Ball joint type rope lock cover and installation method thereof

Abstract

The present application relates to the technical field of aircraft component structure design, and particularly relates to a ball hinge type rope locking port cover and a mounting method thereof, which comprises a port cover plate, front and rear end lugs are arranged on the port cover plate, and a limiting structure is arranged on both sides of the port cover plate; a connecting unit is arranged on the front end lug; the connecting unit is provided with a spherical hinge and an adjusting assembly; and a non-concentric connection hole is arranged on the rear end lug. The technical scheme is characterized in that the non-concentric connection hole, the adjusting assembly and the related limiting structure are arranged, thus perfectly solving the gap and step difference problems existing in the prior art. The step difference between the locking port cover and the front end fuselage frame is eliminated by the internal adjusting assembly, the gap between the locking port cover and the front end fuselage frame is eliminated by the limiting structure, and the step difference and the gap between the locking port cover and the rear end fuselage frame are eliminated by the upward tightening force of the rope, so that the step difference and the gap between the locking port cover and the surrounding structure can be guaranteed within the design requirement range, and the flight safety is not affected.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft component structure design, and particularly relates to a ball hinge type rope locking hatch cover and a mounting method thereof. BACKGROUND

[0002] Hatch covers are widely used in the field of aircraft, and as the main assembly channel and maintenance channel of the aircraft, the hatch cover is an important part of the aircraft body. Meanwhile, the tenth volume of the aircraft design manual classifies the hatch cover into three types, i.e., A, B and C, according to the connection form of the hatch cover and the hatch frame and the frequency of disassembly. Among them, the A type is a hatch cover that can be disassembled without tools, and the opening or closing time is less than 1 min; the B type is a hatch cover that can be disassembled with tools, and the opening or closing time is between 1 min and 10 min; and the C type is a hatch cover that is not often disassembled, and the opening or closing time depends on the number of screws on the hatch cover. However, with the gradual diversification of the equipment and functions of the aircraft, the requirements for use and maintenance are also increasingly diversified. For some special aircraft, special hatch covers may be required when performing special tasks, such as a parachute airbag recoverable small unmanned aerial vehicle, which needs a hatch cover that can be opened or separated from the fuselage during flight.

[0003] To this end, the Chinese patent application No. CN201620995445.2 discloses a swan neck hinge quick-release hatch cover, which comprises a hatch cover plate, a hatch frame, a hinge support, a through bar, a swan neck hinge and a button lock mounted on the hatch cover plate. The hatch cover plate is matched with the hatch frame mounted on the aircraft skin. One end of the swan neck hinge is fixedly installed on the hatch cover plate, and the other end of the swan neck hinge is connected with the hinge support fixedly installed on the hatch frame through the through bar. The swan neck hinge quick-release hatch cover can be quickly opened or closed without using tools, and meets the requirements of aircraft aerodynamics, stealth and waterproof. However, the hatch cover structure has the following defects:

[0004] 1) There is a step difference between the hatch cover and the surrounding structure, that is, the hatch cover is more protruding than the original aircraft shape, so that a gap exists. There is a gap around the hatch cover. The gap and the step difference will bring flight safety hazards. During flight, the airflow flows into the airbag cabin from the gap or the step difference between the hatch cover and the surrounding structure, and the strong airflow will tear the bottom of the airbag and blow it out of the body from the separation gap or the step difference, resulting in no airbag use during landing, and causing safety hazards during landing.

[0005] 2) The structure of the hatch cover (such as a swan neck structure or a spherical hinge) has a risk of jamming in application. That is, due to the influence of part manufacturing errors, assembly deformation, structure hole fitting and the like, the hatch cover may interfere with the body structure during the movement and turning process, thereby causing jamming, resulting in the hatch cover being unable to be normally thrown and placed, and easily causing flight safety accidents.

[0006] 3) The installation of the cover cannot be standardized, and the covers cannot be used interchangeably. SUMMARY

[0007] The present application aims at the deficiencies of the prior art, and provides a ball hinge type rope locking cover and an installation method thereof, which are as follows.

[0008] A ball hinge type rope locking cover comprises a cover plate, one side of the cover plate facing the aircraft body is provided with a front end ear piece and a rear end ear piece at positions close to the two ends, respectively, and limit notches are formed in the two sides of the cover plate, and limit blocks are fitted in the limit notches; at least one connecting unit for connecting the front end of the aircraft body frame is arranged on the front end ear piece; the connecting unit comprises a spherical hinge fixedly connected with the front end ear piece, and an adjusting assembly for adjusting and limiting the activity range of the spherical hinge; a non-concentric connecting hole for connecting the rope with the rear end of the aircraft body frame is formed in the rear end ear piece.

[0009] Preferably, the adjusting assembly comprises an adjusting support, a locking nut, an adjusting bolt and a mounting nut; the mounting nut is riveted on the adjusting support, and the adjusting bolt acts on the spherical hinge after passing through the locking nut, the adjusting support and the mounting nut in sequence.

[0010] Preferably, the cover plate is made of a composite material of carbon cloth fabric.

[0011] Based on the above-mentioned ball hinge type rope locking cover, the present application provides an installation method, which comprises the following steps:

[0012] S1. According to the aircraft model, the cover is assembled under the assistance of the auxiliary assembly tooling to obtain a cover blank;

[0013] S2. The limit blocks are riveted on the longitudinal beam of the aircraft body under the assistance of the assembly positioning tooling;

[0014] S3. The adjusting support with the mounting nut is riveted on the front end of the aircraft body frame corresponding to the self-positioning hole pre-set on the front end of the aircraft body frame, and the adjusting bolt and the locking nut are installed according to the structure of the adjusting assembly;

[0015] S4. The spherical hinge on the cover blank is aligned and placed in the limit connection groove pre-set on the front end of the aircraft body frame, then the heading position of the cover plate is adjusted according to the position of the limit block, and the limit notches on the cover plate are adaptively repaired;

[0016] S5. After the rope is passed through the non-concentric connecting hole on the rear end ear piece and the cover connecting hole on the rear end of the aircraft body frame, the rope is bound and fixed, so that the cover plate and the rear end of the aircraft body frame have no step difference, that is, the rear end of the cover is installed in place;

[0017] S6, using the adjusting assembly to eliminate the step difference between the gusset and the front end fuselage frame of the airplane.

[0018] Preferably, in step S1, the gusset assembly comprises the following steps:

[0019] S11, marking points on the gusset, the front end tab and the rear end tab with the aid of the assembly positioning fixture;

[0020] S12, drilling positioning installation holes at the marked points on the gusset and the front end tab;

[0021] S13, drilling non-concentric connecting holes at the marked points on the rear end tab;

[0022] S14, connecting the front end tab and the rear end tab to the gusset by using fasteners to cooperate with the corresponding positioning installation holes on the gusset;

[0023] S15, connecting the spherical hinge to the front end tab by using fasteners to cooperate with the corresponding positioning installation holes on the front end tab.

[0024] Preferably, in step S6, using the adjusting assembly to eliminate the step difference between the gusset and the front end fuselage frame of the airplane comprises the following steps:

[0025] S61, making axial travel fine adjustment to the adjusting bolt to generate force at the end of the spherical hinge to change the attitude of the spherical hinge;

[0026] S62, fixing the adjusting bolt by using the locking nut.

[0027] Preferably, in step S61, before making axial travel fine adjustment to the adjusting bolt, the number of turns P that the adjusting bolt needs to rotate is obtained according to the step difference H between the gusset and the front end fuselage frame of the airplane, comprising the following steps:

[0028] S611, establishing a relationship between the step difference H and the number of turns P wherein R is the rotational radius of the spherical hinge to the front end edge of the gusset, N is the pitch of the adjusting bolt, and r is the rotational radius of the spherical hinge to the adjusting bolt;

[0029] S612, calculating the number of turns P corresponding to all different step differences H based on the relationship between the step difference H and the number of turns P;

[0030] S613, establishing a relationship table using all step differences H and the number of turns P;

[0031] S614, measuring the target step difference by using a measuring tool;

[0032] S615, querying the corresponding number of turns according to the target step difference in the relationship table.

[0033] The beneficial technical effects brought by the present application are as follows:

[0034] 1) The technical solution discloses a ball hinge type rope locking port cover structure, which perfectly solves the gap and step difference problems existing in the prior art by setting non-concentric connecting holes, adjusting assemblies and related limiting structures. Specifically, the step difference between the locking port cover and the front end of the aircraft body frame is eliminated by the internal adjusting assembly, and the ball hinge is fixed by the adjusting assembly to ensure that the ball hinge and the adjusting assembly are seamlessly fitted, greatly improving the installation quality of the port cover. The gap between the locking port cover and the front end of the aircraft body frame is eliminated by the limiting structure, i.e., the limiting block is used to limit the front and back movement of the port cover plate along the aircraft heading, ensuring seamless fitting and making the port cover plate and the aircraft body structure have no step difference. The step difference and the gap between the locking port cover and the rear end of the aircraft body frame are eliminated by the upward tightening force of the rope. In summary, the step difference and the gap between the locking port cover and the surrounding structure can be ensured within the design requirement range, and the flight safety is not affected.

[0035] 2) The technical solution discloses a mounting method of the ball hinge type rope locking port cover. In the method, the sizes of the parts of the locking port cover are unified, and the adjustment amount of the adjusting assembly is unified by tabulation, which can well solve the part manufacturing errors, assembly deformation, structure opening fitting and other influences existing in the prior art, greatly improve the installation fault tolerance of the locking port cover, and reduce the failure and unqualified product rate of the locking port cover.

[0036] 3) The technical solution discloses a mounting method of the ball hinge type rope locking port cover, which forms a standardized operation process for the installation work of the locking port cover, greatly reduces the installation time and the operating personnel, improves the installation quality, can ensure that any port cover can be interchanged on any aircraft, and greatly improves the outfield support. BRIEF DESCRIPTION OF DRAWINGS

[0037] Figure 1 It is a schematic diagram of the overall structure of the locking port cover.

[0038] Figure 2 It is a schematic diagram of the structure of the port cover body.

[0039] Figure 3 It is a schematic diagram of the local structure of the front end of the port cover.

[0040] Figure 4 It is an axial view of the mounting structure of the locking port cover.

[0041] In the drawings:

[0042] 1, cover plate; 2, front end ear; 3, rear end ear; 4, limiting notch; 5, limiting block; 6, spherical hinge; 7, adjusting assembly; 7.1, adjusting support; 7.2, locking nut; 7.3, adjusting bolt; 7.4, mounting nut; 8, non-concentric connecting hole; 9, rope; 10, front end fuselage frame of airplane; 11, rear end fuselage frame of airplane; 12, airplane body longitudinal beam; 13, cover connecting hole. DETAILED DESCRIPTION

[0043] In order to make the purpose, technical scheme and advantages of the application clearer, the technical scheme in the application will be described clearly and completely below in combination with the drawings in the application. Obviously, the described embodiments are part of the embodiments of the application, rather than all the embodiments.

[0044] Therefore, the following detailed description of the application provided in the drawings is not intended to limit the scope of the claimed application, but only represents selected embodiments of the application. Based on the embodiments in the application, all other embodiments obtained by those of ordinary skill in the art without creative labor are within the scope of protection of the application.

[0045] Embodiment 1

[0046] The embodiment discloses a spherical hinge type rope locking cover, which is a basic embodiment of the application and comprises a cover plate 1. One side of the cover plate 1 facing the airplane body is provided with a front end ear 2 and a rear end ear 3 near the two ends, respectively. Limiting notches 4 are formed in the two sides of the cover plate 1, and limiting blocks 5 are fitted in the limiting notches 4. At least one connecting unit for connecting the front end fuselage frame 10 of the airplane is arranged on the front end ear 2. The connecting unit comprises a spherical hinge 6 fixedly connected with the front end ear 2 and an adjusting assembly 7 for adjusting and limiting the activity range of the spherical hinge 6. A non-concentric connecting hole 8 for connecting the rope 9 with the rear end fuselage frame 11 of the airplane is formed in the rear end ear 3.

[0047] The working principle of the technical solution is as follows: in actual use, the connecting unit is riveted on the front end fuselage frame 10 of the airplane, the limiting block 5 is riveted on the airplane body longitudinal beam 12, and then the spherical hinge 6 on the cover plate 1 is aligned with the pre-set limiting connection groove on the front end fuselage frame 10 of the airplane to preliminarily position the cover. After the cover plate 1 is placed, the cover plate 1 is installed in place and is attached to the airplane body longitudinal beam 12, the limiting gap 4 cooperates with the limiting block 5 to limit the cover plate 1 in the flight direction of the airplane, so that the cover plate 1 cannot move. The rope 9 passes through the non-concentric connection hole 8 and the pre-set cover connection hole 13 on the rear end fuselage frame 11 of the airplane to connect the rear end of the cover with the rear end fuselage frame 11 of the airplane, wherein the non-concentric connection hole 8 means that when the cover plate 1 is connected with the rear end fuselage frame 11 of the airplane through the rear end lug 3, the non-concentric connection hole 8 and the hole (cover connection hole 13) on the rear end fuselage frame 11 of the airplane participating in the connection are in a non-concentric state, so that the rope 9 can provide a diagonal upward tightening force when it is tightened, and the cover plate 1 can be tightly attached to the structure of the airplane, preventing the occurrence of steps. After the rear end of the cover is fixed, the attitude of the spherical hinge 6 is adjusted through the adjusting assembly 7 to eliminate the steps between the cover plate 1 and the front end fuselage frame of the airplane, and then the spherical hinge 6 is fixed through the adjusting assembly 7.

[0048] In the technical solution, the steps between the locking cover and the front end fuselage frame 10 of the airplane are eliminated by the internal adjusting assembly 7, the gap between the locking cover and the front end fuselage frame 10 of the airplane is eliminated by the limiting block 5, the steps and the gap between the locking cover and the rear end fuselage frame 11 of the airplane are eliminated by the diagonal upward tightening force of the rope 9, and the steps and the gap between the locking cover and the surrounding structure can be guaranteed within the design requirement range, which will not affect the flight safety.

[0049] Embodiment 2

[0050] The embodiment discloses a spherical hinge type rope locking cover, which is a preferred embodiment of the application and comprises a cover plate 1, the side of the cover plate 1 facing the airplane body is provided with a front end lug 2 and a rear end lug 3 near the two ends, respectively, limiting gaps 4 are formed in the two sides of the cover plate 1, and the limiting gaps 4 are adapted to fit limiting blocks 5; at least one connecting unit for connecting the front end fuselage frame 10 of the airplane is arranged on the front end lug 2; the connecting unit comprises a spherical hinge 6 fixedly connected with the front end lug 2 and an adjusting assembly 7 for adjusting and limiting the movement range of the spherical hinge 6; and a non-concentric connection hole 8 for connecting the rope 9 with the rear end fuselage frame 11 of the airplane is formed in the rear end lug 3.

[0051] Furthermore, the adjustment assembly 7 includes an adjustment support 7.1, a locking nut 7.2, an adjustment bolt 7.3, and a mounting nut 7.4; the mounting nut 7.4 is riveted to the adjustment support 7.1, and the adjustment bolt 7.3 passes through the locking nut 7.2, the adjustment support 7.1, and the mounting nut 7.4 in sequence, and then acts on the spherical hinge 6.

[0052] Furthermore, in order to limit the deformation of the cover plate 1 and make it recyclable, the cover plate 1 is made of a composite material of carbon cloth fabric (such as HF30C grade material).

[0053] In this technical solution, considering that the spherical hinge 6 serves as the front fixed fulcrum, it is necessary to prevent its deformation as much as possible; therefore, steel is used as the material. After the spherical hinge 6 is placed into the preset limiting connection groove on the front fuselage frame 10 of the aircraft, the spherical hinge 6 and the limiting connection groove fit together along the spanwise direction of the aircraft. The opening size of the limiting connection groove in the longitudinal direction of the aircraft is much larger than the structural size of the spherical hinge 6, ensuring that the flipping movement trajectory of the spherical hinge 6 is free from interference. The preset limiting notch 4 on the cover plate 1 needs to be smaller than the size of the limiting block 5, so that when installing the cover plate 1, the limiting notch 4 can be adjusted according to the position of the limiting block 5 to ensure the fit between the limiting notch 4 and the limiting block 5. In addition, the cooperation between the limiting notch 4 and the limiting block 5 also prevents the cover plate 1 from moving towards the rear fuselage frame 11 of the aircraft under the tension of the rope 9, thus preventing a gap from appearing between the cover plate 1 and the front fuselage frame 10 of the aircraft.

[0054] Furthermore, during installation, the adjusting support 7.1 is riveted to the web and ribs of the aircraft front fuselage frame, and the mounting nut 7.4 is riveted to the adjusting support 7.1. The adjusting bolt 7.3 passes through the locking nut 7.2, the adjusting support 7.1, and the mounting nut 7.4 in sequence before contacting the spherical hinge 6. The upper and lower strokes are finely adjusted by the adjusting bolt 7.3 to change the attitude (rotation arc) of the spherical hinge 6, ensuring that the step difference between the cover plate 1 and the front fuselage frame 10 of the aircraft is reduced or even eliminated. After adjustment, the adjusting bolt 7.3 is finally fixed by the locking nut 7.2, which also restricts the movement of the spherical hinge 6.

[0055] Furthermore, the limit block 5 riveted to the longitudinal beam 12 of the aircraft fuselage is positioned using an assembly positioning fixture (positioning with an assembly positioning fixture is a common technical means in the assembly process, which is not strongly related to this technical solution and is not recommended to be described). The relative position of the limit block 5 on the longitudinal beam 12 of the aircraft fuselage remains consistent in any batch of aircraft. Therefore, the installation position of the upper cover plate 1 of any batch of aircraft can also remain consistent. In this way, all the locking covers that are adjusted and repaired can be used on all aircraft in this series, and have extremely high interchangeability.

[0056] When the locking hatch needs to be opened and thrown, the rope 9 is cut off, the constraint of the rope 9 is released, and the hatch plate 1 is in a needle flipping motion under the action of its own gravity, aerodynamic force and airbag extrusion force (the rear end of the hatch is downward, and the front end of the hatch is upward); after a certain stroke, the front end of the hatch ball hinge 6 is no longer in contact with the adjusting bolt 7.3, the restriction of the adjusting bolt 7.3 on the ball hinge 6 is released, and the ball hinge 6 is separated from the rear end of the aircraft body frame 11, so that the locking hatch is separated from the aircraft body. Among them, the aerodynamic force is the airflow force received by the aircraft itself when flying, and the airbag extrusion force is the force generated by the airbag inflation.

[0057] Embodiment 3

[0058] The embodiment discloses a mounting method of a ball hinge type rope locking hatch, which is a preferred embodiment of the present application, and is used for the ball hinge type rope 9 locking hatch described in embodiment 1 or embodiment 2, and comprises the following steps.

[0059] S1, according to the aircraft model, the hatch assembly is performed under the assistance of a jig assembly, and a hatch blank is obtained;

[0060] S2, the limiting block 5 is riveted on the aircraft body longitudinal beam 12 under the assistance of an assembly positioning jig;

[0061] S3, the adjusting support with the mounting nut 7.4 is riveted on the front end of the aircraft body frame 10 corresponding to the self-positioning hole pre-set on the front end of the aircraft body frame 10, and the adjusting bolt and the locking nut 7.2 are mounted according to the structure of the adjusting assembly 7;

[0062] S4, the ball hinge 6 on the hatch blank is aligned and placed in the limiting connection groove pre-set on the front end of the aircraft body frame 10, then the heading position of the hatch plate 1 is adjusted according to the position of the limiting block 5, and the limiting notch 4 on the hatch plate 1 is adaptively repaired;

[0063] S5, the rope 9 is passed through the non-concentric connection hole 8 on the rear end of the ear 3 and the hatch connection hole 13 on the rear end of the aircraft body frame 11, and then the rope 9 is bound and fixed, so that the hatch plate 1 is not stepped with the rear end of the aircraft body frame 11, that is, the rear end of the hatch is mounted in place;

[0064] S6, the adjusting assembly 7 is used to eliminate the step difference between the hatch plate 1 and the front end of the aircraft body frame 10.

[0065] Embodiment 4

[0066] The embodiment discloses a mounting method of a ball hinge type rope locking hatch, which is a preferred embodiment of the present application, and is used for the ball hinge type rope 9 locking hatch described in embodiment 1 or embodiment 2, and comprises the following steps.

[0067] S1, according to the aircraft model, under the assistance of the under-frame assembly tool, the hatch assembly is assembled to obtain the hatch blank. The hatch assembly includes the following steps:

[0068] S11, under the assistance of the assembly positioning tool, points are drawn on the hatch plate 1, the front end ear piece 2 and the rear end ear piece 3; the under-frame assembly tool is a general technical assembly tool for the aircraft, that is, a general technical point assembly, the positions of the drawn points are unified by the under-frame assembly tool, and it can be understood that the under-frame assembly tool is a mounting reference point.

[0069] S12, positioning installation holes are drilled at the points drawn on the corresponding hatch plate 1 and the front end ear piece 2; the drilled positioning installation holes have two effects: first, the holes are equipped with fasteners, which connect the hatch and the ear piece and the spherical hinge 6 into one body by the fasteners; second, the positions of all positioning installation holes are consistent, so that all the parts of the locking hatch are consistent, and the parts of the locking hatch that are further locked can be universally interchangeable, and if some parts of the locking hatch after being thrown are deformed, the deformed parts can be replaced based on the universal interchangeability;

[0070] S13, a non-concentric connecting hole 8 is drilled at the point drawn on the corresponding rear end ear piece 3;

[0071] S14, the front end ear piece 2 and the rear end ear piece 3 are connected with the hatch plate 1 into one body by cooperating the fasteners with the corresponding positioning installation holes on the hatch plate 1;

[0072] S15, the spherical hinge 6 is connected with the front end ear piece 2 into one body by cooperating the fasteners with the corresponding positioning installation holes on the front end ear piece 2, which can ensure that the positions of the spherical hinge 6, the front end ear piece 2 and the rear end ear piece 3 on each locking hatch are consistent.

[0073] S2, under the assistance of the assembly positioning tool, the limiting block 5 is riveted on the aircraft body longitudinal beam 12;

[0074] S3, corresponding to the self-positioning hole pre-set on the aircraft front end fuselage frame 10, the adjusting support with the mounting nut 7.4 is riveted on the aircraft front end fuselage frame 10, and the adjusting bolt and the locking nut 7.2 are installed according to the structure of the adjusting assembly 7;

[0075] S4, the spherical hinge 6 on the hatch blank is aligned and placed into the limiting connection groove pre-set on the aircraft front end fuselage frame 10, then the heading position of the hatch plate 1 is adjusted according to the position of the limiting block 5, and the limiting gap 4 on the hatch plate 1 is adaptively repaired, that is, the three edges of the limiting gap 4 are trimmed to ensure that the limiting block 5 and the three edges of the limiting gap 4 are closely fitted;

[0076] S5, after the rope 9 is passed through the non-concentric connection hole 8 on the rear end lug 3 and the cover connection hole 13 on the aircraft rear end fuselage frame 11, the rope 9 is tied and fixed, so that the cover plate 1 is not stepped with the aircraft rear end fuselage frame 11, that is, the cover rear end is installed in place;

[0077] S6, the step difference between the cover plate 1 and the aircraft front end fuselage frame 10 is eliminated by using the adjusting assembly 7. Wherein, the step difference between the cover plate 1 and the aircraft front end fuselage frame 10 is eliminated by using the adjusting assembly 7, including the following steps:

[0078] S61, the adjusting bolt 7.3 is axially adjusted, so that the adjusting bolt 7.3 generates a force at the end of the spherical hinge 6 to change the attitude of the spherical hinge;

[0079] S62, the adjusting bolt 7.3 is fixed by the locking nut 7.2.

[0080] When it is needed to throw away the locking cover, the rope 9 is released, the cover plate 1 is opened by itself under the action of the aircraft aerodynamic force and the airbag extrusion force, and then the spherical hinge 6 is separated from the aircraft front end fuselage frame 10, so that the throwing away of the locking cover is realized. The recovered locking cover is visually inspected, if the cover plate 1, the spherical hinge 6, the front end lug 2 and the rear end lug 3 and other parts are not damaged or deformed, the recovered locking cover can be continuously installed and used according to steps S2-S6; if the recovered locking cover cannot be used, the usable parts of the recovered locking cover can be reassembled together with the spare parts according to the way of step S1 to participate in the installation and use, without additional repair and test work, so that any locking cover and any aircraft can be used universally.

[0081] Through the above, the recovered structure is installed in the airbag cabin or the parachute cabin, and the use of the airbag will not be affected.

[0082] Embodiment 5

[0083] The embodiment discloses a mounting method of a spherical hinge type rope locking cover, which is a preferred embodiment of the present application, that is, embodiment 4, before the adjusting bolt 7.3 is axially adjusted in step S61, the number of turns P that the adjusting bolt 7.3 needs to rotate is obtained according to the step difference H between the cover plate 1 and the aircraft front end fuselage frame 10, including the following steps:

[0084] S611, a relationship between the step difference H and the number of turns P is established Wherein, R is the rotation radius of the spherical hinge 6 to the front end edge of the cover, N is the pitch of the adjusting bolt 7.3, and r is the rotation radius of the spherical hinge 6 to the adjusting bolt 7.3;

[0085] S612, the number of turns P corresponding to all different step differences H is calculated based on the relationship between the step difference H and the number of turns P;

[0086] S613, a relationship table is established using all the steps H and the number of turns P;

[0087] S614, the target step is measured using a measuring tool;

[0088] S615, the corresponding number of turns P is queried from the relationship table according to the target step H.

[0089] The relationship between the step H and the number of turns P is obtained according to the following principle:

[0090] Let the pitch of the adjusting bolt 7.3 be N, and the number of turns required to be P, then the stroke S of the upward adjusting movement of the adjusting screw is calculated as S = P·N;

[0091] Let the radius of the spherical hinge 6 to the adjusting bolt 7.3 be r, and the stroke S of the upward adjusting movement of the adjusting screw be approximately equal to the arc length of the rotational movement of the spherical hinge 6, then the radian I is calculated as I = S / r = (P·N) / r;

[0092] The angle a of the rotation of the spherical hinge 6 to the right along the adjusting bolt 7.3 is calculated as The angle of the rotation of the spherical hinge 6 to the left along the front end of the hatch cover is equal to the angle of the rotation to the right, both being a, let the radius of the spherical hinge 6 to the edge of the front end of the hatch cover be R, and the step H between the front end of the hatch cover and the frame, then the following formula is obtained:

[0093]

[0094] H = R·tan(a)

[0095]

[0096] In the formula, the step H between the front end of the hatch cover and the front end of the aircraft fuselage frame 10 can be measured, and in the above formula, the radius R of the spherical hinge 6 to the edge of the front end of the hatch cover is H, the radius r of the spherical hinge 6 to the adjusting bolt 7.3 is determined by the installation position of the spherical hinge 6 on the hatch cover, and the universality of the installation of each hatch cover can be ensured by the underframe assembly tool, and the pitch N of the adjusting bolt 7.3 is determined by the characteristic size of the adjusting bolt 7.3, so a uniform specification of the adjusting bolt 7.3 can be selected, therefore the step H between the front end of the hatch cover and the frame is characterized by the number of turns P to determine, and therefore a size relationship table of the step H and the number of turns P can be established, and according to the measured step H, the corresponding number of turns P can be selected to eliminate the step and ensure the installation of the hatch cover. This can bring the following three advantages: first, the installation operation process of the hatch cover is standardized, which greatly reduces the installation time and personnel, and improves the installation quality; second, it can ensure that any hatch cover can be used universally on any aircraft; third, this technical solution can be applied to other types of hatch covers or other aircraft.

