CN-114074754-B - CFRP fuselage frame secured to vertical tail

Abstract

The present application relates to a CFRP fuselage frame secured to a vertical tail. A securing assembly for securing a vertical tail assembly to an aircraft includes a first tab member secured to the vertical tail assembly. The securing assembly further includes a first U-shaped joint member. The first U-shaped joint member includes a first end of the first U-shaped joint member engaged to the first lug member. The second end of the first U-shaped joint member is secured to a first fuselage frame constructed of composite material with a first fastener that extends through the second end and the first fuselage frame in a first direction transverse to the first fuselage frame.

Inventors

• Paul Depp Bossel
• Feiyan T. PAM

Assignees

• 波音公司
• 波音公司

Dates

Publication Date

20260421

Application Date

20210729

Priority Date

20200812

Claims (18)

1. 1. A securing assembly for securing a vertical tail assembly to an aircraft, wherein the securing assembly comprises: a first lug member fixed to the vertical tail assembly, and A first U-shaped joint member, wherein: the first end of the first U-shaped joint member being joined to the first lug member, and The second end of the first U-joint member is secured to a first fuselage frame composed of composite material with a first fastener that extends through the second end of the first U-joint member and the first fuselage frame in a first direction transverse to the first fuselage frame; Wherein the composite comprises a five ply construction comprising: one ply having a nonlinear fiber architecture; two plies having a first linear fiber configuration extending over a range of angles including plus or minus five degrees angularly displaced by plus thirty degrees from a radial axis of the non-linear fiber configuration, and Two other plies having a second linear fiber configuration extending over an angular range comprising plus or minus five degrees angularly displaced by minus thirty degrees from a radial axis of the nonlinear fiber configuration.
2. 2. The securing assembly of claim 1, wherein: The first U-shaped joint member having a first crotch portion and a second crotch portion, the first crotch portion of the first U-shaped joint member defining a first opening at the first end of the first U-shaped joint member and the second crotch portion of the first U-shaped joint member defining a second opening at the first end of the first U-shaped joint member, and The first lug member is positioned between the first bifurcated portion of the first U-shaped joint member and the second bifurcated portion of the first U-shaped joint member.
3. 3. The securing assembly of claim 2, further comprising a first pin extending through the first opening of the first prong of the first U-shaped joint member, the second opening of the second prong of the first U-shaped joint member, and through a first tab opening, such that the first pin extends in the first direction transverse to the first fuselage frame, the first tab opening being defined by and through the first tab member for engaging the first U-shaped joint member to the first tab member.
4. 4. The securing assembly of claim 2, wherein the second end of the first U-joint member includes a first securing flange extending along a front side of the first fuselage frame, wherein the first fastener extends through the first securing flange and the first fuselage frame.
5. 5. The securing assembly of claim 1, further comprising a first pair of U-joint members including the first and second U-joint members secured to the first fuselage frame, wherein the first and second U-joint members are positioned spaced apart from each other in a second direction along the first fuselage frame, wherein: the first U-shaped joint member has a first bifurcation, the first bifurcation of the first U-shaped joint member defining a first opening at the first end of the first U-shaped joint member, and the second U-shaped joint member has a first bifurcation, the first bifurcation of the second U-shaped joint member defining a first opening at the first end of the second U-shaped joint member; the first U-shaped joint member having a second split, the second split of the first U-shaped joint member defining a second opening at the first end of the first U-shaped joint member, and the second U-shaped joint member having a second split, the second split of the second U-shaped joint member defining a second opening at the first end of the second U-shaped joint member; the first lug member being positioned between the first bifurcated portion of the first one of the first pair of U-shaped joint members and the second bifurcated portion of the first U-shaped joint member, and A second lug member is positioned between the first bifurcation of the second clevis member and the second bifurcation of the second clevis member of the first pair of clevis members.
6. 6. The securing assembly of claim 5, wherein: a first pin extending through the first opening of the first crotch of the first U-joint member, the second opening of the second crotch of the first U-joint member, and through a first lobe opening defined by and passing through the first lobe member such that the first pin extends in the first direction transverse to the first fuselage frame, and A second pin extends through the first opening of the first prong of the second U-shaped joint member, the second opening of the second prong of the second U-shaped joint member, and through a second tab opening defined by and through the second tab member such that the second pin extends in the first direction transverse to the first fuselage frame.
