CFRP fuselage frame fixed 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 lug 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 joined to the first lug member. A second end of the first U-shaped joint member is secured to a first fuselage frame comprised of a composite material with first fasteners extending through the second end and the first fuselage frame in a first direction transverse to the first fuselage frame.

Description

Technical Field

[0001] This disclosure relates to securing a vertical wing assembly to an aerospace vehicle, and more specifically, to securing a vertical wing assembly to the fuselage frame of an aircraft. Background Technology

[0002] There are issues with corrosion in aluminum fuselage frames with composite fiber-reinforced polymer (“CFRP”) skins attached to the aircraft. Furthermore, fatigue problems arise, for example, when constructing an aircraft using an aluminum frame with CFRP skin, due to material differences and their varying thermal expansion effects. For instance, aluminum has a larger coefficient of thermal expansion than CFRP. Aluminum contracts when cold and expands relative to CFRP (which is thermally neutral) when hot. Because the frame and skin structures use different materials, these structures experience compressive and tensile forces as the aircraft operates and experiences varying temperatures. Moreover, regarding production, metal frames such as aluminum fuselage frames require deburring after drilling to prevent fatigue cracking, surface sealing before installation to prevent corrosion, and extended production time requirements.

[0003] Therefore, it is necessary to reduce the costs associated with corrosion protection measures using different materials such as aluminum frames and CFRP aircraft skins, and to reduce thermal fatigue caused by thermal expansion effects on interconnected structures in the aircraft composed of different materials with different coefficients of thermal expansion. Furthermore, it is necessary to shorten production time compared to the time required for production using metal frames. Summary of the Invention

[0004] One embodiment includes a securing assembly for securing a vertical wing assembly to an aircraft, the securing assembly including a first lug member secured to the vertical wing assembly. The securing assembly includes a first clevis member. A first end of the first clevis member engages with the first lug member. A second end of the first clevis member is secured to a first fuselage frame made of composite material using a first fastener that extends through the second end and the first fuselage frame in a first direction transverse to the first fuselage frame.

[0005] One embodiment includes a method for securing a vertical wing assembly to an aircraft, the method comprising: securing a first lug member to a first end of a first U-shaped connector member, the first lug member being secured to the vertical wing assembly. The method further comprises: securing a second end of the first U-shaped connector member to a first fuselage frame made of composite material using a first fastener, the first fastener extending in a first direction transverse to the first fuselage frame through the second end of the first U-shaped connector member and the first fuselage frame.

[0006] The features, functions, and advantages already discussed can be implemented independently in various embodiments or in combination with other embodiments, and further details can be understood with reference to the following description and figures. Attached Figure Description

[0007] Figure 1 It is a 3D diagram of an airplane;

[0008] Figure 2 The composite fuselage frame, which is fixed to the vertical tail assembly of the aircraft, faces... Figure 1 A partial perspective view of the front of the aircraft, where the composite fuselage skin is not shown;

[0009] Figure 3 It is fixed to Figure 2 The composite fuselage frame of the aircraft's vertical tail assembly is oriented towards Figure 1 A partial 3D view of the rear of the aircraft;

[0010] Figure 4 It is fixed to Figure 2 The composite fuselage frame of the aircraft's vertical tail assembly is oriented towards Figure 1 A partial end front view of the front section of the aircraft in the direction of its forward part;

[0011] Figure 5 yes Figure 2 A partial top plan view of the two composite fuselage frames, 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 assembly or lug member.

[0012] Figure 6 It is along Figure 5 The cross-sectional view shown in line 6-6 includes a lug member fixed to a U-shaped joint member extending through the composite fuselage skin;

[0013] Figure 7 It is along Figure 5 The cross-sectional view of line 7-7 shown includes the lug member fixed to the U-shaped joint member;

[0014] Figure 8 Is it representative of the situation caused by Figure 4 See also Figure 8 A schematic diagram showing the fiber arrangement within the composite material of the fuselage frame, as seen at the location of the marked circle;

[0015] Figure 9 yes Figure 1A schematic cross-sectional view of the aircraft's fuselage and vertical tail assembly shows the reaction forces experienced by the fixing components that secure the fuselage frame to the aircraft's vertical tail assembly using lateral forces applied to the vertical tail assembly; and

[0016] Figure 10 This is a flowchart of a method for securing a vertical tail assembly to an aircraft. Detailed Implementation

[0017] refer to Figure 1 The aircraft 10 includes a fuselage assembly 12, a wing assembly 14, and a vertical tail assembly 16. During the manufacture of the aircraft 10, the vertical tail assembly 16 includes a support structure (not shown) consisting of spars and ribs fixed to the skin 18 of the aircraft 10. The vertical tail assembly 16 is further fixed to the fuselage assembly 12 of the aircraft 10 upon connection to the fuselage frame. As previously discussed, in constructing the aircraft 10, the manufacturer has utilized metals such as aluminum to construct the fuselage frame. The metal fuselage frame, along with materials such as aluminum... Figures 2 to 4 The fuselage frames 20a, 20b, 20c, and 20d shown in the image have similar structures. The number of fuselage frames with the vertical tail assembly 16 fixed thereto can vary depending on the design of the specific aircraft 10.