Claims

1. A ball-jointed rope cleat, characterized by: The gusset (1) is provided with a front end lug (2) and a rear end lug (3) at positions close to two ends of a side of the gusset (1) facing an aircraft body, and a limiting gap (4) is formed in each side of the gusset (1), and a limiting block (5) is fitted in the limiting gap (4); A non-concentric connecting hole (8) is formed in the rear end lug (3) for connecting a rope (9) with an aircraft rear end body frame (11); at least one connecting unit for connecting the aircraft front end body frame (10) is arranged on the front end lug (2); the connecting unit comprises a spherical hinge (6) fixedly connected with the front end lug (2), and an adjusting assembly (7) for adjusting and limiting the activity range of the spherical hinge (6); the adjusting assembly (7) comprises an adjusting support (7.1), a locking nut (7.2), an adjusting bolt (7.3) and a mounting nut (7.4); the mounting nut (7.4) is riveted on the adjusting support (7.1), the adjusting bolt (7.3) acts on the spherical hinge (6) after passing through the locking nut (7.2), the adjusting support (7.1) and the mounting nut (7.4) in sequence; the adjusting bolt (7.3) is based on axial stroke fine adjustment, generates an acting force at the end of the spherical hinge (6) to change the posture of the spherical hinge, and after the adjusting bolt (7.3) is fixed by the locking nut (7.2), the step difference between the gusset (1) and the aircraft front end body frame (10) is eliminated.

2. A ball-joint rope cleat cover as in claim 1, wherein: The gusset (1) is made of a carbon cloth composite material.

3. A method of installing a ball-jointed rope cleat cover, characterized by, It is a method for installing a spherical hinge type rope locking gusset as claimed in claim 1 or 2, comprising the following steps: S1, according to the aircraft model, under the assistance of the underframe assembly tooling, the gusset is assembled to obtain a gusset blank; S2, under the assistance of the assembly positioning tooling, the limiting block (5) is riveted on the aircraft body longitudinal beam (12); S3, corresponding to the self-positioning hole pre-set on the aircraft front end body frame (10), the adjusting support with the mounting nut (7.4) is riveted on the aircraft front end body frame (10), and the adjusting bolt and the locking nut (7.2) are installed according to the structure of the adjusting assembly (7); S4, the spherical hinge (6) on the gusset blank is aligned and placed in the limiting connection groove pre-set on the aircraft front end body frame (10), then the heading position of the gusset (1) is adjusted according to the position of the limiting block (5), and the limiting gap (4) on the gusset (1) is adaptively modified; S5, after the rope (9) passes through the non-concentric connecting hole (8) on the rear end lug (3) and the gusset connecting hole (13) on the aircraft rear end body frame (11), the rope (9) is bound and fixed, so that the gusset (1) has no step difference with the aircraft rear end body frame (11), that is, the gusset rear end is installed in place; S6, by adjusting the axial stroke of the adjusting bolt (7.3) and fixing it by the locking nut (7.2), the step difference between the gusset (1) and the aircraft front end body frame (10) is eliminated.

4. The method of installing a ball-jointed rope cleat cover of claim 3, wherein, In the step S1, the gusset assembly comprises the following steps: S11, draw points on the cover plate (1), the front end tab (2) and the rear end tab (3) with the help of the assembly positioning tool; S12, drill positioning installation holes on the points drawn on the cover plate (1) and the front end tab (2); S13, drill non-concentric connecting holes (8) on the points drawn on the rear end tab (3); S14, connect the front end tab (2) and the rear end tab (3) with the cover plate (1) into an integrated whole by using fasteners to cooperate with the corresponding positioning installation holes on the cover plate (1); S15, connect the spherical hinge (6) with the front end tab (2) into an integrated whole by using fasteners to cooperate with the corresponding positioning installation holes on the front end tab (2).

5. The method of installing a ball-jointed rope cleat cover of claim 3, wherein, Before the axial stroke fine adjustment of the adjusting bolt (7.3) in the step S6, the step difference between the access cover plate (1) and the front end fuselage frame (10) of the airplane needs to be measured , the number of turns that the adjusting bolt (7.3) needs to rotate is obtained , comprising the following steps: S611, establish step difference with the number of turns of the relationship ; wherein, is the radius of rotation of the spherical hinge (6) to the front end edge of the flap, is the pitch of the adjusting screw (7.3), is the radius of rotation of the spherical hinge (6) to the adjusting screw (7.3); S612, calculate the number of turns P corresponding to all different order differences H based on the relationship with the number of turns of the relationship S613, utilize all the differences of order and the number of turns establish a relationship table; S614, measure the target step difference by using a measuring tool; S615, query the corresponding number of turns according to the target step difference in the relationship reference table.

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