CN204642143U - Propeller arrangement, vector propulsion system and aircraft - Google Patents
Propeller arrangement, vector propulsion system and aircraft Download PDFInfo
- Publication number
- CN204642143U CN204642143U CN201520028467.7U CN201520028467U CN204642143U CN 204642143 U CN204642143 U CN 204642143U CN 201520028467 U CN201520028467 U CN 201520028467U CN 204642143 U CN204642143 U CN 204642143U
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- propeller
- aircraft
- installation foundation
- driving device
- vector propulsion
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Abstract
The utility model provides a kind of propeller arrangement, vector propulsion system and aircraft, and propeller arrangement comprises: direction adjustment device, has fixed part and is arranged on the movable part on fixed part; Propeller driving device, is arranged on the movable part of direction adjustment device; And propeller blade, be arranged on the drive end of propeller driving device.Propeller driving device is adopted to drive propeller blade to produce power by propeller arrangement of the present utility model, direction adjustment device adjustment propeller driving device towards, thus realize adjustment propeller arrangement go out force direction, this propeller arrangement is set on corresponding aircraft, such as stratosphere flight device, namely can solve the problem that above-mentioned aircraft of the prior art is difficult to control yaw attitude, realize the controlled motor-driven of aircraft, improve alerting ability and the applicability of aircraft.
Description
Technical field
The utility model relates to field of aerospace technology, in particular to a kind of propeller arrangement, vector propulsion system and aircraft.
Background technology
Along with the progress and development of aerospace science technology, stratosphere flight device is all widely used in every field.The operating altitude of stratosphere flight device is positioned at the advection layer leaving ground 12-50km, this space due to its intrinsic feature communication and earth observation field have huge Development volue, and due to stratosphere flight device has can the advantages such as any place is launched in the world, setup time is short, reliability is high, launch cost is low, it is more and more subject to the attention of every country.But stratosphere flight device does not carry power substantially at present, is difficult to maneuvering flight in the horizontal direction, can not controls yaw attitude, also greatly limit field of application.
Utility model content
The utility model provides a kind of propeller arrangement, vector propulsion system and aircraft, is difficult to maneuvering flight and the problem being difficult to control yaw attitude at least to solve prior art stratosphere flight device.
According to an aspect of the present utility model, provide a kind of propeller arrangement, comprising: direction adjustment device, there is fixed part and be arranged on the movable part on fixed part; Propeller driving device, is arranged on the movable part of direction adjustment device; And propeller blade, be arranged on the drive end of propeller driving device.
Further, direction adjustment device is pendulous device, and fixed part is pivoting support, and movable part is the oscillating table be arranged on pivotally on pivoting support, and pendulous device also comprises driving oscillating table relative to the pivotal deflection motor of pivoting support.
Further, also reductor is provided with between deflection motor and oscillating table.
Further, propeller driving device comprises: drive motor, is fixedly installed on oscillating table; Axle drive shaft, first end is connected with the motor shaft of drive motor, and the second end forms drive end.
Further, the motor shaft of axle drive shaft and drive motor is coaxially arranged, and is supported on oscillating table by two bearing seats coaxially arranged.
Further, oscillating table comprises the radial direction that the edge that is positioned at pivot platform above pivoting support and a Ge Cong center oscillating table extends radially outward and extends platform, two bearing seats are arranged on pivot platform, and drive motor is fixedly installed on radial extension on platform.
Further, radial extension on platform is fixedly installed stand, and drive motor is arranged on stand.
Further, propeller driving device also comprises the screw propeller mounting flange of the second end being fixedly installed on axle drive shaft, and propeller blade is arranged on screw propeller mounting flange.
According to another aspect of the application, additionally provide a kind of vector propulsion system, comprise at least two above-mentioned propeller arrangements, at least two propeller arrangements are separately positioned on an installation foundation of aircraft.
Further, installation foundation is truss, and at least two helical mount devices are arranged on the two ends of truss respectively.
Alternatively, installation foundation is hanging box, and at least two helical mount devices are arranged on the relative both sides of hanging box respectively.
Further, at least two propeller arrangements are arranged on two positions respect to one another of installation foundation respectively, and the center that at least two propeller arrangements are mounted opposite basis is centrosymmetric setting.
Further, direction adjustment device and the propeller driving device of arbitrary propeller arrangement have controller respectively, and direction adjustment device and the controller of propeller driving device have the connecting interface be connected with the flight control computer system of aircraft respectively.
According to another aspect of the present utility model, additionally provide a kind of aircraft, comprise utricule, be arranged on the installation foundation below utricule and be arranged on the vector propulsion system on installation foundation, vector propulsion system is above-mentioned vector propulsion system.
Further, installation foundation comprises thrust stand, and thrust stand is arranged on the both sides of the main body of installation foundation, thrust stand is provided with vector propulsion system.
Further, aircraft also comprises the energy source device be connected with direction adjustment device and propeller driving device, and energy source device comprises: solar battery array, is made up of modular solar module; Energy-storage battery, is connected with solar battery array, is piled form by lithium cell; Supply control unit, one end is connected with energy-storage battery with solar battery array, and the other end is connected with propeller driving device with direction adjustment device.
Further, energy source device also comprises follower, and solar battery array is arranged on the bottom of installation foundation by follower, and follower, for following the tracks of the service direction of the sun, controls solar battery array maximum towards the area of the sun.
Further, the covering of utricule is made up of high-strength laminar composite, and helium is filled in utricule inside, and utricule is connected to installation foundation by outside cable.
Propeller driving device is adopted to drive propeller blade to produce power by propeller arrangement of the present utility model, direction adjustment device adjustment propeller driving device towards, thus realize adjustment propeller arrangement go out force direction, this propeller arrangement is set on corresponding aircraft, such as stratosphere flight device, namely can solve the problem that above-mentioned aircraft of the prior art is difficult to control yaw attitude, realize the controlled motor-driven of aircraft, improve alerting ability and the applicability of aircraft.
Accompanying drawing explanation
Accompanying drawing described herein is used to provide further understanding of the present utility model, and form a application's part, schematic description and description of the present utility model, for explaining the utility model, is not formed improper restriction of the present utility model.In the accompanying drawings:
Fig. 1 is the constructional drawing of the aircraft according to the utility model embodiment;
Fig. 2 is the constructional drawing of the propeller arrangement according to the utility model embodiment;
Fig. 3 is the schematic diagram analyzed of exerting oneself of the vector propulsion system according to the utility model embodiment.
Detailed description of the invention
Hereinafter also describe the utility model in detail with reference to accompanying drawing in conjunction with the embodiments.It should be noted that, when not conflicting, the embodiment in the application and the feature in embodiment can combine mutually.
Fig. 2 is the constructional drawing of the propeller arrangement according to the utility model embodiment, and as shown in Figure 2, this device comprises: direction adjustment device, has fixed part and is arranged on the movable part on fixed part; Propeller driving device, is arranged on the movable part of direction adjustment device; And propeller blade, be arranged on the drive end of propeller driving device.
Propeller driving device is adopted to drive propeller blade to produce power by propeller arrangement of the present utility model, direction adjustment device adjustment propeller driving device towards, thus realize adjustment propeller arrangement go out force direction, this propeller arrangement is set on corresponding aircraft, such as stratosphere flight device, namely can solve the problem that above-mentioned aircraft of the prior art is difficult to control yaw attitude, realize the controlled motor-driven of aircraft, improve alerting ability and the applicability of aircraft.
Fig. 1 is the constructional drawing of the aircraft according to the utility model embodiment, this aircraft is a kind of stratosphere balloon, this aircraft visible comprises for controlling yaw attitude and motor-driven vector propulsion system 200, vector propulsion system 200 has the propeller arrangement shown in multiple Fig. 2, and propeller arrangement mainly plays the effect of thrust output and adjustment thrust direction in aircraft flight process.
Preferably, direction adjustment device is pendulous device, and fixed part is pivoting support 10, and movable part is the oscillating table 20 be arranged on pivotally on pivoting support 10, and pendulous device also comprises the driving oscillating table 20 pivotal deflection motor 30 of pivoting support 10 relatively.Also reductor is provided with between deflection motor 30 and oscillating table 20.
More preferably, propeller driving device comprises: drive motor 40, is fixedly installed on oscillating table 20; Axle drive shaft 50, first end is connected with the motor shaft of drive motor 40, and the second end forms drive end.
Visible, deflection motor 30 for control screw propeller towards, and drive motor 40 for drive propeller rotational produce propelling thrust, wherein drive motor 40 can adopt DC permanent magnetism synchronous machine, and deflection motor 30 can adopt stepping motor.In addition, in the another kind of embodiment of propeller driving device, only adopt motor to drive propeller rotational and control screw propeller towards, motor in this embodiment and be provided with driving device and power-transfer clutch between oscillating table 20, and be also provided with latching device between oscillating table 20 and pivoting support 10.
Preferably, axle drive shaft 50 is coaxially arranged with the motor shaft of drive motor 40, and is supported on oscillating table 20 by two bearing seats 60 coaxially arranged.Oscillating table 20 comprises the radial direction that the edge that is positioned at pivot platform 21 above pivoting support 10 and a Ge Cong center oscillating table 21 extends radially outward and extends platform 22, two bearing seats 60 are arranged on pivot platform 21, and drive motor 40 is fixedly installed on radial extension on platform 22.Radial extension on platform 22 is fixedly installed stand, and drive motor 40 is arranged on stand.
As the pendulous device of direction adjustment device, in the specific implementation, also can in the following way, such as, installation foundation fixedly mounts a vertical shaft, oscillating table 21 is pivotally attached on this vertical shaft, then linear advancement mechanism, such as electric pushrod, a lead screw device etc. are set, make the two ends of linear advancement mechanism hinged with oscillating table on installation foundation 21 respectively, like this, by controlling linear advancement mechanism, just can promote oscillating table 21 and swinging around this vertical shaft.
In addition, as shown in Figure 2, Flange joint is passed through between the screw propeller of propeller driving device and axle drive shaft 50, one of them specific embodiment is as follows: propeller driving device also comprises the screw propeller mounting flange 70 of the second end being fixedly installed on axle drive shaft 50, and propeller blade is arranged on screw propeller mounting flange 70.
According to another aspect of the present utility model, additionally provide a kind of vector propulsion system, this vector propulsion system comprises at least two above-mentioned propeller arrangements, and at least two propeller arrangements are separately positioned on an installation foundation of aircraft.
Fig. 3 is the schematic diagram analyzed of exerting oneself of the vector propulsion system according to the utility model embodiment, as shown in Figure 3, this vector propulsion system by control multiple propeller arrangement go out force direction thus control vector propulsion system entirety go out force direction, and the force direction that goes out of multiple propeller arrangement can be the same or different, therefore vector propulsion system can realize displacement or realize pose adjustment by rotation.
State of exerting oneself such as shown in Fig. 3, an angle between propeller arrangement and the direction of x-axis being is α
1, and exert oneself towards the direction of y-axis, the angle between another propeller arrangement and direction of x-axis being is α
2, and exert oneself towards the direction of y-axis.When two propeller arrangements exert oneself identical time, if α
1with α
2equal, then the angle between the reverse direction that the movement tendency of vector propulsion system is x-axis being is α
1and reverse towards y-axis; If α
1with α
2unequal, then according to the composite formula of power, resultant direction and the size of two propeller arrangements can be obtained.
In addition, vector propulsion system can also assist the above-mentioned action realized by controlling to exert oneself by controlling exerting oneself of different screw propellers, or substitutes the above-mentioned action realized by controlling to exert oneself of a part.
Preferably, installation foundation is truss, and at least two helical mount devices are arranged on the two ends of truss respectively.Alternatively, installation foundation is hanging box, and at least two helical mount devices are arranged on the relative both sides of hanging box respectively.
More preferably, at least two propeller arrangements are arranged on two positions respect to one another of installation foundation respectively, and the center that at least two propeller arrangements are mounted opposite basis is centrosymmetric setting.Symmetrically arranged propeller arrangement is easier to control and exerts oneself, and is easier to make aircraft to keep self-respect balance.
In addition, propeller arrangement can be also three, and be arranged on the position that three an of hanging box are different, such as, two are oppositely arranged, and another is arranged on bottom hanging box, or these three screw propellers are arranged three sides being separately positioned on rectangle hanging box.
Preferably, direction adjustment device and the propeller driving device of arbitrary propeller arrangement have controller respectively, and direction adjustment device and the controller of propeller driving device have the connecting interface be connected with the flight control computer system of aircraft respectively.The controller of direction adjustment device and propeller driving device is all connected to flight control computer system by RS422 interface.
According to the 3rd aspect of the present utility model, additionally provide a kind of aircraft, comprise utricule 100, be arranged on the installation foundation below utricule 100 and be arranged on the vector propulsion system 200 on installation foundation, vector propulsion system 200 is above-mentioned vector propulsion system 200.
Fig. 1 is the constructional drawing of the aircraft according to the utility model embodiment, as shown in Figure 1, installation foundation hanging is in the below of utricule 100, and vector propulsion system 200 is connected with utricule 100 by installation foundation, utricule 100 provides buoyancy to make aircraft keep flight, vector propulsion system 200 by multiple propeller arrangement for aircraft provides controlled power, control aircraft move or adjust attitude, improve alerting ability and the applicability of aircraft, this aircraft can be worked widely.
Preferably, installation foundation comprises thrust stand, and thrust stand is arranged on the both sides of the main body of installation foundation, thrust stand is provided with vector propulsion system 200.Installation foundation also comprises structure for pod, and gondola top draws in the net to be connected by load with utricule 100.The flight control computer system of aircraft, communication system, energy resource system and other loadings can be arranged in gondola.In order to alleviate the weight of aircraft, thrust stand and gondola all select light material to make, such as hollow steel or rigid plastic etc., meet load and weight demands under multi-state, possess the feature such as fast integration, convenient assembling simultaneously.
Preferably, the covering of utricule 100 is made up of high-strength laminar composite, and helium is filled in utricule 100 inside, and utricule 100 is connected to installation foundation by outside cable.Utricule 100 in Fig. 1 is spherical in shape, and utricule 100 covering adopts high-strength laminar composite, can bear certain pressure intensity, is connected to installation foundation by outside cable.In addition utricule 100 is provided with the avionics devices such as condition monitoring, valve and emergency control apparatus.Helium is filled in utricule 100 inside, and keeps good leak tightness, can keep more than 1 year flight time at advection layer height.
Preferably, aircraft also comprises the energy source device be connected with direction adjustment device and propeller driving device, and energy source device comprises: solar battery array 300, is made up of modular solar module; Energy-storage battery, is connected with solar battery array 300, is piled form by lithium cell; Supply control unit, one end is connected with energy-storage battery with solar battery array, and the other end is connected with propeller driving device with direction adjustment device.Energy source device also comprises follower, and solar battery array 300 is arranged on the bottom of installation foundation by follower, and follower, for following the tracks of the service direction of the sun, controls solar battery array maximum towards the area of the sun.Energy source device mainly comprises solar battery array, energy-storage battery, power pack and tracking section.Solar battery array part is made up of modular solar module connection in series-parallel, is arranged on gondola bottom by vector tracking mechanism.Array Design considers blocking of utricule 100 pairs of solar cells, can meet the energy requirement of the routine of aircraft avionics and flight control.Closed-center system is piled by lithium cell and is formed, and forms cycle energy system with energy switch, DC/DC, solar battery array.For ensureing ceiling capacity degree of utilization, this aircraft adopts solar energy tracking scheme, can keep in real time solar battery array and sun angle minimum.
Avionics device mainly comprises three kind equipments, and one is the avionics hardware device such as flight control and management, energy management, i.e. managerial tools; Two is the actuating equipments such as valve, peace control; Three is sensing and collecting device, comprises all kinds of temperature sensor, force sensors, tachogen and state sensor, and corresponding collecting device.Avionics device adopts bus design, carries out data transmission, various kinds of equipment connected together by bus.
Vector propulsion system comprises 2-8 group propeller arrangement, and the vector power of aircraft by flight control computer system-computed, provide power by propeller arrangement, thus controls vehicle yaw attitude, makes aircraft can keep the wind resistance speed of 2-10m/s.
Task system, for arranging and the tasks such as the vector of managing aircraft.
The utility model embodiment provide for stratospheric aircraft, more traditional zero-pressure aircraft has stronger structural strength, higher reliability and stability, ensure that the possibility that circumaviation realizes.Vector propulsion system, accurately can control the flight path of this aircraft, is easy to the realization becoming rail flight function; Energy source device, for the change of not position of sun in the same time, can carry out the tracking collection of solar power, can greatly improve solar energy acquisition efficiency.
Obviously, those skilled in the art should be understood that, above-mentioned of the present utility model each module or each step can realize with general computer device, they can concentrate on single computer device, or be distributed on network that multiple computer device forms, alternatively, they can realize with the executable program code of computer device, thus, they can be stored and be performed by computer device in the storage device, and in some cases, step shown or described by can performing with the order be different from herein, or they are made into each integrated circuit modules respectively, or the multiple module in them or step are made into single integrated circuit module to realize.Like this, the utility model is not restricted to any specific hardware and software combination.
The foregoing is only preferred embodiment of the present utility model, be not limited to the utility model, for a person skilled in the art, the utility model can have various modifications and variations.All within spirit of the present utility model and principle, any amendment done, equivalent replacement, improvement etc., all should be included within protection domain of the present utility model.
Claims (18)
1. a propeller arrangement, is characterized in that, comprising:
Direction adjustment device, has fixed part and is arranged on the movable part on described fixed part;
Propeller driving device, is arranged on the movable part of described direction adjustment device; And
Propeller blade, is arranged on the drive end of described propeller driving device.
2. propeller arrangement according to claim 1, it is characterized in that, described direction adjustment device is pendulous device, described fixed part is pivoting support (10), described movable part is the oscillating table (20) be arranged on pivotally on described pivoting support (10), and described pendulous device also comprises driving described oscillating table (20) the pivotal deflection motor of relatively described pivoting support (10) (30).
3. propeller arrangement according to claim 2, is characterized in that, is also provided with reductor between described deflection motor (30) and described oscillating table (20).
4. propeller arrangement according to claim 2, is characterized in that, described propeller driving device comprises:
Drive motor (40), is fixedly installed on described oscillating table (20);
Axle drive shaft (50), first end is connected with the motor shaft of described drive motor (40), and the second end forms described drive end.
5. propeller arrangement according to claim 4, it is characterized in that: described axle drive shaft (50) is coaxially arranged with the motor shaft of described drive motor (40), and be supported on described oscillating table (20) by two bearing seats (60) coaxially arranged.
6. propeller arrangement according to claim 5, it is characterized in that, described oscillating table (20) comprises the pivot platform (21) and radial direction extension platform (22) extended radially outward from the edge of described pivot platform (21) that are positioned at described pivoting support (10) top, described two bearing seats (60) are arranged on described pivot platform (21), and described drive motor (40) is fixedly installed on described radial direction and extends on platform (22).
7. propeller arrangement according to claim 6, is characterized in that, described radial direction extension platform (22) is fixedly installed stand, and described drive motor (40) is arranged on described stand.
8. propeller arrangement according to claim 4, it is characterized in that, described propeller driving device also comprises the screw propeller mounting flange (70) of the second end being fixedly installed on described axle drive shaft (50), and described propeller blade is arranged on described screw propeller mounting flange (70).
9. a vector propulsion system, is characterized in that, comprises the propeller arrangement according to any one of at least two claims 1 to 8, and described at least two propeller arrangements are separately positioned on an installation foundation of aircraft.
10. vector propulsion system according to claim 9, is characterized in that, described installation foundation is truss, and described at least two helical mount devices are arranged on the two ends of described truss respectively.
11. vector propulsion systems according to claim 9, it is characterized in that, described installation foundation is hanging box, described at least two helical mount devices are arranged on the relative both sides of described hanging box respectively.
12. vector propulsion systems according to claim 9, it is characterized in that, described at least two propeller arrangements are arranged on two positions respect to one another of described installation foundation respectively, and the center of the relatively described installation foundation of described at least two propeller arrangements is centrosymmetric setting.
13. vector propulsion systems according to claim 9, it is characterized in that, described direction adjustment device and the described propeller driving device of arbitrary described propeller arrangement have controller respectively, and described direction adjustment device and the controller of propeller driving device have the connecting interface be connected with the flight control computer system of aircraft respectively.
14. 1 kinds of aircraft, it is characterized in that, the installation foundation comprise utricule (100), being arranged on described utricule (100) below and the vector propulsion system (200) be arranged on described installation foundation, the vector propulsion system (200) of described vector propulsion system (200) according to any one of claim 9 to 13.
15. aircraft according to claim 14, it is characterized in that, described installation foundation comprises thrust stand, and described thrust stand is arranged on the both sides of the main body of described installation foundation, described thrust stand is provided with described vector propulsion system (200).
16. aircraft according to claim 14, is characterized in that, also comprise the energy source device be connected with described direction adjustment device and described propeller driving device, described energy source device comprises:
Solar battery array (300), is made up of modular solar module;
Energy-storage battery, is connected with described solar battery array (300), is piled form by lithium cell;
Supply control unit, one end is connected with described energy-storage battery with described solar battery array, and the other end is connected with described propeller driving device with described direction adjustment device.
17. aircraft according to claim 16, it is characterized in that, described energy source device also comprises follower, described solar battery array (300) is arranged on the bottom of described installation foundation by described follower, described follower, for following the tracks of the service direction of the sun, controls described solar battery array maximum towards the area of the sun.
18. aircraft according to claim 14, it is characterized in that, the covering of described utricule (100) is made up of high-strength laminar composite, helium is filled in described utricule (100) inside, and described utricule (100) is connected to described installation foundation by outside cable.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520028467.7U CN204642143U (en) | 2015-01-15 | 2015-01-15 | Propeller arrangement, vector propulsion system and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520028467.7U CN204642143U (en) | 2015-01-15 | 2015-01-15 | Propeller arrangement, vector propulsion system and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204642143U true CN204642143U (en) | 2015-09-16 |
Family
ID=54094910
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520028467.7U Expired - Fee Related CN204642143U (en) | 2015-01-15 | 2015-01-15 | Propeller arrangement, vector propulsion system and aircraft |
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| Country | Link |
|---|---|
| CN (1) | CN204642143U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106892079A (en) * | 2017-03-13 | 2017-06-27 | 天峋（常州）智能科技有限公司 | One kind is tethered at unmanned plane |
| CN110816803A (en) * | 2019-10-12 | 2020-02-21 | 山东科技大学 | Small helium balloon double propeller control device and method |
| CN111114733A (en) * | 2019-12-26 | 2020-05-08 | 中国科学院光电研究院 | High-altitude airship and yaw control method thereof |
-
2015
- 2015-01-15 CN CN201520028467.7U patent/CN204642143U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106892079A (en) * | 2017-03-13 | 2017-06-27 | 天峋（常州）智能科技有限公司 | One kind is tethered at unmanned plane |
| CN110816803A (en) * | 2019-10-12 | 2020-02-21 | 山东科技大学 | Small helium balloon double propeller control device and method |
| CN111114733A (en) * | 2019-12-26 | 2020-05-08 | 中国科学院光电研究院 | High-altitude airship and yaw control method thereof |
| CN111114733B (en) * | 2019-12-26 | 2022-07-12 | 中国科学院光电研究院 | High-altitude airship and yaw control method thereof |
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| GR01 | Patent grant | ||
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| TR01 | Transfer of patent right |
Effective date of registration: 20160802 Address after: 201, room 1, building A, No. 518000, Qianhai Road, Qianhai, Shenzhen Shenzhen cooperation zone, Guangdong, China Patentee after: Shenzhen TV dream Technology Co. Ltd. Address before: Bantian street Longgang District of Shenzhen City, Guangdong province 518000 Jihua Road, the new world Huasai Industrial Area No. 2, building 101 (two floor) 201 Patentee before: Shenzhen Guang Qi space technology Co., Ltd |
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| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150916 Termination date: 20210115 |