Cabin door coordination method with active and passive thermal protection system function

Abstract

The invention relates to a cabin door coordination method with an active and passive thermal protection system function, and solves the problem of appearance accuracy of a cabin door and a fuselage. Comprising the following steps: 1) producing and delivering support parts mounted on the inner surface of the cabin door according to an independent manufacturing principle according to a digital model; (2) appearance scanning is carried out after the cabin door bearing structure is delivered, and the scanning structure is checked to meet design index requirements; 3) simultaneously positioning and mounting the left and right cabin doors on the assembly fixture, checking that a gap between the left and right cabin doors meets a design index, and checking that side vertical surfaces of the left and right cabin doors are attached to a fixture positioning surface; (4) holes are formed in the inner surface of the cabin door according to the jig drilling jig, and the hole forming depth is limited through a limiting tool; the method comprises the steps of (1) installing a cabin door, (2) placing the cabin door on a frame, installing a steel wire thread insert, installing a rocker arm installation base and a retractable mechanism support, (6) installing a connecting rod rocker arm on the cabin door and installing the cabin door on a fuselage, (7) installing a retractable mechanism on the inner surface of the cabin door, retracting the cabin door and checking the matching performance of outer profiles, and (8) bonding the outer surface of the cabin door for thermal protection after the outer profiles are matched.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of overall assembly of aerospace products, and relates to a hatch coordination method with a function of a main and passive thermal protection system. BACKGROUND

[0002] The landing gear hatch structure is an important shape component and sealing structure of a wheeled landing aircraft product, and the accuracy of the component itself and the correctness of the connection with the fuselage directly affect the aerodynamic shape of the whole machine and the take-off and landing control process. At present, some people in China have very high flight speed, and the front windward surface adopts a conventional aluminum alloy material or a carbon fiber material + coating process to meet the aerodynamic load and thermal load requirements in the flight working condition. When the flight speed reaches a higher speed, the temperature of the front windward surface of the outer surface of the aircraft product can reach 800 DEG C, and the traditional material + high-temperature-resistant coating solution cannot meet the flight requirements.

[0003] In view of the extremely fast flight speed and the lightweight structure design requirement, the structure of the current high-speed flight recoverable product generally adopts an internal metal / composite bearing structure + external high-temperature-resistant composite structure design scheme, and a fuel / water cooling active cooling scheme is adopted in the internal bearing structure system to realize the cooling requirement in the flight process. As a moving mechanism, the hatch structure needs to consider the load requirement in the flight process and the stability of the retraction and extension in the flight process, and the current hatch structure design scheme generally adopts a hollow sandwich metal component + external high-temperature-resistant composite component form. The hollow sandwich is used for bearing and cooling liquid circulation, and can realize lightweight design at the same time. The high-temperature-resistant composite structure generally adopts a bonding scheme, and the left and right hatches are independent moving structure components. The left and right hatches need to ensure the thermal deformation matching in the closed state to prevent the opening from being blocked after high-speed and high-temperature. The hole position accuracy of the hollow sandwich component is high, and the post-maintenance risk of the hole filling process is large, so the process positioning hole cannot be designed. The final shape accuracy of the hatch is affected by the superposition of the bearing structure shape and the thermal protection shape, and the control process is complex. SUMMARY

[0004] The application is aimed at the problems of large deformation in the assembly process of a hatch with an active cooling system and a retraction and extension mechanism, great difficulty in coordination of the retraction and extension mechanism, and difficulty in guaranteeing the shape accuracy of the hatch and the fuselage. The assembly process scheme of the hatch and the retraction and extension mechanism is designed to guarantee the hole accuracy of the inner surface of the hatch, reduce the risk of sandwich hole leakage, improve the debugging efficiency of the retraction and extension mechanism, and guarantee the shape accuracy of the hatch and the fuselage. The connection coordination accuracy of the hatch and the fuselage and the shape accuracy of the hatch and the fuselage are mainly solved.

[0005] The application is realized by the following technical scheme: A hatch coordination method with a function of a main and passive thermal protection system, comprising: 1) The rocker arm, mounting seat and other parts installed on the inner surface of the metal hatch door are machined in place according to the numerical model (independent manufacturing principle is adopted), the hatch door bearing structure is assembled in an independent state and delivered to the department, and the parts are assembled with the hatch door using analog quantity coordination, and the hole drilling is completed through the jig; 2) A special jig is designed, the outer surface of the front end frame of the hatch door is used as the positioning reference, the gap compensation limiting is used for the rear end surface, the hatch door butt joint limiting mark is drawn on the surface of the inner and outer clamping plates, the inner clamping plate is designed as an integral drill jig, the outer clamping plate has a detachable limiting function, the clamping plate is fixed with the jig position through the plug-in pin, and 2 groups of bolts are used for fastening, and the positioning and assembly of the left and right hatch doors (2 components) are considered in the same jig; 3) Considering the riveting deformation of the inner and outer skins of the hatch door, the inside of the frame flange of the hatch door is positioned in the hatch door profile direction, and a 0.5mm gap is reserved on the abutting surface of the inner skin and the jig, and the gap is compensated during positioning.

