Connecting structure for machine head cover and adjusting method of connecting structure

Abstract

The invention provides a connecting structure for a machine head cover and an adjusting method of the connecting structure, and belongs to the technical field of machine body structural design. When a machine head cover assembly is opened, a hook lock in a hook lock assembly is unlocked, so that the machine head cover assembly rotates around the axis of a lug of a hinge assembly to a fixed angle, and the machine head cover assembly is supported through an air elastic supporting rod assembly; the machine head cover assembly is kept in an open posture; when the machine head cover assembly is closed, the gas elastic supporting rod assembly is shortened under the external acting force, so that the machine head cover assembly rotates around the axis of the lug piece of the hinge assembly, and the machine head cover assembly closes and locks a hook lock in the hook lock assembly under the guiding effect of the middle plug pin assembly. When the gap and the step difference between the machine head cover and the machine body structure are adjusted, the assembly error is reduced, the adjusting capacity is improved, meanwhile, the hinge can be prevented from protruding out of the shape, and the shape maintaining requirement can be met.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft structure design, and in particular relates to a connection structure for an aircraft head cover and an adjustment method thereof. Background Art

[0002] In order to meet the maintenance needs of the aircraft, the nose is often equipped with an openable nose cover. The nose cover should be easy to open and close, and be able to stably maintain a certain posture after opening; a good sealing structure and water-conducting structure should be formed between the nose cover and the fuselage structure. In addition, the nose cover is the first part of the aircraft to be affected, and its appearance should be as smooth as possible. This requires that the connection structure between it and the fuselage structure should also have a smooth appearance to reduce aerodynamic resistance; in order to achieve assembly interchangeability, the nose cover should have an adjustable function so that the gap value and step difference value meet the design requirements when connected to any aircraft.

[0003] In the prior art, the connector between the nose cover and the fuselage structure docked therewith does not have or cannot have the ability to adjust the heading, vertical and span directions at the same time and lacks the guiding function. Therefore, when the gap and step difference between the nose cover and the fuselage structure are adjusted by the connector, the connector cannot well compensate for the large assembly error. Therefore, the connector between the nose cover and the fuselage structure docked therewith has poor adjustability and poor guiding performance, resulting in poor interchangeability of the nose cover. In addition, the nose cover and the fuselage structure are connected by a hinge, which will protrude the appearance and cannot meet the dimensional requirements. Summary of the invention

[0004] In order to solve the technical problems in the prior art that the nose cover and the fuselage structure connected thereto have poor adjustability, poor guidance, poor interchangeability, and the hinge connection method cannot meet the dimensional requirements, the present invention provides a connection structure for the nose cover and an adjustment method thereof, which can reduce the assembly error and improve the adjustability when adjusting the gap and step difference between the nose cover and the fuselage structure, and can also avoid the hinge protruding from the shape, so as to meet the dimensional requirements. The technical solution is as follows:

[0005] In a first aspect, a connection structure for a nose cover is provided, comprising: a gas elastic strut assembly 4, a hinge assembly 5, a hook lock assembly 6, and a middle latch assembly 7.

[0006] The two ends of the gas elastic strut assembly 4 are respectively connected to the nose cover assembly 1 and the cockpit cover assembly 3; the fixed part of the hinge assembly 5 is connected to the cockpit cover assembly 3, and the movable part is connected to the nose cover assembly 1; the lock hook of the hook lock assembly 6 is connected to the nose cover assembly 1, and the lock ring is connected to the cockpit cover assembly 3; the middle latch pin of the middle latch pin assembly 7 is connected to the nose cover assembly 1, and the middle latch pin box is connected to the cockpit cover assembly 3;

[0007] When opening the nose hood assembly 1, the hook lock in the hook lock assembly 6 is unlocked, so that the nose hood assembly 1 rotates around the ear axis of the hinge assembly 5 and rotates to a fixed angle. The nose hood assembly 1 is supported by the gas elastic strut assembly 4 to keep the nose hood assembly 1 in an open posture; when closing the nose hood assembly 1, the gas elastic strut assembly 4 is shortened under the external force, so that the nose hood assembly 1 rotates around the ear axis of the hinge assembly 5, and the nose hood assembly 1 is closed under the guidance of the middle latch assembly 7, locking the hook lock in the hook lock assembly 6.

[0008] The nose cover assembly 1 includes: a nose cover 8, a nose cover sealing support 9 and a handle 10;

[0009] The nose cover sealing support 9 is riveted on the nose cover 8, and the handle 10 is screwed to the inner side of the nose cover 8 just below to facilitate the closing operation. The nose cover sealing support 9 is provided with a mounting surface for the hook lock assembly 6 and the middle latch assembly 7;

[0010] In order to avoid the hinge assembly 5, the cross-sectional shape of the area on the nose cover sealing support 9 corresponding to the position of the hinge assembly 5 is a special C-shape; the cross-sectional shape of the rest of the nose cover sealing support 9 is a C-shape;

[0011] The nose cover sealing support member 9 is made of glass fiber, which can reduce the weight of the nose cover assembly 1;

[0012] The nose cover sealing support member 9 is divided into two parts, the left and right parts are butted together with rivets using C-shaped angle materials just above the left and right parts, and are connected with rivets in an overlapping manner just below.

