CN107757870A

CN107757870A - Dual system vertical translation aircraft

Info

Publication number: CN107757870A
Application number: CN201610691505.6A
Authority: CN
Inventors: 李海光
Original assignee: Individual
Current assignee: Individual
Priority date: 2016-08-21
Filing date: 2016-08-21
Publication date: 2018-03-06

Abstract

The present invention relates to aircraft field, disclose a kind of dual system vertical translation aircraft, the dual system vertical translation aircraft includes aircraft body, low-speed operations system, high-speed flight system and flying power control system, the afterbody of aircraft body has, the lifting direction wing being symmetrical set centered on the longitudinal axis of aircraft body；Low-speed operations system includes multiple holes for extending vertically through aircraft body marginal zone, and hole is equipped with power control system, the suitable for reading and lower mouth of hole is equipped with dodge gate built with dynamical system in dynamical system；High-speed flight system includes multiple knapsack power systems, and knapsack power system loads onto dynamic control system；The dual system vertical translation aircraft is not only able to be vertically moved up or down, and it can be flown in low-speed operations as helicopter, and the flare maneuver of all helicopters can be completed, can be flown in high-speed flight as fixed wing aircraft, and the flare maneuver of all fixed wing aircrafts can be completed.

Description

Dual system vertical translation aircraft

Technical field

The present invention relates to aircraft field, more particularly to a kind of dual system vertical translation aircraft.

Background technology

Current aircraft is a lot, but the aircraft that can be vertically moved up or down is few.

The content of the invention

It is an object of the invention to provide a kind of dual system vertical translation aircraft, to make up existing vertical translation aircraft The problem of few defect.

To achieve the above object, the invention provides a kind of dual system vertical translation aircraft, dual system vertical lift Aircraft includes aircraft body, and fly at low speed system, high-speed flight system and power control system.

Described aircraft body is that head point, the right and left is arc or linear pattern using the all-wing aircraft design without vertical fin, From head tip, to afterbody, or from head tip straight line to afterbody, afterbody is equipped with the aircraft body longitudinal axis arc always Centered on the lifting direction wing that is symmetrical set；What is be symmetrical set on aircraft body centered on the longitudinal axis also has, Multiple holes for extending vertically through aircraft body the right and left marginal zone, it is equipped with a low-speed operations system in each hole Dynamical system, be equipped with power control system in each dynamical system, activity be equipped with the suitable for reading and lower mouth of each hole Door, there is the air inlet of the knapsack power system in high-speed flight system in aircraft body front portion, in aircraft body afterbody There is the gas outlet of knapsack power system, power control system is equipped with each knapsack power system.

Described low-speed operations system includes multiple holes for extending vertically through aircraft body the right and left marginal zone, hole Quantity be more than 4, including 4, be equipped with a dynamical system in each hole, power be equipped with each dynamical system Control system, the suitable for reading and lower mouth of each hole are equipped with dodge gate；Dynamical system can use jet engine, utilize gas The advantages of stream makes aircraft takeoff and flight, can use fan, and the flabellum of fan is reduced noise, propeller can be used, The power of propeller is more stronger than fan, the variable-pitch propeller oar system of helicopter can also be used, when the displacement spiral shell using helicopter It can realize that low speed is inverted flight when revolving oar system.

Described high-speed flight system includes multiple knapsack power systems, and the quantity of multiple knapsack power systems is 2 More than individual, including 2, the air inlet of knapsack power system is in the front portion of aircraft body, and gas outlet is in aircraft body Afterbody, power control system is equipped with each knapsack power system, and knapsack power system can use jet-propelled start Machine, aircraft is promoted by air-flow, fan can be used, the advantages of flabellum of fan is reduced noise, propeller can be used, The power of propeller is more stronger than fan, the variable-pitch propeller oar system of helicopter can also be used, when the displacement spiral shell using helicopter Winged and inverted flight before being realized when revolving oar system to be switched fast, due to using different engine or propeller, backpack moves Position of the air inlet of Force system on aircraft body has different degrees of rear shifting.

The gas outlet of described knapsack power system, include 5 schemes in the arrangement mode of aircraft body afterbody, Scheme 1 is upper multi-row-type, and scheme 2 is lower multi-row-type, and scheme 3 is middle row's formula, and scheme 4 is more perpendicular integral type, and scheme 5 is more perpendicular points Body formula.

Multi-row-type on the arrangement scheme 1 of described knapsack power system gas outlet, is specifically made up of multiple gas outlets Multiple transverse directions row arranged in a straight line, stacked on top is above aircraft body afterbody；Multiple transverse directions row arranged in a straight line is Refer to more than one transverse direction row arranged in a straight line, wherein comprising transverse direction row arranged in a straight line, the quantity for often discharging gas port is 1 More than individual, wherein being a row comprising a gas outlet.

2 times multi-row-types of arrangement scheme of described knapsack power system gas outlet, are specifically made up of multiple gas outlets Multiple transverse directions row arranged in a straight line, stacked on top is below aircraft body afterbody；Multiple transverse directions row arranged in a straight line is Refer to more than one transverse direction row arranged in a straight line, wherein comprising transverse direction row arranged in a straight line, the quantity for often discharging gas port is 1 More than individual, wherein being a row comprising a gas outlet.

Formula is arranged in the arrangement scheme 3 of described knapsack power system gas outlet, is specifically made up of multiple gas outlets Multiple transverse directions row arranged in a straight line, stacked on top are above aircraft body afterbody transversal line and following；Multiple horizontal straight lines The row of arrangement refers to more than one transverse direction row arranged in a straight line, wherein comprising transverse direction row arranged in a straight line, often discharges gas The quantity of mouth is more than 1, wherein when being a row, an only transverse direction row arranged in a straight line comprising a gas outlet and on afterbody It is lower placed in the middle.

The arrangement scheme more than 4 of described knapsack power system gas outlet erects integral type, specifically by multiple gas outlet groups Into multiple vertical lines arrangement row it is laterally stacked in aircraft body afterbody；The row of multiple vertical lines arrangements refers to one More than vertical lines arrangement row, wherein include the row of vertical lines arrangement, often discharge the quantity of gas port for 1 with On, wherein being a row comprising a gas outlet.

The arrangement scheme more than 5 of described knapsack power system gas outlet is perpendicular split type, specifically by multiple gas outlet groups Into the arrangement of multiple vertical lines row, between the row of multiple vertical lines arrangement at intervals, be horizontally arranged in winged Row device body tail section；The row of multiple vertical lines arrangements refers to the row of more than one vertical lines arrangement, wherein including one The row of vertical lines arrangement, the quantity for often discharging gas port is more than 1, wherein being a row, only one comprising a gas outlet Vertical lines arrangement row when with afterbody center ofthe.

Described power control system includes 4 schemes, and scheme 1 is overall control methods, and scheme 2 controls for chimneying Method, scheme 3 are gas outlet rudder control method, and scheme 4 is Comprehensive Control method.

1 overall control methods of scheme in described power control system, are by changing engine（Start including jet Machine）Or flight attitude or the direction of change of flight device are come in the direction of motor；Particularly with engine support engine or Motor is fixed on interior ring support, interior ring support by vertical pivot and middle ring support axis connection, so in ring support can, with Vertical pivot is axle center left-right rotation, while engine on interior ring support or motor can rotate together, so as to change dynamic air-flow Direction, aircraft is changed posture or direction；Middle ring support is by transverse axis and housing axis connection, housing and aircraft or hole Connection, so middle ring support can, is rotated upwardly and downwardly by axle center of transverse axis, while interior ring support and engine on middle ring support Or motor can rotate together, so as to change the direction of dynamic air-flow, make posture or the direction of aircraft change of flight.

The chimneying control methods of scheme 2 in described power control system, be by change the direction of pipeline one end come Change the airflow direction sprayed in pipeline, flight attitude or direction so as to change of flight device；Specific pipeline is by indent pipe Mutually snap together the pipeline to be formed with outer recessed pipe, the pipeline can up and down, left-right rotation；When using jet engine, Pipeline one end connection engine, the other end can up and down, left-right rotation, the direction by changing pipeline makes the air-flow side of ejection To change, flight attitude or direction so as to change of flight device；When use fan or propeller（Variable-pitch propeller including helicopter Oar system）When, the engine or motor of fan or propeller are fixed one end in the duct with engine support, make fan Or propeller works in pipeline, can also can thus pass through in fan or the air-flow gas outlet pipe laying of propeller Change the direction of pipeline to change the airflow direction sprayed in pipeline, make aircraft change of flight posture or direction；This programme 2 is managed Pipeline in road gas flow optimized method can also use in the market existing, can up and down, the tubing of left-right rotation do pipeline use, Especially in the case where gas flow temperature is not high, can with it is any can up and down, the tubing of left-right rotation do pipeline use.

The gas outlet rudder control method of scheme 3 in described power control system, is to change the direction of air-flow by rudder to make The posture of aircraft change of flight or direction；Specifically in jet engine, fan or propeller（Displacement spiral shell including helicopter Revolve oar system）Air-flow gas outlet horizontal rudder or perpendicular rudder are installed or vertical and horizontal rudder fills together, thus can by control flaps come The direction of air-flow is controlled, flight attitude or direction so as to change of flight device.

The Comprehensive Control method of scheme 4 in described power control system, is overall control methods and chimneying control methods Combination, with overall control methods except that all things in overall control methods in interior ring support are eliminated, directly pipe Pipeline in road gas flow optimized method is fixed in interior ring support, can thus be passed through as the identically controlled pipeline of overall control methods Pipeline changes the direction of air-flow, flight attitude or direction so as to change of flight device.

The described lifting direction wing is located at the left and right sides of aircraft body afterbody, why cry lifting the direction wing, be because There is elevator, rudder and aileron for the lifting direction wing；Lifting direction wing uses two panels design up and down, can be with Open, individually can also be opened up or down simultaneously up and down；The two panels up and down of side is individually opened during high-speed flight The direction wing is lifted, aircraft resistance of opposite side in the case where a collateral resistance is constant is increased suddenly, due to the resistance of side Increase promotes aircraft change of flight direction, and therefore, this lifting direction wing not only has the function that elevator and aileron, also has The effect of rudder.

The invention has the advantages that the dual system vertical translation aircraft is not only able to be vertically moved up or down, and in low speed It during flight, can be flown as helicopter, and the flare maneuver of all helicopters can be completed, can be with high-speed flight Flown as fixed wing aircraft, and the flare maneuver of all fixed wing aircrafts can be completed.

Brief description of the drawings

Fig. 1 is the overall structure diagram of the present invention.

Fig. 2-11 are of the invention, hole distribution and power in the shape and low-speed operations system of aircraft body The distribution schematic diagram of system.

Figure 12 be the present invention knapsack power system gas outlet arrangement mode in scheme 1, the signal of upper multi-row-type Figure.

Figure 13 be the present invention knapsack power system gas outlet arrangement mode in scheme 3, the schematic diagram of middle row's formula.

Figure 14 is the scheme 4 in the arrangement mode of the knapsack power system gas outlet of the present invention, and more perpendicular integral types are shown It is intended to.

Figure 15 is the scheme 5 in the arrangement mode of the knapsack power system gas outlet of the present invention, erects split type show more It is intended to.

Figure 16 is the structural representation of 1 overall control methods of scheme in power control system of the invention.

Figure 17 is the structural representation of the chimneying control methods of scheme 2 in power control system of the invention.

Figure 18 is the structural representation of the gas outlet rudder control method of scheme 3 in power control system of the invention.

Figure 19 is in Figure 17 17 and 18 profile.

In Fig. 1：1-aircraft body, 2-hole, 3-dynamical system, 4-knapsack power system, 5-backpack move Force system air inlet, 6-knapsack power system gas outlet, 7-lifting direction wing, 8-afterbody.

In Fig. 2-11：1-aircraft body, 2-hole, 3-dynamical system.

In Figure 12-15：6-knapsack power system gas outlet, 8-afterbody.

In Figure 16：9-propeller, 10-engine or motor, 11-engine support, 12-interior ring support, 13- Vertical pivot, 14-middle ring support, 15-transverse axis, 16-housing.

In Figure 17：17-outer recessed pipe, 18-indent pipe, 19-pipeline.

In Figure 18：20-horizontal rudder, 21-perpendicular rudder, 22-air-flow gas outlet.

Figure 19 is the profile of the recessed pipe 17 in Figure 17 China and foreign countries and indent pipe 18.

Embodiment

It will be described in detail below with legend additional embodiments；As shown in figures 1-19, the invention provides a kind of dual system Vertical translation aircraft, the dual system vertical translation aircraft include aircraft body 1, and fly at low speed system, high-speed flight system System and power control system.

Described aircraft body 1 is using the all-wing aircraft design without vertical fin, head point, the right and left as shown in Fig. 1-11 For arc or linear pattern, from head tip, to afterbody 8, or 8 from head tip straight line to afterbody, afterbody 8 fills arc always There is the lifting direction wing 7 being symmetrical set centered on the longitudinal axis of aircraft body 1, the global shape of aircraft body 1 is such as Shown in Fig. 1-11；What is be symmetrical set on aircraft body 1 centered on the longitudinal axis also has, multiple to extend vertically through aircraft The hole 2 of the right and left marginal zone of body 1, all holes 2 be all within the marginal zone of the right and left of aircraft body 1, The dynamical system 3 being equipped with each hole 2 in a low-speed operations system, dynamic Control is equipped with each dynamical system 3 System, because power control system has a kinds of schemes, and connected mode is different, thus the connected mode of dynamical system 3 and hole 2 by Power control system determines；Dodge gate is equipped with the suitable for reading and lower mouth of each hole 2, dodge gate is existed for reducing hole 2 The resistance brought during aircraft high-speed flight to aircraft；Backpack in having high-speed flight system in the front portion of aircraft body 1 The air inlet 5 of dynamical system 4, there are the gas outlet 6 of knapsack power system 4, each backpack in the afterbody 8 of aircraft body 1 Power control system is equipped with dynamical system 4, because power control system has kinds of schemes, connected mode is different, so bearing Formula dynamical system 4 and the connected mode of aircraft body 1 are determined by power control system.

Described low-speed operations system includes multiple holes 2 for extending vertically through the right and left marginal zone of aircraft body 1, institute Some holes 2 are all within the marginal zone of the right and left of aircraft body 1, and the quantity of hole 2 is more than 4, including 4, A dynamical system 3 is equipped with each hole 2, the quantity of dynamical system 3 is to have Jing Yin and consideration that is being short of power mostly, each Power control system is equipped with dynamical system 3, the suitable for reading and lower mouth of each hole 2 is equipped with dodge gate, the effect of dodge gate It is the resistance brought for reducing hole 2 in aircraft high-speed flight to aircraft, because power control system has kinds of schemes, And connected mode is different, so dynamical system 3 and the connected mode of hole 2 are determined by power control system；Dynamical system 3 can be with Using jet engine, make aircraft takeoff and flight using air-flow, fan can be used, the flabellum of fan is reduced noise The advantages of, propeller can be used, the power of propeller is more stronger than fan, can also use the variable-pitch propeller system of helicopter System, it can realize that low speed is inverted flight when using the variable-pitch propeller oar system of helicopter；The effect of wherein described dynamical system 3 It is that the power for taking off, landing and flying at low speed is provided for aircraft；The effect of wherein described power control system is control power System 3, and control taking off, land and flying at low speed for aircraft, and control aircraft make various flare maneuvers, wherein institute State, multiple holes 2 for extending vertically through the right and left marginal zone of aircraft body 1 in low-speed operations system, and pacify in hole 2 The dynamical system 3 of dress, its arranged distribution on aircraft body 1 is as shown in Fig. 1-11；Wherein described dodge gate is flying Device is to close when not taking off with high-speed flight, and dodge gate is opened during standby for takeoff, is lived until entering high-speed flight state Dynamic door is just closed, and dodge gate, which is opened, when high-speed flight is slowed down to a certain extent enters low-speed condition, until aircraft drops Fall flight ending activity door just to close.

Described high-speed flight system includes multiple knapsack power systems 4, and the quantity of multiple knapsack power systems 4 is More than 2, including 2, the quantity of knapsack power system 4 is to have Jing Yin and consideration that is being short of power, knapsack power system mostly The air inlet 5 of system 4 is in the front portion of aircraft body 1, and gas outlet 6 is in the afterbody 8 of aircraft body 1, each knapsack power system Power control system is equipped with system 4, because power control system has kinds of schemes, and connected mode is different, so backpack moves The connected mode of Force system 4 and aircraft body 1 is determined by power control system；Knapsack power system 4 can use jet Formula engine, aircraft flight is promoted by air-flow, fan can be used, the advantages of flabellum of fan is reduced noise, can be with Using propeller, the power of propeller is more stronger than fan, can also use the variable-pitch propeller oar system of helicopter, be gone straight up to when using It is winged and inverted flight before being realized during the variable-pitch propeller oar system of machine to be switched fast；The work of wherein described knapsack power system 4 With being power when high-speed flight is provided for aircraft；The effect of wherein described power control system is control knapsack power system System 4, and the high-speed flight of aircraft is controlled, and coordinate co- controlling aircraft to make various flights with the lifting direction wing 7 and move Make, due to using different engine or propeller, the position meeting of the air inlet 5 of knapsack power system 4 in aircraft body 1 There is different degrees of rear shifting.

The gas outlet 6 of described knapsack power system 4, include 5 in the arrangement mode of the afterbody 8 of aircraft body 1 For scheme as shown in Figure 12-15, scheme 1 is upper multi-row-type, and scheme 2 is lower multi-row-type, and scheme 3 is middle row's formula, and scheme 4 is more perpendicular Integral type, scheme 5 are more perpendicular split type.

Multi-row-type on the arrangement scheme 1 of the gas outlet 6 of described knapsack power system 4, as shown in figure 12, specifically by Multiple transverse directions that multiple gas outlets 6 form row arranged in a straight line, stacked on top is above the afterbody 8 of aircraft body 1；Multiple horizontal strokes Refer to more than one transverse direction row arranged in a straight line to row arranged in a straight line, wherein comprising transverse direction row arranged in a straight line, often The quantity for discharging gas port 6 is more than 1, wherein being a row comprising a gas outlet 6.

2 times multi-row-types of arrangement scheme of the gas outlet 6 of described knapsack power system 4, specifically by multiple gas outlets 6 Multiple transverse directions row arranged in a straight line of composition, stacked on top is below the afterbody 8 of aircraft body 1；Multiple transverse directions are arranged in a straight line Row refer to more than one transverse direction row arranged in a straight line, wherein comprising transverse direction row arranged in a straight line, often discharge gas port 6 Quantity is more than 1, wherein be a row comprising a gas outlet 6, due to 2 times multi-row-types of scheme gas outlet 6 position just Position with the gas outlet 6 of multi-row-type in scheme 1 is on the contrary, so legend refers to Figure 12.

Formula is arranged in the arrangement scheme 3 of the gas outlet 6 of described knapsack power system 4, as shown in figure 13, specifically by more The row that multiple transverse directions of the individual composition of gas outlet 6 are arranged in a straight line is stacked on above the transversal line of the afterbody 8 of aircraft body 1 with Face；Multiple transverse directions row arranged in a straight line refers to more than one transverse direction row arranged in a straight line, wherein including a horizontal straight line row During the row of row, an only transverse direction row arranged in a straight line with the afterbody of aircraft body 1 about 8 it is placed in the middle, often discharge the number of gas port 6 Measure as more than 1, wherein being a row comprising a gas outlet 6.

The arrangement scheme more than 4 of the gas outlet 6 of described knapsack power system 4 erects integral type, as shown in figure 14, is specifically The row that the multiple vertical lines being made up of multiple gas outlets 6 arrange, the row of multiple vertical lines arrangements are laterally side by side together, horizontal To the afterbody 8 for being arranged in aircraft body 1；The row of multiple vertical lines arrangements refers to more than one vertical lines arrangement Row, should be in the tail of aircraft body 1 wherein include the row of vertical lines arrangement, during the row of only one vertical lines arrangement The center ofthe of portion 8 is set, and the quantity for often discharging gas port 6 is more than 1, wherein being a row comprising a gas outlet 6.

The arrangement scheme more than 5 of the gas outlet 6 of described knapsack power system 4 is perpendicular split type, as shown in figure 15, is specifically The row that the multiple vertical lines being made up of multiple gas outlets 6 arrange, it is separated by between row's transverse direction of multiple vertical lines arrangements certain Distance, be horizontally arranged in the afterbody 8 of aircraft body 1；The row of multiple vertical lines arrangements refers to more than one vertical straight The row of line arrangement, wherein the row of a vertical lines arrangement is included, should be in aircraft body 1 when only a vertical lines are arranged The center ofthe of afterbody 8 is set, and the quantity for often discharging gas port 6 is more than 1, wherein being a row comprising a gas outlet 6.

1 overall control methods of scheme in described power control system are as shown in figure 16, are by changing engine（Including Jet engine）Or flight attitude or the direction of change of flight device are come in the direction of motor 10；Particularly use engine support 11 engines or motor 10 are fixed on interior ring support 12, and interior ring support 12 is connected by vertical pivot 13 and the middle axle of ring support 14 Connect, so in the can of ring support 12 with vertical pivot 13 for axle center left-right rotation, while the engine or electronic on interior ring support 12 Machine 10 can rotate together, so as to change the direction of dynamic air-flow, aircraft is changed posture or direction；Middle ring support 14 passes through horizontal stroke Axle 15 and the axis connection of housing 16, the so middle can of ring support 14 is rotated upwardly and downwardly with transverse axis 15 for axle center, while middle ring support 14 On interior ring support 12 and engine or motor 10 can rotate together, so as to change the direction of dynamic air-flow, change aircraft The posture or direction, housing 16 for becoming flight are connected with hole 2 or aircraft body 1.

The chimneying control methods of scheme 2 in described power control system, are by changing pipeline 19 as shown in figure 17 Direction, making the air-flow sprayed in pipeline 19 change direction, flight attitude or direction so as to change of flight device；Specifically It is the pipeline 19 in chimneying control methods, is that the pipeline 19 formed is mutually snapped together by outer recessed pipe 17 and indent pipe 18, The profile of outer recessed pipe 17 and indent pipe 18 is as shown in figure 19, the pipeline 19 can up and down, left-right rotation；Start using jet During machine, one end of pipeline 19 connection engine, the other end can up and down, left-right rotation, made by changing the direction of pipeline 19 The airflow direction of ejection changes, flight attitude or direction so as to change of flight device；When use fan or propeller（Including going straight up to The variable-pitch propeller oar system of machine）When, the engine or motor of fan or propeller are fixed on pipeline 19 with engine support In one end, fan or propeller is worked in the pipeline 19, can also be in the air-flow gas outlet installing pipe of fan or propeller Road 19, it thus can change the airflow direction sprayed in pipeline 19 by changing the direction of pipeline 19, change aircraft Flight attitude or direction；Pipeline 19 in the chimneying control methods of this programme 2 can also use in the market existing, can up and down, The tubing of left-right rotation uses to do pipeline 19, especially in the case where gas flow temperature is not high, can with it is any can up and down, The tubing of left-right rotation uses to do pipeline 19.

The gas outlet rudder control method of scheme 3 in described power control system, is to change air-flow by rudder as shown in figure 18 Direction make the posture of aircraft change of flight or direction；Specifically in jet engine, fan or propeller（Including going straight up to The variable-pitch propeller oar system of machine）Air-flow gas outlet 22 horizontal rudder 20 or perpendicular rudder 21 or horizontal rudder 20 and perpendicular rudder 21 are installed together Dress, the direction of air-flow can be thus controlled by control flaps, flight attitude or direction so as to change of flight device.

The Comprehensive Control method of scheme 4 in described power control system is the knot of overall control methods and chimneying control methods Zoarium, from overall control methods as shown in figure 16 unlike eliminate all things in overall control methods in interior ring support 12, Directly the pipeline 19 in chimneying control methods is fixed in interior ring support 12, can thus be controlled as overall control methods Tubing giving sufficient strength 19, change the direction of air-flow by pipeline 19, flight attitude or direction so as to change of flight device.

The described lifting direction wing 7 is as shown in figure 1, why the left and right sides of the afterbody 8 positioned at aircraft body 1, named The direction wing 7 is lifted, is because the lifting direction wing 7 has the function that elevator, rudder and aileron；The lifting direction wing 7 is adopted Designed with upper and lower two panels, can simultaneously open, individually can also open up or down up and down；During high-speed flight individually The lifting direction wing 7 of two panels up and down of side is opened, makes the resistance of aircraft opposite side in the case where a collateral resistance is constant unexpected Increase, because the resistance increase of side promotes aircraft change of flight direction, therefore, this lifting direction wing 7 not only has lifting The effect of rudder and aileron, also has ruddered effect.

The present invention the course of work be：In the dual system vertical translation aircraft standby for takeoff, the work of the upper and lower opening of hole 2 Dynamic door is opened, and the dynamical system 3 in hole 2, which is started working, makes aircraft takeoff, the high-speed flight system when certain altitude is arrived in flight Knapsack power system 4 in system is started working, and aircraft starts to accelerate flight, accelerates to fly at low speed after flying to certain speed Dynamical system 3 is stopped, and dodge gate is closed, and aircraft enters high-speed flight state, when that will arrive at, born Formula dynamical system 4 is reduced speed now, and dodge gate when to a certain extent that slows down is opened, and the dynamical system 3 in low-speed operations system starts Work, knapsack power system 4 continue to slow down, after the dynamical system 3 in low-speed operations system completely takes over flight, born Formula dynamical system 4 is closed, and the dynamical system 3 in low-speed operations system enters low-speed condition after completely taking over flight and reached Destination is landed, and the dynamical system 3 after aircraft landing in low-speed operations system is closed, and dodge gate is closed, and flight terminates；Flight Device can do the flare maneuver that any helicopter can be done, including vertical lift when low-speed operations as helicopter, Flare maneuver can be done as fixed wing aircraft when high-speed flight.

The beneficial effects of the invention are as follows：The dual system vertical translation aircraft is not only able to be vertically moved up or down, and in low speed It can be flown during flight as helicopter, and the flare maneuver of all helicopters can be completed, can picture in high-speed flight Fixed wing aircraft equally flies, and can complete the flare maneuver of all fixed wing aircrafts.

Described above is only that embodiments of the present invention are described in detail, it is noted that for the art Those of ordinary skill for, without departing from the technical principles of the invention, some improvement and deformation can also be made, this A little some improvement and deformation also should be regarded as protection scope of the present invention.

Claims

1. a kind of dual system vertical translation aircraft, including aircraft body, low-speed operations system, high-speed flight system and power Control system；Described aircraft body is that head point, the right and left is arc or straight line using the all-wing aircraft design without vertical fin Type, from head tip, to afterbody, or from head tip straight line to afterbody, afterbody has with the aircraft body longitudinal axis arc always Centered on the lifting direction wing that is symmetrical set, have on aircraft body, it is multiple to extend vertically through aircraft body or so two The hole of side marginal zone, the dynamical system being equipped with each hole in a low-speed operations system, in each dynamical system Equipped with power control system, dodge gate is equipped with the suitable for reading and lower mouth of each hole, it is anterior in aircraft body, have and fly at a high speed The air inlet of knapsack power system in row system, there is the gas outlet of knapsack power system in aircraft body afterbody, There are multiple knapsack power systems on aircraft body, power control system is equipped with each knapsack power system.

2. aircraft according to claim 1, wherein described aircraft body, it is characterised in that aircraft body is to adopt Designed with the all-wing aircraft without vertical fin, head point, the right and left is arc or linear pattern, from head tip always arc to afterbody, or From head tip straight line to afterbody.

3. aircraft according to claim 1, wherein described aircraft body, its feature also has left on aircraft body There are multiple holes for extending vertically through aircraft body in the marginal zone on right both sides.

4. aircraft according to claim 1, wherein described aircraft body, its feature also has in aircraft body tail There is the lifting direction wing being symmetrical set centered on the aircraft body longitudinal axis in portion.

5. aircraft according to claim 1, wherein described hole, it is characterised in that all holes are all in aircraft In the marginal zone of body the right and left, the suitable for reading and lower mouth of each hole is equipped with dodge gate.

6. aircraft according to claim 1, wherein described dodge gate, it is characterised in that hole can be opened and closed Hole, effect are to reduce the resistance that hole is brought in high-speed flight to aircraft, effect also attractive in appearance, waterproof and dustproof in addition.

7. aircraft according to claim 1, wherein the described lifting direction wing, it is characterised in that lifting the direction wing be on The structure design of lower two panels, and can individually open piece or bottom sheet, two panels it can also open simultaneously up and down.

8. aircraft according to claim 1, wherein the dynamical system in described low-speed operations system, it is characterised in that The dynamical system quantity of low-speed operations system is more than 4, including 4.

9. aircraft according to claim 1, wherein the dynamical system in described low-speed operations system, its feature also have All dynamical systems, all in the marginal zone of aircraft body the right and left, all in aircraft body, all extending vertically through In the hole of aircraft body.

10. aircraft according to claim 1, wherein the knapsack power system in described high-speed flight system, its The quantity for being characterised by knapsack power system is more than 2, including 2.

11. aircraft according to claim 1, wherein described knapsack power system, its feature also have all back ofs the body The gas outlet of negative formula dynamical system all in the body afterbody of aircraft sheet, the gas outlets of all knapsack power systems refer to 2 with On quantity, including 2.

12. aircraft according to claim 1, wherein the gas outlet of described knapsack power system includes 5 arrangements Scheme, multi-row-type in scheme 1 therein, it is characterised in that multiple by gas outlet, laterally row arranged in a straight line, stacked on top are flying Above row device body tail section, including a row, the quantity for often discharging gas port is more than one, including one is a row.

13. aircraft according to claim 1, wherein the gas outlet of described knapsack power system includes 5 arrangements Scheme, 2 times multi-row-types of scheme therein, it is characterised in that multiple by gas outlet, laterally row arranged in a straight line, stacked on top are flying Below row device body tail section, including a row, the quantity for often discharging gas port is more than one, including one is a row.

14. aircraft according to claim 1, wherein the gas outlet of described knapsack power system includes 5 arrangements Scheme, formula is arranged in scheme 3 therein, it is characterised in that multiple by gas outlet, laterally row arranged in a straight line, stacked on top are flying Above device body tail section transversal line and following, including a row, the quantity for often discharging gas port is more than one, including one For a row, during an only row with afterbody transversal line center alignment.

15. aircraft according to claim 1, wherein the gas outlet of described knapsack power system includes 5 arrangements Scheme, scheme more than 4 therein erect integral type, it is characterised in that multiple rows arranged by gas outlet vertical lines, it is laterally stacked Together, set with aircraft body afterbody center ofthe, including a row, the quantity for often discharging gas port is more than one, bag It is a row to include one.

16. aircraft according to claim 1, wherein the gas outlet of described knapsack power system includes 5 arrangements Scheme, scheme more than 5 therein are perpendicular split type, it is characterised in that multiple rows arranged by gas outlet vertical lines, are horizontally arranged in The afterbody of aircraft body, the arrangement of multiple vertical lines between row and row between be separated with a certain distance, often discharge the number of gas port Measure for more than one, including one is a row.

17. aircraft according to claim 1, wherein described power control system includes 4 schemes, wherein scheme 1 Overall control methods, it is characterised in that overall control methods are by changing engine（Including jet engine）Or the direction of motor Come flight attitude or the direction of change of flight device.

18. aircraft according to claim 1, wherein described power control system includes 4 schemes, wherein scheme 2 Chimneying control methods, it is characterised in that chimneying control methods are to be sprayed by changing the direction of pipeline one end to change in pipeline The airflow direction gone out, flight attitude or direction so as to change of flight device.

19. aircraft according to claim 1, wherein described power control system includes 4 schemes, wherein scheme 3 Gas outlet rudder control method, it is characterised in that air-flow gas outlet is provided with horizontal rudder or perpendicular rudder or vertical and horizontal rudder fills together.

20. aircraft according to claim 1, wherein described power control system includes 4 schemes, wherein scheme 4 Comprehensive Control method, it is characterised in that all things in interior ring support in overall control methods are eliminated, directly chimneying control Pipeline in preparation method is fixed in interior ring support.