[0018] As previously discussed regarding the metal fuselage frame, in this disclosure, defect-avoiding CFRP material is used instead of metal for the construction of the first to fourth fuselage frames 20a-20d. When using CFRP to construct the fuselage frame, corrosion prevention measures relative to the metal fuselage frame are no longer required. Furthermore, for the CFRP-constructed fuselage frame, material fatigue-related inspections of the first to fourth fuselage frames 20a-20d and the fuselage skin 22 are no longer necessary, as the first to fourth fuselage frames 20a-20d and the skin 18 of the aircraft 10 are all constructed of similar CFRP materials, resulting in similar coefficients of thermal expansion characteristics for the first to fourth fuselage frames 20a-20d and the skin 18. Moreover, since the forging sequence delay is eliminated compared to the manufacturing of the metal fuselage frame, which is removed from the manufacturing schedule, the extended manufacturing time of the aircraft 10 is shortened.

[0019] In this embodiment, these disadvantages are overcome by utilizing the first to fourth fuselage frames 20a-20d, and the fuselage skin 22 is now constructed of CFRP material. With the benefits provided by utilizing the CFRP material used for fuselage frames such as 20a-20d, the securing assembly 24 discussed herein is required for securing the vertical tail assembly 16 to the aircraft 10 via the first to fourth fuselage frames 20a-20d of the fuselage assembly 12. The securing assembly 24 provides the desired transfer of shear loads from the vertical tail assembly 16 to the first to fourth fuselage assemblies 20a-20d of this embodiment, which are constructed of CFRP material.

[0020] The vertical tail assembly 16 is secured to the metal fuselage frame via bolted connections in a generally vertical direction relative to the vertical tail assembly 16 and the metal fuselage frame. However, relative to the fuselage frame currently constructed of CFRP material, this securing configuration does not provide optimal shear resistance relative to the shear loads transferred from the vertical tail assembly 16 to the first to fourth fuselage frames 20a-20d (in this embodiment) during aircraft operation. Therefore, as in Figures 2 to 7 As seen in and described herein, the fixing assembly 24 provides optimal fixation of the vertical tail assembly 16 to the first to fourth fuselage frames 20a-20d (in this embodiment) constructed of CFRP to resist shear loads originating from the vertical tail assembly 16.

[0021] In this embodiment, of the four first to fourth fuselage frames 20a-20d to which the vertical tail assembly 16 is secured, each of the first to fourth fuselage frames 20a-20d has a pair of fixing components 24 spaced apart on each of the first to fourth fuselage frames 20a-20d for securing the vertical tail assembly 16 to each of the first to fourth fuselage frames 20a-20d. (See reference...) Figure 2 I saw a three-dimensional view of the starboard side of aircraft 10, consisting of the first to fourth fuselage frames 20a-20d, and... Figure 3 The image shows a perspective view 28 of the port side of the aircraft 10 with the first to fourth fuselage frames 20a-20d. Both views provide a view of each pair of fixing components 24 relative to each of the first to fourth fuselage frames 20a-20d. The first pair of fixing components 24 (30) is positioned between the first fuselage frames 20a, the second pair of fixing components 24 (32) is positioned on the second fuselage frame 20b, the third pair of fixing components 24 (34) is positioned on the third fuselage frame 20c, and the fourth pair of fixing components 24 (36) is positioned on the fourth fuselage frame 20d.

[0022] Such as in Figure 2 and Figure 3As seen in the diagram, in this embodiment, the first pair of 30 fixing components 24 and the fourth pair of 36 fixing components 24 are configured identically and are optimal in resisting the shear forces transferred from the vertical tail assembly 16 that have caused shear loads in the forward direction 38 and the rearward direction 40. Conversely, in this embodiment, the second pair of 32 fixing components 24 and the third pair of 34 fixing components 24 are configured identically and are optimal in resisting the shear loads transferred from the vertical tail assembly 16 that have caused shear loads oriented in the starboard direction 42 or the port direction 44. The difference between the first pair of 30 fixing components 24 and the fourth pair of 36 fixing components 24, and the difference between the second pair of 32 fixing components 24 and the third pair of 34 fixing components 24, lies in the orientation of the pins used to fix the components 24 to the lug members under discussion. In the first pair of 30 fixing components 24 and the fourth pair of 36 fixing components 24, for each fixing component 24, the pins are positioned to extend along the first fuselage frame 20a and the fourth fuselage frame 20d, respectively. In the second pair of 32 fixing components 24 and the third pair of 34 fixing components 24, for each fixing component 24, the pin is positioned to extend laterally to the second fuselage frame 20b and the third fuselage frame 20c, respectively.

[0023] As in Figure 2 and Figure 3As seen in the diagram, in this embodiment, the first pair of 30 fixing components 24 are positioned on the first fuselage frame 20a, and the second pair of 32 fixing components 24 are positioned on the second fuselage frame 20b. It should be understood that the position of the first fuselage frame 20a carrying the first pair of 30 fixing components 24 is not limited to the rearmost position 48 of the first to fourth fuselage frames 20a-20d fixed to the vertical tail assembly 16, and the position of the fourth fuselage frame 20d carrying the fourth pair of 36 fixing components 24 is not limited to the foremost position 50 of the first to fourth fuselage frames 20a-20d fixed to the vertical tail assembly 16. Similarly, the second pair of 32 fixing components 24 is not limited to being positioned on the second fuselage frame 20b between the first pair of 30 fixing components 24 and the fourth pair of 36 fixing components 24, with the first pair of 30 fixing components 24 and the fourth pair of 36 fixing components 24 respectively positioned on the first fuselage frame 20a and the fourth fuselage frame 20d. Similarly, the third pair of 34 fixing components 24 is not limited to being positioned on the third fuselage frame 20c between the first pair of 30 fixing components 24 and the fourth pair of 36 fixing components 24, which are respectively positioned on the first fuselage frame 20a and the fourth fuselage frame 20d. In this embodiment described herein, the first pair of 30 fixing components 24 and the fourth pair of 36 fixing components 24 are positioned on the first fuselage frame 20a and the fourth fuselage frame 20d, which are respectively positioned at the rearmost position 48 and the foremost position 50 of the aircraft 10 used for fixing to the vertical tail assembly 16. The second pair of 32 fixing components 24 and the third pair of 34 fixing components 24 are respectively positioned on the second fuselage frame 20b and the third fuselage frame 20c, which are positioned between the first fuselage frame 20a and the fourth fuselage frame 20d used for fixing the vertical tail assembly 16.

[0024] refer to Figures 2 to 7 In this embodiment, the fixing assembly 24 that secures the vertical tail assembly 16 to the aircraft 10 by fixing it to the first to fourth fuselage frames 20a-20d includes a first lug member 46, which is fixed (not shown) to the vertical tail assembly 16, such as by bolting (not shown) the first lug member 46 to a frame consisting of spars and ribs (not shown) of the vertical tail assembly 16. Figure 6As seen in the diagram and discussed in further detail, a first U-shaped connector member 52 positioned on the first fuselage frame 20a has a first end 54 that engages with a first lug member 46. The first U-shaped connector member 52 further includes a second end 56 secured to the first fuselage frame 20a, which is constructed of CFRP composite material. As will be discussed further, a first fastener 58 extends through the second end 56 and the first fuselage frame 20a in a first direction 60 transverse to the first fuselage frame 20a. In this embodiment, the first fastener 58 includes a bolt and nut assembly.

[0025] As in Figure 6 As seen in the image, the first U-shaped connector member 52 has a first fork 62 and a second fork 66. The first fork 62 defines a first opening 64 at a first end 54 of the first U-shaped connector member 52, and the second fork 66 defines a second opening 68 at the first end 54 of the first U-shaped connector member 52. A first lug member 46 is positioned between the first fork 62 and the second fork 66 of the first U-shaped connector member 52. A first pin 70 extends through the first opening 64 of the first fork 62, the second opening 68 of the second fork 66, and through the first lug opening 72, such that the first pin 70 extends in a first direction 60 transverse to the first fuselage frame 20a. The first lug opening 72 is defined by and passes through the first lug member 46 for engaging the first U-shaped connector member 52 to the first lug member 46. The second end 56 of the first U-shaped connector member 52 includes a first fixing flange 74 that extends along the front side 76 of the first fuselage frame 20a, wherein a first fastener 58 extends through the first fixing flange 74 and the first fuselage frame 20a. When positioned in a first direction 60 transverse to the first fuselage frame 20a, the first fastener 58 (as in...) Figure 4 and Figure 6 When viewed in the image, the first U-shaped joint member 52 is fixed to the first fuselage frame 20a constructed of CFRP to optimally secure the first fixing flange 74 to the first fuselage frame 20a, thereby optimally responding to the shear load received from the vertical tail assembly 16.

[0026] The first pair of 35 U-shaped joint components (as in) Figure 5(As seen in the image) includes a first U-shaped connector member 52 and a second U-shaped connector member 78 fixed to a first fuselage frame 20a, wherein the first U-shaped connector member 52 and the second U-shaped connector member 78 are positioned spaced apart from each other along a second direction 80 of the first fuselage frame 20a. The first U-shaped connector member 52 has a first fork 62 that defines a first opening 64 at a first end 54 of the first U-shaped connector member 52, and similar to the first end 54 of the first U-shaped connector member 52, the second U-shaped connector member 78 has a first fork 82 that defines a first opening 64 at a first end 89 of the second U-shaped connector member 78 (as seen in the image). Figure 4 The first opening 84 is defined at the location shown in the image. The first U-shaped connector member 52 has a second fork 66, which defines a second opening 68 at the first end 54 of the first U-shaped connector member 52, and is connected to the first end 54 of the first U-shaped connector member 52 (as seen in the image). Figure 6 Similar to what is seen in [the image], the second U-shaped connector member 78 has a second fork 86, which is located at the first end 89 of the second U-shaped connector member 78 (as seen in [the image]). Figure 4 The second opening is limited at (as seen in) 88 (as seen in) Figure 5 (As seen in the video).

[0027] The first lug member 46 is positioned between the first bifurcation 62 and the second bifurcation 66 of the first U-shaped connector member 52 and the second U-shaped connector member 78 in the first pair 35. The second lug member 90 (as in Figure 4 (As seen in the image) The second U-shaped connector 78 is positioned in the first pair of 35 first U-shaped connector members 52 and second U-shaped connector members 78. Figure 5 Between the first fork 82 and the second fork 86. The first pin 70 (as in...) Figure 6 The first pin 70 extends through the first opening 64 of the first branch 62 of the first U-shaped connector member 52, the second opening 68 of the second branch 66 of the first U-shaped connector member 52, and through the first lug opening 72, such that the first pin 70 extends in a first direction 60 transverse to the first fuselage frame 20a. The first lug opening 72 is defined by and passes through the first lug member 46. The second pin (not shown) extends through the first opening 84 of the first branch 82 of the second U-shaped connector member 78, the second opening 88 of the second branch 86 of the second U-shaped connector member 78, and through the second lug opening (not shown), such that the second pin (not shown) extends in a first direction 60 transverse to the first fuselage frame 20a. The second lug opening is defined by the second lug member 90 (as seen in...). Figure 4 (As seen in the image) defines and passes through the second lug member 90. The second U-shaped connector member 78, which engages with the second lug member 90, is configured as follows: Figure 6 The configuration shown is similar to that of the first U-shaped connector member 52 fixed to the first lug member 46.

