CN109110116A - The airframe structure of single rotor unmanned plane - Google Patents
The airframe structure of single rotor unmanned plane Download PDFInfo
- Publication number
- CN109110116A CN109110116A CN201811018696.5A CN201811018696A CN109110116A CN 109110116 A CN109110116 A CN 109110116A CN 201811018696 A CN201811018696 A CN 201811018696A CN 109110116 A CN109110116 A CN 109110116A
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- China
- Prior art keywords
- power
- unmanned plane
- storehouse
- machine body
- power storehouse
- 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.)
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- 230000007704 transition Effects 0.000 claims abstract description 23
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 10
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 10
- 230000007246 mechanism Effects 0.000 claims description 9
- 238000009434 installation Methods 0.000 claims description 6
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 6
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- 239000004917 carbon fiber Substances 0.000 claims description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 8
- 239000004411 aluminium Substances 0.000 description 2
- 238000000354 decomposition reaction Methods 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 238000000605 extraction Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000000116 mitigating effect Effects 0.000 description 2
- 230000006641 stabilisation Effects 0.000 description 2
- 238000011105 stabilization Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/06—Helicopters with single rotor
-
- 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
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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)
- Toys (AREA)
Abstract
The invention discloses a kind of airframe structures of single rotor unmanned plane, including main machine body, tail pipe and coda wave case, the main machine body includes power bin and power storehouse, drive system is equipped in the piggyback pod, the power bin and the power storehouse pass through aluminum Stud connection, fuselage stiffening plate is equipped between the power bin and the power storehouse, the head-shield is fixed on the side wall of the power bin by transition plates, the power storehouse is equipped with the power panel that can pull out the power storehouse, the tail supporting rod that coda wave case and main machine body are connected to by bulb is equipped between the tail pipe and the main machine body.The present invention has the tail supporting rod of bulb connection, has fuselage stiffening plate between the power bin and power storehouse of main machine body, and the head-shield fixed column of main machine body is installed on transition plates, when being all used to guarantee fuselage intensity, and dropping, can protect the complete of components to greatest extent.
Description
Technical field
The invention belongs to air vehicle technique fields, more particularly to a kind of single rotor unmanned plane.
Background technique
Single rotor unmanned plane, also referred to as helicopter unmanned plane, referred to as straight machine, are gone up to the air by main rotor and are flown, pass through tailspin
The wing changes deflection direction, compared to more rotors or fixed-wing unmanned plane, has mobility strong, the fast characteristic of flying speed,
So helicopter unmanned plane is always more popular type, wherein the main body mechanism of helicopter unmanned plane in sports field
Be related to the flying speed of entire unmanned plane, stabilization and it is resistance to fall performance, intensity and rigidity satisfaction and again are constituted with reasonable structure
Not too high fuselage is measured, guarantees the stable operation of straight machine, and when unmanned plane is dropped, additionally it is possible to ratio be effectively protected
The higher part of more important and price saves cost.
Summary of the invention
The invention mainly solves the technical problem of providing a kind of airframe structures of single rotor unmanned plane, connect with bulb
The tail supporting rod connect can fall off when guaranteeing that unmanned plane is dropped with the detachability that bulb connects and guarantee its integrality, in addition, main
There is fuselage stiffening plate between the power bin and power storehouse of fuselage, improve the intensity of main machine body, the head-shield fixed column peace of main machine body
Loaded on transition plates, when dropping, the complete of remaining part can be protected with the damage of transition plates.
In order to solve the above technical problems, a technical solution of use of the invention is as follows:
A kind of airframe structure of single rotor unmanned plane, including main machine body, tail pipe and coda wave case, one end connection of the tail pipe
To main machine body and the other end is connected to coda wave case；
The main machine body includes power bin and the power storehouse for placing battery, and the power bin is located at the power storehouse
Top, the interior drive system for being equipped with driving main rotor body operation of the piggyback pod, the power bin pass through with the power storehouse
Stud connection is equipped with fuselage stiffening plate between the power bin and the power storehouse, the both ends of the fuselage stiffening plate connect respectively
It is connected to the power bin and the power storehouse, and the fuselage stiffening plate and the power bin and the power storehouse constitute triangle
The side wall of structure, the power bin is equipped with head-shield fixed column, and the head-shield fixed column is fixed on transition plates, and the transition plates is fixed
In the side wall of the power bin；
The power storehouse, which is equipped with, can pull out the power panel of the power storehouse, and the power panel and the power storehouse it
Between be equipped with Quick-disassembling mechanism；
Tail supporting rod is equipped between the tail pipe and the main machine body, one end bulb of the tail supporting rod is connected to the tail
Pipe, and other end bulb is connected to the main machine body, the tail pipe, tail supporting rod and main machine body constitute triangular structure.