[0013] The canopy assembly 3 includes: a front upper skin 11, a left skin 12, a right skin 13, a bottom skin 14 and a canopy sealing support 15; the front upper skin 11, the left skin 12, the right skin 13 and the bottom skin 14 form the outer skin of the canopy assembly 3, and the canopy sealing support 15 is riveted at the interface between the canopy assembly 3 and the nose cover assembly 1 of the outer skin;

[0014] The front upper skin 11 is provided with an embedded installation groove 16 for the hinge assembly 5 so that the installation of the hinge assembly 5 does not protrude from the appearance; the cockpit cover sealing support 15 is provided with an installation surface for the hook lock assembly 6 and the middle latch assembly 7; the cross-sectional shape of the cockpit cover sealing support 15 is C-shaped;

[0015] The canopy seal support 15 includes a canopy seal left support 18, a canopy seal right support 19, a canopy seal left lower support 20, a canopy seal right lower support 21, a left lower L-shaped angle 22, and a right lower L-shaped angle 23; the canopy seal left support 18, the canopy seal right support 19, the canopy seal left lower support 20, and the canopy seal right lower support 21 are connected by rivets in an overlapping manner; the front upper skin 11, the left skin 12 and the right skin 13 The mounting planes for the left and right canopy sealing supports 18 and 19 are formed at the joint 17 with the nose cover 8; the lower left L-shaped angle member 22 and the lower right L-shaped angle member 23 are riveted to the bottom skin 14 to form mounting surfaces for the lower left and right canopy sealing supports 20 and 21; the left and right canopy sealing supports 18, 19, 20 and 21 are made of carbon fiber composite material structure.

[0016] Among them, the sealing strip 2 located between the nose cover assembly 1 and the cockpit cover assembly 3,

[0017] The cross section of the sealing strip 2 is an O-shaped strip with a slot shape, and the slot end is stuck on the C-shaped cross section cockpit cover sealing support 15. The cockpit cover sealing support 15 forms a guide groove 42. The O-shaped end is pressed on the nose cover sealing support 9 after the nose cover is locked, thereby solving the problem of imperfect sealing structure between the nose cover and the fuselage structure in the prior art, which causes water leakage.

[0018] Among them, the nose cover assembly 1 is opened with the assistance of maintenance personnel through two groups of gas elastic strut assemblies 4, and the two groups of gas elastic strut assemblies 4 are symmetrically arranged; the gas elastic strut assembly 4 includes: a gas elastic strut 37, a fixed end support 35, and a movable end support 36; the gas elastic strut 37 is screwed with the fixed end support 35 and the movable end support 36, the fixed end support 35 and the nose structure 34 are riveted, and the movable end support 36 is screwed with the nose cover assembly 1, which is used to solve the problem in the prior art that if the nose cover is located at a high position, the mechanical strut without auxiliary power on it cannot be used to prop up the nose cover.

[0019] Among them, the hinge assembly 5 includes: a conductive gasket 24, a peelable gasket 25, a heading adjustment toothed plate 26, a hinge support 27, a hinge joint 28, a span adjustment toothed plate 29 and a bushing 30; the hinge assembly 5 is screwed to the nose cover assembly 1 and the cockpit cover assembly 3, the hinge support 27 is screwed to the cockpit cover assembly 3, the hinge joint 28 is screwed to the nose cover assembly 1, the hinge support 27 and the hinge joint 28 are connected by a flat pin, a gasket and a cotter pin, and a bushing 30 is provided at the connection between the hinge support 27 and the hinge joint 28; the conductive gasket 24, the peelable gasket 25, and the heading adjustment toothed plate 26 are located directly below the hinge support 27; the span adjustment toothed plate 29 is riveted to the cockpit cover assembly 3, and is located between the hinge joint 28 and the cockpit cover assembly 3.

[0020] The peelable gasket 25 is made of aluminum alloy, with a thickness of 0.1 to 0.5 mm per layer; the heading adjustment toothed plate 26 is an aluminum alloy structural part, with an adjustment step of 0.5 to 0.75 mm, and a circular arc-shaped tooth bottom;

[0021] The hinge support 27 is an aluminum alloy structural part, the fiber direction L is parallel to the centerline direction 31, the adjustment step is 0.5-0.75mm, and the bottom of the thread is a flat straight line; the hinge support 27 is provided with a bolt mounting hole for connecting the canopy assembly 3, the bolt mounting hole is a waist-shaped hole 32, the long side is along the heading, and the distance between the two centers of the waist-shaped hole 32 is 2-4mm; at the same time, the hinge support 27 is provided with an outer shape dimension surface for shaping; the waist-shaped hole 32 on the hinge support 27 is used to provide the heading adjustment amount;

[0022] The hinge joint 28 is an aluminum alloy structural part, the fiber direction L is parallel to the center line direction 33, the adjustment step is 0.75mm, the bottom of the thread is arc-shaped, and the hinge joint 28 is provided with a bolt mounting hole 32 for connecting the head cover assembly 1, which is a waist-shaped hole, with the long edge in the span direction, and the distance between the two centers of the waist-shaped hole is 2 to 4mm. The waist-shaped hole on the hinge joint 28 is used to provide the adjustment amount in the span direction;

[0023] The spanwise adjustment toothed plate 29 is an aluminum alloy structural part, with an adjustment step length of 0.5 to 0.75 mm and a straight line at the tooth bottom;

[0024] The bushing 30 is made of stainless steel and is used to prevent corrosion caused by paint shedding due to the kinematic pair between the pin and the hole wall of the hinge support 27 and the hinge joint 28 .

[0025] The middle latch assembly 7 is composed of a middle latch box 38, a middle latch 39 and a middle latch angle material 40; the middle latch 39 is riveted to the nose cover assembly 1 and is provided with a cone head latch 41; the middle latch angle material 40 is riveted to the cockpit cover assembly 3; the middle latch box 38 is screwed to the middle latch angle material 40; the middle latch box 38 is provided with a waist-shaped hole 43 for inserting the middle latch 39, and the long edge of the waist-shaped hole 43 is vertical;

[0026] The bolt hole on the middle pin box 38 that is screwed to the middle pin angle material 40 is a waist-shaped hole, and the long side of the waist-shaped hole extends in the direction; the bolt hole on the middle pin angle material 40 that is screwed to the middle pin box 38 is a round hole.