[0028] The second end 56 of the first U-shaped connector member 52 includes a first fixing flange 74 (as shown in...). Figure 6 (as seen in), and the second end 91 of the second U-shaped connector member 78 includes a second fixing flange 92 (as seen in). Figure 4 (As seen in the image). The first fixed flange 74 extends along the front side 76 of the first fuselage frame 20a, wherein... Figure 6 The first fastener 58 extends in a first direction 60 transverse to the first fuselage frame 20a, passing through the first fixing flange 74 and the first fuselage frame 20a. (As shown in...) Figure 6 Similar to the configuration seen in [the image], the second fixing flange 92 extends along the front side 76 of the first fuselage frame 20a, wherein the second fastener 94 (as seen in [the image]) is located in [the image]. Figure 4 (As seen in the image) it extends in a first direction 60 transverse to the first fuselage frame 20a, passing through the second fixed flange 92 and the first fuselage frame 20a.

[0029] In this embodiment, the third U-shaped connector member 96 (as in...) Figure 5 and Figure 7 (As seen in the image) Fixed to a second fuselage frame 20b constructed of composite CFRP, spaced apart from the first U-shaped joint member 52 along the length L of the aircraft 10, the third U-shaped joint member 96 has a first bifurcation 98 and a second bifurcation 104. The first bifurcation 98 defines a first opening 100 at a first end 102 of the third U-shaped joint member 96, and the second bifurcation 104 defines a second opening 106 at the first end 102 of the third U-shaped joint member 96. A third lug member 108 is positioned between the first bifurcation 98 and the second bifurcation 104 of the third U-shaped joint member 96. A third pin 110 extends through the first opening 100 of the first bifurcation 98, the second opening 106 of the second bifurcation 104, and through the third lug opening (not shown), such that the third pin 110 is positioned in a third direction 112 along the second fuselage frame 20b (as shown in the image). Figure 5 Extending from (as seen in), the third lug opening is defined by and passes through the third lug member 108 for engaging the third U-shaped connector member 96 to the third lug member 108. The second end 114 of the third U-shaped connector member 96 (as seen in) Figure 7(As seen in the image) includes a third fixing flange 116 that extends along the front side 118 of the second fuselage frame 20b, wherein a third fastener 120, such as a bolt and nut, extends through the third fixing flange 116 and the second fuselage frame 20b in a fourth direction 122 transverse to the second fuselage frame 20b.

[0030] This embodiment further includes a second pair of U-shaped connector members 37 (as in...) Figure 5 As seen in the image, the second pair of U-shaped connector members 37 includes a third U-shaped connector member 96 (as described above) and a fourth U-shaped connector member 124 fixed to a second fuselage frame 20b, also made of composite material CFRP. The third U-shaped connector member 96 and the fourth U-shaped connector member 124 are positioned spaced apart from each other along a third direction 112 of the second fuselage frame 20b. The third U-shaped connector member 96, as described above, has a first fork 98 defining a first opening 100 at a first end 102 of the third U-shaped connector member 96, and the fourth U-shaped connector member 124 has a first fork 126 defining a first opening 127 at a first end (not shown) of the fourth U-shaped connector member 124. The first end (not shown) of the fourth U-shaped connector member 124 and... Figure 7 The first end 102 of the third U-shaped connector member 96 shown is similar. As previously discussed and... Figure 5 The third U-shaped connector member 96 seen in the image has a second fork 104 that defines a second opening 106 at a first end 102 of the third U-shaped connector member 96. The fourth U-shaped connector member 124 has a second fork 128 that defines a second opening 130 at a first end (not shown) of the fourth U-shaped connector member 124.

[0031] The third lug member 108 is positioned between the first fork 98 and the second fork 104 of the third U-shaped connector member 96. The fourth lug member 132 (as in...) Figure 3 (See in) Location in Figure 5 Between the first fork 126 and the second fork 128 of the fourth U-shaped connector member 124. The third pin 110 (as in...) Figure 7 (As seen in the image) Extends through the first opening 100 of the first bifurcation 98 of the third U-shaped connector member 96, the second opening 106 of the second bifurcation 104 of the third U-shaped connector member 96, and through the third lug opening (not shown), such that the third pin 110 is positioned in a third direction 112 along the second fuselage frame 20b (as shown in the image). Figure 5 Extending from (as shown), the third lug opening is defined by and passes through the third lug member 108. However, it is related to the third pin 110 (as shown in...). Figure 7A fourth pin (not shown) similar to the one shown extends through... Figure 5 The first opening 127 of the first fork 126 of the fourth U-shaped connector member 124, the second opening 130 of the second fork 128 of the fourth U-shaped connector member 124, and the fourth lug opening (not shown) are passed through, such that the fourth pin (not shown) is in a third direction 112 (e.g., along the second fuselage frame 20b) in the third direction 112. Figure 5 The fourth lug opening extends from the fourth lug member 132 (as shown in the diagram), and the fourth lug opening is formed by the fourth lug member 132. Figure 3 (As shown) defines and passes through the fourth lug member 132.

[0032] The second end 114 of the third U-shaped connector component 96 (as in...) Figure 7 The fourth U-shaped connector member 124 (as seen in the image) includes a third fixing flange 116, and the second end of the fourth U-shaped connector member 124 (not shown) includes a fourth fixing flange 134 (as seen in the image). Figure 2 (As seen in the image). The second end (not shown) of the fourth U-shaped connector member 124 and the fourth fixing flange 134 are compared with the second end 114 and the third fixing flange 116 of the third U-shaped connector member 96 (as shown in the image). Figure 7 Similar to (as shown in the diagram). The third fixed flange 116 runs along the front side 118 of the second fuselage frame 20b (as shown in the diagram). Figure 2 and Figure 7 (As seen in) the extension, wherein the third fastener 120 extends in a fourth direction 122 transverse to the second fuselage frame 20b through the third fixing flange 116 and the second fuselage frame 20b. (As seen in) Figure 7 The fixing arrangement of the third fixing flange 116 seen in the image is similar, as is the fourth fixing flange 134 (as in...). Figure 2 (As seen in the image) extends along the front side 118 of the second fuselage frame 20b, where, however, it is related to... Figure 7 Similar to the third fastener 120, the fourth fastener (not shown) extends through the fourth fixing flange 134 and the second fuselage frame 20b in a fourth direction 122 transverse to the second fuselage frame 20b.

