CN201287827Y - Aircraft capable of hiding in side direction - Google Patents
Aircraft capable of hiding in side direction Download PDFInfo
- Publication number
- CN201287827Y CN201287827Y CNU2008203026075U CN200820302607U CN201287827Y CN 201287827 Y CN201287827 Y CN 201287827Y CN U2008203026075 U CNU2008203026075 U CN U2008203026075U CN 200820302607 U CN200820302607 U CN 200820302607U CN 201287827 Y CN201287827 Y CN 201287827Y
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- CN
- China
- Prior art keywords
- aircraft
- fuel tank
- fuselage
- partition board
- reflective partition
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Abstract
The utility model discloses a flying vehicle which can laterally conceal, which comprises a traditional fixed-wing aircraft, a rotary-wing aircraft, a soft-wing aircraft or a jet type engine missile, wherein two sides in a flying vehicle (1) are symmetrically provided with an inclined reflective-type fuel tank baffle plate (2), and an engine body integral fuel tank (3) which is arranged along the length direction of the engine body of the flying vehicle (1) is formed by the reflective-type fuel tank baffle plate (2) and two lateral surfaces of the flying vehicle (1). The flying vehicle utilizes fuel oil in the engine body integral fuel tanks on two lateral surfaces to reduce radar wave emitted by surveillance radar, thereby achieving lateral stealth of the flying vehicle. The flying vehicle not only has the advantages of lateral stealth, but also has the advantages of effectively utilizing the engine body structure space of the flying vehicle, and having simple structure and convenient manufacture.
Description
Technical field
The utility model relates to a kind of aircraft of energy side invisible, belongs to aircraft stealth technology field.
Background technology
At present, the fuel tank that installs on the existing aircraft fuselage generally all is arranged near the center of gravity of aircraft, this fuel tank is arranged near the aircraft center of gravity structure, must utilize high position, space, thereby the central space that takies aircraft fuselage structures is excessive, and makes the installation of aircraft finished product be subjected to limitation; Because its fuel tank is arranged in the inboard of aircraft fuselage structures, therefore existing aircraft fuel tank only is to play the effect that fuel oil stores simultaneously, and it is stealthy to help aircraft to carry out, and makes its fuel tank performance fail to make full use of.
The utility model content
The purpose of this utility model is: provide a kind of and can help the aircraft side invisible, can effectively utilize aircraft fuselage structures space and aircraft that can side invisible simple in structure, easy to make again, to overcome the deficiencies in the prior art.
The utility model is achieved in that it is to improve to form on the basis of the aircraft of routine, promptly the bilateral symmetry in aircraft is provided with the reflective Partition board for fuel tank of bevelled, the common fuselage integral tank of arranging along the aircraft fuselage length direction of forming of two lateral surfaces of reflective Partition board for fuel tank and aircraft.
Be provided with the ventilation pore at the upper position place of the reflective Partition board for fuel tank that constitutes the fuselage integral tank and have the oil transportation mouth of lid, be provided with the drain oil that has seal cover cap in the lower position of reflective Partition board for fuel tank.
The number of degrees of the angle of the vertical summetry axial plane of the inclined-plane of the reflective Partition board for fuel tank of bevelled and aircraft are 10 °～40 °.
The fuselage integral tank that the common composition of two lateral surfaces of the reflective Partition board for fuel tank of bilateral symmetry setting and aircraft is arranged along the aircraft fuselage length direction in aircraft is two independently fuselage integral tanks, or be 4～20 independently fuselage integral tanks, and be symmetrically distributed in the both sides of aircraft.
Aircraft is fixed wing aircraft, cyclogyro, soft wing machine or jet engine guided missile.
The covering of the side fuselage of aircraft is the electromagnetic wave transparent material covering.
The electromagnetic wave transparent material covering of aircraft side fuselage is the electromagnetic wave transparent material covering of glass-felt plastic, conventional canopy material or radome material.
Reflective Partition board for fuel tank is the dividing plate made of electromagnetic wave transparent material not.
Reflective Partition board for fuel tank is the dividing plate that metallic material, metal coating material or the aluminum alloy materials of not saturating ripple made.
Owing to adopted technique scheme, the utility model to effectively utilize the aircraft fuselage structures space, and effectively utilize the radar wave that the fuel oil in the fuel tank launches reconnaissance radar and decayed, thereby realized the side invisible of aircraft well.When the radar wave of reconnaissance radar saw through the fuselage of aircraft, the fuel oil in the integral tank made the radar wave decay, thereby makes radar be difficult to detect the radar wave of reflected back; When fuel quantity in the fuel tank reduces, radar wave sees through the outside of aircraft fuselage and is mapped on the reflective Partition board for fuel tank, after the reflection of reflective Partition board for fuel tank, most of radar wave is reflected in the fuel oil and decays, other small part radar wave is reflected to the emphasis direction of non-detection, thereby makes the aircraft fuselage side invisible.So the utility model is compared with prior art, the utility model not only have can side invisible advantage, can effectively utilize aircraft fuselage structures space, advantage simple in structure, easy to make but also have.
Description of drawings
Fig. 1 is an architecture scheme drawing of the present utility model;
Fig. 2 is that the A-A of Fig. 1 shows scheme drawing to cuing open.
Being labeled as of accompanying drawing: 1-aircraft, the reflective Partition board for fuel tank of 2-, 3-fuselage integral tank, the 4-pore of ventilating, 5-oil transportation mouth, 6-drain oil.
The specific embodiment
The utility model is described in further detail below in conjunction with embodiment, but not as to restriction of the present utility model.
Embodiment of the present utility model: structural representation of the present utility model as depicted in figs. 1 and 2, comprise traditional aircraft 1, this aircraft 1 can be traditional fixed wing aircraft, cyclogyro, soft wing machine or jet engine guided missile, during making, bilateral symmetry in aircraft 1 is provided with the reflective Partition board for fuel tank 2 of bevelled, makes the number of degrees of angle α of the vertical summetry axial plane of the inclined-plane of the reflective Partition board for fuel tank 2 of bevelled and aircraft 1 be controlled at 10 °～40 ° scope; And the fuselage integral tank 3 that reflective Partition board for fuel tank 2 and the common composition of two lateral surfaces of aircraft 1 are arranged along aircraft 1 fuselage length direction; The common quantity of forming the fuselage integral tank of arranging along aircraft 1 fuselage length direction 3 of reflective Partition board for fuel tank 2 and two lateral surfaces of aircraft 1 can be made as two independently fuselage integral tanks, or adopt separator of battery plates to be made as 4～20 independently fuselage integral tanks, and be symmetrically distributed in the both sides of aircraft 1; Preferably the side fuselage skin of aircraft 1 is made (for example can adopt electromagnetic wave transparent materials such as glass-felt plastic, conventional canopy manufacturing materials or radome manufacturing materials to make) with electromagnetic wave transparent material during making, the manufacturing materials of reflective Partition board for fuel tank 2 is made (for example adopt metallic material, metal coating material or aluminum alloy etc. not electromagnetic wave transparent material make) with electromagnetic wave transparent material not; For easy to use, produce ventilation pore 4 at the upper position place of the reflective Partition board for fuel tank 2 that constitutes fuselage integral tank 3 and have the oil transportation mouth 5 of lid, produce the drain oil 6 that has seal cover cap in the lower position of reflective Partition board for fuel tank 2.
The utility model is symmetrical arranged the fuselage integral tank of arranging along the aircraft fuselage length direction in the two sides of conventional aircraft, the fuselage integral tank that makes these both sides all wraps the two sides of aircraft, the radar wave that can utilize the fuel oil in the fuselage integral tank of two sides that reconnaissance radar is launched is like this decayed, thereby realizes the side invisible of aircraft.
Claims (9)
- The aircraft of [claim 1] a kind of energy side invisible, comprise aircraft (1), it is characterized in that, bilateral symmetry in aircraft (1) is provided with the reflective Partition board for fuel tank of bevelled (2), reflective Partition board for fuel tank (2) and the common fuselage integral tank of arranging along aircraft (1) fuselage length direction (3) of forming of two lateral surfaces of aircraft (1).
- The aircraft of [claim 2] energy according to claim 1 side invisible, it is characterized in that: be provided with ventilation pore (4) at the upper position place of the reflective Partition board for fuel tank (2) that constitutes fuselage integral tank (3) and have the oil transportation mouth (5) of lid, be provided with the drain oil (6) that has seal cover cap in the lower position of reflective Partition board for fuel tank (2).
- The aircraft of [claim 3] energy according to claim 1 side invisible, it is characterized in that: the number of degrees of the angle (α) of the vertical summetry axial plane of the inclined-plane of the reflective Partition board for fuel tank of bevelled (2) and aircraft (1) are 10 °～40 °.
- The aircraft of [claim 4] energy according to claim 1 side invisible, it is characterized in that: the reflective Partition board for fuel tank (2) that bilateral symmetry is provided with in aircraft (1) is two independently fuselage integral tanks with the fuselage integral tank (3) that the common composition of two lateral surfaces of aircraft (1) is arranged along aircraft (1) fuselage length direction, or be 4～20 independently fuselage integral tanks, and be symmetrically distributed in the both sides of aircraft (1).
- [claim 5] is characterized in that according to the aircraft of the described energy of arbitrary claim in the claim 1 to 7 side invisible: aircraft (1) is fixed wing aircraft, cyclogyro, soft wing machine or jet engine guided missile.
- The aircraft of [claim 6] energy according to claim 1 side invisible, it is characterized in that: the covering of the side fuselage of aircraft (1) is the electromagnetic wave transparent material covering.
- The aircraft of [claim 7] energy according to claim 6 side invisible, it is characterized in that: the electromagnetic wave transparent material covering of aircraft (1) side fuselage is the electromagnetic wave transparent material covering of glass-felt plastic, conventional canopy material or radome material.
- [claim 8] aircraft that can side invisible according to claim 1 is characterized in that: the dividing plate that reflective Partition board for fuel tank (2) is made for electromagnetic wave transparent material not.
- The aircraft of [claim 9] energy according to claim 8 side invisible is characterized in that: reflective Partition board for fuel tank (2) is the dividing plate that metallic material, metal coating material or the aluminum alloy materials of not saturating ripple made.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2008203026075U CN201287827Y (en) | 2008-10-31 | 2008-10-31 | Aircraft capable of hiding in side direction |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2008203026075U CN201287827Y (en) | 2008-10-31 | 2008-10-31 | Aircraft capable of hiding in side direction |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201287827Y true CN201287827Y (en) | 2009-08-12 |
Family
ID=40979501
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2008203026075U Expired - Lifetime CN201287827Y (en) | 2008-10-31 | 2008-10-31 | Aircraft capable of hiding in side direction |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201287827Y (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101792022A (en) * | 2010-03-16 | 2010-08-04 | 北京航空航天大学 | Small multipurpose unmanned aerial vehicle with oil tank embedded into blended wing body |
| CN103213683A (en) * | 2010-03-16 | 2013-07-24 | 北京航空航天大学 | Small multipurpose unmanned plane with oil tank embedded into blended wing body |
| CN103640685A (en) * | 2013-12-29 | 2014-03-19 | 陈俞任 | Glass fiber reinforced plastic bulletproof stealth aircraft with aluminum net keel |
| CN104411587A (en) * | 2012-05-02 | 2015-03-11 | 伊顿有限公司 | Aircraft fuel tank inerting system |
| CN108860630A (en) * | 2018-04-25 | 2018-11-23 | 成都飞机工业（集团）有限责任公司 | A kind of exhaust apparatus |
| CN109823516A (en) * | 2019-02-14 | 2019-05-31 | 成都飞机工业（集团）有限责任公司 | A kind of stealthy steering engine bulge of aircraft |
-
2008
- 2008-10-31 CN CNU2008203026075U patent/CN201287827Y/en not_active Expired - Lifetime
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101792022A (en) * | 2010-03-16 | 2010-08-04 | 北京航空航天大学 | Small multipurpose unmanned aerial vehicle with oil tank embedded into blended wing body |
| CN101792022B (en) * | 2010-03-16 | 2013-04-03 | 北京航空航天大学 | Small multipurpose unmanned aerial vehicle with oil tank embedded into blended wing body |
| CN103213683A (en) * | 2010-03-16 | 2013-07-24 | 北京航空航天大学 | Small multipurpose unmanned plane with oil tank embedded into blended wing body |
| CN104411587A (en) * | 2012-05-02 | 2015-03-11 | 伊顿有限公司 | Aircraft fuel tank inerting system |
| CN104411587B (en) * | 2012-05-02 | 2017-09-19 | 伊顿有限公司 | aircraft fuel tank inerting system |
| CN103640685A (en) * | 2013-12-29 | 2014-03-19 | 陈俞任 | Glass fiber reinforced plastic bulletproof stealth aircraft with aluminum net keel |
| CN108860630A (en) * | 2018-04-25 | 2018-11-23 | 成都飞机工业（集团）有限责任公司 | A kind of exhaust apparatus |
| CN109823516A (en) * | 2019-02-14 | 2019-05-31 | 成都飞机工业（集团）有限责任公司 | A kind of stealthy steering engine bulge of aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20090812 Effective date of abandoning: 20081031 |