CN1065192C - Aircraft and method of flying the same - Google Patents
Aircraft and method of flying the same Download PDFInfo
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- CN1065192C CN1065192C CN95118241A CN95118241A CN1065192C CN 1065192 C CN1065192 C CN 1065192C CN 95118241 A CN95118241 A CN 95118241A CN 95118241 A CN95118241 A CN 95118241A CN 1065192 C CN1065192 C CN 1065192C
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Abstract
The present invention relates to a flying vehicle. Balloons made of flexible materials are used as the wings of the flying vehicle, the wings are arranged at the upper side of the body of the flying vehicle and filled with gas which is lighter than air, and the body of the flying vehicle is provided with a screw propeller. The flying vehicle can increase speed and can not crash even when the screw propeller does not work and can not provide thrust force.
Description
The present invention relates in air floating and flight aircraft.
Typical prior art is the balloon 1 that is shown among Figure 21.Balloon 1 comprises spherical envelope 2 and carrying gondola 3, and this air bag 2 fills with lighter-than-air gas, and this gondola 3 is hung from the air bag and is used for loading the occupant.
Another prior art that is shown among Figure 22 discloses a kind of balloon 4, and this balloon 4 comprises spheroidicity air bag that is filled with lighter-than-air gas and the carrying gondola that is used for loading the occupant that hangs from air bag.
Be shown in these prior aries of Figure 21 and 22 at these, because air bag 2,5th is spherical or compressed globular, the flying speed of these air bags can not be increased, in addition, in these prior aries, do not consider to utilize wind to increase the airlift of the buoyancy or the air bag of air bag.
Figure 23 is the three-dimensional diagrammatic sketch of another prior art.This prior art relates to aircraft, and this aircraft obtains thrust by means of the propeller 8 that drives rotatably, and obtains airlift by means of wing 9.
In this class aircraft shown in Figure 23, if any trouble appears in propeller 8.Wing 9 just can not produce airlift, and this will produce some accidents, such as air crash.
The objective of the invention is to propose a kind of aircraft, this aircraft can increase speed and or even also can prevent to crash when propeller does not provide thrust for aircraft.
The objective of the invention is to realize that by a kind of like this aircraft this aircraft comprises:
A body, this body have an axis that extends along heading;
A jet engine;
Wing, they are respectively to make and be included in its volume inside by a kind of flexible material, this space is filled with lighter-than-air gas, wherein:
First subtriangular host wing is installed on the body and is parallel to the axis of body, and first host wing is provided with solar cell, and being used for provides electric energy to illumination equipment in the aircraft or analogue;
Flat top second that at least one is subtriangular and the 3rd host wing are with the closely-spaced first host wing top that is arranged on;
A plurality of vertical wings are perpendicular to first host wing and each top second and the 3rd host wing and be parallel to the axis setting of body, and these a plurality of vertical wings couple together first host wing and second and third host wing;
Go up the upper surface that the vertical wing is arranged on top the 3rd host wing that is arranged in a plurality of tops second and the 3rd host wing topmost for one, should go up the parallel to the axis front end of the 3rd host wing of vertical wing and extend to the back-end, and have a vertical tail in its back-end from top;
Jet engine is arranged on top the 3rd host wing that is arranged in topmost, and this jet engine comprises an air intlet and the gas vent that protrude the 3rd host wing rear end from top towards heading; And
This aircraft also comprises a guide member that is used for air is directed to air intlet, and this guide member extends to the air intlet of jet engine and forms one 10 ° to 45 ° angle with an imaginary perpendicular from last vertical wing front end.
Of the present invention other and further purpose, feature and advantage are from clear below in conjunction with understanding more the detailed description of accompanying drawing.Wherein,
Fig. 1 is the plan view of the aircraft 11 of the embodiment of the invention;
Fig. 2 is the sectional elevation view of host wing 12;
Fig. 3 is the three-dimensional view of aircraft 11;
Fig. 4 is the sectional elevation view of host wing 50 of the aircraft of another embodiment of the present invention;
Fig. 5 is the plan view of the aircraft 21 of yet another embodiment of the invention;
Fig. 6 is the lateral plan of aircraft shown in Fig. 5 21;
Fig. 7 is the plan view of the aircraft 23 of another embodiment of the present invention;
Fig. 8 is the three-dimensional view of the aircraft 25 of another embodiment of the present invention;
Fig. 9 is the three-dimensional view of the aircraft 28 of an embodiment also having of the present invention;
Figure 10 is the three-dimensional view of the aircraft 35 of another embodiment of the present invention;
Figure 11 is the longitudinal section view of aircraft shown in Figure 10 35;
Figure 12 is the plan view of aircraft shown in Figure 10 35;
Figure 13 is the three-dimensional view of the aircraft 37 of another embodiment of the present invention;
Figure 14 is the three-dimensional view of the aircraft 45 of another embodiment of the present invention;
Figure 15 is a cross sectional drawing, is that the edge is cutd open the plane of the axis normal of the body 14 of another embodiment of the present invention;
Figure 16 is the three-dimensional view of the aircraft 110 of another embodiment of the present invention;
Figure 17 is the front elevation of aircraft 110;
Figure 18 is the plan view of aircraft 110;
Figure 19 is the lateral plan of aircraft 110;
Figure 20 is the lateral plan of the aircraft 150 of an embodiment more of the present invention;
Figure 21 is the three-dimensional view of the balloon 1 of typical prior art;
Figure 22 is the three-dimensional view of the balloon 4 of another prior art;
Figure 23 is again the three-dimensional view of the aircraft of a prior art.
Now in conjunction with the accompanying drawings, preferred embodiment of the present invention is described below.
Fig. 1 is the plan view of the aircraft 11 of one embodiment of the present of invention.In Fig. 1, body 14 is to be provided with host wing 12, empennage 13 and vertical tail 15.Body 14 is also for the occupant is provided with the space, and aircraft body 14 is provided with the propeller 17 that is used for producing thrust at its front part, and the combustion engine 18 that drives propeller 17.
Fig. 2 is the cross sectional drawing along the host wing of getting perpendicular to the plane of host wing axis 12.Host wing 12 is air bags made from flexible material, and has its anterior shape that raises (increase at Fig. 1 or place, Fig. 2 left side).Host wing 12 has the inner chamber that charges with lighter-than-air gas.This gas can be unreactable gas, as helium, neon or similar gas, and the natural fuels with at least 80% CH4 containing amount that can use, and wherein may contain a part of blue gas.Natural fuels also may contain ethane, propane, butane or analogue to replace methane.Host wing 12 is arranged on the end face of body 14, and empennage 13 and vertical tail 15 have the structure identical with host wing 12.The heading of aircraft is determined by vertical tail 15.
Fig. 3 is the three-dimensional view of embodiment that is shown in the aircraft 11 of Fig. 1 and 3 because even when propeller 17 and combustion engine lose its function, aircraft 11 can swim in the air, even the crash accident can be prevented under the situation that does not obtain thrust.In addition, when wind, acting on carry-on airlift will produce, and this just can make aircraft rise to high height.
Fig. 4 is the sectional elevation figure of host wing 50, and this host wing is mounted on another aircraft embodiment of the present invention, and this embodiment is similar to previous embodiment, and it is to be equal to previous embodiment mutually except host wing structure wherein.The host wing 50 of present embodiment is hollow, and host wing 50 is to make with material such as the synthetic resin of rigidity and light metal (for example aluminum alloy).Holding the bag 51 that a usefulness flexible material is made in hollow, is to charge lighter-than-air gas in this bag 51.It is easy to make it the gas changed in the host wing 50 with the host wing bag container.Alternatively, body 14 can hold this bag.
Fig. 5 is the planar view of the embodiment of another aircraft 21 among the present invention, and Fig. 6 is its lateral plan.This embodiment is similar in appearance to the foregoing description, and each corresponding element is with identical label indication.In this embodiment, wing 12 is fixed on the body 14, so a space interval is provided between wing and body.
Fig. 7 is the planar view of the embodiment of another aircraft 23 of the present invention, and the shape of host wing 24 is the shapes that are different from host wing 12.The aspect of host wing 12 almost is a rectangle, and the shape of the host wing 24 among the embodiment to be shown among Fig. 7 almost be triangle.
Fig. 8 is the block diagram of the embodiment of another aircraft 25 of the present invention, and aircraft 25 is similar in appearance to the aircraft that is shown in Fig. 1 to 3.Each corresponding element is with identical label indication.Host wing also is provided with the vertical wing 26 thereon, so airlift further increases, cleanliness performance forward also increases.
Fig. 9 is the block diagram of an alternative embodiment of the invention, and embodiment aircraft 28 is provided with the wing 29 that forms vertically, and this wing 29 extends to empennage 13 from host wing 12.Use this structure, because the advantage of this structure, buoyancy can also further increase, and cleanliness performance forward is also higher.
The vertical wing 26 among Fig. 8 is plane symmetry for plane 30, and protruding from host wing 12.The vertical wing 29 among Fig. 9 is the plane symmetry with symmetrical plane 30 also, and outwards protrudes from host wing 12.These vertical wings 26 and 29 are air bags made from flexible material and have charged lighter-than-air balloon.
In the embodiment shown in Fig. 1 to 8, body 14 also can and fill with gas for the air bag made with flexible material.In addition, the also available rigid material of body 14 as metal, is made or is made with lightweight synthetic resin.
Figure 10 is the block diagram according to the embodiment of another aircraft 35 of the present invention.Figure 11 is the lateral plan that is shown in the aircraft 35 among Figure 10, and Figure 12 is the plan view that is shown in the aircraft 35 among Figure 10.In this embodiment, be provided with the central authorities vertically wing 32 and the vertical wing 33,34 of side.These vertical wings extend to outside the front end of host wing 12 from the rear end of empennage 13.Host wing 12 and empennage 13 are arranged in the downside of the vertical wing 32 of central authorities and the vertical wing 33,34 of side, and host wing 12, empennage 13, the central authorities vertically wing 32 and the vertical wing 33,34 of side planar base surface 88 to 90 separately are to be comprised in one and the identical plane 91, in addition, the rear end of host wing 12 is distance L 5 places at the front end of distance empennage 13, the vertical wing 33,34 of side be arranged to for vertical plane surface be symmetry and be parallel to each other, this vertical plane surface is comprising the vertically axis 93 of the wing 32 of central authorities.
The empennage 13 that forms is less than host wing 12 and almost be similar profile.By hollow attaching parts 73,74, almost above host wing 12, to locate, the top separately of the vertical wing 33,34 of side is connected with the top of the central authorities vertical wings 32 respectively.In addition, the top of the vertical wing 33,34 of each side also is connected with the top of the central authorities vertical wings 32 respectively by hollow attaching parts 76,75, and this connection is in the part regional between host wing 12 and empennage 13.Attaching parts 73 to 76 prevents because high-speed air flow separates the vertical wing, and therefore can further increase flying speed.In addition, vertically the rear end of the wing 32 to 34 is consistent with the rear end of empennage 13 respectively.This just makes the intensity of the vertical wing 32 to 34 and empennage 13 increase jointly, host wing 12, and the empennage 13 and the vertical wing 32 to 34 form the single space of air tight respectively.The T﹠B face of the vertical wing 32 to 34 of each side is formed flat, and the horizontal section of each vertical wing 32 to 34 in vertical direction equates.Each vertical wing 32 to 34 is formed stream line pattern, and vertically the front end of the horizontal section of the wing 32 to 34 is that end is circular.In addition, each vertical wing 32 to 34 form the stream line pattern that has be the front portion of horizontal section to the part of host wing 12 tops for increasing gradually, and towards the part of empennage 13 tops for reducing gradually.Therefore, are maximum positions at the vertical width of the horizontal section of the wing 32 to 34, be less than distance L 3 between the front portion of the vertical wing 32 to 34 and the vertical distance L 4 between the wing 32 to 34 rear ends in the distance L between the circular side surface 2.In addition, the part at each vertical wing 32,33,34 at the central authorities vertical wing of the vertical wing 32 the most close each side 33,34 places is that corresponding unanimity rises part 104 in the maximum of host wing 12.In addition, the outer diameter D 1 of propeller 17 distance L 1 between the axis 94,95 of the vertical wing 33,34 of each side no better than.Therefore, the windstream speed that is produced by propeller 17 is being located between the vertical wing 32 of central authorities and the vertical wing 34 of side and central authorities vertically locate to be maximum between the wing 32 and the vertical wing 33 of side respectively, and this just helps producing high airlift.The turning cylinder of propeller 17 is arranged in the horizontal surface 91 and in the central authorities that comprise axis 93 vertically in the vertical section of the wing 32.
Each vertical wing 32 to 34 is formed the air bag of being made by in light weight and flexible material.In addition, vertically the lighter-than-air gas of the wing 32 to 34 usefulness charges, and this gas such as helium, neon and methane are so that further increase buoyancy.
The side end 85,86 of empennage 13 protrudes respectively outside the vertical wing 33,34 of side.Similarly, the side end 83,84 of host wing 12 protrudes respectively outside the vertical wing 33,34 of side.
Be shown among the embodiment of the aircraft 37 among Figure 13 at another.Aircraft 37 comprises the body 14 that is provided with biplanar host wing 38.In addition, body 14 is provided with biplanar empennage.This configuration can make buoyancy and airlift further increase.
Figure 14 is the three-dimensional diagrammatic sketch of another embodiment of the present invention, and this embodiment is roughly similar in appearance to embodiment illustrated in fig. 3, yet the obvious characteristic that this embodiment has is the upside that buoyancy aid 41 is fixed on body 14, and has and vertically have the straight tubular of two ball end.Buoyancy aid 41 charges with lighter-than-air gas.The configuration of other element of present embodiment is identical with the element of the foregoing description.
Figure 15 is the cross sectional drawing of the body 14 of another embodiment of the present invention, is that get perpendicular to the plane of the axis of body on the edge.In this embodiment, body 14 usefulness spacer member 42 in the previous embodiment and be separated into two cell mesh, promptly so-called upper and lower cabin 43,44, last cabin 43 charges with lighter-than-air gas.Last cabin 43 forms on whole machine body length areas longitudinally.The configuration of other element is identical with previous embodiment among this embodiment.Because the configuration of this figure in Figure 15, the buoyancy of aircraft and airlift can be increased.
In the embodiment shown in fig. 14, a plurality of buoyancy aids 41 for example can be arranged in parallel to each other and are fixed on the body 14 as buoyancy aid shown in Figure 10 for three.
Figure 16 is the three-dimensional view of the aircraft 110 of another embodiment of the present invention; Figure 17 is the front elevation of aircraft 110; Figure 18 is the planar view of aircraft 110; Figure 19 is the lateral plan of aircraft 110.The body 111 of aircraft 110 has the streamline-shaped of the tubular of being similar to and has diameter is D.The axis 122 of approximate tubular body 111 is to point to heading A's.Aircraft 110 is configured to respect to imaginary perpendicular 123 and symmetry, and this imagination perpendicular comprises axis 122.First host wing 112 is flat and is approximately triangle and has two rounded ends that this first host wing is attached on the body 111, and is parallel with the bobbin 122 of body 111.The left side of first host wing 112 and right-hand member are formed round, and the bottom side 112a of first host wing 112 is arranged in the top of the axis 122 of body 111.The shape of second host wing 113 is similar to first host wing 112, and be parallel to first host wing and be arranged on first host wing, 112 tops at a distance of the H1 place, first host wing, 112 shapes are similar on the 3rd host wing 114, and are parallel to first and second host wings 112,113 and are set at second host wing, 113 tops at a distance of the H2 place.Distance H 1 and H2 are chosen as mutually and equate.
First and second host wings 112,113 are connected by the vertical wing 116 that is arranged in body 111 tops and a pair of vertical wing 119 that is arranged in the vertical wing 116 right sides and left side.The second and the 3rd host wing 113,114 is connected by the vertical wing 117 that is arranged in the vertical wing 116 tops and a pair of vertical wing 120 that is arranged in the vertical wing 117 left sides and right side.
Vertically the wing 116,117,119,120 forms similar approximate oval cylinder respectively.Vertically the wing 116 and 117 is arranged to make it to form the first imaginary sub-elliptical tube 125, and it is perpendicular to first, second and the 3rd host wing 112 and 114.Vertically the wing 119 and 120 is arranged to make it to form the second imaginary sub-elliptical tube 126, and it is perpendicular to first, second and the 3rd host wing 112 to 114.Oval spindle axis is the longitudinal axis 122 that is arranged to be parallel to body 111, and this ellipse is the section of the vertical wing 116 to 117, is perpendicular to that the longitudinal axis of the vertical wing 116 and 117 gets.Vertically the spindle axis of the ellipse of the wing 119 and 120 section is the longitudinal axis 122 that is arranged to be parallel to body 111, and described this section is perpendicular to that the longitudinal axis of the vertical wing 119 and 120 gets.This configuration has been improved the flight between space length.In addition, at imaginary plane 123 with vertically the distance L 11 between the line of centers of the wing 119 is greater than the distance L 12 between the outer end of the line of centers of the vertical wing 119 and host wing 112, preferably distance L 11 is greater than distance L 12 1.5 times.Therefore, the structural strength of aircraft has increased.
Upward the vertical wing 118 is arranged on the top of the 3rd host wing 114, go up the vertical wing 118 be arranged to from the front end of heading side A extend to the 3rd host wing 114 the A side the rear end and be the axis 122 that is parallel to body 111, vertical tail 124 is arranged on the rear portion of the vertical wing 118, and vertical tail 124 extends upward.The thickness T 1 that vertical tail 124 forms is less than the vertical thickness T 2 of the wing 118, and vertically the wing 118 and vertical tail 124 form as one.From the distance H 1 of first host wing, 112 to second host wings 113 less than distance H 3, this distance H 3 is to the distance of the lower end of vertical tail 124 from the lower end of the vertical wing 118, and distance H 1 is greater than distance H 4, and this distance H 4 is the distances from vertical tail 124 upper ends to the lower end.Preferably, distance H 3 is the twice greater than distance H 4, and distance H 1 is 1.5 times greater than distance H 4.Therefore the stability of flight is enhanced.In addition, each vertical wing 116,117,119 and 120 thickness be equate in the thickness T 2 of the vertical wing 118 lower ends.A pair of jet engine 115 is arranged on the left and right place of the 3rd host wing top.Guide member 121 is arranged to extend to from the place ahead of the last vertical wing 118 the air intlet 115a of each jet engine 115.Because at its rear portion, the section of guide member forms has convex arc, in the flight course of aircraft 110, the air in guide member 121 the place aheads can be directed into the air intlet 115a of jet engine 115 effectively and is compressed, and this is improved with regard to the efficient that makes jet engine 115.The θ angle that is formed by guide member 121 and imaginary plane 123 is elected as 10 and is spent to 45 degree, preferably 35 spend, air can be guided effectively and be entered air intlet 115a, because gas vent 115b is arranged to protrude backward from the 3rd host wing 114, from the high-temperature exhaust air of gas discharge outlet 115b discharging can avoid blowing the parts of aircraft, such as the vertical wing.
With first to the 3rd host wing 112 to 114 that flexible material is made, the vertical wing 116,177,119 and 120, and upward the vertical wing 118 is hollow, and communicates with each other in their inboard.Because first to the 3rd host wing 113 to 114, the vertically wing 116,117,119 and 120 and the inboard of going up the vertical wing 118 charged lighter-than-air gas, for example, even when the accident of trouble appears in jet engine, and when thrust can not obtain, aircraft also can prevent to crash.First to the 3rd host wing 112 to 114 forms similar triangle, so the space in the host wing can be increased to make it to charge the gas of maximum quantity.Gas can be used unreactable gas such as helium and neon and natural fuels.In addition, the number of host wing not necessarily is restricted to three, a plurality of second host wings be can be provided with charge the quantity of gas and the quantity that body 111 charges gas so that increase.In addition, propeller can be set and replace jet engine 115 with the combustion engine that drives propeller.
Figure 20 is the lateral plan of the aircraft 150 of another embodiment of the present invention, and host wing 151 is arranged on the body 152, and the empennage 154 and the vertical wing 153 are arranged in the rear of body 152.Solar cell 156 is arranged on the surface of host wing 151, towards last.Illumination in the aircraft 150 etc. is that the electric energy by solar cell 156 drives.Solar cell 156 can be set at the surface of body 152 and the surface of empennage 154, towards last.In addition, solar cell 156 is arranged on Fig. 1 to the wing of aircraft shown in Figure 19 and the surface of body, towards last.Represent with imaginary line 156.
Host wing 151 is to make with synthetic resin, light metal such as aluminium etc., is rigidity, and is formed with inner chambers.Accommodate the bag made from flexible material in the cavity, charge lighter-than-air gas in the bag.
A pair of jet engine is arranged on the left and right place, below of host wing 151.
Host wing 151 attaching joints 158, the termination of flexible tube 157 is connected to joint dismantledly.By joint 158, the bag in flexible tube 157 and the host wing 151 is communicated with each other.The other end of flexible tube 157 is connected to and is arranged on ground source of the gas 159.By many clues 160, body 152 removable ground connection are connected with ground.When the aircraft built on stilts, by flexible tube 157,, be full of lighter-than-air gas in the bag in the host wing 151 from source of the gas 159, cargo-carring passenger of aircraft and luggage are promoted by buoyancy, and this buoyancy is owing to gas acts on carry-on.Because being connected to ground-surface clue 160 further is raised at the aircraft that prevents to promote, and near floating being retained in the low ground.At this state, bag is to be inflated buoyancy up to hope on aircraft 150.After not inflating, close the opening of joint 158, remove flexible tube 157 from joint 158.
Discharge then clue 160 with ground-surface be connected so that aircraft 150 at the direction buoyance lift of vertical ground.When aircraft 150 rose to predetermined altitude (for example 100 meters), jet engine was started working so that make aircraft 150 flights, in flight course, because because airfoil lift acts on the aircraft 150, aircraft can rise De Genggao.
As mentioned above, because the rising of aircraft 150 is the buoyancy owing to lighter-than-air gas, runway has not just needed or can be for very short.In addition, start working, therefore can make to reduce near noise at jet engine 155 after the buoyance lift of ground.
When aircraft 150 lands, the lighter-than-air gas that charges in the bag in the host wing 151 at leisure by joint 158 dischargings so that reduce to act on buoyancy on the aircraft 150.Joint 158 can be attached on the aircraft, the imaginary line that is Fig. 1 to 19 is indicated, making it in order externally to supply lighter-than-air gas by flexible tube 157, and after their rise, start jet engine or propeller and the aircraft that flies as the identical situation of aircraft 150.
The bag that charges lighter-than-air gas can be arranged in the body 152.
The present invention can be applicable to autogyro or similar device, and uses the air robot leaf slurry that charges lighter-than-air gas.
The present invention can be used for other form and does not deviate from spirit of the present invention and inner characteristic.All aspects that described embodiment considers as shown, but be not confined to this.Category of the present invention such as claim and be not limited to top description, change is in the claim scope.Huge legendary turtle * quarrels
The bag that charges lighter-than-air gas can be arranged in the body 152.
The present invention can be applicable to autogyro or similar device, and uses the air robot leaf slurry that charges lighter-than-air gas.
The present invention can be used for other form and does not deviate from spirit of the present invention and inner characteristic.All aspects that described embodiment considers as shown, but be not confined to this.Category of the present invention such as claim and be not limited to top description, change is in the claim scope.
Claims (1)
1, a kind of aircraft (110), this aircraft comprises:
A body (111), this body have an axis (122) that extends along heading;
A jet engine (115);
Wing (112,113,114,116,117,119,120,118), they are respectively to make and be included in its volume inside by a kind of flexible material, this space is filled with lighter-than-air gas;
It is characterized in that:
Subtriangular first host wing (112) is installed in the axis (122) that body (111) were gone up and be parallel to body (111), first host wing (112) is provided with solar cell, and being used for provides electric energy to illumination equipment or analogue in the aircraft (110);
(H1 H2) is arranged on first host wing (112) top with closely-spaced for flat top second that at least one is subtriangular and the 3rd host wing (113,114);
A plurality of vertical wings (116,117,119,120) perpendicular to first host wing (112) and each top second and the 3rd host wing (113,114) and the axis (122) that is parallel to body these a plurality of vertical wings (116 are set, 117,119,120) first host wing (112) and second and third host wing (113,114) are coupled together;
A last vertical wing (118) is arranged on and is arranged in a plurality of tops second and the 3rd host wing (113,114) upper surface of top the 3rd host wing (114) of topmost, should go up the parallel to the axis front end of the 3rd host wing (114) of vertical wing (118) and extend to the back-end, and have a vertical tail (124) in its back-end from top;
Jet engine (115) is arranged on top the 3rd host wing (114) that is arranged in topmost, and this jet engine (115) comprises an air intlet towards heading (115a) and the gas vent (115b) that protrude the 3rd host wing (114) rear end from top; And
This aircraft also comprises a guide member (121) that is used for air is directed to air intlet (115a), and this guide member (121) extends to the air intlet (115a) of jet engine (115) and forms one 10 ° to 45 ° angle with an imaginary perpendicular (123) from the last vertical wing (118) front end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN95118241A CN1065192C (en) | 1995-10-30 | 1995-10-30 | Aircraft and method of flying the same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN95118241A CN1065192C (en) | 1995-10-30 | 1995-10-30 | Aircraft and method of flying the same |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1149544A CN1149544A (en) | 1997-05-14 |
| CN1065192C true CN1065192C (en) | 2001-05-02 |
Family
ID=5081621
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN95118241A Expired - Fee Related CN1065192C (en) | 1995-10-30 | 1995-10-30 | Aircraft and method of flying the same |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1065192C (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101624094B (en) * | 2009-08-16 | 2013-02-13 | 宋培荣 | Less weight material, micro-weight material, zero weight material and minus weight material and manufacture method thereof |
| CN102092474A (en) * | 2011-01-28 | 2011-06-15 | 曾道强 | Novel airplane |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2181477Y (en) * | 1994-04-28 | 1994-11-02 | 李晓阳 | Solar push-button plane for prospecting |
| JPH0781694A (en) * | 1993-09-17 | 1995-03-28 | Tokuzo Hirose | Flying object |
-
1995
- 1995-10-30 CN CN95118241A patent/CN1065192C/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0781694A (en) * | 1993-09-17 | 1995-03-28 | Tokuzo Hirose | Flying object |
| US5425515A (en) * | 1993-09-17 | 1995-06-20 | Hirose; Tokuzo | Aircraft |
| CN2181477Y (en) * | 1994-04-28 | 1994-11-02 | 李晓阳 | Solar push-button plane for prospecting |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1149544A (en) | 1997-05-14 |
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