CN204264454U - Novel high lift canard configuration connects rotor aircraft - Google Patents

Abstract

The utility model discloses a kind of novel high lift canard configuration and connect rotor aircraft, comprise: fuselage, the main wing being arranged on fuselage both sides, upper limb, the end wing, vertical fin, the described end being arranged on the main wing of fuselage both sides all arranges the end wing, and the top of described two end wings is connected with the vertical fin being arranged on afterbody respectively by the upper limb being arranged on body upper; The head both sides of described fuselage are provided with canard.The utility model can give full play to the lift-rising effect of two groups of aerofoils, and simultaneously under At High Angle of Attack condition, full facility have good stalling characteristics; Fuselage, as the vitals of aircraft, is unified into an entirety wing, vertical fin, canard and driving engine, and the design of its fleetline decreases aerodynamic drag, provides lift simultaneously.

Description

A new type of high-lift canard-type joint-wing aircraft

technical field

The utility model belongs to the field of aircraft design, and in particular relates to a novel high-lift canard-type layout joint-wing aircraft.

Background technique

With the rapid development of aeronautical technology and composite materials, the aircraft research using the joint wing structure has been developed faster. The joint wing structure has the following advantages: light weight, good rigidity, small induced drag, and large trim lift; Potential of direct lift and direct side force, good stability and maneuverability; good anti-drop characteristics, very conducive to improving the payload of the aircraft, with high application value and economic benefits.

Since the center of lift formed by the connecting wings is relatively rearward, it is easy to generate a large nose-down moment, which is not conducive to the longitudinal moment balance control of the whole machine, which will lead to the problem of insufficient longitudinal static stability of the whole machine.

Utility model content

In order to solve the existing technical problems, the embodiment of the utility model provides a novel high-lift canard-type layout joint-wing aircraft.

In order to achieve the above object, the technical solution of the utility model embodiment is achieved in this way:

The embodiment of the utility model provides a novel high-lift canard-type layout connecting wing aircraft, which includes: fuselage, main wings, upper wings, end wings and vertical tails arranged on both sides of the fuselage. The ends of the main wings on the side are all provided with end wings, and the upper parts of the two end wings are respectively connected with the vertical tail arranged at the tail of the fuselage through the upper wing arranged above the fuselage; the two sides of the nose of the fuselage are arranged There are canards.

In the above solution, the tails of the two end wings are provided with rudders, the two upper wings are provided with elevators, and the two main wings are provided with ailerons.

In the above solution, the nose is a flat duckbill nose.

In the above solution, flaps are provided on the two main wings.

In the above solution, the end wing is vertically arranged on the end wing stabilizer at the tip of the main wing.

In the above solution, the upper wing is arranged above the main wing, and there is a gap between them.

In the above scheme, the canard, main wing, upper wing and end wing adopt early airfoil, laminar flow airfoil, high lift airfoil or supercritical airfoil.

In the above solution, a power plant is provided at the tail of the fuselage.

In the above scheme, the power unit adopts a propeller engine or a jet engine.

In the above solution, a retractable rotor shaft is arranged inside the fuselage, a two-leaf foldable rotor is arranged on the top of the rotor shaft, and a rotor hatch is also arranged on the fuselage.

Compared with the prior art, the utility model has the beneficial effects:

The embodiment of the utility model provides a novel high-lift canard-type layout connecting wing aircraft, which includes: fuselage, main wings, upper wings, end wings and vertical tails arranged on both sides of the fuselage. The ends of the main wings on the side are all provided with end wings, and the upper parts of the two end wings are respectively connected with the vertical tail arranged at the tail of the fuselage through the upper wing arranged above the fuselage; the two sides of the nose of the fuselage are arranged There are canards; its streamlined design reduces aerodynamic resistance, through the main wing swept back, the upper wing adopts forward sweep, and the aircraft's upper reverse-swept wing and lower reverse-sweep upper wing are connected together to form a front and rear The wing layout makes the shape of the aircraft close to a rhombus in both the top view and the front view, and the aerodynamic efficiency is high. Within the range, the unfavorable interference ratio between each other is small, and the lift-increasing effect of the two sets of airfoils is fully utilized. At the same time, under the condition of high angle of attack, the whole aircraft has good stall characteristics; , vertical tail, canard and engine are integrated into a whole, and its streamlined design reduces aerodynamic drag while providing lift.

Description of drawings

Fig. 1 is a schematic structural view of a high-lift long-endurance connected-wing layout aircraft provided by Embodiment 1 of the utility model;

Fig. 2 is a top view of a high-lift long-endurance connected-wing layout aircraft provided by Embodiment 1 of the utility model;

Fig. 3 is a front view of a high-lift long-endurance connected-wing layout aircraft provided by Embodiment 1 of the utility model;

Fig. 4 is a side view of a high-lift long-endurance connected wing layout aircraft provided by Embodiment 1 of the utility model;

Fig. 5 is a schematic structural view of a high-lift long-endurance connected-wing layout aircraft provided by Embodiment 2 of the utility model;

Fig. 6 is a schematic structural view of a high-lift long-endurance connected-wing layout aircraft provided by Embodiment 3 of the present invention;

Fig. 7 is a schematic structural view of a high-lift long-endurance aircraft with connected wings provided by Embodiment 4 of the present invention;

Fig. 8 is a schematic structural view of a high-lift long-endurance aircraft with a joint-wing layout provided by Embodiment 5 of the utility model;

Fig. 9 is a schematic structural view of a high-lift long-endurance aircraft with a joint-wing layout provided by Embodiment 6 of the present invention;

Fig. 10 is a schematic structural diagram of a deployed state of a high-lift long-endurance aircraft with a joint-wing layout provided by Embodiment 6 of the utility model.

In the figure: 1-fuselage; 2-canard; 3-main wing; 4-upper wing; 5-end wing; 6-aileron; 7-elevator; 8-rudder; 9-vertical tail; 10-power plant; 11-head; 12-moving rotor shaft; 13-foldable rotor; 14-rotor hatch; 15-flaps.

Detailed ways

The utility model will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

Example 1:

The embodiment of the utility model provides a novel high-lift canard-type layout joint wing aircraft, as shown in Figures 1 to 4, the aircraft includes: a fuselage 1, a main wing 3 arranged on both sides of the fuselage 1, an upper wing 4, an end Wing 5, vertical tail 9, the ends of the main wing 3 arranged on both sides of the fuselage 1 are all provided with end wings 5, and the upper parts of the two end wings 5 pass through the upper wing 4 and the upper wing arranged on the fuselage 1 top respectively. The vertical tail 9 that is arranged on fuselage 1 afterbody is connected; The nose 11 both sides of described fuselage 1 is provided with canard 2; The lower and forward-swept upper wings are connected together to form a front-to-back wing layout. This layout makes the shape of the aircraft's top view and front view close to a rhombus, and the aerodynamic efficiency is high. The upper wing 4 and the main wing 3 are respectively It has the aerodynamic characteristics of the forward-swept wing and the swept-back wing, and the distance between the two wing surfaces is sufficient. In the range of large angle of attack, the adverse interference ratio between them is small, and the lift effect of the two sets of airfoils is fully exerted. Under these conditions, the whole machine has good stall characteristics.

The swept or straight design of the canard 2 depends on the specific design parameters of the wing.

The canard 2 is designed to be reversed up or down or straight depending on the specific design parameters of the wing. The canard 2 is used to increase the nose-up moment of the whole machine, and the active control technology is adopted to solve the problem of the whole machine in the prior art. The problem of insufficient longitudinal static stability.

The fuselage 1, the main wing 3 and the canard 2 have undergone wing-to-body fusion processing respectively, thereby increasing the structural strength of the fuselage-wing connection under the premise of improving its aerodynamic performance. The apex of the main wing 3 and the The lower surface of the end-wing 5 is fused to achieve the effect of combining the wing and the end-wing, and the vertical tail 9 and the fuselage 1 are fused to increase the strength.

Example 2:

The embodiment of the utility model provides a new type of high-lift canard-type layout connected wing aircraft, as shown in Figure 5, the aircraft includes: fuselage 1, main wings 3, upper wings 4, and end wings 5 arranged on both sides of the fuselage 1 , vertical tail 9, the ends of the main wings 3 that are arranged on both sides of the fuselage 1 are provided with end wings 5, and the upper parts of the two end wings 5 pass through the upper wing 4 arranged on the top of the fuselage 1 and are arranged on the The vertical tail 9 of fuselage 1 afterbody is connected; The nose 11 both sides of described fuselage 1 is provided with canard 2; The forward-swept upper wings are connected together to form a front-to-back wing layout. This layout makes the shape of the aircraft's top view and front view close to a rhombus, and the aerodynamic efficiency is high. The upper wing 4 and the main wing 3 respectively have front The aerodynamic characteristics of the swept wing and the swept wing, the distance between the two airfoils is sufficient, and the unfavorable interference ratio between them is small in the range of a large angle of attack. , the whole machine has good stall characteristics.

The swept or straight design of the canard 2 depends on the specific design parameters of the wing.

The canard 2 is designed to be reversed up or down or straight depending on the specific design parameters of the wing. The canard 2 is used to increase the nose-up moment of the whole machine, and the active control technology is adopted to solve the problem of the whole machine in the prior art. The problem of insufficient longitudinal static stability.

The fuselage 1, the main wing 3 and the canard 2 have undergone wing-to-body fusion processing respectively, thereby increasing the structural strength of the fuselage-wing connection under the premise of improving its aerodynamic performance. The apex of the main wing 3 and the The lower surface of the end-wing 5 is fused to achieve the effect of combining the wing and the end-wing, and the vertical tail 9 and the fuselage 1 are fused to increase the strength.

The tails of the two end wings 5 are provided with rudders 8 , the two upper wings 4 are provided with elevators 7 ; the two main wings 3 are provided with ailerons 6 .

At the same time, the rudder 8 is arranged on the end wing 5 to increase the directional stability of the aircraft and the control efficiency of the rudder surface, improve the crosswind resistance performance of the aircraft, and reduce the structural design complexity of the joint.

Example 3:

The embodiment of the utility model provides a novel high-lift canard-type layout joint wing aircraft, as shown in Figure 6, the aircraft includes: a fuselage 1, a main wing 3 arranged on both sides of the fuselage 1, an upper wing 4, and an end wing 5 , vertical tail 9, the ends of the main wings 3 that are arranged on both sides of the fuselage 1 are provided with end wings 5, and the upper parts of the two end wings 5 pass through the upper wing 4 arranged on the top of the fuselage 1 and are arranged on the The vertical tail 9 of fuselage 1 afterbody is connected; The nose 11 both sides of described fuselage 1 is provided with canard 2; The forward-swept upper wings are connected together to form a front-to-back wing layout. This layout makes the shape of the aircraft's top view and front view close to a rhombus, and the aerodynamic efficiency is high. The upper wing 4 and the main wing 3 respectively have front The aerodynamic characteristics of the swept wing and the swept wing, the distance between the two airfoils is sufficient, and the unfavorable interference ratio between them is small in the range of a large angle of attack. , the whole machine has good stall characteristics.

The swept or straight design of the canard 2 depends on the specific design parameters of the wing.

Described canard 2 is determined for up-reversing or down-reversing or flat design depending on the specific design parameters of the wing.

The fuselage 1, the main wing 3 and the canard 2 have undergone wing-to-body fusion processing respectively, thereby increasing the structural strength of the fuselage-wing connection under the premise of improving its aerodynamic performance. The apex of the main wing 3 and the The lower surface of the end-wing 5 is fused to achieve the effect of combining the wing and the end-wing, and the vertical tail 9 and the fuselage 1 are fused to increase the strength.

The tails of the two end wings 5 are provided with rudders 8 , the two upper wings 4 are provided with elevators 7 ; the two main wings 3 are provided with ailerons 6 .

At the same time, the rudder 8 is arranged on the end wing 5 to increase the directional stability of the aircraft and the control efficiency of the rudder surface, improve the crosswind resistance performance of the aircraft, and reduce the structural design complexity of the joint.

Through the combined control of the elevator 7 and the canard 2, it is beneficial to obtain the direct lift control of the whole aircraft; through the combined control of the two rudders and the aileron 6, it is beneficial to generate the direct lateral force control of the whole aircraft, so that the aircraft can move unconventional Modal control becomes possible and improves the control response quality of the aircraft.

The nose 11 is a flat duckbill nose, and the design of the duckbill flat nose has fully utilized the biosimulation. The flat lips are the common feature of wild geese and other creatures, which reduces air resistance and is beneficial to the flight of creatures.

The utility model adopts the canard 2 and the flat duckbill nose, which can make the aircraft basically be in the positive trim state during the flight, that is: in the trim flight, the canard 2 and the elevator 7 can be controlled to generate positive lift at the same time, further increasing the overall The lift efficiency of the aircraft increases the payload of the aircraft.

Example 4:

The embodiment of the utility model provides a new type of high-lift canard-type layout connected wing aircraft, as shown in Figure 7, the aircraft includes: fuselage 1, main wings 3, upper wings 4, and end wings 5 arranged on both sides of the fuselage 1 , vertical tail 9, the ends of the main wings 3 that are arranged on both sides of the fuselage 1 are provided with end wings 5, and the upper parts of the two end wings 5 pass through the upper wing 4 arranged on the top of the fuselage 1 and are arranged on the The vertical tail 9 of fuselage 1 afterbody is connected; The nose 11 both sides of described fuselage 1 is provided with canard 2; The forward-swept upper wings are connected together to form a front-to-back wing layout. This layout makes the shape of the aircraft's top view and front view close to a rhombus, and the aerodynamic efficiency is high. The upper wing 4 and the main wing 3 respectively have front The aerodynamic characteristics of the swept wing and the swept wing, the distance between the two airfoils is sufficient, and the unfavorable interference ratio between them is small in the range of a large angle of attack. , the whole machine has good stall characteristics.

The swept or straight design of the canard 2 depends on the specific design parameters of the wing.

Described canard 2 is determined for up-reversing or down-reversing or flat design depending on the specific design parameters of the wing.

The fuselage 1, the main wing 3 and the canard 2 have undergone wing-to-body fusion processing respectively, thereby increasing the structural strength of the fuselage-wing connection under the premise of improving its aerodynamic performance. The apex of the main wing 3 and the The lower surface of the end-wing 5 is fused to achieve the effect of combining the wing and the end-wing, and the vertical tail 9 and the fuselage 1 are fused to increase the strength.

The tails of the two end wings 5 are provided with rudders 8 , and the two upper wings 4 are provided with elevators 7 .

At the same time, the rudder 8 is arranged on the end wing 5 to increase the directional stability of the aircraft and the control efficiency of the rudder surface, improve the crosswind resistance performance of the aircraft, and reduce the structural design complexity of the joint.

The nose 11 is a flat duckbill nose, and the design of the duckbill flat nose has fully utilized the biosimulation. The flat lips are the common feature of wild geese and other creatures, which reduces air resistance and is beneficial to the flight of creatures.

Both main wings 3 are provided with flaps 15 and ailerons 6 . The length of the flap 15 on the main wing 3 and the length of the aileron 6 can be the same or different, depending on the design needs of the aircraft.

Further, on the basis of any one of embodiments 1 to 4, the end wing 5 is vertically arranged on the end wing stabilizer at the wing tip of the main wing 3, and the end wing stabilizer at the wing tip is used to make the upper and lower The lower wing surface is integral.

Further, on the basis of any one of Embodiments 1 to 4, the upper wing 4 is arranged above the main wing 3, and there is a distance between the two. , the unfavorable interference ratio between each other is small, and the lift-increasing effect of the two sets of airfoils is fully utilized. At the same time, the whole aircraft has good stall characteristics under the condition of high angle of attack.

Further, on the basis of any one of embodiments 1 to 4, the canard 2, main wing 3, upper wing 4 and end wing 5 adopt early airfoil, laminar flow airfoil, high-lift airfoil or supercritical airfoil.

Example 5:

On the basis of Embodiment 1, as shown in FIG. 8 , a power plant 10 is provided at the tail of the fuselage 1 , and the power plant 10 adopts a propeller engine or a jet engine.

Further, on the basis of Embodiment 5, the tails of the two end wings 5 are provided with rudders 8, the two upper wings 4 are provided with elevators 7, and the main wings 3 are provided with ailerons 6 .

Further, on the basis of Embodiment 5, rudders 8 are provided at the tails of the two end wings 5 , and elevators 7 are provided on the two upper wings 4 . Flaps 15 and ailerons 6 are all arranged on the two main wings 3, and the length of the flaps 15 on the main wings 3 and the length of the ailerons 6 can be the same or different, depending on the design needs of the aircraft.

Embodiment 6:

The embodiment of the utility model provides a new type of high-lift canard-type layout joint-wing aircraft, as shown in Figures 9 and 10, the aircraft includes: a fuselage 1, a main wing 3 arranged on both sides of the fuselage 1, an upper wing 4, an end Wing 5, vertical tail 9, the ends of the main wing 3 arranged on both sides of the fuselage 1 are all provided with end wings 5, and the upper parts of the two end wings 5 pass through the upper wing 4 and the upper wing arranged on the fuselage 1 top respectively. The vertical tail 9 that is arranged on fuselage 1 afterbody is connected; The nose 11 both sides of described fuselage 1 is provided with canard 2; The lower and forward-swept upper wings are connected together to form a front-to-back wing layout. This layout makes the shape of the aircraft's top view and front view close to a rhombus, and the aerodynamic efficiency is high. The upper wing 4 and the main wing 3 are respectively It has the aerodynamic characteristics of the forward-swept wing and the swept-back wing, and the distance between the two wing surfaces is sufficient. In the range of large angle of attack, the adverse interference ratio between them is small, and the lift effect of the two sets of airfoils is fully exerted. Under these conditions, the whole machine has good stall characteristics.

The swept or straight design of the canard 2 depends on the specific design parameters of the wing.

Described canard 2 is determined for up-reversing or down-reversing or flat design depending on the specific design parameters of the wing.

The fuselage 1, the main wing 3 and the canard 2 have undergone wing-to-body fusion processing respectively, thereby increasing the structural strength of the fuselage-wing connection under the premise of improving its aerodynamic performance. The apex of the main wing 3 and the The lower surface of the end-wing 5 is fused to achieve the effect of combining the wing and the end-wing, and the vertical tail 9 and the fuselage 1 are fused to increase the strength.

The interior of the fuselage 1 is provided with a retractable rotor shaft 12, and the top of the rotor shaft 12 is provided with a two-leaf foldable rotor 13, and the fuselage 1 is also provided with a rotor hatch 14, so that the aircraft has a short Vertical landing function from takeoff.

When preparing to land, the working state of the propulsion engine is gradually reduced, and the aircraft starts to decelerate. When the flight speed reaches a certain threshold, the flight control system controls to open the rotor canopy 14 to drive the rotor shaft 12 to rise. When the rotor shaft 12 is fully Stretch out and lock, and open the locking device of the foldable rotor 13, so that the foldable rotor 13 is unfolded under the effect of the pre-tightening force; at the same time, the connection between the propulsion power unit 10 and the drive shaft of the engine is disconnected, and the power conversion is adopted. The device connects the engine drive shaft with the rotor shaft 12 for vertical landing, drives the rotor shaft 12 to work, generates the landing lift required by the whole aircraft, makes the aircraft land vertically at the predetermined place, and the rotor decelerates until it stops working. The foldable rotor 13 is folded, the rotor shaft 12 is received in the fuselage, the rotor hatch 14 is closed, and the aircraft completes the vertical landing.

Further, on the basis of Embodiment 6, a power plant 10 is provided at the tail of the fuselage 1, and the power plant 10 adopts a propeller engine or a jet engine.

The above is only a preferred embodiment of the utility model, and is not used to limit the protection scope of the utility model. Any modification, equivalent replacement and improvement made within the spirit and principles of the utility model shall be Included within the protection scope of the present utility model.

Claims (10)

1. a novel high lift canard configuration connects rotor aircraft, it is characterized in that, this aircraft comprises: fuselage (1), the main wing (3) being arranged on fuselage (1) both sides, upper limb (4), the end wing (5), vertical fin (9), the described end being arranged on the main wing (3) of fuselage (1) both sides all arranges the end wing (5), and the top of described two ends wing (5) is connected with the vertical fin (9) being arranged on fuselage (1) afterbody respectively by the upper limb (4) being arranged on fuselage (1) top; Head (11) both sides of described fuselage (1) are provided with canard (2).

2. novel high lift canard configuration according to claim 1 connects rotor aircraft, it is characterized in that: the afterbody of described two ends wing (5) is provided with yaw rudder (8), and described two upper limbs (4) are provided with elevating rudder (7); Described two main wings (3) are provided with aileron (6).

3. novel high lift canard configuration according to claim 2 connects rotor aircraft, it is characterized in that: described head (11) is flat duckbilled head.

4. novel high lift canard configuration according to claim 3 connects rotor aircraft, it is characterized in that: described two main wings (2) are provided with wing flap (15).

5. the novel high lift canard configuration according to claim 1 or 2 or 3 or 4 connects rotor aircraft, it is characterized in that: the described end wing (5) is vertically set on the end wing stabilator at main wing (3) wingtip place.

6. the novel high lift canard configuration according to claim 1 or 2 or 3 or 4 connects rotor aircraft, it is characterized in that: described upper limb (4) is arranged on the top of main wing (3), and is provided with spacing between the two.

7. the novel high lift canard configuration according to claim 1 or 2 or 3 or 4 connects rotor aircraft, it is characterized in that: described canard (2), main wing (3), upper limb (4) and the end wing (5) adopt early stage aerofoil profile, laminar f1ow airfoil profile, high lift aerofoil profile or supercritical airfoil.

8. the novel high lift canard configuration according to claim 1 or 2 or 3 or 4 connects rotor aircraft, it is characterized in that: the afterbody of described fuselage (1) is provided with engine installation (10).

9. novel high lift canard configuration according to claim 8 connects rotor aircraft, it is characterized in that: described engine installation (10) adopts airscrew engine or jet engine.

10. the novel high lift canard configuration according to claim 1 or 2 or 3 or 4 connects rotor aircraft, it is characterized in that: described fuselage (1) inside is provided with telescopic rotor shaft (12), the top of described rotor shaft (12) is provided with two leaf folding rotors (13), described fuselage (1) is also provided with rotor hatchcover (14).