CN205675236U - A kind of course of new aircraft - Google Patents
A kind of course of new aircraft Download PDFInfo
- Publication number
- CN205675236U CN205675236U CN201620613956.3U CN201620613956U CN205675236U CN 205675236 U CN205675236 U CN 205675236U CN 201620613956 U CN201620613956 U CN 201620613956U CN 205675236 U CN205675236 U CN 205675236U
- Authority
- CN
- China
- Prior art keywords
- fuselage
- baffle
- montant
- course
- new aircraft
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Abstract
The utility model discloses a kind of course of new aircraft, including fuselage, it is arranged on the wing of fuselage both sides, empennage, fuselage is connected by gripper shoe with empennage, the afterbody of fuselage is provided with motor, it is provided with propeller on the output shaft of motor, the bottom of fuselage is provided with two resilient support cylinders, and the bottom of resilient support cylinder is provided with transverse slat, and the bottom of transverse slat is provided with a pair roller.It provides the benefit that: resilient support cylinder can play the effect of damping, it is to avoid fuselage is damaged during landing.
Description
Technical field
This utility model relates to a kind of course of new aircraft.
Background technology
Chinese patent 201120485304.3 provides a kind of SUAV, including: forebody, two wings and tail
The wing, two wings are symmetrically arranged at the both sides of forebody, and empennage is connected with forebody by shoe, the company of being provided with on forebody
Extension bar part, wing is connected with forebody by connecting rod.The SUAV of this utility model uses forebody, wing and tail
The wing independently makes to refill and is fitted on together, and its simple in construction, deadweight are relatively light, and this unmanned plane can be dismantled and carry respectively, makes
Obtain easy to carry；Unmanned plane uses shell girder structure, has the eyelid covering of glass fiber compound material in surface configuration, in satisfied nothing
On the premise of man-machine structural strength rigidity so that the deadweight of unmanned plane is greatly reduced.But do not take bottom this unmanned plane to subtract
Shake measure, has the biggest impact with ground during landing, is easily damaged.
Utility model content
Problem to be solved in the utility model is to provide a kind of course of new aircraft, and the resilient support cylinder of this course of new aircraft can
Playing the effect of damping, it is to avoid fuselage is damaged during landing.
In order to solve above-mentioned technical problem, the technical solution adopted in the utility model is: a kind of course of new aircraft, including machine
Body, being arranged on the wing of described fuselage both sides, empennage, described fuselage is connected by gripper shoe with described empennage, described fuselage
Afterbody is provided with motor, and the output shaft of described motor is provided with propeller, it is characterised in that the bottom of described fuselage is provided with
Two resilient support cylinders, the bottom of described resilient support cylinder is provided with transverse slat, and the bottom of described transverse slat is provided with a pair roller；Institute
State resilient support cylinder and include being arranged on the base plate at described transverse slat top, the hollow posts being welded on described base plate, support column, described
It is movably set with the baffle suitable with described hollow posts inner chamber in hollow posts, described base plate is provided with two through described
Baffle the montant being slidably connected with described baffle, described montant is positioned at below described baffle the most sheathed
Having sleeve, two described sleeve pipes are connected by bow, and described bow is connected by pole with described baffle, described perpendicular
Between described baffle and sleeve pipe, it is arranged with the first spring on bar, described montant overlaps between described sleeve pipe and base plate
Being provided with the second spring, the top of described support column is connected with described fuselage, bottom extend in described hollow posts and with described every
Soundboard connects.
Preferably, above-mentioned course of new aircraft, wherein said baffle includes the cylindrical cavity of hollow, is arranged on institute
State the upper cover plate at cylindrical cavity top, be arranged on the lower cover of described cylindrical cavity bottom, described upper cover plate, cylinder
It is provided with acoustical cotton in the space that bodily form cavity, lower cover are formed.
Preferably, above-mentioned course of new aircraft, the top of wherein said montant is provided with limiting plate.
Preferably, above-mentioned course of new aircraft, sheathed between described limiting plate and baffle on wherein said montant
There is the 3rd spring.
Preferably, above-mentioned course of new aircraft, the wherein said hollow posts inwall near top is provided with at least limit
Position bar, accordingly, the outer wall of described support column is provided with at least one stopper slot, described limit along the length direction of described support column
In the termination of position bar extends to described stopper slot and it is slidably connected with described stopper slot.
Of the present utility model have the technical effect that: resilient support cylinder can play the effect of damping, it is to avoid machine
It is damaged during landing, extends service life of the present utility model, practical；During landing, fuselage drives
Support column moves downward, and support column drives baffle to move downward, and is further driven to two sleeve pipes and moves downward, so that the
One spring compresses together with the second spring, and so design makes the elastic performance flexibly supporting cylinder be improved；Two sleeve pipes lead to
Cross bow to connect so that two sleeve pipes can move together；Baffle produces when can absorb the first spring and the second spring-compressed
Raw noise.
Accompanying drawing explanation
Fig. 1 is top view of the present utility model；
Fig. 2 is front view of the present utility model；
Fig. 3 is the structural representation of Fig. 2 Elastic support tube；
Fig. 4 is the structural representation of baffle in Fig. 3；
Fig. 5 is the right view of support column in Fig. 3.
Detailed description of the invention
Below in conjunction with accompanying drawing, detailed description of the invention of the present utility model is further described, so that this utility model
Technical scheme be more readily understood and grasp.
As shown in Fig. 1,2,3,4,5, a kind of course of new aircraft, including fuselage 1, it is arranged on the wing 11 of fuselage 1 both sides, tail
The wing 12, fuselage 1 is connected by gripper shoe 13 with empennage 12, and the afterbody of fuselage 1 is provided with motor 14, and the output shaft of motor 14 sets
It is equipped with propeller 15.
