CN104590567A - Aerocraft - Google Patents
Aerocraft Download PDFInfo
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- CN104590567A CN104590567A CN201510032337.5A CN201510032337A CN104590567A CN 104590567 A CN104590567 A CN 104590567A CN 201510032337 A CN201510032337 A CN 201510032337A CN 104590567 A CN104590567 A CN 104590567A
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- fuselage
- driving engine
- duct
- gas
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Abstract
The invention discloses aerocraft, the whole weight of the aerocraft can be reduced, the manufacturing cost is low, and the failure rate is lower. The aerocraft comprises a fuselage and an engine, wherein the engine is composed of a duct engine which is installed in the fuselage, an axial lead of the duct engine coincides with that of the fuselage, an airflow inlet of the duct engine is communicated with a confluence cavity which is formed in the fuselage and positioned at the outer side of the airflow inlet of the duct engine, an airflow outlet of the duct engine is communicated with a shunting cavity which is formed in the fuselage and positioned at the outer side of the airflow outlet of the duct engine, at least two air inlet ducts and at least two air outlet ducts are formed in the fuselage, air inlets are formed in the ends, which are far from the duct engine, of the air inlet ducts, air outlets are formed in the ends, which are far from the duct engine, of the air outlet ducts, all of the air inlet ducts are communicated with the confluence cavity, and all of the air outlet ducts are communicated with the shunting cavity.
Description
Technical field
The present invention relates to telecontrolled aircraft production field, particularly relate to aviation aircraft.
Background technology
Telecontrolled aircraft is a kind of aviation aircraft being carried out Remote driving by remote controller.Its classification is more, and wherein one is the jet-propelled aviation aircraft of fixed-wing.This kind of aircraft generally comprises fuselage, is provided with receiver, control desk, driving electricity tune, battery, driving engine etc. in fuselage.Receiver is for receiving the instruction of remote controller, and control desk, for controlling the work of each mechanism, drives electricity to call in start the engine, and battery is used for powering to associated mechanisms.
The quantity of the driving engine that existing this aircraft comprises is two, two driving engines are symmetricly set on fuselage interior, each driving engine is equipped with a battery, this whole aircraft overall weight just made is heavier, and this just have impact on the flying speed of aircraft and the alerting ability of flying power and manipulation.And, owing to being provided with two driving engines, need to arrange inlet channel and gas off-take to each driving engine in fuselage, owing to also needing in fuselage to install other mechanism, therefore the design of inlet channel and gas off-take is generally through type, and the windage that heads on of formation is larger, the windage that heads on that duct driving engine is subject to when speed is faster is larger, this just increases the load of driving engine, the work efficiency of driving engine is reduced, shortens the service life of driving engine.Meanwhile, it is owing to adopting hybrid power system, and cost is higher.The fault rate of aircraft is also higher.
Summary of the invention
The technical matters that the present invention solves is to provide and a kind ofly reduces the low and aviation aircraft that fault rate is lower of aircraft overall weight, productive costs.
The technical solution adopted for the present invention to solve the technical problems is: aviation aircraft, comprise fuselage and driving engine, described driving engine is made up of the duct driving engine be arranged in fuselage, the described axial line of duct driving engine overlaps with the axial line of fuselage, the air flow inlet of duct driving engine is communicated with the chamber of confluxing outside the air flow inlet being positioned at duct driving engine be arranged in fuselage, the air stream outlet of duct driving engine is communicated with the branch chamber outside the air stream outlet being positioned at duct driving engine be arranged in fuselage, at least two inlet channels and at least two gas off-takes are provided with in fuselage, inlet channel is provided with admission port away from one end of duct driving engine, gas off-take is provided with air extractor duct away from one end of duct driving engine, each inlet channel is communicated with chamber of confluxing, each gas off-take is communicated with branch chamber.
Further: the angle of the axial line of each inlet channel described and fuselage is acute angle.
Further: the number of described inlet channel is 2, described two inlet channels with the vertical section crossing fuselage axial line for the plane of symmetry is symmetrical arranged.
Further: described gas off-take is arc.
Further: the number of described gas off-take is 2, described two gas off-takes with the vertical section crossing fuselage axial line for the plane of symmetry is symmetrical arranged.
The invention has the beneficial effects as follows:
1, only adopt a duct driving engine, fuselage overall weight significantly reduces, and flying power gets a promotion;
2, inlet channel and gas off-take reasonable in design, the windage that heads on when admission port actv. has dodged high-speed flight, to the load of driving engine, is conducive to driving engine and makes full use of air-flow and provide thrust to aircraft;
3, owing to only adopting a duct driving engine, fuselage interior structure is simplified, and has sufficient space to arrange inlet channel and gas off-take, decreases the usage quantity of respective accessory simultaneously, and the setting of control system is also relatively simple, reduces fault rate.
4, owing to decreasing driving engine and related accessory, capacity of cell is corresponding reduction also, and productive costs is significantly reduced.
