阅读说明：本技术 一种飞机右主起落架航向约束装置 (Course restraining device for right main landing gear of airplane ) 是由 臧伟锋 陈安 张移花 沈翔 姚勇 于 2020-05-26 设计创作，主要内容包括：本发明实施例公开了一种飞机右主起落架航向约束装置,其中,滚轮组件包括滚轮支架和安装于滚轮支架安装孔的滚轮和滚轮螺栓,滚轮支架通过其中央安装孔和单耳接头螺栓与单耳接头的一端连接；底座通过立柱螺栓安装在立柱上,通过衬套螺栓依次连接底座、衬套和端板,并将滚轮组件安装于底座和端板之间的内部空间后固定端板,使得单耳接头穿过端板的中央通孔,从而使得单耳接头可在中央通孔内部侧向移动；单耳接头的另一端依次安装有松紧螺套、双头螺柱、载荷传感器和双耳接头,并通过双耳接头螺栓连接双耳接头和右主起落架假轮。本发明实施例通过提供一种可随动的飞机右主起落架航向约束装置,满足了飞机地面试验中主起落架的约束要求。(The embodiment of the invention discloses a course restraining device of a right main undercarriage of an airplane, wherein a roller component comprises a roller bracket, a roller and a roller bolt, wherein the roller and the roller bolt are arranged in a mounting hole of the roller bracket; the base is installed on the upright column through upright column bolts, the base, the bushing and the end plate are sequentially connected through bushing bolts, the roller components are installed in an inner space between the base and the end plate, and then the end plate is fixed, so that the monaural joint penetrates through a central through hole of the end plate, and the monaural joint can laterally move in the central through hole; the other end of the single-lug connector is sequentially provided with an elastic threaded sleeve, a stud, a load sensor and a double-lug connector, and the double-lug connector and the right main undercarriage false wheel are connected through a double-lug connector bolt. The embodiment of the invention provides a follow-up course constraint device for a right main undercarriage of an airplane, and meets the constraint requirement of the main undercarriage in an airplane ground test.)

1. An aircraft right main landing gear course restraint device, comprising: the device comprises an upright post bolt, an upright post, a base, a bushing bolt, an end plate with a central through hole, a single-lug joint, a tightening screw sleeve, a stud bolt, a load sensor, a double-lug joint bolt, a right main undercarriage false wheel, a single-lug joint bolt and a roller assembly, wherein the roller assembly comprises a roller bracket, 4 rollers and the roller bolt, the rollers are arranged in an upper mounting hole and a lower mounting hole which are formed in the two sides of the roller bracket, the roller bolt is used for mounting the rollers, and the roller bracket is connected with one end of the single-lug joint through the central mounting hole;

the base is installed on the upright column through upright column bolts, the base, the bushing and the end plate are sequentially connected through bushing bolts, the roller assemblies are installed in an inner space between the base and the end plate, and then the end plate is fixed, so that the single-lug joint penetrates through a central through hole of the end plate, and the single-lug joint can laterally move in the central through hole;

the other end of the single lug joint is sequentially provided with an elastic threaded sleeve, a stud, a load sensor and a double lug joint, and the double lug joint and the right main undercarriage false wheel are connected through a double lug joint bolt.

2. The aircraft right main landing gear course restraining device according to claim 1, wherein connecting holes for installing bushing bolts are formed in the circumferential direction and in symmetrical positions of the base and the end plate, at least two through holes for installing stud bolts are formed in the base, a central through hole of the end plate is a rectangular through hole, and triangular reinforcing ribs are arranged on the edges of the rectangular through hole.

3. An aircraft right main landing gear heading restraint device according to claim 2, wherein the bushing is a tubular structure mounted centrally on a bushing bolt for forming an interior space between the base and the end plate in which the roller assembly is mounted.

4. The aircraft right main landing gear course restraining device according to claim 1, wherein the elastic thread insert is of a cylindrical structure, and a rectangular groove for rotating the elastic thread insert and observing the connection condition is formed in the cylindrical center of the elastic thread insert;

the elastic thread insert is used for adjusting the total length of the course restraining device through rotation.

