CN208278319U - A kind of aircraft avoidance protective cover - Google Patents
A kind of aircraft avoidance protective cover Download PDFInfo
- Publication number
- CN208278319U CN208278319U CN201820859301.3U CN201820859301U CN208278319U CN 208278319 U CN208278319 U CN 208278319U CN 201820859301 U CN201820859301 U CN 201820859301U CN 208278319 U CN208278319 U CN 208278319U
- Authority
- CN
- China
- Prior art keywords
- protective cover
- aircraft
- plectane
- sliding bar
- movable hinge
- 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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- Vibration Prevention Devices (AREA)
Abstract
The utility model discloses a kind of aircraft avoidance protective covers, including return spring, protective cover, resilient cushion, warning light and spherical movable hinge, by setting return spring for the vibration that plectane generates when being contacted with ground to be buffered and absorbed, it avoids shaking and excessive causes certain damage to aircraft body and shield itself, move up sliding bar in cylinder under the action of the parts self gravity such as aircraft body and protective cover simultaneously, to further make to contact at the top of shield bottom and plectane, to play the role of sealing to protective cover bottom, the sundries such as weeds of the aircraft when droping to ground on ground are avoided to enter inside protective cover by protective cover bottom opening, further play the role of protection to aircraft body, improve the practicability of equipment, it is used for by setting resilient cushion to plectane and ground The vibration generated when contact is further absorbed.
Description
Technical field
The utility model relates to a kind of protective cover, specifically a kind of aircraft avoidance protective cover.
Background technique
Currently, unmanned plane is widely used in each field, rotor is exposed to external more or is filled using the protection of fixed frame posture
It sets.In the application scenarios such as city, forest, there are the various disorders objects such as tree branches and leaves, electric wire, sunning object in low latitude, once fly
Row device is interfered by barrier, and rotor lift moment changes with attitude of flight vehicle, is easy to fall aircraft stall, and rotor is naked
It exposes outside, easily by foreign-body aspiration, while existing unmanned plane is easy to nobody to drop to vibration when being contacted with ground larger
Machine itself causes certain damage.
Utility model content
The purpose of this utility model is to provide a kind of aircraft avoidance protective covers, to solve to propose in above-mentioned background technique
The problem of.
To achieve the above object, the utility model provides the following technical solutions:
A kind of aircraft avoidance protective cover, including connecting bracket, spherical movable hinge, connecting rod, landing protective device, mention
Show that lamp, auxiliary landing device, protective cover and aircraft body, the protective cover are netted rigid, setting inside protective cover
There is spherical movable hinge, spherical movable hinge bottom end is along the circumferential direction equidistant to be fixedly connected there are four connecting bracket, is connected
It connects bracket and is not fixedly mounted on protective cover inner wall, the ballhead of the spherical movable hinge with the hinged one end of spherical movable
Outside is fixedly connected with one end of connecting rod, and the other end of connecting rod is fixedly mounted on aircraft body bottom, the protective cover
It is designed using spindle, the bottom of protective cover is designed using circular open, and the protective cover Basolateral is along the circumferential direction equidistant
From multiple warning lights are equipped with, the spherical movable hinged base is provided with landing protective device, the landing protective device packet
Cylinder, plectane, sliding bar and return spring are included, the cylinder is fixedly mounted on spherical movable hinged base, and sliding is set in cylinder
It is equipped with sliding bar, protective cover is stretched out after passing through protective cover bottom opening in the end of sliding bar, and sliding boom end is fixedly mounted on circle
Plate top circular position, the radius of the plectane are greater than the radius of protective cover bottom circular opening, the sliding bar top and cylinder
Return spring is provided between internal lateral roof, the both ends of return spring are respectively fixedly connected at the top of sliding bar and on the inside of cylinder
Top, the protective cover Basolateral have along the circumferential direction been equidistantly positioned multiple auxiliary landing devices.
As a further solution of the present invention: the ballhead of the connecting rod and spherical movable hinge is integrated into
Type.
The protective cover is set in aircraft body outside and and aircraft as a further solution of the present invention,
Body maintains a certain distance.
The warning light is LED light as a further solution of the present invention,.
The plectane bottom is fixedly connected with resilient cushion, the resilient cushion as a further solution of the present invention,
For rubber material.
The auxiliary landing device is identical as landing protective device structure as a further solution of the present invention,.
