CN105947188A - Rapid collecting device for undercarriage of unmanned aerial vehicle - Google Patents
Rapid collecting device for undercarriage of unmanned aerial vehicle Download PDFInfo
- Publication number
- CN105947188A CN105947188A CN201610419083.7A CN201610419083A CN105947188A CN 105947188 A CN105947188 A CN 105947188A CN 201610419083 A CN201610419083 A CN 201610419083A CN 105947188 A CN105947188 A CN 105947188A
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- CN
- China
- Prior art keywords
- unmanned plane
- base
- supporting plate
- steering wheel
- shaft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/24—Operating mechanisms electric
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Steering-Linkage Mechanisms And Four-Wheel Steering (AREA)
Abstract
The invention discloses a rapid collecting device for an undercarriage of an unmanned aerial vehicle. The rapid collecting device comprises a steering engine (2), a support plate (1) and a tube seat (5) hinged to the support plate (1), the tube seat (5) and the steering engine (2) are located on the same side of the support plate (1), an output shaft of the steering engine (2) penetrates through the support plate (1) and is in transmission connection with a rocker arm (3), the output shaft can control the rocker arm (3) to swing, a limiting shaft (11) penetrating through the support plate (1) is installed at the free end of the rocker arm (3), a sliding groove (8) for the limiting shaft (11) to pass through is formed in the support plate (1), and the rocker arm (3) is in transmission connection with the tube seat (5) so that the tube seat (5) can be controlled to rotate through the rocker arm (3). The rapid collecting device has the advantages that by arranging the limiting shaft, when the unmanned aerial vehicle lands, impact can be transmitted to the support plate through the limiting shaft, and the impact can be prevented from being transmitted to the steering engine so that the steering engine can be protected against damage, and the service life of the steering engine can be prolonged.
Description
Technical field
The present invention relates to unmanned plane accessory, specifically, be the quickly retracting device of a kind of unmanned plane undercarriage.
Background technology
UAV, is called for short unmanned plane, its have maneuverability, reaction quickly, unmanned flight, operation require low advantage.Unmanned plane is by carrying multiclass sensor, it is possible to achieve image real-time Transmission, high-risk areas detecting function, is that satellite remote sensing supplements with the strong of tradition air remote sensing.
At present, the main application fields of unmanned plane is to take photo by plane, and owing to undercarriage plays the effect of unmanned plane of supporting, the The Cloud Terrace of unmanned plane is mutually confidential to be realized 360 ° and take photo by plane, and will necessarily clap by undercarriage, affecting the most very much using effect, current solution is all gear up structure.The undercarriage control structure of unmanned plane uses screw rod steering wheel mostly at present, this makes unmanned plane undercarriage control the slowest, and part uses the undercarriage control structure of rocking arm steering wheel, but owing to lacking reasonably design so that steering wheel bears the biggest torsion when unmanned plane lands and damages steering wheel.
Summary of the invention
It is an object of the invention to provide a kind of simple in construction, easy to use, can reduce and steering wheel is impacted thus protect steering wheel to use the quickly retracting device of unmanned plane undercarriage of safety.
The present invention is achieved through the following technical solutions: the quickly retracting device of a kind of unmanned plane undercarriage, the supporting plate including steering wheel, being arranged on steering wheel output shaft side and the base being hinged on supporting plate, base and steering wheel are positioned at the same side of supporting plate, the output shaft of steering wheel is through supporting plate and is connected with rocking arm, output shaft can control rocking arm and swing; the free end of rocking arm is provided with the limit shaft through supporting plate; supporting plate is provided with the chute passed through for limit shaft, and rocking arm and base are in transmission connection so that controlling base by the rotation of rocking arm and rotating.
Described steering wheel is double output shaft steering wheel, and supporting plate has two, and limit shaft is each passed through two supporting plates.
The free end of described rocking arm is hinged with push-pull piece, and push-pull piece is hinged with base.
Described push-pull piece is provided with connecting shaft with the hinged place of base, and connecting shaft passes push-pull piece and base.
Described base is provided with rotating shaft with the hinged place of supporting plate, and rotating shaft passes base and supporting plate.
It is provided with the connecting plate for being connected with unmanned plane between two described supporting plates.
It is provided with through hole in described base, carbon fiber pipe is installed in through hole.
