CN204916161U - No rotorcraft multiaxis aircraft - Google Patents
No rotorcraft multiaxis aircraft Download PDFInfo
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- CN204916161U CN204916161U CN201520627047.0U CN201520627047U CN204916161U CN 204916161 U CN204916161 U CN 204916161U CN 201520627047 U CN201520627047 U CN 201520627047U CN 204916161 U CN204916161 U CN 204916161U
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Abstract
The utility model discloses a no rotorcraft multiaxis aircraft, including mounting platform and a plurality of lift air jet system, a plurality of lift air jet systems are the level or non - horizontal opposition is installed on the mounting platform, the lift air jet system includes the supercharging device that always breathes in, annular air -out device, conveying tuber pipe, power drive device and impeller and air inlet unit, and the both ends of conveying tuber pipe are connected with always breathe in supercharging device and annular air -out device respectively, the supercharging device that always breathes in be 90 degrees upwards or be 90 degrees downwards or be geared to the needs of the job and install on the mounting platform, the tip of connecting the mounting platform at the conveying tuber pipe is connected to the power drive device, impeller and air inlet unit are connected with the power drive device, be equipped with annular air outlet on the annular air -out device, annular air outlet one side is equipped with air loop duct opening air outlet. The utility model discloses can reduce the noise that unmanned vehicles flight produced by a wide margin, improve the reliability greatly, improve unmanned aerial vehicle ability loss -rate, obtain the continuation of the journey of longer time.
Description
Technical field
The utility model relate to a kind of can with recording with aviation, industry, amusement, shooting, military, etc. the unmanned vehicle in field, particularly relate to a kind of without rotary wind type Multi-axis aircraft.
Background technology
Existing unmanned plane adopts multiaxis propeller type to obtain lift and drives, and existing many rotary wind types unmanned plane noise is large, and it is low that its proprotor crash resistance can differ from reliability, conventional aircraft meets with foreign material in-flight, branch, collision may directly cause screw propeller to scrap, and energy consumption is large, and cruise duration is short.
Utility model content
The purpose of this utility model: provide a kind of without rotary wind type Multi-axis aircraft, higher reliability and less noise can be obtained, and higher observable index thus acquisition longer cruise duration.
To achieve these goals, the technical solution of the utility model is:
A kind of without rotary wind type Multi-axis aircraft, comprise erecting stage and multiple lift-jet device, described lift-jet device is that odd number or even numbers are individual, and to be that level or non-horizontal are opposed be arranged on described erecting stage described multiple lift-jet devices; Described lift-jet device comprises total air-breathing pressurizer, annular exhaust apparatus, transmits airduct, Power Drive Unit and impeller and air inlet system, and the two ends of described transmission airduct are connected with described total air-breathing pressurizer and annular exhaust apparatus respectively; Described total air-breathing pressurizer is 90 degree, and downward or counterpart is arranged on described erecting stage upwards or in 90 degree, described Power Drive Unit is connected to one end that described transmission airduct is connected with described erecting stage, and described impeller is connected with described Power Drive Unit with air inlet system; Described annular exhaust apparatus is provided with annular air outlet, described annular air outlet is hollow structure and downward-sloping, the downward-sloping side of described annular air outlet is provided with air loop duct opening air outlet, and described total air-breathing pressurizer is sucked air and is sent to the air loop duct opening air outlet ejection of described annular exhaust apparatus by described transmission airduct.
Above-mentioned without rotary wind type Multi-axis aircraft, wherein, described transmission airduct is hollow tubular structure, and described transmission airduct is made up of carbon fiber, highstrenghtpiston and lightweight alloy.
Above-mentioned without rotary wind type Multi-axis aircraft, wherein, described erecting stage is provided with wireless remote control receiving device, battery pack, outer extending apparatus, and described outer extending apparatus comprises camera pan-tilt, mapping equipment, fire-fighting and military abduction equipment.
Above-mentioned without rotary wind type Multi-axis aircraft, wherein, also comprise alighting gear, described alighting gear is arranged on the bottom of described erecting stage.
Above-mentioned without rotary wind type Multi-axis aircraft, wherein, when described total air-breathing pressurizer counterpart is arranged on described erecting stage, the height of described alighting gear is not less than 10cm.
Above-mentioned without rotary wind type Multi-axis aircraft, wherein, also comprise steering hardware, described steering hardware be connected to described transmission airduct connect described in the end of annular exhaust apparatus.
Above-mentioned without rotary wind type Multi-axis aircraft, wherein, described air loop duct opening air outlet is that multiple borehole structure interval is arranged.
Above-mentioned without rotary wind type Multi-axis aircraft, wherein, described air loop duct opening air outlet structure ringwise.
Above-mentioned without rotary wind type Multi-axis aircraft, wherein, described air loop duct opening air outlet is that many single arcuate structure intervals are arranged.
Above-mentioned without rotary wind type Multi-axis aircraft, wherein, described air loop duct opening air outlet is that the arcuate structure intervals that many two superpositions are formed are arranged.
The noise that the utility model produces by using the supercharging of asymmetric geometry impeller significantly to reduce unmanned vehicle flight, by changing the low shortcoming of traditional unmanned plane rotor crash resistance without rotor design, improves reliability greatly; Improving unmanned plane observable index by arranging multipole impeller, obtaining the continuation of the journey of longer time.
Accompanying drawing explanation
Fig. 1 is the structural representation of the utility model without rotary wind type Multi-axis aircraft.
Fig. 2 is the structural representation of the utility model without the lift-jet device of rotary wind type Multi-axis aircraft.
Fig. 3 is the birds-eye view of the utility model without the lift-jet device of rotary wind type Multi-axis aircraft.
Fig. 4 is the structural representation of the utility model without the annular exhaust apparatus of rotary wind type Multi-axis aircraft.
Fig. 5 is the spray apparatus mouth principle schematic of the utility model without rotary wind type Multi-axis aircraft.In figure, UA is upflow air.
Fig. 6 is the schematic diagram of the utility model without the air loop duct opening air outlet of the borehole structure of rotary wind type Multi-axis aircraft.
Fig. 7 is the schematic diagram of the utility model without the air loop duct opening air outlet of the loop configuration of rotary wind type Multi-axis aircraft.
Fig. 8 is the schematic diagram of the utility model without the air loop duct opening air outlet of the single arcuate structure of rotary wind type Multi-axis aircraft.
Fig. 9 is the schematic diagram of the utility model without the air loop duct opening air outlet of the arcuate structure of two superpositions of rotary wind type Multi-axis aircraft.
Detailed description of the invention
Embodiment of the present utility model is further illustrated below in conjunction with accompanying drawing.
Refer to shown in accompanying drawing 1 to accompanying drawing 5, a kind of without rotary wind type Multi-axis aircraft, comprise erecting stage C1 and multiple lift-jet device P1, described lift-jet device P1 is odd number or even numbers, and to be that level or non-horizontal are opposed be arranged on described erecting stage C1 described multiple lift-jet device P1; Described lift-jet device P1 comprises total air-breathing pressurizer A1, annular exhaust apparatus A2, transmits airduct 08, Power Drive Unit 55 and impeller and air inlet system 21, and the two ends of described transmission airduct 08 are connected with described total air-breathing pressurizer A1 and annular exhaust apparatus A2 respectively; Described total air-breathing pressurizer A1 be 90 degree upwards or be arranged on described erecting stage C1 in 90 degree downward (F4 mounting meanss) or counterpart (F5 mounting means), described Power Drive Unit 55 is connected to one end that described transmission airduct 08 is connected with described erecting stage C1, and described impeller is connected with described Power Drive Unit 55 with air inlet system 21; Described annular exhaust apparatus A2 is provided with annular air outlet 32, described annular air outlet 32 is hollow structure and downward-sloping, the downward-sloping side of described annular air outlet 32 is provided with air loop duct opening air outlet 18, air is sprayed and forms lift, described total air-breathing pressurizer A1 is sucked air and is sprayed by the air loop duct opening air outlet 18 that described transmission airduct 08 is sent to described annular exhaust apparatus A2.
Described transmission airduct 08 is hollow tubular structure, and described transmission airduct 08 is made up of carbon fiber, highstrenghtpiston and lightweight alloy, transmits airduct 08 and uses as strut bar simultaneously.
Described erecting stage C1 is provided with wireless remote control receiving device, battery pack, outer extending apparatus etc., and described outer extending apparatus comprises camera pan-tilt, mapping equipment, fire-fighting and military abduction equipment etc.
Also comprise alighting gear 13, described alighting gear 13 is arranged on the bottom of described erecting stage C1.
When described total air-breathing pressurizer A1 counterpart is arranged on described erecting stage C1, the height of described alighting gear 13 is not less than 10cm, to facilitate total air-breathing pressurizer A1 by air intake.
Also comprise steering hardware 15, described steering hardware 15 is connected to the end that described transmission airduct 08 connects described annular exhaust apparatus A2.
Refer to shown in accompanying drawing 6, described air loop duct opening air outlet 18 is that multiple borehole structure interval is arranged.
Refer to shown in accompanying drawing 7, described air loop duct opening air outlet 18 structure ringwise.
Refer to shown in accompanying drawing 8, described air loop duct opening air outlet 18 is many single arcuate structure interval settings.
Refer to shown in accompanying drawing 9, described air loop duct opening air outlet 18 is that the arcuate structure interval that many two superpositions are formed is arranged.
Described Power Drive Unit 55 is the power plant module that alternating current dynamo or DC machine or other modes carry out driving: comprise oil-burning machine, belt drive etc.
Described impeller and air inlet system 21 are charging turbine impeller, and multilayer turbine design can be adopted to improve kinetic energy, also asymmetric Impeller Design can be adopted to reduce noise.
The utility model uses on-bladed air jet system to provide lift, traditional propeller is not used to provide lift, lift-jet device P1 will provide power for whole machine, principle of work is: rotated by Power Drive Unit 55 drives impeller and air inlet system 21 and sucked by air A and increase pressure, by transmitting airduct 08 air A being conducted to the annular air outlet 32 of annular exhaust apparatus A2, also can set up angle that steering hardware 15 changes annular exhaust apparatus A2 with the action such as complete that hovering turns to.Also steering hardware 15 can not be set up, driven can be carried out move ahead, to be sprayed by annular air outlet 32 and from the opening that multiple air loop duct opening air outlet 18 is downward by the air of total air-breathing pressurizer A1 supercharging and obtain lift and drive aircraft, the air of top is converted to downward potential energy by the air driven sprayed downwards thus can obtains more kinetic energy.Can be obtained different air outputs by the design changing air loop duct opening air outlet 18, be met the carriage requirement of distinct device and environmental requirement, whole annular exhaust apparatus A2 can directly dismantle or change.Aerial statue and the manipulation advance of whole aircraft can be controlled by controlling each independently lift-jet device P1 air output.
In sum, the noise that the utility model produces by using the supercharging of asymmetric geometry impeller significantly to reduce unmanned vehicle flight, by changing the low shortcoming of traditional unmanned plane rotor crash resistance without rotor design, improves reliability greatly; Improving unmanned plane observable index by arranging multipole impeller, obtaining the continuation of the journey of longer time.
The foregoing is only preferred embodiment of the present utility model; not thereby the scope of the claims of the present utility model is limited; every equivalent structure transformation utilizing the utility model description to do; or directly or indirectly use the technical field being attached to other Related products, be all in like manner included in scope of patent protection of the present utility model.
Claims (10)
1. one kind without rotary wind type Multi-axis aircraft, it is characterized in that: comprise erecting stage and multiple lift-jet device, described lift-jet device is odd number or even numbers, and to be that level or non-horizontal are opposed be arranged on described erecting stage described multiple lift-jet devices; Described lift-jet device comprises total air-breathing pressurizer, annular exhaust apparatus, transmits airduct, Power Drive Unit and impeller and air inlet system, and the two ends of described transmission airduct are connected with described total air-breathing pressurizer and annular exhaust apparatus respectively; Described total air-breathing pressurizer is 90 degree, and downward or counterpart is arranged on described erecting stage upwards or in 90 degree, described Power Drive Unit is connected to one end that described transmission airduct is connected with described erecting stage, and described impeller is connected with described Power Drive Unit with air inlet system; Described annular exhaust apparatus is provided with annular air outlet, described annular air outlet is hollow structure and downward-sloping, the downward-sloping side of described annular air outlet is provided with air loop duct opening air outlet, and described total air-breathing pressurizer is sucked air and is sent to the air loop duct opening air outlet ejection of described annular exhaust apparatus by described transmission airduct.
2. according to claim 1 without rotary wind type Multi-axis aircraft, it is characterized in that: described transmission airduct is hollow tubular structure, described transmission airduct is made up of carbon fiber, highstrenghtpiston and lightweight alloy.
3. according to claim 1 without rotary wind type Multi-axis aircraft, it is characterized in that: described erecting stage is provided with wireless remote control receiving device, battery pack, outer extending apparatus, described outer extending apparatus comprises camera pan-tilt, mapping equipment, fire-fighting and military abduction equipment.
4. according to claim 1 without rotary wind type Multi-axis aircraft, it is characterized in that: also comprise alighting gear, described alighting gear is arranged on the bottom of described erecting stage.
5. according to claim 4 without rotary wind type Multi-axis aircraft, it is characterized in that: when described total air-breathing pressurizer counterpart is arranged on described erecting stage, the height of described alighting gear is not less than 10cm.
6. according to claim 1 without rotary wind type Multi-axis aircraft, it is characterized in that: also comprise steering hardware, described steering hardware is connected to the end of the described annular exhaust apparatus described in the connection of transmission airduct.
7. according to claim 1 without rotary wind type Multi-axis aircraft, it is characterized in that: described air loop duct opening air outlet is that multiple borehole structure interval is arranged.
8. according to claim 1 without rotary wind type Multi-axis aircraft, it is characterized in that: described air loop duct opening air outlet structure ringwise.
9. according to claim 1 without rotary wind type Multi-axis aircraft, it is characterized in that: described air loop duct opening air outlet is many single arcuate structure interval settings.
10. according to claim 1 without rotary wind type Multi-axis aircraft, it is characterized in that: described air loop duct opening air outlet is that the arcuate structure interval that many two superpositions are formed is arranged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520627047.0U CN204916161U (en) | 2015-08-19 | 2015-08-19 | No rotorcraft multiaxis aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520627047.0U CN204916161U (en) | 2015-08-19 | 2015-08-19 | No rotorcraft multiaxis aircraft |
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| CN204916161U true CN204916161U (en) | 2015-12-30 |
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| CN201520627047.0U Active CN204916161U (en) | 2015-08-19 | 2015-08-19 | No rotorcraft multiaxis aircraft |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105620739A (en) * | 2016-02-17 | 2016-06-01 | 杨海涛 | Turbojet type multiple-spindle aircraft and control method thereof |
| CN107364580A (en) * | 2017-06-26 | 2017-11-21 | 安徽盛美金属科技有限公司 | A kind of agricultural spills medicine machine with nobody |
| CN107985555A (en) * | 2017-11-13 | 2018-05-04 | 上海顺砾智能科技有限公司 | One kind is without the mute unmanned plane of wing formula |
| CN106240809B (en) * | 2016-08-23 | 2018-06-01 | 南京航空航天大学 | Flow controlling multi-rotor aerocraft and control method based on fanjet |
| CN108163213A (en) * | 2018-02-07 | 2018-06-15 | 屈楠 | A kind of multi-stage booster Bladeless formula air propulsion method and propulsion device |
| CN108263594A (en) * | 2018-01-31 | 2018-07-10 | 曹蔚萌 | A kind of bladeless fan power vertical take-off and landing drone |
| CN108945484A (en) * | 2018-07-02 | 2018-12-07 | 山东理工大学 | A kind of two-way air injection aerial vehicle |
| CN109878669A (en) * | 2019-03-29 | 2019-06-14 | 南京涵铭置智能科技有限公司 | A kind of underwater acquisition robot and its acquisition method for preventing water plant from winding |
| CN110481760A (en) * | 2019-07-15 | 2019-11-22 | 陈云桥 | No blade rotates air duct engine aircraft engine |
| CN113247258A (en) * | 2021-07-02 | 2021-08-13 | 国网福建省电力有限公司连城县供电公司 | Unmanned aerial vehicle without rotor wing |
| US11370529B2 (en) | 2018-03-29 | 2022-06-28 | Walmart Apollo, Llc | Aerial vehicle turbine system |
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2015
- 2015-08-19 CN CN201520627047.0U patent/CN204916161U/en active Active
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105620739A (en) * | 2016-02-17 | 2016-06-01 | 杨海涛 | Turbojet type multiple-spindle aircraft and control method thereof |
| CN106240809B (en) * | 2016-08-23 | 2018-06-01 | 南京航空航天大学 | Flow controlling multi-rotor aerocraft and control method based on fanjet |
| CN107364580A (en) * | 2017-06-26 | 2017-11-21 | 安徽盛美金属科技有限公司 | A kind of agricultural spills medicine machine with nobody |
| CN107985555A (en) * | 2017-11-13 | 2018-05-04 | 上海顺砾智能科技有限公司 | One kind is without the mute unmanned plane of wing formula |
| CN108263594A (en) * | 2018-01-31 | 2018-07-10 | 曹蔚萌 | A kind of bladeless fan power vertical take-off and landing drone |
| CN108263594B (en) * | 2018-01-31 | 2019-05-10 | 曹蔚萌 | A kind of bladeless fan power vertical take-off and landing drone |
| CN108163213A (en) * | 2018-02-07 | 2018-06-15 | 屈楠 | A kind of multi-stage booster Bladeless formula air propulsion method and propulsion device |
| CN108163213B (en) * | 2018-02-07 | 2024-02-06 | 屈楠 | Multistage supercharging fan-blade-free air propulsion method and propulsion device |
| US11370529B2 (en) | 2018-03-29 | 2022-06-28 | Walmart Apollo, Llc | Aerial vehicle turbine system |
| CN108945484A (en) * | 2018-07-02 | 2018-12-07 | 山东理工大学 | A kind of two-way air injection aerial vehicle |
| CN109878669A (en) * | 2019-03-29 | 2019-06-14 | 南京涵铭置智能科技有限公司 | A kind of underwater acquisition robot and its acquisition method for preventing water plant from winding |
| CN110481760A (en) * | 2019-07-15 | 2019-11-22 | 陈云桥 | No blade rotates air duct engine aircraft engine |
| CN113247258A (en) * | 2021-07-02 | 2021-08-13 | 国网福建省电力有限公司连城县供电公司 | Unmanned aerial vehicle without rotor wing |
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