CN201132609Y - Invisible energy-conserving VTOL aircraft - Google Patents
Invisible energy-conserving VTOL aircraft Download PDFInfo
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- CN201132609Y CN201132609Y CNU2007200155629U CN200720015562U CN201132609Y CN 201132609 Y CN201132609 Y CN 201132609Y CN U2007200155629 U CNU2007200155629 U CN U2007200155629U CN 200720015562 U CN200720015562 U CN 200720015562U CN 201132609 Y CN201132609 Y CN 201132609Y
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- electrical motor
- engine
- hydraulic
- fuselage
- launcher
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- 238000009434 installation Methods 0.000 claims abstract description 9
- 238000004134 energy conservation Methods 0.000 claims description 9
- 239000002828 fuel tank Substances 0.000 claims description 6
- 238000005452 bending Methods 0.000 claims description 5
- 239000002131 composite material Substances 0.000 abstract description 7
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 230000005540 biological transmission Effects 0.000 abstract 1
- 206010022000 influenza Diseases 0.000 abstract 1
- 208000002925 dental caries Diseases 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 239000000295 fuel oil Substances 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- IWEDIXLBFLAXBO-UHFFFAOYSA-N dicamba Chemical compound COC1=C(Cl)C=CC(Cl)=C1C(O)=O IWEDIXLBFLAXBO-UHFFFAOYSA-N 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
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Abstract
The utility model relates to an energy-saving stealth jump-jet, comprising a jump-jet body, a power installation, a hydraulic transmission gear, and a guided missile launcher. The jump-jet body is made of composite material; two inlet channels are arranged at the lower part of a main body, and the tails thereof are jointed to form a front-row air flue; a left fresh flue and a right fresh flue of rear engines are symmetrically arranged on the lower part of the jump-jet body, and are connected with an exhaust airway of the rear engines; the rear parts of the fresh flues of the rear engines are communicated with the front end of the inlet channel of a boost engine; the rear end of the inlet channel of the boost engine is jointed to form a tail gas exhaust passage. The power installation comprises a central unit, a front engine and the rear engines; an end shaft wheel of the engine is connected with an electric generator wheel through a strap; the output terminal of an electric generator is respectively connected with the front engine and three rear engines through leads. The guided missile launcher adopts a launching shoe hydraulic cylinder to be fixed in a main body cavity, and a connecting rod at the front end of the launching shoe hydraulic cylinder is fixed and connected with a missile launcher. A missile is fixed on the missile launcher through a cartridge clip. The energy-saving stealth jump-jet has the advantages of skillful conception, compact structure and simple manufacture.
Description
Technical field
The utility model relates to aircraft, concrete is a kind of stealth, energy-conservation, vertical take-off and landing aircraft (VTOL aircraft).
Background technology
Along with rapid development of science and technology, aeronautical technology more and more are subject to people's attention, especially the stealthy problem of aircraft is the emphasis problem that the professional studies always, at present the housing of aircraft all adopts metal, will return to penetrate and be received discovery when meeting the radar radiowave.Both be that fuselage is reformed, take certain stealthy measure, but parts such as the driving engine of work still is that metal is made in the machine, this effect to airplane hidden can be brought certain influence, in addition, aero-engine is to convert power to by fuel oil, this means the wake flame that ejects from engine nozzle, can find aircraft whereabouts on high with infrared detector, this stealth to aircraft also is a big problem naturally in the same old way.
Though at present aircraft is various informative in a word, performance is different, all exists in the stealth, to the consumption of fuel oil and on the mode of landing not allow the problem ignored.The fuel utilization ratio of aero-engine is lower even have some oil gas also not come behind driving engine and burning just together sprays in the air with jet, and this has constituted pollution to air, and what is more important is a kind of great waste to the energy.Also have the landing of present aircraft all need pass through runway, do not have the function of vertical lift, this all is a big problem to the alerting ability of aircraft and the construction investment on airport.
Summary of the invention
The purpose of this utility model is to possess the problem of vertical lift performance greatly and not in order to solve present airplane hidden poor performance, to consume energy, and provides a kind of stealth energy-conservation vertical take-off and landing aircraft (VTOL aircraft).