Described chute is arc chute, the center of circle of chute and the dead in line of steering wheel output shaft.
The present invention compared with prior art, has the following advantages and beneficial effect:
(1) present invention is by arranging limit shaft, it is possible to when unmanned plane lands, and by limit shaft, impact passes to supporting plate, thus avoids impact to pass to steering wheel, steering wheel can be protected not to be damaged with this, extends the service life of steering wheel；
(2) by using double output shaft steering wheel to be conducive to improving the bonding strength of the present invention and unmanned plane, and the balance of beneficially retentivity, it is to avoid the present invention is arranged on run-off the straight phenomenon on unmanned plane；
(3) present invention can increase the contact area of the present invention and unmanned plane by arranging connecting plate, thus the reduction present invention is to the pressure in the unit are of unmanned plane when unmanned plane lands, and can be to improve the bonding strength of the present invention and unmanned plane；
(4) present invention can play the effect of bumper and absorbing shock by being provided with carbon fiber pipe in through hole, thus reduce the impact that the present invention receives, and carbon fiber pipe has the advantages such as light weight, density is low, is conducive to alleviating the weight of whole device, it is to avoid unmanned plane affects flight because gravity is excessive.
Accompanying drawing explanation
Fig. 1 is the structural representation of the quickly retracting device of a kind of unmanned plane undercarriage；
Fig. 2 is the expansion schematic diagram of the quickly retracting device of a kind of unmanned plane undercarriage；
Fig. 3 is the structural representation of steering wheel；
Fig. 4 is the structural representation of base；
Wherein 1 supporting plate, 2 steering wheels, 3 rocking arms, 4 push-pull pieces, 5 bases, 6 rotating shafts, 7 connecting shafts, 8 chutes, 11 limit shafts.
Detailed description of the invention
Below in conjunction with embodiment, the present invention is described in further detail, but embodiments of the present invention are not limited to this.
Embodiment 1:
nullSuch as Fig. 1、Shown in shown in Fig. 2，In the present embodiment，A kind of quickly retracting device of unmanned plane undercarriage，Including steering wheel 2、The supporting plate 1 being arranged on steering wheel 2 output shaft side and the base 5 being hinged on supporting plate 1，Base 5 and supporting plate 1 are hinged by rotating shaft 6，Base 5 and steering wheel 2 are positioned at the same side of supporting plate 1，The output shaft of steering wheel 2 is through supporting plate 1 and is connected with rocking arm 3，Output shaft can control rocking arm 3 and swing，The free end of rocking arm 3 is provided with the limit shaft 11 through supporting plate 1，Supporting plate 1 is provided with the chute 8 passed through for limit shaft 11，Described chute 8 is arc chute，The center of circle of chute 8 and the dead in line of steering wheel 2 output shaft，With this it can be avoided that interfere when limit shaft 11 swings in chute 8，Rocking arm 3 is in transmission connection with base 5 so that controlling base 5 by the rotation of rocking arm 3 and rotating，The free end of rocking arm 3 is hinged with push-pull piece 4，As shown in Figure 3，Push-pull piece 4 and base 5 are hinged by connecting shaft 7.
Mounted in pairs of the present invention is below unmanned plane, by making supporting plate 1 be connected with unmanned plane, in order to auxiliary unmanned plane landing.During unmanned plane landing, control rocking arm 3 by steering wheel 2 to swing, thus drive push-pull piece 4 to rotate so that rotating out by base 5, the landing of unmanned plane is completed by making base 5 contact with ground, when rocking arm 3 swings, limit shaft 11 can be driven to swing in chute 8, when base 5 contacts with ground thus is impacted, impact passes to push-pull piece 4 by base 5, limit shaft 11 is passed to again by push-pull piece 4, owing to limit shaft 11 is limited in chute 8, therefore limit shaft 11 can just impact and pass to supporting plate 1, thus avoid impact to pass to steering wheel 2, the use safety of steering wheel 2 can be protected with this.
Embodiment 2:
As shown in Figure 1, Figure 3, on the basis of embodiment 1, in the present embodiment, described steering wheel 2 is double output shaft steering wheel, supporting plate 1 has two, limit shaft 11 is each passed through two supporting plates 1, by using two supporting plates 1 can improve the present invention and the bonding strength of unmanned plane, installation strength of the present invention and the stability of installation, and is conducive to making impulsive force disperse.
Embodiment 3:
On the basis of embodiment 2; in the present embodiment; it is provided with the connecting plate for being connected with unmanned plane between two described supporting plates 1; by using connecting plate to be connected with unmanned plane; the contact area of the present invention and unmanned plane can be increased such that it is able to the impact in the unit are that when reducing landing, unmanned plane is subject to, be conducive to protecting the safety of unmanned plane; and the bonding strength of the present invention and unmanned plane can be improved, be conducive to improving the rigidity that unmanned plane is overall.
Embodiment 4:
On the basis of embodiment 1, in the present embodiment, it is provided with through hole in described base 5, carbon fiber pipe is installed in through hole, the effect of bumper and absorbing shock can be played by being provided with carbon fiber pipe in through hole, thus reduce the impact that the present invention receives, and carbon fiber pipe has the advantages such as light weight, density is low, be conducive to alleviating the weight of whole device, it is to avoid unmanned plane affects flight because gravity is excessive.
Embodiment 5:
On the basis of embodiment 1, in the present embodiment, supporting plate 1, rocking arm 3, push-pull piece 4, base 5, rotating shaft 6, connecting shaft 7 and limit shaft 11 use light-high-strength composite to make, the quality being conducive to reducing the present invention under conditions of proof strength with this, described light-high-strength composite can select foamed aluminium, it is little that it has density, high-selenium corn impact capacity is strong, high temperature resistant, fire protecting performance is strong, anticorrosive, weatherability is strong, easily processing, easily install, forming accuracy is high and can carry out external coating, be conducive to alleviating the quality of the present invention, and there is the ability of buffering shock-absorbing.
The above, be only presently preferred embodiments of the present invention, and the present invention not does any pro forma restriction, every above example is made according to the technical spirit of the present invention any simple modification, equivalent variations, within each falling within protection scope of the present invention.
Claims (8)
1. the quickly retracting device of a unmanned plane undercarriage, it is characterized in that: include steering wheel (2), the supporting plate (1) being arranged on steering wheel (2) output shaft side and the base (5) being hinged on supporting plate (1), base (5) and steering wheel (2) are positioned at the same side of supporting plate (1), the output shaft of steering wheel (2) is through supporting plate (1) and is connected with rocking arm (3), output shaft can control rocking arm (3) and swing, the free end of rocking arm (3) is provided with the limit shaft (11) through supporting plate (1), supporting plate (1) is provided with the chute (8) passed through for limit shaft (11), rocking arm (3) and base (5) are in transmission connection so that controlling base (5) by the rotation of rocking arm (3) and rotating.
The quickly retracting device of a kind of unmanned plane undercarriage the most according to claim 1, it is characterised in that: described steering wheel (2) is double output shaft steering wheel, and supporting plate (1) has two, and limit shaft (11) is each passed through two supporting plates (1).
The quickly retracting device of a kind of unmanned plane undercarriage the most according to claim 1, it is characterised in that: the free end of described rocking arm (3) is hinged with push-pull piece (4), and push-pull piece (4) is hinged with base (5).
The quickly retracting device of a kind of unmanned plane undercarriage the most according to claim 3, it is characterised in that: described push-pull piece (4) is provided with connecting shaft (7) with the hinged place of base (5), and connecting shaft (7) is through push-pull piece (4) and base (5).
The quickly retracting device of a kind of unmanned plane undercarriage the most according to claim 4, it is characterised in that: described base (5) is provided with rotating shaft (6) with the hinged place of supporting plate (1), and rotating shaft (6) is through base (5) and supporting plate (1).
The quickly retracting device of a kind of unmanned plane undercarriage the most according to claim 2, it is characterised in that: it is provided with the connecting plate for being connected with unmanned plane between two described supporting plates (1).
The quickly retracting device of a kind of unmanned plane undercarriage the most according to claim 1, it is characterised in that: it is provided with through hole in described base (5), carbon fiber pipe is installed in through hole.