[0033] In this embodiment, the first to fourth fuselage frames 20a-20d are constructed of a composite material such as CFRP. In this embodiment, for each layer of composite material used in constructing the first to fourth fuselage frames 20a-20d, the composite material has a five-layer configuration; in this embodiment, a multi-layer composite material is used. (Reference) Figure 8One layer of the composite material has a nonlinear fiber configuration 136. In constructing each layer of the composite material, one layer of the composite material includes a nonlinear fiber configuration 136, which comprises twenty percent (20%) of the layer. In this embodiment, the nonlinear fiber configuration 136 extends in a bending direction having a radial axis R. Two layers of the composite material have a first linear fiber configuration 138, which extends within an angular range including a displacement of ±30 degrees from the radial axis R by an angle of ±5 degrees. The angular displacement is denoted as angle "A". Two layers of the composite material have a first linear fiber configuration 138, which comprises approximately forty percent (40%) of the layer. Two additional layers of the composite material for this layer include a second linear fiber configuration 140, which extends within an angular range including a displacement of ±30 degrees from the radial axis R by an angle of ±5 degrees. This embodiment of the fiber structure in the composite material provides a structure that is lighter in weight than the corresponding metal fuselage frame and provides the necessary resistance to shear loads originating from the vertical tail assembly 16 due to the operation of the aircraft 10.

[0034] refer to Figure 9 A schematic cross-section of aircraft 10 is shown, with fuselage assembly 12 and vertical tail assembly 16 viewed from a rearward position 48 toward aircraft 10. An embodiment of reactive shear forces relative to the first to fourth fuselage frames 20a-20d during the operation of aircraft 10 is shown. In this embodiment, during the operation of aircraft 10, an aerodynamic operating force F can be applied from the starboard side 26 of aircraft 10. The resultant load of the aerodynamic operating force F is transmitted through the vertical tail assembly 16, such that the fuselage frames, such as 20a-20d, provide a reactive force F1 on the port side 28 of the vertical tail assembly 16 of aircraft 10 in a direction toward the vertical tail assembly 16, and provide F2 on the starboard side 26 of the vertical tail assembly 16 of aircraft 10 in a direction away from the vertical tail assembly 16 in resistance to the aerodynamic operating force F. Since the aerodynamic operating forces F are opposite in direction, the reactive forces F1 and F2 are opposite in direction. In the embodiment of the fixing components 24 described herein, a second pair of 32 fixing components 24 and a third pair of 34 fixing components 24, respectively positioned on fuselage frames 20b and 20c, provide optimal load transfer between fuselage frames 20b and 20c when addressing aerodynamic operating forces F experienced from the starboard side 26 or port side 28 of the aircraft 10. A first pair of 30 fixing components 24 and a fourth pair of 36 fixing components 24, respectively positioned on fuselage frames 20a and 20d, provide optimal load transfer between fuselage frames 20a and 20d and the vertical tail assembly 16 when addressing longitudinal operating forces along the length L of the aircraft 10 on the vertical tail assembly 16.

[0035] refer to Figure 10 A method 142 for securing a vertical tail assembly 16 to an aircraft 10 includes: step 144, securing a first lug member 46, which is secured to the vertical tail assembly 16, to a first end 54 of a first U-shaped connector member 52. Method 142 further includes: step 146, securing a second end 56 of the first U-shaped connector member 52 to a first fuselage frame 20a constructed of composite material using a first fastener 58, the first fastener 58 extending in a first direction 60 transverse to the first fuselage frame 20a through the second end 56 of the first U-shaped connector member 52 and the first fuselage frame 20a.

[0036] As in Figure 5 As seen in the image, step 144 of fixing the first lug member 46 to the first end 54 of the first U-shaped connector member 52 includes: the first U-shaped connector member 52 having a first fork 62 and a second fork 66, the first fork 62 defining a first opening 64 at the first end 54 of the first U-shaped connector member 52, and the second fork 66 defining a second opening 68 at the first end 54 of the first U-shaped connector member 52. (As seen in...) Figure 6 As seen in the image, the first lug member 46 is positioned between the first fork portion 62 and the second fork portion 66 of the first U-shaped connector member 52, and extends through the first lug member 46 to define a first lug opening 72. The first pin 70 extends through the first opening 64 of the first fork portion 62, the second opening 68 of the second fork portion 66, and through the first lug opening 72 of the first lug member 46, such that the first pin 70 extends in a first direction 60 transverse to the first fuselage frame 20a.

[0037] As in Figure 5 As seen in the image, the method 142 for fixing further includes: a first pair of 35 U-shaped connector members including a first U-shaped connector member 52 and a second U-shaped connector member 78, wherein the second U-shaped connector member 78 is fixed to the first fuselage frame 20a at a distance spaced apart from the first U-shaped connector member 52 along a second direction 80 of the first fuselage frame 20a. A second pin (not shown) extends through a first opening 84 of a first bifurcation 82 of a first end 89 of the second U-shaped connector member 78, a second opening 88 of a second bifurcation 86 of the first end 89 of the second U-shaped connector member 78, and through a second lug opening (not shown) of a second lug member 90, such that the second pin (not shown) extends in a first direction 60 transverse to the first fuselage frame 20a. A second fastener 94 extends in a first direction 60 transverse to the first fuselage frame 20a through a second end 91 of the second U-shaped connector member 78 (as shown in the image). Figure 4(As seen in the image) and passes through the first fuselage frame 20a, the second U-shaped connector component 78 is fixed to the first fuselage frame 20a.

