CN207617981U - A kind of multi-rotor unmanned aerial vehicle structured testing device based on reducing rack - Google Patents
A kind of multi-rotor unmanned aerial vehicle structured testing device based on reducing rack Download PDFInfo
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- CN207617981U CN207617981U CN201721767566.2U CN201721767566U CN207617981U CN 207617981 U CN207617981 U CN 207617981U CN 201721767566 U CN201721767566 U CN 201721767566U CN 207617981 U CN207617981 U CN 207617981U
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- shell
- pedestal
- fixedly connected
- groove
- aerial vehicle
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Abstract
The utility model discloses a kind of multi-rotor unmanned aerial vehicle structured testing device based on reducing rack, including pedestal and shell, shell is fixedly connected with the upper end of pedestal, cavity is equipped in pedestal, threaded rod is rotatably connected in cavity, worm gear has been fixedly and coaxially connected on threaded rod, the side of worm gear is equipped with the worm screw being engaged with, one end of worm screw and the side wall of cavity are rotatablely connected, the other end of worm screw is arranged through pedestal, the upper end of threaded rod extends in shell and is rotatablely connected with the madial wall of shell, threaded rod is located at the partial threads in shell and is connected with two pieces of movable blocks, the outside of shell is equipped with more motor mounting rods disposed in parallel, the both ends of motor mounting rod are mounted on propeller motor, multiple propeller blades are fixedly connected in the drive shaft of propeller motor.The utility model can test the rack radius of unmanned plane and the carry ability of unmanned plane, easy to operate, easy to use.
Description
Technical field
The utility model is related to air vehicle technique field more particularly to a kind of multi-rotor unmanned aerial vehicles based on reducing rack
Structured testing device.
Background technology
Multi-rotor unmanned aerial vehicle be a kind of tool there are three and the above rotor shaft special pilotless helicopter, by every
Motor on a axis drives rotor rotational, to generate a liter thrust.It, can be with by changing the relative rotation speed between different rotors
The size for changing uniaxial propulsive force, to control the running orbit of aircraft.Existing unmanned plane structured testing device can not root
According to needing the rack radius to unmanned plane to be adjusted, and the carry load-bearing capacity of unmanned plane can not be tested, to survey
Examination person brings inconvenience, in addition, unmanned plane often will appear the case where falling out of control in test, existing unmanned plane delays
The case where rushing that ability is poor, being easy to generate larger impact with ground when unmanned plane is born or landing, unmanned plane is caused to damage.
For this purpose, it is proposed that a kind of next multi-rotor unmanned aerial vehicle structured testing device based on reducing rack solves above-mentioned ask
Topic.
Utility model content
Purpose of the utility model is to solve the deficiencies of unmanned plane structured testing function in the prior art, and to nobody
The poor problem of the protective capability of machine, and a kind of multi-rotor unmanned aerial vehicle structured testing device based on reducing rack proposed.
To achieve the goals above, the utility model uses following technical solution：
A kind of multi-rotor unmanned aerial vehicle structured testing device based on reducing rack, including pedestal and shell, the shell
It is fixedly connected with the upper end of pedestal, cavity is equipped in the pedestal, threaded rod, the threaded rod are rotatably connected in the cavity
On be fixedly and coaxially connected worm gear, the side of the worm gear is equipped with the worm screw being engaged with, one end of the worm screw and cavity
Side wall is rotatablely connected, and the other end of the worm screw is arranged through pedestal, and the upper end of the threaded rod extends in shell and and shell
The madial wall of body is rotatablely connected, and the threaded rod is located at the partial threads in shell and is connected with two pieces of movable blocks, the shell
Outside is equipped with more motor mounting rods disposed in parallel, and the both ends of the motor mounting rod are mounted on propeller motor, described
Multiple propeller blades are fixedly connected in the drive shaft of propeller motor, the motor mounting rod is close to the side wall both sides of shell
It is rotatably connected to connecting rod, the one end of the connecting rod far from motor mounting rod is rotatably connected to link block, the link block
It is fixedly connected with the side wall of movable block, the side wall of the shell is equipped with fluting corresponding with link block, under the pedestal
Side four corners are equipped with the first groove, and column is slidably connected in first groove, and the lower end of the column is fixedly connected with
Supporting block, is fixedly connected with sliding bar in first groove, and the upper surface of the column is equipped with for accommodating sliding bar
Two grooves, are arranged with spring on the sliding bar, and the side wall of the both ends of the spring respectively with the first groove and column offsets
The lower face of contact, the pedestal is equipped with multiple counterweight tanks, is equipped with clump weight in the counterweight tank, the both sides of the counterweight tank are equal
Equipped with the position-limit mechanism for being limited to clump weight.
Preferably, one end that the worm screw is located at outside pedestal is fixedly connected with turning handle.
Preferably, the both ends of the column have been fixedly connected with sliding block, and the side wall of first groove is equipped with and sliding block
The sliding slot to match.