The quickly retracting device of a kind of unmanned plane undercarriage the most according to claim 1, it is characterised in that: described chute (8) is arc chute, the center of circle of chute (8) and the dead in line of steering wheel (2) output shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610419083.7A CN105947188A (en) | 2016-06-13 | 2016-06-13 | Rapid collecting device for undercarriage of unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610419083.7A CN105947188A (en) | 2016-06-13 | 2016-06-13 | Rapid collecting device for undercarriage of unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN105947188A true CN105947188A (en) | 2016-09-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610419083.7A Pending CN105947188A (en) | 2016-06-13 | 2016-06-13 | Rapid collecting device for undercarriage of unmanned aerial vehicle |
Country Status (1)
| Country | Link |
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| CN (1) | CN105947188A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107776891A (en) * | 2017-11-02 | 2018-03-09 | 赵郑益 | A kind of medical rescue aircraft |
| CN108177762A (en) * | 2017-12-22 | 2018-06-19 | 航天神舟飞行器有限公司 | A kind of Quick folding mechanism of multi-rotor unmanned aerial vehicle undercarriage |
| CN109573037A (en) * | 2019-01-24 | 2019-04-05 | 吉林大学 | A kind of power-line patrolling unmanned plane and patrolling method based on VR and multisensor |
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| WO2009146148A2 (en) * | 2008-04-04 | 2009-12-03 | Tactair Fluid Controls, Inc. | Locking mechanism with bi-modal actuator |
| CN103754356A (en) * | 2014-01-10 | 2014-04-30 | 江苏艾锐泰克无人飞行器科技有限公司 | Landing gear |
| CN203698652U (en) * | 2014-01-06 | 2014-07-09 | 江苏神谷无人飞行器技术有限公司 | Undercarriage of unmanned aerial vehicle |
| CN103963965A (en) * | 2014-02-26 | 2014-08-06 | 郑荣武 | Electric folding landing gear and control method thereof |
| CN104760690A (en) * | 2015-04-23 | 2015-07-08 | 零度智控（北京）智能科技有限公司 | Retractable landing gear of unmanned aircraft |
| CN104787308A (en) * | 2015-04-08 | 2015-07-22 | 零度智控（北京）智能科技有限公司 | Aircraft undercarriage driving device, aircraft undercarriage and aircraft |
| CN205661652U (en) * | 2016-06-13 | 2016-10-26 | 四川建筑职业技术学院 | Quick winding and unwinding devices of unmanned aerial vehicle undercarriage |
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2016
- 2016-06-13 CN CN201610419083.7A patent/CN105947188A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009146148A2 (en) * | 2008-04-04 | 2009-12-03 | Tactair Fluid Controls, Inc. | Locking mechanism with bi-modal actuator |
| CN203698652U (en) * | 2014-01-06 | 2014-07-09 | 江苏神谷无人飞行器技术有限公司 | Undercarriage of unmanned aerial vehicle |
| CN103754356A (en) * | 2014-01-10 | 2014-04-30 | 江苏艾锐泰克无人飞行器科技有限公司 | Landing gear |
| CN103963965A (en) * | 2014-02-26 | 2014-08-06 | 郑荣武 | Electric folding landing gear and control method thereof |
| CN104787308A (en) * | 2015-04-08 | 2015-07-22 | 零度智控（北京）智能科技有限公司 | Aircraft undercarriage driving device, aircraft undercarriage and aircraft |
| CN104760690A (en) * | 2015-04-23 | 2015-07-08 | 零度智控（北京）智能科技有限公司 | Retractable landing gear of unmanned aircraft |
| CN205661652U (en) * | 2016-06-13 | 2016-10-26 | 四川建筑职业技术学院 | Quick winding and unwinding devices of unmanned aerial vehicle undercarriage |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107776891A (en) * | 2017-11-02 | 2018-03-09 | 赵郑益 | A kind of medical rescue aircraft |
| CN108177762A (en) * | 2017-12-22 | 2018-06-19 | 航天神舟飞行器有限公司 | A kind of Quick folding mechanism of multi-rotor unmanned aerial vehicle undercarriage |
| CN108177762B (en) * | 2017-12-22 | 2021-06-04 | 航天神舟飞行器有限公司 | Quick folding mechanism of many rotor unmanned aerial vehicle undercarriage |
| CN109573037A (en) * | 2019-01-24 | 2019-04-05 | 吉林大学 | A kind of power-line patrolling unmanned plane and patrolling method based on VR and multisensor |
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| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
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| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160921 |