It further says, the tail pipe is equipped with tail supporting rod fixing seat, and the tail supporting rod fixing seat includes that two cooperations are held tightly
In the semicircular pedestal of the tail pipe, the both ends of two pedestals are connected by screw bolt and nut lock respectively, the spiral shell
One end of bolt is additionally provided with bulb, and the both ends of the tail supporting rod are all equipped with bulb button, and the bulb button is connect with the bulb.
It further says, the side wall of the power storehouse of the fuselage is equipped with linkage bulb, the tail supporting rod and the linkage ball
Head connection.
It further says, the power bin includes two epipleurals, and two epipleurals are arranged in parallel and described in constituting
Power bin is equipped with the spindle drum for installing the motor cabinet of driving motor and for installing main shaft between two epipleurals,
And two epipleurals are connected and fixed by the motor cabinet and spindle drum.
It further says, the power storehouse includes two lower side panels, is vertically connected with plate and bottom plate, described two lower side panel phases
Pair and be arranged in parallel, about two side plates and described be vertically connected with plate and bottom plate constitutes the power storehouse, two lower side panels
Respectively with two epipleurals by the Stud connection, and then it is connected and fixed the power bin and power storehouse, and described dynamic
What power storehouse was placed in the power storehouse is vertically connected with plate.
It further says, the stud is aluminum stud.
It further says, the transition plates is carbon fiber transition plates.
Further say, the Quick-disassembling mechanism include set on the power panel positioning seat and be installed on described be vertically connected with
The spring detent of plate, the spring detent are inserted into and extract the positioning seat.
It further says, the side wall of two epipleurals is all equipped with steering engine mounting rack, and the steering engine mounting rack passes through spiral shell
Nail is installed on the epipleural, and the screw passes through the epipleural and is fixed on the spindle drum.
It further says, is set below the power storehouse there are two foot prop, foot prop company is connected between two foot props
Extension bar.
Beneficial effects of the present invention:
One, of the invention is single rotor unmanned plane, the tail supporting rod with bulb connection, when normal operation, bulb connection
It can guarantee the smooth connection of tail supporting rod, when getting rid of existing screw installation connection, tail supporting rod is constantly in stress deformation
State, moreover, the detachability of bulb connection, when can guarantee that unmanned plane is dropped, the bulb of connection can free dropping without
Meeting stress damage, to guarantee its integrality；In addition, having fuselage stiffening plate between the power bin and power storehouse of main machine body, have
The intensity of the raising main machine body of effect；Head-shield fixed column for installing unmanned nose shell is indirectly installed on host by transition plates
Body when dropping unmanned plane, can protect the complete of remaining components with the damage of transition plates；
Two, power storehouse be equipped with can the power panel of movable pull easily battery can be fixed on after power panel extraction
Power panel installs pusher telegram in reply source plate, and power panel is fixed by quick-disassembly structure, improves the convenience of battery installation；
Three, power bin includes two blocks of epipleurals, and it is simple that two blocks of epipleurals by motor cabinet and spindle drum are connected and fixed structure
And can guarantee the intensity of fuselage, unnecessary component is saved, the effective weight for mitigating complete machine；In addition power bin and power storehouse
Between fixed by the Stud connection of aluminum, it is direct when effectively can prevent unmanned plane from dropping by the ductility of aluminium
Damage, and aluminum stud density is low, can also mitigate the weight of complete machine.
The above description is only an overview of the technical scheme of the present invention, in order to better understand the technical means of the present invention,
And can be implemented in accordance with the contents of the specification, the following is a detailed description of the preferred embodiments of the present invention and the accompanying drawings.
Detailed description of the invention
Fig. 1 is the overall structure diagram of unmanned plane of the invention；
Fig. 2 is the structural schematic diagram of main machine body of the invention (containing drive system and main rotor body)；
Fig. 3 is the structural schematic diagram of main machine body of the invention；
Fig. 4 is the portion A (head-shield fixed column) enlarged drawing of Fig. 3；
Fig. 5 is the drawing structure schematic diagram of power panel of the invention；
Fig. 6 is the attachment structure schematic diagram of tail supporting rod of the invention；
Fig. 7 is the portion B (shoe fixing seat) enlarged drawing of Fig. 6；
Fig. 8 is the decomposition diagram of Fig. 7 (shoe fixing seat)；
Fig. 9 is the schematic diagram that this tail supporting rod of the invention is connect with fuselage；
Figure 10 is the decomposition diagram of main machine body of the invention；
Each section label is as follows in attached drawing:
Main machine body 601, tail pipe 602, power bin 6011, power storehouse 6012, drive system 40, main rotor body 30, stud
603, fuselage stiffening plate 604, head-shield fixed column 609, transition plates 6010, power panel 605, Quick-disassembling mechanism 606, tail supporting rod 607, solid
Reservation 608, pedestal 6081, bolt 6082, nut 6083, bulb 6084, bulb buckle 50312, linkage bulb 5032, epipleural
60111, motor cabinet 60112, spindle drum 60113, lower side panel 60121, be vertically connected with plate 60122, bottom plate 60123, steering engine installation
Frame 6015, spindle drum 60113, foot prop 6016, foot prop connecting rod 6017 and coda wave case 702.
Specific embodiment
The preferred embodiments of the present invention will be described in detail with reference to the accompanying drawing, so that advantages and features of the invention energy
It is easier to be readily appreciated by one skilled in the art, so as to make a clearer definition of the protection scope of the present invention.
Embodiment: a kind of airframe structure of single rotor unmanned plane includes main machine body 601, tail pipe 602 and tail as shown in Figure 1:
Wave case 702, one end of the tail pipe is connected to main machine body and the other end is connected to coda wave case；
As shown in Figure 2: the main machine body includes power bin 6011 and the power storehouse 6012 for placing battery, the power
Position in storehouse is in the drive system 40 for being equipped with the driving operation of main rotor body 30 in the top of the power storehouse, the piggyback pod；
As shown in Figure 3: the power bin is connect with the power storehouse by stud 603, the power bin and the power supply
Fuselage stiffening plate 604 is equipped between storehouse, the both ends of the fuselage stiffening plate are connected to the power bin and the power storehouse,
And the fuselage stiffening plate constitutes triangular structure with the power bin and the power storehouse, the stability characteristic (quality) for passing through triangle increases
The stabilization of strong airframe structure；
As shown in Figure 4: the side wall of the power bin is equipped with head-shield fixed column 609, and the head-shield fixed column is fixed on transition
Plate 6010, the transition plates are fixed on the side wall of the power bin, and the head-shield fixed column is indirectly solid by the transition plates
Due to the main machine body, the head-shield of unmanned plane is installed on the head-shield fixed column, and accident occurs for the unmanned plane when dropping, described
The complete of main machine body can be effectively protected in the head-shield fixed column being indirectly connected with, and the position of damage is allowed to be only positioned at transition plates.
As shown in Figure 5: the power storehouse is equipped with the power panel 605 that can pull out the power storehouse, and the power panel
Quick-disassembling mechanism 606 is equipped between the power storehouse, the power panel is fixed by the Quick-disassembling mechanism or unclamps and can extract out
In the power storehouse, to reach the quick dismounting and change function of battery.
It is as shown in Figure 6: tail supporting rod 607, one end bulb of the tail supporting rod are equipped between the tail pipe and the main machine body
It is connected to the tail pipe, and other end bulb is connected to the main machine body, the tail pipe, tail supporting rod and main machine body constitute triangle
Structure increases the stability of tail pipe equally with triangular structure.
As shown in Fig. 6, Fig. 7 and Fig. 8: the tail pipe is equipped with tail supporting rod fixing seat 608, and the tail supporting rod fixing seat includes two
A cooperation is held tightly in the semicircular pedestal 6081 of the tail pipe, and the both ends of two pedestals pass through bolt 6082 and spiral shell respectively
6083 connection locking of mother, one end of the bolt are additionally provided with bulb 6084, and the both ends of the tail supporting rod are all equipped with bulb button
50312, the bulb button is connect with the bulb.
As shown in Fig. 6 and Fig. 9: the side wall of the power storehouse of the fuselage is equipped with linkage bulb 5032, the tail supporting rod and institute
State linkage bulb connection.
As shown in Figure 10: the power bin includes two epipleurals 60111, and two epipleurals are arranged in parallel and constitute
The power bin is equipped with for installing the motor cabinet 60112 of driving motor and for installing main shaft between two epipleurals
Spindle drum 60113, and two epipleurals are connected and fixed by the motor cabinet and spindle drum；
The power storehouse includes two lower side panels 60121, is vertically connected with plate 60122 and bottom plate 60123, described two downsides
Plate is opposite and is arranged in parallel, and about two side plates are vertically connected with plate and the bottom plate composition power storehouse with described, under two described
Side plate is connect with two epipleurals by the stud 603 respectively, and then is connected and fixed the power bin and power storehouse, and
What the power bin was placed in the power storehouse is vertically connected with plate.
The stud is aluminum stud.
The transition plates is carbon fiber transition plates.
The Quick-disassembling mechanism include set on the power panel positioning seat and be installed on the springlock for being vertically connected with plate
Pin, the spring detent are inserted into and extract the positioning seat, and under normal conditions, the spring detent is inserted into the positioning seat, this
When power panel fixed with the relative position for being vertically connected with plate, when extracting the spring detent, stationary state is unlocked, the electricity
Source plate can be extracted out.
The side wall of two epipleurals is all equipped with steering engine mounting rack 6015, and the steering engine mounting rack is installed on by screw
The epipleural, and the screw passes through the epipleural and is fixed on the spindle drum 60113.
It is set below the power storehouse there are two foot prop 6016, is connected with foot prop connecting rod between two foot props
6017。
The course of work and working principle of the invention is as follows:
Its tail supporting rod with bulb connection of unmanned plane, when normal operation, bulb connection can guarantee the smooth of tail supporting rod
Connection, when getting rid of existing screw installation connection, tail supporting rod is constantly in the state of stress deformation, moreover, bulb connection
Detachability, when can guarantee that unmanned plane is dropped, the bulb of connection can free dropping damaged without stress, to guarantee it
Integrality；In addition, there is fuselage stiffening plate between the power bin and power storehouse of main machine body, the effective intensity for improving main machine body；
Head-shield fixed column for installing unmanned nose shell is indirectly installed on main machine body by transition plates, when dropping unmanned plane, energy
The damage with transition plates is reached to protect the complete of remaining components；
Power storehouse be equipped with can the power panel of movable pull battery easily can be fixed on electricity after power panel extraction
Source plate installs pusher telegram in reply source plate, and power panel is fixed by quick-disassembly structure, improves the convenience of battery installation；
Power bin includes two blocks of epipleurals, and two blocks of epipleurals are connected and fixed structure simply and energy by motor cabinet and spindle drum
The intensity for enough guaranteeing fuselage, saves unnecessary component, the effective weight for mitigating complete machine；In addition between power bin and power storehouse
It is fixed by the Stud connection of aluminum, by the ductility of aluminium, direct damage when effectively can prevent unmanned plane from dropping,
And aluminum stud density is low, can also mitigate the weight of complete machine.
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 transformation made by bright specification and accompanying drawing content is applied directly or indirectly in other relevant technical fields,
Similarly it is included within the scope of the present invention.
Claims (10)
1. a kind of airframe structure of single rotor unmanned plane, it is characterised in that: including main machine body (601), tail pipe (602) and coda wave case
(702), one end of the tail pipe is connected to main machine body and the other end is connected to coda wave case；
The main machine body includes power bin (6011) and the power storehouse (6012) for placing battery, and the power bin is located at described
The top of power storehouse, the interior drive system (40) for being equipped with driving main rotor body (30) operation of the piggyback pod, the power bin
It is connect with the power storehouse by stud (603), is equipped with fuselage stiffening plate (604) between the power bin and the power storehouse,
The both ends of the fuselage stiffening plate are connected to the power bin and the power storehouse, and the fuselage stiffening plate is moved with described
Power storehouse and the power storehouse constitute triangular structure, and the side wall of the power bin is equipped with head-shield fixed column (609), and the head-shield is solid
Fixed column is fixed on transition plates (6010), and the transition plates is fixed on the side wall of the power bin；
The power storehouse is equipped with the power panel (605) that can pull out the power storehouse, and the power panel and the power storehouse
Between be equipped with Quick-disassembling mechanism (606)；
Tail supporting rod (607) are equipped between the tail pipe and the main machine body, one end bulb of the tail supporting rod is connected to the tail
Pipe, and other end bulb is connected to the main machine body, the tail pipe, tail supporting rod and main machine body constitute triangular structure.
2. the airframe structure of single rotor unmanned plane according to claim 1, it is characterised in that: the tail pipe is equipped with tail supporting rod
Fixing seat (608), the tail supporting rod fixing seat include that two cooperations are held tightly in the semicircular pedestal (6081) of the tail pipe, and two
The both ends of a pedestal pass through bolt (6082) and nut (6083) connection locking respectively, and one end of the bolt is additionally provided with ball
Head (6084), the both ends of the tail supporting rod are all equipped with bulb button (50312), and the bulb button is connect with the bulb.
3. the airframe structure of single rotor unmanned plane according to claim 2, it is characterised in that: the power storehouse of the fuselage
Side wall is equipped with linkage bulb (5032), and the tail supporting rod is connect with the linkage bulb.
4. the airframe structure of single rotor unmanned plane according to claim 1, it is characterised in that: the power bin includes two
Epipleural (60111), two epipleurals are arranged in parallel and constitute the power bin, are equipped with and use between two epipleurals
Motor cabinet (60112) in installation driving motor and spindle drum (60113) for installing main shaft, and two epipleurals are logical
It crosses the motor cabinet and spindle drum is connected and fixed.
5. the airframe structure of single rotor unmanned plane according to claim 4, it is characterised in that: the power storehouse includes two
Lower side panel (60121) is vertically connected with plate (60122) and bottom plate (60123), and described two lower side panels are opposite and are arranged in parallel, two
A side plate up and down and plate and the bottom plate of being vertically connected with constitute the power storehouse, two lower side panels respectively with two it is described on
Side plate is connected by the stud (603), and then is connected and fixed the power bin and power storehouse, and the power bin be placed in it is described
Power storehouse is vertically connected with plate.
6. the airframe structure of single rotor unmanned plane according to claim 1 or 5, it is characterised in that: the stud is aluminum
Stud.
7. the airframe structure of single rotor unmanned plane according to claim 1, it is characterised in that: the transition plates is carbon fiber
Transition plates.
8. the airframe structure of single rotor unmanned plane according to claim 5, it is characterised in that: the Quick-disassembling mechanism includes setting
It is inserted into and pulls out with the spring detent for being vertically connected with plate, the spring detent is installed in the positioning seat of the power panel
The positioning seat out.
9. the airframe structure of single rotor unmanned plane according to claim 4, it is characterised in that: the side of two epipleurals
Wall is all equipped with steering engine mounting rack (6015), and the steering engine mounting rack is installed on the epipleural by screw, and the screw is worn
It crosses the epipleural and is fixed on the spindle drum (60113).
10. the airframe structure of single rotor unmanned plane according to claim 1, it is characterised in that: the lower section of the power storehouse
If being connected with foot prop connecting rod (6017) between two foot props there are two foot prop (6016).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811018696.5A CN109110116A (en) | 2018-09-03 | 2018-09-03 | The airframe structure of single rotor unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811018696.5A CN109110116A (en) | 2018-09-03 | 2018-09-03 | The airframe structure of single rotor unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109110116A true CN109110116A (en) | 2019-01-01 |
Family
ID=64861765
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811018696.5A Withdrawn CN109110116A (en) | 2018-09-03 | 2018-09-03 | The airframe structure of single rotor unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109110116A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111434579A (en) * | 2019-01-11 | 2020-07-21 | 海鹰航空通用装备有限责任公司 | Unmanned aerial vehicle tail boom quick assembly disassembly structure |
| CN111924120A (en) * | 2020-08-19 | 2020-11-13 | 汇众翔环保科技股份有限公司 | Airborne monitoring control device and control method for unmanned aerial vehicle |
-
2018
- 2018-09-03 CN CN201811018696.5A patent/CN109110116A/en not_active Withdrawn
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111434579A (en) * | 2019-01-11 | 2020-07-21 | 海鹰航空通用装备有限责任公司 | Unmanned aerial vehicle tail boom quick assembly disassembly structure |
| CN111924120A (en) * | 2020-08-19 | 2020-11-13 | 汇众翔环保科技股份有限公司 | Airborne monitoring control device and control method for unmanned aerial vehicle |
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Application publication date: 20190101 |
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