The bottom of fuselage 1 is provided with two resilient support cylinders 2, and the bottom of resilient support cylinder 2 is provided with transverse slat 3, transverse slat 3
Bottom is provided with a pair roller 31.
Flexibly support hollow posts 22, support that cylinder 2 includes the base plate 21 being arranged on transverse slat 3 top, is welded on base plate 21
Post 23, is movably set with the baffle 4 suitable with hollow posts 22 inner chamber, base plate 21 is provided with two and passes in hollow posts 22
Baffle 4 and with the montant 24 that baffle 4 is slidably connected, montant 24 is positioned at below baffle 4 and is the most slidably arranged with one
Sleeve pipe 25, two sleeve pipes 25 are connected by bow 26, and bow 26 is connected by pole 27 with baffle 4, and montant 24 is upper
Between baffle 4 and sleeve pipe 25, it is arranged with the first spring 28, montant 24 is arranged with between sleeve pipe 25 and base plate 21
Two springs 29, the top of support column 23 is connected with fuselage 1, in bottom extends to hollow posts 22 and is connected with baffle 4.
Wherein baffle 4 includes the cylindrical cavity 41 of hollow, is arranged on the upper cover plate at cylindrical cavity 41 top
42, being arranged on the lower cover 43 bottom cylindrical cavity 41, upper cover plate 42, cylindrical cavity 41, lower cover 43 are formed
It is provided with acoustical cotton 44, so design in space and makes the firm in structure of baffle 4.
Wherein the top of montant 24 is provided with limiting plate 5, and limiting plate 5 prevents baffle 4 to depart from montant 24.Montant 24
On between limiting plate 5 and baffle 4, be arranged with the 3rd spring 6, the 3rd spring 6 is further such that resilient support the subtracting of cylinder 2
Shock stability is improved.
Wherein the hollow posts 22 inwall near top is provided with two gag lever posts 71, accordingly, the outer wall edge of support column 23
The length direction of support column 23 is provided with two stopper slots 72, in the termination of gag lever post 71 extends to stopper slot 72 and and stopper slot
72 are slidably connected, and so design avoids during support column 23 rises or declines and occurs rocking so that resilient support cylinder 2
Structure is firmer.
Certainly, these are only preferred embodiment of the present utility model, non-the most i.e. limit to patent of the present utility model
Scope, all utilization this utility model description and graphic content institute are simple for it modifies and equivalent structure change, all should in like manner wrap
Within being contained in scope of patent protection of the present utility model.
Claims (5)
1. a course of new aircraft, including fuselage, is arranged on the wing of described fuselage both sides, empennage, described fuselage and described tail
The wing is connected by gripper shoe, and the afterbody of described fuselage is provided with motor, and the output shaft of described motor is provided with propeller, and it is special
Levy and be: the bottom of described fuselage is provided with two resilient support cylinders, and the bottom of described resilient support cylinder is provided with transverse slat, described
The bottom of transverse slat is provided with a pair roller；Described resilient support cylinder includes being arranged on the base plate at described transverse slat top, being welded on institute
State the hollow posts on base plate, support column, in described hollow posts, be movably set with the baffle suitable with described hollow posts inner chamber,
It is provided with two on described base plate and passes described baffle the montant being slidably connected with described baffle, described montant is positioned at
The most slidably being arranged with sleeve below described baffle, two described sleeve pipes are connected by bow, described bow with
Described baffle is connected by pole, and described montant is arranged with between described baffle and sleeve pipe the first spring, described
Being arranged with the second spring on montant between described sleeve pipe and base plate, the top of described support column is connected with described fuselage, the end
In end extends to described hollow posts and it is connected with described baffle.
Course of new aircraft the most according to claim 1, it is characterised in that: described baffle includes the cylindrical chamber of hollow
Body, it is arranged on the upper cover plate at described cylindrical cavity top, is arranged on the lower cover of described cylindrical cavity bottom, described
It is provided with acoustical cotton in the space that upper cover plate, cylindrical cavity, lower cover are formed.
Course of new aircraft the most according to claim 1, it is characterised in that: the top of described montant is provided with limiting plate.
Course of new aircraft the most according to claim 3, it is characterised in that: it is positioned at described limiting plate and sound insulation on described montant
The 3rd spring it is arranged with between plate.
Course of new aircraft the most according to claim 1, it is characterised in that: the described hollow posts inwall near top is provided with
At least gag lever post, accordingly, the outer wall of described support column is provided with at least one limit along the length direction of described support column
Position groove, in the termination of described gag lever post extends to described stopper slot and is slidably connected with described stopper slot.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620613956.3U CN205675236U (en) | 2016-06-21 | 2016-06-21 | A kind of course of new aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620613956.3U CN205675236U (en) | 2016-06-21 | 2016-06-21 | A kind of course of new aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205675236U true CN205675236U (en) | 2016-11-09 |
Family
ID=57431460
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620613956.3U Expired - Fee Related CN205675236U (en) | 2016-06-21 | 2016-06-21 | A kind of course of new aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205675236U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108609440A (en) * | 2018-05-07 | 2018-10-02 | 刘延昌 | A kind of Anti-seismic electric system stringing auxiliary device |
-
2016
- 2016-06-21 CN CN201620613956.3U patent/CN205675236U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108609440A (en) * | 2018-05-07 | 2018-10-02 | 刘延昌 | A kind of Anti-seismic electric system stringing auxiliary device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161109 Termination date: 20170621 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |