CN113911322B - Method for connecting front landing gear of large helicopter and transferring load - Google Patents
Method for connecting front landing gear of large helicopter and transferring load Download PDFInfo
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- CN113911322B CN113911322B CN202111376072.2A CN202111376072A CN113911322B CN 113911322 B CN113911322 B CN 113911322B CN 202111376072 A CN202111376072 A CN 202111376072A CN 113911322 B CN113911322 B CN 113911322B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/04—Arrangement or disposition on aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/22—Operating mechanisms fluid
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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
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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
Abstract
The application provides a method for connecting a nose landing gear of a large helicopter and transferring load, which comprises the following steps: determining a nose landing gear connection point A, a connection point B and a connection point C; connecting the connection point A, the connection point B and the connection point C with the machine body supporting structure; determining load transfer types of the connection point A, the connection point B and the connection point C, wherein the load transfer types comprise force and moment of each connection point; according to the load transfer type, determining load transfer values of the connection point A, the connection point B and the connection point C; according to the load transmission types of the connection point A, the connection point B and the connection point C, determining the specific installation forms of the connection point A, the connection point B and the connection point C of the nose landing gear; the specific mounting dimensions of nose landing gear connection point a, connection point B and connection point C are determined from the load transfer values of connection point a, connection point B and connection point C.
Description
Technical Field
The invention relates to the field of aircraft landing gear and machine body structural strength design, in particular to a method for connecting a front landing gear of a large helicopter and transmitting load.
Background
Because the self weight of the large helicopter is large (more than 20 tons), under the working conditions of landing and ground load, the magnitude of the load born by the landing gear is far greater than that of the active medium-sized helicopter, taking the helicopter which adopts the arrangement of the front three-point landing gear as an example, when the helicopter is horizontally landed at three points in the maximum weight state, the vertical load born by the front landing gear is approximately equal to the weight of the whole active medium-sized helicopter. The nose landing gear support structure cannot be designed to be heavy due to design weight limitations, while also taking into account ease of disassembly and maintenance. Based on the two design limits, the load transmission path of the nose landing gear connection point needs to be reasonably set, and the load transmission requirement is realized through corresponding connection and supporting structures.
Disclosure of Invention
The application provides a connection of a front landing gear of a large helicopter and a load transfer method, which can improve the weight efficiency of a supporting structure, realize quick disassembly and assembly of the landing gear and improve maintainability.
The technical scheme of the invention is as follows: the application provides a method for connecting a nose landing gear of a large helicopter and transferring load, which comprises the following steps:
determining a nose landing gear connection point A, a connection point B and a connection point C;
connecting the connection point A, the connection point B and the connection point C with the machine body supporting structure;
determining load transfer types of the connection point A, the connection point B and the connection point C, wherein the load transfer types comprise force and moment of each connection point;
according to the load transfer type, determining load transfer values of the connection point A, the connection point B and the connection point C;
according to the load transmission types of the connection point A, the connection point B and the connection point C, determining the specific installation forms of the connection point A, the connection point B and the connection point C of the nose landing gear;
the specific mounting dimensions of nose landing gear connection point a, connection point B and connection point C are determined from the load transfer values of connection point a, connection point B and connection point C.
Specifically, the connection point A is connected with a fixed strut of the non-retractable nose landing gear, or the connection point A is connected with a hydraulic actuator cylinder of the retractable landing gear;
the connecting point B is connected with a web plate of a right longitudinal beam of the front fuselage;
the connection point C is connected with the web plate of the left longitudinal beam of the front fuselage.
Specifically, the landing gear load is force in three directions Fx0, fy0, and Fz0, wherein:
the vertical load Fz0 is transmitted by the forces of Fzb and Fzc of the connection point B and the connection point C;
the side load Fy0 is transmitted by Fyb force of the connection point B;
the heading load is transferred by the forces of Fxa, fxb, fxc of connection point a, connection point B and connection point C,
fxa is the force of the connection point A in the x direction; fxb, fyb, fzb the forces in the x, y and z directions at the connection point B; fxc and Fzc are forces in the x-direction and z-direction, respectively, at the connection point C.
Specifically, according to the load transfer type, the load transfer values of the connection point a, the connection point B and the connection point C are determined, and specifically include:
the load transfer values for connection point a, connection point B and connection point C are determined according to the force and moment balance principles, and include Fxa, fxb, fyb, fzb, fxc, fzc.
Specifically, according to the force and moment balance principle, the load transmission values of the connection point A, the connection point B and the connection point C are determined, and the method specifically comprises the following steps:
the load transmission values Fxa, fxb, fyb, fzb, fxc, fzc of the connection point a, the connection point B, and the connection point C are calculated according to the following formula.
Vertical load: fz0= Fzb + Fzc;
side load: fy0=fyb;
heading load: fx0=fxa+fxb+ Fxc;
my moment balance: fx0 (l1+l2) =fxb×l1, fxb= Fxc;
mx moment balance: fy0 (L1+L2) = Fzb ×L3×0.5-Fzc ×L3×0.5
Wherein Fx0, fy0, fz0, L1, L2, L3 are predetermined values, L1 is the distance from the connection point a to the BC axis, L2 is the distance from the BC axis to the point O, and L3 is the distance between the connection point B and the connection point C.
Specifically, according to the load transmission values of the connection point a, the connection point B and the connection point C, the specific installation dimensions of the connection point a, the connection point B and the connection point C of the nose landing gear are determined, and the method specifically comprises the following steps:
determining the sizes of the single lug and the double lug at the connection point A and the brand of the connecting bolt according to Fxa;
determining the size of a bolt at the connecting point B according to Fxb, fyb, fzb and the brands of a joint bearing, a bushing, a gasket and a nut;
and determining the size of the bolt at the connection point C according to Fxc and Fzc, and the joint bearing and the lining mark.
Specifically, according to the load transmission types of the connection point A, the connection point B and the connection point C, the specific installation forms of the connection point A, the connection point B and the connection point C of the nose landing gear are determined, and the method specifically comprises the following steps:
the bushing and the knuckle bearing are respectively arranged at the left longitudinal beam bolt hole, the bushing and the knuckle bearing are respectively arranged at the right longitudinal beam web bolt hole, and the gasket and the bushing nut are arranged at the other side of the right longitudinal beam web. .
Specifically, connect the tie point a, the tie point B, and the tie point C with the body support structure, specifically including:
the connection point A is connected with a fixed support of the non-retractable nose landing gear by adopting a lug, or is connected with a hydraulic actuating cylinder of the retractable landing gear;
the connecting point B is connected with a web plate of a right longitudinal beam of the front fuselage by adopting a detachable bolt;
the connecting point C is connected with the web plate of the left longitudinal beam of the front fuselage by adopting a detachable bolt.
In summary, in the design of the helicopter nose landing gear connection and support structure, the load transmission path is reasonably designed by using the method, the weight of the landing gear support structure is reduced, and the structural efficiency is improved. Meanwhile, the whole process also considers the realization of disassembly and assembly, and is convenient for daily use and maintenance.
Drawings
FIG. 1 is a schematic view of a nose landing gear and connection points provided herein;
FIG. 2 is a schematic illustration of a load transfer at a connection point provided herein;
FIG. 3 is a schematic view of distances between connection points according to the present application;
FIG. 4 is a view of an attachment assembly provided herein at the opening of a left and right stringer;
FIG. 5 is a schematic view of mounting and securing left and right pins of a landing gear provided herein;
fig. 6 is a schematic view of a rear support structure load transfer provided herein.
Detailed Description
Example 1
The application provides a method for connecting a nose landing gear of a large helicopter and transferring load, which comprises the following steps:
step 101: nose landing gear connection point a, connection point B, and connection point C are determined.
As shown in fig. 1, the present application exemplifies the reverse heading arrangement of the nose landing gear top support structure, with the nose landing gear having A, B, C three connection points. The connecting point A is connected with a fixed support of the non-retractable nose landing gear, or is connected with a hydraulic actuating cylinder of the retractable landing gear; the connecting point B is connected with the right longitudinal beam web plate of the front fuselage, and the connecting point C is connected with the left longitudinal beam web plate of the front fuselage.
Step 102: the connection point A, the connection point B and the connection point C are connected with the machine body supporting structure.
The connection point A is connected with a fixed support of the non-retractable nose landing gear by adopting a lug, or is connected with a hydraulic actuating cylinder of the retractable landing gear.
The connecting point B is connected with the web plate of the right longitudinal beam of the front fuselage by adopting a detachable bolt.
The connecting point C is connected with the web plate of the left longitudinal beam of the front fuselage by adopting a detachable bolt.
In practical application, the connection point A is connected by adopting a single lug and a double lug, and the joint bearing is arranged in the single lug.
Step 103: the load transfer types of the connection point A, the connection point B and the connection point C are determined, wherein the load transfer types comprise the force and the moment of each connection point.
Specifically, the nose landing gear coordinate system xyz defines: the reverse heading of the X-axis is positive; the right side of the y-axis along the heading is positive; the z-axis is perpendicular to the x-axis and positive in the z-axis direction.
Fx0, fy0 and Fz0 are loads of the nose landing gear in the x direction, the y direction and the z direction respectively; fxa is the force of connection point a in the x direction; fxb, fyb, fzb the forces in the x, y and z directions at the connection point B; fxc and Fzc are forces in the x direction and the z direction of the connection point C respectively;
mx is the moment about the x-axis and My is the moment about the y-axis.
As shown in fig. 2, the landing gear load is force in three directions Fx0, fy0, and Fz0, wherein the vertical load Fz0 is transmitted by force of Fzb and Fzc of the connection point B and the connection point C. The side load Fy0 is transmitted by the Fyb force of the connection point B. The heading load is transferred by the forces of Fxa, fxb, fxc at connection point a, connection point B, connection point C. The moment My generated by the heading load Fx0 is diffused by a couple formed by Fxa of the connection point A, fxb and Fxc of the connection point B and the connection point C. The moment Mx generated by the side load Fy0 is spread by the couple formed by Fzb, fzc of the connection point B, C.
Step 104: and determining the load transmission values of the connection point A, the connection point B and the connection point C according to the load transmission type.
Specifically, the load transfer values of connection point a, connection point B, and connection point C are determined according to the force and moment balance principle, and the load transfer values include Fxa, fxb, fyb, fzb, fxc, fzc.
Vertical load: fz0= Fzb + Fzc;
side load: fy0=fyb;
heading load: fx0=fxa+fxb+ Fxc;
my moment balance: fx0 (l1+l2) =fxb×l1, fxb= Fxc;
mx moment balance: fy0 (L1+L2) = Fzb ×L3×0.5-Fzc ×L3×0.5
Wherein Fx0, fy0, fz0, L1, L2, L3 are predetermined values, L1 is the distance from the connection point a to the BC axis, L2 is the distance from the BC axis to the point O, and L3 is the distance between the connection point B and the connection point C.
As shown in fig. 3, a formula symbol is labeled. When the load is calculated, typical landing working conditions such as three-point horizontal landing, three-point horizontal resistive landing, side-shifting landing and the like are considered.
Step 105: the specific installation form of the nose landing gear connection point A, the connection point B and the connection point C is determined according to the load transmission type of the connection point A, the connection point B and the connection point C.
The landing gear loads are forces in three directions of Fx0, fy0 and Fz0, and the connection point A transmits force Fxa in the x direction; the connection point B transmits forces Fxb, fyb, fzb in the x direction, the y direction and the z direction respectively; the connection point C transmits forces Fxc, fzc in the x-direction and z-direction, respectively.
As shown in fig. 4, for load transmission, the left and right longitudinal beam bolts are installed in the attachment holes. The bushing and the knuckle bearing are respectively arranged at the left longitudinal beam bolt hole, the bushing and the knuckle bearing are respectively arranged at the right longitudinal beam web bolt hole, and the gasket and the bushing nut are arranged at the other side of the right longitudinal beam web.
As shown in fig. 5, the landing gear latch is schematically installed and secured for load transfer. The first step, a left bolt is inserted into the landing gear through a left longitudinal beam web plate opening; secondly, inserting a right bolt into the landing gear through a left longitudinal beam web plate opening, then putting a gasket into the landing gear, screwing a nut, and breaking the safety; and thirdly, installing left and right bolt fixing bolts. Through these three steps, the assembly clearance of left landing gear joint and left longeron is greater than the assembly clearance of right landing gear joint and right longeron, and the landing gear is when the side is loaded, and left landing gear joint and left longeron do not take place to contact, does not produce side load at tie point C promptly, and only tie point B produces side load Fyb, draws or presses right longeron junction portion, gets into diffusion Y to the load.
Step 106: the specific mounting dimensions of nose landing gear connection point a, connection point B and connection point C are determined from the load transfer values of connection point a, connection point B and connection point C.
Specifically, determining the sizes of the single lug and the double lug at the connection point A and the brand of the connecting bolt according to Fxa;
determining the size of a bolt at the connecting point B according to Fxb, fyb, fzb and the brands of a joint bearing, a bushing, a gasket and a nut;
and determining the size of the bolt at the connection point C according to Fxc and Fzc, and the joint bearing and the lining mark.
Rear support structure load transfer. Because the joint bearings are arranged at the connection point A and the connection point D, the load Fxa at the connection point A is transmitted to the connection point D through the fixed support column or the hydraulic actuator cylinder, small Y-direction and Z-direction load components can be generated at the connection point D, the lateral angle boxes need to be used for diffusing to two side structures, the main heading load Fxd is approximately equal to Fxa, and the loads are diffused to the structures along the longitudinal angle boxes.
The key point of the invention is as follows: the front landing gear of the large helicopter with three connection points is designed through a corresponding structure, so that the top connection point only transmits heading load Fx and does not transmit loads (Fx and Fy) in an XOY plane; the two connection points with the left and right stringers transfer the heading Fx, vertical Fz load, while only the single side stringer connection point transfers the side load Fy. Through such load transmission design, avoid nose landing gear top tie point to increase huge in-plane machine and add the connection plate, the longeron that does not transmit the side load does not need to increase side load diffusion structure simultaneously. Through the measures, the weight of the front landing gear supporting structure is obviously reduced, and the structural efficiency is improved. In order to achieve the above load transfer objective, it is necessary to design a top connection point longitudinal diffusion structure, and the left and right longitudinal beam connection points are realized by different bolt mounting forms and assemblies.
Example two
S1: for the typical nose landing gear configuration of fig. 1, connection point a transmits a heading load Fx, connection point B transmits loads in three directions of heading Fx, lateral Fy, and vertical Fz, and connection point C transmits loads in heading Fx and vertical Fz;
s2: the loading of S1 is realized through the structure form and the assembly. The landing gear top connection point A adopts a fixed strut (which is used by an undeployed nose landing gear) or a hydraulic actuator cylinder (which is used by a retractable landing gear) arranged along the reverse course; the joint bearings are arranged at the openings of the web plates of the left side beam and the right side beam, the end parts of the right side bolts are connected by nuts, the end parts of the left side bolts are not provided with nuts, and the installation clearance of the joint of the right side undercarriage is smaller than that of the left side, so that the joint of the right side can transmit Fx, fy and Fz, and the right side can only transmit Fx and Fz. In order to prevent the bolts from falling out, the left bolt, the right bolt and the landing gear are fixed by bolts;
and S3, calculating the specific load distribution of each connecting point according to the load design in the step S2 and under the typical landing working conditions of three large helicopters. The load of each working condition is shown in table 1;
table 1 landing load values under three conditions
| Name of working condition | Fx(N) | Fy(N) | Fz(N) |
| Working condition 1 | 0 | 71000 | 88000 |
| Working condition 2 | 65000 | 0 | 230000 |
| Working condition 3 | 0 | 0 | 490000 |
From the length scale of fig. 3, l1=385 mm, l2=1115 mm, l3=920 mm, the specific loads at the three connection points are determined according to the force and moment balance equation.
Under working conditions 1-3, the loads of the three connection points are shown in tables 2-4 respectively.
TABLE 2 working condition 1 tie point load
| Name of working condition | Fx(N) | Fy(N) | Fz(N) |
| Top connection point A | 0 | / | / |
| Right connection point B | 0 | -71000 | -130049 |
| Left connection point C | 0 | / | 42049 |
TABLE 3 working condition 2 tie point load
| Name of working condition | Fx(N) | Fy(N) | Fz(N) |
| Top connection point A | 188246 | / | / |
| Right connection point B | -126623 | 0 | -114999 |
| Left connection point C | -126623 | / | -114999 |
TABLE 4 working condition 3 tie point load
| Name of working condition | Fx(N) | Fy(N) | Fz(N) |
| Top connection point A | 0 | / | / |
| Right connection point B | 0 | 0 | -24500 |
| Left connection point C | 0 | 0 | -24500 |
S4: determining the sizes of bolts and the sizes of bolts at the three connecting points according to the three connecting values calculated in the step 3;
s5: determining the form and the size of a load transmission structure according to the load value of the right-side connection part;
s6: and determining the form and the size of the heading load transmission structure according to the load value at the top connection point, and finally completing the connection design of the nose landing gear.
In summary, in the design of the helicopter nose landing gear connection and support structure, the load transmission path is reasonably designed by using the method, the weight of the landing gear support structure is reduced, and the structural efficiency is improved. Meanwhile, the whole process also considers the realization of disassembly and assembly, and is convenient for daily use and maintenance.
Claims (6)
1. A method of connecting and load transferring a nose landing gear of a large helicopter, the method comprising:
determining a nose landing gear connection point A, a connection point B and a connection point C;
connecting the connection point A, the connection point B and the connection point C with the machine body supporting structure;
determining load transfer types of the connection point A, the connection point B and the connection point C, wherein the load transfer types comprise force and moment of each connection point;
according to the load transfer type, determining load transfer values of the connection point A, the connection point B and the connection point C;
according to the load transmission types of the connection point A, the connection point B and the connection point C, determining the specific installation forms of the connection point A, the connection point B and the connection point C of the nose landing gear;
according to the load transmission values of the connection point A, the connection point B and the connection point C, determining the specific installation sizes of the connection point A, the connection point B and the connection point C of the nose landing gear;
the connection point A is connected with a fixed strut of the non-retractable nose landing gear, or the connection point A is connected with a hydraulic actuating cylinder of the retractable landing gear;
the connecting point B is connected with a web plate of a right longitudinal beam of the front fuselage;
the connection point C is connected with a left longitudinal beam web plate of the front fuselage;
the connection point A is connected with a fixed support of the non-retractable nose landing gear by adopting a lug, or is connected with a hydraulic actuating cylinder of the retractable landing gear;
the connecting point B is connected with a web plate of a right longitudinal beam of the front fuselage by adopting a detachable bolt;
the connecting point C is connected with the web plate of the left longitudinal beam of the front fuselage by adopting a detachable bolt.
2. The method of claim 1, wherein the landing gear load is a force in three directions Fx0, fy0, fz0, wherein:
the vertical load Fz0 is transmitted by the forces of Fzb and Fzc of the connection point B and the connection point C;
the side load Fy0 is transmitted by Fyb force of the connection point B;
the heading load is transferred by the forces of Fxa, fxb, fxc of connection point a, connection point B and connection point C,
fxa is the force of the connection point A in the x direction; fxb, fyb, fzb the forces in the x, y and z directions at the connection point B; fxc and Fzc are forces in the x-direction and z-direction, respectively, at the connection point C.
3. The method according to claim 2, wherein determining load transfer values for connection point a, connection point B and connection point C based on load transfer type, comprises:
the load transfer values for connection point a, connection point B and connection point C are determined according to the force and moment balance principles, and include Fxa, fxb, fyb, fzb, fxc, fzc.
4. A method according to claim 3, characterized in that the determination of the load transmission values of the connection points a, B and C according to the force and moment balancing principle comprises in particular:
the load transfer values Fxa, fxb, fyb, fzb, fxc, fzc for connection point a, connection point B, and connection point C are calculated according to the following formula:
vertical load: fz0= Fzb + Fzc;
side load: fy0=fyb;
heading load: fx0=fxa+fxb+ Fxc;
my moment balance: fx0 (l1+l2) =fxb×l1, fxb= Fxc;
mx moment balance: fy0 (L1+L2) = Fzb ×L3×0.5-Fzc ×L3×0.5
Wherein Fx0, fy0, fz0, L1, L2, L3 are predetermined values, L1 is the distance from the connection point a to the BC axis, L2 is the distance from the BC axis to the point O, and L3 is the distance between the connection point B and the connection point C.
5. The method according to claim 4, wherein determining the specific mounting dimensions of nose landing gear connection point a, connection point B and connection point C from the load transfer values of connection point a, connection point B and connection point C, comprises:
determining the sizes of the single lug and the double lug at the connection point A and the brand of the connecting bolt according to Fxa;
determining the size of a bolt at the connecting point B according to Fxb, fyb, fzb and the brands of a joint bearing, a bushing, a gasket and a nut;
and determining the size of the bolt at the connection point C according to Fxc and Fzc, and the joint bearing and the lining mark.
6. A method according to claim 2, wherein determining the specific mounting form of nose landing gear connection point a, connection point B and connection point C, based on the load transfer type of connection point a, connection point B and connection point C, comprises in particular:
the bushing and the knuckle bearing are respectively arranged at the left longitudinal beam bolt hole, the bushing and the knuckle bearing are respectively arranged at the right longitudinal beam web bolt hole, and the gasket and the bushing nut are arranged at the other side of the right longitudinal beam web.
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