False part for injecting sudden fracture fault of main transmission shaft of aircraft flap actuator

Abstract

The invention belongs to the technical field of test verification of an aircraft flap crosslinking system, and particularly relates to a false part for injecting a sudden fracture fault of a main transmission shaft of an aircraft flap actuator, which can effectively simulate the situation of sudden fracture of the main transmission shaft of the aircraft flap actuator in a verification test and effectively verify the reliability of the aircraft flap crosslinking system.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft flap cross-linking system test verification, and specifically relates to a dummy component for injecting a sudden fracture fault of a main drive shaft of an aircraft flap actuator. Background Art

[0002] The aircraft flap actuator is usually a torque output actuator, the end of which is connected to the flap drive link through a spline. The aircraft flap actuator outputs torque through the main drive shaft, drives the drive link to rotate, and drives the flap to retract and extend.

[0003] Each aircraft flap is driven by at least two actuators. The main drive shaft of the flap actuator may break due to manufacturing defects, fatigue damage and other reasons. When the main drive shaft breaks suddenly, the aircraft flap will excessively tilt, which will have an unpredictable impact on the lift and drag characteristics of the wing, seriously threatening the safety of the aircraft flight and its take-off and landing. For this reason, a flap cross-linking system is designed between adjacent flaps. When the main drive shaft of the flap actuator breaks suddenly, it can effectively prevent the faulty flap from excessively tilting, provide flap buffering energy, and perform auxiliary restraint, thereby ensuring the safety of the aircraft flight and its take-off and landing.

[0004] The reliability of the aircraft flap cross-linking system needs to be verified through ground tests, but there is currently a lack of a reliable means to effectively simulate the sudden fracture of the main drive shaft of the flap actuator in the verification test. In view of this, the present application is proposed. Summary of the invention

[0005] The purpose of the present application is to provide a dummy for injecting a sudden fracture fault of a main drive shaft of an aircraft flap actuator, so as to effectively simulate the sudden fracture of the main drive shaft of the flap actuator in a verification test and effectively verify the reliability of the aircraft flap cross-linking system.

[0006] The technical solution of this application is:

[0007] A dummy for injecting sudden fracture fault of the main transmission shaft of an aircraft flap actuator, comprising a double-ear bracket, a flap driving connecting rod, a main transmission shaft dummy, a forward stop end cover, and a reverse bearing end cover;

[0008] The double-ear bracket is connected to the rear beam of the wing, one ear piece on the bracket is the first ear piece, and the other ear piece is the second ear piece;

[0009] One end of the flap driving link is connected to the flap, and the other end extends between the two ear pieces of the double ear bracket. The flap driving link has a support shaft at this end, and the support shaft extends into the ear hole on the first ear piece.

[0010] The main transmission shaft dummy is arranged between the two ear pieces of the double ear bracket, one end of which is connected to the support shaft through a spline, and the other end extends from the ear hole on the second ear piece. The end of the main transmission shaft dummy has a forward rotation stop boss and a reverse rotation bearing boss, and an annular breaking groove is provided between the forward rotation stop boss and the reverse rotation bearing boss;

[0011] The forward rotation stop end cover is sleeved on the outer periphery of the main transmission shaft dummy with a through hole, connected to the outer side of the second ear piece, and has a forward rotation stop surface in the through hole that can cooperate with the forward rotation stop boss;

[0012] The reverse bearing end cover is sleeved on the outer periphery of the main transmission shaft dummy with a through hole and connected to the outer side of the forward stop end cover. The through hole is provided with a reverse bearing surface that can cooperate with the reverse bearing boss.

[0013] According to at least one embodiment of the present application, in the above-mentioned dummy for injecting a sudden fracture fault of the main transmission shaft of the aircraft flap actuator, the double-ear bracket is connected to the rear beam of the wing by screws;

[0014] The forward rotation stop end cover is bolted to the outside of the second ear piece;

[0015] The reverse bearing end cover is connected to the outer side of the forward stop end cover by bolts.

