CN104386237A - High-speed aircraft and cartridge - Google Patents
High-speed aircraft and cartridge Download PDFInfo
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- CN104386237A CN104386237A CN201410655140.2A CN201410655140A CN104386237A CN 104386237 A CN104386237 A CN 104386237A CN 201410655140 A CN201410655140 A CN 201410655140A CN 104386237 A CN104386237 A CN 104386237A
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Abstract
The invention discloses a high-speed aircraft which comprises a shell and an engine, wherein the shell is internally provided with an outer fluid passageway and an inner fluid passageway in sequence; the outer fluid passageway and the inner fluid passageway are communicated with the outside respectively through respective openings; the outer fluid passageway is communicated with an air suction hole of the engine; the shell is selectively provided with or not provided with wings. In addition, the invention also discloses another high-speed aircraft and a cartridge. The high-speed aircrafts and the cartridge have the beneficial effects that the direction of the drag force of fluid outside the aircraft shell, acting on the shell from outside to inside is changed, and the pressure difference is transferred from inside to outside in the opposite direction, so that the drag force of fluid of the flying aircraft is reduced, and the flying rate is improved.
Description
Technical field
The present invention relates to flight structure field, particularly relate to a kind of high-speed aircraft and ammunition.
Background technology
Since existing more than 100 year of today appearred in aircraft, the power of about 90% is had for overcoming above fluid resistance during aircraft flight, only remaining can not 10% power driven flight fast running, people design various fleetline fuselage to reduce fluid resistance, but effect is also bad, more run at high speed by more high-performance engine drive aircraft again, but speed is faster, fluid resistance is larger.
Also do not have up to now a kind of running gear on the go can effectively reduce fluid resistance Theories and methods occur, all running gears in a fluid rapid movement time, the energy consumption of about 90% is used for overcoming fluid resistance, and aircraft is no exception.Contriver has applied for the patent of invention of nearly 40 relevant flight device aspects at home and abroad, and wherein existing ten multinomial patents are authorized at home and abroad, on this basis, proposes the scheme of the application.
Summary of the invention
Technical matters to be solved by this invention can awing there is the problem of larger resistance by flight structure for existing, provides a kind of high-speed aircraft, can reduce fluid resistance, derive a kind of ammunition simultaneously according to this structure.
In order to solve the problems of the technologies described above, the technical solution used in the present invention is: a kind of high-speed aircraft, comprise housing and driving engine, outer fluid passage and fluid passage is provided with successively in described housing, described outer fluid passage and fluid passage are in communication with the outside respectively by respective port, and outer fluid passage communicates with the air suctiton inlet of described driving engine; Housing is selectively arranged or wing is not set.
Another technical solution used in the present invention is: a kind of high-speed aircraft, comprise housing, outer fluid passage and fluid passage is provided with successively in housing, described outer fluid passage and fluid passage communicate with the external world respectively by respective port, are provided with concavo-convex in the flow-disturbing face of channel wall in outer fluid passage.
Another technical solution used in the present invention is: a kind of ammunition, comprise bullet and shell case, the maximum square section of described bullet to bullet tip between bullet inside be provided with outer fluid passage and fluid passage successively, described outer fluid passage and fluid passage communicate with the external world respectively by respective port, are provided with concavo-convex in the flow-disturbing face of channel wall in outer fluid passage.
Beneficial effect of the present invention is: 1, the inside and outside two-layer fluid passage including the fluid of different in flow rate is set in the housing of aircraft, the high-velocity fluid that outer fluid passage under the powerful suction of driving engine and housing are formed, far faster than the fluid of low flow velocity in fluid passage, the huge difference of pressure produced because flow velocity is different thus, formed around the difference of pressure transfer circle around fuselage, the original fluid resistance acted on from outside to inside on housing is changed original pressure direction, from contrary direction, shift pressure is poor from inside to outside, fluid resistance in aircraft flight is reduced, 2, the flow velocity difference in inside and outside LAYER FLUID passage is larger, and the transfer of the difference of pressure around the casing surroundings circle formed outwards shifts fluid pressure more, makes the flight of aircraft more energy-conservation, apparent, the flow effect of the powerful suction of driving engine convection cell in not too wide outer fluid passage is little, but the impact that fluid flow rate produces is very large, make the fluid by flank speed in passage, and by the control to driving engine, be easy to make its outer fluid inner fluid passage flow velocity faster than the fluid several times in fluid passage, so just produce the even more difference of pressure of several times, the part acted on housing, even most fluid pressure shifts the difference of pressure transfer circle formed around around it in the opposite direction, original aircraft is made to expend 90% energy consumption to overcome fluid resistance, only the power of surplus about 10% promotes the state generation reverse of aircraft flight, change into fluid resistance part, even major part reduces, change the power resources of aircraft thus into, act in thrust to the less loss of propelling thrust that aircraft produces, make existing aircraft under the state not increasing power, increase larger propelling thrust, thoroughly remould oneself thoroughly, not only flying radius is multiplied, improve with hourly velocity, energy consumption reduces.
Accompanying drawing explanation
Fig. 1 is the structural representation of the aircraft of the embodiment of the present invention.
Fig. 2 be in Fig. 1 A-A to generalized section.
Fig. 3 is the generalized section of the wing of the aircraft of the embodiment of the present invention.
Fig. 4 is the schematic diagram not establishing the aircraft of both sides wing of the embodiment of the present invention.
Fig. 5 is the structural representation of the triangle aircraft of the embodiment of the present invention.
Fig. 6 is the generalized section of the triangle aircraft of the embodiment of the present invention.
Fig. 7 is the structural representation of the guided missile of the embodiment of the present invention.
Fig. 8 is the structural representation of the ammunition of the embodiment of the present invention.
Fig. 9 be in Fig. 8 B-B to generalized section.
Figure 10 is the structural representation of the passenger plane of the embodiment of the present invention.
Label declaration:
1, body shell; 101, missile case; 102, internal layer shell; 103, flow-disturbing face; 104, helix flow-disturbing face; 105, bullet; 106, shell case; 107, maximum cross section;
2, fluid passage;
3, outer fluid passage; 301, high-velocity fluid layer; 302, difference of pressure transfer circle;
4, driving engine; 401, exhausr port; 402, air suctiton inlet;
5, wing shell; 501, rear wing;
6, port; 601, port; 602, conduit; 603, small-bore port; 604, control setup.
Detailed description of the invention
By describing technology contents of the present invention, structural attitude in detail, realized object and effect, accompanying drawing is coordinated to be explained in detail below in conjunction with embodiment.
The design of most critical of the present invention is: a kind of power resources of original proposition, the structure of aircraft is applied to based on " forming the fluid of inside and outside two-layer different in flow rate around running gear; as internal layer flow velocity is slower than skin; the high flow rate shift pressure of the inevitable outer layers of slug flow speed of internal layer is poor; make fluid resistance reduce and change power resources into, otherwise making fluid resistance increase just increase consumption of power " this discussion.
Wherein, the flow velocity difference of inside and outside LAYER FLUID is larger, and energy-saving effect is better, changes power resources into more, otherwise fluid resistance is larger, and the energy consumption of generation is larger.High pressure shifts to low pressure, and as water flows the same from high to low, being all the natural law, is the natural law, and above-mentioned conclusion is just set up.
All running gears of rapid movement in a fluid in any reality are treated by above-mentioned conclusion, be not difficult to find out, all around inside and outside LAYER FLUID around all running gears, with on unlike, internal layer is the high-velocity fluid being approximately equal to its flow velocity near housing, and to leave outwards the slow down gradually skin of environment flow velocity of housing be low flow velocity fluid, this fluid pressure just causing large-scale outer low flow velocity inner layer high flow rate transfer how extra, make the running gear of all rapid movement in a fluid must expend the energy consumption of about 90% to overcome the reason that fluid resistance can't improve speed, mass energy is caused to waste, accumulative carbon emission causes the topmost reason of global warming today.
The present invention is contrary with the fluid distrbution state of present all running gears, the fluid of two-layer different in flow rate inside and outside being formed around running gear, internal layer flow velocity is slower than outer flow velocity, the then high pressure of internal layer slug flow speed generation, the low pressure shift pressure that inevitable outer layers high flow rate produces is poor, form the difference of pressure transfer circle made a circle around running gear week, running gear fluid in rapid movement, act on the fluid pressure on running gear housing from outside to inside, from inside to outside shift in the opposite direction again, formed around running gear and difference of pressure transfer circle, the fluid pressure outwards inside with surrounding due to difference of pressure transfer circle is contrary, so at least part of, or outside most of fluid pressure is blocked in, thus the fluid resistance of running gear is reduced, wherein inside and outside two-layer flow velocity difference is larger, fluid resistance outwards shift more, change power resources into more, energy-saving effect is more obvious.
The invention provides a kind of high-speed aircraft, comprise housing and driving engine, be provided with outer fluid passage and fluid passage successively in described housing, described outer fluid passage and fluid passage are in communication with the outside respectively by respective port, and outer fluid passage communicates with the air suctiton inlet of described driving engine; Housing is selectively arranged or wing is not set.
Further, above-mentioned high-speed aircraft also comprises internal layer shell, described internal layer shell is located between described outer fluid passage and fluid passage, internal layer shell is provided with multiple port and is communicated with inside and outside fluid passage, and the area of the port on the port of fluid passage and internal layer shell is less than the area of the port of described outer fluid passage.
Further, the housing of above-mentioned high-speed aircraft arranges wing, in wing shell, be provided with described fluid passage and outer fluid passage, and the outer fluid passage in wing shell communicates with the outer fluid passage in described housing.
Further, the fluid passage of above-mentioned high-speed aircraft and outer fluid passage be only arranged at described housing the first half in and described wing upper surface in.
Further, above-mentioned high-speed aircraft is provided with control setup in described port, and described control setup changes the keying of port and the change of port opening angle.
Further, above-mentioned high-speed aircraft comprises guided missile, fighter plane and passenger plane.
Present invention also offers another kind of high-speed aircraft, comprise housing, in housing, be provided with outer fluid passage and fluid passage successively, described outer fluid passage and fluid passage communicate with the external world respectively by respective port, are provided with concavo-convex in the flow-disturbing face of channel wall in outer fluid passage.
Further, above-mentioned another kind of high-speed aircraft also comprises internal layer shell, described internal layer shell is located between described outer fluid passage and fluid passage, internal layer shell is provided with multiple port and is communicated with inside and outside fluid passage, and the area of the port on the port of fluid passage and internal layer shell is less than the area of the port of described outer fluid passage.
Present invention also offers a kind of ammunition, comprise bullet and shell case, the maximum square section of described bullet to bullet tip between bullet inside be provided with outer fluid passage and fluid passage successively, described outer fluid passage and fluid passage communicate with the external world respectively by respective port, are provided with concavo-convex in the flow-disturbing face of channel wall in outer fluid passage.
Further, above-mentioned ammunition also comprises internal layer shell, described internal layer shell is located between described outer fluid passage and fluid passage, internal layer shell is provided with multiple port and is communicated with inside and outside fluid passage, and the area of the port on the port of fluid passage and internal layer shell is less than the area of the port of described outer fluid passage.
Please refer to Fig. 1 and Fig. 2, embodiments of the invention one are:
A kind of aircraft, fluid passage 2 and outer fluid passage 3 is respectively equipped with around around fuselage in body shell 1, fluid passage 2 and outer fluid passage 3 are respectively equipped with multiple port communicate with body shell 1, wherein fluid passage 2 is communicated with port 6 by conduit 602, outer fluid passage 3 communicates with port 601, and driving engine 4 is located at the afterbody of body shell 1, and its air suctiton inlet communicates with outer fluid passage 3, exhausr port communicates with the external world, and wherein the air inlet area of port 601 is greater than port 6.
When aircraft flight, fluid is from port 6, 601 enter in inside and outside fluid passage respectively, now driving engine 4 produces powerful suction by uniform multiple ports 601 in the fluid high-speed suction outer fluid passage 3 be attached on body shell, thus make on body shell and the roughly equal high-velocity fluid layer 301 communicated with each other again of the outer fluid passage 3 two-layer flow velocity of inside and outside formation, fluid now in fluid passage 2 produces higher air pressure because flow velocity is slow, high-velocity fluid layer 301 shift pressure that this part fluid is formed the high pressure that fluid passage 2 inside produces by uniform multiple ports 6 on body shell 1 is poor, thus formed around the difference of pressure transfer circle 302 around body shell 1 the fluid pressure acted on around body shell 1 produced during aircraft flight, in the opposite direction from inside to outside after transfering fluid pressure around aircraft mineralization pressure transfer circle 302, because difference of pressure transfer circle 302 is contrary with the fluid pressure direction around aircraft, at least partly or mostly fluid pressure is blocked in outside difference of pressure transfer circle 302, the fluid resistance that aircraft flight is produced reduces, change the power resources of aircraft thus into.
Between fluid passage 2 and outer fluid passage 3, flow velocity difference is larger, the difference of pressure produced is larger, the fluid pressure of transfer is more, apparent, outer fluid passage 3 is in the large suction force state of driving engine semi-finals, flow velocity in its velocity ratio fluid passage 2 is in its natural state a lot of soon, by the control to driving engine 4, be easy to faster than fluid passage 2 flow velocity several times, even manyly can to accomplish easily, thus more fluid pressure is from inside to outside shifted, form the difference of pressure transfer circle 302 around airframe surrounding, make the difference of pressure transfer circle 302 lain around during aircraft flight the part of fluid pressure, after even major part outwards shifts, fluid resistance is greatly reduced, load carrying ability increases, flying radius increases, improve with hourly velocity, energy consumption reduces.
It is worth mentioning that: the flow velocity between fluid passage 2 and outer fluid passage 3 differs several times under the powerful suction of power, even more times are all easy to accomplish, thus make the present situation of " during aircraft flight, the energy consumption of about 90% only remains the energy consumption of about 10% to promote aircraft flight for overcoming fluid resistance " produce the reverse of essence.
First, because produce the several times even difference of pressure of more times between fluid passage 2 and outer fluid passage 3, be easy to fluid pressure ecto-entad during aircraft flight acted on body shell, change pressure direction from inside to outside transfer part pressure again, even most of pressure, power with regard to making original aircraft expend about 90% is used for driving aircraft normal flight to change into because most of fluid pressure outwards shifts to overcome about 10% power of fluid resistance, also just the power originally expended is changed into propelling thrust source, if the fluid resistance reducing 10% is just the power resources of aircraft increase about at least 50%, but many times of fluid pressure differentials even more arrived only can not reduce by the fluid resistance of 10%, even increase more power resources to be all easy to realize.
Secondly, power resources of the present invention are consumed in the power overcoming fluid resistance from aircraft 90% to obtain, the method obtained is that inside and outside fluid passage flow velocity difference is larger, the fluid pressure of outside transfer is more, the speed of aircraft is faster, the power obtained is more, because of reduce fluid resistance part even major part change propelling thrust into, after making the power of aircraft increase several times, the more important thing is simultaneously, around the difference of pressure transfer circle 302 around aircraft part, after even more fluid resistance outwards shifts, under equal power driven, the flying speed of aircraft is all faster.
So greatly reduce under power increases again the interaction of several times in the fluid resistance of aircraft, the benefit produced is not that 1+1 equals 2, but be greater than 2, now under the state not increasing any power, aircraft flight speed is just made greatly to improve, flying radius significantly improves, and aircraft function of the present invention, far beyond the concept of present aircraft, produces a kind of aircraft of real high-speed and energy-saving thus.
Present aircraft will improve some propelling thrusts and flying radius is very difficult thing, by means of only the fleetline structure changing aircraft, is difficult to reduce fluid resistance; In the face of the reality overcoming fluid resistance by the energy consumption of 90% is also helpless, although created a lot of running gear since its reason is the industrial revolution, but effectively do not reduce the theory of fluid resistance, method and apparatus, more fluid resistance can not be converted into propelling thrust, so all ambient pressures are all guided into self produce how extra fluid pressure around; The present invention is contrary with existing common practise, in the fluid pressure around running gear is outwards shifted, obtain power resources, and unique difference is between the two: the pressure direction of fluid is contrary.
And above-mentioned conclusion of the present invention is as that water flows from high to low is the same, high pressure is the natural law to low pressure shift pressure difference.The present invention only changes the fluid distrbution state of stream layer inside and outside running gear, the original distribution naturally producing fluid resistance, the contrary distribution changing into transfering fluid resistance, between inside and outside fluid passage, flow velocity differs, the transfer of difference of pressure transfer circle is how many fluid pressures, the speed of aircraft is just made to improve how many, just can save how much energy, be transformed into how many propelling thrust source, this is relation one to one, thus, the present invention, by the development to all running gears, produces revolutionary change, and the development in profound influence its future.
Please refer to Fig. 1 and Fig. 2, embodiments of the invention two are:
A kind of aircraft, with embodiment one unlike removing conduit 602 and port 6, the small-bore port 603 that uniform multiple aperture is less on internal layer shell 102, makes fluid passage 2 communicate with outer fluid passage 3.
When aircraft travels, driving engine produces powerful suction, naturally more easily the fluid high-speed on housing is sucked by larger port 601, two layers of high-velocity fluid layer 301 that machine flow velocity is approximately equal are each other formed at passage and surface of shell, driving engine also sucks a small amount of fluid in fluid passage 2 in outer fluid passage 3 by the small-bore port 603 that uniform aperture is less simultaneously, because the air inlet area ratio small-bore port 603 of port 601 is much bigger, so outer fluid passage is more faster than fluid passage flow velocity, at driving engine powerful suction, flow velocity in outer fluid passage is exceedingly fast, far away from the flow velocity in fluid passage mouth, internal and external channel produces very large difference of pressure because of the huge difference of flow velocity, by being distributed on the port on internal layer shell 102, high-velocity fluid layer 301 shift pressure that the outside fluid passage of high pressure 3 produced compared with low flow velocity in fluid passage 2 is formed is poor, thus formed around the difference of pressure transfer circle 302 around body shell 1, make the fluid pressure acted on from outside to inside on housing produced during aircraft flight, from inside to outside shift in the opposite direction, the fluid resistance of flight is greatly reduced.
As the improvement to the present embodiment, with reference to embodiment one, be provided with small-bore port 603 in internal layer shell 102 upper part, another part is communicated with port by conduit 602.
Please refer to Fig. 1 to Fig. 3, embodiments of the invention three are:
A kind of aircraft, be provided with fluid passage 2 and outer fluid passage 3 around upper and lower surface in its wing shell 5, the fluid passage 2 wherein in body shell 1 communicates with the outer fluid passage 3 in wing shell.
During aircraft flight, the suction that driving engine semi-finals is large passes through fuselage, port 601 uniform on body shell 1 sucks fluid high-speed in outer fluid passage, make to form high-velocity fluid layer 301 around fuselage and wing, enormous pressure difference is produced because flow velocity is different between the fluid passage 2 in body shell 1 and wing shell 5, high pressure outside high-velocity fluid layer 301 shift pressure that fluid passage 2 is produced low flow velocity in it by conduit 602 and uniform port 6 is poor, formed around the circle difference of pressure transfer circle 302 around fuselage and wing, the fluid pressure acted on from outside to inside aboard produced during aircraft flight, under the effect of difference of pressure, from inside to outside transfering fluid pressure in the opposite direction, between fluid passage 2 and outer fluid passage 3, flow velocity difference is larger, the fluid pressure of outside transfer is more, obviously, the flow velocity of outer fluid passage 3 inner fluid is easy to the several times being greater than fluid passage 2 inner fluid, even more, more fluid resistance is outwards shifted, produce a kind of aircraft of high-speed and energy-saving of brand-new structure thus.
Please refer to Fig. 1 to Fig. 3, embodiments of the invention four are:
A kind of aircraft, fluid passage 2 and outer fluid passage 3 is provided with in the first half of body shell 1 and in the upper surface of wing, outer fluid passage 3 communicates with the port 601 on body shell 1 and wing shell 5, also be communicated with the air suctiton inlet of driving engine 4, fluid passage 2 is communicated with the port 6 on body shell 1 and wing shell 5 by conduit 602 simultaneously.During aircraft flight, the powerful suction of driving engine sucks fluid high-speed in outer fluid passage 3 by port 601 uniform on body shell 1 and wing shell 5, thus high-velocity fluid layer 301 is formed in the fuselage first half and upper surface of the airfoil, with the low flow velocity in fluid passage 2, very large difference of pressure is produced because flow velocity is different between anticyclonic pressure fluid, poor by high-velocity fluid layer 301 shift pressure in conduit 602 and the port 6 on uniform housing from inside to outside portion, thus at the fuselage first half and upper surface of the airfoil mineralization pressure difference transfer circle 302, the fluid resistance acting on the fuselage first half and upper surface of the airfoil when aircraft is travelled outwards shifts, shift direction is upwards just make the lift of aircraft improve.Meanwhile, produce larger difference of pressure because flow velocity is different and produces greater lift between fuselage and wing top and the bottom.
Please refer to Fig. 2 and Fig. 4, embodiments of the invention five are:
A kind of can the aircraft of supersonic flight, the wing of both sides is not set, only arrange rear wing 501 come controlling party to, be provided with by controlling the control setup 604 making it to open or close and produce angle change in port, owing to removing wing, also do not have the free air diffuser of conventional airplane, reduce by the windward side area of about 80% than conventional airplane, the aircraft of the present embodiment naturally can improve speed, reduce energy consumption.
When aircraft flight, the port 601 of aircraft lower part is closed by control setup 604, the powerful suction of driving engine makes the aircraft first half form high-velocity fluid layer 301, produce enormous pressure difference with the flow velocity in lower part state of nature and produce greater lift, aloft can part or most of port 601 opening aircraft lower part.
Make to form high-velocity fluid layer 301 around outer fluid passage 3 and body shell 1 at the suction that driving engine is powerful, and produce very large difference of pressure between the fluid that in fluid passage 2, flow velocity is very slow, outwards shift pressure is poor with the port 6 be distributed on body shell 1 by conduit 602 for fluid passage 2, thus form the difference of pressure transfer circle 302 made a circle around aircraft week, make fluid resistance part even major part outwards transfer, shift how many fluid pressures, just obtain how many power resources, the power resources of aircraft are just made to improve how many, the speed of aircraft is just made to improve how many, the energy part of saving changes the power of driving engine into, the power of driving engine is made to improve more times, after removing fuselage and free air diffuser simultaneously, windward side area reduces about 80% than conventional airplane again, so the flying radius of this aircraft, speed is all much larger than conventional airplane, as hawk and sparrow do not have comparability.
Further, the structure of this aircraft also can be used for unmanned plane, usually the sole cause affecting air speed after engine power is determined is exactly fluid resistance, the difference of pressure transfer circle 302 that transposition of the present invention produces shifts how many fluid resistances and just improves how much speed, just produce how many power resources, removing wing and air inlet duct makes again windward side reduce about 80%, forms many times of real supersonic vehicles in the state simultaneously greatly improved at lift.
Further, remove or partial removal conduit 602 and port 6, the small-bore port 603 that uniform multiple aperture is relatively little on the internal layer shell 102 of fluid passage 2 communicates with high-velocity fluid layer 301.
Please refer to Fig. 5 and Fig. 6, embodiments of the invention six are:
A kind of triangle aircraft, from overlooking, look up, front, any one side in side be all that triangle is formed, leg-of-mutton rock-steady structure is best, several tabular just can be formed, make more simply too much than present aircraft, with low cost many, performance is also more advantageous, and polyhedron is best stealth structure simultaneously.
Delta aircraft is formed by connecting by several blocks of leg-of-mutton sheet materials, fuselage and wing one integrated mass all become the carrying space of inner manned loading, be arranged with inside and outside two-layer fluid passage 2 and outer fluid passage 3 in body shell inner circumferential, communicate with the external world respectively by port 6,601.Driving engine 4 is located in the middle of the rear portion housing of the aircraft first half, and the air suctiton inlet 402 of driving engine 4 communicates with outer fluid passage 3, and the exhausr port 401 of driving engine 4 communicates with the external world.Under the suction that driving engine is powerful, outer fluid passage 3 and housing form high-velocity fluid layer 301, with low flow velocity in fluid passage 2, very large difference of pressure is formed between the fluid of high pressure, by conduit 602 and the port 6 be distributed on above body shell 1, the high pressure in fluid passage 2 is shifted to the high flow rate low pressure zone on high-velocity fluid layer 301, make body shell 1 surrounding mineralization pressure difference transfer circle 302, aircraft is travelled the fluid pressure of the ecto-entad produced, shift its fluid pressure from inside to outside in the opposite direction, the even most of fluid pressure of part is outwards shifted, fluid resistance greatly reduces.
Further, the special construction of this aircraft can be used for unmanned plane.
Further, driving engine also can be located between the base plane at body shell rear portion and joint portion, top.
Please refer to Fig. 2 and Fig. 7, embodiments of the invention seven are:
A kind of guided missile, in missile case 101, is provided with inside and outside two-layer fluid passage 2 and outer fluid passage 3, communicates respectively by port 6,601 with the external world.Driving engine 4 produces powerful suction when working, make outer fluid passage 3 inside and outside formation high-velocity fluid layer 301, from between fluid passage 2 because of difference of pressure that the different formation of flow velocity is very large, thus mineralization pressure difference transfer circle 302, fluid resistance part around guided missile, even major part outwards transfer, the speed of guided missile is improved greatly, reduce fluid resistance simultaneously and be converted into power, the power of guided missile is increased, after the aerodynamic power of guided missile is determined, the energy reserves of guided missile and fluid resistance directly affect its emission rate and distance, the difference of pressure that fluid passage produces inside and outside this changes power resources into, and the even most of fluid resistance of part is reduced, make scope farther, speed is faster, the structure of this guided missile, change common practise, be different from the brand-new structure of traditional guided missile, development for following guided missile opens a new road.
Please refer to Fig. 8 and Fig. 9, embodiments of the invention eight are:
A kind of ammunition, comprise bullet 105 and shell case 106, the afterbody of bullet 105 is conical, be provided with in bullet between the tip of maximum cross section 107 place of bullet 105 to bullet and be provided with outer fluid passage 3 and fluid passage 2 successively, fluid passage 2 and outer fluid passage 3 communicate with the external world respectively by port 6,601, are provided with concavo-convex in the flow-disturbing face 103 on surface in outer fluid passage 3.
When ammunition is launched, the afterbody due to bullet 105 is conical, is multiplied with the afterbody contact surface of the contact surface after gunpowder explosion than plane, so the propelling thrust produced also improves greatly.Usually, helix rifling in the partial shell at the rear, maximum cross section 107 of bullet 105 and gun barrel makes bullet accelerate to launch, bullet in rotating under force of inertia effect parabolically track flight way in, produce very big friction force with fluid and bullet flying distance shortened.Now, fluid is from port 601, 6 enter in inside and outside fluid passage respectively, it is a lot of that the air inlet area of port 601 is greater than port 6, more fluid is made to enter in outer fluid passage 3, because be provided with concavo-convex in the flow-disturbing face 103 on surface in outer fluid passage 3, the path of outer fluid passage 3 fluid process is greater than the path of corresponding fluid passage 2, the approximately equal high-velocity fluid layer 301 of two-layer flow velocity is formed on surface of shell and in outer fluid passage 3, the flow velocity of high-velocity fluid layer 301 produces difference of pressure faster than fluid passage 2, when the outer fluid passage 3 of the bullet of High Rotation Speed throws to the external world from multiple port 601 its high-velocity fluid under centrifugal action, accelerate again the flow velocity of high-velocity fluid layer, the low pressure zone shift pressure its high pressure produced to the high flow rate by rapid fluid layer 301 from uniform multiple ports 6 by conduit 602 with the fluid of low flow velocity high pressure in fluid passage 2 is poor, so form the difference of pressure transfer circle 302 made a circle around bullet week, fluid is acted on the fluid pressure on bullet housing from outward, from inside to outside transfering fluid pressure in the opposite direction, from the difference of pressure transfer circle outwards transfer around bullet windward side, the fluid resistance that bullet is flown reduces, so the speed of bullet flight accelerates, the distance of flight increases, produce a kind of range thus farther, speed is bullet faster.
Between fluid passage 2 and outer fluid passage 3, the difference of pressure of the larger generation of flow velocity difference is larger, apparent: because of fluid passage 2 inside, its radius is less than outer fluid passage 3 to one; One is because be provided with flow-disturbing face 103 in outer fluid passage 3, the path of fluid in it is made more to be greater than path in fluid passage 2, so the two superposition just make the path of fluid process at least be greater than at least one times of fluid passage 2, so with regard to produce at least one times difference of pressure to reduce fluid resistance.
Further, inside face in the outer fluid passage 3 of bullet or appearance at least one are provided with helix flow-disturbing face 104, the path of fluid process is made to be greater than fluid passage 2 several times, because it is just longer than the path of fluid passage process that helix flow-disturbing face 104 makes fluid turn around in fluid passage 3 outside, so rate of flow of fluid is faster than fluid passage several times, the flow velocity also several times faster than fluid passage of high-velocity fluid layer 301, so the more multidirectional outer transfer of fluid pressure that the difference of pressure that difference of pressure transfer circle just produces several times runs into bullet, outside transfer how many fluid pressures, just improve speed how soon, just produce great propelling thrust source, so just make bullet flying distance greatly improve, speed improves, bite also improves, a kind of long-range high velocity bullet produces thus.
Further, internal layer shell 102 is established multiple port 6 fluid passage 2 and outer fluid passage 3 are communicated, the air inlet area of port 6 is less than the air inlet area of port 601, when fluid passage 2 produces difference of pressure with outer fluid passage 3 because flow velocity is different, high-velocity fluid layer 301 shift pressure that fluid passage 2 is formed by the uniform outwards fluid passage 3 of multiple port 6 is poor, thus mineralization pressure difference transfer circle 302.
Further, during bullet flight, difference of pressure transfer circle 302 makes the resistance of windward side greatly reduce, the conical structure at its rear portion effectively occupies the position of zone of negative pressure simultaneously, fluid is flow through along the shell of conical, after vertebra point place surrounding fluid converges, negative pressure resistance greatly reduces, and windward side and zone of negative pressure drag reduction, make its speed improve further.
Further, after removing flow-disturbing face 103, helix flow-disturbing face 104, because the path that outer fluid passage is corresponding is greater than fluid passage and produces difference of pressure, also can improve its speed and range.
Further, above-described structure is equally applicable to shell, and the long-range shell of a kind of high speed produces thus thus.
It is worth mentioning that, the ammunition of the present embodiment comprises bullet and shell, and the sole cause affecting bullet and artillery range and speed is exactly fluid resistance, the present invention does not increase the consumption of gunpowder, only on original bullet or shell, by difference of pressure transfer circle, its speed is improved, range improves, and the present invention is that the future development of ammunition opens new direction.
Please refer to Fig. 3, Fig. 9 and Figure 10, embodiments of the invention nine are:
A kind of passenger plane, around or/and the upper and lower surface in wing is provided with inside and outside two-layer fluid passage 2 and outer fluid passage 3 in body shell 1, communicated with the external world by respective port 6,601, two sides outside in fluid passage 3 at least one are provided with the concavo-convex flow-disturbing face 103 in surface or helix flow-disturbing face 104, make the path of fluid process be greater than the path of fluid passage 2.
When aircraft flight, flow-disturbing face 103 concavo-convex in outer fluid passage 3 extends the path that fluid passes through, especially helix flow-disturbing face 104, and the path of fluid process is more increased, and is greater than in fluid passage 2 a lot.Flow velocity now in outer fluid passage 3 is faster than air speed, producing inside side force namely under internal pressure effect around aircraft surrounding fluid simultaneously, make a large amount of fluids on housing from each port 601 access passage, so two-layer high-velocity fluid layer 301 produces very large difference of pressure between fluid passage 2 because flow velocity is different inside and outside forming passage and housing, difference of pressure is outwards shifted by the fluid of the low flow velocity in fluid passage 2, high pressure towards high-velocity fluid layer 301 from multiple port be distributed in body shell 1 by conduit 602.Because the air inlet area of port 601 is greater than port 6, therefore the fluid pressure produced to body shell 1 and wing shell 5 (the multiple evenly distributed helix trouble flow strip of wing) during aircraft flight is from inside to outside shifted its fluid pressure in the opposite direction, so form the difference of pressure transfer circle 302 made a circle around fuselage week, fluid resistance during flight is greatly reduced.Now, between fluid passage 2 and outer fluid passage 3, flow velocity difference is larger, the difference of pressure produced is larger, apparent, it is a lot of that flow-disturbing face 103 or helix flow-disturbing face 104 make the path of fluid process be greater than fluid passage 2, so difference of pressure transfer circle just produces more difference of pressure, fluid resistance is outwards shifted, make segment fluid flow drag reduction, be then transformed into again the power that air speed increases, produce a kind of aircraft of high-speed and energy-saving thus.This embodiment also can produce very large difference of pressure without power, is suitable for the aircraft such as various aircraft, guided missile.
Further, establish flow-disturbing face and multiple helix trouble flow strip that the lift of aircraft is increased in the outer fluid passage 3 in upper surface of the airfoil.
In sum, aircraft provided by the invention produces difference of pressure by the fluid passage of the inside and outside two-layer different in flow rate in housing, between two-layer, flow velocity difference is larger, the difference of pressure produced is larger, by difference of pressure transfer circle, the part of huge fluid pressure action on aircraft casing, even major part outwards transfer, makes fluid resistance part or most minimizing and changes power resources into.Because when aircraft is run at high speed, the power of about 90% is used for overcoming fluid resistance, only surplus about 10% aircraft is driven normally to travel, if by the fluid resistance of difference of pressure transfer circle minimizing 10%, the power of aircraft at least can be made to improve more than 50%, in like manner make various running gear by difference of pressure transfer circle, the running gear comprised in water, in air can reduce by the fluid resistance of 10%, also just reduce more than 50% of worldwide petrochemical fuel, the climate change caused due to row's carbon will be controlled on source.The fluid resistance that apparent the present invention can reduce will never be only 10%.The present invention changes the common practise that running gear moves in a fluid, has in fact found a kind of power resources, this inexhaustible, nexhaustible power resources but have not a particle of pollution, the discovery of this power resources is only that The natural flow of water always proceeds from a higher level to a lower one, the natural law that high pressure shifts to low pressure.
The foregoing is only embodiments of the invention; not thereby the scope of the claims of the present invention is limited; every equivalents utilizing specification sheets of the present invention and accompanying drawing content to do, or be directly or indirectly used in relevant technical field, be all in like manner included in scope of patent protection of the present invention.
Claims (10)
1. a high-speed aircraft, comprise housing and driving engine, it is characterized in that, in described housing, be provided with outer fluid passage and fluid passage successively, described outer fluid passage and fluid passage are in communication with the outside respectively by respective port, and outer fluid passage communicates with the air suctiton inlet of described driving engine; Housing is selectively arranged or wing is not set.
2. high-speed aircraft according to claim 1, it is characterized in that, also comprise internal layer shell, described internal layer shell is located between described outer fluid passage and fluid passage, internal layer shell is provided with multiple port and is communicated with inside and outside fluid passage, and the area of the port on the port of fluid passage and internal layer shell is less than the area of the port of described outer fluid passage.
3. high-speed aircraft according to claim 1, is characterized in that, described housing arranges wing, is provided with described fluid passage and outer fluid passage in wing shell, and the outer fluid passage in wing shell communicates with the outer fluid passage in described housing.
4. high-speed aircraft according to claim 3, is characterized in that, the first half that described fluid passage and outer fluid passage are only arranged at described housing is interior with in the upper surface of described wing.
5. high-speed aircraft according to claim 1, is characterized in that, in described port, be provided with control setup, and described control setup changes the keying of port and the change of port opening angle.
6. high-speed aircraft according to claim 1, is characterized in that, described high-speed aircraft comprises guided missile, fighter plane and passenger plane.
7. a high-speed aircraft, comprise housing, it is characterized in that, in housing, be provided with outer fluid passage and fluid passage successively, described outer fluid passage and fluid passage communicate with the external world respectively by respective port, are provided with concavo-convex in the flow-disturbing face of channel wall in outer fluid passage.
8. high-speed aircraft according to claim 7, it is characterized in that, also comprise internal layer shell, described internal layer shell is located between described outer fluid passage and fluid passage, internal layer shell is provided with multiple port and is communicated with inside and outside fluid passage, and the area of the port on the port of fluid passage and internal layer shell is less than the area of the port of described outer fluid passage.
9. an ammunition, comprise bullet and shell case, it is characterized in that, the maximum square section of described bullet to bullet tip between bullet inside be provided with outer fluid passage and fluid passage successively, described outer fluid passage and fluid passage communicate with the external world respectively by respective port, are provided with concavo-convex in the flow-disturbing face of channel wall in outer fluid passage.
10. ammunition according to claim 9, it is characterized in that, also comprise internal layer shell, described internal layer shell is located between described outer fluid passage and fluid passage, internal layer shell is provided with multiple port and is communicated with inside and outside fluid passage, and the area of the port on the port of fluid passage and internal layer shell is less than the area of the port of described outer fluid passage.
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| CN201410655140.2A CN104386237A (en) | 2014-11-17 | 2014-11-17 | High-speed aircraft and cartridge |
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| CN201410655140.2A CN104386237A (en) | 2014-11-17 | 2014-11-17 | High-speed aircraft and cartridge |
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