CN212332955U - Folding auxiliary takeoff support of surveying and mapping fixed-wing aircraft - Google Patents
Folding auxiliary takeoff support of surveying and mapping fixed-wing aircraft Download PDFInfo
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- CN212332955U CN212332955U CN202020435998.9U CN202020435998U CN212332955U CN 212332955 U CN212332955 U CN 212332955U CN 202020435998 U CN202020435998 U CN 202020435998U CN 212332955 U CN212332955 U CN 212332955U
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- 238000013507 mapping Methods 0.000 title description 3
- 238000003466 welding Methods 0.000 claims abstract description 19
- 230000002457 bidirectional effect Effects 0.000 claims abstract description 15
- 230000006835 compression Effects 0.000 claims description 6
- 238000007906 compression Methods 0.000 claims description 6
- 230000002146 bilateral effect Effects 0.000 claims description 5
- 238000000034 method Methods 0.000 claims description 4
- 230000003139 buffering effect Effects 0.000 abstract description 5
- 230000035939 shock Effects 0.000 abstract description 5
- 230000008901 benefit Effects 0.000 abstract description 3
- 230000006872 improvement Effects 0.000 abstract description 3
- 230000000694 effects Effects 0.000 description 8
- 238000005457 optimization Methods 0.000 description 5
- 238000013461 design Methods 0.000 description 4
- 230000002596 correlated effect Effects 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000001174 ascending effect Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
The utility model provides a folding supplementary support of taking off of survey and drawing fixed wing aircraft, include: the bidirectional screw rod, the rod sleeve, the connecting rod and the fixing box; a rod sleeve is arranged on the outer side of the bidirectional screw rod, and the bidirectional screw rod is connected with the rod sleeve in a thread fit manner; the second hinge plate is arranged below the right side of the first hinge plate, and the second hinge plate is movably connected with the first hinge plate through a connecting rod; the connecting rod is arranged between the first hinge plate and the second hinge plate and is respectively hinged with the first hinge plate and the second hinge plate; the fixed box is arranged on the right side of the second hinge plate and is connected with the second hinge plate in a welding mode. Through structurally the improvement, it is strong to have the equilibrium, stable in structure and shock attenuation buffering's advantage to effectual solution the utility model discloses the problem that proposes in one of the prior art is with not enough.
Description
Technical Field
The utility model relates to an undercarriage technical field, more specifically the utility model specifically says, especially relates to a folding supplementary support of taking off of survey and drawing fixed wing aircraft.
Background
The landing gear, which is an indispensable part of a fixed wing aircraft, plays a very important role in the taxiing and takeoff process of the aircraft, and as the landing gear is the only supporting part of the aircraft, if the landing gear cannot bear the impact load of the aircraft, the consequences are very serious, so the requirement of the durability of the landing gear is very important.
However, the conventional undercarriage is composed of three independent folding supports, and when the fixed-wing aircraft takes off in a sliding manner, the stability of the whole structure of the undercarriage is poor due to the fact that the three folding supports are not provided with the correlated mechanisms, and the problem of unbalanced airframe can occur.
In view of this, research improvement is carried out to current problem, provides a survey and drawing fixed wing aircraft folding auxiliary takeoff support, aims at through this technique, reaches the purpose that solves the problem and improve practical value nature.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a folding supplementary support of taking off of survey and drawing fixed wing aircraft to solve present common undercarriage that proposes in the above-mentioned background and constitute by three independent folding support, when the fixed wing aircraft is slided and is taken off, because there is not the mechanism of correlation between the three folding support, lead to undercarriage overall structure's stability can be relatively poor, can appear the unbalanced problem of fuselage and not enough.
In order to achieve the above object, the utility model provides a folding supplementary support of taking off of survey and drawing fixed wing aircraft is reached by following concrete technical means:
a folding assisted take-off support for a survey fixed-wing aircraft, comprising: the bidirectional screw rod, the rod sleeve, the first hinge plate, the second hinge plate, the connecting rod, the fixed box, the limiting rod, the limiting plate, the support, the shaft sleeve, the fixed shaft, the fixed plate and the roller group; a rod sleeve is arranged on the outer side of the bidirectional screw rod, and the bidirectional screw rod is connected with the rod sleeve in a thread fit manner; the first hinge plate is arranged on the lower side of the rod sleeve and is connected with the rod sleeve in a welding mode; the second hinge plate is arranged below the right side of the first hinge plate, and the second hinge plate is movably connected with the first hinge plate through a connecting rod; the connecting rod is arranged between the first hinge plate and the second hinge plate and is respectively hinged with the first hinge plate and the second hinge plate; the fixed box is arranged on the right side of the second hinge plate and is connected with the second hinge plate in a welding mode; the limiting rod is arranged on the lower side in the fixing box and is connected with the fixing box in a welding mode; the limiting plate is arranged on the outer side of the limiting rod, and the limiting plate and the limiting rod are in sliding connection in a clearance fit mode; the support is arranged in the middle of the upper side of the limiting plate and is connected with the limiting plate in a welding mode; the shaft sleeve is arranged on the upper side of the support, and the shaft sleeve is connected with the support in a welding machine mode; the fixed shaft is arranged in the shaft sleeve and is connected with the shaft sleeve through a bearing; the fixed plates are respectively arranged at two ends of the fixed shaft and are connected with the fixed shaft in a welding mode; the roller train sets up the downside at fixed box, and the roller train is connected through the bolt fastening mode with fixed box.
As a further optimization of this technical scheme, the utility model relates to a folding supplementary support of taking off of survey and drawing fixed wing aircraft the rod cover is the pipe column structure, and the inside of rod cover is equipped with the screw thread to the mode that the rod cover is bilateral symmetry is provided with two.
As a further optimization of this technical scheme, the utility model relates to a folding supplementary support of taking off of survey and drawing fixed wing aircraft the centre of connecting rod is cylindric structure, and both ends are the platelike structure of shape for \21274, and the both ends of connecting rod are bilateral symmetry's mode setting.
As a further optimization of this technical scheme, the utility model relates to a folding supplementary support of taking off of survey and drawing fixed wing aircraft fixed box is the box body structure of cuboid, and the centre in the fixed box is provided with compression spring.
As a further optimization of this technical scheme, the utility model relates to a folding supplementary support of taking off of survey and drawing fixed wing aircraft the screwed cylindric structure is established for the upper end to the gag lever post, and the mode that the gag lever post is the rectangle range is provided with everywhere.
As a further optimization of this technical scheme, the utility model relates to a folding supplementary support of taking off of survey and drawing fixed wing aircraft the limiting plate is square platelike structure, and the mode that the surface of limiting plate is the rectangle range is provided with the circular shape through-hole of four places.
Because of above-mentioned technical scheme's application, compared with the prior art, the utility model have the following advantage:
1. the utility model relates to a folding supplementary support of taking off of survey and drawing fixed wing aircraft is through using two-way screw rod to be correlated with two folding supports, can guarantee that it carries out the activity of same frequency to make the device play the strong effect of equilibrium.
2. The utility model relates to a folding supplementary support of taking off of survey and drawing fixed wing aircraft designs through using the folding mode of side direction, compares the design of fore-and-aft direction among the prior art, when the aircraft descends, can avoid causing the problem that folding support was rolled over and is decreased because of the impact force is great to make the device play stable in structure's effect.
3. The utility model relates to a folding supplementary support of taking off of survey and drawing fixed wing aircraft sets up gag lever post and compression spring through the inside at fixed box, utilizes its collocation with the limiting plate, can cushion the aircraft take off or when descending with the impact force on ground to make the device play the effect of shock attenuation buffering.
4. The utility model discloses a to above-mentioned device structural improvement, it is strong to have the equilibrium, the advantage of stable in structure and shock attenuation buffering to effectual solution the utility model discloses the problem that proposes in background art one with not enough.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification. In the drawings:
fig. 1 is a schematic structural view of the present invention;
fig. 2 is a schematic view of the structure of the present invention;
fig. 3 is a schematic view of the sectional structure of the fixing box of the present invention.
In the figure: the bidirectional screw rod comprises a bidirectional screw rod 1, a rod sleeve 2, a first hinge plate 3, a second hinge plate 4, a connecting rod 5, a fixed box 6, a limiting rod 7, a limiting plate 8, a support 9, a shaft sleeve 10, a fixed shaft 11, a fixed plate 12 and a roller group 13.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments.
It is to be noted that, in the description of the present invention, "a plurality" means two or more unless otherwise specified; the terms "upper", "lower", "left", "right", "inner", "outer", "front", "rear", "head", "tail", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are merely for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Meanwhile, in the description of the present invention, unless otherwise explicitly specified or limited, the terms "connected" and "connected" should be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; the connection can be mechanical connection or electrical connection; may be directly connected or indirectly connected through an intermediate. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Referring to fig. 1 to 3, the utility model provides a survey and drawing fixed wing aircraft folding assisted take-off support's specific technical implementation:
a folding assisted take-off support for a survey fixed-wing aircraft, comprising: the device comprises a bidirectional spiral screw rod 1, a rod sleeve 2, a first hinge plate 3, a second hinge plate 4, a connecting rod 5, a fixed box 6, a limiting rod 7, a limiting plate 8, a support 9, a shaft sleeve 10, a fixed shaft 11, a fixed plate 12 and a roller group 13; a rod sleeve 2 is arranged on the outer side of the bidirectional screw rod 1, and the bidirectional screw rod 1 is connected with the rod sleeve 2 in a thread fit manner; the first hinge plate 3 is arranged on the lower side of the rod sleeve 2, and the first hinge plate 3 is connected with the rod sleeve 2 in a welding mode; the second hinge plate 4 is arranged below the right side of the first hinge plate 3, and the second hinge plate 4 is movably connected with the first hinge plate 3 through a connecting rod 5; the connecting rod 5 is arranged between the first hinge plate 3 and the second hinge plate 4, and the connecting rod 5 is respectively hinged with the first hinge plate 3 and the second hinge plate 4; the fixed box 6 is arranged on the right side of the second hinge plate 4, and the fixed box 6 is connected with the second hinge plate 4 in a welding mode; the limiting rod 7 is arranged at the lower side in the fixing box 6, and the limiting rod 7 is connected with the fixing box 6 in a welding mode; the limiting plate 8 is arranged on the outer side of the limiting rod 7, and the limiting plate 8 and the limiting rod 7 are in sliding connection in a clearance fit mode; the support 9 is arranged in the middle of the upper side of the limiting plate 8, and the support 9 is connected with the limiting plate 8 in a welding mode; the shaft sleeve 10 is arranged on the upper side of the support 9, and the shaft sleeve 10 is connected with the support 9 in a welding machine mode; the fixed shaft 11 is arranged inside the shaft sleeve 10, and the fixed shaft 11 is connected with the shaft sleeve 10 through a bearing; the fixed plates 12 are respectively arranged at two ends of the fixed shaft 11, and the fixed plates 12 are connected with the fixed shaft 11 in a welding mode; the roller group 13 is arranged at the lower side of the fixed box 6, and the roller group 13 is connected with the fixed box 6 in a bolt fixing mode.
Specifically, the rod sleeve 2 is of a circular tubular structure, threads are arranged inside the rod sleeve 2, and the rod sleeve 2 is arranged at two positions in a bilateral symmetry mode.
Specifically, the middle of the connecting rod 5 is of a cylindrical structure, the two ends of the connecting rod are of a v-21274; shaped plate-shaped structure, and the two ends of the connecting rod 5 are arranged in a left-right symmetrical mode.
Specifically, the fixed box 6 is a cuboid box body structure, and a compression spring is arranged in the middle of the fixed box 6.
Specifically, the limiting rod 7 is a cylindrical structure with threads at the upper end, and the limiting rod 7 is arranged at four positions in a rectangular arrangement mode.
Specifically, the limiting plate 8 is a square plate-shaped structure, and the surface of the limiting plate 8 is provided with four circular through holes in a rectangular arrangement.
The method comprises the following specific implementation steps:
first utilize the bolt hole on its surface of fixed plate 12 to install the both sides in the aircraft bottom, install two-way screw rod 1 in the centre of aircraft bottom, and insert outside rotation control device, when two-way screw rod 1 is rotatory, can drive rod cover 2 and carry out the ascending removal in relative direction, then control the flexible of wheel bank 13 through connecting rod 5, during through gag lever post 7 and 6 interior compression spring of fixed box and limiting plate 8's cooperation, can improve the impact force that the aircraft produced ground greatly, thereby still have stronger shock attenuation buffering effect when making the device possess the firm effect of structure, its practical value is greatly improved.
In summary, the following steps: according to the folding auxiliary takeoff support for the surveying and mapping fixed-wing aircraft, the two folding supports are associated by using the bidirectional spiral screw rod, so that the two folding supports can be guaranteed to move at the same frequency, and the device has a strong balance effect; compared with the design in the front-back direction in the prior art, the design in the side folding mode can avoid the problem that the folding bracket is broken due to large impact force when the aircraft lands, so that the device has the effect of stable structure; through set up gag lever post and compression spring in the inside of fixed box, utilize its collocation with the limiting plate, can cushion the aircraft take off or when descending with the impact force on ground to make the device play the effect of shock attenuation buffering.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (6)
1. A folding assisted take-off support for a survey fixed-wing aircraft, comprising: the device comprises a bidirectional spiral screw rod (1), a rod sleeve (2), a first hinge plate (3), a second hinge plate (4), a connecting rod (5), a fixed box (6), a limiting rod (7), a limiting plate (8), a support (9), a shaft sleeve (10), a fixed shaft (11), a fixed plate (12) and a roller set (13); the method is characterized in that: a rod sleeve (2) is arranged on the outer side of the bidirectional screw rod (1), and the bidirectional screw rod (1) is connected with the rod sleeve (2) in a thread fit manner; the first hinge plate (3) is arranged on the lower side of the rod sleeve (2), and the first hinge plate (3) is connected with the rod sleeve (2) in a welding mode; the second hinge plate (4) is arranged below the right side of the first hinge plate (3), and the second hinge plate (4) is movably connected with the first hinge plate (3) through a connecting rod (5); the connecting rod (5) is arranged between the first hinge plate (3) and the second hinge plate (4), and the connecting rod (5) is hinged with the first hinge plate (3) and the second hinge plate (4) respectively; the fixed box (6) is arranged on the right side of the second hinge plate (4), and the fixed box (6) is connected with the second hinge plate (4) in a welding mode; the limiting rod (7) is arranged on the lower side in the fixing box (6), and the limiting rod (7) is connected with the fixing box (6) in a welding mode; the limiting plate (8) is arranged on the outer side of the limiting rod (7), and the limiting plate (8) is in sliding connection with the limiting rod (7) in a clearance fit mode; the support (9) is arranged in the middle of the upper side of the limiting plate (8), and the support (9) is connected with the limiting plate (8) in a welding mode; the shaft sleeve (10) is arranged on the upper side of the support (9), and the shaft sleeve (10) is connected with the support (9) in a welding machine mode; the fixed shaft (11) is arranged inside the shaft sleeve (10), and the fixed shaft (11) is connected with the shaft sleeve (10) through a bearing; the fixing plates (12) are respectively arranged at two ends of the fixing shaft (11), and the fixing plates (12) are connected with the fixing shaft (11) in a welding mode; the roller group (13) is arranged on the lower side of the fixed box (6), and the roller group (13) is connected with the fixed box (6) in a bolt fixing mode.
2. The folding assisted take-off support for a survey and drawing fixed wing aircraft as claimed in claim 1, wherein: the rod sleeve (2) is of a circular tubular structure, threads are arranged inside the rod sleeve (2), and the rod sleeve (2) is arranged at two positions in a bilateral symmetry mode.
3. The folding assisted take-off support for a survey and drawing fixed wing aircraft as claimed in claim 1, wherein: the middle of the connecting rod (5) is of a cylindrical structure, the two ends of the connecting rod are of a v-21274; shaped plate-shaped structure, and the two ends of the connecting rod (5) are arranged in a bilateral symmetry mode.
4. The folding assisted take-off support for a survey and drawing fixed wing aircraft as claimed in claim 1, wherein: the fixed box (6) is of a cuboid box body structure, and a compression spring is arranged in the middle of the inside of the fixed box (6).
5. The folding assisted take-off support for a survey and drawing fixed wing aircraft as claimed in claim 1, wherein: the limiting rod (7) is of a cylindrical structure with threads at the upper end, and the limiting rod (7) is arranged at four positions in a rectangular arrangement mode.
6. The folding assisted take-off support for a survey and drawing fixed wing aircraft as claimed in claim 1, wherein: the limiting plates (8) are of square plate-shaped structures, and the surfaces of the limiting plates (8) are provided with through holes in four circular shapes in a rectangular arrangement mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020435998.9U CN212332955U (en) | 2020-03-31 | 2020-03-31 | Folding auxiliary takeoff support of surveying and mapping fixed-wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020435998.9U CN212332955U (en) | 2020-03-31 | 2020-03-31 | Folding auxiliary takeoff support of surveying and mapping fixed-wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212332955U true CN212332955U (en) | 2021-01-12 |
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ID=74069767
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020435998.9U Expired - Fee Related CN212332955U (en) | 2020-03-31 | 2020-03-31 | Folding auxiliary takeoff support of surveying and mapping fixed-wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212332955U (en) |
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2020
- 2020-03-31 CN CN202020435998.9U patent/CN212332955U/en not_active Expired - Fee Related
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20210112 |
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| CF01 | Termination of patent right due to non-payment of annual fee |