CN205971813U - Foot rest structure of unmanned helicopter - Google Patents
Foot rest structure of unmanned helicopter Download PDFInfo
- Publication number
- CN205971813U CN205971813U CN201621002957.0U CN201621002957U CN205971813U CN 205971813 U CN205971813 U CN 205971813U CN 201621002957 U CN201621002957 U CN 201621002957U CN 205971813 U CN205971813 U CN 205971813U
- Authority
- CN
- China
- Prior art keywords
- frame
- right crus
- left foot
- depopulated helicopter
- connecting rod
- 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
Links
Abstract
The utility model discloses a foot rest structure of unmanned helicopter, including left foot frame and the right crus of diaphragm frame that is located unmanned helicopter bottom both sides symmetrical arrangement, left foot frame is buckled by the body with the right crus of diaphragm frame and is the isosceles trapezoid form, and the bottom of left foot frame and right crus of diaphragm frame be the enclosed construction, and the left foot frame puts up with the right crus of diaphragm and passes through the connecting rod connection between the top, is equipped with the bumper shock absorber on the connecting rod, and the bumper shock absorber is connected bottom unmanned helicopter. The utility model discloses the left foot frame that sets up and the bottom of right crus of diaphragm frame are the enclosed construction, and the in -process left foot puts up and the right crus of diaphragm frame catches on weeds to avoid unmanned helicopter to take off and land in the field, brings the potential safety hazard for the flight of unmanned helicopter, the cushioning effect is played when making unmanned helicopter descend to setting up of bumper shock absorber, has protected the safety of unmanned helicopter.
Description
Technical field
This utility model belongs to depopulated helicopter field, particularly to a kind of foot rest structure of depopulated helicopter.
Background technology
Rotor wing unmanned aerial vehicle, also referred to as depopulated helicopter, its construction is fairly simple, and also ratio is less expensive for price, even more important
It is that it does not need emission system moreover it is possible to VTOL, more can freely hover, and motility of flying is quite superb,
Can use various speed, flown with the air route of various flight profile, mission profiles.In general flight quality, also can present that " two is little
The important feature of one height "：Chatter is little, noise is little, and Reliability comparotive is high.Therefore, in the country that Helicopter Technology is flourishing, nobody drives
Sail helicopter to begin to very early develop.For example, the Kaman company of the U.S. just once released pilotless helicopter early in the fifties, and
And had some models to put into the practice stage.
At present, the front and back end of the bottom of the foot rest of existing depopulated helicopter all has and stretches out structure, in the wild during landing, stretches
Go out structure and may catch on thick grass, bring risk to depopulated helicopter.Further, existing foot rest and body are generally rigidity and connect
Connect, when depopulated helicopter lands, foot rest contacts the moment on ground, can be subject to be delivered to the enormous impact force of fuselage from foot rest,
It is unfavorable for the landing safety of depopulated helicopter.
Content of the invention
For overcoming the problem of the deficiencies in the prior art and presence, this utility model provides a kind of foot rest knot of depopulated helicopter
Structure, structure is simple, safe.
This utility model is achieved through the following technical solutions：
A kind of foot rest structure of depopulated helicopter, including the left foot frame being arranged symmetrically positioned at depopulated helicopter two bottom sides and
Right crus of diaphragm frame, described left foot frame and right crus of diaphragm frame are in isosceles trapezoid shape by body bending, and the bottom of left foot frame and right crus of diaphragm frame is envelope
Close structure, connected by connecting rod between left foot frame and right crus of diaphragm frame top, connecting rod is provided with amortisseur, amortisseur is straight with unmanned
Rise motor spindle to connect.
Described connecting rod is provided with two, and each connecting rod is equipped with two amortisseurs.
Described amortisseur includes fixed mechanism and fix bar, and fixed mechanism is fixed in connecting rod, and fix bar is straight with unmanned
The bottom of the machine of liter connects, and is provided with damping spring between fix bar and fixed mechanism.
Described fixed mechanism includes sleeve, and damping spring is placed in fix bar, and damping spring is located in sleeve, sleeve side
It is provided with the fixed block for fixed connecting rod.
Described sleeve bottom end is provided with the anchor tip for fixing water tank.
Described left foot frame and right crus of diaphragm frame are in that " eight " shape is arranged.
Described left foot frame, right crus of diaphragm frame and connecting rod are integrated bending forming.
It is provided with bracing piece between two connecting rods between described left foot frame and right crus of diaphragm frame.
The bottom of the left foot frame of this utility model setting and right crus of diaphragm frame is enclosed construction, it is to avoid depopulated helicopter rises in the wild
During fall, left foot frame and right crus of diaphragm frame catch on thick grass, bring potential safety hazard to the flight of depopulated helicopter；The setting of amortisseur makes
Play cushioning effect when obtaining depopulated helicopter landing, protect the safety of depopulated helicopter.
Brief description
Fig. 1 is structural representation of the present utility model；
Fig. 2 is the perspective view of amortisseur in this utility model；
Fig. 3 is the cross section structure diagram of amortisseur in this utility model.
In figure：1- left foot frame, 2- right crus of diaphragm frame, 3- connecting rod, 4- amortisseur, 41- fix bar, 42- fixed mechanism, 421- covers
Cylinder, 422- fixed block, 43- damping spring, 44- anchor tip, 5- bracing piece, 6- water tank.
Specific embodiment
For the ease of the understanding of those skilled in the art, below in conjunction with the drawings and specific embodiments this utility model is made into
One step describes in detail.
As shown in figure 1, a kind of foot rest structure of depopulated helicopter, it is arranged symmetrically including positioned at depopulated helicopter two bottom sides
Left foot frame 1 and right crus of diaphragm frame 2, left foot frame 1 and right crus of diaphragm frame 2 are in that " eight " shape is arranged, this structural stability is good.Left foot frame 1 and the right side
Foot rest 2 is in isosceles trapezoid shape by body bending, and the bottom of left foot frame 1 and right crus of diaphragm frame 2 is enclosed construction.Left foot frame 1 and the right side
Connected by connecting rod 3 between foot rest 2 top.Left foot frame 1, right crus of diaphragm frame 2 and connecting rod 3 are integrated bending forming, and integral type sets
Meter is easy to manufacture.Connecting rod 3 is provided with amortisseur 4, and amortisseur 4 is connected with depopulated helicopter bottom.Connecting rod 3 is provided with two,
Two amortisseurs 4 are equipped with each connecting rod 3.For increasing the stability of structure, two between left foot frame 1 and right crus of diaphragm frame 2
It is provided with bracing piece 5 between connecting rod 3.
As shown in Figures 2 and 3, amortisseur 4 includes fixed mechanism 42 and fix bar 41, and fixed mechanism 42 is fixed on connecting rod
On 3, fix bar 41 is connected with the bottom of depopulated helicopter, is provided with damping spring 43 between fix bar 41 and fixed mechanism 42.Gu
Determine mechanism 42 and include sleeve 421, damping spring 43 is placed in fix bar 41, damping spring 43 is located in sleeve 421, sleeve 421
Side is provided with the fixed block 422 for fixed connecting rod 3.Sleeve 421 bottom is provided with the anchor tip 44 for fixing water tank 6.
The work process of the present embodiment：During depopulated helicopter landing, left foot frame 1 and right crus of diaphragm frame 2 touch ground first, fall
, so that impulsive force is released, impulsive force that fuselage is subject to reduces it is ensured that the pacifying of fuselage for impact compress damping spring 43 when falling
Entirely.
Above-described embodiment is preferably implementation of the present utility model, is not to restriction of the present utility model, not
On the premise of departing from inventive concept of the present utility model, any obvious replace all protection domain of the present utility model it
Interior.
Claims (8)
1. a kind of foot rest structure of depopulated helicopter, including the left foot frame being arranged symmetrically positioned at depopulated helicopter two bottom sides（1）
With right crus of diaphragm frame（2）It is characterised in that：Described left foot frame and right crus of diaphragm frame are in isosceles trapezoid shape by body bending, and left foot frame and
The bottom of right crus of diaphragm frame is enclosed construction, passes through connecting rod between left foot frame and right crus of diaphragm frame top（3）Connect, connecting rod is provided with and subtracts
Shake device（4）, amortisseur is connected with depopulated helicopter bottom.
