CN108045575B - Short-distance take-off vertical landing aircraft - Google Patents
Short-distance take-off vertical landing aircraft Download PDFInfo
- Publication number
- CN108045575B CN108045575B CN201711364349.3A CN201711364349A CN108045575B CN 108045575 B CN108045575 B CN 108045575B CN 201711364349 A CN201711364349 A CN 201711364349A CN 108045575 B CN108045575 B CN 108045575B
- Authority
- CN
- China
- Prior art keywords
- wing
- wings
- aircraft
- main
- propeller
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 241000272525 Anas platyrhynchos Species 0.000 claims abstract description 22
- 230000007246 mechanism Effects 0.000 claims description 2
- 230000005484 gravity Effects 0.000 description 10
- 230000000694 effects Effects 0.000 description 6
- 230000009286 beneficial effect Effects 0.000 description 5
- 230000008878 coupling Effects 0.000 description 5
- 238000010168 coupling process Methods 0.000 description 5
- 238000005859 coupling reaction Methods 0.000 description 5
- 241000272517 Anseriformes Species 0.000 description 4
- 230000009471 action Effects 0.000 description 4
- 238000005096 rolling process Methods 0.000 description 4
- 239000003381 stabilizer Substances 0.000 description 4
- 238000009966 trimming Methods 0.000 description 4
- 238000005452 bending Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000004927 fusion Effects 0.000 description 3
- 238000004904 shortening Methods 0.000 description 3
- 244000291564 Allium cepa Species 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 229910003460 diamond Inorganic materials 0.000 description 2
- 239000010432 diamond Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 235000010167 Allium cepa var aggregatum Nutrition 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000037396 body weight Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 230000010006 flight Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 235000021184 main course Nutrition 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000002441 reversible effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/12—Canard-type aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C2009/005—Ailerons
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Toys (AREA)
Abstract
A short-distance take-off vertical landing aircraft comprises a fuselage, a main engine, a vertical tail and main wings, upper wings, end wings and duck wings which are respectively arranged at two sides of the fuselage; extension wings are arranged on the outer sides of the two end wings, ailerons are arranged on the two extension wings, and elevators are arranged on the two upper wings; rudders are arranged at the tail parts of the two end wings; the lower parts of the two end wings are respectively provided with a forward extending supporting structure, and each forward extending supporting structure is provided with a main engine, a main engine propeller and a propeller inclination angle driving device; a retractable main landing gear is arranged at the lower part of each end wing; the rear part of the vertical tail is provided with a backward extending supporting structure, and the backward extending supporting structure is provided with a posture adjusting engine propeller. The aircraft of the invention not only has the performance of short-distance take-off and vertical landing, but also has the flight performances of high speed, long endurance, large range and the like.
Description
Technical Field
The invention belongs to the field of aircraft design, and particularly relates to a wing-connected duck-type pneumatic layout with excellent pneumatic performance, which can realize short-distance take-off and vertical landing of an aircraft.
Background
The aircraft has the characteristics of high speed, high maneuverability and the like, is not blocked by mountains, rivers, deserts and oceans, and does not need to build expensive roads or railways like automobiles and trains. However, the aircraft has limitations, particularly the landing sites, and the aircraft, particularly the large fixed wing aircraft, must depend on the landing of an airport runway, the construction scale of the airport runway is large, the construction scale is generally more than 2 kilometers, and the occupied space is large, and in the range of tens of kilometers of the airport runway, high-rise buildings or non-air-tube air flying objects are not allowed, so that at most a few airports are arranged in one city, and the airports are distributed in a suburb.
The prior aircraft is only suitable for transportation with light weight, urgent time requirement and less voyage. However, the development of high speed railways even presents a serious challenge for this function of the aircraft. Therefore, in the long term development of aircraft, the key problem to be solved is how to lighten, even break away from the dependence on the airfield runway.
The wing-connected duck-type layout aircraft comprehensively utilizes the pneumatic/structure integrated design technology and has the characteristics of high effective lift force, high cruising lift-drag ratio of the whole aircraft, light engine body weight, strong main body structure, large payload space in the aircraft, long clearance time, good low-altitude/low-speed performance, excellent take-off and landing performance and the like.
The conventional layout aircraft mainly depends on the wing to generate the lift force required by the whole aircraft flight, and the wing generates certain bending and torsion moment additionally while generating the lift force, and a stronger and heavier wing structure is required to be adopted for bearing, so that a larger structural weight is required to be paid. The coupling wings are arranged in a duck-shaped mode, and are not only lifting surfaces of an airplane, but also bearing frames of the lifting surfaces, so that bending moment and torque generated by the wings can be converted into tensile stress to the end wings and the vertical tails, the load distribution of the wings along the spanwise direction is greatly optimized, and the structural weight and the total weight of the wings are greatly reduced.
The aircraft with the conventional layout adopts the cooperation of the wings and the tail wings to realize the longitudinal trimming control of the whole aircraft, so that certain lift loss is required for achieving the longitudinal trimming of the whole aircraft under different gravity center conditions. The aircraft with the coupling wing duck-shaped layout can utilize three groups of lifting surfaces to participate in longitudinal trim control, is very beneficial to reducing the loss of longitudinal trim lifting force, and can even realize the forward trim control function.
The conventional layout aircraft adopts the vertical tail fin as a main course stabilizer, and the rudder is positioned on the vertical tail, so that the improvement of course stability and operability requires larger vertical tail and rudder, and the vertical tail has large weight and complex structure. The aircraft with the coupling wing ducks layout can realize the control of the course stability characteristics of the aircraft by comprehensively utilizing the end wings and the rudders arranged on the end wings.