Compared with prior art, the utility model has the beneficial effects that by setting protective cover for preventing foreign-body aspiration
Rotor, to play the role of protection to aircraft body, protective cover ensure that the normal stream of air-flow by using mesh design
It is logical, to further ensure the normal flight of aircraft body, the practicability of equipment is improved, when protective cover is by can not resist
When refusing external force, protective cover can make aircraft body held stationary posture, to further ensure winged according to external force direction activity
The normal flight of row device body, when protective cover tip touches barrier, can fly in the ascent stage of aircraft body
It pushes the flexible barriers such as leaf, and the fusiform streamiline surface of join protection cover under the impetus of device body lift open, avoids just
Sexual dysfunction object improves the practicability of equipment, by setting warning light for improving the identification of equipment itself in night flight
Degree improves the practicability of equipment, sliding bar exists so that operator be facilitated to observe and grasp in face of device location on ground
It is moved in cylinder under the action of the vibration that plectane generates when being contacted with ground and return spring is squeezed, by being arranged back
Position spring avoids shaking excessive to aircraft body for the vibration that plectane generates when being contacted with ground to be buffered and absorbed
Certain damage is caused with shield itself, improves the damping performance of equipment, while in aircraft body and protective cover etc. zero
Move up sliding bar in cylinder under the action of part self gravity, to further make to connect at the top of shield bottom and plectane
Touching, to play the role of sealing to protective cover bottom, avoids the weeds of aircraft when droping to ground on ground etc. miscellaneous
Object is entered inside protective cover by protective cover bottom opening, further plays the role of protection to aircraft body, is improved
The practicability of equipment, by setting resilient cushion for further being absorbed to the vibration that plectane generates when being contacted with ground,
Further play the role of damping when aircraft lands by setting auxiliary landing device, further improves subtracting for equipment
Shock stability ensure that the safe falling of aircraft.
Detailed description of the invention
Fig. 1 is a kind of structural schematic diagram of aircraft avoidance protective cover.
Fig. 2 is a kind of structural schematic diagram of landing protective device in aircraft avoidance protective cover.
Fig. 3 is a kind of top view of aircraft avoidance protective cover.
Fig. 4 is a kind of usage state diagram of aircraft avoidance protective cover.
It is as shown in the figure: connecting bracket 1, spherical movable hinge 2, connecting rod 3, landing protective device 4, warning light 5, auxiliary drop
Dropping control device 6, protective cover 7, cylinder 8, resilient cushion 9, plectane 10, sliding bar 11, return spring 12, aircraft body 13.
Specific embodiment
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are without making creative work
Every other embodiment obtained, fall within the protection scope of the utility model.
Please refer to Fig. 1~4, in the utility model embodiment, a kind of aircraft avoidance protective cover, including connecting bracket 1, ball
Shape hinges 2, connecting rod 3, landing protective device 4, warning light 5, auxiliary landing device 6, protective cover 7 and aircraft body
13, the protective cover 7 is netted rigid, and protective cover 7 is internally provided with spherical movable hinge 2, the spherical movable hinge 2
Bottom end is along the circumferential direction equidistant to be fixedly connected there are four connecting bracket 1, what connecting bracket 1 was not connect with spherical movable hinge 2
One end is fixedly mounted on 7 inner wall of protective cover, is fixedly connected with the one of connecting rod 3 on the outside of the ballhead of the spherical movable hinge 2
End, the other end of connecting rod 3 are fixedly mounted on 13 bottom of aircraft body, the spherical shape of the connecting rod 3 and spherical movable hinge 2
Head is integrally formed, and the protective cover 7 is set in 13 outside of aircraft body and maintains a certain distance with aircraft body 13,
By setting protective cover 7 for preventing foreign-body aspiration rotor, to play the role of protection to aircraft body, protective cover 7 is logical
It crosses and ensure that the normal circulation of air-flow mentions to further ensure the normal flight of aircraft body 13 using mesh design
The high practicability of equipment, when protective cover 7 is by irresistible external force, protective cover 7 can make to fly according to external force direction activity
13 held stationary posture of device body, to further ensure the normal flight of aircraft body 13, the protective cover 7 is using spinning
Capitate design, the ascent stage of aircraft body 13 can be in aircraft body when 7 tip of protective cover touches barrier
It pushes the flexible barriers such as leaf, and the fusiform streamiline surface of join protection cover under the impetus of 13 lift open, avoids rigid barrier
Hinder object, improve the practicability of equipment, the bottom of the protective cover 7 is designed using circular open, 7 Basolateral of protective cover
Along the circumferential direction equidistant to be equipped with multiple warning lights 5, the warning light 5 is LED light, is used for by setting warning light 5 at night
The identification of equipment itself is improved when late flight, so that operator is facilitated to observe and grasp in face of device location on ground,
Improve the practicability of equipment；
2 bottom of spherical movable hinge be provided with landing protective device 4, the landing protective device 4 including cylinder 8,
Resilient cushion 9, plectane 10, sliding bar 11 and return spring 12, the cylinder 8 are fixedly mounted on 2 bottom of spherical movable hinge, cylinder
Sliding is provided with sliding bar 11 in 8, and protective cover 7, sliding bar 11 are stretched out after passing through 7 bottom opening of protective cover in the end of sliding bar 11
End is fixedly mounted on 10 top circular position of plectane, and the radius of the plectane 10 is greater than the half of 7 bottom circular of protective cover opening
Diameter is provided with return spring 12 between 11 top of sliding bar and 8 inside top of cylinder, and the both ends of return spring 12 are solid respectively
Surely it is connected to 11 top of sliding bar and 8 inside top of cylinder, when aircraft landing, plectane 10 with ground face contact, avoids first
Shield 7 is directly contacted with ground, so that people plays the role of protection to shield 7, sliding bar 11 is on plectane 10 and ground
It is moved in cylinder 8 under the action of the vibration generated when contact and return spring 12 is squeezed, by the way that return spring is arranged
12, for the vibration that plectane 10 generates when being contacted with ground to be buffered and absorbed, avoid shaking excessive to aircraft body 13
Certain damage is caused in itself with shield 7, improves the damping performance of equipment, while in aircraft body 13 and protective cover 7
Move up sliding bar 11 in cylinder 8 under the action of equal parts self gravity, to further make 7 bottom of shield and circle
It is contacted at the top of plate 10, to play the role of sealing to 7 bottom of protective cover, avoids aircraft when droping to ground on ground
The sundries such as weeds entered inside protective cover 7 by 7 bottom opening of protective cover, protection further is played to aircraft body 13
Effect, improve the practicability of equipment, 10 bottom of plectane is fixedly connected with resilient cushion 9, and the resilient cushion 9 is rubber material
Matter, by setting resilient cushion 9 for further being absorbed to the vibration that plectane 10 generates when being contacted with ground, the protection
It covers 7 Basolaterals and has along the circumferential direction been equidistantly positioned multiple auxiliary landing devices 6, the auxiliary landing device 6 and landing are anti-
4 structure of protection unit is identical, further plays the role of damping when aircraft lands by setting auxiliary landing device 6, into
One step improves the damping performance of equipment, ensure that the safe falling of aircraft.
The working principle of the utility model is: by setting protective cover 7 for preventing foreign-body aspiration rotor, thus to flight
Device body plays the role of protection, and protective cover 7 ensure that the normal circulation of air-flow by using mesh design, to further protect
The normal flight for having demonstrate,proved aircraft body 13 improves the practicability of equipment, when protective cover 7 is by irresistible external force, protects
Shield 7 can make 13 held stationary posture of aircraft body, to further ensure aircraft body according to external force direction activity
13 normal flight, the ascent stage of aircraft body 13 can be in aircraft when 7 tip of protective cover touches barrier
It pushes the flexible barriers such as leaf, and the fusiform streamiline surface of join protection cover under the impetus of 13 lift of body open, avoids just
Sexual dysfunction object improves the practicability of equipment, by setting warning light 5 for improving the identification of equipment itself in night flight
Degree improves the practicability of equipment, works as aircraft so that operator be facilitated to observe and grasp in face of device location on ground
When landing, plectane 10 with ground face contact, avoids shield 7 from directly contacting with ground first, so that people plays guarantor to shield 7
The effect of shield, sliding bar 11 move and to return under the action of the vibration that plectane 10 generates when being contacted with ground in cylinder 8
Spring 12 is squeezed, by setting return spring 12 be used for the vibration that plectane 10 generates when being contacted with ground carry out buffering and
Absorb, avoid shaking it is excessive certain damage is caused in itself to aircraft body 13 and shield 7, improve the damping property of equipment
Can, while making under the action of the parts self gravitys such as aircraft body 13 and protective cover 7 sliding bar 11 in cylinder 8 to moving up
It is dynamic, thus further make to contact at the top of 7 bottom of shield and plectane 10, thus play the role of sealing to 7 bottom of protective cover,
The sundries such as weeds of the aircraft when droping to ground on ground are avoided to enter inside protective cover 7 by 7 bottom opening of protective cover,
Further play the role of protection to aircraft body 13, improve the practicability of equipment, by setting resilient cushion 9 for pair
The vibration that plectane 10 generates when being contacted with ground is further absorbed, and is further being flown by setting auxiliary landing device 6
Row device plays the role of damping when landing, and further improves the damping performance of equipment, ensure that the safe falling of aircraft.
