JP2015166244A5 - Method of constructing aircraft wing, aircraft wing configuration and aircraft comprising wing configuration - Google Patents

Claims (23)

A method of configuring an aircraft wing for a specific application, comprising :
The wing comprises a main wing extending over the width of a half wing;
The chord of the main wing (M) at the position of the outermost rib (R5) of the main wing (M) when viewed from the wing root is 5% to 15% of the half wing width of the main wing (M),
The main wing (M) is designed to form the wing base region (10) and the outer end region of the main wing (M) as viewed from the wing root, and fix the wing tip device (W1, W2, W3). wings adapter portion (20) and is configured de,
The wing adapter part (20) extends from the outer rib (R2) of the wing base region (10) to the outermost rib (R5) of the main wing (M) over 2% to 10% of the half wing width of the main wing (M). It extends outward until rib (R5) of the blade adapter unit to form a (20),
The upper angle of the blade adapter part (20) indicating the respective local blade width direction is 10 ° to from the outer rib (R2) of the blade base region (10) to the outermost rib (R5) of the blade adapter part (20). only 60 ° continuously increased Ri Na,
The method
Specific applications from a plurality of different wing tip devices (W1, W2, W3) each having different aerodynamic characteristics and each adapted to be selectively secured to the wing adapter portion (20) Selecting a wing tip device (W1, W2, W3) suitable for
Fixing the selected blade tip device (W1, W2, W3) to the blade adapter portion (20);
Having a method .   The method of claim 1, wherein the plurality of different wing tip devices (W1, W2, W3) have different shapes and sizes.   3. Configuring an aircraft wing for a particular application includes either configuring a different type of aircraft wing and / or improving aerodynamic characteristics. The method described in 1.   The plurality of different wing tip devices (W1, W2, W3) include a first wing tip device attached to the wing adapter portion (20), and one or more second wing tip devices; The fixing of claim 1, further comprising replacing the first tip device with a selected one of the one or more second tip devices. Method.   The aircraft wing is a first wing, and the method introduces an additional second wing of an aircraft and configures the first wing to connect the wing adapter portion to the existing wing. The method of claim 1, further comprising attaching to the second wing. A wing configuration for use in the method of claim 1, comprising:
An aircraft wing with a main wing extending across the width of a half wing;
The chord of the main wing (M) at the position of the outermost rib (R5) of the main wing (M) when viewed from the wing root is 5% to 15% of the half wing width of the main wing (M),
The main wing (M) is designed to form the wing base region (10) and the outer end region of the main wing (M) as viewed from the wing root, and fix the wing tip device (W1, W2, W3). wings adapter portion (20) and is configured de,
The wing adapter part (20) extends from the outer rib (R2) of the wing base region (10) to the outermost rib (R5) of the main wing (M) over 2% to 10% of the half wing width of the main wing (M). It extends outward until rib (R5) of the blade adapter unit to form a (20),
The upper angle of the blade adapter part (20) indicating the respective local blade width direction is 10 ° to from the outer rib (R2) of the blade base region (10) to the outermost rib (R5) of the blade adapter part (20). Continuously increases by 60 ° ,
Aircraft wings,
A plurality of different wing tip devices (W1, W2, W3) having different aerodynamic characteristics and each adapted to be selectively secured to said wing adapter portion (20);
Wing configuration equipped with. The blade adapter unit (20), the Ru integral component der wing (M), configuration of the blade according to claim 6. The blade adapter unit (20) is attached to the wing base region (10), wherein the wing (M) Ru component der separate, construction of blade according to claim 6. The main wing (M) includes a spar that extends along the spanwise its, a plurality of ribs which are sequentially arranged one behind as seen in the spanwise (R1, R2, R3, R4 , R5), the outer plate and Nde including has been the wing box (K) composed of a,
・ The chord of the main wing (M) at the position of the outermost rib (R5) of the main wing (M) as viewed from the wing root is 5% to 15% of the half wing width of the wing box (K). ,
The wing box (K) forms a wing box base portion (K10) and an outer end region of the wing box (K) when viewed from the wing root, and fixes the wing tip devices (W1, W2, W3). is composed out by wing box adapter unit and (K20) designed,
-The wing box adapter section (K20) extends from the outer rib (R2) of the wing box base section (K10) to the outermost rib (R5) of the main wing over 2% to 10% of the half wing width of the wing box (K). extends outward until rib (R5) of the wing box adapter portion forming the (K20),
The upper angle of the wing box adapter part (K20) indicating each local wing width direction is 10 ° to from the outer rib (R2) of the wing box base part (K10) to the outermost rib (R5) of the wing box adapter part. 60 ° only ing to large continuous structure of the wing according to any one of claims 6-8. Local sweep angle of the leading edge of the Oiteso based build state of the blade, only 10 ° to 45 ° in the region of the wing box adapter unit increases ing, construction of blade according to claim 9. The wing box adapter portion outer end of the (K20), the plurality of which have a coupling device for securing a different wing tip device, the configuration of the blade according to claim 9. Wing box adapter portion forming the outer end region of the wing box is designed to mount a plurality of different wing tip device, the wing tip device, the wing box base portion inside rib (K 2 0) It is coupled to the outer ribs, configuration of the blade according to claim 1 1. The coupling device, as to securely attach the wing tip device that is coupled to the wing box adapter section the box adapter part is designed as a forced locking parts at the outer end as viewed from the blade root, claim 11 or configuration of the blade according to 12. Local sweep angle of the leading edge of the wing, in the region of the wing box adapter unit, the maximum ing only 45 ° larger in the configuration of the blade according to claim 9. Local sweep angle of the trailing edge of the wing, in the region of the wing box adapter unit, up to 5 ° larger by ing the structure of the blade according to claim 9. Local sweep angle of the trailing edge of the wing, in the region of the wing box adapter part, at most 20 ° as large ing, construction of blade according to claim 9. The outer end portion of the wing box base portion (K10) as viewed from the wing root, together with the inner end portion of the adjacent wing box adapter portion (K20), connects the wing box adapter portion to the wing box base portion (K10). and coupling apparatus possess respectively, construction of blade according to claim 9. In the connecting device , the outer rib of the wing box base portion (K10) and the inner rib of the wing box adapter portion each have a bore hole, the outer rib is fixed to the inner rib, and the main wing box portion (K10) is fixed to the wing box adapter. The wing arrangement of claim 17 , wherein the wing arrangement is designed to be provided with a coupling element for coupling to the part. The coupling device is designed to be separated by breaking the connecting element, the configuration of the blade according to claim 1 8. The communication YuiSo location is consists as separated without any destruction, construction of blade according to claim 1 8. The wing configuration according to claim 17 , wherein the inner ribs of the wing box adapter part and the outer ribs of the wing box base part (K10) are designed to be securely joined and engaged when secured together. . Chord of the wing, in the region of the wing box adapter part from the outer ribs to the outermost rib of the wing box adapter portion of the wing box base section (K10), at least 95%, Ru is reduced to 45% at maximum, The configuration of the wing according to claim 9 .   An aircraft comprising the wing configuration according to any one of claims 9 to 22.