CN111452994B - Aircraft nose landing gear supporting device - Google Patents
Aircraft nose landing gear supporting device Download PDFInfo
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- CN111452994B CN111452994B CN202010323675.5A CN202010323675A CN111452994B CN 111452994 B CN111452994 B CN 111452994B CN 202010323675 A CN202010323675 A CN 202010323675A CN 111452994 B CN111452994 B CN 111452994B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The application belongs to the technical field of aircraft structural strength ground test, in particular to aircraft nose landing gear supporting device for supporting aircraft nose landing gear during aircraft structural strength ground test, include: a support base having a support plate at the top thereof; the ball support is arranged on the support plate, and the top surface of the ball support is provided with a plurality of ball holes and adaptive balls; the clip-shaped frame is arranged on the ball bearing bracket; the upper end cover is covered on the clip-shaped frame; the single lug of the basket is movably arranged in the square-shaped frame, the single lug penetrates through the through hole of the upper end cover, and the top surface of the flat plate is provided with a plurality of ball holes and adaptive balls; and the sensor fixing part is used for fixedly connecting the load sensor with the single lug part of the single lug of the lifting basket and the false wheel of the nose landing gear. The supporting device for the nose landing gear of the airplane has the advantages of convenience in part machining and assembly, low cost, safety and reliability, and the nose landing gear can freely move longitudinally and laterally, so that the supporting requirement of the ground test of the airplane on the nose landing gear is met.
Description
Technical Field
The application belongs to the technical field of aircraft structural strength ground tests, and particularly relates to an aircraft nose landing gear supporting device.
Background
The ground test of the structural strength of the airplane needs to complete the full-airplane test under various working conditions, and when the bending and twisting combined working condition test of the front airplane body is carried out, the front undercarriage generates lateral and longitudinal deformation, as shown in figures 1 and 2. When the front fuselage bending and twisting combined working condition test is carried out, the airplane is supported in a front and main hoisting suspension mode, namely, the airplane is suspended in a crow bar mode in the vertical direction of the front hoisting dummy wheels, the left main hoisting dummy wheels and the right main hoisting dummy wheels, so that the airplane is in a suspension state (see figure 3); selecting a left main undercarriage to form a fixed support and limit the vertical, longitudinal and lateral displacement of the airplane; selecting a right main landing gear to limit the vertical and lateral displacement of the airplane; the nose landing gear limits the vertical displacement of the airplane and relaxes the longitudinal displacement and the lateral displacement. According to the supporting method, when the lateral and longitudinal deformation of the front landing gear is large, the horizontal rotation angle of the crow bar is large, the vertical support deviates from the central line of the supporting upright column, the aircraft support is unreliable, and the risk of twisting off the crow bar, the pulling plate and the sensor exists.
Disclosure of Invention
In order to solve at least one of the above technical problems, the present application provides an aircraft nose landing gear support device.
The application discloses aircraft nose landing gear supporting device for supporting aircraft nose landing gear during aircraft structural strength ground test, include
The bottom of the supporting base is fixed, and the top of the supporting base is provided with a horizontal supporting plate;
the ball support is horizontally and fixedly arranged on the top surface of the supporting plate, a plurality of first ball holes are formed in the middle of the top surface of the ball support, and first balls matched with the first ball holes are arranged in the first ball holes;
the square-shaped frame is fixedly arranged on the upper surface of the ball support, a cavity is formed in the middle of the square-shaped frame, and a first ball hole in the ball support is located in the cavity;
the upper end cover is fixedly covered on the upper surface of the square-shaped frame, and a through hole is formed in the upper end cover in a penetrating manner;
the single basket lug comprises a flat plate part at the bottom and a single lug part vertically arranged on the flat plate part, wherein the flat plate part is horizontally arranged in a cavity of the square-shaped frame, the single lug part penetrates through a through hole of the upper end cover from bottom to top, the flat plate part can drive the single lug part to horizontally move on a first ball in the cavity of the square-shaped frame, in addition, the top surface of the flat plate part is provided with a plurality of second ball holes, and the second ball holes are internally provided with second balls which are matched with each other;
the sensor fixing piece is characterized in that a load sensor is arranged in the middle of the sensor fixing piece, the bottom end of the sensor fixing piece is fixedly connected with the single lug part of the single lug of the basket, and the top end of the sensor fixing piece is fixedly connected with the false wheel of the nose landing gear.
According to at least one embodiment of the present application, the load sensor is cylindrical, and internal threaded holes are formed at both axial ends of the load sensor;
the sensor mount includes:
two diplopore joints with the same structure, one end of each diplopore joint is a double-lug part, and the other end is provided with a threaded column, wherein
One double-hole joint is fixedly connected with the single lug part of the single lug of the lifting basket at the bottom through the double lug parts of the double-hole joint and is in threaded connection with the load sensor at the top through a threaded column;
and the other double-hole joint is fixedly connected with the nose landing gear false wheel at the top through double lugs of the double-hole joint and is in threaded connection with the load sensor at the bottom through a threaded column.
According to at least one embodiment of the application, two bolt holes are respectively formed in the double lug parts of the double-hole joint and the single lug parts of the single lugs of the lifting basket along the vertical direction, and the double-hole joint and the single lug parts of the single lugs of the lifting basket are fixed through adaptive short bolts.
According to at least one embodiment of the application, two bolt holes are respectively formed in the double lug parts of the double-hole joint and the false nose landing gear wheel in the vertical direction, and the double lug parts and the false nose landing gear wheel are fixed through adaptive short bolts.
According to at least one embodiment of the application, a plurality of fixing through holes are respectively formed in the integral piece composed of the support plate, the ball support, the clip-shaped frame and the upper end cover in a penetrating mode in the horizontal direction of the integral piece, and the integral piece is provided with the matched long bolts.
According to at least one embodiment of the present application, the first ball hole of the ball support is a square through hole, the side length of the square through hole is larger than the diameter of the first ball, and the thickness of the ball support is smaller than the diameter of the first ball.
According to at least one embodiment of the present application, the second ball hole on the top surface of the flat plate portion is a counter bore, the depth of the counter bore is smaller than the diameter of the second ball, and the side length of the counter bore is larger than the diameter of the second ball.
According to at least one embodiment of the present application, the support base further comprises:
a horizontally disposed beam portion, a bottom of which is fixed;
the top of the supporting rod is fixedly arranged in the middle of the top of the beam part, and the supporting plate is fixedly arranged on the top of the supporting rod.
The application has at least the following beneficial technical effects:
the supporting device for the nose landing gear of the airplane has the advantages of convenience in part machining and assembly, low cost, safety and reliability, and the nose landing gear can freely move longitudinally and laterally, so that the supporting requirement of the ground test of the airplane on the nose landing gear is met.
Drawings
FIG. 1 is a schematic diagram of a front deformation of an aircraft test structure (wherein the upper and lower diagrams are schematic diagrams before and after change);
FIG. 2 is a schematic side deformation diagram of an aircraft test structure (wherein the upper diagram and the lower diagram are schematic diagrams before and after change);
FIG. 3 is a prior art pre-operative landing gear crow bar support;
fig. 4 is a schematic structural view (structural exploded view) of the nose landing gear support device of the aircraft;
FIG. 5 is a schematic view of the structure of a support base in the nose landing gear support of the aircraft;
FIG. 6 is a schematic view of a ball bearing support in the nose landing gear support of the aircraft;
FIG. 7 is a schematic view of the structure of a clip frame in the nose landing gear support of an aircraft;
FIG. 8 is a schematic view of the construction of an upper head cover in the nose landing gear support of the aircraft;
FIG. 9 is a schematic view of a single lug of a basket in the nose landing gear support of the aircraft;
fig. 10 is a schematic view of the structure of a double-bore joint in a nose landing gear support device for an aircraft.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the accompanying drawings are illustrative and intended to explain the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
It should be understood that in the description of the present application, the orientation or positional relationship that may be referred to by technical terms such as "central", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., is based on the orientation or positional relationship shown in the drawings, and is only for convenience of description and simplicity of description, and does not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the scope of the present application.
The aircraft nose landing gear support device of the present application is described in further detail below with reference to fig. 4-10.
The application discloses a supporting device for a nose landing gear of an airplane, which is used for supporting the nose landing gear of the airplane during a ground test of the structural strength of the airplane; as shown in fig. 4, the aircraft nose landing gear supporting device may include a supporting base 1, a ball bracket 2, a frame 4, an upper end cover 7, a single basket ear 6, a load sensor 10, a sensor fixing member, and other components.
Specifically, the bottom of the support base 1 is fixed, for example, may be fixed on the ground of the laboratory through a special bolt; in addition, as shown in fig. 5, a horizontal support plate 11 is provided on the top of the support base 1.
As shown in fig. 6, the ball holder 2 is flat and horizontally fixed on the top surface of the support plate 11, a plurality of first ball holes 21 (or through holes) are formed in the middle of the top surface of the ball holder 2, and first balls 31 are disposed in the first ball holes 21.
It should be noted that the number and the sequencing of the first ball holes 21 may be various, in this embodiment, it is preferable that the first ball holes 21 on the ball support 2 are square through holes, the square through holes are arranged in four rows and four columns, the side length of the through holes is 1 mm larger than the diameter of the first ball 31, and the thickness of the ball support 2 is 2 mm smaller than the diameter of the first ball 31.
As shown in fig. 7, the frame 4 is fixed on the upper surface of the ball support 2, and is preferably a hollow steel member with a shape like a Chinese character 'hui', so that the frame 4 has a cavity in the middle, and the cavity can be in various suitable shapes, such as rectangle, ellipse, etc., wherein the first ball hole 21 of the ball support 2 is located in the cavity.
As shown in fig. 8, the upper end cap 7 is fixedly covered on the upper surface of the clip frame 4, and a through hole is formed through the upper end cap 7.
As shown in fig. 9, the single handle 6 includes a bottom plate portion 61 and a single ear portion 62 vertically disposed on the bottom plate portion 61; the flat plate part 61 is horizontally arranged in the cavity of the square-shaped frame 4, and the single lug part 62 penetrates through the through hole of the upper end cover 7 from bottom to top; the bottom surface of the flat plate part 61 contacts with the first ball 31 in the cavity of the square-wave frame 4, so that the single lug part 62 can be driven to horizontally move in the cavity of the square-wave frame 4, and it should be noted that the through hole on the upper end cover 7 is provided with a shape meeting the horizontal movement requirement of the single lug part 62; in addition, a plurality of second ball holes 63 are formed in the top surface of the flat plate portion 61, and the second balls 32 which are matched with each other are arranged in the second ball holes 63, so that when the single basket lug 6 moves upwards under tension, the top surface of each second ball 32 can be in contact with the bottom surface of the upper end cover 7, and the horizontal movement of the single basket lug 6 is not affected.
Similarly, the number and the sequencing manner of the second ball holes 63 on the top surface of the flat plate portion 61 may be various, in this embodiment, the second ball holes 63 are counter bores, the depth of the counter bores is less than 2 mm of the diameter of the second balls 32, and the side length of the counter bores is greater than 1 mm of the diameter of the second balls 32.
In addition, the single basket lug 6 can only move in the cavity of the square-shaped frame 4, the sum of the upper gap and the lower gap of the single basket lug 6 is preferably 2 mm, and the longitudinal distance and the lateral distance are designed according to the deformation of the nose landing gear during the airplane test. Further, it is preferable that the four sides of the lower end surface of the basket single lug 6 are rounded to be in the order of R15 mm, and the radius of the balls (i.e., the first ball 31 and the second ball 32) is also in the order of R15 mm, and it is preferable that the basket single lug 6 is a spherical steel member processed from 45 steel, and has a heat treatment level of 800MPa and a surface roughness level of 1.6, and the basket single lug 6 is not blocked by the balls when moving between the upper and lower sets of balls.
The load sensor 10 is fixedly arranged in the middle of a sensor fixing piece, the bottom end of the sensor fixing piece is fixedly connected with the single lug part 62 of the single basket lug 6, and the top end of the sensor fixing piece is fixedly connected with the nose landing gear false wheel 14.
To sum up, in the aircraft nose landing gear supporting device of the present application, after a set of balls (i.e., the first ball 31 and the second ball 32) is respectively placed on the ball support 2 and the single basket lug 6, the ball support 2, the square-shaped frame 4, the single basket lug 6 and the upper end cover 7 are fixedly installed above the supporting base 1 in sequence; further, the load sensor 10 is fixedly connected with the upper and lower false nose landing gear wheels 14 and the basket single lug 6 through the sensor fixing piece, so that the aircraft nose landing gear supporting device effectively supports the aircraft in the vertical direction and realizes free movement of the nose landing gear in the longitudinal direction and the lateral direction.
The supporting device for the nose landing gear of the airplane is convenient to machine and assemble parts and low in cost; the supporting device for the nose landing gear of the airplane is safe and reliable in supporting, the nose landing gear can freely move longitudinally and laterally, and the supporting requirement of the ground test of the airplane on the nose landing gear is met.
Further, in the aircraft nose landing gear supporting device of the present application, the shape of the load sensor 10 may be selected as various as required, and correspondingly, the structure of the sensor fixing member may also be adaptively adjusted according to the shape of the load sensor 10; in this embodiment, as shown in fig. 9 and 10, the load sensor 10 is preferably cylindrical, and both ends in the axial direction thereof are provided with internal threaded holes; correspondingly, the sensor mount comprises two identically constructed double bore connections 9.
Specifically, one end of each double-hole joint 9 is a double-lug part 91, and the other end is provided with a threaded column 92, wherein one double-hole joint 9 (see the lower double-hole joint 9 in fig. 4) is fixedly connected with the single lug part 62 of the single basket lug 6 at the bottom through the double-lug part 91, and is in threaded connection with the load sensor 10 at the top through the threaded column 92; more specifically, two bolt holes are respectively formed in the double lug part 91 of the double-hole joint 9 and the single lug part 62 of the single basket lug 6 in the vertical direction, and the two bolt holes are fixed by the short bolts 8.
Correspondingly, the other double-hole joint 9 (see the upper double-hole joint 9 in fig. 4) is fixedly connected with the nose landing gear false wheel 14 at the top through the double lug parts 91 thereof, and is in threaded connection with the load sensor 10 at the bottom through the threaded columns 92. More specifically, two bolt holes are respectively formed in the double lug part 91 of the double-hole joint 9 and the nose landing gear false wheel 14 in the vertical direction, and are fixed by the short bolts 8.
Further, in the aircraft nose landing gear support device of the present application, the support plate 11, the ball support 2, the frame 4 and the upper end cap 7 may be fixed to each other by various suitable means, such as welding, bolting; in the present embodiment, as shown in fig. 4, preferably, a plurality of fixing through holes are respectively formed through the integral member composed of the support plate 11, the ball support 2, the square frame 4 and the upper end cover 7 on both sides in the horizontal direction, for example, 4 to 5 fixing through holes are uniformly formed on each side, and the integral member is provided with the adapted long bolts 5.
Similarly, in the aircraft nose landing gear support device according to the present application, the structure of the support base 1 may be suitably arranged as needed, and in the present embodiment, as shown in fig. 5, it is preferable that the support base 1 is a steel member, and is formed by welding a channel steel as a framework, and a square support plate 11 is welded above the channel steel, and two rows of Φ 30 bolt holes (that is, the above-mentioned fixing through holes) are processed on both sides of the square support plate 11, and are used for assembling the ball support 2, the clip frame 4, the single carrier lug 6, and the upper end cap 7.
Further, it is preferable that the supporting base 1 further includes a beam portion 12 and a supporting rod 13; the beam part 12 is formed by arranging two pieces of channel steel in parallel, is wholly horizontally arranged, and is fixedly connected with the ground of a laboratory by penetrating a gap between the two pieces of channel steel through a special bolt. The supporting rods 13 may be vertically disposed, the top of the supporting rod 13 is fixedly disposed (e.g., welded) at the middle position of the top of the beam portion 12, and the top of the supporting rod 13 is fixedly disposed (e.g., welded) with the supporting plate 11.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. The utility model provides an aircraft nose landing gear supporting arrangement for support aircraft nose landing gear when aircraft structural strength ground test, a serial communication port, include
The supporting base (1), the bottom of the supporting base (1) is fixed, and the top of the supporting base (1) is provided with a horizontal supporting plate (11);
the ball bearing support is characterized by comprising a flat-plate-shaped ball support (2), wherein the ball support (2) is horizontally and fixedly arranged on the top surface of the support plate (11), a plurality of first ball holes (21) are formed in the middle of the top surface of the ball support (2), and first balls (31) which are matched with each other are arranged in the first ball holes (21);
the square-shaped frame (4), the square-shaped frame (4) is fixedly arranged on the upper surface of the ball support (2), a cavity is formed in the middle of the square-shaped frame (4), and a first ball hole (21) in the ball support (2) is located in the range of the cavity;
the upper end cover (7) is fixedly covered on the upper surface of the square-shaped frame (4), and a through hole is formed in the upper end cover (7) in a penetrating manner;
the basket single lug (6) comprises a flat plate part (61) at the bottom and a single lug part (62) vertically arranged on the flat plate part (61), wherein the flat plate part (61) is horizontally arranged in a cavity of the square-shaped frame (4), the single lug part (62) penetrates through a through hole of the upper end cover (7) from bottom to top, the flat plate part (61) can drive the single lug part (62) to horizontally move on a first ball (31) in the cavity of the square-shaped frame (4), in addition, the top surface of the flat plate part (61) is provided with a plurality of second ball holes (63), and the second ball holes (63) are internally provided with second balls (32) matched with each other;
the sensor fixing piece is characterized in that a load sensor (10) is arranged in the middle of the sensor fixing piece, the bottom end of the sensor fixing piece is fixedly connected with a single lug portion (62) of a single basket lug (6), and the top end of the sensor fixing piece is fixedly connected with a nose landing gear false wheel (14).
2. The aircraft nose landing gear support device according to claim 1, wherein the load sensor (10) is cylindrical, and has internal threaded holes formed at both axial ends thereof;
the sensor mount includes:
two diplopore joints (9) with the same structure, one end of each diplopore joint (9) is a double lug part (91), the other end is provided with a threaded column (92), wherein
One double-hole joint (9) is fixedly connected with the single lug part (62) of the single basket lug (6) at the bottom through a double-lug part (91) of the double-hole joint and is in threaded connection with the load sensor (10) at the top through a threaded column (92);
the other double-hole joint (9) is fixedly connected with the nose landing gear false wheel (14) at the top through double lug parts (91) of the double-hole joint, and is in threaded connection with the load sensor (10) at the bottom through a threaded column (92).
3. The aircraft nose landing gear support device according to claim 2, wherein two bolt holes are respectively formed in the double lug part (91) of the double-hole joint (9) and the single lug part (62) of the basket single lug (6) in the vertical direction, and the two bolt holes are fixed through the adaptive short bolts (8).
4. The aircraft nose landing gear supporting device according to claim 2, wherein two bolt holes are respectively formed in the double lug part (91) of the double-hole joint (9) and the nose landing gear false wheel (14) in the vertical direction, and the two bolt holes are fixed through the adaptive short bolts (8).
5. The aircraft nose landing gear supporting device according to claim 1, wherein a plurality of fixing through holes are respectively formed in the integral member composed of the supporting plate (11), the ball support (2), the square-shaped frame (4) and the upper end cover (7) in a penetrating manner on both sides in the horizontal direction, and the fixing through holes are provided with the long bolts (5) which are matched with each other.
6. Aircraft nose landing gear support device according to claim 1, wherein the support base (1) further comprises:
a horizontally arranged beam part (12), wherein the bottom of the beam part (12) is fixed;
and the top of the supporting rod (13) is fixedly arranged at the middle position of the top of the beam part (12), and the top of the supporting rod (13) is fixedly provided with the supporting plate (11).
7. Aircraft nose landing gear support device according to claim 1, wherein the first ball hole (21) of the ball support (2) is a square through hole, the side length of the square through hole is greater than the diameter of the first ball (31), and the thickness of the ball support (2) is less than the diameter of the first ball (31).
8. Aircraft nose landing gear support device according to claim 1, wherein the second ball hole (63) in the top face of the plate portion (61) is a counter bore, the depth of the counter bore being smaller than the diameter of the second ball (32), the side length of the counter bore being larger than the diameter of the second ball (32).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010323675.5A CN111452994B (en) | 2020-04-22 | 2020-04-22 | Aircraft nose landing gear supporting device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010323675.5A CN111452994B (en) | 2020-04-22 | 2020-04-22 | Aircraft nose landing gear supporting device |
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| CN111452994A CN111452994A (en) | 2020-07-28 |
| CN111452994B true CN111452994B (en) | 2023-03-24 |
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| CN113173260B (en) * | 2021-04-20 | 2024-04-09 | 中国飞机强度研究所 | All-machine statically indeterminate supporting device and method |
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