Preferably, the position-limit mechanism includes the second groove being arranged in base lower surface, is rotated in second groove
It is connected with shaft, the lower end of the shaft is fixedly connected with limiting plate.
Preferably, ratchet has been fixedly and coaxially connected in the shaft, the lower surface of the pedestal is rotatably connected to pawl, institute
Pawl is stated to abut with ratchet.
Compared with prior art, the beneficial effects of the utility model are：It, can be to motor by being threaded bar and rotating bar
The distance of mounting rod to shell is adjusted, and achievees the effect that change rack radius, convenient to test unmanned plane；By
Multiple counterweight tanks are set on pedestal, tester can be facilitated to be changed the weight of pedestal, the convenient carry energy to unmanned plane
Power is tested；By the way that spring and supporting block is arranged, the buffering effect of unmanned plane is improved, prevents unmanned plane in landing and ground
Fierce shock occurs；The utility model can test the rack radius of unmanned plane and the carry ability of unmanned plane, and
And there is preferable buffer capacity, avoid unmanned plane in landing by larger vibrations.
Description of the drawings
Fig. 1 be the utility model proposes a kind of multi-rotor unmanned aerial vehicle structured testing device based on reducing rack knot
Structure perspective view；
Fig. 2 is enlarged structure schematic diagram at the A in Fig. 1；
Fig. 3 is enlarged structure schematic diagram at the B in Fig. 1；
Fig. 4 be the utility model proposes a kind of multi-rotor unmanned aerial vehicle structured testing device based on reducing rack it is outer
Portion's structural schematic diagram.
In figure：1 pedestal, 2 shells, 3 threaded rods, 4 worm gears, 5 worm screws, 6 movable blocks, 7 mounting rods, 8 propeller motors, 9 spiral shells
Revolve paddle blade, 10 connecting rods, 11 link blocks, 12 columns, 13 supporting blocks, 14 sliding bars, 15 springs, 16 clump weights, 17 turning handles, 18
Sliding block, 19 shafts, 20 limiting plates, 21 ratchets, 22 pawls.
Specific implementation mode
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.
Referring to Fig.1-4, a kind of multi-rotor unmanned aerial vehicle structured testing device based on reducing rack, including pedestal 1 and shell
Body 2, shell 2 are fixedly connected with the upper end of pedestal 1, and cavity is equipped in pedestal 1, threaded rod 3, threaded rod are rotatably connected in cavity
Worm gear 4 is fixedly and coaxially connected on 3, the side of worm gear 4 is equipped with the worm screw 5 being engaged with, one end of worm screw 5 and the side wall of cavity
The other end of rotation connection, worm screw 5 is arranged through pedestal 1, it is worth mentioning at this point that, worm screw 5 is located at one end outside pedestal 1 and fixes company
It is connected to turning handle 17, the upper end of threaded rod 3 extends in shell 2 and is rotatablely connected with the madial wall of shell 2, and threaded rod 3 is located at shell
Partial threads in body 2 are connected with two pieces of movable blocks 6, and the outside of shell 2 is equipped with more motor mounting rods 7 disposed in parallel, electricity
The both ends of machine mounting rod 7 are mounted on propeller motor 8, and multiple propellers are fixedly connected in the drive shaft of propeller motor 8
Blade 9, motor mounting rod 7 are rotatably connected to connecting rod 10 close to the side wall both sides of shell 2, and connecting rod 10 is installed far from motor
One end of bar 7 is rotatably connected to link block 11, and link block 11 is fixedly connected with the side wall of movable block 6, and the side wall of shell 2 is equipped with
Fluting corresponding with link block 11.
In the utility model, the downside four corners of pedestal 1 are equipped with the first groove, and column is slidably connected in the first groove
12, specifically, the both ends of column 12 have been fixedly connected with sliding block 18, the side wall of the first groove is equipped with to match with sliding block 18
The lower end of sliding slot, column 12 is fixedly connected with supporting block 13, and sliding bar 14, the upper end of column 12 are fixedly connected in the first groove
Face is equipped with the second groove for accommodating sliding bar 14, is arranged with spring 15 on sliding bar 14, and the both ends of spring 15 are respectively with the
The side wall of one groove and column 12 abuts, and the lower face of pedestal 1 is equipped with multiple counterweight tanks, and clump weight is equipped in counterweight tank
16, the both sides of counterweight tank are equipped with the position-limit mechanism for being limited to clump weight 16, specifically, position-limit mechanism includes setting
The second groove in 1 lower surface of pedestal is rotatably connected to shaft 19 in the second groove, and the lower end of shaft 19 is fixedly connected with limit
Plate 20, and ratchet 21 has been fixedly and coaxially connected in shaft 19, the lower surface of pedestal 1 is rotatably connected to pawl 22, pawl 22 and spine
Wheel 21 abuts.
