CN104960665B

CN104960665B - A kind of aircraft with plurality of flight

Info

Publication number: CN104960665B
Application number: CN201510432369.4A
Authority: CN
Inventors: 田悦丰; 乔晶晶
Original assignee: Individual
Current assignee: Individual
Priority date: 2015-06-29
Filing date: 2015-07-22
Publication date: 2017-03-08
Anticipated expiration: 2035-07-22
Also published as: CN104960665A

Abstract

The invention discloses a kind of aircraft with plurality of flight, feature is to install wing on the basis of the aircraft by multiple stage combination of drive means produces driving force additional to aid in its flight, the present invention is by the feature organic combination of helicopter class aircraft and fixed-wing class aircraft, so that this aircraft not only can be with the long-distance flight of high-speed and energy-saving mode but also can be with low speed accurately mode accurate flying, present its advantage with plurality of flight combination in complicated aerial mission, in military domain, can be widely applied to investigation patrol, commander's control, Strike, rescue of battlefield, the aspects such as logistics support；In civil area, the aspects such as aerial survey, Material Transportation, medical aid, height rescue, fire-fighting fire extinguishing, agricultural plant protection of taking photo by plane are can be widely applied to.

Description

A kind of aircraft with plurality of flight

Technical field

The present invention relates to a kind of aircraft with plurality of flight.

Background technology

At present, by taking aircraft engine group as an example：In the driving means such as combined engine, mostly using tandem, directly Wire type, the arrangement mode such as square, annular.It is loaded down with trivial details that this mode is limited in assembly connected mode between engine, engine Group mutual when working is mutually disturbed, and can produce unnecessary space, space between engine, causes the volume for combining the unit, weight to increase Plus.Interconnect fixing part in assembly between diverse location engine causes assembly (system) because component is uneven Middle stress concentration, the engine that infinitely adds up eventually result in the collapse of aircraft attachment structure, thus can not infinitely increase assembly Middle engine quantity, load weight ability are also very limited.Additionally, the common disadvantage of current helicopter class aircraft be energy consumption relatively High, voyage is shorter, adverse circumstances stability inferior can be not good enough, thus when can not be long, stably accomplish various aerial missions.

Content of the invention

For solving the above problems, the present invention puts forward a kind of aircraft with plurality of flight, and helicopter class is flown The feature organic combination of row device and fixed-wing class aircraft so that this aircraft not only can with the long-distance flight of high-speed and energy-saving mode but also Which can be presented with the excellent of plurality of flight combination in complicated aerial mission with low speed accurately mode accurate flying Gesture.

First, a distinguishing feature of aircraft is that driving means can be accommodated more with rounded projections arranged in unit volume Many driving means, aircraft can keep optimum space layout under conditions of equal propulsive force is obtained.

Basic principle is aircraft driving device with rounded projections arranged, group triangularity driving means module；Triangle drives The space length between adjacent driven device in dynamic apparatus module is preferably equal；Driving means module with rounded projections arranged Based on become, to direction in space mapping permutation and combination, the combination of drive means body that is made up of multiple stage driving means；Combination of drive means In body, the quantity of driving means is N platform, N >=3.

The method for optimizing of driving means mapping permutation and combination may be used to the statement of lower method of geometry, and triangle ABC is equilateral three Angular, rhombus ABCD is constituted with the equilateral Δ BCD of axial symmetry that Δ ABC is made as axle in the BC side of equilateral Δ ABC, respectively along AB, BD, CD, AC intercept the side equal with the rhombus length of side to both sides reverse extending, connect respective point, constitute countless rhombuses, then will be all The short diagonal of rhombus is coupled together, and forms the rhombus geometry being made up of countless equilateral triangles, the section of geometry It is considered as the preferred installation site of driving means at point, node overlapping position is considered as common location, according to actual needs, each of node is empty Between direction driving means can be all installed.In addition, the shape of combination of drive means body and driving means quantity can be according to flying rings Border or load weight, form etc. need to make respective change.

In the present invention, aircraft is if the less driving means of jet class rotary torsion can be from odd number platform or even number Platform combination of drive means；If the driving means stronger using rotary torsion is produced, for example, engine connects the side of screw Formula, needs preferred even number platform engine connection screw to offset anti-twisted power.For at present, driven by multiple stage driving means flies Screw mode is connected using engine more than row device, thus, the preferred version of the present invention is mapped for rhombus, i.e., with equilateral triangle Diamondwise module being organized based on module, engine being installed at the node of rhombus, engine can be arranged up and down.

The assembly built based on rhombus driving means module (two triangular module compositions) in geometry In, due to the 26S Proteasome Structure and Function characteristic of aircraft, the space length of rhombus module inner opposite angle line needs to adjust according to aircraft In section, also, the connector that constituted of geometry, the corner angle of rhombus can be adjusted.

In the present invention, connected by connector between the driving means of aircraft, connector can be adopted but be not limited to skeleton Or other connectors.According to characteristic and the prior art condition of aircraft, aircraft preferably connects for skeleton, can between skeleton For fixed or movable connection.Refer to manufacture integral framework or solid by fixedly connected part using fixed skeleton Determine the form of skeleton component；Connected by active connection between movable skeleton, skeleton that is foldable or decomposing is made, is being used When skeleton skeleton activity limited by fixture constitute firm form, the consolidating of the skeleton activity that needs to lift restrictions when reducing volume Determine part to can achieve skeleton folding or decompose, aircraft is so efficiently reduced, especially the volume of Large Scale Space Vehicle, convenient Storage and transport.

The second largest feature of the present invention is that aircraft can determine winged according to flight environment of vehicle, the form of load and weight The size, shape and driving means quantity of row device.Remove outside the installation site that driving means are occupied on aircraft, remaining region is equal Can be used as the installation of flight servicing unit or load thing or carry region.Due to the special framework of aircraft of the present invention, aircraft Load carry region or and overall load can be all set in every driving means or every group of driving means region in drive system The region being connected, the purpose for so arranging are to make the driving force produced in aircraft drive system be applied evenly to load Connection between part, driving means in aircraft and load would not occur because stress concentration causes in certain region A series of pernicious chain reaction of the overall flight system of impact.

The third-largest feature of the present invention is that to install wing and wing quantity on the basis of aircraft driving device additional be M, M >= 1.So that skeleton mode connects as an example, wing is connected with airframe by connector, and wing can be with axial rotation.Flying Cheng Zhong, when there is relative velocity between aircraft and air, appropriate adjustment angle of attack wing can produce lift with auxiliary drive Lift is provided to aircraft, especially in low-speed operations, wing is by the different flights of the different angular compliance aircraft of adjustment Attitude, so as to reduce unfavorable resistance to greatest extent.When aircraft has relative velocity with air under special circumstances, aircraft Can rely on airfoil flight or using wing slow down, for example, during aircraft driving device failure can using wing glide as Buffering, is effectively protected aircraft, or the adjustment wing anglec of rotation makes which produce resistance on the direction that advances so as to right Aircraft is slowed down.

The wing that left and right is correspondingly arranged produces rolling power by way of changing differential seat angle makes aircraft that horizontal rolling to occur, Function similar to the aileron rudder of fixed wing aircraft；The wing being correspondingly arranged in front and back or single wing are produced by adjusting the angle of attack Rise or lower pressure makes aircraft that longitudinal pitching to occur, similar to the function of the elevator of fixed wing aircraft.The aircraft with During certain speed flight, wing can produce extra lift so as to reduce the burden of driving means, meanwhile, manipulate wing and produce Rudder face effect make aircraft when changing attitude, can also reduce the burden of driving means, this has saved the energy to a certain extent, Cruising time is extended, also improves load-carrying ability.

In addition, when wing axially rotates and reaches certain angle with fuselage plane, wing is also used as aircraft Fluctuation support device, i.e. undercarriage, so as to effectively reduce structural burden and the take-off weight of aircraft.

Description of the drawings

Several preferred embodiments of the present invention are specifically described below in conjunction with accompanying drawing：

Fig. 1 is the basic distribution schematic diagram of inventive drive means；

Fig. 2 is the geometry embodiment schematic diagram of aircraft driving device mapping arrangement；

Fig. 3 is another embodiment schematic diagram of the geometry of aircraft driving device mapping arrangement；

Fig. 4 is one of aircraft of the present invention and is preferable to carry out layout type schematic diagram；

Fig. 5 is an enforcement layout type schematic diagram of aircraft of the present invention；

Fig. 6 is that another of aircraft of the present invention implements layout type schematic diagram.

Fig. 7 a, Fig. 7 b, Fig. 7 c, Fig. 7 d, Fig. 7 e and Fig. 7 f are the preferred mode of operation side view of aircraft of the present invention respectively.

01- triangle driving means module 02- node 03- mapping body 04- skeleton 05- driving means 06- skeleton connects Fitting 07- wing 08- wing connection 09- screw 10- horizontal reference line 11- geometry reference line 12- starts Machine

Specific embodiment

Fig. 1 shows the basic distribution of the driving means of aircraft of the present invention, and in figure triangle ABC is equilateral triangle, Three apex of triangle are aircraft driving device (05) position, group triangularity driving means module (01)；Preferably, Space length between adjacent driven device (05) is equal；To space based on the driving means module (01) of rounded projections arranged Direction mapping permutation and combination becomes driving means (05) assembly being made up of multiple stage driving means (05), and this in figure rhombus ABCD is It is derived by triangle ABC driving means module and rhombus module is formed, the rest may be inferred, the driving dress of various forms can be formed Put (05) assembly；In driving means (05) assembly, the quantity of driving means (05) is N platform, N >=3.Wherein, (03) is geometry The mapping body of structure intermediate cam shape, (11) are geometry reference line.

In aircraft of the present invention, the preferred embodiment of driving means mapping permutation and combination may be used to the statement of lower method of geometry, If Fig. 2, triangle ABC are equilateral triangle, the equilateral Δ BCD structure of axial symmetry of Δ ABC is made with the BC side of equilateral Δ ABC as axle Diamondwise ABCD, respectively along AB, BD, CD, AC to both sides reverse extending, intercepts the side equal with the rhombus length of side, connects respective point, Countless rhombuses are constituted, then the short diagonal of all rhombuses is coupled together, formed and be made up of countless equilateral triangles (03) Rhombus geometry, node (02) place of geometry is considered as driving means (05) preferably installation site, and node (02) overlaps Place is considered as common location.

In aircraft of the present invention, another embodiment of multiple stage driving means mapping permutation and combination specifically may be used to down several Where method is stated：If Fig. 3, triangle ABC are equilateral triangle, make Δ ABC by symmetric points centered on A, B, C at 3 points respectively Central Symmetry Δ ADE, Δ CPG, Δ BHI, centered on D, E, F, G, H, I point, symmetric points make equilateral triangle respectively, with this Analogize the geometry that can obtain that countless equilateral triangles (03) are constituted, node (02) place of geometry is considered as driving dress (05) preferably installation site is put, node (02) overlapping position is considered as common location.

It should be mentioned that for the best power source effect for playing aircraft, the node in all of above geometry (02) each direction in space can all install driving means (05), wherein optimal with node (02) above-below direction installation effect.This Outward, the size of driving means (05) assembly, shape and driving means (05) quantity can make change as needed.

With regard to state of the art, aircraft driving device is preferably engine, and connector, below will be concrete by taking skeleton as an example Introduce and developed by geometry and several feasibility topology layout schemes of next aircraft.

As Fig. 4, in the preferred version of this specific embodiment offer, engine (12-1), (12-2), (12-3), (12- 4) arranged with rhombus geometry, connected by skeleton (04), engine (12) is fixedly installed in skeleton (04) place, skeleton (04) Between by skeleton connector (06) connect, skeleton connector (06) can be fixed, or movable, engine (12) connection screw (09), wing (07) are connected to be respectively arranged in by wing connection (08) with airframe (04) and send out Motivation (12-2) and the both sides of engine (12-4), wing (07) can be with axial rotation.

Fig. 5 is also a kind of feasibility embodiment of this programme.This in figure can be developed into by the method for geometry of Fig. 2 or Fig. 3 Aircraft layout structure, engine (12-5), (12-6), (12-7), (12-8) are intersected by skeleton (04) with rectangular arranged Connection install, can be fixed connection, or movable connection, engine (12) connection screw (09), wing (07) skeleton (04) both sides are symmetrically arranged on, and wing (07) is respectively Wei Yu engine (12-5) and (12-7) between and engine (12-6) region and (12-8) between, is connected by wing connection (08) between wing (07) and skeleton (04), and wing (07) can With axial rotation.

As Fig. 6, another kind of feasibility embodiment of this programme is represented.Can be developed into by the method for geometry of Fig. 2 or Fig. 3 The aircraft layout structure of this in figure, is combined by three complete triangles driving means module (01), i.e. engine (12-9), (12-10) and (12-11) constitute triangle driving means module (01), engine (12-12), (12-13) with (12-14) constitute triangle driving means module (01), engine (12-15), (12-16) and (12-17) constitute one Triangle driving means module (01), between engine (12) by skeleton (04) connect, can be fixed connection, or Movable connection, engine (12) connection screw (09), coaxial wing (07) is symmetrically arranged on triangle driving means module (01) both sides of engine (12-9) in, another wing (07) are installed on engine in triangle driving means module (01) (12-14) region and between (12-17), is connected by wing connection (08) between wing (07) and skeleton (04), wing (07) all can axial rotation.

In all of above embodiment, due to the characteristic of aircraft, skeleton (04) place all can above-below direction installation engine (12), if there is special demands, also it is not excluded for engine (12) or other devices are installed in other directions.

Fig. 7 in accompanying drawing illustrates several preferred mode of operation of aircraft of the present invention.As schemed, (10) represent level ginseng Line is examined, the direction of arrow is aircraft flight direction.Fig. 7 a is auxiliary lifting and upward flight pattern, and wing (07) is while to updip Rake angle can produce lift and provide lift with assisted engine (12) to aircraft；Fig. 7 b is auxiliary descending flight pattern, wing (07) decline aircraft while downward-sloping angle can produce to push to make every effort to promote, while coaxial wing (07) can be independent in aircraft Action is realized making aircraft change luffing angle such as the effect of elevator in Fixed Wing AirVehicle；Fig. 7 c is low speed drop resistance flight Pattern, wing (07) keep less parallel with engine (12) plane or keep optimal wind with heading, airflow direction The angle of resistance maintains flight optimization state to reduce resistance；Fig. 7 d is cruising flight pattern, flies under the different speed of a ship or plane for reaching Device is respectively provided with optimal performance, and wing (07) can reach optimal aerodynamic arrangement by adjusting the angle of attack, so that flight Device can all assume optimal lift-drag ratio under various attitudes, the speed of a ship or plane.；Fig. 7 e is rolling flight pattern, by coaxial wing (07) Left and right differential deflection produced by rolling moment can make aircraft do roll motor-driven (relative flight device heading or meet stream direction Difference is differential)；When Fig. 7 f needs to land for landing or landing pattern, i.e. aircraft, wing (07) and fuselage plane reach necessarily Angle can be used as the fluctuation support device of aircraft, i.e. undercarriage, and this in figure wing (07) is approximately perpendicular to fuselage plane.If Also can increase with landing face contact site in wing (07) when needing to increase undercarriage size and support or dampening assembly.

It should be noted that, in addition to the embodiments described above, the present invention can also have other embodiments, for example：By In structure and the functional characteristic of aircraft, need not also may be used in strict accordance with equilateral triangle block combiner between some driving means To be the combination of isosceles triangle alignment placement.In the same manner, some driving means also need not be in strict accordance with rhombus block combiner, it is also possible to It is parallelogram alignment placement combination etc..Additionally, the wing in Flight Vehicle Structure of the present invention is also to allow in technical conditions In the case of select installation site.It can be seen that, related equivalent technical scheme all should fall in the protection domain of application claims Interior.

Claims

1. a kind of aircraft with plurality of flight, the aircraft include the combination of drive means body being made up of driving means And wing, it is characterised in that：

A. driving means organize triangularity driving means module with rounded projections arranged；

B. become by multiple stage driving means to direction in space mapping permutation and combination based on the driving means module of rounded projections arranged The combination of drive means body of composition；

C. in combination of drive means body, the quantity of driving means is N platform, N >=3；

D. load carry region or and overall load are respectively provided with every driving means or the driving means module region The region being connected；

E. on the basis of aircraft driving device additional wing is installed；

F. wing quantity is M, M >=1.

2. aircraft according to claim 1, it is characterised in that：Adjacent driven in the triangle driving means module Space length between device is equal.

3. aircraft according to claim 1, it is characterised in that：The method of the mapping permutation and combination is with following geometry side Method is stated, and triangle ABC is equilateral triangle, makes the equilateral △ BCD of axial symmetry of △ ABC with the BC side of equilateral △ ABC as axle Rhombus ABCD is constituted, respectively along AB, BD, CD, AC to both sides reverse extending, the side equal with the rhombus length of side is intercepted, connection is corresponding Point, constitutes countless rhombuses, then couples together the short diagonal of all rhombuses, and formation is made up of countless equilateral triangles Rhombus geometry, is considered as the installation site of driving means at the node of the geometry, node overlapping position is considered as shared position Put.

4. aircraft according to claim 1, it is characterised in that：Aircraft is according to actual needs determining the chi of aircraft Very little, shape and the quantity of driving means and wing.

5. the aircraft according to any one of Claims 1-4, it is characterised in that：Driving means and the shape of wing assembly Shape and driving means, wing quantity make change as needed.

6. aircraft according to any one of Claims 1-4, the aircraft are characterised by：By connector between driving means Connection, connector is using skeleton or other connectors.

7. aircraft according to claim 5, the aircraft are characterised by：Connected by connector between driving means, even Fitting is using skeleton or other connectors.

8. the aircraft according to Claims 1-4 and 7 any one, it is characterised in that：In skeleton mode between driving means Connection, is to be fixedly connected or be flexibly connected.

9. aircraft according to claim 5, it is characterised in that：Connected in skeleton mode between driving means, be fixing Connection is flexibly connected.

10. aircraft according to claim 6, it is characterised in that：Connected in skeleton mode between driving means, be fixing Connection is flexibly connected.

11. aircraft according to claim 3, it is characterised in that：The space of rhombus inner opposite angle line in rhombus geometry Distance needs to adjust according to aircraft.

12. according to Claims 1-4,7 and any one of 9-11 described in aircraft, it is characterised in that：When wing axially revolves Turn with fuselage plane not in same level, wing is used as the fluctuation support device of aircraft.

13. aircraft according to claim 5, it is characterised in that：Do not exist with fuselage plane when wing axially rotates During same level, wing is used as the fluctuation support device of aircraft.

14. aircraft according to claim 6, it is characterised in that：Do not exist with fuselage plane when wing axially rotates During same level, wing is used as the fluctuation support device of aircraft.

15. aircraft according to claim 8, it is characterised in that：Do not exist with fuselage plane when wing axially rotates During same level, wing is used as the fluctuation support device of aircraft.

16. aircraft according to Claims 1-4,7, any one of 9-11 and 13-15, it is characterised in that：Remove on aircraft Outside the installation site for going driving means and wing to occupy, remaining region is used as installation or the carry of flight servicing unit or load thing Region.

17. aircraft according to claim 5, it is characterised in that：On aircraft, removing driving means and wing are occupied Outside installation site, remaining region is used as installation or the carry region of flight servicing unit or load thing.

18. aircraft according to claim 6, it is characterised in that：On aircraft, removing driving means and wing are occupied Outside installation site, remaining region is used as installation or the carry region of flight servicing unit or load thing.

19. aircraft according to claim 8, it is characterised in that：On aircraft, removing driving means and wing are occupied Outside installation site, remaining region is used as installation or the carry region of flight servicing unit or load thing.

20. aircraft according to claim 12, it is characterised in that：On aircraft, removing driving means and wing are occupied Outside installation site, remaining region is used as installation or the carry region of flight servicing unit or load thing.