The ailerons of the conventional layout aircraft are arranged on the main wing and are close to the fuselage, and if the roll operation efficiency is to be improved, larger aileron control surfaces must be adopted. And the aircraft adopts a coupling wing ducks layout, and ailerons are installed by utilizing forward-swept extension wings, so that the high-efficiency roll control of the whole aircraft can be realized under the condition of smaller aileron control area.
The aircraft with conventional layout mainly depends on lifting surfaces such as wings and tail wings to generate lifting force required by flight, and only when the flight speed reaches high, the lifting force enough to support the weight of the aircraft can be generated, and as a result, the lifting and landing running distances of the aircraft are necessarily long. The aircraft adopting the layout can utilize the engine tilting control technology to generate certain lifting force through power tilting, which is equivalent to reducing the take-off and landing weight of the aircraft, greatly reducing the take-off and landing speed or the landing ground speed of the aircraft and greatly shortening the take-off and landing ground running distance of the aircraft.
When an airplane with a conventional layout takes off and land, longitudinal control moment is mainly generated by virtue of pneumatic efficiency of a control surface. The aircraft adopting the layout can utilize the engine tilting and control technology to generate control moment such as pitching, rolling and the like, particularly in the take-off and landing stage of the aircraft, the engine power tilting and control can be adopted to generate large head-up moment, so that the aircraft can achieve a large controllable attack angle under the condition of taking-off and reducing speed, and the aircraft is very beneficial to the lift off of the aircraft in the take-off stage; the method can also create conditions for realizing landing grounding of the aircraft with a large attack angle (near stall attack angle) and a small speed (even vertically downwards) in the landing stage.
A good aircraft is an art with the smallest energy effort and the largest possible efficient use of aerodynamic forces for safe and reliable flight. The aircraft may have excellent vertical take-off and landing capabilities provided that the engine propellers mounted in front of the end wings have sufficient tension to lift off the aircraft "dry land scallion" from the ground, and such aircraft may even perform various flights similar to helicopters, but tend to result in significant redundancy in its power during long cruise flight phases, thereby necessarily providing significant redundancy in structural strength and aircraft weight, so a short take-off/vertical landing aircraft may be the best choice.
Disclosure of Invention
The invention aims to overcome the defects and shortcomings of the prior art and provide a short-distance take-off vertical landing aircraft, which not only can realize short-distance take-off, but also can ensure that the aircraft can finish taking-off smoothly on a short-distance runway or even without a special runway, and can finish safe landing on any flat ground under the condition of no runway, and meanwhile, the aircraft has the flight performances of high speed, long endurance, large range and the like.
In order to achieve the above purpose, the technical scheme of the invention is as follows:
a short-distance take-off vertical landing aircraft comprises a main body, a main engine, a vertical tail and main wings, upper wings, end wings and duck wings which are respectively arranged at two sides of the main body; the upper parts of the two end wings are respectively connected with the vertical tail through an upper wing arranged above the machine body; extension wings connected with the upper wings are arranged on the outer sides of the two end wings; the elevators are arranged on the two upper wings, and are characterized in that: the lower parts of the two end wings are provided with forward extending support structures, each forward extending support structure is provided with a main engine, a main engine propeller and a propeller inclination angle driving device, and the lower part of each end wing is provided with a retractable main undercarriage; and a backward extending support structure is arranged at the rear part of the vertical tail, and a posture adjusting engine propeller is arranged on the backward extending support structure. Preferably, in the above technical solution, each of the two extending wings is provided with an aileron; the tail parts of the two end wings are provided with rudders.
Preferably, the main wing, the duck wing, the upper wing and the extension wing adopt forward swept wings, backward swept wings or straight wings.
Preferably, the main wing adopts a sweepback wing, and the upper wing adopts a sweepforward wing. The main wing is slightly provided with a dihedral angle; the upper wing is slightly provided with a dihedral angle.
Preferably, the propeller pitch drive means employs a ball screw drive mechanism.
Preferably, the end wing and the extension wing are conventional wing type, laminar flow wing type, high lift wing type or supercritical wing type. The front edge of the end wing is provided with a sweepback angle, and the rear edge of the end wing is provided with a sweepforward angle.
Preferably, the blades of the main engine propeller and the attitude-adjusting engine propeller are two-blade propeller, three-blade propeller, four-blade propeller, five-blade propeller or six-blade propeller.
Compared with the prior art, the invention has the following advantages and outstanding technical effects:
the invention can realize short-distance take-off, and can smoothly finish take-off on a runway with a shorter distance, even without a special runway; the vertical landing can be realized, and the aircraft can finish the safe landing on any flat ground under the condition of no runway. The aircraft provided by the invention has the characteristics of short-distance take-off/vertical landing performance, high-speed, long-endurance and large-range flight performance, and larger task load. The specific aspects are as follows:
(1) the connecting wing ducks (namely, the main wing, the upper wing and the synthetic appearance of the duckwing) are adopted, and the connecting wing is not only a lifting surface of an aircraft, but also a bearing frame of the lifting surface, so that bending moment and torque generated by the wing can be converted into tensile stress to the end wing and the vertical wing, the load distribution of the wing along the span direction is greatly optimized, and the structural weight and the total weight of the wing are greatly reduced.
(2) By adopting the coupling wing duck type layout aircraft, three groups of lifting surfaces can be used for participating in longitudinal trim control, which is very beneficial to reducing the lift loss of longitudinal trim and even realizing the forward trim control function. (3) The invention can comprehensively utilize the end wing and the rudder arranged on the end wing to realize the control of the course stability characteristics of the aircraft. (4) By adopting the invention, the main engine propeller inclination angle driving device can be utilized to generate certain lifting force through power tilting, which is equivalent to reducing the take-off and landing weight of the aircraft, greatly reducing the take-off and landing speed or the landing ground speed of the aircraft and greatly shortening the take-off and landing ground running distance of the aircraft. (5) The invention can generate control moment such as pitching, rolling and the like by utilizing the main engine propeller inclination angle driving device, particularly in the take-off and landing stage of the aircraft, the main engine propeller inclination angle driving device can generate large head-up moment, so that the aircraft can achieve a large controllable attack angle under the condition of taking-off and slowing-down, and the high lift off of the aircraft is very beneficial to the take-off stage; the method can also create conditions for realizing landing grounding of the aircraft with a large attack angle (near stall attack angle) and a small speed (even vertically downwards) in the landing stage.
Drawings
Fig. 1 is a schematic view of the external structure of a short take-off vertical landing aircraft (landing gear down, engine propeller vertically up) according to the present invention.
Fig. 2 is a top view of a landing gear down and engine propeller up 45 ° tilting for a short take-off vertical landing aircraft provided by the present invention.
Fig. 3 is a vertical forward tilting top view of an engine propeller with a retracted landing gear of a short-distance take-off vertical landing aircraft.
Fig. 4 is a vertical upward tilting side view of an engine propeller with landing gear down of a short take-off vertical landing aircraft provided by the present invention.
Fig. 5 is a side view of a landing gear stowed, engine propeller tilted up 45 ° of a short take-off vertical landing aircraft provided by the present invention.
Fig. 6 is a vertical forward tilting side view of an engine propeller with landing gear stowed for a short take-off vertical landing aircraft provided by the present invention.
In the figure, 1-fuselage; 2-duck wings; 3-main wings; 4-upper wings; 5-extending wings; 6-end wings; 7-elevators; 8-ailerons; 9-rudder; 10-vertical fin; 11-propeller pitch drive means; 12-main engine propeller; 13-extending the support structure rearward; 14-adjusting the attitude of the engine propeller; 15-retractable main landing gear; 16-retractable nose landing gear; 17-forward extending support structure.
Detailed Description
The invention will be described in detail below with reference to the drawings and the detailed description.
As shown in fig. 1, the short-distance take-off vertical landing aircraft provided by the present invention includes: the aircraft comprises an aircraft body 1, an active engine, duck wings 2 arranged on two sides of the front end of the aircraft body 1, main wings 3, upper wings 4 and end wings 6 respectively arranged on two sides of the aircraft body 1, and a vertical fin 10 arranged above the tail of the aircraft body 1; the end wings 6 are arranged at the end parts of the main wings 3 at two sides of the fuselage, the upper parts of the two end wings 6 are respectively connected with a vertical tail 10 arranged at the tail part of the fuselage 1 through an upper wing 4 arranged above the fuselage 1, and the two upper wings 4 are respectively provided with an elevator 7; the outer sides of the two end wings 6 are provided with extension wings 5 connected with the upper wings, and ailerons 8 are arranged on the two extension wings 5; the tail parts of the two end wings 6 are provided with rudders 9. A front extending supporting structure 17 is arranged at the lower parts of the two end wings 6, a main engine and a propeller inclination angle driving device 11 are arranged on each front extending supporting structure 17, and a main engine propeller 12 is arranged on the main engine; the forward extending support structure 17 is internally provided with a ball screw inclination angle driving device 11 which can adjust the angle of the main engine propeller 12.
The lower parts of the two end wings 6 are respectively provided with a retractable main landing gear 15, and the middle part under the machine body is provided with a retractable nose landing gear 16; a rear extending support structure 13 is arranged above the rear part of the vertical fin 10, a posture-adjusting engine propeller 14 is arranged above the extending support structure 13, and the blades of the main engine propeller 12 and the posture-adjusting engine propeller 14 are two-blade, three-blade, four-blade, five-blade or six-blade propellers.
The main wing 3, the duck wings 2, the upper wing 4 and the extension wings 5 adopt forward swept wings, backward swept wings or straight wings. The main wing 3 is swept back, the upper wing 4 is swept forward, a front-back wing layout form is formed, the aerodynamic efficiency is high, and the lift-increasing effect of two groups of wing surfaces can be fully exerted. The extension wings 5 increase the effective lifting area of the whole aircraft, and greatly improve the effective lifting force of the aircraft. The main engine is mounted on a front extension support structure 17 at the lower part of the end wing, and the tilting control of the engine propeller is realized by using a ball screw on the front extension support structure 17. When the main engine propeller 12 tilts upwards to work in a lifting state, almost no shielding exists in the downwash direction, the lift-increasing pneumatic efficiency of the rotor wing can be fully exerted, and the effective power lifting force is provided for the whole engine in the lifting stage, so that the power lifting force loss caused by shielding of the downwash is avoided. When the main engine propeller 12 is in a vertical upward and lift-increasing maximum state, the propeller is sufficiently close to the ground, so that the lift-increasing efficiency of the propeller near the ground can be greatly enhanced, and the lift-increasing and lowering performance of the aircraft can be improved. In the cruising flight phase of the aircraft, the slip stream generated by the main engine propeller 12 does not generate adverse aerodynamic interference on the wing 3; at this time, the propeller slipstream flows backward through the end wing 6 and the main wing 3, which can generate favorable aerodynamic interference to the end wing 6 and the main wing 3, and increase the lift-drag ratio of the main wing 3 and the directional stability of the end wing 6. The retractable main landing gear 15 is arranged below the end wing 6, so that the structural advantage of the aircraft is fully utilized, and the available space inside the fuselage 1 and the wings 3 is increased.