[0016] According to at least one embodiment of the present application, in the above-mentioned dummy for injecting sudden fracture fault of the main transmission shaft of the aircraft flap actuator, one end of the main transmission shaft dummy extending outward from the second ear piece is a square structure.

[0017] According to at least one embodiment of the present application, in the dummy component for injecting a sudden fracture fault into the main drive shaft of the aircraft flap actuator, the cross section of the annular fracture groove is V-shaped.

[0018] According to at least one embodiment of the present application, in the above-mentioned aircraft flap actuator main transmission shaft sudden fracture fault injection dummy, the forward rotation stop boss on the main transmission shaft dummy and the forward rotation stop surface in the through hole of the forward rotation stop end cover have two groups, which are symmetrically distributed at 180°;

[0019] There are two groups of inverted bearing surfaces in the through holes of the inverted bearing boss and the inverted bearing end cover on the main transmission shaft dummy, which are symmetrically distributed at 180 degrees.

[0020] According to at least one embodiment of the present application, in the above-mentioned dummy for injecting sudden fracture fault of the main transmission shaft of the aircraft flap actuator, the forward rotation stop boss portion on the main transmission shaft dummy and the through hole of the forward rotation stop end cover, as well as the reverse rotation bearing boss portion on the main transmission shaft dummy and the through hole of the reverse bearing end cover, are matched with a gradually opening surface.

[0021] This application has at least the following beneficial technical effects:

[0022] A dummy for injecting a sudden fracture fault of a main transmission shaft of an aircraft flap actuator is provided, which can effectively simulate the sudden fracture of the main transmission shaft of the flap actuator in a verification test and effectively verify the reliability of the aircraft flap cross-linking system. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a schematic diagram of a dummy component for injecting a sudden fracture fault of a main transmission shaft of an aircraft flap actuator provided by an embodiment of the present application;

[0024] Figure 2 It is a schematic diagram of an exploded view of a dummy component for injecting a sudden fracture fault of a main transmission shaft of an aircraft flap actuator provided by an embodiment of the present application;

[0025] Figure 3 is a schematic diagram of a main transmission shaft provided in an embodiment of the present application;

[0026] Figure 4 It is a cross-sectional schematic diagram of the cooperation between the main transmission shaft dummy and the forward rotation stop end cover provided in an embodiment of the present application;

[0027] Figure 5 It is a cross-sectional schematic diagram of the cooperation between the main transmission shaft dummy and the inverted bearing end cover provided in an embodiment of the present application;

[0028] in:

[0029] 1- double ear bracket; 2- flap driving connecting rod; 3- main transmission shaft dummy; 4- forward stop end cover; 5- reverse bearing end cover.

[0030] In order to better illustrate the present embodiment, some contents of the drawings may be omitted, enlarged or reduced, which is only used for illustrative purposes and should not be construed as limiting the present application. DETAILED DESCRIPTION

[0031] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0032] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should be the common meanings understood by those skilled in the art in the field to which this application belongs. The term "include" used in the description of this application means that the concepts appearing before the term include the concepts listed after the term and their equivalents, without excluding other related concepts.

[0033] In addition, the words indicating orientation used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and other similar words used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0034] A dummy component for injecting sudden fracture fault of the main transmission shaft of an aircraft flap actuator, such as Figure 1-Figure 2 As shown, it includes a double-ear bracket 1, a flap driving connecting rod 2, a main transmission shaft dummy 3, a forward rotation stop end cover 4, and a reverse rotation bearing end cover 5.

[0035] The double-ear bracket 1 is connected to the rear beam of the wing, and can be specifically connected to the rear beam of the wing by screws, wherein one ear piece is a first ear piece, and the other ear piece is a second ear piece.

[0036] One end of the flap driving link 2 is connected to the flap, and the other end extends between the two ears of the double-ear bracket 1. The flap driving link 2 has a support shaft at this end, and the support shaft extends into the ear hole on the first ear.

[0037] The main transmission shaft dummy 3 is arranged between the two ear pieces of the double ear bracket 1, one end of which is connected to the support shaft through a spline, and the other end extends from the ear hole on the second ear piece. The main transmission shaft dummy 3 has a forward rotation stop boss and a reverse rotation bearing boss at this end, and an annular breaking groove is provided between the forward rotation stop boss and the reverse rotation bearing boss, such as Figure 3 shown.

[0038] The forward rotation stop end cover 4 is sleeved on the outer periphery of the main transmission shaft dummy 3 with a through hole, and is connected to the outer side of the second ear piece. Specifically, it can be connected to the outer side of the second ear piece by bolts, and its through hole has a forward rotation stop surface that can cooperate with the forward rotation stop boss to constrain the main transmission shaft dummy 3 to rotate forward. Figure 4 shown.

[0039] The reverse bearing end cover 5 is sleeved on the outer periphery of the main transmission shaft dummy 3 with a through hole, and is connected to the outer side of the forward rotation stop end cover 4. Specifically, it can be connected to the outer side of the forward rotation stop end cover 4 by bolts, and its through hole has a reverse bearing surface that can cooperate with the reverse bearing boss to constrain the main transmission shaft dummy 3 to reverse, such as Figure 5 shown.

[0040] The dummy for injecting sudden fracture fault of the main transmission shaft of the aircraft flap actuator disclosed in the above-mentioned embodiment limits the rotation of the main transmission shaft dummy 3 through the cooperation between the forward rotation stop surface and the reverse rotation bearing surface on the forward rotation stop end cover 4 and the reverse rotation bearing end cover 5, and the forward rotation stop boss and the reverse rotation bearing boss on the main transmission shaft dummy 3, so as to support the flap at a required angle position.

[0041] Under normal conditions, the load transmitted from the flap to the main drive shaft dummy 3 through the flap drive connecting rod 2 is borne by the inverted load-bearing boss and the forward rotation stop boss. At the beginning of the test, a torsional load can be applied to the end of the main drive shaft dummy 3 extending outward from the second ear piece, so that the load-bearing system is changed from the inverted load-bearing boss and the forward rotation stop boss to the forward rotation stop boss and the forward rotation stop surface. The torsional load is gradually increased to cause the main drive shaft dummy 3 to break at the annular breaking groove. After that, the load transmitted from the flap to the main drive shaft dummy 3 through the flap drive connecting rod 2 can no longer be borne by the reverse load-bearing boss and the forward rotation stop boss. The constraint on the rotation of the main drive shaft dummy 3 is thereby released, simulating the sudden fracture of the main drive shaft of the flap actuator, and verifying the reliability of the flap cross-linking system.

[0042] At the beginning of the test, a torsional load can also be applied to the end of the main transmission shaft dummy 3 extending outside the second ear piece, so that the reverse load-bearing boss and the forward stop boss continue to cooperate to carry the load, and the torsional load is gradually increased to cause the main transmission shaft dummy 3 to break from the annular breaking groove.

[0043] In order to facilitate applying a torsional load on the main transmission shaft dummy 3, the end of the main transmission shaft dummy 3 extending outside the second ear piece can be designed to have a square structure. When applying a torsional load, it can be applied with the help of a wrench tool or an electric motor.

[0044] The design of the annular breaking groove of the main transmission shaft dummy 3 is based on the principle of being able to withstand the normal load transmitted by the flap and being easy to break when a torsional load is applied. The cross-section of the annular breaking groove can be designed to be V-shaped.

[0045] There are two groups of forward rotation stop bosses on the main transmission shaft dummy 3 and forward rotation stop surfaces in the through holes of the forward rotation stop end cover 4, which are symmetrically distributed at 180 degrees.

[0046] There are two groups of inverted bearing surfaces on the main transmission shaft dummy 3 and inverted bearing end cap 5 through holes thereof, which are symmetrically distributed at 180°.

[0047] The forward rotation stop boss on the main transmission shaft dummy 3 and the through hole of the forward rotation stop end cover 4, as well as the reverse rotation bearing boss on the main transmission shaft dummy 3 and the through hole of the rotation bearing end cover 5, are matched with involute surfaces in a ratchet shape, so that after the main transmission shaft dummy 3 breaks, the rotation range of the main transmission shaft dummy 3 can be constrained by the curved surface matching, thereby ensuring the safety of the test.

[0048] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. A dummy for injecting a sudden fracture fault of a main transmission shaft of an aircraft flap actuator, characterized in that: It comprises a double-ear bracket (1), a flap driving connecting rod (2), a main transmission shaft dummy (3), a forward rotation stop end cover (4), and a reverse rotation bearing end cover (5); The double-ear bracket (1) is connected to the rear beam of the wing, one ear piece on the bracket is a first ear piece, and the other ear piece is a second ear piece; One end of the flap driving connecting rod (2) is connected to the flap, and the other end extends between two ear pieces of the double ear bracket (1). The flap driving connecting rod (2) has a support shaft at this end, and the support shaft extends into the ear hole on the first ear piece. The main transmission shaft dummy (3) is arranged between the two ear pieces of the double-ear bracket (1), one end of which is connected to the support shaft via a spline, and the other end of which extends out from the ear hole on the second ear piece. The end of the main transmission shaft dummy (3) has a forward rotation stop boss and a reverse rotation bearing boss, and an annular breaking groove is provided between the forward rotation stop boss and the reverse rotation bearing boss. The forward rotation stop end cover (4) is sleeved on the outer periphery of the main transmission shaft dummy (3) with a through hole, connected to the outer side of the second ear piece, and has a forward rotation stop surface in the through hole that can cooperate with the forward rotation stop boss; The reverse bearing end cover (5) is sleeved on the outer periphery of the main transmission shaft dummy (3) with a through hole, and is connected to the outer side of the forward rotation stop end cover (4), and has a reverse bearing surface in the through hole that can cooperate with the reverse bearing boss.

2. The dummy component for injecting sudden fracture fault of the main transmission shaft of the aircraft flap actuator according to claim 1, characterized in that: The double-ear bracket (1) is connected to the rear beam of the wing by screws; The forward rotation stop end cover (4) is bolted to the outside of the second ear piece; The reverse bearing end cover (5) is connected to the outer side of the forward stop end cover (4) by means of bolts.

3. The dummy component for injecting sudden fracture fault of the main transmission shaft of the aircraft flap actuator according to claim 2, characterized in that: One end of the main transmission shaft dummy (3) extending outward from the second ear piece is a square structure.

4. The dummy component for injecting sudden fracture fault of the main transmission shaft of the aircraft flap actuator according to claim 3, characterized in that: The cross section of the annular breaking groove is V-shaped.

5. The dummy component for injecting sudden fracture fault of the main transmission shaft of the aircraft flap actuator according to claim 4, characterized in that: There are two groups of forward rotation stop bosses on the main transmission shaft dummy (3) and forward rotation stop surfaces in the through holes of the forward rotation stop end cover (4), which are symmetrically distributed at 180 degrees. There are two groups of inverted bearing surfaces in the through hole of the inverted bearing boss on the main transmission shaft dummy (3) and the inverted bearing end cover (5), which are symmetrically distributed at 180 degrees.

6. The dummy component for injecting sudden fracture fault of the main transmission shaft of the aircraft flap actuator according to claim 5, characterized in that: The forward rotation stop boss on the main transmission shaft dummy (3) and the through hole of the forward rotation stop end cover (4), as well as the reverse rotation bearing boss on the main transmission shaft dummy (3) and the through hole of the rotation bearing end cover (5) are matched with involute surfaces.

Images