CN204433072U - A kind of canard with vector spout and a kind of aircraft - Google Patents
A kind of canard with vector spout and a kind of aircraft Download PDFInfo
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- CN204433072U CN204433072U CN201520044728.4U CN201520044728U CN204433072U CN 204433072 U CN204433072 U CN 204433072U CN 201520044728 U CN201520044728 U CN 201520044728U CN 204433072 U CN204433072 U CN 204433072U
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- canard
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Abstract
The utility model discloses a kind of canard with vector spout and a kind of aircraft, canard with vector spout comprises canard and is arranged on the air jet system for generation of the wing direction air-flow towards aircraft on described canard, described air jet system comprises the inlet channel, air compressor, combustion chamber, turbine, jet pipe, multiple guide piece and the flat mouth jet pipe that set gradually, and described guide piece is for making the combustion gas in described jet pipe form uniform air-flow and being sprayed by described flat mouth jet pipe.The invention also discloses a kind of aircraft.By the utility model, the problem that canard configuration faces upward in At High Angle of Attack pitching moment can be solved.
Description
Technical field
The utility model relates to aircraft circles, in particular to a kind of canard with vector spout and a kind of aircraft.
Background technology
Along with the development of active control technology, the maturation of Flight By Wire technology, designs front wing larger (relative area 8%-15%) form so-called nearly coupling canard configuration near wing and become a reality.Canard configuration's At High Angle of Attack superior performance is also a kind of aerodynamic arrangement's form with high maneuverability energy.But the difficult point of canard configuration is the problem that the selection of canard position and At High Angle of Attack pitching moment are faced upward.Because canard area is large, the lift of generation is before center of gravity, and pitching moment is faced upward seriously when At High Angle of Attack, due to without horizontal tail, how to ensure that having enough operating torques of bowing at At High Angle of Attack becomes a difficult problem.
Utility model content
Technical problem to be solved in the utility model is, provides a kind of canard solving the problem that canard configuration faces upward in At High Angle of Attack pitching moment.
Therefore, the technical solution of the utility model is as follows:
A kind of canard with vector spout, comprise canard and be arranged on the air jet system for generation of the wing direction air-flow towards aircraft on described canard, described air jet system comprises the inlet channel, air compressor, combustion chamber, turbine, jet pipe, multiple guide piece and the flat mouth jet pipe that set gradually, and described guide piece is for making the combustion gas in described jet pipe form uniform air-flow and being sprayed by described flat mouth jet pipe.
By this technical scheme, the problem that canard configuration faces upward in At High Angle of Attack pitching moment can be solved, and the air-flow of canard driving engine passes through upper surface of the airfoil, aircraft is made to obtain lift augment in flight course, reduce the minimum flying speed of aircraft, shorten taking off and landing run of aircraft, and upper surface of the airfoil boundary-layer can be suppressed to be separated.
The utility model additionally provides a kind of aircraft, comprise the canard of the band vector spout described in body, wing and technique scheme, the canard of described band vector spout is arranged on the front end of described body, described wing is arranged on described body, and the height of described canard is higher than the center of gravity of described aircraft and described wing.
Accompanying drawing explanation
Fig. 1 is the birds-eye view of the canard of band vector spout according to the utility model embodiment;
Fig. 2 is the block diagram of the canard of band vector spout according to the utility model embodiment;
Fig. 3 is the front view of the aircraft according to the utility model embodiment;
Fig. 4 is the lateral plan of aircraft in Fig. 3.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the utility model is described in further detail.It should be noted that, when not conflicting, the feature in the embodiment of the application and embodiment can combine mutually.
As depicted in figs. 1 and 2, according to the canard of the band vector spout of embodiment of the present utility model, the air jet system comprising canard 1 and be arranged on for generation of the wing direction air-flow towards aircraft on described canard 1, described air jet system comprises the inlet channel 2, air compressor 3, combustion chamber 4, turbine 5, jet pipe 6, multiple guide piece 7 and the flat mouth jet pipe 8 that set gradually, and described guide piece 7 is for making the combustion gas in described jet pipe 6 form uniform air-flow and being sprayed by described flat mouth jet pipe 8.
The canard of the band vector spout in this technical scheme, become the canard configuration with vector spout, this layout can not only solve the problem that canard configuration faces upward in At High Angle of Attack pitching moment, and the air-flow of canard driving engine passes through upper surface of the airfoil, aircraft is made to obtain lift augment in flight course, reduce the minimum flying speed of aircraft, shorten taking off and landing run of aircraft; Nozzle is become flat, make driving engine can form vector power with the deflection of canard, and make the vertical position of vertical position higher than wing of canard, the center of gravity of airplane is arranged on below canard, when aircraft is in At High Angle of Attack state, the vertical coordinate position of aircraft due to spout is higher than center of gravity of airplane position, then now canard spout produces the moment that aircraft is bowed, thus the nose-up pitching moment that balance canard produces under At High Angle of Attack attitude, make aircraft also have good road-holding property when At High Angle of Attack.The air-flow of canard driving engine, by upper surface of the airfoil, makes aircraft obtain lift augment in flight course, reduces the minimum flying speed of aircraft, reaches and shortens taking off and the object of landing run of aircraft.
By this technical scheme, the problem that canard configuration faces upward in At High Angle of Attack pitching moment can be solved, and the air-flow of canard driving engine passes through upper surface of the airfoil, aircraft is made to obtain lift augment in flight course, reduce the minimum flying speed of aircraft, shorten taking off and landing run of aircraft, and upper surface of the airfoil boundary-layer can be suppressed to be separated.
As shown in Figure 3 and Figure 4, the utility model additionally provides a kind of aircraft, comprise the canard of body 10, wing 11 and the band vector spout described in technique scheme, the canard of described band vector spout is arranged on the front end of described body 10, described wing 11 is arranged on described body 10, and the height of described canard 1 is higher than the center of gravity of described aircraft and described wing 11.
When the canard of the band vector spout in the utility model and aircraft work: air successfully introduces air compressor 3 by inlet channel 2 with minimum flow losses, and air compressor 3 to do work pressurized air to air with High Rotation Speed, improves the pressure of air; High pressure air mixes with fuel oil in combustion chamber 4, and converts chemical energy is heat energy by burning, forms the combustion gas of High Temperature High Pressure; First the combustion gas of High Temperature High Pressure expands in turbine 5, promotes turbine 5 and rotates, and goes to drive air compressor 3; Then combustion gas continues to expand in jet pipe 6, accelerates combustion gas, improves the speed of combustion gas, combustion gas is sprayed with higher speed.The High Rotation Speed gas sprayed from jet pipe 6 is become the gas that evenly flows backward and enters flat mouth jet pipe 8 by guide piece 7, gas from flat mouth jet pipe 8 out afterwards through wing 11 upper surface, wing 11 upper surface air-flow is accelerated, aircraft is made to obtain lift augment in flight course, reduce the minimum flying speed of aircraft, shorten taking off and landing run of aircraft.When aircraft is in At High Angle of Attack attitude, the vertical coordinate position of aircraft due to flat mouth jet pipe 8 is higher than the center of gravity of airplane 9 position, therefore the air-flow that flat mouth jet pipe 8 sprays has the moment making body 10 bow around center of gravity 9 for aircraft, thus the problem that solution canard configuration faces upward in At High Angle of Attack pitching moment.
In sum, content of the present utility model is not limited in the above-described embodiment, and those skilled in the art can propose other embodiment within technical director's thought of the present utility model, but this embodiment is all included within scope of the present utility model.
Claims (2)
1. the canard with vector spout, it is characterized in that, comprise canard (1) and be arranged on the air jet system for generation of the wing direction air-flow towards aircraft on described canard (1), described air jet system comprises the inlet channel (2), air compressor (3), combustion chamber (4), turbine (5), jet pipe (6), multiple guide piece (7) and the flat mouth jet pipe (8) that set gradually, and described guide piece (7) is for making the combustion gas in described jet pipe (6) form uniform air-flow and being sprayed by described flat mouth jet pipe (8).
2. an aircraft, it is characterized in that, comprise the canard of body (10), wing (11) and band vector spout as described in claim 1, the canard of described band vector spout is arranged on the front end of described body (10), described wing (11) is arranged on described body (10), and the height of described canard (1) is higher than the center of gravity of described aircraft and described wing (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520044728.4U CN204433072U (en) | 2015-01-22 | 2015-01-22 | A kind of canard with vector spout and a kind of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520044728.4U CN204433072U (en) | 2015-01-22 | 2015-01-22 | A kind of canard with vector spout and a kind of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204433072U true CN204433072U (en) | 2015-07-01 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520044728.4U Expired - Fee Related CN204433072U (en) | 2015-01-22 | 2015-01-22 | A kind of canard with vector spout and a kind of aircraft |
Country Status (1)
| Country | Link |
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| CN (1) | CN204433072U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105366049A (en) * | 2015-11-24 | 2016-03-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Vertical takeoff and landing unmanned aerial vehicle |
| CN107271135A (en) * | 2015-10-28 | 2017-10-20 | 中国航空工业集团公司沈阳飞机设计研究所 | The wind tunnel system of model aircraft experiment is promoted for vector |
-
2015
- 2015-01-22 CN CN201520044728.4U patent/CN204433072U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107271135A (en) * | 2015-10-28 | 2017-10-20 | 中国航空工业集团公司沈阳飞机设计研究所 | The wind tunnel system of model aircraft experiment is promoted for vector |
| CN107389296A (en) * | 2015-10-28 | 2017-11-24 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of model aircraft for wind-tunnel |
| CN107389292A (en) * | 2015-10-28 | 2017-11-24 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of wind tunnel system for vector propulsion trial |
| CN105366049A (en) * | 2015-11-24 | 2016-03-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Vertical takeoff and landing unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150701 Termination date: 20160122 |
|
| EXPY | Termination of patent right or utility model |