[0038] As in Figure 7 As seen in [the text], method 142 further includes: fixing a third lug member 108 to a first end 102 of a third U-shaped connector member 96, wherein a third fixing flange 116 of a second end 114 of the third U-shaped connector member 96 is fixed to a second fuselage frame 20b spaced apart from the first fuselage frame 20a. [The text then repeats itself, so the translation will only include the first part.] Figure 5 As seen in the diagram, the third U-shaped connector member 96 includes a first fork 98 and a second fork 104. The first fork 98 defines a first opening 100 at a first end 102 of the third U-shaped connector member 96, and the second fork 104 defines a second opening 106 at the first end 102 of the third U-shaped connector member 96. A third lug member 108 is positioned between the first fork 98 and the second fork 104 of the third U-shaped connector member 96 and defines a third lug opening (not shown) through the third lug member 108. A third pin 110 extends through the first opening 100 of the first fork 98, the second opening 106 of the second fork 104, and through the third lug opening (not shown) of the third lug member 108, such that the third pin 110 extends in a third direction 112 along the second fuselage frame 20b. Figure 7 As seen in the image, the third fastener 120 extends in a fourth direction 122 transverse to the second fuselage frame 20b, passing through the third fixing flange 116 of the second end 114 of the third U-shaped connector member 96 and the second fuselage frame 20b.

[0039] As in Figure 5 As seen in the image, the second pair of U-shaped connector members 37 includes a third U-shaped connector member 96 and a fourth U-shaped connector member 124, wherein the fourth U-shaped connector member 124 is fixed to the second fuselage frame 20b at a distance 112 from the third U-shaped connector member 96. The fourth U-shaped connector member 124 has a first fork 126 and a second fork 128. The first fork 126 defines a first opening 127 at a first end (not shown) of the fourth U-shaped connector member 124, and the second fork 128 defines a second opening 130 at the first end (not shown) of the fourth U-shaped connector member 124. The first end (not shown) of the fourth U-shaped connector member 124 and... Figure 7 The first end 102 of the third U-shaped connector member 96 shown is similar. (As in...) Figure 3 As seen in the image, the fourth lug member 132 is positioned between the first fork 126 and the second fork 128 of the fourth U-shaped connector member 124, and defines a fourth lug opening (not shown) through the fourth lug member 132. (The last sentence appears to be incomplete and possibly refers to a different context.) Figure 7Similar to the third pin 110 seen in the diagram, a fourth pin (not shown) extends through the first opening 127 of the first bifurcation 126, the second opening 130 of the second bifurcation 128, and through the fourth lug opening (not shown) of the fourth lug member 132, such that the fourth pin (not shown) extends in a third direction 112 along the second fuselage frame 20b. Similar to Figure 7 Similar to the third fastener 120, the fourth fastener (not shown) extends in a fourth direction 122 transverse to the second fuselage frame 20b through the fourth fixing flange 134 (not shown) at the second end of the fourth U-shaped joint member 124. Figure 2 (as seen in) and the second fuselage frame 20b, which is consistent with... Figure 7 The third fixed flange 116 seen in the image is fixed in a similar arrangement.

[0040] As in Figure 8 As seen in the diagram, the composite material used in constructing the first to fourth fuselage frames 20a-20d includes five plate-layer structures for the layers, wherein, as previously described in this embodiment, multiple layers are employed, including one plate layer with a first nonlinear fiber structure 136 having fibers. Two plate layers have a first linear fiber structure 138 having fibers extending within an angular range, which includes an angular displacement of ±30 degrees or ±5 degrees from the radial axis R of the nonlinear fiber structure 136. The other two plate layers have a second linear fiber structure 140 having fibers extending within an angular range, which includes an angular displacement of ±30 degrees or ±5 degrees from the radial axis R of the nonlinear fiber structure 136.

[0041] Although various embodiments have been described above, this disclosure is not intended to be limited thereto. Changes may be made to the disclosed embodiments, and they shall still fall within the scope of the appended claims.

Claims

1. A securing assembly for securing a tail fin assembly to an aircraft, wherein, The fixing component includes: A first lug member is fixed to the vertical tail fin assembly; and The first U-shaped joint component, wherein: The first end of the first U-shaped connector member is engaged with the first lug member; and The second end of the first U-shaped connector component is fixed to the first fuselage frame made of composite material by a first fastener, the first fastener extending through the second end of the first U-shaped connector component and the first fuselage frame in a first direction transverse to the first fuselage frame; The composite material comprises a five-layer structure, wherein the five-layer structure includes: A plate with a nonlinear fiber structure; Two plates having a first linear fiber structure extending within an angular range, the angular range including a displacement of ±30 degrees or ±5 degrees from the radial axis of the nonlinear fiber structure; and Two additional layers have a second linear fiber structure that extends within an angular range, the angular range including a positive or negative 5 degree offset from the radial axis of the nonlinear fiber structure by a factor of -30 degrees.

2. The fixing component according to claim 1, wherein: The first U-shaped connector member has a first forked portion and a second forked portion, the first forked portion defining a first opening at the first end of the first U-shaped connector member, and the second forked portion defining a second opening at the first end of the first U-shaped connector member; and The first lug member is positioned between the first bifurcation of the first U-shaped connector member and the second bifurcation of the first U-shaped connector member.

3. The fastening assembly of claim 2, further comprising a first pin extending through the first opening of the first bifurcation of the first U-shaped connector member, the second opening of the second bifurcation of the first U-shaped connector member, and through a first lug opening, such that the first pin extends in the first direction transverse to the first fuselage frame, the first lug opening being defined by and passing through the first lug member for engaging the first U-shaped connector member to the first lug member.

4. The fixture assembly of claim 2, wherein, The second end of the first U-shaped connector component includes a first fixing flange that extends along the front side of the first fuselage frame, wherein the first fastener extends through the first fixing flange and the first fuselage frame.

5. The fixed assembly of claim 1, further comprising a first pair of U-joint members including the first U-joint member and a second U-joint member fixed to the first fuselage frame, wherein, The first U-shaped connector member and the second U-shaped connector member are positioned spaced apart from each other along a second direction along the first fuselage frame; wherein: The first U-shaped connector member has a first forked portion, the first forked portion of the first U-shaped connector member defining a first opening at the first end of the first U-shaped connector member, and the second U-shaped connector member has a first forked portion, the first forked portion of the second U-shaped connector member defining a first opening at the first end of the second U-shaped connector member; The first U-shaped connector member has a second forked portion, the second forked portion of the first U-shaped connector member defining a second opening at the first end of the first U-shaped connector member, and the second U-shaped connector member has a second forked portion, the second forked portion of the second U-shaped connector member defining a second opening at the first end of the second U-shaped connector member; The first lug member is positioned between the first bifurcation of the first U-shaped connector member and the second bifurcation of the first U-shaped connector member in the first pair of U-shaped connector members; and The second lug member is positioned between the first forked portion of the second U-shaped connector member and the second forked portion of the second U-shaped connector member in the first pair of U-shaped connector members.

6. The fixing component according to claim 5, wherein: The first pin extends through the first opening of the first bifurcation of the first U-shaped connector member, the second opening of the second bifurcation of the first U-shaped connector member, and through the first lug opening, such that the first pin extends in the first direction transverse to the first fuselage frame, and the first lug opening is defined by the first lug member and passes through the first lug member. and The second pin extends through the first opening of the first bifurcation of the second U-shaped connector member, the second opening of the second bifurcation of the second U-shaped connector member, and through the second lug opening, such that the second pin extends in the first direction transverse to the first fuselage frame, the second lug opening being defined by and passing through the second lug member.

7. The fixing component according to claim 5, wherein: The second end of the first U-shaped connector member includes a first fixing flange, and the second end of the second U-shaped connector member includes a second fixing flange; The first fixing flange extends along the front side of the first fuselage frame, wherein the first fastener extends through the first fixing flange and the first fuselage frame in a first direction transverse to the first fuselage frame; and The second fixing flange extends along the front side of the first fuselage frame, wherein the second fastener extends through the second fixing flange and the first fuselage frame in the first direction transverse to the first fuselage frame.

8. The fixing component according to claim 1, further comprising: A third U-shaped connector component is fixed to a second fuselage frame made of composite material. The third U-shaped connector component is spaced apart from the first U-shaped connector component along the length of the aircraft. The third U-shaped connector component has a first branch and a second branch. The first branch of the third U-shaped connector component defines a first opening at a first end of the third U-shaped connector component, and the second branch of the third U-shaped connector component defines a second opening at the first end of the third U-shaped connector component. and The third lug member is positioned between the first bifurcation of the third U-shaped connector member and the second bifurcation of the third U-shaped connector member.

9. The fastening assembly of claim 8, further comprising a third pin extending through the first opening of the first bifurcation of the third U-shaped connector member, the second opening of the second bifurcation of the third U-shaped connector member, and through a third lug opening, such that the third pin extends upward along a third third of the second fuselage frame, the third lug opening being defined by and passing through the third lug member for engaging the third U-shaped connector member to the third lug member.

10. The fixture assembly of claim 8, wherein, The second end of the third U-shaped connector component includes a third fixing flange that extends along the front side of the second fuselage frame, wherein a third fastener extends through the third fixing flange and the second fuselage frame in a fourth direction transverse to the second fuselage frame.

11. The fixing assembly of claim 8, further comprising a second pair of U-shaped connector members, the second pair of U-shaped connector members including a third U-shaped connector member and a fourth U-shaped connector member fixed to the second fuselage frame and positioned spaced apart from each other in a third direction along the second fuselage frame.

12. The fixing component according to claim 11, wherein: The third U-shaped connector member has a first forked portion, the first forked portion of the third U-shaped connector member defining a first opening at the first end of the third U-shaped connector member, and the fourth U-shaped connector member has a first forked portion, the first forked portion of the fourth U-shaped connector member defining a first opening at the first end of the fourth U-shaped connector member. The third U-shaped connector member has a second forked portion, the second forked portion of the third U-shaped connector member defining a second opening at the first end of the third U-shaped connector member, and the fourth U-shaped connector member has a second forked portion, the second forked portion of the fourth U-shaped connector member defining a second opening at the first end of the fourth U-shaped connector member; The third lug member is positioned between the first bifurcation of the third U-shaped connector member and the second bifurcation of the third U-shaped connector member; and The fourth lug member is positioned between the first bifurcation of the fourth U-shaped connector member and the second bifurcation of the fourth U-shaped connector member.