7. 7. The securing assembly of claim 5, wherein: The second end of the first U-shaped joint member includes a first securing flange and the second end of the second U-shaped joint member includes a second securing flange; The first securing flange extending along a front side of the first fuselage frame, wherein the first fastener extends through the first securing flange and the first fuselage frame in the first direction transverse to the first fuselage frame, and The second securing flange extends along the front side of the first fuselage frame, wherein a second fastener extends through the second securing flange and the first fuselage frame in the first direction transverse to the first fuselage frame.
8. 8. The securing assembly of claim 1, further comprising: a third U-joint member secured to a second fuselage frame constructed of composite material, the third U-joint member being spaced apart from the first U-joint member along the length of the aircraft, the third U-joint member having a first bifurcation and a second bifurcation, the first bifurcation of the third U-joint member defining a first opening at a first end of the third U-joint member, the second bifurcation of the third U-joint member defining a second opening at the first end of the third U-joint member, and A third lug member is positioned between the first bifurcated portion of the third U-shaped joint member and the second bifurcated portion of the third U-shaped joint member.
9. 9. The securing assembly of claim 8, further comprising a third pin extending through the first opening of the first prong of the third U-shaped joint member, the second opening of the second prong of the third U-shaped joint member, and through a third tab opening, such that the third pin extends in a third direction along the second fuselage frame, the third tab opening being defined by and through the third tab member for engaging the third U-shaped joint member to the third tab member.
10. 10. The securing assembly of claim 8, wherein the second end of the third U-joint member includes a third securing flange extending along a front side of the second fuselage frame, wherein a third fastener extends through the third securing flange and the second fuselage frame in a fourth direction transverse to the second fuselage frame.
11. 11. The securing assembly of claim 8, further comprising a second pair of U-joint members including the third and fourth U-joint members secured to the second fuselage frame, positioned spaced apart from one another in a third direction along the second fuselage frame.
12. 12. The securing assembly of claim 11, wherein: The third U-shaped joint member has a first bifurcation, the first bifurcation of the third U-shaped joint member defining a first opening at the first end of the third U-shaped joint member, and the fourth U-shaped joint member has a first bifurcation, the first bifurcation of the fourth U-shaped joint member defining a first opening at the first end of the fourth U-shaped joint member; The third U-shaped joint member having a second bifurcated portion, the second bifurcated portion of the third U-shaped joint member defining a second opening at the first end of the third U-shaped joint member, and the fourth U-shaped joint member having a second bifurcated portion, the second bifurcated portion of the fourth U-shaped joint member defining a second opening at the first end of the fourth U-shaped joint member; The third lug member being positioned between the first bifurcated portion of the third U-shaped joint member and the second bifurcated portion of the third U-shaped joint member, and A fourth lug member is positioned between the first bifurcated portion of the fourth U-shaped joint member and the second bifurcated portion of the fourth U-shaped joint member.
13. 13. The securing assembly of claim 12, wherein: A third pin extending through the first opening of the first crotch of the third U-joint member, the second opening of the second crotch of the third U-joint member, and through a third lobe opening defined by and passing through the third lobe member such that the third pin extends in the third direction along the second fuselage frame, and A fourth pin extends through the first opening of the first prong of the fourth U-shaped joint member, the second opening of the second prong of the fourth U-shaped joint member, and through a fourth lobe opening defined by and through the fourth lobe member such that the fourth pin extends in the third direction along the second fuselage frame.
14. 14. The securing assembly of claim 12, wherein: The second end of the third U-shaped joint member includes a third securing flange and the second end of the fourth U-shaped joint member includes a fourth securing flange; the third securing flange extending along a front side of the second fuselage frame, wherein a third fastener extends through the third securing flange and the second fuselage frame in a fourth direction transverse to the second fuselage frame, and The fourth securing flange extends along the front side of the second fuselage frame, and a fourth fastener extends through the fourth securing flange and the second fuselage frame in the fourth direction transverse to the second fuselage frame.
15. 15. A method for securing a vertical tail assembly to an aircraft, wherein the method comprises: Securing a first lug member to a first end of a first U-joint member, the first lug member secured to the vertical tail assembly, and Securing a second end of the first U-joint member to a first fuselage frame composed of composite material with a first fastener extending through the second end of the first U-joint member and the first fuselage frame in a first direction transverse to the first fuselage frame; wherein the composite comprises a plurality of sets of five ply construction comprising: one ply having a nonlinear fiber architecture; two plies having a first linear fiber configuration extending over a range of angles including plus or minus five degrees angularly displaced by plus thirty degrees from a radial axis of the non-linear fiber configuration, and Two other plies having a second linear fiber configuration extending over an angular range comprising plus or minus five degrees angularly displaced by minus thirty degrees from a radial axis of the nonlinear fiber configuration.
16. 16. The method of claim 15, wherein securing the first lug member to the first end of the first U-joint member comprises: The first U-shaped joint member has a first bifurcated portion and a second bifurcated portion, the first bifurcated portion of the first U-shaped joint member defining a first opening at the first end of the first U-shaped joint member and the second bifurcated portion of the first U-shaped joint member defining a second opening at the first end of the first U-shaped joint member; The first tab member being positioned between the first bifurcated portion of the first U-shaped joint member and the second bifurcated portion of the first U-shaped joint member and defining a first tab opening therethrough, and A first pin extends through the first opening of the first prong of the first U-shaped joint member, the second opening of the second prong of the first U-shaped joint member, and through the first tab opening of the first tab member such that the first pin extends in the first direction transverse to the first fuselage frame.
17. 17. The method of claim 16, further comprising: A first pair of U-joint members comprising the first U-joint member and a second U-joint member, wherein the second U-joint member is secured to the first fuselage frame, spaced apart from the first U-joint member in a second direction along the first fuselage frame; A second pin extending through a first opening of a first prong of a first end of the second U-shaped joint member, a second opening of a second prong of the first end of the second U-shaped joint member, and through a second tab opening of a second tab member such that the second pin extends in the first direction transverse to the first fuselage frame, and A second fastener extends through the second portion of the second U-joint member and the first fuselage frame in the first direction transverse to the first fuselage frame, securing the second U-joint member to the first fuselage frame.
18. 18. The method of claim 16, further comprising: securing a third lug member to a first end of a third U-joint member, wherein a third securing flange of a second end of the third U-joint member is secured to a second fuselage frame spaced apart from the first fuselage frame, comprising: The third U-shaped joint member having a first bifurcation and a second bifurcation, the first bifurcation of the third U-shaped joint member defining a first opening at the first end of the third U-shaped joint member and the second bifurcation of the third U-shaped joint member defining a second opening at the first end of the third U-shaped joint member; The third lobe member being positioned between the first bifurcation of the third U-shaped joint member and the second bifurcation of the third U-shaped joint member and defining a third lobe opening therethrough; A third pin extends through the first opening of the first prong of the third U-shaped joint member, the second opening of the second prong of the third U-shaped joint member, and through the third tab opening of the third tab member such that the third pin extends in a third direction along the second fuselage frame; A third fastener extends through the third securing flange of the second end of the third U-joint member and the second fuselage frame in a fourth direction transverse to the second fuselage frame; A second pair of U-joint members including the third U-joint member and a fourth U-joint member, wherein the fourth U-joint member is secured to the second fuselage frame, spaced apart from the third U-joint member in the third direction along the second fuselage frame; The fourth U-shaped joint member having a first furcation portion and a second furcation portion, the first furcation portion of the fourth U-shaped joint member defining a first opening at the first end of the fourth U-shaped joint member and the second furcation portion of the fourth U-shaped joint member defining a second opening at the first end of the fourth U-shaped joint member; A fourth lug member is positioned between the first bifurcated portion of the fourth U-shaped joint member and the second bifurcated portion of the fourth U-shaped joint member and defines a fourth lug opening therethrough; A fourth pin extending through the first opening of the first prong of the fourth U-shaped joint member, the second opening of the second prong of the fourth U-shaped joint member, and through the fourth tab opening of the fourth tab member such that the fourth pin extends in the third direction along the second fuselage frame, and A fourth fastener extends through the fourth securing flange of the second end of the fourth U-joint member and the second fuselage frame in a fourth direction transverse to the second fuselage frame.

