JP2021003057A - combine - Google Patents

Abstract

To provide a combine capable of preventing damage of a fuel tank caused by contact with an obstacle.SOLUTION: A combine includes a machine body frame K, a fuel tank 75 placed on/supported by the machine body frame K, on the rear end of the machine body, and a protective member 80 arranged on the rear of the fuel tank 75, for protecting a back surface part of the fuel tank 75. The protective member 80 is erected on the rear end of the machine body frame K.SELECTED DRAWING: Figure 8

Description

The present invention relates to a combine in which a fuel tank is provided at the rear of the airframe.

Conventionally, there has been a configuration in which a tank support frame is extended so as to project rearward from the rear end of the airframe, and a fuel tank is placed and supported on the tank support frame (for example, Patent Document 1). reference).

Japanese Unexamined Patent Publication No. 2014-183815

In the above conventional configuration, the fuel tank is supported by a tank support frame provided so as to project rearward from the fuselage frame. Therefore, when the fuselage is retracted, the fuel tank is located at the rear end of the fuselage. There is a risk of problems such as contact with obstacles and damage to the fuel tank.

The present invention has been made in view of the above circumstances, and an object of the present invention is to provide a combine capable of preventing damage to the fuel tank due to contact with an obstacle.

The characteristic configuration of the combine according to the present invention is the airframe frame and
At the rear end of the fuselage, a fuel tank mounted and supported on the fuselage frame and
A protective member, which is arranged behind the fuel tank and protects the back surface of the fuel tank, is provided.
The protective member is erected at the rear end of the airframe.

According to the above-mentioned feature configuration, at the rear end of the airframe, the back surface of the fuel tank is provided by a protective member arranged behind the fuel tank mounted and supported on the airframe and erected at the rear end of the airframe. The part is protected.

Therefore, if there is an obstacle behind the aircraft, even if the aircraft is retracted, the protective member will withstand the impact even if it collides with the obstacle because the protective member is erected on the aircraft frame. Since the protective member prevents the contact of the obstacle with the back surface of the fuel tank, damage to the fuel tank due to the contact with the obstacle can be prevented.

A further characteristic configuration of the combine according to the present invention is that the width of the protective member is larger than the width of the back surface of the fuel tank.
The protective member is at a point that covers the lower part of the fuel tank.

Generally, the lower part of the fuel tank is likely to come into contact with obstacles. According to the above characteristic configuration, the lower portion of the fuel tank, which is likely to come into contact with an obstacle, is covered with a protective member having a width wider than that of the back surface of the fuel tank. Therefore, the back surface of the fuel tank can be effectively protected.

A further characteristic configuration of the combine according to the present invention is that the protective member has plate-shaped members having protrusions protruding toward the front of the aircraft on both the left and right sides, and the fuel tank between the protrusions. Arranged so that the back part of the
A gap filling member is arranged between at least one of the left and right protruding portions and the fuel tank.

According to the above feature configuration, the protective member is arranged so that the back portion of the fuel tank is located between the protrusions, the fuel tank can be extended to the rear position of the fuselage as much as possible to increase the capacity, and the fuel can be increased. Not only the back of the tank but also the corners can be protected.

Further, since the gap filling member is arranged between at least one of the left and right protrusions and the fuel tank, a waste straw or a waste straw can be discharged between the protection member and the fuel tank through the protrusion and the fuel tank. It is possible to prevent mud and the like from entering.

A further characteristic configuration of the combine according to the present invention is that the protective member is
A vertical frame erected at the rear end of the fuselage frame and
It is supported by the vertical frame and is provided with a protective portion wider than the vertical frame.

According to the above-mentioned feature configuration, since the protective member has a strong structure including a vertical frame and a protective portion supported by the vertical frame, the fuel even if an obstacle violently collides with the fuel. The contact of obstacles with the back surface of the tank can be suppressed, and damage to the fuel tank due to contact with obstacles can be prevented.

