CN105620739A - Turbojet type multiple-spindle aircraft and control method thereof - Google Patents
Turbojet type multiple-spindle aircraft and control method thereof Download PDFInfo
- Publication number
- CN105620739A CN105620739A CN201610088073.XA CN201610088073A CN105620739A CN 105620739 A CN105620739 A CN 105620739A CN 201610088073 A CN201610088073 A CN 201610088073A CN 105620739 A CN105620739 A CN 105620739A
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- China
- Prior art keywords
- axis aircraft
- power set
- aircraft
- framework platform
- support arms
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/16—Aircraft characterised by the type or position of power plant of jet type
- B64D27/18—Aircraft characterised by the type or position of power plant of jet type within or attached to wing
Abstract
The invention discloses a turbojet type multiple-spindle aircraft and a control method thereof. The multiple-spindle aircraft comprises a multiple-spindle aircraft machine frame platform, a plurality of support arms, a plurality of multiple-spindle aircraft power devices and a control platform, wherein the control platform is arranged on the upper end surface of the multiple-spindle aircraft machine frame platform; a control system, and a battery for electric turbojet or fuel used for a fuel oil jet turbine are mounted on the control platform; one ends of the support arms are respectively connected with the multiple-spindle aircraft machine frame platform, and the support arms are distributed around the multiple-spindle aircraft machine frame platform; the multiple-spindle aircraft power devices are correspondingly arranged at the other ends of the support arms and are connected with the control system on the control platform; an electric turbojet or a fuel oil turbine jet engine is arranged in each of the multiple-spindle aircraft power devices. The turbine type multiple-spindle aircraft disclosed by the invention is a multiple-spindle aircraft with large power, high load, long range and high safety.
Description
Technical field
The present invention relates to a kind of Multi-axis aircraft, particularly relate to a kind of vortex-spraying type Multi-axis aircraft and control method thereof.
Background technology
The multiaxis unmanned plane that existing use propeller aircraft is power is short for cruising time, very-long-range task cannot be completed, because the thrust that propeller aircraft provides is limited, thus cannot carry more battery and expanded application equipment, cannot the big dead weight cargo of carry, affect the extent of spreading amd application of unmanned plane.
The multiaxis unmanned plane that existing use propeller aircraft is power very easily damages, and awing propeller aircraft meets with foreign material, bird strike or knocks the barriers such as trunk and all can cause the impaired safety even scrapping, threatening aircraft itself and borne device of exposed prop-rotor blades.
The Powerpush Unit having rotor is by high speed propeller or the produced thrust of rotor band moving air flow, if personnel's distance rotor is too near or direct touching all can serious threat personal safety.
Using rotor is the Multi-axis aircraft that air force advances, because helical blade is exposed outside, high speed rotating time the air that can rub produce substantial amounts of noise.
Summary of the invention
The purpose of the present invention: a kind of vortex-spraying type Multi-axis aircraft and control method thereof are provided, using the spray of electronic whirlpool or fuel oil turbojet is power, solve the Multi-axis aircraft of existing use propeller or rotor power device cannot complete because rotor power is limited that superelevation load-carrying and the task of super oceangoing voyage journey, reliability be low, propeller or rotor is fragile, easily produce personal safety to threaten, use in can send the problem of a large amount of noise.
To achieve these goals, the technical scheme is that
A kind of vortex-spraying type Multi-axis aircraft, including Multi-axis aircraft framework platform, many support arms, multiple Multi-axis aircraft power set and parametric controller; Described parametric controller is arranged on the upper surface of described Multi-axis aircraft framework platform, and described parametric controller is provided with the battery of control system and the spray use of electronic whirlpool or the fuel of fuel oil jet turbine use; One end of many described support arms is connected with described Multi-axis aircraft framework platform respectively, and many described support arms are odd number or even number, and are distributed in the surrounding of described Multi-axis aircraft framework platform; Described multiple Multi-axis aircraft power set are correspondingly arranged at the other end of many described support arms respectively, described multiple Multi-axis aircraft power set are connected with the control system on described parametric controller, in described multiple Multi-axis aircraft power set are generally aligned in the same plane; Described Multi-axis aircraft power set are the spray of electronic whirlpool or fuel oil turbojet, and described electronic whirlpool spray or fuel oil turbojet are controlled by the control system on described parametric controller.
Above-mentioned vortex-spraying type Multi-axis aircraft, wherein, uses described electronic whirlpool spray or fuel oil whirlpool to spray as power set, and is connected to described Multi-axis aircraft framework platform by described support arm.
Above-mentioned vortex-spraying type Multi-axis aircraft, wherein, the lower surface of described Multi-axis aircraft framework platform is provided with undercarriage.