Description

CFRP fuselage frame secured to vertical tail Technical Field The present disclosure relates to securing a vertical wing assembly of an aerospace vehicle to an aerospace vehicle, and more particularly to securing a vertical wing assembly to a fuselage frame of an aircraft. Background There are problems with corrosion occurring with respect to aluminum fuselage frames having composite fiber reinforced polymer ("CFRP") skins attached to aircraft. Further, for example, in the case of constructing an aircraft using an aluminum frame having a CFRP skin, fatigue problems occur due to material differences and their different thermal expansion effects. For example, aluminum has a coefficient of thermal expansion greater than that of CFRP. Aluminum undergoes shrinkage in the cold state and expands in the hot state relative to CFRP material (which is thermally neutral in comparison). Because the frames and skin structures use different materials, these structures experience compressive and tensile forces as the aircraft experiences different temperatures when the aircraft is in operation. Also, with respect to production, metal frames such as aluminum airframe frames require deburring after drilling to prevent fatigue cracking, joint surface sealing to prevent corrosion prior to installation, and impose the need for extended time at production. Accordingly, there is a need to reduce the cost of aircraft production associated with corrosion protection measures taken with different materials such as aluminum frames and CFRP aircraft skin, and to reduce thermal fatigue due to thermal expansion effects on interconnect structures in the aircraft that are composed of different materials each having a different coefficient of thermal expansion. Further, it is necessary to shorten the production time relative to the time required for production with a metal frame. Disclosure of Invention One embodiment includes a securing assembly for securing a vertical wing assembly to an aircraft, the securing assembly including a first tab member secured to the vertical wing assembly. The securing assembly includes a first U-shaped joint member (clevis member). The first end of the first U-shaped joint member is joined to the first lug member. The second end of the first U-shaped joint member is secured to a first fuselage frame constructed of composite material with a first fastener that extends through the second end and the first fuselage frame in a first direction transverse to the first fuselage frame. One embodiment includes a method for securing a vertical wing assembly to an aircraft that includes securing a first tab member to a first end of a first U-shaped joint member, the first tab member secured to the vertical wing assembly. The method further includes securing the second end of the first U-shaped joint member to a first fuselage frame constructed of a composite material with a first fastener that extends through the second end of the first U-shaped joint member and the first fuselage frame in a first direction transverse to the first fuselage frame. The features, functions, and advantages that have been discussed can be achieved independently in various embodiments or may be combined in yet other embodiments further details of which can be seen with reference to the following description and drawings. Drawings FIG. 1 is a perspective view of an aircraft; FIG. 2 is a partial perspective view of a composite fuselage frame secured to a portion of a vertical tail assembly of an aircraft in a direction toward the front of the aircraft in FIG. 1, with the composite fuselage skin not shown; FIG. 3 is a partial perspective view of a composite fuselage frame secured to a portion of the vertical tail assembly of the aircraft of FIG. 2 in a direction toward the rear of the aircraft of FIG. 1; FIG. 4 is a partial end elevation view of a composite fuselage frame secured to a portion of the vertical tail assembly of the aircraft of FIG. 2 in a direction toward the front of the aircraft of FIG. 1; FIG. 5 is a partial top plan view of the two composite fuselage frames of FIG. 2, wherein each fuselage frame has two U-shaped joint members positioned spaced apart from each other along each of the two composite fuselage frames without any vertical tail assemblies or lug members; FIG. 6 is a cross-sectional view along line 6-6 shown in FIG. 5, including a tab member secured to a U-shaped joint member extending through the composite fuselage skin; FIG. 7 is a cross-sectional view along line 7-7 shown in FIG. 5, including a tab member secured to a U-shaped joint member; FIG. 8 is a schematic illustration of fiber placement within the composite of the fuselage frame as representatively seen at the location of the circle identified by reference to FIG. 8 in FIG. 4; FIG. 9 is a schematic cross-sectional view of the fuselage and vertical tail assembly of the aircraft of FIG. 1, showing reaction forces experienced by a securing assembly securing a fu