CN109383776A - H.D unmanned plane is determined with air pressure - Google Patents
H.D unmanned plane is determined with air pressure Download PDFInfo
- Publication number
- CN109383776A CN109383776A CN201710651716.1A CN201710651716A CN109383776A CN 109383776 A CN109383776 A CN 109383776A CN 201710651716 A CN201710651716 A CN 201710651716A CN 109383776 A CN109383776 A CN 109383776A
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- CN
- China
- Prior art keywords
- cantilever
- air pressure
- unmanned plane
- locking level
- locking
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- 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.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/006—Safety devices
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses one kind, and there is air pressure to determine H.D unmanned plane, it is related to four-axle aircraft, when shooting for solving unmanned plane, the variation of air pressure will cause several upward or downward meters of sideslips of aircraft, and the duration is longer, or the height inaccuracy that earth station shows, occur negative altitude once in a while, the problem for causing to survey and draw landform inaccuracy.It includes flight rack, the flight rack includes cantilever design, helical-blade, Ding Gaomo group, the Ding Gaomo group includes locking level, locking frame, fixed high module, and locking level is respectively set in described four angles of locking frame, and cantilever design is inserted into the locking level lower end respectively.The technical program has accurate fixed height, can improve the accuracy of mapping landform.
Description
Technical field
The present invention relates to four-axle aircrafts, are to determine H.D unmanned plane with air pressure specifically.
Background technique
Personnel are carried using manned helicopter and equipment is shot, risk is big, costly.In recent years, start benefit occur
It is shot with small drone Portable device, staff can carry out according to the video information remote control holder of its passback
Shooting.
But prior art has the following disadvantages, when unmanned plane is shot, the variation of air pressure will cause winged
, there is negative height once in a while in several upward or downward meters of sideslips of row device, and the height inaccuracy that the duration is longer or earth station shows
Degree, the problem for causing to survey and draw landform inaccuracy.
Summary of the invention
Object of the present invention is to be intended to provide accurate fixed height, accurately there is mapping landform air pressure to determine H.D unmanned plane.
To realize the above-mentioned technical purpose, The technical solution adopted by the invention is as follows:
H.D unmanned plane, including flight rack are determined with air pressure, and the flight rack includes cantilever design, spiral
Leaf, Ding Gaomo group, the Ding Gaomo group include locking level, locking frame, fixed high module, and lock is respectively set in described four angles of locking frame
Cantilever design is inserted into fixed pole, the locking level lower end respectively.
It further limits, the cantilever design is made of the first cantilever and the second cantilever, and first cantilever and second hangs
The distribution of arm across, the first cantilever central axis two sides are equipped with the first circular hole for being inserted into locking level, and described first is outstanding
Helical-blade is respectively set far from Ding Gaomo group both ends in arm, and the second cantilever central axis two sides are equipped with for being inserted into locking level
Helical-blade is respectively set far from Ding Gaomo group both ends in one circular hole, second cantilever.
It further limits, the first cantilever central axis is equipped with the first groove, and the second cantilever central axis is equipped with second
Groove.
It further limits, the cantilever design bottom is equipped with the mounting plate for connecting holder.
It further limits, the mounting plate is built-in with the power supply for giving high module for power supply.
It further limits, the cantilever design two sides are symmetrically arranged with landing stabilizer blade.
It further limits, the cantilever design is equipped with location structure, and the location structure includes upper positioning plate and lower fixed
Position plate, the cantilever design central axis top connect upper positioning plate, and central shaft bottom connects lower positioning plate.
It further limits, the locking frame inner surface is equipped with neonychium towards fixed high module side.
The present invention compared with prior art, first, utilize locking level and locking frame cooperate, especially, lock frame in table
It is equipped with neonychium facing towards surely high module side, avoids hitting and surely high module is caused to destroy, second, locking four angles of frame are respectively set
Locking level is tilted using the high module corner of the anti-fastening of locking level, and the variation of such air pressure not will cause aircraft upward or downward
Several meters of sideslips improve and determine the accuracy of high measurement, third, the first cantilever with the first groove, and second with the second groove
Cantilever after assembling, improves the stability of device entirety, and installing and dismounting, which carries, to be more convenient, and the fixed high state of flight of air pressure is reached.
Detailed description of the invention
The present invention can be further illustrated by the nonlimiting examples that attached drawing provides；
Fig. 1 is that there is the present invention air pressure to determine H.D unmanned plane perspective view；
Fig. 2 is Ding Gaomo group schematic diagram of the present invention；
Fig. 3 is four axis unmanned plane during flying principles of the invention；
Main element symbol description is as follows:
Cantilever design 1, helical-blade 2, locking level 3, locking frame 4, fixed high module 5, the first cantilever 6, the second cantilever 7, first
Circular hole 8, the second circular hole 9, the first groove 10, the second groove 11, mounting plate 12 land stabilizer blade 13, upper positioning plate 14, lower positioning plate
15。
Specific embodiment
In order to make those skilled in the art that the present invention may be better understood, with reference to the accompanying drawings and examples to this hair
Bright technical solution further illustrates.