13. The fixing component according to claim 12, wherein: The third pin extends through the first opening of the first bifurcation of the third U-shaped connector member, the second opening of the second bifurcation of the third U-shaped connector member, and through the third lug opening, such that the third pin extends upward along the third third of the second fuselage frame, the third lug opening being defined by the third lug member and passing through the third lug member; and The fourth pin extends through the first opening of the first bifurcation of the fourth U-shaped connector member, the second opening of the second bifurcation of the fourth U-shaped connector member, and through the fourth lug opening, such that the fourth pin extends upward along the third side of the second fuselage frame, the fourth lug opening being defined by and passing through the fourth lug member.

14. The fixing component according to claim 12, wherein: The second end of the third U-shaped connector component includes a third fixing flange, and the second end of the fourth U-shaped connector component includes a fourth fixing flange; The third fixing flange extends along the front side of the second fuselage frame, wherein the third fastener extends through the third fixing flange and the second fuselage frame in a fourth direction transverse to the second fuselage frame; and The fourth fixing flange extends along the front side of the second fuselage frame, and the fourth fastener extends through the fourth fixing flange and the second fuselage frame in the fourth direction transverse to the second fuselage frame.

15. A method for securing a tailfin assembly to an aircraft, wherein, The method includes: The first lug member is fixed to the first end of the first U-shaped connector member, and the first lug member is fixed to the vertical tail fin assembly; and The second end of the first U-shaped connector component is fixed to the first fuselage frame made of composite material using a first fastener. The first fastener extends through the second end of the first U-shaped connector component and the first fuselage frame in a first direction transverse to the first fuselage frame. The composite material comprises multiple sets of five-layer structures, the five-layer structures including: A plate with a nonlinear fiber structure; Two plates having a first linear fiber structure extending within an angular range, the angular range including a displacement of ±30 degrees or ±5 degrees from the radial axis of the nonlinear fiber structure; and Two additional layers have a second linear fiber structure that extends within an angular range, the angular range including a positive or negative 5 degree offset from the radial axis of the nonlinear fiber structure by a factor of -30 degrees.

16. The method of claim 15, wherein, Fixing the first lug member to the first end of the first U-shaped connector member includes: The first U-shaped connector member has a first branch portion and a second branch portion, wherein the first branch portion of the first U-shaped connector member defines a first opening at the first end of the first U-shaped connector member, and the second branch portion of the first U-shaped connector member defines a second opening at the first end of the first U-shaped connector member. The first lug member is positioned between the first bifurcation of the first U-shaped connector member and the second bifurcation of the first U-shaped connector member, and extends through the first lug member to define a first lug opening; and The first pin extends through the first opening of the first bifurcation of the first U-shaped connector member, the second opening of the second bifurcation of the first U-shaped connector member, and through the first lug opening of the first lug member, such that the first pin extends in the first direction transverse to the first fuselage frame.

17. The method of claim 16, further comprising: The first pair of U-shaped connector components includes a first U-shaped connector component and a second U-shaped connector component, wherein the second U-shaped connector component is fixed to the first fuselage frame and spaced apart from the first U-shaped connector component in a second direction along the first fuselage frame; The second pin extends through the first opening of the first fork at the first end of the second U-shaped connector member, the second opening of the second fork at the first end of the second U-shaped connector member, and through the second lug opening of the second lug member, such that the second pin extends in the first direction transverse to the first fuselage frame; and The second fastener extends in the first direction transverse to the first fuselage frame, passing through the second portion of the second U-shaped connector member and the first fuselage frame, thereby securing the second U-shaped connector member to the first fuselage frame.

18. The method of claim 16, further comprising: Fixing the third lug member to the first end of the third U-shaped connector member, wherein the third fixing flange at the second end of the third U-shaped connector member is fixed to a second fuselage frame spaced apart from the first fuselage frame, includes: The third U-shaped connector member has a first branch portion and a second branch portion, wherein the first branch portion of the third U-shaped connector member defines a first opening at the first end of the third U-shaped connector member, and the second branch portion of the third U-shaped connector member defines a second opening at the first end of the third U-shaped connector member. The third lug member is positioned between the first bifurcation of the third U-shaped connector member and the second bifurcation of the third U-shaped connector member, and extends through the third lug member to define a third lug opening; The third pin extends through the first opening of the first bifurcation of the third U-shaped connector member, the second opening of the second bifurcation of the third U-shaped connector member, and through the third lug opening of the third lug member, such that the third pin extends upward along a third side of the second fuselage frame. The third fastener extends in a fourth direction transverse to the second fuselage frame, passing through the third fixing flange at the second end of the third U-shaped joint member and the second fuselage frame; The second pair of U-shaped connector components includes the third U-shaped connector component and the fourth U-shaped connector component, wherein the fourth U-shaped connector component is fixed to the second fuselage frame and spaced apart from the third U-shaped connector component in the third direction along the second fuselage frame; The fourth U-shaped connector member has a first branch portion and a second branch portion, wherein the first branch portion of the fourth U-shaped connector member defines a first opening at the first end of the fourth U-shaped connector member, and the second branch portion of the fourth U-shaped connector member defines a second opening at the first end of the fourth U-shaped connector member. The fourth lug member is positioned between the first bifurcation of the fourth U-shaped connector member and the second bifurcation of the fourth U-shaped connector member, and extends through the fourth lug member to define a fourth lug opening; The fourth pin extends through the first opening of the first bifurcation of the fourth U-shaped connector member, the second opening of the second bifurcation of the fourth U-shaped connector member, and through the fourth lug opening of the fourth lug member, such that the fourth pin extends upward along the third side of the second fuselage frame; and The fourth fastener extends in the fourth direction transverse to the second fuselage frame through the fourth fixing flange of the second end of the fourth U-shaped joint member and the second fuselage frame.

Images