuating members is arranged substantially parallel to the at least one rib in the region between the upper shell and the lower shell. ### Claim 33 (depends on 21) The wing unit according to claim 21, wherein at least one of the first or second ribs is arranged between the upper shell and the lower shell, and wherein the at least two actuating members are arranged crosswise to each other substantially in parallel to the at least one rib for forming a tension shear field. ### Claim 34 (depends on 21) The wing unit according to claim 21, wherein at least one of the at least two actuating members is rod-shaped. ### Claim 35 (depends on 21) The wing unit according to claim 21, wherein at least one of the at least two actuating members comprise at least one actuator, wherein the at least one actuator is adapted to vary a length of the at least one actuating member. ### Claim 36 (depends on 35) The wing unit according to claim 35, wherein the at least one actuator is formed with at least one piezoelectric element selected from the group consisting of particular piezoelectric stacks, piezoelectric plates, and piezoelectric filaments with at least one shape memory element, wherein the at least one piezoelectric element is adapted in such a way that it is operateable through control signals generated by a control and regulation device. ### Claim 37 (depends on 36) The wing unit according to claim 36, wherein the control signals for the at least one actuator are electrical voltages or electrical currents, or both electrical voltages and electrical currents. ### Claim 38 (depends on 21) The wing unit according to claim 21, wherein at least one of the at least two actuating members comprises at least one sensor, wherein the at least one sensor is adapted to detect loading states in the at least one actuating member or a length variation of the at least one actuating member, or both loading states in the at least one actuating member and a length variation of the at least one actuating member.