[0027] In a second aspect, a method for adjusting a connection structure of a nose cover is provided, which is applied to any connection structure described in the first aspect, and the method comprises:

[0028] Step 1: Adjust the length of the lock ring of the hook lock assembly 6 at position 4 until the gap J2 in area 2 meets the design requirements;

[0029] Step 2, adjusting the relative positions of the hinge joint 28 at position 1 and the spanwise adjustment toothed plate 29 until the step difference D3 of area 3 and the step difference D4 of area 4 meet the design requirements;

[0030] Step 3: Adjust the relative positions of the hinge support 27 at position 2 and the heading adjustment toothed plate 26 until the gap J1 in area 1 meets the design requirements;

[0031] Step 4, adjusting the thickness of the peelable gasket 25 at position 1, with the gap J3 of area 3 and the gap J4 of area 4 meeting the design requirements first, until the step difference D1 of area 1 and the step difference D2 of area 2 meet the design requirements;

[0032] Step 5: Make sure J1, J2, J3, D1, D2, D3, and D4 all meet the design requirements;

[0033] Among them, position 1 is the position of the hinge joint 28, position 2 is the position of the hinge support 27 and the peelable gasket 25 thereunder, position 3 is the position of the middle latch box 38, and position 4 is the position of the lock hook of the hook lock assembly 6;

[0034] The four areas are:

[0035] Area 1: located on the xoz surface of the helicopter and is the connection area between the nose cover assembly 1 and the canopy assembly 3 on the top of the nose cover;

[0036] Area 2: located on the xoz surface of the helicopter and is the connection area between the nose cover assembly 1 and the canopy assembly 3 at the bottom of the nose cover;

[0037] Area 3: The connection area between the nose cover assembly 1 and the canopy assembly 3 at the designated height position H, located on the left side of the helicopter. The designated height position H is the position where the step difference direction is in the horizontal direction;

[0038] Area 4: At a designated height position H, the connection area between the nose cover assembly 1 and the canopy assembly 3 is located on the right side of the helicopter. The designated height position H is a position where the step difference direction is in the horizontal direction.

[0039] Among them, from step 1 to step 5, ensure that the middle latch 39 of the middle latch assembly 7 does not contact the middle latch box 38, and the lock hook of the hook lock assembly 6 is positioned and connected reliably;

[0040] In step 1, when judging whether the gap J2 meets the design requirements, ensure that the nose cover is closed when measuring J2.

[0041] The beneficial effects of the present invention are at least:

[0042] 1) Safe and reliable: adopts sealed double insurance structure, the sealing is more reliable;

[0043] 2) Shape: The hinge and hook lock structure do not protrude from the appearance and have shape-maintaining function, reducing aerodynamic resistance;

[0044] 3) Simple to use and easy to maintain: Use a push-type hook lock to lock and open the nose cover, and the gas-elastic strut assists in opening the nose cover. Specific adjustment methods are given, which is simple to use and easy to maintain;

[0045] 4) Wide application range: The configuration of the invention or similar configurations derived from the invention can be used in the structural design of the nose fairing, nose radome or other parts of the cover;

[0046] 5) Manufacturing and assembly friendly: The nose cover seal support assembly and the cockpit cover seal support assembly fully consider the processing deformation and structural assembly error caused by their complex shapes, and reasonably carry out block design;

[0047] At present, the flat threshold maintenance channel structure has been implemented on board, with good actual results. BRIEF DESCRIPTION OF THE DRAWINGS

[0048] Figure 1 It is a schematic diagram of the nose cover structure;

[0049] Figure 2 This is the heading view of the nose cover assembly;

[0050] Figure 3 This is a reverse heading view of the nose cover assembly;

[0051] Figure 4-1 It is a schematic diagram of a C-shaped cross-section of a nose cover sealing support;

[0052] Figure 4-2 This is a schematic diagram of the C-shaped cross-section of the nose cover sealing support;

[0053] Figure 5 This is the along-course view of the canopy assembly;

[0054] Figure 6 The reverse heading view for the canopy assembly;

[0055] Figure 7 It is a cross-sectional schematic diagram of a canopy sealing support member;

[0056] Figure 8 It is a schematic diagram of the structure of the canopy sealing support;

[0057] Fig. 9 The cross-sectional shape of the sealing strip and its installation diagram;

[0058] Fig.10 It is a schematic diagram of the structure of the gas elastic strut assembly;

[0059] Fig.11 is a schematic diagram of the hinge assembly structure;

[0060] Fig.12 This is a schematic diagram of the structure of the heading adjustment toothed plate;

[0061] Fig.13 Schematic diagram of hinge support structure;

[0062] Fig.14 Schematic diagram of hinge joint structure;

[0063] Fig.15 It is a schematic diagram of the hook lock structure;

[0064] Fig.16 Schematic diagram of the structure of the middle latch assembly;

[0065] Fig.17 It is a schematic diagram of the dimensional structure;

[0066] Fig.18 This is a schematic diagram of the measurement area;

[0067] Fig.19 Schematic diagram of the measurement area gap and step difference.

[0068] Among them, 1-nose cover assembly, 2-sealing strip, 3-cockpit cover assembly, 4-gas elastic strut assembly, 5-hinge assembly, 6-hook lock assembly, 7-middle latch assembly, 8-nose cover, 9-nose cover sealing support, 10-handle, 11-front upper skin, 12-left skin, 13-right skin, 14-bottom skin, 15-cockpit cover sealing support, 16-embedded installation groove, 17-docking point, 18-cockpit cover sealing left support, 19-cockpit cover sealing right support, 20-cockpit cover sealing left lower support, 21-cockpit cover sealing right lower support Parts, 22-lower left L-shaped angle material, 23-lower right L-shaped angle material, 24-conductive gasket, 25-peelable gasket, 26-course adjustment toothed plate, 27-hinge support, 28-hinge joint, 29-span adjustment toothed plate, 30-bushing, 31-centerline direction of the two ear pieces, 32-waist-shaped hole, 33-centerline direction, 34-nose structure, 35-fixed end support, 36-movable end support, 37-gas elastic strut, 38-middle pin box, 39-middle pin, 40-middle pin angle material, 41-conical head pin, 42-guide groove, 43-insert waist-shaped hole. DETAILED DESCRIPTION

[0069] The present invention is further described in detail below through specific implementation modes and drawings.

[0070] See also Figure 1 The embodiment of the present invention provides a connection structure for a nose cover, comprising: a gas elastic strut assembly 4, a hinge assembly 5, a hook lock assembly 6 and a middle latch assembly 7; the two ends of the gas elastic strut assembly 4 are respectively connected to the nose cover assembly 1 and the cockpit cover assembly 3; the fixing part of the hinge assembly 5 is connected to the cockpit cover assembly 3,

[0071] The movable part is connected to the nose cover assembly 1; the lock hook of the hook lock assembly 6 is connected to the nose cover assembly 1, and the lock ring is connected to the cockpit cover assembly 3; the middle latch of the middle latch assembly 7 is connected to the nose cover assembly 1, and the middle latch box is connected to the cockpit cover assembly 3;

[0072] like Fig.15 As shown, the nose cover assembly 1 is connected to the cockpit cover assembly 3 through a manually unlocked hook lock assembly 6, the hook lock assembly 6 is fixed to the nose cover assembly 1 and the cockpit cover assembly 3, and the hook lock assembly 6 can be opened and locked and has an adjustment function.

[0073] like Fig.17 As shown, the hinge assembly 5 and the hook lock assembly 6 are both embedded, and the outer surfaces of the structures do not protrude from the outer shape and are the outer shape surfaces; thus, the surface of the nose cover smoothly transitions to the surface of the cockpit cover along the outer shape surface. This structural form reduces the aerodynamic resistance of the nose cover and has a beautiful appearance.

[0074] When opening the hood assembly 1, the hook lock in the hook lock assembly 6 is manually unlocked, and the hand-held hood assembly 1 rotates around the axis of the ear of the hinge assembly 5 to a fixed angle, and the gas-elastic strut assembly 4 maintains the open posture; when closing the hood assembly 1, the gas-elastic strut assembly 4 shortens under the external force, and the hand-held hood assembly 1 rotates around the axis of the ear of the hinge assembly 5. The hood assembly 1 is closed under the guidance of the middle latch assembly 7, and the hook lock in the hook lock assembly 6 is manually locked. Figure 2 , Figure 3 As shown, the nose cover assembly 1 includes a nose cover 8, a nose cover sealing support 9 and a handle 10; the nose cover sealing support 9 is riveted to the nose cover 8, and the handle 10 is screwed to the inner side of the nose cover 8 just below to facilitate the closing operation, and the nose cover sealing support 9 is provided with mounting surfaces for the hook lock assembly 6 and the middle pin assembly 7.

[0075] like Figure 4-2 As shown, in order to avoid the hinge assembly 5, the cross-sectional shape of the area on the nose cover sealing support 9 corresponding to the position of the hinge assembly 5 is an irregular C-shape. Figure 4-1 As shown, the cross-sectional shape of the remaining area of ​​the nose cover sealing support member 9 is C-shaped.

[0076] The nose cover sealing support 9 is only a functional part rather than a load-bearing part of the whole machine, and has a complex shape. It is made of glass fiber, which can reduce the weight of the nose cover assembly 1. Considering the processing deformation of the composite material and the structural assembly error, the nose cover sealing support 9 is divided into two parts, the C-shaped angle material is used to connect the upper part with rivets, and the overlap method is used to connect the lower part with rivets.

[0077] like Figure 5 , Figure 6 As shown, the canopy assembly 3 includes a front upper skin 11, a left skin 12, a right skin 13, a bottom skin 14 and a canopy sealing support 15; the front upper skin 11, the left skin 12, the right skin 13, and the bottom skin 14 form the outer skin of the canopy assembly 3, and the canopy sealing support 15 is riveted at the interface between the canopy assembly 3 and the nose cover assembly 1 of the outer skin.

[0078] The front upper skin 11 is provided with an embedded installation groove 16 for the hinge assembly 5 so that the installation of the hinge assembly 5 does not protrude from the appearance; the cockpit cover sealing support 15 is provided with an installation surface for the hook lock assembly 6 and the middle latch assembly 7. Figure 7 As shown, the cross-sectional shape of the canopy sealing support 15 is C-shaped;

[0079] like Figure 8As shown, the canopy sealing support 15 is a load-bearing member of the whole machine. Considering the riveting with multiple structures and the deformation of complex-shaped composite materials, the canopy sealing support 15 is divided into a canopy sealing left support 18, a canopy sealing right support 19, a canopy sealing left lower support 20, a canopy sealing right lower support 21, a left lower L-shaped angle 22, and a right lower L-shaped angle 23; the canopy sealing left support 18, the canopy sealing right support 19, the canopy sealing left lower support 20, and the canopy sealing right lower support 21 are connected to each other by overlapping with rivets; the front upper skin 11, the left skin 12 and the right skin 13 form a mounting surface of the canopy sealing left support 18 and the canopy sealing right support 19 at the joint 17 with the nose cover 8; the left lower L-shaped angle 22 and the right lower L-shaped angle 23 are riveted with the bottom skin 14 to form a canopy sealing left support 18 and a canopy sealing right support 19; The canopy seals the mounting surface of the lower left support member 20 and the lower right support member 21 of the cockpit canopy; the canopy here has a complex shape and a large curvature change. In order to solve the problem of large deformation and demoulding difficulty in manufacturing composite structural parts, the canopy skin here needs to be reasonably divided into four parts: the front upper skin 11, the left skin 12, the right skin 13 and the bottom skin 14; in order to provide a mounting surface for the sealing strip 2, it is necessary to rivet a support member with a strip mounting surface at the joint between the canopy assembly 3 and the nose cover 8, including the canopy seal left support member 18, the canopy seal right support member 19, the canopy seal left lower support member 20 and the canopy seal right lower support member 21; because the canopy seal support member 15 is a load-bearing member for the entire machine, except for the lower left L-shaped angle member 22 and the lower right L-shaped angle member 23 which are made of aluminum alloy sheet metal, other sealing support members are made of carbon fiber composite material structure;

[0080] See also Figure 1 and Fig. 9 The embodiment of the present invention provides a connection structure further comprising: a sealing strip 2 located between the nose cover assembly 1 and the cockpit cover assembly 3,

[0081] like Fig. 9 As shown, the cross section of the sealing strip 2 is an O-shaped shape with a slot, the slot end is stuck on the C-shaped cross section cockpit cover sealing support 15, the cockpit cover sealing support 15 forms a guide groove 42, and the O-shaped end is pressed on the nose cover sealing support 9 after the nose cover is locked; under the compression action of the cockpit cover sealing support 15 and the nose cover sealing support 9, the sealing strip 2 produces a compression amount of 20% to 30%, and the sealing strip 2 and the cockpit cover sealing support 15 and the nose cover sealing support 9 form a dense and seamless fitting surface, thereby avoiding water leakage between the nose cover and the fuselage structure.

[0082] like Fig.10As shown, the nose cover assembly 1 is opened by the assistance of maintenance personnel through two groups of gas elastic strut assemblies 4, and the two groups of gas elastic strut assemblies 4 are symmetrically arranged; the gas elastic strut assembly 4 comprises a gas elastic strut 37, a fixed end support 35, and a movable end support 36; the gas elastic strut 37 is screwed with the fixed end support 35 and the movable end support 36 by bolts, the fixed end support 35 is riveted with the nose structure 34 by rivets, and the movable end support 36 is screwed with the nose cover assembly 1 by bolts. The gas elastic strut 37 has gas elastic force. When its component in the gravity direction of the nose cover assembly 1 is greater than the gravity of the nose cover assembly 1, the nose cover assembly 1 will automatically lift up under the action of the gas elastic force of the gas elastic strut 37 until the maximum stroke of the gas elastic strut 37 is reached. This design is used to solve the problem in the prior art that if the nose cover is at a high position, the mechanical strut without auxiliary power on it cannot be used to prop up the nose cover.

[0083] like Fig.11 As shown, the hinge assembly 5 includes a conductive gasket 24, a peelable gasket 25, a heading adjustment toothed plate 26, a hinge support 27, a hinge joint 28, a span adjustment toothed plate 29 and a bushing 30; the hinge assembly 5 is screwed to the nose cover assembly 1 and the cockpit cover assembly 3, the hinge support 27 is screwed to the cockpit cover assembly 3 by bolts, the hinge joint 28 is screwed to the nose cover assembly 1 by countersunk screws, the hinge support 27 is connected to the hinge joint 28, and a bushing 30 is provided at the connection between the hinge support 27 and the hinge joint 28; the conductive gasket 24, the peelable gasket 25 and the heading adjustment toothed plate 26 are located directly below the hinge support 27, the span adjustment toothed plate 29 is riveted to the cockpit cover assembly 3, and is located between the hinge joint 28 and the cockpit cover assembly 3.

[0084] The conductive pad 24 is used to transfer the current on the hinge support 27 to the body structure, and the upper and lower surfaces are not painted in contact with other parts;

[0085] The peelable gasket 25 is made of aluminum alloy, with a thickness of 0.1 mm per layer, and is bonded to other parts without spraying paint on the upper and lower surfaces;

[0086] like Fig.12 As shown, the heading adjustment toothed plate 26 is an aluminum alloy structural part, with an adjustment step length of 0.75mm and a tooth bottom in an arc shape. The arc-shaped tooth bottom can avoid stress concentration and improve the fatigue performance of the parts. The heading adjustment toothed plate 26 is fitted with other parts and the upper and lower surfaces are not painted;

[0087] like Fig.13 As shown, the hinge support 27 is an aluminum alloy structural part, the fiber direction L is along the center line direction 31 of the two ear pieces, the adjustment step is 0.75mm, the bottom of the thread is a straight line, the bolt mounting hole is a waist-shaped hole, the waist-shaped hole can provide a heading adjustment, the long side is along the heading, the distance between the two centers of the waist-shaped hole is 4mm, and the upper and lower surfaces are not painted in contact with the lower parts; at the same time, the hinge support 27 is designed with an outer dimensional surface;

[0088] like Fig.14 As shown, the hinge joint 28 is an aluminum alloy structural part, the fiber direction L is along the center line direction 33, the adjustment step is 0.75mm, the bottom of the thread is an arc, the bolt mounting hole is a waist-shaped hole, the long edge is in the span direction, the distance between the two centers of the waist-shaped hole is 4mm, and all the outer surfaces of the parts are painted; the waist-shaped hole can provide adjustment in the span direction.

[0089] The spanwise adjustment toothed plate 29 is an aluminum alloy structural part, with an adjustment step length of 0.75 mm, a straight line at the bottom of the tooth, and all outer surfaces of the part are painted;

[0090] Among all the parts of the hinge assembly 5, except for the hinge support 27 and the hinge joint 28, which have waist-shaped bolt mounting holes, the bolt mounting holes of other parts are all round, and the waist-shaped holes can provide the adjustment amount in the heading and span direction;

[0091] The hinge support 27 and the hinge joint 28 can be connected by a flat head pin, a gasket and a split pin;

[0092] The bushing 30 is made of stainless steel to solve the corrosion problem caused by paint shedding caused by the kinematic pair between the pin and the hole wall of the hinge support 27 and the hinge joint 28;

[0093] The hinge assembly 5 is designed with a peelable gasket and a toothed plate, so that an adjustable shaft connection structure can be formed.

