Transporter super-long cabin door adjusting structure and adjusting method

Abstract

The invention belongs to the technical field of aircraft design, and particularly relates to an ultra-long cabin door adjusting structure and method for a transport plane, which mainly comprise cabin door initial centering adjustment, cabin door gap and jump adjustment and adjustment of a closed position centering guide device. And the hatch can be ensured to be positioned on the symmetric line of the airplane.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft design, and in particular relates to an adjustment structure and an adjustment method for an extra-long door of a transport aircraft. Background Art

[0002] Aircraft doors, especially those that open in the air, are mainly used for cargo delivery to ensure the continuity of the fuselage opening. Extra-long doors are difficult to adjust. The main background involved is as follows:

[0003] 1. The extra-long door is subject to the principle of leverage, and the adjustment of the rear hinge will cause a large change in the front position;

[0004] 2. Due to the influence of assembly error, the extra-long door is difficult to assemble in one go and must be compensated later;

[0005] 3. It is difficult to center an extra-long door. The door body has weak rigidity and it is difficult to maintain the door on the symmetry plane of the aircraft simply by relying on its own rigidity. Summary of the invention

[0006] In order to solve the above problems, the present application provides an adjustment structure of an extra-long door of a transport aircraft, the door comprising:

[0007] The door frame located at the rear belly, the two side doors hinged on the door frames on both sides, and the middle door;

[0008] The rear end of the middle door is hinged on the hinge joint, the hinge axis of the side door is parallel to the heading, and the hinge axis of the middle door is perpendicular to the heading; the front end of the middle door opens and closes up and down; when the door is opened, the two side doors rotate downward along the hinge axis, and the middle door rotates upward along the hinge axis; when the door is closed, the two side doors rotate upward along the hinge axis, and the middle door rotates downward along the hinge axis;

[0009] The adjustment structure includes:

[0010] The hinge joint mounting surface is fitted with the vertical surface of the fuselage and fixed by bolts, and the mounting surface has a part of vertical tooth-shaped grooves and a part of transverse tooth-shaped grooves; the vertical surface of the fuselage has a tooth-shaped groove matching the mounting surface, which is used to adjust the position of the hinge joint, and then adjust the vertical and span positions of the middle hatch;

[0011] A guide device is adjustably installed at the fuselage position at the front door frame position, the guide device has a guide groove, the guide groove has a Y-shaped groove surface, the front end of the middle door is provided with a guide roller, the axis of the guide roller is parallel to the heading, when the door is closed, the guide roller enters the groove bottom along the Y-shaped groove surface; it is used to adjust the spanwise position of the middle door closed position;

[0012] When the front end of the middle hatch is closed, it is in vertical contact with the supporting surface of the door frame through a contact assembly. The contact assembly has an adjustable bolt with adjustable height. The number of contact assemblies includes at least two distributed in the span direction, which are used to adjust the vertical position of the closed position of the middle hatch.

[0013] Preferably, one surface of the guide device has a portion of vertical toothed grooves and a portion of transverse toothed grooves; the vertical surface of the fuselage at the front door frame position has a toothed groove matching a surface of the guide device, which is used to adjust the position of the guide device, and thereby adjust the vertical and spanwise positions of the middle hatch.

[0014] Preferably, the edge of the side door has a plurality of locking rings, and the two edges of the middle door have a plurality of locking hooks hooked on the locking rings; when the door is opened, the locking hooks hook on the locking rings; when the door is closed, the locking hooks are disengaged from the locking rings.

[0015] Preferably, the heading length of the guide roller is greater than the heading width of the guide groove, so that there is a gap between the middle door and the end surface of the guide groove.

[0016] Preferably, the guide groove is provided with a margin hole at a position corresponding to the end of the guide roller, so as to compensate for the movement caused by the heading deformation of the middle door.

[0017] Preferably, when the door is closed, the side door has an over-retraction angle, which is the angle formed by the side door and the middle door, and the side door is higher than the middle door.

[0018] Preferably, the height difference between the side doors and the middle door is determined by the total width of the doors.

[0019] Preferably, the height difference between the side door and the middle door does not exceed 5 mm.

[0020] Preferably, the span width of the guide groove is determined by the span deformation of the front end of the door under extreme conditions.

[0021] Preferably, the span width of the guide groove is equal to the span deformation of the front end of the door in an extreme case plus a set margin.

[0022] Preferably, a front end surface of the middle door and the front end door frame have a reserved gap, and the reserved gap is equal to the forward movement of the middle door under a sharp pitch of the aircraft multiplied by a safety factor.

[0023] Preferably, the safety factor is 1.5.

[0024] Preferably, both side edges of the middle door each have at least one guide roller, door frame supports are fixed on both side door frames, the door frame supports have guide surfaces, the guide rollers are attached to the guide surfaces, and roll along the guide surfaces when the door is opened or closed.

[0025] A method for adjusting an extra-long door of a transport aircraft, comprising:

[0026] Door centering adjustment: measure the deviation between the symmetry line of the middle door and the symmetry line of the front fuselage. When the deviation is greater than the set threshold, adjust the spanwise position of the hinge joint or add a gasket between the middle door and the hinge joint. After adding the gasket, the lateral play clearance between the middle door and the hinge joint is not greater than the set limit value.

[0027] Front end step adjustment of the door: When the step of the middle door exceeds 2 / 3 of the tolerance of the aerodynamic shape, adjust the adjustable bolt of the contact assembly to make the step between the front end of the middle door and the fuselage within the allowable range;

[0028] Adjust the rear step difference of the hatch door: the lateral clearance between the middle hatch door and the guide roller is less than 0.2mm, the clearance between the bottom of the guide groove and the guide roller is less than 2mm, and the position of the guide device is adjusted.

[0029] The advantages of the present application include: the inventive door structure with adjustment function can better adjust the position of the door. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is a schematic diagram of an extra-long cabin door of a transport aircraft according to a preferred embodiment of the present application. DETAILED DESCRIPTION

[0031] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.

[0032] In order to solve the above problems, the present application provides an adjustment structure of an extra-long door of a transport aircraft, the door comprising:

[0033] The door frame located at the rear fuselage belly, two side doors (D.1, D.3) hinged to the door frames on both sides, and the middle door (D.2);

[0034] The rear end of the middle door (D.2) is hinged on the hinge joint, the hinge axes of the side doors (D.1, D.3) are parallel to the heading, and the hinge axis of the middle door (D.2) is perpendicular to the heading; the front end of the middle door (D.2) opens and closes up and down; when the door is opened, the two side doors (D.1, D.3) rotate downward along the hinge axis, and the middle door (D.2) rotates upward along the hinge axis; when the door is closed, the two side doors (D.1, D.3) rotate upward along the hinge axis, and the middle door (D.2) rotates downward along the hinge axis;

[0035] The adjustment structure includes:

[0036] The hinge joint mounting surface is fitted with the vertical surface of the fuselage and fixed by bolts, and the mounting surface has a part of vertical tooth-shaped grooves and a part of transverse tooth-shaped grooves; the vertical surface of the fuselage has a tooth-shaped groove matching the mounting surface, which is used to adjust the position of the hinge joint, and then adjust the vertical and spanwise position of the middle door (D.2);

[0037] A guide device is adjustably installed at the position of the fuselage at the front door frame position, the guide device has a guide groove (G.1), the guide groove (G.1) has a Y-shaped groove surface, the front end of the middle cabin door (D.2) is provided with a guide roller (G.2), the axis of the guide roller (G.2) is parallel to the heading, when the cabin door is closed, the guide roller (G.2) enters the groove bottom along the Y-shaped groove surface; it is used to adjust the spanwise position of the closed position of the middle cabin door (D.2);

[0038] When the middle hatch (D.2) is closed, the front end is in vertical contact with the supporting surface of the door frame through a contact assembly. The contact assembly has an adjustable bolt with adjustable height. The number of contact assemblies includes at least two distributed in the span direction, which are used to adjust the vertical position of the closed position of the middle hatch (D.2).

[0039] Preferably, one surface of the guide device has a portion of vertical toothed grooves and a portion of transverse toothed grooves; the vertical surface of the body at the front door frame position has a toothed groove matching a surface of the guide device, which is used to adjust the position of the guide device, and then adjust the vertical and spanwise position of the intermediate door (D.2).

[0040] In some optional embodiments, a guide groove G.1 is provided at the front door frame, the guide groove G.1 has a Y-shaped groove surface, and the front end of the middle hatch D.2 has a guide roller G.2 overlapped on the body, which is installed as shown in FIG. Figure 1 At the G1 position shown, the axis of the guide roller G.2 is parallel to the heading. When the cabin door is closed, the guide roller G.2 enters the groove bottom along the Y-shaped groove surface.

[0041] In some optional embodiments, the heading length of the guide roller G.2 is greater than the heading width of the guide groove G.1, so that there is a gap between the middle door D.2 and the end surface of the guide groove G.1.

[0042] In some optional embodiments, the guide groove G.1 is provided with a margin hole at a position corresponding to the end of the guide roller G.2, so as to compensate for the movement caused by the heading deformation of the middle door D.2.

[0043] In some optional embodiments, when the doors are closed, the side doors D.1 and D.3 have an over-retraction angle, which is the angle formed by the side doors D.1 and D.3 and the middle door D.2. The heights of the side doors D.1 and D.3 are greater than those of the middle door D.2, and the height difference between the side doors D.1 and D.3 and the middle door D.2 does not exceed 5 mm.

[0044] In some optional embodiments, the spanwise width of the guide groove G.1 is equal to the spanwise deformation of the front end of the door in the extreme case plus a set margin.

[0045] In some optional embodiments, a front end surface of the middle door D.2 and the front end door frame have a reserved gap, and the reserved gap is equal to the forward movement of the middle door D.2 under a sharp pitch of the aircraft multiplied by a safety factor of 1.5.

[0046] In some optional embodiments, the two sides of the intermediate door D.2 each have at least one guide roller U.1, forming a lateral guide assembly U, which is respectively installed as follows: Figure 1 At the positions U1 and U2 shown, door frame supports U.2 are fixed on the door frames on both sides, and the door frame supports U.2 have guide surfaces U.3. The guide roller U.1 is attached to the guide surfaces U.3 and rolls along the guide surfaces U.3 when the cabin door is opened or closed.

[0047] A typical method for adjusting an extra-long door of a transport aircraft is as follows: it mainly includes initial centering adjustment of the door, adjustment of the door gap and step difference, and adjustment of the centering guide device of the closed position.

[0048] Centering guide adjustment of the hatch door: when the hatch door is in a fully closed state, the position of the guide groove is adjusted by the tooth shape to ensure that the gap between the roller and the guide groove is not less than a certain value, preferably, the value is 0.2mm, and the distance between the roller and the bottom surface of the guide groove is not less than a certain value, preferably, the value is 2mm.

[0049] The initial centering adjustment of the door mainly adopts the method of installing the door to the closed position by bracket, and then realizing the initial centering state of the door by moving the bracket. This operation is mainly used to limit the initial position within a certain range of the fuselage symmetry line, which can ensure the symmetry characteristics of the initial position. In addition, the use of the bracket can also ensure that the initial step difference of the door floats within a certain range.

[0050] The front end step difference adjustment of the hatch is mainly achieved through the contact assembly. The contact assembly is equipped with an adjustment bolt. According to the screw-in and screw-out lengths of the thread, the front end step difference can be effectively adjusted steplessly to accurately ensure that the front end step difference is met.

[0051] The rear end step difference of the hatch door is adjusted mainly through the tooth plate on the hinge. Generally, the size of the tooth plate should not be too large or too small. If the tooth plate is too large, the adjustment resolution will be small and accurate adjustment cannot be achieved. If the tooth plate is too small, the teeth will break and jump under the load. Preferably, the size of a single tooth of the tooth plate is 0.5-2mm. The rear end can achieve relatively accurate step difference adjustment.

[0052] The gap adjustment of the hatch door is divided into three positions: front, side and rear. Generally, the reserved skin margin on the front side of the hatch door is large, which can be achieved by filing down the hatch door skin. The reserved gaps on the sides and rear are small. In order to ensure the installation of the sealing tape, it is usually achieved by filing down the surrounding structure skin.

[0053] The centering guide adjustment of the hatch is provided with guide rollers and guide grooves at the initial centering contact. The guide rollers fall precisely into the guide grooves to judge whether they are completely centered. There is a gap between the guide rollers and the guide grooves. The gap cannot be too small. If it is too small, the guide rollers will be subjected to additional loads under the action of the load, which is not conducive to the force. The side and upper gaps can effectively prevent additional additional loads on the guide.

[0054] This application also has margin compensation, which is specifically in three directions:

[0055] In heading, when the middle door D.2 is in the closed position, the guide roller G.2 of the middle door falls into the front guide slot G.1, and the middle part of the guide slot G.1 has a hole. When the middle door pitches sharply and the heading moves, the guide roller G.2 moves forward and enters the margin hole of the guide slot G.1, which can compensate for the movement caused by heading deformation and prevent the guide roller G.2 from interfering with the guide slot G.1. In addition, a certain gap is reserved between the skin of the middle door D.2 and the front door frame.

[0056] In the vertical direction, when the side doors D.1 and D.3 are closed, they do not stop when they are flush with the middle door D.2, but continue to move until the side doors D.1 and D.3 are over-retracted. Preferably, the over-retraction angle is usually determined according to the width of the door body to ensure that the over-retraction amount is no more than 5mm. In addition, a lock ring S.2 is installed on the side doors D.1 and D.3, and a lock hook S.1 is installed on the middle door D.2. The lock hook S.1 can be adjusted according to the vertical position of the lock ring S.2 to compensate for the vertical deformation.

[0057] In the span direction, when the middle door is closed, the guide roller G.2 of the middle door hits the two guide planes of the front guide groove G.1. The minimum span width of the two guide planes determines the span deformation of the front end of the door. Preferably, the width = the span deformation of the front end of the door in the extreme case + 5mm. When the middle door is opened, the guide roller U.1 of the middle door contacts the U.3 guide surface installed on the fuselage to ensure that the door is located on the symmetry plane of the fuselage when in the upper position. The span width of the guide surface U.3 determines the span deformation of the middle door D.2 in the upper position.

[0058] Preferably, the gap value between the middle hatch D.2 skin and the front door frame can be calculated. The calculation method of the gap value is usually to obtain the forward movement of the middle hatch D.2 under the condition of sharp pitch through finite element simulation, and multiply the movement by a safety factor of 1.5 as the reserved gap between the middle hatch D.2 skin and the front door frame. The advantages of the present application include: the invention of a hatch structure with an adjustment function can better adjust the position of the hatch.

[0059] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. An adjustment structure for an extra-long door of a transport aircraft, characterized in that: The hatch comprises: The door frame located at the rear fuselage, the two side doors (D.1, D.3) hinged to the door frames on both sides, and the middle door (D.2); The rear end of the middle door (D.2) is hinged on the hinge joint, the hinge axes of the side doors (D.1, D.3) are parallel to the heading, and the hinge axis of the middle door (D.2) is perpendicular to the heading; the front end of the middle door (D.2) opens and closes up and down; when the door is opened, the two side doors (D.1, D.3) rotate downward along the hinge axis, and the middle door (D.2) rotates upward along the hinge axis; when the door is closed, the two side doors (D.1, D.3) rotate upward along the hinge axis, and the middle door (D.2) rotates downward along the hinge axis; The adjustment structure includes: The hinge joint mounting surface is fitted with the vertical surface of the fuselage and fixed by bolts, and the mounting surface has a part of vertical tooth-shaped grooves and a part of transverse tooth-shaped grooves; the vertical surface of the fuselage has a tooth-shaped groove matching the mounting surface, which is used to adjust the position of the hinge joint, and then adjust the vertical and spanwise position of the middle door (D.2); A guide device is adjustably installed at the position of the fuselage at the front door frame position, the guide device has a guide groove (G.1), the guide groove (G.1) has a Y-shaped groove surface, the front end of the middle cabin door (D.2) is provided with a guide roller (G.2), the axis of the guide roller (G.2) is parallel to the heading, when the cabin door is closed, the guide roller (G.2) enters the groove bottom along the Y-shaped groove surface; it is used to adjust the spanwise position of the closed position of the middle cabin door (D.2); When the middle hatch (D.2) is closed, the front end is in vertical contact with the supporting surface of the door frame through a contact assembly. The contact assembly has an adjustable bolt with adjustable height. The number of contact assemblies includes at least two distributed in the span direction, which are used to adjust the vertical position of the closed position of the middle hatch (D.2).

2. The transport aircraft super-long door adjustment structure according to claim 1, characterized in that: One surface of the guide device has a portion of vertical toothed grooves and a portion of transverse toothed grooves; the vertical surface of the fuselage at the front door frame position has a toothed groove matching a surface of the guide device, which is used to adjust the position of the guide device and thereby adjust the vertical and spanwise position of the intermediate door (D.2).

3. The transport aircraft super-long door adjustment structure according to claim 1, characterized in that: The edges of the side doors (D.1, D.3) are provided with a plurality of locking rings (S.2), and the two edges of the middle door (D.2) are provided with a plurality of locking hooks (S.1) hooked with the locking rings (S.2); when the door is opened, the locking hooks (S.1) hook with the locking rings (S.2); when the door is closed, the locking hooks (S.1) are separated from the locking rings (S.2).

4. The transport aircraft super-long door adjustment structure according to claim 1, characterized in that: The heading length of the guide roller (G.2) is greater than the heading width of the guide groove (G.1), so that a gap exists between the end surface of the middle door (D.2) and the guide groove (G.1).

5. The transport aircraft super-long door adjustment structure according to claim 1, characterized in that: The guide groove (G.1) is provided with a margin hole at a position corresponding to the end of the guide roller (G.2) for compensating for the movement caused by the heading deformation of the middle cabin door (D.2).

6. The transport aircraft super-long door adjustment structure according to claim 1, characterized in that: When the hatch is closed, the side hatches (D.1, D.3) have an over-retraction angle, which is the angle formed by the side hatches (D.1, D.3) and the middle hatch (D.2), and the height of the side hatches (D.1, D.3) is greater than that of the middle hatch (D.2).

7. The transport aircraft super-long door adjustment structure according to claim 6, characterized in that: The height difference between the side doors (D.1, D.3) and the middle door (D.2) is determined by the total width of the doors.

8. The transport aircraft super-long door adjustment structure according to claim 7, characterized in that: The height difference between the side doors (D.1, D.3) and the middle door (D.2) shall not exceed 5 mm.

9. The transport aircraft super-long door adjustment structure according to claim 6, characterized in that: The span width of the guide groove (G.1) is determined by the span deformation of the front end of the door under extreme conditions.

10. The transport aircraft super-long door adjustment structure according to claim 6, characterized in that: The span width of the guide groove (G.1) is equal to the span deformation of the front end of the door in the limit case plus the set margin.

11. The transport aircraft super-long door adjustment structure according to claim 1, characterized in that: A reserved gap is provided between the front end surface of the middle cabin door (D.2) and the front end door frame, and the reserved gap is equal to the forward movement amount of the middle cabin door (D.2) when the aircraft pitches sharply multiplied by a safety factor.

12. The transport aircraft super-long door adjustment structure according to claim 10, characterized in that: The safety factor is 1.

5.

13. The transport aircraft super-long door adjustment structure according to claim 1, characterized in that: The two side edges of the middle hatch (D.2) are respectively provided with at least one guide roller (U.1), door frame supports (U.2) are fixed on the door frames on both sides, the door frame supports (U.2) are provided with guide surfaces (U.3), the guide roller (U.1) is attached to the guide surfaces (U.3), and rolls along the guide surfaces (U.3) when the hatch door is opened or closed.

14. A method for adjusting an extra-long door of a transport aircraft, comprising: Door centering adjustment: measure the deviation between the symmetry line of the middle door (D.2) and the symmetry line of the front fuselage. When the deviation is greater than the set threshold, adjust the spanwise position of the hinge joint or add a shim between the middle door (D.2) and the hinge joint. After adding the shim, the lateral play clearance between the middle door (D.2) and the hinge joint is not greater than the set limit value. Front end step adjustment of the door: When the step of the middle door (D.2) exceeds 2 / 3 of the tolerance of the aerodynamic shape, adjust the adjustable bolt of the contact assembly to make the step between the front end of the middle door (D.2) and the fuselage within the allowable range; Rear step adjustment of the door: when the step between the middle door (D.2) and the rear fuselage is greater than 2 / 3 of the tolerance of the aerodynamic shape, adjust the vertical position of the hinge joint; Door clearance adjustment: The front end clearance is adjusted by filing the door skin, and the side and rear clearances are adjusted by filing the skin of adjacent parts; Centering guide adjustment of the hatch door: When the lateral clearance between the guide groove (G.1) and the guide roller (G.2) is less than 0.2mm, and the clearance between the bottom of the guide groove (G.1) and the guide roller (G.2) is less than 2mm, adjust the position of the guide device.

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