The aircraft is designed according to the aerodynamic principle, has the characteristics of small resistance, large effective lifting surface, high lift-drag ratio and the like, and the main wing 3 adopts a sweepback angle, so that the main wing 6 is far away from the gravity center of the aircraft as far as possible, and the direction stability of the vertical stabilizer of the main wing 6 is enhanced. The upper wing 4 adopts a forward swept wing, and the forward swept wing has excellent aerodynamic performance, can greatly improve the low-speed maneuvering performance of an airplane, obviously reduces the resistance in transonic speed flight, and has good stall characteristic under a large attack angle. The main wing 3 of the aircraft is slightly provided with a dihedral angle, and the upper wing 4 is slightly provided with a dihedral angle, so that the appearance of the top view and the front view of the aircraft wing (comprising the main wing 3 of the upper wing 4) are approximate to a diamond, the overall rigidity of the aircraft is good, and the structural bearing characteristic is good. In the design of the aircraft, the distance between the wing surfaces of the main wing 3 and the upper wing 4 is enough, and the mutual interference between the main wing 3 and the upper wing 4 is smaller, so that the aerodynamic characteristics of the two groups of wing surfaces can be fully exerted. The duck wings 2 are arranged near the aircraft nose of the aircraft, so that the total lift force of the aircraft is improved, the longitudinal control capability of the aircraft is greatly improved, and the leading edge vortex pulled out by the duck wings 2 can stabilize the upper boundary layer of the main wing 3 under certain conditions (mainly under the condition of a flat flight state), so that the air flow separation is delayed, and the effective lift force and the stall attack angle of the main wing 3 are increased. The extension wing 5 increases the effective lifting area of the whole aircraft, and has great lifting efficiency because the extension wing 5 is just near the center of gravity of the whole aircraft and can provide lift for the whole aircraft almost without trimming.
The forward edge of the end wing 6 is swept back, and the backward edge of the end wing 6 is swept forward, so that the distance between the vertical stabilizer of the end wing 6 and the gravity center of the aircraft can be increased, and the direction stability of the aircraft is improved. A main engine and a propeller inclination angle driving device are arranged in front of the lower parts of the left end wing 6 and the right end wing 6, and a retractable main landing gear 15 is arranged in the middle of the lower parts of the left end wing 6 and the right end wing 6; rudders 9 are arranged at the tail parts of the two end wings 6; the installation position of the rudder 9 is positioned between the upper wing 4 and the main wing 3, so that the upper wing 4 and the main wing 3 generate stronger end wing effect on the rudder 9, the aerodynamic efficiency of the rudder 9 can be increased, and the rudder surface efficiency of the rudder can be improved; because the pneumatic center of the rudder 9 control surface is close to the vertical gravity center of the whole engine, the non-command rolling moment generated by rudder deflection is greatly reduced; the aileron 8 arranged on the extension wing 5 is close to the longitudinal gravity center of the airplane, so that the deflection of the aileron 8 does not generate large non-instruction pitching moment, the comprehensive effect is achieved, the roll angle control precision and the crosswind landing resistance of the airplane are greatly improved, and the control quality of the airplane is improved.
In the take-off stage, the 'dry land shallot pulling' type vertical take-off and landing of the aircraft can be realized as long as the weight of the aircraft is close to the power lift force of the engine propeller. Even if the power lift force of the engine is insufficient to directly lift the aircraft, the take-off performance of the aircraft can be greatly improved, and short-distance take-off is realized: in the stage of taking off, the aircraft still needs to slide on the ground to accelerate, and when the aircraft has a certain flying speed, the main engine propeller 12 tilts upwards by a certain angle, so that the engine generates a certain power lift force while generating forward pulling force; under the action of dynamic lift force, the aircraft generates head-up moment, so that the aircraft can use a large takeoff attack angle even under a low-speed condition, the effective lift force of the lifting surface of the whole aircraft is increased, and the aircraft can lift off from the ground with a short running distance. Then, the lift force of the attitude-adjusting engine propeller 14 is gradually increased, the flight attack angle is gradually reduced, the flight resistance is reduced, the main engine propeller 12 is gradually tilted forwards, the tension component of the propeller is increased, the aircraft continuously accelerates and flies, the total lift force is increased along with the increase of the flying speed until the lift force generated by each lifting surface of the aircraft is enough to support the total flight weight, and the aircraft can shift to a high-efficiency cruise flight stage of the fixed wing.
In the landing phase, vertical landing of the aircraft can be achieved as long as the weight of the aircraft is close to the engine power lift. Even if the power lift force generated by the engine is insufficient to support the landing weight of the whole aircraft, the landing speed of the aircraft can be greatly reduced: when landing and sliding down to approach the ground, the engine can work at full load, most of thrust acts in the lifting direction by utilizing the propeller inclination angle driving device 11, and the generated lifting force is equivalent to reducing the landing weight of the aircraft, so that the landing grounding speed of the aircraft is greatly reduced. At the later stage of landing, the main engine propeller 12 can be completely vertical upwards and run in the maximum working state, at this time, under the action of the head-up moment generated by the main engine propeller 12, the aircraft can generate a larger attack angle and a pitch angle, so that the main engine propeller 12 and the attitude-adjusting engine propeller 14 generate the largest power lift force and simultaneously generate a larger thrust in the flying speed direction, the aircraft can be rapidly decelerated, the aircraft is kept to move forwards in the attitude with a large attack angle and large aerodynamic resistance, the aircraft can be ensured to move forwards in the attitude with a large pitch angle and large aerodynamic resistance after being grounded even if the lift force of the main engine propeller 12 is insufficient to ensure that the aircraft lands vertically, and the aircraft can be ensured to move forwards in the attitude with a large pitch angle and a large aerodynamic resistance after being grounded, thereby greatly shortening the landing sliding distance.
Example 1:
the embodiment of the invention provides an aircraft for short-distance take-off and vertical landing, which comprises: the wing-mounted aircraft comprises a fuselage 1, duck wings 2 arranged on two sides of the front end of the fuselage 1, main wings 3, upper wings 4 and end wings 6 respectively arranged on two sides of the fuselage 1, and a vertical tail 10 arranged above the tail of the fuselage 1; the end wings 6 are arranged at the end parts of the main wings 3 at two sides of the fuselage, the upper parts of the two end wings 6 are respectively connected with a vertical tail 10 arranged at the tail part of the fuselage 1 through an upper wing 4 arranged above the fuselage 1, and the two upper wings 4 are respectively provided with an elevator 7; the outer sides of the two end wings 6 are provided with extension wings 5 connected with the upper wings, and ailerons 8 are arranged on the two extension wings 5; the tail parts of the two end wings 6 are provided with rudders 9. A front extension supporting structure 17 is arranged at the lower part of the two end wings 6, a main engine and a propeller inclination angle driving device 11 are arranged on each front extension supporting structure 17, the propeller inclination angle driving device 11 is used for adjusting the inclination angle of the propeller (see fig. 2, 3, 4, 5 and 6), and the propeller inclination angle driving device 11 can adopt a ball screw driving device. The lower parts of the two end wings 6 are provided with retractable landing gears 15; a rear extending support structure 13 is arranged above the rear part of the vertical fin 10, and a posture adjusting engine propeller 14 is arranged above the extending support structure 13.
The aircraft is designed according to the aerodynamic principle, and has the characteristics of small resistance, large effective lifting surface, high lift-drag ratio and the like, the main wing 3 adopts the backward swept wing, the upper wing 4 adopts the forward swept wing, the forward swept wing has excellent aerodynamic performance, the low-speed maneuvering performance of the aircraft can be greatly improved, the resistance in flying below transonic speed is obviously reduced, and the aircraft has good stall characteristic under a large attack angle. The main wing 3 of the aircraft is slightly provided with a dihedral angle, and the upper wing 4 is slightly provided with a dihedral angle, so that the top view and front view of the main wing 3 and the upper wing 4 of the aircraft are similar to diamond shapes, the overall rigidity of the aircraft is good, and the structural bearing characteristic is good. In the design of the aircraft, the distance between the wing surfaces of the main wing 3 and the upper wing 4 is enough, and the mutual interference between the main wing 3 and the upper wing 4 is smaller, so that the aerodynamic characteristics of the two groups of wing surfaces can be fully exerted. The duck wings 2 are arranged near the aircraft nose of the aircraft, so that the lift force of the whole aircraft is improved, and the longitudinal control capability of the whole aircraft is greatly improved; the leading edge vortex towed out by the canard 2 can stabilize the upper surface boundary layer of the main wing 3 under certain conditions (mainly in the flat flight condition), thereby delaying the airflow separation, so that the effective lift and stall attack angle of the main wing 3 are increased. The extension wing 5 increases the effective lifting area of the whole aircraft, and has great lifting efficiency because the extension wing 5 is just near the longitudinal gravity center of the whole aircraft and can provide lift for the whole aircraft almost without trimming.
In the invention, the front edge of the end wing 6 is swept back, and the rear edge of the end wing 6 is swept forward, which is beneficial to enlarging the distance between the vertical stabilizer of the end wing 6 and the center of gravity of the whole aircraft, improving the directional stability of the aircraft, and arranging a main engine and a propeller inclination angle driving device 11 on each forward extending support structure 17; a retractable main landing gear 15 is arranged at the middle position of the lower part of the left end wing 6 and the right end wing 6; the rudder 9 is arranged at the tail part of the end wing 6 and is positioned between the wing surfaces of the upper wing 4 and the main wing 3, so that the upper wing 4 and the main wing 3 generate stronger end wing effect on the rudder 9, the aerodynamic efficiency of the rudder 9 can be increased, and the rudder 9 control surface efficiency can be improved. Because the pneumatic center of the rudder surface of the rudder 9 is close to the vertical gravity center of the whole engine, the non-command rolling moment generated by deflection of the rudder 9 is greatly reduced; meanwhile, the aileron 8 is arranged on the extension section 5, and because the longitudinal gravity center of the whole aircraft is approached, the aileron 8 deflects without generating large non-instruction pitching moment, the comprehensive effect is achieved, the roll angle control precision and the crosswind landing resistance of the aircraft are greatly improved, and the control quality of the aircraft is improved.
According to the aircraft, the fuselage 1 and the main wing 3 of the aircraft are subjected to wing body fusion treatment, and the fuselage 1 and the duck wings 2 are subjected to wing body fusion treatment, so that the structural strength of the joint of the wing 3 and the duck wings 2 of the fuselage 1 is increased on the premise of improving the aerodynamic efficiency of the aircraft; the vertical fin 10 is in fusion connection with the machine body 1, so that the strength is increased. The main wing 3, the duck wings 2, the upper wing 4, the extension wings 5 and the end wings 6 adopt conventional wing profiles, laminar flow wing profiles, high lift wing profiles or supercritical wing profiles. The duck wings 2 and the extension wings 5 are forward swept wings, backward swept wings or straight wings.
Example 2:
the embodiment of the invention provides a short-distance take-off aircraft, which comprises: the wing structure comprises a machine body 1, duck wings 2 arranged on two sides of the front end of the machine body 1, main wings 3 and upper wings 4 arranged on two sides of the machine body 1, end wings 6 and a vertical tail 10 arranged above the tail of the machine body 1; the end parts of the main wings 3 at the two sides of the machine body 1 are respectively provided with an end wing 6, and the upper parts of the two end wings 6 are respectively connected with a vertical tail 10 arranged at the tail part of the machine body through an upper wing 4 arranged above the machine body 1; the outer sides of the two end wings 6 are provided with extension wings 5 connected with the upper wings; the two upper wings 4 are provided with elevators 7, the two extension wings 5 are provided with ailerons 8, and the tail parts of the two end wings 6 are provided with rudders 9; the lower parts of the two end wings 6 are provided with forward extending support structures 17, and the front ends of the forward extending support structures 17 are provided with propeller inclination angle driving devices 11; the main engine propeller 12 is arranged on the propeller inclination angle driving device; the lower parts of the two end wings 6 are provided with retractable main landing gears 15; a backward extending support structure 13 is arranged above the rear part of the vertical fin 10, and a posture adjusting engine propeller 14 is arranged above the backward extending support structure 13.
In the take-off stage, the aircraft can fly off the ground vertically as long as the weight of the aircraft is close to the power lift of the main engine propeller.
Even if the power lift force of the main engine propeller 12 is insufficient to directly lift the aircraft, the take-off performance of the aircraft can be greatly improved, and short-distance take-off can be realized: in the take-off stage, the aircraft still needs to slide on the ground to accelerate, and when the aircraft has a certain flying speed, the main engine propeller 12 tilts upwards by a certain angle, so that the main engine propeller generates a certain power lift force while generating forward pulling force; the power lift force of the main engine propeller 12 also generates larger head-up moment, and the control surface efficiencies of the duck wings 2 and the elevators 7 are superposed; a retractable main landing gear 15 is arranged below the end wing 6, so that the aircraft has a large enough floor wiping angle; results of its combined action: the aircraft can use a large takeoff attack angle even under the low-speed condition, so that the effective lift force of the lifting surfaces of the whole aircraft duck wings 2, the main wings 3, the upper wings 4 and the extension wings 5 is increased, and the aircraft is lifted off from the ground with a short running distance. Then, the lift force of the attitude-adjusting engine propeller 14 is gradually increased, the flight attack angle is gradually reduced, the flight resistance is reduced, the main engine is gradually tilted forwards, the tension component of the main engine propeller 12 is increased, the aircraft continuously accelerates and flies, the lift force of each lifting surface of the aircraft is increased along with the increase of the flying speed until the lift force generated by each lifting surface of the aircraft is enough to support the flight weight of the whole aircraft, and the aircraft can be shifted to a high-efficiency cruise flight stage of the fixed wing.
Example 3
Embodiments of the present invention provide a vertical (short-range) landing aircraft, the aircraft comprising: the wing structure comprises a machine body 1, duck wings 2 arranged on two sides of the front end of the machine body, main wings 3, upper wings 4, end wings 6 arranged on two sides of the machine body 1 and a vertical tail 10 arranged above the tail of the machine body; the end parts of the main wings 3 arranged on the two sides of the machine body are respectively provided with an end wing 6, and the upper parts of the two end wings 6 are respectively connected with a vertical tail 10 arranged on the tail part of the machine body through an upper wing 4 arranged on the upper part of the machine body; the outer sides of the two end wings 6 are provided with extension wings 5 connected with the upper wings; the two upper wings 4 are provided with elevators 7, the two extension wings 5 are provided with ailerons 8, and the tail parts of the two end wings 6 are provided with rudders 9; the lower parts of the two end wings 6 are provided with forward extending support structures 17, and the front ends of the forward extending support structures 17 are provided with propeller inclination angle driving devices 11; a propeller engine is arranged on the propeller inclination angle driving device; the lower parts of the two end wings 6 are provided with retractable main landing gears 15; a backward extending support structure 13 is arranged above the rear part of the vertical fin 10, and a posture adjusting engine propeller 14 is arranged above the backward extending support structure 13.
In the landing phase, vertical landing of the aircraft can be achieved as long as the weight of the aircraft is close to the power lift of the main engine propeller 12.
Even if the dynamic lift generated by the main engine propeller 12 is insufficient to support the landing weight of the whole aircraft, the landing speed of the aircraft can be greatly reduced. When the aircraft is landed and slipped down to be close to the ground, the main engine propeller 12 can work at full load, and most of thrust acts in the lifting direction by utilizing the propeller inclination angle driving device 11, so that the lifting force generated by the main engine propeller 12 is equivalent to the reduction of the landing weight of the aircraft. At the later stage of landing, the main engine propeller 12 can be completely vertical upwards and run in the maximum working state, at the moment, under the combined action of the lifting moment generated by the main engine propeller 12, the duck wings 2 and the elevators 7, the aircraft can generate a larger attack angle or pitch angle, at the moment, the main engine propeller 12 and the attitude-adjusting engine propeller 14 generate the maximum power lift force and also generate a large reverse thrust in the flying speed direction, so that the aircraft is rapidly decelerated; meanwhile, because the adopted retractable main landing gear 15 has almost unlimited ground wiping angles, the aircraft can ground and move forwards in a large attack angle/large aerodynamic resistance gesture, and even if the lifting force of the main engine propeller is insufficient to ensure the aircraft to vertically land, the landing running distance can be greatly shortened.
In addition, the oversized main track of the retractable main landing gear 15 can ensure that the lateral course stability of the aircraft is not problematic when the aircraft is lifted off at a large angle of attack and lands at a large angle of attack.
The duck wings 2, the main wings 3, the upper wings 4, the end wings 6 and the extension wings 5 can adopt conventional wing profiles, laminar flow wing profiles, high lift wing profiles or supercritical wing profiles, and the blades of the main engine propeller 12 and the attitude-adjusting engine propeller 14 are two-blade paddles, three-blade paddles, four-blade paddles, five-blade paddles or six-blade paddles.
Claims (9)
1. A short-distance take-off vertical landing aircraft comprises a main body (1), a main engine, a vertical tail (10), main wings (3), upper wings (4), end wings (6) and duck wings (2) which are respectively arranged at two sides of the main body; the upper parts of the two end wings (6) are respectively connected with the vertical fin (10) through an upper wing (4) arranged above the machine body; extension wings (5) connected with the upper wings (4) are arranged on the outer sides of the two end wings (6); elevator (7) are arranged on the two upper wings (4), and the elevator is characterized in that: the lower parts of the two end wings are provided with forward extending supporting structures (17), each forward extending supporting structure is provided with a main engine, a main engine propeller (12) and a propeller inclination angle driving device (11), and the lower part of each end wing is provided with a retractable main landing gear (15); a backward extending supporting structure (13) is arranged at the rear part of the vertical fin (10), and a posture adjusting engine propeller (14) is arranged on the backward extending supporting structure.
2. A short take-off vertical landing aircraft as defined in claim 1, wherein: ailerons (8) are arranged on the two extension wings; the tail parts of the two end wings are provided with rudders (9).
3. A short take-off vertical landing aircraft as defined in claim 1, wherein: the main wing, the duck wing, the upper wing and the extension wing adopt forward swept wings, backward swept wings or straight wings.
4. A short take-off vertical landing aircraft as claimed in claim 3, wherein: the main wing adopts a sweepback wing, and the upper wing adopts a sweepforward wing.
5. A short take off vertical landing aircraft as defined in claim 1, wherein: the propeller inclination angle driving device (11) adopts a ball screw driving mechanism.
6. A short take-off vertical landing aircraft as defined in claim 1, wherein: the end wing (6) and the extension wing (5) are conventional wing profiles, laminar flow wing profiles, high lift wing profiles or supercritical wing profiles.
7. A short take off vertical landing aircraft as defined in claim 6, wherein: the front edge of the end wing is provided with a sweepback angle, and the rear edge of the end wing is provided with a sweepforward angle.
8. A short take-off vertical landing aircraft as claimed in any one of claims 1 to 7, wherein: the main wing (3) is slightly provided with a dihedral angle; the upper wing (4) is slightly provided with a dihedral angle.
9. A short take off vertical landing aircraft as defined in claim 8, wherein: the blades of the main engine propeller (12) and the attitude-adjusting engine propeller (14) are two-blade paddles, three-blade paddles, four-blade paddles, five-blade paddles or six-blade paddles.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711364349.3A CN108045575B (en) | 2017-12-18 | 2017-12-18 | Short-distance take-off vertical landing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711364349.3A CN108045575B (en) | 2017-12-18 | 2017-12-18 | Short-distance take-off vertical landing aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108045575A CN108045575A (en) | 2018-05-18 |
| CN108045575B true CN108045575B (en) | 2024-03-19 |
Family
ID=62133549
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711364349.3A Active CN108045575B (en) | 2017-12-18 | 2017-12-18 | Short-distance take-off vertical landing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108045575B (en) |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108725775A (en) * | 2018-07-20 | 2018-11-02 | 平湖市职业中学 | A kind of VTOL fixed-wing unmanned plane |
| US10322814B1 (en) * | 2018-09-01 | 2019-06-18 | Autoflightx International Limited | Aircraft vertical stabilizer having a lift propeller and the method of using the same |
| CN109774916B (en) * | 2019-01-14 | 2021-10-15 | 北京航空航天大学 | A solar-powered aircraft with a three-dimensional layout design |
| CN109987223B (en) * | 2019-04-02 | 2023-03-10 | 夏季风 | A new type of vertical take-off and landing UAV with joint wing configuration |
| JP7586838B2 (en) * | 2019-05-07 | 2024-11-19 | エヌエフティー インコーポレイテッド | Electric or hybrid VTOL vehicles capable of running and flying |
| CN110775263B (en) * | 2019-10-22 | 2023-01-31 | 上海交通大学 | Tailseat sea-air cross-domain unmanned aerial vehicle |
| CN112027078B (en) * | 2020-09-16 | 2022-06-07 | 郑州航空工业管理学院 | An amphibious composite wing unmanned aerial vehicle and its control method |
| CN114104280A (en) * | 2021-04-09 | 2022-03-01 | 常州市锦织机械有限公司 | Safe and efficient electric vertical take-off and landing aircraft |
| CN113911318A (en) * | 2021-09-22 | 2022-01-11 | 重庆理工大学 | Posture self-adaptive adjustment annular lift wing device for pneumatic suspension train |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203283375U (en) * | 2013-04-16 | 2013-11-13 | 赵嘉珩 | Aircraft wing layout structure |
| CN204507270U (en) * | 2015-03-25 | 2015-07-29 | 刘行伟 | Novel high lift joined wing configuration aircraft |
| CN105818980A (en) * | 2016-05-06 | 2016-08-03 | 刘行伟 | Novel large-lift-force vertical take-off and landing aircraft |
| CN105882961A (en) * | 2016-04-13 | 2016-08-24 | 邓阳平 | High-speed aircraft capable of taking off and landing vertically as well as control method of high-speed aircraft |
| CN106586001A (en) * | 2016-11-30 | 2017-04-26 | 中国电子科技集团公司第三十八研究所 | Multimode and multi-based unmanned aerial vehicle with tailed flying wing configuration |
| CN106697257A (en) * | 2015-11-17 | 2017-05-24 | 北京航空航天大学 | Overall design of tilt-rotor aircraft |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6655631B2 (en) * | 2000-07-28 | 2003-12-02 | John Frederick Austen-Brown | Personal hoverplane with four tiltmotors |
| US7121503B2 (en) * | 2002-09-30 | 2006-10-17 | Cordy Jr Clifford B | Better balanced canard airplane with forward engine |
-
2017
- 2017-12-18 CN CN201711364349.3A patent/CN108045575B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203283375U (en) * | 2013-04-16 | 2013-11-13 | 赵嘉珩 | Aircraft wing layout structure |
| CN204507270U (en) * | 2015-03-25 | 2015-07-29 | 刘行伟 | Novel high lift joined wing configuration aircraft |
| CN106697257A (en) * | 2015-11-17 | 2017-05-24 | 北京航空航天大学 | Overall design of tilt-rotor aircraft |
| CN105882961A (en) * | 2016-04-13 | 2016-08-24 | 邓阳平 | High-speed aircraft capable of taking off and landing vertically as well as control method of high-speed aircraft |
| CN105818980A (en) * | 2016-05-06 | 2016-08-03 | 刘行伟 | Novel large-lift-force vertical take-off and landing aircraft |
| CN106586001A (en) * | 2016-11-30 | 2017-04-26 | 中国电子科技集团公司第三十八研究所 | Multimode and multi-based unmanned aerial vehicle with tailed flying wing configuration |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108045575A (en) | 2018-05-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108045575B (en) | Short-distance take-off vertical landing aircraft | |
| CN107176286B (en) | Foldable fixed-wing vertical take-off and landing unmanned aerial vehicle based on dual-ducted fan power system | |
| US8657226B1 (en) | Efficient control and stall prevention in advanced configuration aircraft | |
| US9545993B2 (en) | Aircraft stability and efficient control through induced drag reduction | |
| CN102826215B (en) | Light and small flying-wing manned aircraft with short takeoff and landing capacity | |
| CN104290906B (en) | A kind of vertically taking off and landing flyer | |
| EP3705401A1 (en) | Assembly of three composite wings for aerial, water, land or space vehicles | |
| CN202481309U (en) | Vector power vertical take-off and landing aircraft and vector power system thereof | |
| US20120074264A1 (en) | Airplane wing | |
| CN110901906B (en) | Ground effect rotor craft and flight mode switching method | |
| CN103241376A (en) | Vector power vertical takeoff and landing aircraft and vector power system thereof | |
| CN103158856B (en) | Light airscrew flying wing aircraft capable of taking off and landing in short distance | |
| US11407507B2 (en) | Lift rotor system | |
| US8262017B2 (en) | Aircraft with forward lifting elevator and rudder, with the main lifting surface aft, containing ailerons and flaps, and airbrake | |
| CN114212252B (en) | Tandem type tilting wing aircraft and control method | |
| CN106043687A (en) | Double-engine rear-propelling type duck type rotor/fixed wing combined type vertical take-off and landing aircraft | |
| WO2006022813A2 (en) | High-lift, low-drag dual fuselage aircraft | |
| CN113086184B (en) | Tandem distributed electric propulsion coaxial duct vertical take-off and landing aircraft | |
| CN218463872U (en) | Vertical take-off and landing aircraft with combined layout of tilting type propeller and fixed propeller | |
| CN114148516A (en) | Distributed tilting duct vertical take-off and landing aircraft and control method thereof | |
| US20240174353A1 (en) | Vertical take-off and landing aircraft based on variable rotor-wing technology and dual rotor-wing layout | |
| CN1974323A (en) | Ground effect flyer | |
| CN207725616U (en) | Double coaxial tilting rotor wing unmanned aerial vehicles of shoe formula | |
| US20220388648A1 (en) | Vtol box-wing multirotor aerial vehicle | |
| CN109941430B (en) | Four-blade rotary wing, rotary wing airplane and control method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB02 | Change of applicant information | ||
| CB02 | Change of applicant information |
Address after: 100076 District seven, 6 East guard Road, Fengtai District, Beijing. Applicant after: Liu Xingwei Address before: 100083 Haidian District, Beijing, learning Qingyuan Road, Qingyuan District 3 Building 3 unit 1201 Applicant before: Liu Xingwei |
|
| GR01 | Patent grant | ||
| GR01 | Patent grant |