Above-mentioned vortex-spraying type Multi-axis aircraft, wherein, many described support arms are lightweight alloy or highstrenghtpiston or fibrous material.
Above-mentioned vortex-spraying type Multi-axis aircraft, wherein, described Multi-axis aircraft framework platform includes framework platform body and one or more expansion platform.
The control method of a kind of vortex-spraying type Multi-axis aircraft, the method at least comprises the steps:
Step 1: described Multi-axis aircraft framework platform is connected described multiple Multi-axis aircraft power set by many described support arms.
Step 2: control described multiple Multi-axis aircraft power set by the control system on described parametric controller, make described multiple Multi-axis aircraft power set by air after supercharging is sprayed in electronic whirlpool or the spray supercharging of fuel oil whirlpool is lighted, obtain lift by ejection below described multiple Multi-axis aircraft power set.
Step 3: the power being controlled described multiple Multi-axis aircraft power set by the control system on described parametric controller carries out aerial statue adjustment, it is achieved the steadily hovering of Multi-axis aircraft and movement.
Step 4: hang the standby application realizing unmanned plane by attached on described expansion platform or framework platform body.
The present invention has bigger load-carrying and farther endurance distance relative to conventional multi-axis unmanned plane, because the spray of electronic whirlpool or the dynamic turbojet of oil compare conventional electric or the dynamic rotor of oil has more powerful power, more battery or fuel can be carried, can the more equipment of attached extension, Multi-axis aircraft can be expanded more multi-functional, be more beneficial for application and the development of unmanned plane; Multiaxis flight instruments can be made more safe and reliable, because there is no external propeller thus without worry branch, flying bird, etc. foreign material collision cause propeller to damage; Noise when can reduce Multi-axis aircraft flight, because using the spray of electronic whirlpool or the dynamic turbojet of oil, it does not have the noise that external blade propeller produces with air high-speed friction, it is possible to make the Multi-axis aircraft of the application present invention have less noise.
Accompanying drawing explanation
Fig. 1 is the front view of vortex-spraying type Multi-axis aircraft of the present invention.
Fig. 2 is the top view of vortex-spraying type Multi-axis aircraft of the present invention.
Fig. 3 is the partial enlarged drawing of the Multi-axis aircraft power set of vortex-spraying type Multi-axis aircraft of the present invention.
Fig. 4 is the operating diagram of the Multi-axis aircraft power set of vortex-spraying type Multi-axis aircraft of the present invention.
Detailed description of the invention
Embodiments of the invention are further illustrated below in conjunction with accompanying drawing.
Referring to shown in accompanying drawing 1 to accompanying drawing 3, a kind of vortex-spraying type Multi-axis aircraft, including Multi-axis aircraft framework platform 202, many support arms 208, multiple Multi-axis aircraft power set 206 and parametric controller 207; Described parametric controller 207 is arranged on the upper surface of described Multi-axis aircraft framework platform 202, and described parametric controller 207 is provided with the battery of control system and the spray use of electronic whirlpool or the fuel of fuel oil jet turbine use; One end of described many support arms 208 is connected with described Multi-axis aircraft framework platform 202 respectively, and described many support arms 208 are odd number or even number, and are distributed in the surrounding of described Multi-axis aircraft framework platform 202; Described multiple Multi-axis aircraft power set 206 are correspondingly arranged at the other end of described many support arms 208 respectively, described multiple Multi-axis aircraft power set 206 are connected with the control system on described parametric controller 207, in described multiple Multi-axis aircraft power set 206 are generally aligned in the same plane; Described Multi-axis aircraft power set 206 are the spray of electronic whirlpool or fuel oil turbojet, and described electronic whirlpool spray or fuel oil turbojet are controlled by the control system on described parametric controller 207.
Use described electronic whirlpool spray or fuel oil whirlpool to spray as power set, and be connected to described Multi-axis aircraft framework platform 202 by described support arm 208.
The lower surface of described Multi-axis aircraft framework platform 202 is provided with undercarriage 311, it is simple to the present invention rises and falls.
For lightweight alloy or highstrenghtpiston or fibrous material etc. have high intensity to described many support arms 208 and light-weighted material is made, light weight, and intensity is big, are more beneficial for flight.
Described Multi-axis aircraft framework platform 202 includes framework platform body and one or more expansion platform, can be used for the more expansion equipment of carry.
Multi-axis aircraft framework platform 202 is connected by many support arms 208 multiple Multi-axis aircraft power set 206 of aircraft, the control system on parametric controller 207 is used to carry out the manipulation of unmanned plane, unmanned plane can carry expanded application equipment above or below expansion platform, reaches the expanded application purpose of unmanned plane.
Referring to shown in accompanying drawing 4, the control method of a kind of vortex-spraying type Multi-axis aircraft, the method at least comprises the steps:
Step 1: described Multi-axis aircraft framework platform 202 is connected described multiple Multi-axis aircraft power set 206 by described many support arms 208.
Step 2: control described multiple Multi-axis aircraft power set 206 by the control system on described parametric controller 207, make described multiple Multi-axis aircraft power set 206 by air A after supercharging is sprayed in electronic whirlpool or the spray supercharging of fuel oil whirlpool is lighted, obtain lift by ejection below described multiple Multi-axis aircraft power set 206.
Step 3: the power being controlled described multiple Multi-axis aircraft power set 206 by the control system on described parametric controller 207 carries out aerial statue adjustment, it is achieved the steadily hovering of Multi-axis aircraft and movement.
Step 4: hang the standby application realizing unmanned plane by attached on described expansion platform or framework platform body.
The electric whirlpool spray of the Multi-axis aircraft power set 206 that the present invention is supported by the several support arms 208 being arranged on Multi-axis aircraft framework platform 202 or fuel oil turbojet jet provide rising thrust, are manipulated by the control system being arranged on the parametric controller 207 expanded on platform of Multi-axis aircraft framework platform 202. The function application of unmanned plane is realized by carry expansion equipment.
The present invention is for increasing the reliability of Multi-axis aircraft, sprayed by several times of electronic whirlpools higher than traditional rotor formula multiaxis unmanned plane power or the load capacity being greatly improved multiaxis unmanned plane is sprayed in fuel oil whirlpool, make Multi-axis aircraft can carry more battery or fuel, improve the long-range flying power of Multi-axis aircraft and the off-loadable more equipment of attached extension, make Multi-axis aircraft function more diversified, be greatly improved application and the popularization of Multi-axis aircraft.
In describing the invention, it will be appreciated that, term " upper end ", " on ", " one end ", " outside ", " surrounding ", " other end ", " lower end ", the orientation of the instruction such as " interior " or position relationship be based on orientation shown in the drawings or position relationship, it is for only for ease of the description present invention and simplifies description, rather than instruction or hint indication device or element must have specific orientation, with specific azimuth configuration and operation, be therefore not considered as limiting the invention.
Additionally, in describing the invention, " multiple " are meant that at least two, for instance two, three etc., unless otherwise expressly limited specifically.
In the present invention, unless otherwise clearly defined and limited, the term such as term " installation ", " setting ", " connection " should be interpreted broadly, for instance, it is possible to it is fixing connection, it is also possible to be removably connect, or integral; Can be mechanically connected, it is also possible to be electrical connection; Can be joined directly together, it is also possible to be indirectly connected to by intermediary, it is possible to be connection or the interaction relationship of two elements of two element internals, unless otherwise clear and definite restriction. For the ordinary skill in the art, it is possible to understand above-mentioned term concrete meaning in the present invention as the case may be.
In sum, the present invention has bigger load-carrying and farther endurance distance relative to conventional multi-axis unmanned plane, because the spray of electronic whirlpool or the dynamic turbojet of oil compare conventional electric or the dynamic rotor of oil has more powerful power, more battery or fuel can be carried, can the more equipment of attached extension, Multi-axis aircraft can be expanded more multi-functional, be more beneficial for application and the development of unmanned plane; Multiaxis flight instruments can be made more safe and reliable, because there is no external propeller thus without worry branch, flying bird, etc. foreign material collision cause propeller to damage; Noise when can reduce Multi-axis aircraft flight, because using the spray of electronic whirlpool or the dynamic turbojet of oil, it does not have the noise that external blade propeller produces with air high-speed friction, it is possible to make the Multi-axis aircraft of the application present invention have less noise.
The foregoing is only the preferred embodiments of the present invention; not thereby the scope of the claims of the present invention is limited; every equivalent structure transformation utilizing description of the present invention to make; or directly or indirectly use the technical field being attached to other Related products, all in like manner include in the scope of patent protection of the present invention.
Claims (6)
1. a vortex-spraying type Multi-axis aircraft, it is characterised in that: include Multi-axis aircraft framework platform, many support arms, multiple Multi-axis aircraft power set and parametric controller; Described parametric controller is arranged on the upper surface of described Multi-axis aircraft framework platform, and described parametric controller is provided with the battery of control system and the spray use of electronic whirlpool or the fuel of fuel oil jet turbine use; One end of many described support arms is connected with described Multi-axis aircraft framework platform respectively, and many described support arms are odd number or even number, and are distributed in the surrounding of described Multi-axis aircraft framework platform; Described multiple Multi-axis aircraft power set are correspondingly arranged at the other end of many described support arms respectively, described multiple Multi-axis aircraft power set are connected with the control system on described parametric controller, in described multiple Multi-axis aircraft power set are generally aligned in the same plane; Described Multi-axis aircraft power set are the spray of electronic whirlpool or fuel oil turbojet, and described electronic whirlpool spray or fuel oil turbojet are controlled by the control system on described parametric controller.
2. vortex-spraying type Multi-axis aircraft according to claim 1, it is characterised in that: use described electronic whirlpool spray or fuel oil whirlpool to spray as power set, and be connected to described Multi-axis aircraft framework platform by described support arm.
3. vortex-spraying type Multi-axis aircraft according to claim 1, it is characterised in that: the lower surface of described Multi-axis aircraft framework platform is provided with undercarriage.
4. vortex-spraying type Multi-axis aircraft according to claim 1, it is characterised in that: many described support arms are lightweight alloy or highstrenghtpiston or fibrous material.
5. vortex-spraying type Multi-axis aircraft according to claim 1, it is characterised in that: described Multi-axis aircraft framework platform includes framework platform body and one or more expansion platform.
6. the control method of the described vortex-spraying type Multi-axis aircraft being applied to claim 1-5 any one, it is characterised in that: the method at least comprises the steps:
Step 1: described Multi-axis aircraft framework platform is connected described multiple Multi-axis aircraft power set by many described support arms;
Step 2: control described multiple Multi-axis aircraft power set by the control system on described parametric controller, make described multiple Multi-axis aircraft power set by air after supercharging is sprayed in electronic whirlpool or the spray supercharging of fuel oil whirlpool is lighted, obtain lift by ejection below described multiple Multi-axis aircraft power set;
Step 3: the power being controlled described multiple Multi-axis aircraft power set by the control system on described parametric controller carries out aerial statue adjustment, it is achieved the steadily hovering of Multi-axis aircraft and movement;
Step 4: hang the standby application realizing unmanned plane by attached on described expansion platform or framework platform body.
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CN201610088073.XA CN105620739A (en) | 2016-02-17 | 2016-02-17 | Turbojet type multiple-spindle aircraft and control method thereof |
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CN201610088073.XA CN105620739A (en) | 2016-02-17 | 2016-02-17 | Turbojet type multiple-spindle aircraft and control method thereof |
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Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
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CN106438042A (en) * | 2016-10-27 | 2017-02-22 | 成都翼高九天科技有限公司 | Wireless communication unmanned plane-based engine device |
CN107054668A (en) * | 2017-01-20 | 2017-08-18 | 成都前沿动力科技有限公司 | A kind of stealthy unmanned plane based on electronic Wo Pen VTOL Flying-wing |
CN109963783A (en) * | 2016-12-01 | 2019-07-02 | 朴炯琇 | Unmanned plane |
CN113277079A (en) * | 2021-05-12 | 2021-08-20 | 上海工程技术大学 | Jet-propelled vertical take-off and landing unmanned aerial vehicle capable of realizing thrust vector control |
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CN101367435A (en) * | 2008-09-16 | 2009-02-18 | 广州伟韬电子科技有限公司 | Novel air injection aerial vehicle |
CN104369863A (en) * | 2014-10-31 | 2015-02-25 | 吴建伟 | Composite vertical take-off/landing aircraft |
CN204916161U (en) * | 2015-08-19 | 2015-12-30 | 杨海涛 | No rotorcraft multiaxis aircraft |
CN205327408U (en) * | 2016-02-17 | 2016-06-22 | 杨海涛 | Formula multiaxis aircraft is spouted in whirlpool |
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Patent Citations (5)
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RU2163216C2 (en) * | 1999-11-10 | 2001-02-20 | Кочетков Борис Федорович | Vertical take-off and landing aircraft |
CN101367435A (en) * | 2008-09-16 | 2009-02-18 | 广州伟韬电子科技有限公司 | Novel air injection aerial vehicle |
CN104369863A (en) * | 2014-10-31 | 2015-02-25 | 吴建伟 | Composite vertical take-off/landing aircraft |
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Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
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CN106438042A (en) * | 2016-10-27 | 2017-02-22 | 成都翼高九天科技有限公司 | Wireless communication unmanned plane-based engine device |
CN109963783A (en) * | 2016-12-01 | 2019-07-02 | 朴炯琇 | Unmanned plane |
CN107054668A (en) * | 2017-01-20 | 2017-08-18 | 成都前沿动力科技有限公司 | A kind of stealthy unmanned plane based on electronic Wo Pen VTOL Flying-wing |
CN113277079A (en) * | 2021-05-12 | 2021-08-20 | 上海工程技术大学 | Jet-propelled vertical take-off and landing unmanned aerial vehicle capable of realizing thrust vector control |
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Application publication date: 20160601 |