CN106005356B - A kind of aircraft and its signal wire protect component - Google Patents
A kind of aircraft and its signal wire protect component Download PDFInfo
- Publication number
- CN106005356B CN106005356B CN201610415566.XA CN201610415566A CN106005356B CN 106005356 B CN106005356 B CN 106005356B CN 201610415566 A CN201610415566 A CN 201610415566A CN 106005356 B CN106005356 B CN 106005356B
- Authority
- CN
- China
- Prior art keywords
- foot prop
- signal wire
- sleeve pipe
- protection sleeve
- electricity
- 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
- 238000005183 dynamical system Methods 0.000 claims abstract description 16
- 230000005611 electricity Effects 0.000 claims description 34
- 239000003292 glue Substances 0.000 claims description 9
- 238000013016 damping Methods 0.000 claims description 3
- 230000003139 buffering effect Effects 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 2
- 238000005194 fractionation Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
-
- 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
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02G—INSTALLATION OF ELECTRIC CABLES OR LINES, OR OF COMBINED OPTICAL AND ELECTRIC CABLES OR LINES
- H02G3/00—Installations of electric cables or lines or protective tubing therefor in or on buildings, equivalent structures or vehicles
- H02G3/02—Details
- H02G3/04—Protective tubing or conduits, e.g. cable ladders or cable troughs
- H02G3/0462—Tubings, i.e. having a closed section
- H02G3/0481—Tubings, i.e. having a closed section with a circular cross-section
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Architecture (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Casings For Electric Apparatus (AREA)
- Earth Drilling (AREA)
Abstract
The invention discloses a kind of aircraft and its signal wire to protect component.It includes foot prop and protection sleeve pipe that signal wire, which protects component; foot prop includes foot prop casing; the foot prop casing includes carrying platform and holding part; the one side of the carrying platform is used to carry the dynamical system of driving rotor; the holding part is arranged in another side, and the holding part is for accommodating and fixing the protection sleeve pipe.At least part of protection sleeve pipe is contained in foot prop casing, and protection sleeve pipe prevents damage of the signal wire by external environment, for accommodating signal wire so as to which signal wire is effectively protected.
Description
The application is that international application no is PCT/CN2014/080845, and international filing date is on June 26th, 2014, is entered
National Phase in China application No. is 201480002728.6, the hair of entitled " a kind of aircraft and its signal wire protect component "
The divisional application of bright patent application.
Technical field
The present invention relates to unmanned vehicle fields, protect component more particularly, to a kind of aircraft and its signal wire.
Background technique
Before unmanned vehicle takes off, aircraft makes aircraft standing support by foot prop.When aircraft landing, foot prop
Aircraft stops flight behind ground.The elements such as dynamical system, electricity tune usually can be also installed on foot prop, therefore have many signals
Line, the prior art are usually that signal wire is arranged outside foot prop, this will make signal wire be easy to the damage by external environment
It is bad.
Summary of the invention
The invention mainly solves the technical problem of providing a kind of aircraft and its signal wire to protect component, can solve letter
Number line is easy the problem of damage by external environment.
In order to solve the above technical problems, one technical scheme adopted by the invention is that：A kind of signal wire of aircraft is provided
Component is protected, the signal wire protection component includes foot prop and protection sleeve pipe, and the foot prop includes foot prop casing, the protective case
At least part of pipe is contained in the foot prop casing, and the protection sleeve pipe prevents the signal wire for accommodating signal wire
Damage by external environment；The foot prop casing includes carrying platform and holding part, and the one side of the carrying platform is used for
The holding part is arranged in the dynamical system of carrying driving rotor, another side, and the holding part is for accommodating and fixing the guarantor
Protecting pipe.
Wherein, the position that the protection sleeve pipe is contacted with the holding part is provided with glue, to pass through the glue into one
The fixed protection sleeve pipe of step.
Wherein, the foot prop is at least two, and the both ends of the protection sleeve pipe are respectively accommodated in the foot of two foot props
In frame casing.
Wherein, line-entering hole is provided in the protection sleeve pipe, the carrying platform of two foot prop casings is respectively in correspondence
The position at the both ends of the protection sleeve pipe is provided with outlet hole, and the signal wire enters the protection sleeve pipe from the line-entering hole
It is interior, it is further pierced by from the outlet hole into the dynamical system after the end of the protection sleeve pipe is pierced by.
Wherein, the aircraft include frame main body, from outwardly extending at least two adjutage of the frame main body with
And the vertically extending bracket of extending direction with the adjutage；The bracket is the protection sleeve pipe；The line-entering hole setting
In the bracket of the aircraft and the junction of adjutage.
Wherein, the holding part at least two, is separately positioned on the both ends of the another side of the carrying platform；Institute
State protection sleeve pipe both ends extended through from the holding part of foot prop casing one end respectively it is another to the foot prop casing
The holding part at end.
Wherein, the electricity that the electricity that the foot prop is additionally provided with the receiving aircraft is adjusted adjusts storehouse.
Wherein, the carrying platform setting of the foot prop casing is adjusted on storehouse in the electricity, and the accommodating of the foot prop casing
Portion is contained in the electricity and adjusts in storehouse, so that the protection sleeve pipe is contained in the electricity and adjusts in storehouse.
Wherein, the foot prop further comprises foot prop lower cover and buffer, and one end of the foot prop lower cover and the electricity are adjusted
The one end in storehouse connects, and is located at the lower section that the electricity adjusts storehouse, and the buffer is connected to the electricity and adjusts the other end in storehouse and described
Between the other end of foot prop lower cover, and storehouse and the foot prop lower cover is adjusted to form triangular structure with the electricity.
Wherein, the buffer is hydraulic damping buffer.
Wherein, an antenna cavity is set on lid under the foot prop, for accommodating the antenna of receivable external signal, to prevent
State damage of the antenna by external environment.
Wherein, the antenna includes that figure passes antenna.
Wherein, the signal wire includes the data line of data line and power supply line and the antenna that the electricity is adjusted.
In order to solve the above technical problems, another technical solution used in the present invention is：A kind of aircraft is provided, the flight
Device includes dynamical system and above-mentioned signal wire protection component.
Wherein, the aircraft further includes frame main body, from outwardly extending at least two adjutage of the frame main body
And the vertically extending bracket of extending direction with the adjutage；Rotor, rotor is respectively set at the both ends of the bracket
Dynamical system and the foot prop.
Wherein, the bracket is the protection sleeve pipe；
Alternatively, the protection sleeve pipe can be accommodated by the bracket and foot prop casing completely.
The beneficial effects of the invention are as follows：It is in contrast to the prior art, the present invention accommodates at least portion by foot prop casing
The dynamical system of code insurance protecting pipe and carrying driving rotor, further accommodates signal wire by protection sleeve pipe, thus by signal
Line is arranged in foot prop inside pipe casing, it is therefore prevented that damage of the signal wire by external environment effectively protects signal wire.
Detailed description of the invention
Fig. 1 is a kind of structural schematic diagram of aircraft provided in an embodiment of the present invention；
Fig. 2 is the fractionation structural representation of foot prop shown in FIG. 1；
Fig. 3 is the main view of signal wire protection component shown in FIG. 1；
Fig. 4 is cross-sectional view of the signal wire protection component shown in Fig. 3 along EF line.
Specific embodiment
It is a kind of structural schematic diagram of aircraft provided in an embodiment of the present invention also referring to Fig. 1-Fig. 4, Fig. 1, Fig. 2 is
The fractionation structural representation of foot prop shown in FIG. 1, Fig. 3 are the main views of signal wire protection component shown in FIG. 1, and Fig. 4 is Fig. 3 institute
Cross-sectional view of the signal wire protection component shown along EF line.First as shown in Figure 1, aircraft 10 of the invention includes frame main body
11, from outwardly extending at least two adjutage 12 of frame main body 11 and with the vertically extending branch of extending direction of adjutage 12
Frame 13, wherein rotor 14, the dynamical system 15 of rotor and foot prop 16 is respectively set at the both ends of bracket 13.
In the present embodiment, bracket 13 and foot prop 16 have been combined into the signal wire protection component 136 of aircraft 10.That is bracket 13
It is again protection sleeve pipe 131, is preferably carbon pipe, for accommodating signal wire 100.
Specifically, referring to Figure 2 together -4, foot prop 16 includes foot prop casing 161, it is used to carry rotor 14 and drives
The dynamical system 15 of dynamic rotor 14, protection sleeve pipe 131 are partially housed in foot prop casing 161, and protection sleeve pipe 131 is for accommodating letter
Number line 100, prevents signal wire 100 by the damage of external environment.Wherein, signal wire 100 is used for transmission driving signal to power
In system 15.
As a result, in the present embodiment, since signal wire 100 to be contained in protection sleeve pipe 131, it can effectively protect signal
Line, and space may further be saved.
In other embodiments, in addition protection sleeve pipe 131 can also be set, it can be completely by bracket 13 and foot prop casing
161 receivings.
In the present embodiment, foot prop casing 161 includes carrying platform 162 and holding part 163, the one side of carrying platform 162
For carrying rotor 14 and dynamical system 15, holding part 163 is arranged in another side, and holding part 163 is for accommodating and fixing guarantor
Protecting pipe 131.Wherein, in order to enhance fixed effect, holding part 163 at least two is separately positioned on carrying platform 162
The both ends of another side.
Further, the position that protection sleeve pipe 131 is contacted with holding part 163 is provided with glue, with further by glue
Fixed protection sleeve pipe 131.The present embodiment is also provided with glue on the another side of carrying platform 162, can reinforce to protection
The fixed function of casing 131.The present embodiment is fixed protection sleeve pipe 131 by holding part 163 and glue, and method is simple,
And it avoids the prior art and uses the big problems of fixed forms bring weight such as screw.
Referring again to Fig. 1, the present embodiment is quadrotor, thus includes two brackets 13 and is separately positioned on two
Four foot props 16 of 13 end of bracket.For ease illustration and understanding, the present embodiment is only to a bracket 13 corresponding with its two
The signal wire protection component that a foot prop 16 forms is illustrated.Fig. 2-4 is please referred to, the both ends of protection sleeve pipe 131 are received respectively
It is dissolved in the foot prop casing 161 of two foot props 16, specifically, the both ends of protection sleeve pipe 131 are respectively from 161 one end of foot prop casing
Holding part 163 in extend through the holding part 163 of 161 other end of foot prop casing.
Line-entering hole 200 is provided in protection sleeve pipe 131, the carrying platform 162 of two foot prop casings 161 is protected corresponding respectively
The position at the both ends of protecting pipe 131 is provided with outlet hole 300, and signal wire 100 enters in protection sleeve pipe 131 from line-entering hole 200,
It is further pierced by from outlet hole 300 into dynamical system 15 after the end of protection sleeve pipe 131 is pierced by.
It should be understood that the line-entering hole 200 of protection sleeve pipe 131 is preferably provided at bracket 13 and adjutage 12 according to Fig. 1
Junction.
The electricity that the foot prop 16 of the present embodiment is additionally provided with receiving aircraft 10 adjusts 165 electricity to adjust storehouse 164, wherein electricity adjusts 165
It is adjusted the speed by motor of the voltage to dynamical system 15.The setting of carrying platform 162 of foot prop casing 161 is adjusted on storehouse 164 in electricity,
And the holding part 163 of foot prop casing 161 is contained in electricity and adjusts in storehouse 164, so that protection sleeve pipe 131 is contained in electricity and adjusts in storehouse 164.
It is possible thereby to save volume.
Foot prop 16 further comprises foot prop lower cover 166, and one end of foot prop lower cover 166 adjusts the one end in storehouse 164 to connect with electricity, and
The lower section that storehouse 164 is adjusted positioned at electricity, is arranged an antenna cavity 167, for accommodating the day of receivable external signal on foot prop lower cover 166
Line, to prevent damage of the antenna by external environment, to effectively protect antenna.Wherein, antenna includes that figure passes antenna.