Embodiment one,
As shown in Fig.1 and Fig.2, there is air pressure to determine H.D unmanned plane, including flight rack, flight rack include cantilever
Structure 1, helical-blade 2, Ding Gaomo group, Ding Gaomo group include locking level 3, locking frame 4, fixed high module 5, locking 4 four angles of frame point
Not She Zhi locking level 3, cantilever design 1 is inserted into 3 lower end of locking level respectively.
Cantilever design 1 is made of the first cantilever 6 and the second cantilever 7, the first cantilever 6 and the distribution of 7 across of the second cantilever,
First cantilever, 6 central axis two sides are equipped with the first circular hole 8 for being inserted into locking level 3, and the first cantilever 6 is far from Ding Gaomo group both ends point
Not She Zhi helical-blade 2,7 central axis two sides of the second cantilever are equipped with the second circular hole 9 for being inserted into locking level 3, and the second cantilever 7 is separate
Helical-blade 2 is respectively set in Ding Gaomo group both ends.
First cantilever, 6 central axis is equipped with the first groove 10, and 7 central axis of the second cantilever is equipped with the second groove 11.
1 bottom of cantilever design is equipped with the mounting plate 12 for connecting holder.
Mounting plate 12 is built-in with the power supply powered for giving high module 5.
Embodiment two,
As shown in Fig.1 and Fig.2, there is air pressure to determine H.D unmanned plane, including flight rack, flight rack include cantilever
Structure 1, helical-blade 2, Ding Gaomo group, Ding Gaomo group include locking level 3, locking frame 4, fixed high module 5, locking 4 four angles of frame point
Not She Zhi locking level 3, cantilever design 1 is inserted into 3 lower end of locking level respectively.
Cantilever design 1 is made of the first cantilever 6 and the second cantilever 7, the first cantilever 6 and the distribution of 7 across of the second cantilever,
First cantilever, 6 central axis two sides are equipped with the first circular hole 8 for being inserted into locking level 3, and the first cantilever 6 is far from Ding Gaomo group both ends point
Not She Zhi helical-blade 2,7 central axis two sides of the second cantilever are equipped with the second circular hole 9 for being inserted into locking level 3, and the second cantilever 7 is separate
Helical-blade 2 is respectively set in Ding Gaomo group both ends.
First cantilever, 6 central axis is equipped with the first groove 10, and 7 central axis of the second cantilever is equipped with the second groove 11.
1 bottom of cantilever design is equipped with the mounting plate 12 for connecting holder.
Mounting plate 12 is built-in with the power supply powered for giving high module 5.
1 two sides of cantilever design are symmetrically arranged with landing stabilizer blade 13.
Cantilever design 1 is equipped with location structure, and location structure includes upper positioning plate 14 and lower positioning plate 15, cantilever design 1
Upper positioning plate 14 is connected at the top of central axis, central shaft bottom connects lower positioning plate 15.
It locks 4 inner surface of frame and is equipped with neonychium towards fixed high 5 side of module.
The difference of embodiment one and embodiment two is, for opposite embodiment one, in embodiment two, locks frame inner surface
It is equipped with neonychium towards fixed high module side, prevents from hitting and surely high module is caused to destroy.
| Flight rack battery | 7000mAh | Lithium battery |
| Flight rack weight | 1150g | |
| The fixed high hovering precision of air pressure | 92~98% | |
| Maximum rise/fall speed | Rise: 6.1~8.2m/s | Decline: 1.7~2.3m/s |
| Cantilever design wheelbase | 400mm |
As shown in figure 3, four axis unmanned plane during flying principles are as follows,
A. turn right flight: two groups of the front and back power (being generated by turning to rub to beat counterclockwise) that turns rubbed and beaten that turns right is greater than and turns left to rub and spin
Power (is generated) by turning to rub to beat clockwise, can enable fuselage that will turn right；Operation principles in the middle are, when turn beaten that rub counterclockwise
When speed rises, the revolving speed beaten that rubs clockwise declines, rotor counterclockwise is greater than the reaction torque (Anti-torque) of fuselage clockwise
Rotor is to the reaction torque of fuselage, then fuselage just rotates clockwise under the mechanics of reaction torque.
B. straight forward: when two rub clockwise beat turn power it is consistent when, unmanned plane body will rise.When wherein one group
When the power beaten and turned to counterclockwise that rubs is greater than another group, body can be pushed to the weaker side of strength, realize rectilinear flight.
C. to left: principle is with forward, only direction is not.
D. hover in midair: four groups are rubbed to beat and fight force of gravity with constant speed rotation, and realization is hovered effect in midair.
Barometric surveying elevation principle
Working principle is that input signal (pressure) is converted to resistance variations, that is, passes through the pressure resistance type of Wheatstone bridge framework
Pressure sensor incudes the pressure being applied in thin membrane.To provided by the invention there is air pressure to determine H.D unmanned plane above
It is described in detail.The explanation of specific embodiment is merely used to help understand method and its core concept of the invention.It should
It points out, it for those skilled in the art, without departing from the principle of the present invention, can also be to this hair
Bright some improvement and modification can also be carried out, and these improvements and modifications also fall within the scope of protection of the claims of the present invention.