The technical scheme that adopts is:
Stealthy energy-conservation vertical take-off and landing aircraft (VTOL aircraft) comprises body, engine installation, hydraulic actuator, guided missile launcher.
Described body is to make with composite material, body is provided with fuselage, front wing, rear wing and last empennage, the front portion of fuselage is provided with cockpit, is provided with the front support bracket of lateral support fuselage in the fuselage cavity of cockpit back, and the bottom of front support bracket is symmetrically arranged with two cover center units.Underbelly at unit position, center is provided with two inlet channels, the afterbody tandem of inlet channel is a front exhaust, on the inlet channel front portion, be provided with preceding fuel tank in the fuselage cavity, center and the middle central support that is provided with of rear wing at front support bracket, two rear engine air inlet ducts about being symmetrically arranged with below the mmi machine wing and the fuselage connecting portion, about the rear portion of two rear engine air inlet ducts be connected with the front end of boost engine inlet channel respectively, the rear end tandem of two boost engine inlet channels is the tail gas exhaust duct, the rear engine air inlet duct is connected with the rear engine air exhausting duct, the front end of rear engine air inlet duct is connected with inlet channel, the symmetrical fuel tank that is provided with in the inner chamber of two front wings.
Described engine installation comprises two cover center units, electrical motor behind preceding electrical motor, three platforms; Described center unit is made up of driving engine, electrical generator and hydraulic compressor, the housing of driving engine, electrical generator and hydraulic compressor is formed by the composite material compacting, the arbor wheel that goes out of driving engine is rotationally connected by belt and generating wheel, generator output end is connected with electrical motor behind three platforms with preceding electrical motor by lead is corresponding respectively, preceding electrical motor is arranged in front-seat air flue, captives joint with exhaust duct.Electrical motor lays respectively at behind tail gas exhaust duct and two in the electrical motor air exhausting duct behind three platforms, and captives joint with the inwall of electrical motor air exhausting duct after two with the tail gas exhaust duct respectively.The electrical motor air exhausting duct is trapezoidal tubular ring by the elevation profile and combines behind tail gas exhaust duct and two, per two tubular ring phase interlocks and middle with soft circle pad sealing, the top of electrical motor air exhausting duct profile afterbody is fixed with a connecting rod that has 90 ° of crooked camber lines behind tail gas exhaust duct and two, both sides are fixed by the two joint movable rods that can be bent into 90 °, and the camber line connecting rod is connected with the hydraulic compressor outlet by hydraulic tubing with movable rod.
Described guided missile launcher comprises missile launcher, launcher hydraulic actuating cylinder, and the launcher hydraulic actuating cylinder is fixedly connected in the fuselage cavity, and the preceding end link of launcher hydraulic actuating cylinder is captiveed joint with missile launcher.Guided missile is fixedly connected on the missile launcher by cartridge clip, and missile launcher is positioned at the MISSILE LAUNCHING storehouse;
Described hydraulic actuator comprises that a plurality of missile launcher hydraulic actuating cylinders, MISSILE LAUNCHING Cang Dibuwaikeguan open hydraulic actuating cylinder, three hydraulic actuating cylinders of controlling tail gas exhaust duct and back electrical motor air exhausting duct respectively; Hydraulic compressor is positioned at the center unit, hydraulic compressor is connected with electrical generator by lead in the unit of center, and hydraulic compressor is opened hydraulic actuating cylinder, front-seat air flue hydraulic actuating cylinder, tail gas exhaust duct and the hydraulic actuating cylinder of back electrical motor air exhausting duct with missile launcher hydraulic actuating cylinder, MISSILE LAUNCHING Cang Dibuwaikeguan respectively by hydraulic tubing respectively and is connected;
The bottom in above-mentioned MISSILE LAUNCHING storehouse is provided with a shell, and shell and fuselage are hinged.
The shaft of electrical motor installing screw propeller before above-mentioned.
The shaft installing impeller of above-mentioned a plurality of backs electrical motor.
The utility model job procedure:
When launching a guided missile, needs open the MISSILE LAUNCHING door at cockpit, control launcher hydraulic actuating cylinder, making the connecting rod of its front end stretch out and promote missile launcher leans out outside the fuselage, press the launch intruction key, following MISSILE LAUNCHING is gone out, top guided missile has substituted the guided missile position of just having launched under the effect of cartridge clip spring and guided missile gravity, wait for next launch intruction.