Accompanying drawing explanation
Fig. 1 is the set-up mode schematic diagram of the inlet channel of aviation aircraft of the present invention, gas off-take and duct driving engine;
Be labeled as in figure: fuselage 1, inlet channel 2, admission port 3, duct driving engine 4, chamber 5 of confluxing, branch chamber 6, gas off-take 7, air extractor duct 8.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the present invention is further described.
As shown in Figure 1, aviation aircraft of the present invention, comprise fuselage 1 and driving engine, described driving engine is made up of the duct driving engine 4 be arranged in fuselage 1, the axial line of described duct driving engine 4 overlaps with the axial line of fuselage 1, the air flow inlet of duct driving engine 4 is communicated with the chamber 5 of confluxing outside the air flow inlet being positioned at duct driving engine 4 be arranged in fuselage 1, the air stream outlet of duct driving engine 4 is communicated with the branch chamber 6 outside the air stream outlet being positioned at duct driving engine 4 be arranged in fuselage 1, at least two inlet channels 2 and at least two gas off-takes 7 are provided with in fuselage 1, inlet channel 2 is provided with admission port 3 away from one end of duct driving engine 4, gas off-take 7 is provided with air extractor duct 8 away from one end of duct driving engine 4, each inlet channel 2 is communicated with chamber 5 of confluxing, each gas off-take 7 is communicated with branch chamber 6.When duct driving engine 4 works, air-flow enters inlet channel 2 from admission port 3, then conflux after inlet channel 2 and enter chamber 5 of confluxing, the air-flow confluxed in chamber 5 can enter duct driving engine 4, the air-flow that duct driving engine 4 sprays is introduced into branch chamber 6, branch chamber 6 is owing to being connected with multiple gas off-take 7, and the air-flow therefore in branch chamber 6 can be divided into multiple tracks air-flow and spray from the air extractor duct 8 of each gas off-take 7 respectively.
The structure such as receiver, control desk, driving electricity tune, battery of above-mentioned aviation aircraft can be arranged in fuselage.Because the present invention is only provided with a duct driving engine 4, therefore the set-up mode of two driving engines in existing design is compared, the usage quantity of related accessory can significantly reduce, simultaneously, owing to only needing control driving engine, the interlock circuits such as control desk are corresponding simplification also, and the fault rate of this aviation aircraft entirety is significantly reduced.Further, the main by weight of this aviation aircraft is from driving engine, and the use reducing by a driving engine significantly can reduce the weight of aviation aircraft entirety.And, owing to only needing to power to a driving engine, the therefore weight of battery also corresponding reduction.Be conducive to energy-conserving and environment-protective like this.Simultaneously, although only use a duct driving engine 4, the flying speed of aviation aircraft of the present invention and flying power do not reduce, and calculate according to fluid mechanics principle, when the volume of aircraft and span area constant, the body weight of aircraft determines flying speed and the flying power of aircraft, and the lighter speed of body weight is faster, and the power of needs is less, draw according to barodynamics principle, body weight is lighter, and the speed of decline is slower, and flying power can be stronger.
Owing to only using a driving engine, the inlet channel therefore in fuselage and the set-up mode of gas off-take just seem particularly important, and this performance being related to driving engine could give full play to.Because fuselage interior is also provided with other parts, therefore the setting of inlet channel and gas off-take can not arbitrarily be arranged, and will dodge other parts on the one hand, also will consider how to reduce vapour lock, so that driving engine can give full play to its performance on the other hand as far as possible.Based on above-mentioned thinking, as shown in Figure 1, each inlet channel 2 of the present invention is acute angle with the angle of the axial line of fuselage 1.Further, on the basis of the above, proved by actual experiment, the number of described inlet channel 2 is 2, and described two inlet channels 2 with the vertical section crossing fuselage axial line for the plane of symmetry is symmetrical arranged.This setup is more conducive to air-flow and passes through smoothly, and windage is less, and the performance of driving engine is effectively ensured.
Similar with the principle of design of inlet channel, gas off-take 7 also needs to carry out appropriate design, so that driving engine can give full play to its due performance.For this reason, gas off-take 7 of the present invention is arc, as shown in Figure 1.Gas off-take 7 entirety is one section of round and smooth arcuate structure.Further, on the basis of the above, proved by actual experiment, the number of described gas off-take 7 is 2, described two gas off-takes 7 with the vertical section crossing fuselage axial line for the plane of symmetry is symmetrical arranged.This setup is more conducive to air-flow and passes through smoothly, and windage is less.
By the reasonable setting of above-mentioned inlet channel 2 and gas off-take 7, make the present invention just can realize aviation aircraft smooth flight only by a driving engine, and compared with two driving engines, its flying speed does not only reduce, and raises on the contrary.
Embodiment:
Aviation aircraft comprises fuselage 1, a duct driving engine 4 is installed in fuselage 1, the axial line of duct driving engine 4 overlaps with the axial line of fuselage 1, the air flow inlet of duct driving engine 4 is communicated with the chamber 5 of confluxing outside the air flow inlet being positioned at duct driving engine 4 be arranged in fuselage 1, the air stream outlet of duct driving engine 4 is communicated with the branch chamber 6 outside the air stream outlet being positioned at duct driving engine 4 be arranged in fuselage 1, two inlet channels 2 and two gas off-takes 7 are set in fuselage 1, inlet channel 2 is provided with admission port 3 away from one end of duct driving engine 4, each inlet channel 2 is communicated with chamber 5 of confluxing, gas off-take 7 is provided with air extractor duct 8 away from one end of duct driving engine 4, each gas off-take 7 is communicated with branch chamber 6, and, each inlet channel 2 described is acute angle with the angle of the axial line of fuselage 1, described two inlet channels 2 with the vertical section crossing fuselage axial line for the plane of symmetry is symmetrical arranged, described gas off-take 7 is arc, described two gas off-takes 7 with the vertical section crossing fuselage axial line for the plane of symmetry is symmetrical arranged.
Above-described specific embodiment; object of the present invention, technical scheme and beneficial effect are further described; be understood that; the foregoing is only specific embodiments of the invention; be not limited to the present invention; within the spirit and principles in the present invention all, any amendment made, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (5)
1. aviation aircraft, comprise fuselage and driving engine, it is characterized in that: described driving engine is made up of the duct driving engine be arranged in fuselage, the described axial line of duct driving engine overlaps with the axial line of fuselage, the air flow inlet of duct driving engine is communicated with the chamber of confluxing outside the air flow inlet being positioned at duct driving engine be arranged in fuselage, the air stream outlet of duct driving engine is communicated with the branch chamber outside the air stream outlet being positioned at duct driving engine be arranged in fuselage, at least two inlet channels and at least two gas off-takes are provided with in fuselage, inlet channel is provided with admission port away from one end of duct driving engine, gas off-take is provided with air extractor duct away from one end of duct driving engine, each inlet channel is communicated with chamber of confluxing, each gas off-take is communicated with branch chamber.
2. aviation aircraft as claimed in claim 1, is characterized in that: the angle of the axial line of each inlet channel described and fuselage is acute angle.
3. aviation aircraft as claimed in claim 2, is characterized in that: the number of described inlet channel is 2, described two inlet channels with the vertical section crossing fuselage axial line for the plane of symmetry is symmetrical arranged.
4. aviation aircraft as claimed in claim 1, is characterized in that: described gas off-take is arc.
5. aviation aircraft as claimed in claim 4, is characterized in that: the number of described gas off-take is 2, described two gas off-takes with the vertical section crossing fuselage axial line for the plane of symmetry is symmetrical arranged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510032337.5A CN104590567A (en) | 2015-01-22 | 2015-01-22 | Aerocraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510032337.5A CN104590567A (en) | 2015-01-22 | 2015-01-22 | Aerocraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104590567A true CN104590567A (en) | 2015-05-06 |
Family
ID=53116712
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510032337.5A Pending CN104590567A (en) | 2015-01-22 | 2015-01-22 | Aerocraft |
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| CN (1) | CN104590567A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4478378A (en) * | 1981-10-15 | 1984-10-23 | Aeritalia-Societa Aerospaziale Italiana-Per Azioni | Aircraft with jet propulsion |
| CN1779224A (en) * | 2004-11-05 | 2006-05-31 | 通用电气公司 | Thrust vectoring aft FLADE engine |
| CN2900357Y (en) * | 2006-04-07 | 2007-05-16 | 叶万章 | Novel aviation energy saving power device |
| US20100044504A1 (en) * | 2008-02-29 | 2010-02-25 | Airbus France | Rear propulsion system with lateral air inlets for an aircraft with such system |
| US20140263824A1 (en) * | 2013-03-13 | 2014-09-18 | Rolls-Royce North American Technologies, Inc. | Generator for flight vehicle |
| CN204452946U (en) * | 2015-01-22 | 2015-07-08 | 谭现东 | Aviation aircraft |
-
2015
- 2015-01-22 CN CN201510032337.5A patent/CN104590567A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4478378A (en) * | 1981-10-15 | 1984-10-23 | Aeritalia-Societa Aerospaziale Italiana-Per Azioni | Aircraft with jet propulsion |
| CN1779224A (en) * | 2004-11-05 | 2006-05-31 | 通用电气公司 | Thrust vectoring aft FLADE engine |
| CN2900357Y (en) * | 2006-04-07 | 2007-05-16 | 叶万章 | Novel aviation energy saving power device |
| US20100044504A1 (en) * | 2008-02-29 | 2010-02-25 | Airbus France | Rear propulsion system with lateral air inlets for an aircraft with such system |
| US20140263824A1 (en) * | 2013-03-13 | 2014-09-18 | Rolls-Royce North American Technologies, Inc. | Generator for flight vehicle |
| CN204452946U (en) * | 2015-01-22 | 2015-07-08 | 谭现东 | Aviation aircraft |
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Application publication date: 20150506 |
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