Although the utility model is described in detail with reference to the foregoing embodiments, come for those skilled in the art
Say, it is still possible to modify the technical solutions described in the foregoing embodiments, or to part of technical characteristic into
Row equivalent replacement, within the spirit and principle of the utility model, any modification, equivalent replacement, improvement and so on should all
It is included within the scope of protection of this utility model.
Claims (6)
1. a kind of aircraft avoidance protective cover, including connecting bracket (1), spherical movable hinge (2), connecting rod (3), landing protection
Device (4), warning light (5), auxiliary landing device (6), protective cover (7) and aircraft body (13), which is characterized in that the guarantor
Shield (7) is netted rigid, and protective cover (7) is internally provided with spherical movable hinge (2), the spherical movable hinge (2)
Bottom end is along the circumferential direction equidistant to be fixedly connected there are four connecting bracket (1), connecting bracket (1) not with spherical movable hinge (2)
One end of connection is fixedly mounted on protective cover (7) inner wall, the company of being fixedly connected on the outside of the ballhead of the spherical movable hinge (2)
One end of extension bar (3), the other end of connecting rod (3) are fixedly mounted on aircraft body (13) bottom, and the protective cover (7) uses
Spindle design, the bottom of protective cover (7) is using circular open design, and protective cover (7) Basolateral is along the circumferential direction etc.
Distance is equipped with multiple warning lights (5), and spherical movable hinge (2) bottom is provided with landing protective device (4), the landing
Protective device (4) includes cylinder (8), plectane (10), sliding bar (11) and return spring (12), and the cylinder (8) is fixedly mounted
In spherical movable hinge (2) bottom, sliding is provided with sliding bar (11) in cylinder (8), and the end of sliding bar (11) passes through protection
Protective cover (7) are stretched out after covering (7) bottom opening, sliding bar (11) end is fixedly mounted on plectane (10) top circular position, institute
The radius for stating plectane (10) is greater than the radius of protective cover (7) bottom circular opening, and sliding bar (11) top and cylinder (8) are interior
Be provided between lateral roof return spring (12), the both ends of return spring (12) be respectively fixedly connected at the top of the sliding bar (11) and
Cylinder (8) inside top, protective cover (7) Basolateral have along the circumferential direction been equidistantly positioned multiple auxiliary landing devices
(6)。
2. a kind of aircraft avoidance protective cover according to claim 1, which is characterized in that the connecting rod (3) and spherical shape
The ballhead of hinges (2) is integrally formed.
3. a kind of aircraft avoidance protective cover according to claim 1, which is characterized in that the protective cover (7) is set in
It is maintained a certain distance on the outside of aircraft body (13) and with aircraft body (13).
4. a kind of aircraft avoidance protective cover according to claim 1, which is characterized in that the warning light (5) is LED
Lamp.
5. a kind of aircraft avoidance protective cover according to claim 1, which is characterized in that plectane (10) bottom is fixed
It is connected with resilient cushion (9), the resilient cushion (9) is rubber material.
6. a kind of aircraft avoidance protective cover according to claim 1, which is characterized in that the auxiliary landing device (6)
It is identical as landing protective device (4) structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820859301.3U CN208278319U (en) | 2018-06-04 | 2018-06-04 | A kind of aircraft avoidance protective cover |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820859301.3U CN208278319U (en) | 2018-06-04 | 2018-06-04 | A kind of aircraft avoidance protective cover |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208278319U true CN208278319U (en) | 2018-12-25 |
Family
ID=64706155
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820859301.3U Expired - Fee Related CN208278319U (en) | 2018-06-04 | 2018-06-04 | A kind of aircraft avoidance protective cover |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208278319U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112623181A (en) * | 2020-12-16 | 2021-04-09 | 北华航天工业学院 | Shuttle-shaped structure for aircraft |
| CN116767500A (en) * | 2022-02-23 | 2023-09-19 | 张庆玲 | Multi-range multi-azimuth laser mapping system |
-
2018
- 2018-06-04 CN CN201820859301.3U patent/CN208278319U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112623181A (en) * | 2020-12-16 | 2021-04-09 | 北华航天工业学院 | Shuttle-shaped structure for aircraft |
| CN116767500A (en) * | 2022-02-23 | 2023-09-19 | 张庆玲 | Multi-range multi-azimuth laser mapping system |
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Legal Events
| 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: 20181225 Termination date: 20210604 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |