CN117163288A - Y5/Y5B series aircraft extinguishing bomb mounting platform - Google Patents
Y5/Y5B series aircraft extinguishing bomb mounting platform Download PDFInfo
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- CN117163288A CN117163288A CN202311297705.XA CN202311297705A CN117163288A CN 117163288 A CN117163288 A CN 117163288A CN 202311297705 A CN202311297705 A CN 202311297705A CN 117163288 A CN117163288 A CN 117163288A
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- 210000001015 abdomen Anatomy 0.000 claims abstract description 31
- 230000002787 reinforcement Effects 0.000 claims abstract description 28
- 230000005484 gravity Effects 0.000 claims abstract description 12
- 238000005452 bending Methods 0.000 claims abstract description 10
- 230000003014 reinforcing effect Effects 0.000 claims description 33
- 229910000831 Steel Inorganic materials 0.000 claims description 6
- 238000009434 installation Methods 0.000 claims description 6
- 239000010959 steel Substances 0.000 claims description 6
- 230000001629 suppression Effects 0.000 claims 8
- 238000013461 design Methods 0.000 description 4
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
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Abstract
The application provides a Y/YB series aircraft fire extinguishing platform, which comprises two front supports, two rear supports, a front corner box and a rear corner box, wherein the front supports are arranged on the front support; the front corner box and the rear corner box are arranged oppositely; the front corner box and the rear corner box are fixedly connected through a base and are used for balancing the gravity moment generated by the self weight of the fire extinguishing bomb to the front beam and the rear beam; the two bases are symmetrical about the symmetry axis of the aircraft fuselage; two fire extinguishing bombs are arranged at the lower part of the belly, and the other two fire extinguishing bombs are respectively arranged at the lower parts of the left wing and the right wing; the hanger is provided with a body abdomen reinforcement structure, and the body abdomen reinforcement structure comprises longitudinal reinforcement structures respectively arranged on the front beam and the rear beam, transverse reinforcement structures arranged between the longitudinal reinforcement structures and end transverse reinforcement parts respectively arranged between two ends of the longitudinal reinforcement structures; when the aircraft is in normal flight, the fire extinguishing bomb mounted on the belly generates lateral bending moment due to self gravity, inertia moment along the course and turning during flight.
Description
Technical Field
The application relates to the technical field of aircrafts, in particular to a Y5/Y5B series aircraft extinguishing bomb mounting platform.
Background
With the development of technology and the construction requirement of a national emergency rescue system, aviation power begins to be largely put into emergency rescue. At present, aviation force is mainly used for aspects such as aerial patrol monitoring, reconnaissance command and personnel transportation in fire rescue, and although some airplanes also participate in aviation hanging sprinkling and spraying fire extinguishing agents, the fire extinguishing efficiency is low. The fire extinguishing bomb with accurate guidance is applied to generate, and the guided fire extinguishing bomb is thrown into an airplane to early, small and good fire at the beginning, so that the big fire is extinguished in a sprouting state.
Because the fire extinguishing bomb is generally in the order of 100-200 kg, the helicopter is limited by the conditions of self structure and the like, the number of the mounting is limited to a certain extent, and the fixed wing aircraft can fully utilize the space of the fuselage and the wings to mount the fire extinguishing bomb;
the general aircraft generally does not consider the loading of a heavy external store in structural design, the structure is generally weaker than that of a military aircraft, and particularly the Y5/Y5B series aircraft wings are characterized in that the wings are more and denser, the skin adopts a cloth covering structure, and only the shape is maintained without bearing force; the strength of the fuselage and wings of fixed wing aircraft is difficult to directly bear the weight of the fire extinguishing bomb and needs to be solved.
Disclosure of Invention
Aiming at the problems, the application aims to provide a Y5/Y5B series aircraft fire extinguishing bomb mounting platform which can mount 4 fire extinguishing bombs of 200kg grade or 8 fire extinguishing bombs of 100kg grade and solve the problem of carrying and throwing the fire extinguishing bomb with accurate guidance.
In order to solve the problem, the specific structure and strength requirements of the airplane body and wings and the external dimensions of the fire extinguishing bomb are fully considered, and the position of the fire extinguishing bomb is reasonably determined with the aim of having minimal influence on the aerodynamics and strength of the airplane.
In the scheme design, the frame of the aircraft is reinforced by taking the shape of the fire extinguishing bomb and the elevation angle of the aircraft during take-off and landing into consideration. In order to balance the lateral bending moment generated by the gravity of the belly mount during normal flight and the moment of inertia along the course during flight and turning, the following force transmission design is carried out.
Taking 200kg fire extinguishing bomb as an example, through necessary pneumatic analysis and strength check, the method finally determines that 2 fire extinguishing bombs are mounted on the belly of the fuselage, and 1 fire extinguishing bomb is mounted on the lower parts of the left wing and the right wing respectively.
In order to achieve the purpose of the application, the application is realized by the following technical scheme:
the Y/YB series aircraft fire extinguishing platform is arranged on a hanger below the belly of an aircraft, the hanger is of a groined frame structure and comprises a front beam, a rear beam and a plurality of connecting ribs arranged between the front beam and the rear beam; the device is characterized by comprising two front supports arranged on a front beam at intervals, two rear supports arranged on a rear beam at intervals, front corner boxes respectively arranged on the front supports and rear corner boxes respectively arranged on the rear supports; the front corner box and the rear corner box are arranged oppositely; the front corner box and the rear corner box are fixedly connected through a base and are used for balancing the gravity moment generated by the self weight of the fire extinguishing bomb to the front beam and the rear beam; the two bases are symmetrical about the symmetry axis of the aircraft fuselage;
two fire extinguishing bombs are arranged at the lower part of the belly, and the other two fire extinguishing bombs are respectively arranged at the lower parts of the left wing and the right wing;
the hanging frame is provided with a frame belly reinforcing structure for balancing lateral bending moment generated by the fire extinguishing bomb mounted on the frame belly due to self gravity, inertia moment along the course and turning during flight when the aircraft is in normal flight.
Further, the belly reinforcing structure of the fuselage comprises longitudinal reinforcing structures respectively arranged on the front beam and the rear beam, transverse reinforcing structures arranged between the longitudinal reinforcing structures and end transverse reinforcing parts respectively arranged between two ends of the longitudinal reinforcing structures.
Further, the longitudinal reinforcing structure comprises reinforcing supports fixedly connected with the front beam and cross beams fixedly connected with the reinforcing supports, and the number of the reinforcing supports is two and is divided into two ends of the cross beams.
Further, the transverse reinforcement structure includes a mounting joint and a connecting beam; the mounting joint is fixedly connected with the middle part of the cross beam; the installation joints are two, and the connecting beam is installed between the two installation joints.
Further, the end part transverse reinforcing part comprises four supporting rods, every two supporting rods form a group, and one end of each supporting rod is fixedly connected with one end of a cross beam on the front beam; the other end of the supporting rod is fixedly connected with the other end of the cross beam; a group of support rods are respectively arranged at two ends of the cross beam.
Further, reinforcing beams are arranged at the two ends of the connecting beam.
Further, the connecting beam is of a channel steel structure, and reinforcing ribs are arranged in the channel steel.
Further, a rear joint is arranged in the middle of the connecting beam; a front joint is arranged at one end of the connecting beam; the front joint and the rear joint are both provided with fire extinguishing bombs.
Further, one end of the connecting beam on the rear beam is provided with a front connecting seat; one end of the connecting beam on the front beam is provided with a rear connecting seat; the surfaces of the front connecting seat and the rear connecting seat are fixed with skins.
Further, the mounting joint comprises an upper joint fixedly connected with the bottom plate of the machine body and a lower joint fixedly connected with the connecting beam.
The beneficial effects of the application are as follows:
the front and rear supports with large enough area are arranged on the frame (hanging frame) of the airplane, and are simultaneously connected with the upper and lower edge strips of the frame, so that the lateral bending moment is transmitted to the belly floor of the frame of the airplane; the base of the fixed hanging frame is connected with the front support and the rear support through the front corner box and the rear corner box so as to balance the gravity distance generated by the self weight of the fire extinguishing bomb to the frame of the machine body;
through the fuselage belly reinforcement structure that sets up, to fuselage belly reinforcement, avoid causing fuselage to warp because of the weight of fire extinguishing bomb, influence aircraft safety.
Drawings
FIG. 1 is a schematic diagram of the structure of the present application;
FIG. 2 is a schematic perspective view of the abdomen reinforcement structure of the fuselage of the present application;
FIG. 3 is a schematic view of another angular perspective of the belly reinforcement structure of the present application;
FIG. 4 is a schematic perspective view of a beam of the present application;
FIG. 5 is a schematic view of another angular perspective of the beam of the present application;
fig. 6 is a color exploded view of the belly reinforcing structure of the fuselage.
Wherein: 1-reinforcing support, 2-cross beam, 3-supporting rod, 5-skin, 6-front connecting seat, 7-connecting beam, 8-hanging frame, 11-rear joint, 21-installation joint and 51-front joint.
Detailed Description
The present application will be further described in detail with reference to the following examples, which are only for the purpose of illustrating the application and are not to be construed as limiting the scope of the application.
Example 1
The Y5/Y5B series aircraft fire extinguishing platform is arranged on a hanging frame 8 below the belly of an aircraft, the hanging frame 8 is of a groined frame structure, and the hanging frame 8 comprises a front beam, a rear beam and a plurality of connecting ribs arranged between the front beam and the rear beam; the device is characterized by comprising two front supports arranged on a front beam at intervals, two rear supports arranged on a rear beam at intervals, front corner boxes respectively arranged on the front supports and rear corner boxes respectively arranged on the rear supports; the front corner box and the rear corner box are arranged oppositely; the front corner box and the rear corner box are fixedly connected through a base and are used for balancing the gravity moment generated by the self weight of the fire extinguishing bomb to the front beam and the rear beam; the two bases are symmetrical about the symmetry axis of the aircraft fuselage;
two fire extinguishing bombs are arranged at the lower part of the belly, and the other two fire extinguishing bombs are respectively arranged at the lower parts of the left wing and the right wing;
the hanging frame 8 is provided with a frame belly reinforcing structure for balancing lateral bending moment generated by the fire extinguishing bomb mounted on the frame belly due to self gravity, inertia moment along the course and turning during flight when the aircraft is in normal flight.
The machine body abdomen reinforcement structure comprises longitudinal reinforcement structures arranged on the front beam and the rear beam respectively, transverse reinforcement structures arranged between the longitudinal reinforcement structures and end transverse reinforcement parts arranged between two ends of the longitudinal reinforcement structures respectively.
The longitudinal reinforcing structure comprises two reinforcing supports 1 fixedly connected with the front beam and two cross beams 2 fixedly connected with the reinforcing supports, wherein the two reinforcing supports 1 are respectively arranged at two ends of the cross beams 2.
The transverse reinforcement structure comprises a mounting joint 21 and a connecting beam 7; the mounting joint 21 is fixedly connected with the middle part of the cross beam 2; the number of the mounting joints 21 is two, and the connecting beam 7 is arranged between the two mounting joints 21.
The end part transverse reinforcing part comprises four supporting rods 3, each two supporting rods 3 are in a group, and one end of each supporting rod 3 is fixedly connected with one end of a cross beam 2 on the front beam; the other end of the supporting rod 3 is fixedly connected with the other end of the cross beam 2; a group of support rods 3 are respectively arranged at two ends of the cross beam 2.
And the connecting beam 7 is provided with a reinforcing beam.
The middle part of the connecting beam 7 is provided with a rear joint 11; a front joint 51 is arranged at one end of the connecting beam 7; the front joint 51 and the rear joint 11 are provided with fire extinguishing bombs.
One end of the connecting beam 7 on the rear beam is provided with a front connecting seat 6; one end of the connecting beam 7 on the front beam is provided with a rear connecting seat; the surfaces of the front connecting seat 6 and the rear connecting seat are fixed with a skin 5.
The mounting joint 21 comprises an upper joint fixedly connected with the bottom plate of the machine body and a lower joint fixedly connected with the connecting beam 7.
The fixed connection mode adopts a riveting or bolt-nut connection mode, and the welding mode is forbidden, so that stress concentration is avoided, and the organization of a machine body is damaged.
Example two
This example is a further modification of example 1,
the connecting beam 7 is of a channel steel structure, and reinforcing ribs are arranged in the channel steel. The strength of the connection beam 2 can be enhanced.
Example III
This embodiment is substantially identical to embodiment 1 except for describing the structure of the present application in more detail;
the frame of the aircraft is reinforced by taking the shape of the fire extinguishing bomb and the elevation angle of the aircraft during take-off and landing into consideration. In order to balance the lateral bending moment generated by the gravity of the belly mount during normal flight and the moment of inertia along the course during flight and turning, the following force transfer design is carried out: the frame of the frame hanger 8 is provided with a front support 1 and a rear support 1 with large enough areas, and the front support 1 and the rear support 1 are simultaneously connected with the upper edge strip and the lower edge strip of the frame to transfer the lateral bending moment to the belly floor of the frame; the base of the fixed hanging frame 8 is connected with the front and rear supports 1 through the front and rear corner boxes to balance the gravity distance generated by the self-weight of the fire extinguishing bomb to the frame.
As shown in figure 6 of the drawings,
according to the size of the fire extinguishing bomb body and the distance between the hanging racks, the hanging rack installation positions are increased on the belly, and the two hanging bomb installation positions are symmetrical relative to the plane symmetry axis surface between the stringers. Each mounting location has two mounting points with the fuselage between frames 8-9 of the fuselage. The belly structure mount comprises a front support 1, a rear support, a front corner box, a rear corner box and a base, wherein the front support, the rear support, the front corner box, the rear corner box, the upper edge strip, the lower edge strip, the web plate of an underfloor 8 frame and an underfloor 9 frame are fixed through rivets, and the middle of the front support, the rear support and the front corner box is connected with the base.
In order to ensure the downward deflection angle of the wing flap of the airplane, fire extinguishing bomb hangers are arranged on the front and back of the front beam of the wing rib 5-6 of the lower wing. In order to balance the bending moment of the wing mounted to the wing interface position, besides the fixed joint reinforcing front support seat and the supporting beam which are arranged on the front and rear beams of the No. 5-6 wing ribs, front and rear supports are respectively arranged between the No. 4-5 wing ribs and between the front and rear beams of the No. 6-7 wing ribs of the lower wing; the supports on the front beam and the rear beam are respectively connected into a whole through the front beam and the rear beam. The front and rear beam upper supports of the ribs between the ribs 4 and 5 and the ribs 6 and 7 are supported by the supporting rods to balance the bending moment of the wing mounting dead weight on the front and rear beam upper supports.
The reinforcing structure consists of a front beam reinforcement, a rear beam reinforcement, a supporting rod, a connecting beam, a front mounting seat, a mounting seat and a mounting carrier.
The principle of this embodiment is basically the same as that of embodiment 2, and will not be described in detail.
The foregoing has shown and described the basic principles, principal features and advantages of the application. It will be understood by those skilled in the art that the present application is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present application, and various changes and modifications may be made without departing from the spirit and scope of the application, which is defined in the appended claims. The scope of the application is defined by the appended claims and equivalents thereof.
Claims (10)
1. The Y5/Y5B series aircraft fire extinguishing platform is arranged on a hanging frame (8) below the belly of an aircraft, the hanging frame (8) is of a groined frame structure, and the hanging frame (8) comprises a front beam, a rear beam and a plurality of connecting ribs arranged between the front beam and the rear beam; the device is characterized by comprising two front supports arranged on a front beam at intervals, two rear supports arranged on a rear beam at intervals, front corner boxes respectively arranged on the front supports and rear corner boxes respectively arranged on the rear supports; the front corner box and the rear corner box are arranged oppositely; the front corner box and the rear corner box are fixedly connected through a base and are used for balancing the gravity moment generated by the self weight of the fire extinguishing bomb to the front beam and the rear beam; the two bases are symmetrical about the symmetry axis of the aircraft fuselage;
two fire extinguishing bombs are arranged at the lower part of the belly, and the other two fire extinguishing bombs are respectively arranged at the lower parts of the left wing and the right wing;
the hanging frame (8) is provided with a frame belly reinforcing structure for balancing lateral bending moment generated by the fire extinguishing bomb mounted on the frame belly due to self gravity, inertia moment along the course and turning during flight when the aircraft is in normal flight.
2. The Y5/Y5B series aircraft fire suppression platform of claim 1, wherein: the machine body abdomen reinforcement structure comprises longitudinal reinforcement structures arranged on the front beam and the rear beam respectively, transverse reinforcement structures arranged between the longitudinal reinforcement structures and end transverse reinforcement parts arranged between two ends of the longitudinal reinforcement structures respectively.
3. The Y5/Y5B series aircraft fire suppression platform of claim 2, wherein: the longitudinal reinforcing structure comprises two reinforcing supports (1) fixedly connected with the front beam and two cross beams (2) fixedly connected with the reinforcing supports, wherein the two reinforcing supports (1) are respectively arranged at two ends of the cross beams (2).
4. A Y5/Y5B series aircraft fire suppression platform according to claim 3, wherein: the transverse reinforcement structure comprises a mounting joint (21) and a connecting beam (7); the mounting joint (21) is fixedly connected with the middle part of the cross beam (2); the number of the mounting joints (21) is two, and the connecting beam (7) is arranged between the two mounting joints (21).
5. The Y5/Y5B series aircraft fire suppression platform of claim 4, wherein: the end part transverse reinforcing part comprises four supporting rods (3), each two supporting rods (3) are in a group, and one end of each supporting rod (3) is fixedly connected with one end of a cross beam (2) on the front beam; the other end of the supporting rod (3) is fixedly connected with the other end of the cross beam (2); two ends of the cross beam (2) are respectively provided with a group of support rods (3).
6. The Y5/Y5B series aircraft fire suppression platform of claim 4, wherein: and reinforcing beams (71) are arranged at the two ends of the connecting beam (7).
7. The fire extinguishing platform for Y5/Y5B series aircraft according to claim 4, wherein the connecting beam (7) is of a channel steel structure, and reinforcing ribs are arranged in the channel steel.
8. The Y5/Y5B series aircraft fire suppression platform of claim 4, wherein: the middle part of the connecting beam (7) is provided with a rear joint (11); a front joint (51) is arranged at one end of the connecting beam (7); the front joint (51) and the rear joint (11) are both provided with fire extinguishing bombs.
9. The Y5/Y5B series aircraft fire suppression platform of claim 8, wherein: one end of the connecting beam (7) on the rear beam is provided with a front connecting seat (6); one end of the connecting beam (7) on the front beam is provided with a rear connecting seat (61); the surfaces of the front connecting seat (6) and the rear connecting seat (61) are fixedly provided with a skin (5).
10. The Y5/Y5B series aircraft fire suppression platform of claim 9, wherein: the installation joint (21) comprises an upper joint fixedly connected with the bottom plate of the machine body and a lower joint fixedly connected with the connecting beam (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311297705.XA CN117163288A (en) | 2023-10-09 | 2023-10-09 | Y5/Y5B series aircraft extinguishing bomb mounting platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311297705.XA CN117163288A (en) | 2023-10-09 | 2023-10-09 | Y5/Y5B series aircraft extinguishing bomb mounting platform |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117163288A true CN117163288A (en) | 2023-12-05 |
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ID=88943195
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311297705.XA Pending CN117163288A (en) | 2023-10-09 | 2023-10-09 | Y5/Y5B series aircraft extinguishing bomb mounting platform |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117163288A (en) |
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2023
- 2023-10-09 CN CN202311297705.XA patent/CN117163288A/en active Pending
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