Wherein, the signal wire 100 of the present embodiment includes that electricity adjusts 165 power supply line and the data of data line and control antenna
Line.Specifically, what protection sleeve pipe 131 accommodated is that electricity adjusts 165 power supply line and the data line of data line and control antenna.
Foot prop 16 further includes a buffer 168, be connected to electricity adjust storehouse 164 the other end and foot prop lower cover 166 it is another
Between end, and triangular structure is formed therewith.Specifically, adjusting the other end in storehouse 164 to be provided with a fixed part 1641 in electricity, in foot
The other end of frame lower cover 166 is provided with another fixing end 1661, and the both ends of buffer 168 are plugged in fixed part 1641 respectively and consolidate
In the cannula structure for determining portion 1661.Preferably, buffer 168 is hydraulic damping buffer.
In conclusion the present invention is by the way that signal wire and antenna to be respectively accommodated in protection sleeve pipe and antenna cavity, effectively
Protect signal wire and antenna.
Further, the present invention effectively alleviates the weight of aircraft by the fixed protection sleeve pipe of glue and foot prop casing
Amount.
The above description is only an embodiment of the present invention, is not intended to limit the scope of the invention, all to utilize this hair
Equivalent structure or equivalent flow shift made by bright specification and accompanying drawing content is applied directly or indirectly in other relevant skills
Art field, is included within the scope of the present invention.
Claims (15)
1. a kind of signal wire of aircraft protects component, which is characterized in that the signal wire protection component includes foot prop and protection
Casing, the foot prop include foot prop casing, and at least part of the protection sleeve pipe is contained in the foot prop casing, the guarantor
Protecting pipe prevents the signal wire by the damage of external environment for accommodating signal wire；The foot prop casing includes that carrying is flat
Platform and holding part, the one side of the carrying platform are used to carry the dynamical system of driving rotor, and the appearance is arranged in another side
Portion is set, the holding part is for accommodating and fixing the protection sleeve pipe；The foot prop is additionally provided with the electricity for accommodating the aircraft
The electricity of tune adjusts storehouse, and the signal wire includes the power supply line that the electricity is adjusted.
2. signal wire according to claim 1 protects component, which is characterized in that the protection sleeve pipe connects with the holding part
The position of touching is provided with glue, to further fix the protection sleeve pipe by the glue.
3. signal wire according to claim 1 protects component, which is characterized in that the foot prop is at least two, the guarantor
The both ends of protecting pipe are respectively accommodated in the foot prop casing of two foot props.
4. signal wire according to claim 3 protects component, which is characterized in that be provided in the protection sleeve pipe into line
Hole, the carrying platform of two foot prop casings are provided with outlet in the position at the both ends of the correspondence protection sleeve pipe respectively
Hole, the signal wire enter in the protection sleeve pipe from the line-entering hole, after the end of the protection sleeve pipe is pierced by further
It is pierced by from the outlet hole into the dynamical system.
5. signal wire according to claim 4 protects component, which is characterized in that the aircraft include frame main body, from
Outwardly extending at least two adjutage of the frame main body and the vertically extending bracket of extending direction with the adjutage；
The bracket is the protection sleeve pipe；The bracket of the aircraft and the junction of adjutage is arranged in the line-entering hole.
6. signal wire according to claim 3 protects component, which is characterized in that the holding part at least two, point
The both ends of the another side of the carrying platform are not set；The both ends of the protection sleeve pipe are respectively from foot prop casing one end
Holding part in extend through the holding part of the foot prop casing other end.
7. signal wire according to claim 1 protects component, which is characterized in that the carrying platform of the foot prop casing is arranged
It is adjusted on storehouse in the electricity, and the holding part of the foot prop casing is contained in the electricity and adjusts in storehouse, so that the protection sleeve pipe is received
The electricity is dissolved in adjust in storehouse.
8. signal wire according to claim 1 protects component, which is characterized in that the foot prop further comprises foot prop lower cover
And buffer, one end of the foot prop lower cover adjust the one end in storehouse to connect with the electricity, and are located at the lower section that the electricity adjusts storehouse, it is described
Buffer is connected to the electricity and adjusts between the other end in storehouse and the other end of the foot prop lower cover, and adjusts storehouse and described with the electricity
Foot prop lower cover forms triangular structure.
9. signal wire according to claim 8 protects component, which is characterized in that the buffer is hydraulic damping buffering
Device.
10. signal wire according to claim 8 protects component, which is characterized in that an antenna is arranged on lid under the foot prop
Chamber, for accommodating the antenna of receivable external signal, to prevent the antenna by the damage of external environment.
11. signal wire according to claim 10 protects component, which is characterized in that the antenna includes that figure passes antenna.
12. signal wire according to claim 10 protects component, which is characterized in that the signal wire further includes that the electricity is adjusted
Data line and the antenna data line.
13. a kind of aircraft, which is characterized in that the aircraft includes any one of dynamical system and claim 1~12 institute
The signal wire protection component stated.
14. aircraft according to claim 13, which is characterized in that the aircraft further includes frame main body, from described
Outwardly extending at least two adjutage of frame main body and the vertically extending bracket of extending direction with the adjutage；Institute
Rotor, the dynamical system of rotor and the foot prop is respectively set in the both ends for stating bracket.
15. aircraft according to claim 14, which is characterized in that the bracket is the protection sleeve pipe；
Alternatively, the protection sleeve pipe can be accommodated by the bracket and foot prop casing completely.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610415566.XA CN106005356B (en) | 2014-06-26 | 2014-06-26 | A kind of aircraft and its signal wire protect component |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201480002728.6A CN104755371B (en) | 2014-06-26 | 2014-06-26 | A kind of aircraft and holding wire protection assembly thereof |
| CN201610415566.XA CN106005356B (en) | 2014-06-26 | 2014-06-26 | A kind of aircraft and its signal wire protect component |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201480002728.6A Division CN104755371B (en) | 2014-06-26 | 2014-06-26 | A kind of aircraft and holding wire protection assembly thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106005356A CN106005356A (en) | 2016-10-12 |
| CN106005356B true CN106005356B (en) | 2018-11-27 |
Family
ID=57127988
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610415566.XA Expired - Fee Related CN106005356B (en) | 2014-06-26 | 2014-06-26 | A kind of aircraft and its signal wire protect component |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106005356B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109071000B (en) * | 2017-11-30 | 2022-07-22 | 深圳市大疆创新科技有限公司 | Connection structure, driving system and unmanned aerial vehicle |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1639500A (en) * | 2002-03-06 | 2005-07-13 | 艾劳埃斯·乌本 | Aircraft |
| CN202670095U (en) * | 2012-04-10 | 2013-01-16 | 深圳市大疆创新科技有限公司 | Multi-rotor craft |
| CN103350752A (en) * | 2012-10-29 | 2013-10-16 | 深圳市哈博森科技有限公司 | Four-rotor aircraft |
| CN203306225U (en) * | 2013-01-10 | 2013-11-27 | 深圳市大疆创新科技有限公司 | Aircraft deformation structure and micro aircraft |
| KR20130130116A (en) * | 2012-01-06 | 2013-12-02 | 서울대학교산학협력단 | Multi-rotor aircraft |
-
2014
- 2014-06-26 CN CN201610415566.XA patent/CN106005356B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1639500A (en) * | 2002-03-06 | 2005-07-13 | 艾劳埃斯·乌本 | Aircraft |
| KR20130130116A (en) * | 2012-01-06 | 2013-12-02 | 서울대학교산학협력단 | Multi-rotor aircraft |
| CN202670095U (en) * | 2012-04-10 | 2013-01-16 | 深圳市大疆创新科技有限公司 | Multi-rotor craft |
| CN103350752A (en) * | 2012-10-29 | 2013-10-16 | 深圳市哈博森科技有限公司 | Four-rotor aircraft |
| CN203306225U (en) * | 2013-01-10 | 2013-11-27 | 深圳市大疆创新科技有限公司 | Aircraft deformation structure and micro aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106005356A (en) | 2016-10-12 |
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Granted publication date: 20181127 |