5. An aircraft right main landing gear heading restraint device according to claim 1, wherein the roller assembly further comprises: a thrust bearing installed between the roller bracket and the roller, and a thrust bearing installed between the bolt head of the roller bolt and the roller.

6. An aircraft right main landing gear course restraining device according to any one of claims 1-5, wherein a slack screw sleeve, a stud and a load sensor which are assembled between the single lug joint and the double lug joint are in hard connection.

7. An aircraft right main landing gear heading restraint device according to any one of claims 1 to 5,

in the test process, the forward deformation of the airplane structure is restrained by 4 rollers contacting the base, and the backward deformation of the airplane structure is restrained by 4 rollers contacting the end plate.

8. An aircraft right main landing gear heading restraint device according to any one of claims 1 to 5, wherein during testing, left and right movement of the right main landing gear is achieved by 4 rollers rolling in the interior space between the base and the end plate.

9. The aircraft right main landing gear heading restraint device of claim 8,

when the course restraining device bears the tensile load, the roller is used for rolling left and right on the inner side of the end plate along the lateral direction of the airplane;

when the course restraining device bears the compressive load, the roller is used for rolling left and right along the lateral direction of the airplane on the inner side of the base.

Technical Field

The application relates to the technical field of ground test of structural strength of aircrafts, in particular to a heading restraining device of a right main undercarriage of an aircraft.

Background

The ground verification of the structural strength of the airplane needs to complete a full-airplane test under multiple working conditions, the wings of most working conditions apply upward loads, the fuselage applies downward loads, the wings deform upward, and the main landing gear mounted on the wings generates outward lateral deformation, as shown in fig. 1, the ground verification is a schematic diagram of the structural deformation of the airplane test in the ground verification process of the structural strength of the airplane.

During the whole airplane test, the airplane is restrained in a front suspension mode and a main suspension mode, namely the airplane is suspended on the front landing gear wheel, the left main landing gear fake wheel and the right main landing gear fake wheel in a crow bar mode, so that the airplane is in a suspension state; selecting a left main undercarriage to form fixed constraint, namely limiting the vertical, course and lateral displacement of the airplane; and selecting a right main undercarriage to limit the vertical and heading displacement of the airplane and relax the lateral displacement, wherein the right main undercarriage is shown in fig. 2 and is a schematic diagram of the constraint mode of the left main undercarriage and the right main undercarriage in the ground verification of the structural strength of the airplane. The course constraint of the right main landing gear is required to satisfy the sum of the lateral displacements of the left and right main landing gears. The existing aircraft right main undercarriage adopts a restraint method that a position control actuator cylinder is connected with a load sensor, as shown in fig. 3, the structure schematic diagram of the existing aircraft right main undercarriage course restraint device realizes the course restraint of the right main undercarriage by controlling the extension of the position control actuator cylinder through a computer, the false wheel of the right main undercarriage course restraint device of the right main undercarriage bears extra additional load, the test verification result is influenced, the clamping stagnation phenomenon can occur between the undercarriage false piece and the restraint double ears, and the test safety is seriously influenced.

Disclosure of Invention

In order to solve the technical problem, the embodiment of the invention provides a heading constraint device of a right main undercarriage of an airplane, and the heading constraint device of the right main undercarriage of the airplane capable of following is provided so as to meet the constraint requirement of the main undercarriage in an airplane ground test.

The embodiment of the invention provides a course restraining device of a right main undercarriage of an airplane, which comprises: the device comprises an upright post bolt, an upright post, a base, a bushing bolt, an end plate with a central through hole, a single-lug joint, a tightening screw sleeve, a stud bolt, a load sensor, a double-lug joint bolt, a right main undercarriage false wheel, a single-lug joint bolt and a roller assembly, wherein the roller assembly comprises a roller bracket, 4 rollers and the roller bolt, the rollers are arranged in an upper mounting hole and a lower mounting hole which are formed in the two sides of the roller bracket, the roller bolt is used for mounting the rollers, and the roller bracket is connected with one end of the single-lug joint through the central mounting hole;

the base is installed on the upright column through upright column bolts, the base, the bushing and the end plate are sequentially connected through bushing bolts, the roller assemblies are installed in an inner space between the base and the end plate, and then the end plate is fixed, so that the single-lug joint penetrates through a central through hole of the end plate, and the single-lug joint can laterally move in the central through hole;

the other end of the single lug joint is sequentially provided with an elastic threaded sleeve, a stud, a load sensor and a double lug joint, and the double lug joint and the right main undercarriage false wheel are connected through a double lug joint bolt.

Optionally, in the course restriction device for the right main landing gear of the aircraft, the base and the end plate are circumferentially provided with connecting holes for installing bushing bolts at symmetrical positions, the base is provided with at least two through holes for installing stud bolts, the central through hole of the end plate is a rectangular through hole, and the edge of the rectangular through hole is provided with a triangular reinforcing rib.

Optionally, in the aircraft right main landing gear heading restraint apparatus as described above, the bushing is a tubular structure mounted centrally on a bushing bolt for forming an interior space between the base and the end plate in which the roller assembly is mounted.

Optionally, in the course restraining device for the right main landing gear of the aircraft as described above, the elastic threaded sleeve is of a cylindrical structure, and a rectangular groove for rotating the elastic threaded sleeve and observing the connection condition is formed in the cylindrical center of the elastic threaded sleeve;

the elastic thread insert is used for adjusting the total length of the course restraining device through rotation.

Optionally, in the aircraft right main landing gear heading restraint device as described above, the roller assembly further includes: a thrust bearing installed between the roller bracket and the roller, and a thrust bearing installed between the bolt head of the roller bolt and the roller.

Optionally, in the aircraft right main landing gear heading restriction device as described above, the elastic threaded sleeve, the stud bolt and the load sensor which are arranged between the single lug joint and the double lug joint are in hard connection.

Optionally, in the aircraft right main landing gear heading restraint device as described above,

in the test process, the forward deformation of the airplane structure is restrained by 4 rollers contacting the base, and the backward deformation of the airplane structure is restrained by 4 rollers contacting the end plate.

Optionally, in the aircraft right main landing gear heading restraint device as described above, during the test, the left and right movement of the right main landing gear is realized by 4 rollers rolling in the inner space between the base and the end plate.

Optionally, in the aircraft right main landing gear heading restraint device as described above,

when the course restraining device bears the tensile load, the roller is used for rolling left and right on the inner side of the end plate along the lateral direction of the airplane;

when the course restraining device bears the compressive load, the roller is used for rolling left and right along the lateral direction of the airplane on the inner side of the base.

According to the aircraft right main landing gear course restraining device provided by the embodiment of the invention, the total length of the frame course restraining device can be adjusted through the elastic thread sleeve, so that the course restraining load of the right main landing gear is zero before a test; the lug joints and the double lug joints are assembled in a hard connection mode, so that the course restraining device can bear tensile load and compressive load; when the aircraft bears a tensile load, the roller can roll along the lateral direction of the aircraft on the inner side of the end plate, and when the aircraft bears a compressive load, the roller can roll along the lateral direction of the aircraft on the inner side of the base, so that the fore-and-aft deformation of the right main undercarriage of the aircraft along the course of the aircraft is effectively restrained, and the coordinated movement of the right main undercarriage along the lateral direction of the aircraft is realized. In addition, the aircraft right main landing gear course restraining device provided by the invention is convenient to machine and assemble parts and low in cost; the course restraining device ensures safe and reliable course restraint of the right main undercarriage, the right main undercarriage moves flexibly laterally, and the restraining requirement of the main undercarriage in the airplane ground test is met.

Drawings

The accompanying drawings are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the example serve to explain the principles of the invention and not to limit the invention.

FIG. 1 is a schematic diagram of a test structure deformation of an aircraft during ground verification of structural strength of the aircraft;

FIG. 2 is a schematic diagram of the left and right main landing gear constraint patterns in ground validation of aircraft structural strength;

FIG. 3 is a schematic structural diagram of a current aircraft right main landing gear heading constraint device;

FIG. 4 is a schematic structural diagram of a heading constraint device for a right main landing gear of an aircraft according to an embodiment of the present invention;

FIG. 5 is a schematic structural diagram of an upright bolt in a heading restraining device of a right main landing gear of an aircraft according to an embodiment of the invention;

FIG. 6 is a schematic structural diagram of an upright post in a heading restraint device of a right main landing gear of an aircraft according to an embodiment of the invention;

FIG. 7 is a schematic structural diagram of a base in a heading restraint device of a right main landing gear of an aircraft according to an embodiment of the invention;

FIG. 8 is a schematic structural diagram of an end plate of a heading restraint device for a right main landing gear of an aircraft according to an embodiment of the invention;

FIG. 9 is a schematic structural view of a bushing in a heading restraint device of a right main landing gear of an aircraft according to an embodiment of the invention;

FIG. 10 is a schematic structural diagram of a single-lug joint in a heading restraint device for a right main landing gear of an aircraft according to an embodiment of the invention;

FIG. 11 is a schematic structural view of a turnbuckle in a heading restraining device of a right main landing gear of an aircraft according to an embodiment of the invention;

FIG. 12 is a schematic structural diagram of a stud in a heading restraint device of a right main landing gear of an aircraft according to an embodiment of the invention;

FIG. 13 is a schematic structural diagram of a load sensor in a heading restraint system for a right main landing gear of an aircraft according to an embodiment of the invention;

FIG. 14 is a schematic structural diagram of a binaural joint in a heading constraint device for a right main landing gear of an aircraft according to an embodiment of the present invention;

FIG. 15 is a schematic structural diagram of a roller in a heading restraint device of a right main landing gear of an aircraft according to an embodiment of the invention;

fig. 16 is a schematic structural diagram of a roller bracket in a heading restraining device of a right main landing gear of an aircraft according to an embodiment of the invention.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the embodiments and features of the embodiments in the present application may be arbitrarily combined with each other without conflict.

The following specific embodiments of the present invention may be combined, and the same or similar concepts or processes may not be described in detail in some embodiments.

Fig. 4 is a schematic structural diagram of a heading constraint device of a right main landing gear of an aircraft according to an embodiment of the present invention. The aircraft right main landing gear heading restraint device provided by the embodiment can comprise: the device comprises an upright bolt 1, an upright 2, a base 3, a bushing 4, a bushing bolt 5, an end plate 6 with a central through hole, a single lug joint 7, a turnbuckle 8, a stud 9, a load sensor 10, a double lug joint 11, a double lug joint bolt 12, a right main undercarriage false wheel 13, a single lug joint bolt 14 and a roller assembly. The roller assembly comprises a roller bracket 16, 4 rollers 15 arranged in upper and lower mounting holes at two sides of the roller bracket 16, and a roller bolt 18 for mounting the rollers 15, wherein the roller bracket 16 is connected with one end of the monaural joint 7 through a central mounting hole and a monaural joint bolt 14.

In the structure of the course restraining device of the right main landing gear of the airplane as shown in fig. 4, a base 3 is installed on an upright 2 through an upright bolt 1, the base 3, a bushing 4 and an end plate 6 are sequentially connected through a bushing bolt 5, and in the process of connecting the base 3, the bushing 4 and the end plate 6, a roller assembly is installed in an inner space between the base 3 and the end plate 6 and then the fixed end plate 6 is pressed tightly, so that a monaural joint 7 penetrates through a central through hole of the end plate 6, and the monaural joint 7 can move laterally in the central through hole.

It should be noted that, before the structure is installed, in the embodiment of the present invention, the rollers 15 may be installed in the mounting holes on both sides of the roller bracket 16 (including the mounting holes above both sides and the mounting holes below both sides, and 4 mounting holes corresponding to the 4 rollers 15) through the roller bolts 18; one end of the monaural joint 7 is fitted over the central mounting hole of the roller bracket 16 by a monaural joint bolt 14.

After the installation structure is completed, the other end of the single lug joint 7 can be sequentially provided with a loose screw sleeve 8, a stud 9, a load sensor 10 and a double lug joint 11, and is connected with the double lug joint 11 and a right main undercarriage false wheel 13 through a double lug joint bolt 12.

The following respectively describes each component in the aircraft right main landing gear heading restriction device provided by the embodiment of the invention in detail.

Fig. 5 is a schematic structural diagram of an upright bolt in a heading restraining device of a right main landing gear of an aircraft according to an embodiment of the invention. As shown in FIG. 5, the stud bolt 1 in the embodiment of the present invention may use an existing member, has a long length, needs to pass through the stud 2, is provided with one nut, may be made of 30CrMnSiA, and has a heat treatment level of 1000MPa, as shown in FIG. 5, and therefore, M36 external threads are processed within 60 cm of both ends of the stud bolt 1 for the fixed connection of the base 3 and the stud 2.

Fig. 6 is a schematic structural diagram of an upright post in a heading restraining device of a right main landing gear of an aircraft according to an embodiment of the invention. As shown in fig. 6, the upright 2 in the embodiment of the present invention may be an existing member including a horizontal portion connected to the ground and a vertical portion connected to the base 3, and may be made of a material Q345, a welding member, for connecting the heading restraint device to the ground.

Fig. 7 is a schematic structural diagram of a base in the aircraft right main landing gear heading restraint device provided in the embodiment of the present invention, and fig. 8 is a schematic structural diagram of an end plate in the aircraft right main landing gear heading restraint device provided in the embodiment of the present invention. Referring to fig. 7 and 8, in the embodiment of the present invention, connection holes for installing bushing bolts are formed in the circumferential direction and at symmetrical positions of the base 3 and the end plate 6, at least two through holes for installing the stud bolts 1 are formed in the base 3, the central through hole of the end plate 6 is a rectangular through hole, and triangular reinforcing ribs are formed on the edges of the rectangular through hole.

In practical application, the base 3 is a rectangular steel member, the material can be Q345, the thickness is 40 mm, as shown in fig. 7, M36 internal threads are processed on two large holes for connecting with M36 external threads of the upright bolt 1, ten small holes are processed into fisheye holes for installing the lining bolt 5, and the bolt head of the lining bolt 5 can sink into the large hole of the fisheye hole. The end plate 6 is a rectangular steel member, the material can be Q345, the thickness is 40 mm, as shown in fig. 8, a connecting hole with the same position as the base 3 is processed on the end plate 6, a rectangular through hole is processed in the center of the end plate 6, the single lug connector 7 can move laterally in the rectangular through hole, and a triangular reinforcing rib is processed on the edge of the through hole to increase the strength of the end plate 6.

FIG. 9 is a schematic structural diagram of a bushing in a heading restraining device for a right main landing gear of an aircraft according to an embodiment of the invention. As shown in fig. 9, the bushing 4 of the embodiment of the present invention is a tubular steel member, which may be Q235, and the bushing 4 is placed at the center of the bushing bolt 5 to make a space for installing the roller 15 between the base 3 and the end plate 6.

The bushing bolt 5 in the embodiment of the invention can be a 12.9-grade long bolt processed according to GB/T5782-2000, and is provided with a nut and a gasket, wherein the bolt is generally designed as M30 and is used for connecting the base 3 and the end plate 6, and the bushing 4 is placed in the center during connection.

FIG. 10 is a schematic structural diagram of a single-lug joint in a heading restraining device of a right main landing gear of an aircraft according to an embodiment of the invention. The material of the single lug joint 7 in the embodiment of the invention can be 30CrMnSiA, the heat treatment level is 1000MPa, as shown in figure 10, one end of the single lug joint 7 is processed into a through hole with phi 30 and is used for connecting the single lug joint 7 with the roller bracket 16, and the other end of the single lug joint 7 is processed into M27 right-hand external threads and is used for connecting the single lug joint 7 with M27 right-hand internal threads at one end of the elastic thread insert 8.

Fig. 11 is a schematic structural diagram of an elastic threaded sleeve in a heading restraining device of a right main landing gear of an aircraft according to an embodiment of the invention. In the embodiment of the invention, the elastic thread sleeve 8 is a cylindrical steel member, the material can be 30CrMnSiA, the heat treatment level is 1000MPa, as shown in figure 11, one end of the elastic thread sleeve 8 is processed into M27 right-handed internal threads for being connected with M27 right-handed external threads at one end of the single lug joint 7, the other end of the elastic thread sleeve 8 is processed into M27 left-handed internal threads for being connected with M27 left-handed external threads at one end of the stud bolt 9, and a rectangular groove for rotating the elastic thread sleeve 8 and observing the connection condition of the threads is processed in the cylindrical center of the elastic thread sleeve 8.

It should be noted that the total length of the heading constraint device in the embodiment of the present invention may be adjusted by rotating the elastic threaded sleeve 8, so as to ensure that the heading constraint load of the right main landing gear is zero before the test.

Fig. 12 is a schematic structural diagram of a stud in a heading restraining device for a right main landing gear of an aircraft according to an embodiment of the invention. The stud 9 in the embodiment of the invention is a cylindrical steel member, the material of the stud 9 can be 30CrMnSiA, the heat treatment level is 1000MPa, as shown in FIG. 12, one end of the stud 9 is processed with M27 left-hand external threads and connected with M27 left-hand internal threads of the elastic thread sleeve 8, the other end of the stud 9 is processed with M27 right-hand external threads and connected with the load sensor 10, and the center is processed with M30 external hexagonal threads for clamping by a wrench during installation.

Fig. 13 is a schematic structural diagram of a load sensor in a heading restraining device of a right main landing gear of an aircraft according to an embodiment of the invention. The load sensor 10 in the embodiment of the invention can adopt an existing component for measuring and monitoring the vertical load of the right main landing gear, and M27 internal threads are machined at two ends of the load sensor 10.

Fig. 14 is a schematic structural diagram of a binaural joint in the heading restriction device for the right main landing gear of the aircraft according to the embodiment of the present invention. In the embodiment of the invention, the material of the double-lug joint 11 can be 30CrMnSiA, the heat treatment level is 1000MPa, as shown in FIG. 14, one end of the double-lug joint 11 is processed into a through hole with phi 30 and used for connecting the double-lug joint 11 with the right main landing gear fake wheel 13, and the other end of the double-lug joint 11 is processed into M27 right-hand external threads and used for connecting the double-lug joint 11 with M27 right-hand internal threads at one end of the load sensor 10.

The dummy wheel 13 of the right main landing gear in the embodiment of the invention is an airplane component, and is connected with the heading restraining device of the right main landing gear of the airplane provided by the embodiment of the invention through the aircraft component.

The lug joint bolt 14 of the present embodiment is a class 12.9 bolt manufactured according to GB/T5782-2000, with a nut and washer, typically designated M30, for connection of the lug joint 7 to the roller bracket 16.

FIG. 15 is a schematic structural diagram of a roller in a heading restraining device for a right main landing gear of an aircraft according to an embodiment of the invention. The rollers 15 in the embodiment of the present invention may be made of 45 steel, and have four pieces, a heat treatment level of 800MPa, a surface roughness of 1.6 level, and a diameter of 2 mm smaller than the length of the bushing 4, and as shown in fig. 15, are respectively installed on the upper and lower sides of the roller support 16, and can roll laterally in the space between the base 3 and the end plate 6.

Fig. 16 is a schematic structural diagram of a roller bracket in a heading restraining device of a right main landing gear of an aircraft according to an embodiment of the invention. The roller bracket 16 in the embodiment of the invention is a rectangular porous steel member, the material can be 30CrMnSiA, the heat treatment level is 1000MPa, as shown in FIG. 16, the central mounting hole of the roller bracket 16 can be a horizontal square hole for mounting the single lug joint 7, and four circular through holes on the upper side and the lower side are used for mounting the rollers 15 in a one-to-one correspondence manner.

In practical applications, the roller assembly in the embodiment of the present invention may further include: a thrust bearing 17 installed between the roller bracket 16 and the roller 15, and a thrust bearing 17 installed between the bolt head of the roller bolt 18 and the roller 15. As shown in fig. 4, the thrust bearing 17 of the embodiment of the present invention may be formed of eight existing members, and is installed between the roller bracket 16 and the roller 15, and also installed between the bolt head of the roller bolt 18 and the roller 15, for reducing the frictional resistance of the roller 15 in rolling.

The roller bolt 18 in the embodiment of the present invention is similar to the one-ear joint bolt 14 for mounting the roller 15 on both sides of the roller bracket 16.

The installation mode of the aircraft right main landing gear course restraining device provided by the embodiment of the invention is as follows:

1) the base 3 is arranged on the upright post 2 through an upright post bolt 1;

2) the base 3 and the bush 4 are connected through a bush bolt 5;

3) a thrust bearing 17 and a roller 15 are arranged above and below the mounting holes at two sides of the roller bracket 16 through a roller bolt 18 to form a roller assembly;

4) before the end plate 6 is installed, a roller assembly is installed between the base 3 and the bushing 4;

5) installing an end plate 6 and pressing the end plate by a bushing bolt 5;

6) assembling a single lug joint 7 on a central mounting hole of a roller bracket 16 through a single lug joint bolt 14; the monaural joint 7 is made to pass through the central through hole of the end plate 6;

7) after the single lug joint 7, the elastic threaded sleeve 8, the stud bolt 9, the load sensor 10 and the double lug joint 11 are connected in sequence, the double lug joint 11 and the right main undercarriage false wheel 13 are connected through the double lug joint bolt 12.

In the course restraining device of the right main landing gear of the airplane provided by the embodiment of the invention, the elastic threaded sleeve 8, the stud bolt 9 and the load sensor 10 which are assembled between the single lug joint and the double lug joint are in hard connection, so that the course restraining device can bear tensile load and compressive load.

In the process of testing by adopting the aircraft right main landing gear course restraining device provided by the embodiment of the invention, the forward deformation of the aircraft structure is restrained by contacting 4 rollers 15 with the base 3, the backward deformation of the aircraft structure is restrained by contacting 4 rollers 15 with the end plate 6, and the restrained load is measured by the load sensor 10.

In addition, during the test, the left and right movement of the right main landing gear is realized by the rolling of 4 rollers 15 in the inner space between the base 3 and the end plate 6.

In a specific implementation, when the course restraining device bears tensile load, the roller 15 can roll along the lateral direction of the airplane on the inner side of the end plate in a follow-up manner; when the course restraint device bears compressive load, the roller 15 can roll along the lateral direction of the airplane on the inner side of the base. The front and back deformation of the right main undercarriage of the airplane along the course of the airplane is effectively restrained, and the lateral coordinated movement of the right main undercarriage of the airplane along the airplane is realized.

According to the aircraft right main landing gear course restraining device provided by the embodiment of the invention, the total length of the frame course restraining device can be adjusted through the elastic thread sleeve, so that the course restraining load of the right main landing gear is zero before a test; the lug joints and the double lug joints are assembled in a hard connection mode, so that the course restraining device can bear tensile load and compressive load; when the aircraft bears a tensile load, the roller can roll along the lateral direction of the aircraft on the inner side of the end plate, and when the aircraft bears a compressive load, the roller can roll along the lateral direction of the aircraft on the inner side of the base, so that the fore-and-aft deformation of the right main undercarriage of the aircraft along the course of the aircraft is effectively restrained, and the coordinated movement of the right main undercarriage along the lateral direction of the aircraft is realized. In addition, the aircraft right main landing gear course restraining device provided by the invention is convenient to machine and assemble parts and low in cost; the course restraining device ensures safe and reliable course restraint of the right main undercarriage, the right main undercarriage moves flexibly laterally, and the restraining requirement of the main undercarriage in the airplane ground test is met.

Although the embodiments of the present invention have been described above, the above description is only for the convenience of understanding the present invention, and is not intended to limit the present invention. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.