When the radius of rack is adjusted in the utility model, turning handle 17 need to be rotated, turning handle 17 drives worm screw 5 to rotate, snail
Bar 5 drives worm gear 4 to rotate, and worm gear 4 drives threaded rod 3 to rotate, and threaded rod 3 drives two movable blocks 6 to move in the opposite direction,
It is noted that the threaded hole on two movable blocks 6 is oppositely oriented, movable block 6 drives connecting rod 10 to rotate, 10 band of connecting rod
Dynamic mounting rod 7 moves, to achieve the effect that adjust rack radius；When the utility model needs to carry out carry heavy burden to unmanned plane
When test, clump weight 16 can be installed as needed, when installation, clump weight 16 is put into counterweight tank first, then by both sides
Limiting plate 20 turns to the lower section of clump weight 16, then by pawl 22 and 21 mutual clamping of ratchet.
The preferable specific implementation mode of the above, only the utility model, but the scope of protection of the utility model is not
Be confined to this, any one skilled in the art within the technical scope disclosed by the utility model, according to this practicality
Novel technical solution and its utility model design are subject to equivalent substitution or change, should all cover the protection model in the utility model
Within enclosing.
Claims (5)
1. a kind of multi-rotor unmanned aerial vehicle structured testing device based on reducing rack, including pedestal（1）And shell（2）, special
Sign is, the shell（2）With pedestal（1）Upper end be fixedly connected, the pedestal（1）It is interior to be equipped with cavity, turn in the cavity
It is dynamic to be connected with threaded rod（3）, the threaded rod（3）On be fixedly and coaxially connected worm gear（4）, the worm gear（4）Side be equipped with
The worm screw being engaged with（5）, the worm screw（5）One end and cavity side wall be rotatablely connected, the worm screw（5）The other end pass through
Wear pedestal（1）Setting, the threaded rod（3）Upper end extend to shell（2）Interior and and shell（2）Madial wall rotation connection,
The threaded rod（3）Positioned at shell（2）Interior partial threads are connected with two pieces of movable blocks（6）, the shell（2）Outside be equipped with
More motor mounting rods disposed in parallel（7）, the motor mounting rod（7）Both ends be mounted on propeller motor（8）, described
Propeller motor（8）Drive shaft on be fixedly connected with multiple propeller blades（9）, the motor mounting rod（7）Close to shell
（2）Side wall both sides be rotatably connected to connecting rod（10）, the connecting rod（10）Far from motor mounting rod（7）One end rotation
It is connected with link block（11）, the link block（11）With movable block（6）Side wall be fixedly connected, the shell（2）Side wall on
It is equipped with and link block（11）Corresponding fluting, the pedestal（1）Downside four corners be equipped with the first groove, described first is recessed
Column is slidably connected in slot（12）, the column（12）Lower end be fixedly connected with supporting block（13）, in first groove
It is fixedly connected with sliding bar（14）, the column（12）Upper surface be equipped with for accommodating sliding bar（14）The second groove, institute
State sliding bar（14）On be arranged with spring（15）, the spring（15）Both ends respectively with the first groove and column（12）Side
Wall abuts, the pedestal（1）Lower face be equipped with multiple counterweight tanks, clump weight is equipped in the counterweight tank（16）, described
The both sides of counterweight tank are equipped with for clump weight（16）The position-limit mechanism limited.
2. a kind of multi-rotor unmanned aerial vehicle structured testing device based on reducing rack according to claim 1, feature
It is, the worm screw（5）Positioned at pedestal（1）Outer one end is fixedly connected with turning handle（17）.
3. a kind of multi-rotor unmanned aerial vehicle structured testing device based on reducing rack according to claim 1, feature
It is, the column（12）Both ends be fixedly connected with sliding block（18）, the side wall of first groove is equipped with and sliding block
（18）The sliding slot to match.
4. a kind of multi-rotor unmanned aerial vehicle structured testing device based on reducing rack according to claim 1, feature
It is, the position-limit mechanism includes being arranged in pedestal（1）Second groove of lower surface is rotatably connected in second groove
Axis（19）, the shaft（19）Lower end be fixedly connected with limiting plate（20）.
5. a kind of multi-rotor unmanned aerial vehicle structured testing device based on reducing rack according to claim 4, feature
It is, the shaft（19）On be fixedly and coaxially connected ratchet（21）, the pedestal（1）Lower surface be rotatably connected to pawl
（22）, the pawl（22）With ratchet（21）It abuts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721767566.2U CN207617981U (en) | 2017-12-18 | 2017-12-18 | A kind of multi-rotor unmanned aerial vehicle structured testing device based on reducing rack |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721767566.2U CN207617981U (en) | 2017-12-18 | 2017-12-18 | A kind of multi-rotor unmanned aerial vehicle structured testing device based on reducing rack |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207617981U true CN207617981U (en) | 2018-07-17 |
Family
ID=62821438
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721767566.2U Expired - Fee Related CN207617981U (en) | 2017-12-18 | 2017-12-18 | A kind of multi-rotor unmanned aerial vehicle structured testing device based on reducing rack |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207617981U (en) |
-
2017
- 2017-12-18 CN CN201721767566.2U patent/CN207617981U/en not_active Expired - Fee Related
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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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180717 Termination date: 20201218 |