A further characteristic configuration of the combine according to the present invention is that the vertical frame is a plate-shaped member having protrusions protruding toward the rear of the machine body on both the left and right sides.
The protective portion is a plate-shaped member having protrusions protruding toward the front of the machine body on both the left and right sides.
The point is that the protective portion is supported on the front surface of the vertical frame.

According to the above-mentioned feature configuration, the protruding portion of the vertical frame and the protruding portion of the protective portion are oriented in opposite directions, and the structure of the protective member becomes stronger. Therefore, even if an obstacle violently collides with the fuel tank, the contact of the obstacle with the back surface of the fuel tank can be further suppressed, and damage to the fuel tank due to the contact with the obstacle can be prevented.

It is a left side view of the combine. It is a top view of the combine. It is a left side view which shows the grain storage part and a fuel tank. It is a top view of the airframe frame. It is a rear view of a combine. It is a left side view which shows the fuel tank supported by the fuselage frame. It is a top view which shows the rear side of the fuel tank supported by the fuselage frame. It is a rear view which shows the fuel tank supported by the fuselage frame. It is a vertical sectional left side view which shows the connection structure of a cutting part and a feeder. It is a partial cross-sectional plan view which shows the connection structure of a cutting part and a feeder. It is a side view which shows the connection structure of a cutting part and a feeder. It is a partial longitudinal rear view which shows the connection structure of a cutting part and a feeder. It is an exploded perspective view of a claw part. It is a top view which shows the driving part.

Hereinafter, a case where the embodiment according to the present invention is applied to a conventional combine as an example of a combine will be described with reference to the drawings.

〔overall structure〕
As shown in FIGS. 1, 2, and 3, the ordinary combine harvester is provided with a driving unit 3 on the front right side of a traveling machine 2 equipped with a pair of left and right crawler traveling devices 1, and threshs the cut crops. The device 4 and a grain storage unit 5 for storing the grains obtained by the threshing treatment are provided. The grain storage unit 5 is provided in a state of being located behind the operation unit 3, the grain storage unit 5 is located on the right side of the machine body, and the threshing device 4 is located on the left side of the machine body. The threshing device 4 is placed and supported on the machine frame K side by side along the width direction of the machine. Further, an engine (not shown) is provided below the driving unit 3, and the power of the engine is transmitted to each part of the combine via a transmission mechanism (not shown) in a mission case 27 provided on the side of the engine. ..

In this embodiment, when defining the front-rear direction of the aircraft, it is defined along the traveling direction of the aircraft in the working state, and when defining the left-right direction of the aircraft, the left and right are defined as viewed in the traveling direction of the aircraft. .. That is, the direction indicated by the reference numeral (F) in FIGS. 1, 2, 3 and 4 is the front side of the fuselage, and the direction indicated by the reference numeral (B) in FIGS. 1, 2, 3 and 4 is the rear side of the fuselage. .. The direction indicated by the reference numeral (L) in FIGS. 2 and 4 is the left side of the aircraft, and the direction indicated by the reference numeral (R) in FIGS. 2 and 4 is the right side of the aircraft. Further, the direction indicated by reference numeral (U) in FIGS. 1 and 3 is the upper side in the vertical direction, and the direction indicated by reference numeral (D) in FIGS. 1 and 3 is the lower side in the vertical direction.

A feeder 41, which is a transport device for transporting cut grain culms, is connected to the front part of the threshing device 4 so as to swing up and down around the horizontal axis, and the front end of the feeder 41 has a cutting width equivalent to the width of the machine body. The parts 8 are connected. The cutting unit 8 has a rotary reel 9 that scrapes the planted culm backwards, a clipper-type reaping device 10 that cuts and cuts the root of the planted culm, and laterally cuts the culm to the middle side in the width direction of the machine body. A horizontal feed auger 11 and the like for feeding and transferring are provided, and these are appropriately attached and fixed to a cutting section frame 12 formed by connecting a square pipe and an L-shaped member. The feeder 41 includes a transport case 42 formed in a square tube shape, and a frying conveyor 43 arranged inside the transport case 42 to transport the cut grain culms. The grain culm cut by the cutting device 10 is laterally fed by the lateral feed auger 11 and supplied to the feeder 41 through the opening 12a formed in the cutting section frame 12. The feeder 41 is provided with a dust suction fan 90 for sucking dust in the feeder 41 and around the cutting portion 8. The dust suction fan 90 is driven by an electric motor (not shown), and is configured so that the breaker switch 17 is turned off and stopped when the exhaust straw or the like is clogged. The operation of the dust suction fan 90 is restarted by the operator turning on the breaker switch 17 after removing the exhaust straw and the like from the dust suction fan 90.

The driver unit 3 includes a driver's seat 13, a front panel 14 located in front of the driver's seat 13 and having a plurality of operating tools, and a side panel located on the left side of the driver's seat 13 and having various operating tools. 18 mag is provided. On the right lateral side of the driver's seat 13, a dustproof duct 24 for sucking cooling air to the engine by the action of a radiator fan (not shown) is provided. The driving unit 3 is provided with a driving unit canopy 25 having functions such as preventing sunlight from the driver seated in the driving unit 3 and avoiding rainwater.

The left and right sides of the threshing device 4 are covered by the side walls 4A, and the upper portion is covered by the top plate 4B. Although not shown, the harvested grains that have a culm and a net (not shown) on the upper side of the internal space surrounded by the left and right side walls 4A and the top plate 4B and are transported from the feeder 41. A handling room is formed to handle the culm. Further, at the lower part of the handling chamber, a sorting processing unit is provided for sorting the treated products leaking from the receiving net into secondary products such as grains and paddy with branches, and waste straw waste.

The grains sorted by the sorting processing section are discharged to the lateral outside on the grain storage section 5 side of the threshing device 4 by a first-class recovery screw (not shown). A grain raising device 26 composed of a screw conveyor is provided on the lateral outer side of the side wall 4A on the grain storage portion 5 side of the threshing device 4. The grains discharged to the outside on the lateral side of the grain storage section 5 of the threshing device 4 are conveyed upward by the grain frying device 26 and stored in the grain storage section 5. The second product obtained in the sorting processing unit is reduced to the front side portion of the threshing device 4, and the waste straw waste and the like are discharged to the outside through the discharge case 4C provided at the rear part of the machine body of the threshing device 4.

[Crawler traveling device]
As shown in FIG. 1, the crawler traveling device 1 is provided with a drive wheel 28 located on the front side of the machine body, a tension wheel 29 located on the rear side of the machine body, and a plurality of intermediate parts thereof provided at intervals in the front-rear direction. It is provided with a grounding wheel 30, a crawler belt 31 wound around each of these wheels, an upper wheel 32 acting on the upper side of the crawler belt 31, a track frame (not shown) that supports the entire traveling device, and the like. It is composed of.

The drive wheels 28 are attached to an output shaft (not shown) of the transmission case 27, and power from the engine is supplied via a transmission mechanism in the transmission case 27 to rotate the crawler belt 31.

[Grain storage section]
The grain storage unit 5 will be described.
As shown in FIGS. 3 and 5, the grain storage section 5 has a storage space for storing threshed grains, and a storage hopper 35 capable of discharging grains below the storage space, and storage. A collection unit 36 for collecting grains discharged from the hopper 35 and a hopper support frame 37 for supporting the storage hopper 35 are provided.

[Airframe support structure]
Next, the airframe support structure will be described.
The traveling machine body 2 is provided with a front frame K1 on which a threshing device 4, a grain storage section 5, and the like are mounted and supported. As shown in FIG. 4, the front frame K1 is formed in a substantially rectangular grid in a plan view, and is configured by connecting a plurality of front-rear frame bodies 58 and a plurality of lateral frame bodies 59 in a grid pattern. ing. The plurality of front-rear frame bodies 58 and the plurality of lateral frame bodies 59 are each composed of square tubular members, and they are integrally connected to form a support structure.

The front frame K1 is provided with a driving unit support portion 60 for supporting the driving unit 3 at a location on the right front side, and an engine support for mounting and supporting the engine on the rear side of the driving unit support unit 60 via a mount rubber (not shown). A unit 61 is provided. A storage portion support 62 that supports the front side of the hopper support frame 37 is provided on the rear side of the engine support portion 61.

As shown in FIGS. 4 and 5, two front-rear support frames 63 and 64 for supporting the track frames (not shown) on both the left and right sides are provided below the front frame K1. Of the two support frames 63, 64, the left support frame 63 located on the left side extends to a position where the front side corresponds to the front end portion of the track frame, and the rear side is laterally located on the rear side of the front frame K1. It extends to a position corresponding to the frame body 59.

The right side support frame 64 located on the right side of the two support frames 63 and 64 extends laterally so that the front side extends to a position corresponding to the front end portion of the track frame and the rear side is located at the rear end portion of the front frame K1. It is larger than the frame body 59 and extends rearward.

Further, the rear frame K2 is continuously provided so as to project rearward from the lateral frame body 59 located at the rear end of the front frame K1. That is, in the combine in the present embodiment, the airframe frame K is composed of the front frame K1 and the rear frame K2. The rear frame K2 is rearward of the left front-rear frame body 66 extending rearward from the rear end portion of the front frame K1 and the lateral frame body 59 located at the rear end portion of the front frame K1. It includes a front-rear frame body 58 at the right end and a side-direction frame body 67 provided over the left front-rear frame body 66. Further, two lateral frame bodies 67 are provided in a state of being arranged side by side in the front-rear direction, each lateral frame body 67 is formed in a solid state, and the front lateral frame body 67 is provided on the rear side of the hopper support frame 37. I support it.

A weight attachment portion 71 to which the balance weight 70 can be attached is provided on the lateral frame body 67 located on the rear side of the two lateral frame bodies 67. As shown in FIGS. 4 and 5, one balance weight 70 is attached to the lateral frame body 67.

[Fuel tank support structure]
As shown in FIGS. 4 and 5, it is an intermediate position in the left-right direction of the machine between the storage hopper 35 and the threshing device 4, and is located at the rear side of the machine, behind the rear end of the storage hopper 35. The fuel tank 75 is provided in a protruding state. The fuel tank 75 has a rectangular shape that is wide in the front-rear direction and narrow in the left-right direction in the plan view, and is narrow in the left-right direction and wide in the up-down direction in the front-rear direction of the aircraft. It is configured. As described above, the shape is compact in the left-right direction, and while it can be deployed using a narrow area between the threshing device 4 and the grain storage unit 5, a large fuel storage capacity can be secured.

Further, the fuel tank 75 is supported by a rear end portion of the front frame K1 and a rear end frame K2 (hereinafter, referred to as "rear end portion of the airframe frame K"). As shown in FIG. 5, the fuel tank 75 is located between the right side wall 4A of the threshing device 4 and the left column 54 of the hopper support frame 37, and is located at the rear end portion of the front frame K1 and the rear frame. It is placed and supported over the left side of K2 except the part where the balance weight 70 is attached.

Further, as shown in FIGS. 6, 7 and 8, the fuel tank 75 is fixed to the rear end portion of the airframe frame K by three mounting bands 76. Specifically, the right end of each mounting band 76 is fixed to each stay 77a provided at the rear end of the body frame K with bolts, and the left end of each mounting band 76 is attached to the left end of the body. , The screw rod 78 is attached. Then, the screw rod 78 is inserted into the hole of the stay 77b provided at the rear end of the machine frame K, and each mounting band 76 is attached in a state where the position can be adjusted with respect to the stay 77b by two nuts. Further, the two mounting bands 76 on the front side of the machine body among the three mounting bands 76 are prevented from slipping on the fuel tank 75 by the non-slip members 79 fixed to both side surfaces of the fuel tank 75.

[Fuel tank protection structure]
As shown in FIGS. 6, 7 and 8, a protective member 80 for protecting the back surface of the fuel tank 75 is provided behind the fuel tank 75. The protective member 80 was supported by a vertical frame 81 erected at the rear end of the rear frame K2 constituting the airframe frame K in a vertically extending posture and a vertical frame 81 in a vertically extending posture. It is composed of a protection unit 82.

The vertical frame 81 is a plate-shaped member having protruding portions 81a protruding toward the rear of the machine body on both the left and right sides, and is bolted to a stay 85 provided on the lateral frame body 67 on the rear side of the rear frame K2. ing. On the other hand, the protective portion 82 has protruding portions 82a protruding toward the front of the machine body on both the left and right sides, and is a plate-shaped member having a width wider than the width of the vertical frame 81 and the back surface of the fuel tank 75, and the protruding portions. The back portion of the fuel tank 75 is located between the 82a and is supported on the front surface of the vertical frame 81 so as to cover the lower portion of the fuel tank 75. Further, an elastic body 83 such as a sponge is disposed between the protruding portion 82a of the protective portion 82 and the side surface of the fuel tank 75 as a gap filling member for filling the gap between the two. In the present embodiment, the protective member 80 covers the back surface of the fuel tank 75 from slightly above the center of the fuel tank 75 in the vertical direction to slightly above the lower end of the fuel tank 75.

In the combine of the present embodiment, the protective member 80 having the protective portion 82 wider than the back surface of the fuel tank 75 is provided behind the fuel tank 75, and the protective member 80 provides the back surface portion of the fuel tank 75. Is in a protected state. Therefore, when there is an obstacle behind the airframe, even if the airframe is retracted, the protective member 80 can prevent the obstacle from coming into contact with the back surface of the fuel tank 75, and the fuel tank 75 is damaged. Can be prevented.
In particular, in the present embodiment, since the protective portion 82 is arranged so as to cover the lower portion of the fuel tank 75, the lower portion of the fuel tank 75, which has a relatively high risk of coming into contact with an obstacle, is covered with the protective member 80. Therefore, the back surface of the fuel tank 75 can be effectively protected.

Further, in the combine according to the present embodiment, the protruding portion 82a of the protective portion 82 protrudes forward of the airframe, and the back portion of the fuel tank 75 is located between the protruding portions 82a, so that the fuel tank 75 is provided. The capacity can be increased by extending it to the rear position of the fuselage as much as possible, and not only the back surface of the fuel tank 75 but also the corners can be protected. Further, since the elastic body 83 is arranged between the protruding portion 82a of the protective portion 82 and the side surface of the fuel tank 75, the protective portion 82 and the protective portion 82 pass between the protruding portion 82a and the side surface of the fuel tank 75. It is possible to suppress the entry of waste straw and mud into the fuel tank 75.

Further, in the combine according to the present embodiment, the structure of the protective member 80 is such that the protective portion 82 is supported on the front surface of the vertical frame 81 so that the protruding portions 81a and 82a face each other in opposite directions. As a result, the structure of the protective member 80 is strengthened. Therefore, even if an obstacle violently collides with the fuel tank 75, the contact of the obstacle with the back surface of the fuel tank 75 can be suppressed, and the fuel tank 75 can be prevented from being damaged.

[Connecting structure between the cutting section and the feeder]
Next, the connection structure between the cutting unit 8 and the feeder 41 will be described.
As shown in FIGS. 9 to 12, in the feeder 41, an opening 42a through which the grain culm supplied from the lateral feed auger 11 of the cutting portion 8 passes is formed on the front end surface of the transport case 42, and above the opening 42a. Two claw bodies 44 are fixed to the edges at predetermined intervals in the left-right direction. Further, a horizontal frame 45 having a U-shaped cross section extending in the left-right direction is provided on the lower surface of the front portion of the transport case 42, and a U-shaped cross section extending in the vertical direction is provided on the left and right side surfaces of the front portion of the transport case 42. A character-shaped vertical frame 46 is provided, and an L-shaped frame 47 having an L-shaped cross section is provided on the side surface of each of the vertical frames 46. Further, reinforcing ribs 46a are provided inside each vertical frame 46, and reinforcing ribs are provided inside each L-shaped frame 47 so as to be located above the reinforcing ribs 46a provided in the vertical frame 46. 47a is provided.

As shown in FIG. 13, the two claw bodies 44 provided on the feeder 41 are composed of a back plate 44a forming the back surface and two side plates 44b forming the side surfaces, and the back plate 44a and the two side plates 44b are sheet metal processed. It is formed by molding and welding these from the inside. These two claw bodies 44 are fixed in a state where the lower back surface of the back plate 44a is welded to the upper edge of the opening 42a of the feeder 41. There is a problem that the cost is high when the claw body 44 is manufactured by machined blocks, and sufficient shape accuracy cannot be obtained when the claw body 44 is manufactured by press working, but assembling the parts molded by sheet metal processing. By doing so, sufficient shape accuracy can be obtained while suppressing the cost.

The cutting section frame 12 of the cutting section 8 includes a square tubular upper horizontal frame 12b extending in the left-right direction above the opening 12a and a U-shaped lower horizontal frame extending in the left-right direction below the opening 12a. A vertical frame 12d having a U-shaped cross section extending in the vertical direction is provided on both the left and right sides of the opening 12a.

In the combine according to the present embodiment, the claw body 44 is inserted into the opening 12a of the cutting portion frame 12, the back surface of the claw body 44 faces the front surface of the upper horizontal frame 12b of the cutting portion 8, and then the feeder 41 The cutting portion 8 and the feeder 41 can be connected by fixing the front surface of the horizontal frame 45 and the back surface of the lower horizontal frame 12c of the cutting portion 8 with a bolt 48 and a nut 49 welded to the lower horizontal frame 12c. .. In a state where the cutting portion 8 and the feeder 41 are connected, the front surfaces of the left and right L-shaped frames 47 in the feeder 41 come into contact with the back surfaces of the left and right vertical frames 12d in the cutting portion 8.

When the feeder 41 is not provided with the left and right L-shaped frames 47, when a load is applied to the cutting portion 8 toward the rear of the machine body, bending stress with the portion fixed by the bolt 48 and the nut 49 as a fulcrum is applied. It acts on the bolt 48, and an excessive load may be applied to the bolt 48 and the like.

In the combine according to the present embodiment, even if bending stress is generated, a reaction force in a direction against the bending stress acts on the vertical frame 12d from the L-shaped frame 47, so that the load applied to the bolt 48 or the like can be relaxed. ..

[Arrangement of operating tools on the front panel and side panel]
As shown in FIG. 14, the front panel 14 of the driving unit 3 has a display unit 15 in the center, a steering operation lever 16 on the right side, and a breaker switch 17 on the left side. The main shift lever 19 is arranged on the right front side, the auxiliary shift lever 20 is arranged on the left front side, the cutting clutch lever 21 is on the right side behind these shift levers 19 and 20, the grain removal clutch lever 22 is in the center, and the forward / reverse lever 23 is on the left side. Have been placed. By arranging the breaker switch 17 on the front panel 14 so as to be located substantially immediately before the main shift lever 19 in this way, the main shift lever 19 can be operated smoothly without interfering with the breaker switch 17. It has become.

[Another Embodiment]
(1) In the above embodiment, the protective member 80 is composed of two members, a vertical frame 81 and a protective portion 82, but the present invention is not limited to this configuration, and the protective member 80 is erected at the rear end of the machine frame K. As long as the back surface of the fuel tank 75 can be protected, the fuel tank 75 may be composed of three or more members, or may be composed of a single member.

(2) In the above embodiment, the shape of the protective portion 82 is a shape having protrusions 82a on both the left and right sides, but the shape is not limited to this, and a shape having no protrusions 82a is a shape having no protrusions 82a. It may be adopted as the shape of. Even if a single member or a plurality of members are used as the protective member, the member for protecting the back surface of the fuel tank has protrusions protruding toward the front of the aircraft on both the left and right sides. It may be a member having a member or a member having no protruding portion.

(3) In the above embodiment, the protective member 80 adopts a configuration in which the protective portion 82 is supported on the front surface of the vertical frame 81, but the present invention is not limited to this configuration, and the protective portion is supported on the back surface of the vertical frame 81. The configuration may be adopted.

(4) In the above embodiment, the configuration of the protective member 80 is a configuration that covers the lower portion of the fuel tank 75, but the configuration is not limited to this configuration, and for example, a configuration that covers the upper portion of the fuel tank 75 may be used. However, it may be configured to cover the entire back surface of the fuel tank 75.

(5) In the above embodiment, the elastic body 83 is arranged between the protruding portion 82a of the protective member 80 and both side surfaces of the fuel tank 75, but the configuration is not limited to this configuration and is not limited to this configuration. An elastic body 83 may be arranged between at least one of the left and right protruding portions 82a of the member 80 and the side surface of the fuel tank 75 facing the protruding portion 82a, or the protruding portion 82a and the fuel tank may be arranged. The structure may be such that the elastic body 83 is not arranged between the side surface of the 75.
Further, the gap filling member does not necessarily have to be an elastic body 83, and is not particularly limited as long as it can prevent exhaust straw and mud from entering between the protective member 80 and the fuel tank 75. ..

(6) In the above embodiment, the case where the combine is a normal type combine is illustrated, but the combine may be a head-feeding combine.

The configurations disclosed in the above embodiments (including other embodiments) can be applied in combination with the configurations disclosed in other embodiments as long as there is no contradiction, and are disclosed in the present specification. The embodiment described is an example, and the embodiment of the present invention is not limited to this, and can be appropriately modified without departing from the object of the present invention.

The present invention can be applied to a combine having a fuel tank at the rear of the airframe.

75 Fuel tank 80 Protective member 81 Vertical frame 81a Protruding part 82 Protecting part 82a Protruding part K Airframe frame

Claims (5)

Airframe frame and
At the rear end of the fuselage, a fuel tank mounted and supported on the fuselage frame and
A protective member, which is arranged behind the fuel tank and protects the back surface of the fuel tank, is provided.
The protective member is a combine that is erected at the rear end of the airframe. The width of the protective member is larger than the width of the back surface of the fuel tank.
The combine according to claim 1, wherein the protective member covers the lower part of the fuel tank. The protective member has plate-shaped members having protrusions protruding toward the front of the aircraft on both the left and right sides, and is arranged so that the back surface portion of the fuel tank is located between the protrusions.
The combine according to claim 1 or 2, wherein a gap filling member is arranged between at least one of the left and right protruding portions and the fuel tank. The protective member is
A vertical frame erected at the rear end of the fuselage frame and
The combine according to any one of claims 1 to 3, further comprising a protective portion supported by the vertical frame and wider than the vertical frame. The vertical frame is a plate-shaped member having protrusions protruding toward the rear of the machine body on both the left and right sides.
The protective portion is a plate-shaped member having protrusions protruding toward the front of the machine body on both the left and right sides.
The combine according to claim 4, wherein the protective portion is supported on the front surface of the vertical frame.

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