Claims (8)
1. having air pressure to determine H.D unmanned plane, including flight rack, it is characterised in that: the flight rack includes cantilever knot
Structure, helical-blade, Ding Gaomo group, the Ding Gaomo group include locking level, locking frame, fixed high module, described four angles of locking frame point
Not She Zhi locking level, cantilever design is inserted into the locking level lower end respectively.
2. according to claim 1 there is air pressure to determine H.D unmanned plane, it is characterised in that: the cantilever design is by the
One cantilever and the second cantilever are constituted, first cantilever and the distribution of the second cantilever across, the first cantilever central axis two
Side is equipped with the first circular hole for being inserted into locking level, and helical-blade is respectively set far from Ding Gaomo group both ends in first cantilever, institute
The second cantilever central axis two sides are stated equipped with the first circular hole for being inserted into locking level, second cantilever is far from Ding Gaomo group both ends
Helical-blade is respectively set.
3. according to claim 1 or 2 there is air pressure to determine H.D unmanned plane, it is characterised in that: first cantilever
Central axis is equipped with the first groove, and the second cantilever central axis is equipped with the second groove.
4. according to claim 3 there is air pressure to determine H.D unmanned plane, it is characterised in that: the cantilever design bottom
Equipped with the mounting plate for connecting holder.
5. according to claim 4 there is air pressure to determine H.D unmanned plane, it is characterised in that: the mounting plate is built-in with
For giving the power supply of high module for power supply.
6. according to claim 5 there is air pressure to determine H.D unmanned plane, it is characterised in that: the cantilever design two sides
It is symmetrically arranged with landing stabilizer blade.
7. according to claim 6 there is air pressure to determine H.D unmanned plane, it is characterised in that: set in the cantilever design
There is location structure, the location structure includes upper positioning plate and lower positioning plate, is determined in connection at the top of the cantilever design central axis
Position plate, central shaft bottom connect lower positioning plate.
8. according to claim 7 there is air pressure to determine H.D unmanned plane, it is characterised in that: the locking frame inner surface
Neonychium is equipped with towards fixed high module side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710651716.1A CN109383776A (en) | 2017-08-02 | 2017-08-02 | H.D unmanned plane is determined with air pressure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710651716.1A CN109383776A (en) | 2017-08-02 | 2017-08-02 | H.D unmanned plane is determined with air pressure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109383776A true CN109383776A (en) | 2019-02-26 |
Family
ID=65412507
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710651716.1A Pending CN109383776A (en) | 2017-08-02 | 2017-08-02 | H.D unmanned plane is determined with air pressure |
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| Country | Link |
|---|---|
| CN (1) | CN109383776A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102381471A (en) * | 2010-09-02 | 2012-03-21 | 梦想空间世界有限公司 | Unmanned flying vehicle made with PCB |
| CN103640696A (en) * | 2013-12-05 | 2014-03-19 | 新誉集团有限公司 | Vertical touchdown type unmanned aerial vehicle and control method thereof |
| CN205060006U (en) * | 2015-09-24 | 2016-03-02 | 广州地理研究所 | Four -rotor unmanned aerial vehicle |
| CN106081084A (en) * | 2016-07-11 | 2016-11-09 | 南京航空航天大学 | A kind of spherical unmanned plane of portable and collapsible |
| CN205707333U (en) * | 2016-05-27 | 2016-11-23 | 深圳市汇金智能科技有限公司 | A kind of four-axle aircraft |
| CN106477032A (en) * | 2016-09-11 | 2017-03-08 | 珠海市磐石电子科技有限公司 | Multi-axis aircraft |
| CN206107559U (en) * | 2016-10-20 | 2017-04-19 | 河海大学 | Unmanned vehicles based on sharp infrared ray sensor decides highly |
-
2017
- 2017-08-02 CN CN201710651716.1A patent/CN109383776A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102381471A (en) * | 2010-09-02 | 2012-03-21 | 梦想空间世界有限公司 | Unmanned flying vehicle made with PCB |
| CN103640696A (en) * | 2013-12-05 | 2014-03-19 | 新誉集团有限公司 | Vertical touchdown type unmanned aerial vehicle and control method thereof |
| CN205060006U (en) * | 2015-09-24 | 2016-03-02 | 广州地理研究所 | Four -rotor unmanned aerial vehicle |
| CN205707333U (en) * | 2016-05-27 | 2016-11-23 | 深圳市汇金智能科技有限公司 | A kind of four-axle aircraft |
| CN106081084A (en) * | 2016-07-11 | 2016-11-09 | 南京航空航天大学 | A kind of spherical unmanned plane of portable and collapsible |
| CN106477032A (en) * | 2016-09-11 | 2017-03-08 | 珠海市磐石电子科技有限公司 | Multi-axis aircraft |
| CN206107559U (en) * | 2016-10-20 | 2017-04-19 | 河海大学 | Unmanned vehicles based on sharp infrared ray sensor decides highly |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190226 |
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| RJ01 | Rejection of invention patent application after publication |