[0094] like Fig.16 As shown, the middle latch assembly 7 is composed of a middle latch box 38, a middle latch 39 and a middle latch angle material 40; wherein, the middle latch 39 is riveted to the nose cover assembly 1, and is provided with a cone head latch 41, the cone head makes it easier for the cone head latch 41 to enter the insertion waist hole 43 at the moment when it contacts the insertion waist hole 43, and then under the guidance of the insertion waist hole 43, the cone head latch 41 completes the corresponding movement; the middle latch angle material 40 is riveted to the cockpit cover assembly 3; the middle latch box 38 is screwed to the middle latch angle material 40 by bolts; the middle latch box 38 is provided with a waist hole 43 for inserting the middle latch 39, and the long side of the waist hole 43 is vertical, and the riveting position of the middle latch 39 on the nose cover assembly 1 can be adjusted along the long side direction of the waist hole 43;

[0095] The bolt hole on the middle latch box 38 that is screwed to the middle latch angle material 40 is a waist-shaped hole, and the long side of the waist-shaped hole is along the direction of the extension, and the middle latch box 38 can be adjusted along the long side of the waist-shaped hole.

[0096] The bolt holes on the middle latch angle material 40 that are screwed to the middle latch box 38 are round holes;

[0097] Due to the design of the vertical long side of the waist-shaped hole 43 and the span-wise long side of the middle latch box 38, the middle latch assembly 7 has vertical and span-wise adjustment functions;

[0098] The structure of the hook lock assembly 6 may refer to the relevant technology, for example, it may include a lock hook and a lock ring.

[0099] When adjusting the gap and step between the nose cover and the fuselage structure, the helicopter is on the landing gear and the seals need to be installed. The adjustment does not require the use of grease. The adjustment criteria are as follows:

[0100] Functional principle: The sealing of the nose cover area is ensured by the compression of the seal; when in the locked position, the position and locking force are controlled to avoid damage to the equipment.

[0101] Aerodynamic principle: Control the step difference and gap to reduce the disturbance of airflow during forward flight.

[0102] like Fig.18 As shown, by adjusting the structures of position 1, position 2, position 3 and position 4, the step difference and gap of the four regions 1, 2, 3 and 4 are adjusted to achieve the purpose of adjusting the step difference and gap to the target range. Position 1 is the position of the hinge joint 28, position 2 is the position of the hinge support 27 and the peelable gasket 25 thereunder, position 3 is the position of the middle latch box 38, and position 4 is the position of the lock hook of the hook lock assembly 6. In the present invention, the definitions of the four regions are as follows:

[0103] Area 1: located on the xoz surface of the helicopter and is the connection area between the nose cover assembly 1 and the canopy assembly 3 on the top of the nose cover;

[0104] Area 2: located on the xoz surface of the helicopter and is the connection area between the nose cover assembly 1 and the canopy assembly 3 at the bottom of the nose cover;

[0105] Area 3: The connection area between the nose cover assembly 1 and the canopy assembly 3 at the designated height position H, located on the left side of the helicopter. The designated height position H is the position where the step difference direction is in the horizontal direction;

[0106] Area 4: the connection area between the nose cover assembly 1 and the canopy assembly 3 at the designated height position H, located on the right side of the helicopter, and the designated height position H is the position where the step difference direction is in the horizontal direction;

[0107] The gap and step difference of each area need to be measured, and the target range of the gap and step difference is set according to the design requirements; Fig.19 As shown, the gap of area 1 is represented by J1, and the step difference of area 1 is represented by D1. And so on J2, J3, J4, D2, D3, D4.

[0108] Position 1 and Position 2 are set within the design range with a step size of 0.75mm. The step size is consistent with the spacing between the teeth of the toothed plate. The peelable gasket is 1.4mm thick, and each sheet is 0.1mm. Compared with the adjustable joint, the adjustment amount of the peelable gasket is relatively small. The gasket is adjusted last. Before any adjustment, it will always be installed with the maximum thickness.

[0109] The measurement should be carried out with the nose cover closed, the hook locked in place and the connection secure;

[0110] The present invention adjusts the structures of position 1, position 2, position 3 and position 4, thereby adjusting the step difference and gap of the four regions 1, 2, 3 and 4, so that the step difference and gap reach the target range. The specific process is as follows:

[0111] 1) Adjust the length of the lock ring of the hook lock assembly 6 at position 4 until the gap J2 in area 2 meets the design requirements;

[0112] When judging whether the gap J2 meets the design requirements, it is necessary to ensure that the nose cover is closed when measuring J2, and the lock hook of the hook lock assembly 6 is positioned and connected reliably;

[0113] Make sure that the middle latch pin 39 of the middle latch pin assembly 7 is not in contact with the middle latch pin box 38;

[0114] 2) Adjust the relative positions of the hinge joint 28 at position 1 and the spanwise adjustment toothed plate 29 until the step difference D3 of area 3 and the step difference D4 of area 4 meet the design requirements;

[0115] When judging whether the step difference D3 of area 3 and the step difference D4 of area 4 meet the design requirements, it is necessary to ensure that the middle latch 39 of the middle latch assembly 7 is not in contact with the middle latch box 38 when measuring the step difference D3 of area 3 and the step difference D4 of area 4; and the lock hook positioning and connection of the hook lock assembly 6 are reliable.

[0116] 3) Adjust the relative positions of the hinge support 27 at position 2 and the heading adjustment toothed plate 26 until the gap J1 in area 1 meets the design requirements;

[0117] When judging whether the gap J1 of area 1 meets the design requirements, it is necessary to ensure that the middle latch 39 of the middle latch assembly 7 is not in contact with the middle latch box 38 when measuring the gap J1 of area 1; and the lock hook of the hook lock assembly 6 is positioned and connected reliably.

[0118] 4) Adjust the thickness of the peelable gasket 25 at position 1, with the gap J3 of area 3 and the gap J4 of area 4 meeting the requirements first, until the step difference D1 of area 1 and the step difference D2 of area 2 meet the design requirements;

[0119] When judging whether the step difference D1 of area 1 and the step difference D2 of area 2 meet the design requirements, it is necessary to ensure that the middle latch 39 of the middle latch assembly 7 is not in contact with the middle latch box 38 when measuring the step difference D1 of area 1 and the step difference D2 of area 2; and the lock hook positioning and connection of the hook lock assembly 6 are reliable.

[0120] Before removing the gasket, mark the position of the toothed gasket that has been adjusted; this saves the need for further adjustment during reassembly.

[0121] 5) Make sure J1, J2, J3, D1, D2, D3, and D4 all meet the design requirements;

[0122] And ensure that the middle latch 39 of the middle latch assembly 7 does not contact the middle latch box 38; and the lock hook of the hook lock assembly 6 is positioned and connected reliably;

[0123] After the step difference and gap adjustment of area 1, area 2, area 3 and area 4 are completed, it should be checked whether the sealing strip 2 is in uniform contact with the head cover assembly 1, and vaseline should be applied on the outer edge of the O-shaped end of the sealing strip 2 (the side close to the head cover assembly 1); if the vaseline does not leave any mark on the head cover sealing support 9 of the head cover assembly 1, it is determined that the sealing strip 2 is not in contact with the head cover assembly 1. At this time, repeat the above steps 1) to 4) until the vaseline marks on the head cover sealing support 9 of the head cover assembly 1 are evenly distributed and there are no blank spaces; then, clean up the vaseline.

[0124] The above only expresses the implementation mode of the present invention, and its description is relatively specific and detailed, but it cannot be understood as limiting the scope of the patent. It should be pointed out that for ordinary technicians in this field, several modifications and improvements can be made without departing from the concept of the present invention, which all belong to the protection scope of the present invention. In addition, the parts not detailed in the present invention are all conventional technologies.

Claims

1. A connection structure for a nose cover, characterized in that: include: Gas elastic strut assembly, hinge assembly, hook lock assembly, center latch assembly, The two ends of the gas-elastic strut assembly are respectively connected to the nose cover assembly and the cockpit cover assembly; the fixed part of the hinge assembly is connected to the cockpit cover assembly, and the movable part is connected to the nose cover assembly; the lock hook of the hook lock assembly is connected to the nose cover assembly, and the lock ring is connected to the cockpit cover assembly; the middle latch pin of the middle latch pin assembly is connected to the nose cover assembly, and the middle latch pin box is connected to the cockpit cover assembly; When opening the nose hood assembly, the hook lock in the hook lock assembly is unlocked, so that the nose hood assembly rotates around the ear axis of the hinge assembly to a fixed angle, and the nose hood assembly is supported by the gas elastic strut assembly to keep the nose hood assembly in an open posture; when closing the nose hood assembly, the gas elastic strut assembly shortens under the external force, so that the nose hood assembly rotates around the ear axis of the hinge assembly, and the nose hood assembly is closed under the guidance of the middle pin assembly, locking the hook lock in the hook lock assembly.

2. The connection structure according to claim 1, characterized in that: The nose cover assembly includes: a nose cover, a nose cover sealing support and a handle; The nose cover sealing support is riveted on the nose cover, the handle is screwed to the lower part of the inner side of the nose cover, and the nose cover sealing support is provided with a mounting surface for the hook lock assembly and the middle latch assembly; The cross-sectional shape of the area on the nose cover sealing support corresponding to the position of the hinge assembly is a special C-shape; the cross-sectional shape of the remaining area of ​​the nose cover sealing support is a C-shape; The nose cover sealing support is made of glass fiber; the nose cover sealing support is divided into two parts, the left and right parts are connected by rivets using C-shaped angle materials at the top and connected by rivets using overlap at the bottom.

3. The connection structure according to claim 2, characterized in that: The canopy assembly includes: a front upper skin, a left skin, a right skin, a bottom skin and a canopy sealing support; the front upper skin, the left skin, the right skin and the bottom skin form the outer skin of the canopy assembly, and the canopy sealing support is riveted at the interface between the canopy assembly of the outer skin and the nose cover assembly; An embedded mounting groove for the hinge assembly is provided on the front upper skin; a mounting surface for a hook lock assembly and a middle latch assembly is provided on the canopy sealing support; the cross-sectional shape of the canopy sealing support is C-shaped; The canopy sealing support comprises a canopy sealing left support, a canopy sealing right support, a canopy sealing left lower support, a canopy sealing right lower support, a left lower L-shaped angle bar, and a right lower L-shaped angle bar; the canopy sealing left support, the canopy sealing right support, the canopy sealing left lower support, and the canopy sealing right lower support are connected by rivets in an overlapping manner; the front upper skin, the left skin, and the right skin form mounting planes for the canopy sealing left support and the canopy sealing right support at the joints with the nose cover; the left lower L-shaped angle bar and the right lower L-shaped angle bar are riveted to the bottom skin to form mounting surfaces for the canopy sealing left lower support and the canopy sealing right lower support; the canopy sealing left support, the canopy sealing right support, the canopy sealing left lower support, and the canopy sealing right lower support adopt a carbon fiber composite material structure.