[0006] The present application realizes the accuracy of the assembly of the hollow sandwich hatch door and the accuracy of the thermal protection system shape by reasonably using the digital quantity coordination scheme and the analog quantity coordination scheme, reduces the hole leakage quality risk in the assembly process of the active cooling system, and can be widely applied to components with high bearing structure hole drilling accuracy requirement, difficult positioning and bonded thermal protection system. BRIEF DESCRIPTION OF DRAWINGS

[0007] Figure 1 is a hatch door assembly coordination roadmap with active and passive thermal protection systems. DETAILED DESCRIPTION

[0008] The technical scheme of the present application will be further described in detail below through the drawings and implementation cases.

[0009] Referring to Figure 1 , the left and right hatch door coordination roadmap is shown.

[0010] Implementation process: 1) According to the numerical model, the support parts installed on the inner surface of the hatch door are produced and delivered according to the independent manufacturing principle.

[0011] 2) After the hatch door bearing structure is delivered, the shape is scanned, and it is checked that the scanned structure meets the design index requirements.

[0012] 3) The left and right hatch doors are positioned and installed in the assembly jig at the same time, it is checked that the gap between the left and right hatch doors meets the design index, and it is checked that the side surface of the left and right hatch doors is abutted with the positioning surface of the jig.

[0013] 4) The holes are drilled on the inner surface of the hatch door according to the jig drill jig, and the limiting tool is used to limit the drilling depth.

[0014] 5) The hatch door is removed, the steel wire sleeve is installed, the rocker arm mounting seat and the retraction mechanism support are installed.

[0015] 6) Install the connecting rod rocker arm on the hatch door, and install the hatch door to the fuselage.

[0016] 7) Install the retracting mechanism on the inner surface of the hatch door, retract the hatch door, and check the matching of the outer shape.

[0017] 8) After the matching of the outer shape, bond the thermal protection layer on the outer surface of the hatch door.

[0018] Through the above steps, the accuracy of the position relationship between the left and right hatch doors, the accuracy of the shape of the left and right hatch doors and the fuselage bearing structure, and the accuracy of the hatch door thermal protection layer and the fuselage shape can be realized, the rivet temperature can be accurately controlled, and the assembly quality, the shape accuracy, and the stability of the retracting process of the left and right hatch doors are improved.

Claims

1. A method for coordinating hatches with active and passive thermal protection systems, characterized in that: include: 1) The rocker arm and mounting base parts installed on the inner surface of the metal hatch are machined in place according to the digital model. The hatch load-bearing structure is assembled and delivered to the sub-assembly unit in an independent state. The assembly of parts and hatch is coordinated by analog quantity, and the connection hole is made by using a jig. 2) Design a special jig, using the outer facade of the front frame edge and the outer facade of the side of the hatch as the positioning reference, and the rear face adopts gap compensation limit. The hatch butt joint limit marks are drawn on the surface of the inner and outer clamping plates. The inner clamping plate and the frame are designed as an integral drilling jig. The outer clamping plate has a detachable limit function. The outer clamping plate is fixed to the position of the clamping plate and the jig by the plug-in pin and fastened with 2 sets of bolts. The positioning and assembly of the left and right hatches are considered simultaneously within the same jig. 3) Considering the deformation of the inner and outer skin riveting of the hatch, the hatch profile direction is positioned by the inner side of the hatch frame flange, and a 0.5mm gap is reserved on the mating surface between the inner skin and the frame to compensate for the gap during the positioning process.

2. The hatch coordination method with active and passive thermal protection system function according to claim 1, characterized in that: Including the following Specific steps: 1) Based on the digital model, all support parts installed on the inner surface of the hatch will be manufactured and delivered according to the principle of independent manufacturing; 2) After the door load-bearing structure is delivered, an external scanning is carried out to check whether the scanned structure meets the design requirements; 3) Position and install the left and right hatches on the assembly frame simultaneously, check that the gap between the left and right hatches meets the design specifications, and check that the side facades of the left and right hatches fit the positioning surface of the frame. 4) Drill holes on the inner surface of the hatch according to the die frame, and use a limiting fixture to limit the drilling depth; 5) Remove the hatch frame, install the wire threaded sleeve, and install the rocker arm mounting seat and the retraction mechanism support; 6) Install the linkage rocker arm on the hatch and install the hatch to the fuselage; 7) Install the retraction mechanism on the inner surface of the hatch, retract and extend the hatch, and check the matching of the outer surface; 8) After the outer surface is matched, the thermal protection of the outer surface of the hatch is bonded.

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