Control the launcher hydraulic actuating cylinder by the aviator after battery has fired, make the connecting rod withdrawal of its front end, missile launcher is collected, and the MISSILE LAUNCHING door is closed, and MISSILE LAUNCHING door and fuselage match, and not only play stealthy effect but also reduce flight resistance.
Fuselage is by the composite material extrusion forming, and whole fuselage does not have opening and seam, does not more have prominent salient points such as metal rivet, and smooth surface is stealthy respond well, reduces fuselage fleetline flight resistance simultaneously.The body of electrical generator and driving engine is all formed by the composite material compacting, therefore increases stealthy effect.
The engine installation of integrated airplane is an electrical motor, what the electrical motor impeller sprayed backward is the wake flame that air rather than one powerful, available infrared detector detect, engine body exterior is coated with the invisible coating of radio wave absorbing again simultaneously, and stealthy effect is highly desirable.
The forebody of aircraft has the electrical motor of a downward thrust, it is just worked when takeoff and landing, the electrical motor air channel of back can 90 ° of bendings, can carry out 90 ° of bendings under the tail gas exhaust duct of back and the effect of back electrical motor air exhausting duct in hydraulic efficiency pressure system when aircraft is prepared lift-off or landed, aircraft just can carry out vertical takeoff and landing like this.When aircraft aloft during normal flight the tail gas exhaust duct of back and back electrical motor air exhausting duct revert to horizontality.
The utility model is skillfully constructed, original, compact conformation, tight, and whole investment is little, and low production cost is made simple.
Need to prove: under the prerequisite that does not change principle of the present utility model and design, change of having done or distortion all belong to protection domain of the present utility model.
Description of drawings
Fig. 1 is the utility model structural representation.
Fig. 2 is a missile launcher scheme drawing of the present utility model.
Fig. 3 is tail gas exhaust duct of the present utility model and back electrical motor air exhausting duct contour structures scheme drawing.
Fig. 4 is tail gas exhaust duct of the present utility model and back electrical motor air exhausting duct case of bending scheme drawing.
The specific embodiment
Embodiment
Stealthy energy-conservation vertical take-off and landing aircraft (VTOL aircraft) comprises body, engine installation, hydraulic actuator, guided missile launcher.Body is to make with composite material, body is provided with fuselage 22, front wing 14, rear wing 13 and last empennage 12, the front portion of fuselage 22 is provided with cockpit 1, be provided with the front support bracket 2 of lateral support fuselage in fuselage 22 cavitys of cockpit 1 back, the bottom of front support bracket 2 is symmetrically arranged with two cover center units 3.Fuselage 22 bottoms at center unit 3 positions are provided with two inlet channels 4, the afterbody tandem of inlet channel 4 is a front-seat air flue 19, fuel tank 6 before on inlet channel 4 front portions, being provided with in fuselage 22 cavitys, center and the middle central support 7 that is provided with of rear wing at front support bracket 2, two rear engine air inlet ducts 9 about the mmi machine wing 14 is symmetrically arranged with below fuselage 22 connecting portions, about the rear portion of two rear engine air inlet ducts 9 be connected with the front end of boost engine inlet channel 10 respectively, the rear end tandem of two boost engine inlet channels 10 is a tail gas exhaust duct 18, rear engine air inlet duct 9 is connected with rear engine air exhausting duct 17, the front end of rear engine air inlet duct 9 is connected with inlet channel 16, the symmetrical fuel tank 15 that is provided with in the inner chamber of two front wings 14.
Engine installation comprises two cover center units 3, electrical motor 11 behind preceding electrical motor 5, three platforms; Described center unit 3 is made up of driving engine, electrical generator and hydraulic compressor, the housing of driving engine, electrical generator and hydraulic compressor is formed by the composite material compacting, the arbor wheel that goes out of driving engine is rotationally connected by belt and generating wheel, generator output end is connected with electrical motor 11 behind three platforms with preceding electrical motor 5 by lead is corresponding respectively, preceding electrical motor 5 is arranged in front-seat air flue 19, captive joint the shaft installing screw propeller of preceding electrical motor 5 with exhaust duct 19.Electrical motor 11 lays respectively at behind tail gas exhaust duct 18 and two in the electrical motor air exhausting duct 17 behind three platforms, and captive joint with the inwall of electrical motor air exhausting duct 17 after two with tail gas exhaust duct 18 respectively, electrical motor air exhausting duct 17 is trapezoidal tubular ring 25 by the elevation profile and combines behind tail gas exhaust duct 18 and two, per two tubular rings, 25 phase interlocks and middle with soft circle pad 26 sealings, the top of electrical motor air exhausting duct 17 profile afterbodys is fixing with a camber line connecting rod 20 that has 90 ° of bendings behind tail gas exhaust duct 18 and two, both sides are fixed by the movable rod 28 that can be bent into 90 ° two joints, and camber line connecting rod 20 is connected with the hydraulic compressor outlet by hydraulic tubing with movable rod 28.The shaft installing impeller of back electrical motor 11.
Guided missile launcher comprises missile launcher 24, launcher hydraulic actuating cylinder 21, and launcher hydraulic actuating cylinder 21 is fixedly connected in fuselage 22 cavitys, and the preceding end link of launcher hydraulic actuating cylinder 21 is captiveed joint with missile launcher 24.Guided missile is fixedly connected on the missile launcher 24 by cartridge clip 23, and missile launcher 24 is positioned at MISSILE LAUNCHING storehouse 8; The bottom in MISSILE LAUNCHING storehouse 8 is provided with a shell, and shell and fuselage 22 are hinged.
Hydraulic actuator comprises that a plurality of missile launcher hydraulic actuating cylinders 21, MISSILE LAUNCHING storehouse 8 bottom enclosure close and opens hydraulic actuating cylinder, three hydraulic actuating cylinders of controlling tail gas exhaust duct 18 and back electrical motor air exhausting duct 17 respectively; Hydraulic compressor is positioned at center unit 3, hydraulic compressor is connected with electrical generator by lead in center unit 3, and hydraulic compressor is opened hydraulic actuating cylinder, tail gas exhaust duct 18 and back electrical motor air exhausting duct 17 outer link with missile launcher hydraulic actuating cylinder 21, MISSILE LAUNCHING storehouse 8 bottom enclosure pass respectively by hydraulic tubing respectively and is connected.
Claims (4)
1, stealthy energy-conservation vertical take-off and landing aircraft (VTOL aircraft) comprises body, engine installation, hydraulic actuator, guided missile launcher; Described body is provided with fuselage (22), front wing (14), rear wing (13) and last empennage (12), and the front portion of fuselage (22) is provided with cockpit (1), it is characterized in that:
Be provided with the front support bracket (2) of lateral support fuselage in fuselage (22) cavity of described cockpit (1) back, the bottom of front support bracket (2) is symmetrically arranged with two cover center units (3), fuselage (22) bottom at center unit (3) position is provided with two inlet channels (4), the afterbody tandem of inlet channel (4) is a front-seat air flue (19), on inlet channel (4) is anterior, be provided with preceding fuel tank (6) in fuselage (22) cavity, center and the middle central support (7) that is provided with of rear wing at front support bracket (2), two rear engine air inlet ducts (9) about the mmi machine wing (14) is symmetrically arranged with below fuselage (22) connecting portion, about the rear portion of two rear engine air inlet ducts (9) be connected with the front end of boost engine inlet channel (10) respectively, the rear end tandem of two boost engine inlet channels (10) is tail gas exhaust duct (18), rear engine air inlet duct (9) is connected with rear engine air exhausting duct (17), the front end of rear engine air inlet duct (9) is connected with inlet channel (16), the symmetrical fuel tank (15) that is provided with in the inner chamber of two front wings (14);
Described engine installation comprises two cover center units (3), electrical motor (11) behind preceding electrical motor (5), three platforms; Described center unit (3) is made up of driving engine, electrical generator and hydraulic compressor, the arbor wheel that goes out of driving engine is rotationally connected by belt and generating wheel, generator output end is connected with electrical motor (11) behind three platforms with preceding electrical motor (5) by lead is corresponding respectively, preceding electrical motor (5) is arranged in front-seat air flue (19), captives joint with exhaust duct (19); Electrical motor behind three platforms (11) lays respectively at behind tail gas exhaust duct (18) and two in the electrical motor air exhausting duct (17), and captives joint with the inwall of electrical motor air exhausting duct (17) after two with tail gas exhaust duct (18) respectively; Electrical motor air exhausting duct (17) is combined by tubular ring (25) behind tail gas exhaust duct (18) and two, per two tubular rings (25) phase interlock and centre seal with soft circle pad (26), the top of electrical motor air exhausting duct (17) profile afterbody is fixing with a camber line connecting rod (20) that has 90 ° of bendings behind tail gas exhaust duct (18) and two, both sides are fixing by the two joint movable rods (28) that can be bent into 90 °, and camber line connecting rod (20) is connected with the hydraulic compressor outlet by hydraulic tubing with movable rod (28);
Described guided missile launcher comprises missile launcher (24), launcher hydraulic actuating cylinder (21), and launcher hydraulic actuating cylinder (21) is fixedly connected in fuselage (22) cavity, and the preceding end link of launcher hydraulic actuating cylinder (21) is captiveed joint with missile launcher (24); Guided missile is fixedly connected on the missile launcher (24) by cartridge clip (23), and missile launcher (24) is positioned at MISSILE LAUNCHING storehouse (8);
Described hydraulic actuator comprises that a plurality of missile launcher hydraulic actuating cylinders (21), MISSILE LAUNCHING storehouse (8) bottom enclosure close and opens hydraulic actuating cylinder, three and control the tail gas exhaust duct (18) and the back hydraulic actuating cylinders of electrical motor air exhausting duct (17) respectively; Hydraulic compressor is positioned at center unit (3), hydraulic compressor is connected with electrical generator by lead in center unit (3), and hydraulic compressor closes the hydraulic actuating cylinder of opening hydraulic actuating cylinder, front-seat air flue (19) hydraulic actuating cylinder, tail gas exhaust duct (18) and back electrical motor air exhausting duct (17) with missile launcher hydraulic actuating cylinder (21), MISSILE LAUNCHING storehouse (8) bottom enclosure respectively by hydraulic tubing respectively and is connected.
2, the energy-conservation vertical take-off and landing aircraft (VTOL aircraft) of stealth according to claim 1 is characterized in that: the bottom in above-mentioned MISSILE LAUNCHING storehouse (8) is provided with a shell, and shell and fuselage (22) are hinged.
3, the energy-conservation vertical take-off and landing aircraft (VTOL aircraft) of stealth according to claim 1 is characterized in that: the shaft of electrical motor (5) installing screw propeller before above-mentioned.
4, the energy-conservation vertical take-off and landing aircraft (VTOL aircraft) of stealth according to claim 1 is characterized in that: the shaft installing impeller of above-mentioned a plurality of back electrical motors (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007200155629U CN201132609Y (en) | 2007-10-30 | 2007-10-30 | Invisible energy-conserving VTOL aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007200155629U CN201132609Y (en) | 2007-10-30 | 2007-10-30 | Invisible energy-conserving VTOL aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201132609Y true CN201132609Y (en) | 2008-10-15 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2007200155629U Expired - Fee Related CN201132609Y (en) | 2007-10-30 | 2007-10-30 | Invisible energy-conserving VTOL aircraft |
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| Country | Link |
|---|---|
| CN (1) | CN201132609Y (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103717912A (en) * | 2011-07-26 | 2014-04-09 | 空中客车德国运营有限责任公司 | Hydraulic motor-pump-arrangement and hydraulic system for a vehicle |
-
2007
- 2007-10-30 CN CNU2007200155629U patent/CN201132609Y/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103717912A (en) * | 2011-07-26 | 2014-04-09 | 空中客车德国运营有限责任公司 | Hydraulic motor-pump-arrangement and hydraulic system for a vehicle |
| CN103717912B (en) * | 2011-07-26 | 2016-10-05 | 空中客车德国运营有限责任公司 | Hydraulic motor-pump installation and the hydraulic system for the vehicles |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20081015 Termination date: 20091130 |