4. The connection structure according to claim 3, characterized in that: The sealing strip between the nose cover assembly and the canopy assembly, The cross section of the sealing strip is an O-shaped strip with a slot shape, the slot end is stuck on the C-shaped cross section canopy sealing support, the canopy sealing support forms a guide groove, and the O-shaped end is pressed on the nose cover sealing support after the nose cover is locked.

5. The connection structure according to claim 1, characterized in that: The nose cover assembly is opened with the assistance of maintenance personnel by two groups of gas-elastic strut assemblies, and the two groups of gas-elastic strut assemblies are arranged symmetrically; the gas-elastic strut assembly includes: a gas-elastic strut, a fixed end support, and a movable end support; the gas-elastic strut is screwed to the fixed end support and the movable end support, the fixed end support is riveted to the nose structure, and the movable end support is screwed to the nose cover assembly.

6. The connection structure according to claim 1, characterized in that: The hinge assembly includes: a conductive gasket, a peelable gasket, a heading adjustment toothed plate, a hinge support, a hinge joint, a span adjustment toothed plate and a bushing; the hinge assembly is screwed to the nose cover assembly and the canopy assembly, the hinge support is screwed to the canopy assembly, the hinge joint is screwed to the nose cover assembly, the hinge support and the hinge joint are connected by a flat pin, a gasket and a cotter pin, and a bushing is provided at the connection between the hinge support and the hinge joint; the conductive gasket, the peelable gasket and the heading adjustment toothed plate are located directly below the hinge support; the span adjustment toothed plate is riveted to the canopy assembly, and is located between the hinge joint and the canopy assembly.

7. The connection structure according to claim 6, characterized in that: The peelable gasket is made of aluminum alloy, with a thickness of 0.1 to 0.5 mm per layer; the heading adjustment toothed plate is an aluminum alloy structural part, with an adjustment step of 0.5 to 0.75 mm, and the tooth bottom is arc-shaped; The hinge support is an aluminum alloy structural part, the fiber direction L is parallel to the centerline direction, the adjustment step is 0.5-0.75mm, and the bottom of the thread is a flat straight line; the hinge support is provided with a bolt mounting hole for connecting the canopy assembly, the bolt mounting hole is a waist-shaped hole, the long side is along the heading, and the distance between the two centers of the waist-shaped hole is 2-4mm; at the same time, the hinge support is provided with an outer shape shaping surface for shaping; the waist-shaped hole on the hinge support is used to provide the heading adjustment amount; The hinge joint is an aluminum alloy structural part. The fiber direction L is parallel to the center line direction. The adjustment step is 0.75mm. The bottom of the thread is arc-shaped. The hinge joint is provided with a waist-shaped hole for bolt mounting for connecting the head cover assembly. The long edge is in the span direction. The distance between the two centers of the waist-shaped hole is 2 to 4mm. The waist-shaped hole on the hinge joint is used to provide the adjustment amount in the span direction. The spanwise adjustment toothed plate is an aluminum alloy structural part, the adjustment step length is 0.5 to 0.75 mm, and the tooth bottom is a straight line.

8. The connection structure according to claim 1, characterized in that: The middle latch assembly is composed of a middle latch box, a middle latch and a middle latch angle material; wherein the middle latch is riveted to the nose cover assembly and is provided with a cone head latch; the middle latch angle material is riveted to the cockpit cover assembly; the middle latch box is screwed to the middle latch angle material; the middle latch box is provided with a waist-shaped hole for inserting the middle latch, and the long edge of the waist-shaped hole is vertical; The bolt hole on the middle latch box that is screwed to the middle latch angle material is a waist-shaped hole, and the long side of the waist-shaped hole extends in the direction; the bolt hole on the middle latch angle material that is screwed to the middle latch box is a round hole.

9. A method for adjusting the connection structure of a nose cover, characterized in that: Applied to the connection structure according to any one of claims 1 to 8, the method comprises: Step 1: Adjust the length of the lock ring of the hook lock assembly at position 4 until the gap J2 in area 2 meets the design requirements; Step 2: Adjust the relative positions of the hinge joint at position 1 and the spanwise adjustment toothed plate until the step difference D3 of area 3 and the step difference D4 of area 4 meet the design requirements; Step 3: Adjust the relative positions of the hinge support at position 2 and the heading adjustment toothed plate until the gap J1 in area 1 meets the design requirements; Step 4, adjusting the thickness of the peelable gasket at position 1, with the gap J3 of area 3 and the gap J4 of area 4 meeting the design requirements first, until the step difference D1 of area 1 and the step difference D2 of area 2 meet the design requirements; Step 5: Make sure J1, J2, J3, D1, D2, D3, and D4 all meet the design requirements; Among them, position 1 is the position of the hinge joint, position 2 is the position of the hinge support and the peelable gasket below it, position 3 is the position of the middle latch box, and position 4 is the position of the lock hook of the hook lock assembly; The four areas are: Area 1: located on the xoz surface of the helicopter and is the connection area between the nose cover assembly and the canopy assembly on the top of the nose cover; Area 2: located on the xoz surface of the helicopter and is the connection area between the nose cover assembly and the canopy assembly at the bottom of the nose cover; Area 3: The connection area between the nose cover assembly and the canopy assembly at the specified height position H, located on the left side of the helicopter. The specified height position H is the position where the step difference direction is in the horizontal direction. Area 4: At the specified height position H, the connection area between the nose cover assembly and the canopy assembly is located on the right side of the helicopter. The specified height position H is the position where the step difference direction is in the horizontal direction.

10. The method according to claim 9, characterized in that From step 1 to step 5, ensure that the middle latch of the middle latch assembly does not contact the middle latch box, and the lock hook of the hook lock assembly is positioned and connected reliably; In step 1, when judging whether the gap J2 meets the design requirements, ensure that the nose cover is closed when measuring J2.

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