2. depopulated helicopter according to claim 1 foot rest structure it is characterised in that：Described connecting rod（3）It is provided with two
Individual, each connecting rod is equipped with two amortisseurs（4）.
3. depopulated helicopter according to claim 2 foot rest structure it is characterised in that：Described amortisseur（4）Including solid
Determine mechanism（42）And fix bar（41）, fixed mechanism is fixed in connecting rod, and fix bar is connected with the bottom of depopulated helicopter, Gu
It is provided with damping spring between fixed pole and fixed mechanism（43）.
4. depopulated helicopter according to claim 3 foot rest structure it is characterised in that：Described fixed mechanism（42）Including
Sleeve（421）, damping spring is placed in fix bar, and damping spring is located in sleeve, and sleeve side is provided with for fixed connecting rod
Fixed block（422）.
5. depopulated helicopter according to claim 4 foot rest structure it is characterised in that：Described sleeve（421）Bottom sets
Have for fixing water tank（6）Anchor tip（44）.
6. depopulated helicopter according to claim 5 foot rest structure it is characterised in that：Described left foot frame（1）And right crus of diaphragm
Frame（2）The arrangement in " eight " shape.
7. depopulated helicopter according to claim 6 foot rest structure it is characterised in that：Described left foot frame（1）, right crus of diaphragm frame
（2）And connecting rod（3）It is integrated bending forming.
8. the depopulated helicopter according to any one of claim 2-7 foot rest structure it is characterised in that：Described left foot frame
（1）With right crus of diaphragm frame（2）Between two connecting rods（3）Between be provided with bracing piece（5）.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621002957.0U CN205971813U (en) | 2016-08-31 | 2016-08-31 | Foot rest structure of unmanned helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621002957.0U CN205971813U (en) | 2016-08-31 | 2016-08-31 | Foot rest structure of unmanned helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205971813U true CN205971813U (en) | 2017-02-22 |
Family
ID=58038698
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621002957.0U Expired - Fee Related CN205971813U (en) | 2016-08-31 | 2016-08-31 | Foot rest structure of unmanned helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205971813U (en) |
-
2016
- 2016-08-31 CN CN201621002957.0U patent/CN205971813U/en not_active Expired - Fee Related
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101973393A (en) | High-strength cage-type undercarriage of unmanned helicopter | |
| CN107571994B (en) | Aircraft | |
| CN107891972A (en) | Plant protection list rotor wing unmanned aerial vehicle drop resistant damping foot stool and plant protection list rotor wing unmanned aerial vehicle | |
| CN205971813U (en) | Foot rest structure of unmanned helicopter | |
| CN205971860U (en) | Spout water tank structure of unmanned helicopter of medicine | |
| CN206307266U (en) | A kind of multi-rotor unmanned aerial vehicle double damping undercarriage | |
| Lippisch | Man powered flight in 1929 | |
| CN204473119U (en) | Lightweight unmanned plane | |
| CN103523230A (en) | Landing assistant parachute of unmanned aerial vehicle | |
| CN207523932U (en) | Tandem wing tilting rotor wing unmanned aerial vehicle | |
| CN207637332U (en) | A kind of helicopter ground training device | |
| CN211336422U (en) | Unmanned helicopter with good stability | |
| CN204159032U (en) | A kind of ejection model airplane | |
| CN203601562U (en) | Boomerang quadrotor aircraft | |
| CN205602097U (en) | Unmanned plant protection machine shock attenuation undercarriage | |
| CN108438213A (en) | A kind of plant protection drone undercarriage bearing | |
| CN206766322U (en) | One kind uses the new-type racing machine frame of upper counterangle structure | |
| CN207595249U (en) | A kind of fixed-wing unmanned plane undercarriage of Simple detachable | |
| CN212530055U (en) | Unmanned aerial vehicle with novel undercarriage | |
| CN206278261U (en) | A kind of single-point hangs umbrella-type unmanned plane | |
| CN206334347U (en) | Step wing for ejection type soaring aeroplane model | |
| CN204473124U (en) | Without empennage unmanned plane | |
| CN205675236U (en) | A kind of course of new aircraft | |
| CN212797298U (en) | Centrifugal vertical lifting mechanism | |
| JP2926160B2 (en) | Model airplane |
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: 20170222 Termination date: 20190831 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |