CN102267557A - Canard forward-sweep telescoping wing aerodynamic configuration with variable span wing area - Google Patents

Abstract

A canard-type forward-swept telescopic wing aerodynamic layout with variable length wing area, including a fuselage, a canard, a wing and a vertical tail, the wing includes a forward-swept inner wing and a forward-swept retractable outer wing, and the forward-swept The telescopic outer wing is internally connected with the forward-swept inner wing through the telescopic mechanism. When the Mach number of the UAV is 0.2, the telescopic mechanism stretches out the forward-swept retractable outer wing to the outside of the forward-swept inner wing. When the Mach number of the aircraft is 0.4, the retractable mechanism contracts to shrink the forward-swept retractable outer wing inside the forward-swept inner wing, wherein the area ratio of the forward-swept retractable outer wing to the forward-swept inner wing is 0.25-0.45. The present invention adopts the telescopic wing layout of the variable length wing area, so that the unmanned aerial vehicle has good aerodynamic performance in different airspaces and different speed state ranges, and improves the maneuverability and flexibility of the unmanned aerial vehicle; = 0.2 and 0.4 range, when flying at low speed, the lift-to-drag ratio of aerodynamic layout with large aspect ratio is more than 20% higher than that with small aspect ratio; when flying at high speed, the lift-to-drag ratio of aerodynamic layout with small aspect ratio is 15% higher than that with large aspect ratio Left and right, with the capability of Ma0.2 and Ma0.4 cruise flight.

Description

Aerodynamic layout of a canard-swept forward-swept telescoping wing with variable wing area

technical field

The invention relates to an aerodynamic layout of an unmanned aerial vehicle, in particular to an aerodynamic layout of a canard-type forward-sweep variable wing area and a telescopic wing, which belongs to the technical field of aerodynamic layout of an unmanned aerial vehicle.

Background technique

In recent years, with the rapid development of aviation technology, the design of aircraft is gradually developing in the direction of multi-task and multi-function. The traditional design of fixed-wing aircraft, limited by technology, can only make compromises between different flight mission states. The aircraft can only have good aerodynamic performance in a certain airspace range and a certain speed state range. The aerodynamic performance of the aircraft decreases when flying at the design point. Therefore, the function of a kind of fixed-wing aircraft type is highlighted single, and its maneuverability and flexibility all are greatly restricted. The morphing aircraft can make the aircraft have the most optimized aerodynamic performance in each mission stage, thereby enhancing the endurance of the aircraft or saving fuel, improving the take-off and landing performance and stability characteristics of the aircraft, and improving the adaptability of the aircraft to combat tasks.

At present, UAVs mainly adopt fixed-wing aerodynamic layout, which has problems such as inability to balance high and low speed performance, few combat functions, and poor survivability.

Contents of the invention

The problem solved by the technology of the present invention is to overcome the deficiencies of the prior art and provide a canard forward-sweep variable-length wing area that takes into account the performance requirements of various combat tasks such as aircraft high-speed cruise, low-speed hovering reconnaissance, and high-speed dive attack on the ground. The aerodynamic layout of the retractable wing.

The technical solution of the present invention is: a canard-type forward-swept telescopic wing aerodynamic layout with variable length wing area, including fuselage, canard, wing and vertical tail, and the wing includes a forward-swept inner wing and a forward-sweepable The retractable outer wing, the forward-swept retractable outer wing is internally connected with the forward-swept inner wing through the telescopic mechanism. When the Mach number of the UAV is 0.2, the telescopic mechanism stretches out the forward-swept retractable outer wing to the forward-swept Outside the inner wing, when the Mach number of the UAV is 0.4, the retractable mechanism shrinks the forward-swept retractable outer wing to the inside of the forward-swept inner wing, wherein the forward-swept retractable outer wing and the forward-swept inner wing The area ratio is 0.25 to 0.45.

The telescopic mechanism includes a drive mechanism, a hinge link mechanism, a telescopic guide rail and an outer wing connecting frame, and the telescopic guide rail, the hinge link mechanism and the outer wing connecting frame are symmetrically distributed on both sides of the driving mechanism, and the driving mechanism includes a motor, two synchronous Gears and supports, telescopic guide rails are guide rail grooves processed directly on the double beams of the forward-swept inner wing, the hinge linkage mechanism is a diamond-shaped mechanism composed of several hinges and struts, and a convex rod is installed on the struts at the end of the prismatic mechanism , the protruding rod is stuck in the telescopic guide rail, the outer wing connecting frame is fixedly installed at the end of the prismatic mechanism, and the forward-swept retractable outer wing is installed on the outer wing connecting frame, and the pole at the front end of the prismatic mechanism is connected with the synchronous gear. The synchronous gears are kneaded with each other, and one of the synchronous gears is connected with the transmission shaft of the motor. The motor and the two synchronous gears are fixedly mounted on a support, and the support is fixedly installed on the symmetry axis of the fuselage.

Compared with the prior art, the present invention has beneficial effects as follows:

(1) The present invention adopts the telescopic wing layout of the variable length wing area, so that the unmanned aerial vehicle has good aerodynamic performance in different airspaces and different speed state ranges, and improves the maneuverability and flexibility of the unmanned aerial vehicle;

(2) The present invention is in the range of Ma=0.2 and 0.4. When flying at low speed, the lift-to-drag ratio of aerodynamic layout with large aspect ratio is more than 20% higher than that with small aspect ratio. When flying at high speed, the lift-to-drag ratio of aerodynamic layout with small aspect ratio The large aspect ratio is about 15% higher. Compared with the fixed-wing aircraft of the same magnitude, the telescopic and deformable aircraft of the present invention can increase the flight range by 10%, and has the capability of Ma0.2 and Ma0.4 cruising flight at the same time;

(3) The present invention adopts telescopic wing aerodynamic layout, on the basis of not increasing the structural complexity of the aircraft, taking into account the high and low speed performance of the aircraft, and improving the combat capability of the aircraft;

(4) The present invention adopts telescoping mechanism, which is not easy to lock, has stronger robustness, is easy to realize the integrated design of forward-swept inner wing and forward-swept retractable outer wing, and is lighter in weight. Fast shrinkage and deformation.

Description of drawings

Fig. 1 is the structural representation under the low-speed state of the present invention;

Fig. 2 is the structural representation under the high-speed state of the present invention;

Fig. 3 is a structural schematic diagram of the telescoping mechanism of the present invention;

Fig. 4 is a schematic diagram of the hinge linkage mechanism of the present invention;

Fig. 5 is the lift-drag pole curve of the aerodynamic layout with large aspect ratio and small aspect ratio (the abscissa D represents resistance, and the ordinate L represents lift);

Fig. 6 is the relationship curve between lift-drag ratio and lift force of aerodynamic layouts with large aspect ratio and small aspect ratio (the abscissa L represents the lift force, and the ordinate K represents the lift-drag ratio).

Detailed ways

The design principle of the present invention is: on the basis of not increasing the structural complexity of the aircraft, taking into account the high and low speed performance of the aircraft, and improving the combat capability of the aircraft.

In the range of Ma=0.2 and 0.4. The aerodynamic layout of the telescopic wing can bring benefits based on the following principles. The aerodynamic drag of a UAV is mainly composed of two parts, waste drag and induced drag.

${\mathrm{<span\; class="notranslate">\; C</span>}}_{\mathrm{<span\; class="notranslate">\; D.</span>}}<span\; class="notranslate">\; =</span>{\mathrm{<span\; class="notranslate">\; C</span>}}_{\mathrm{<span\; class="notranslate">\; D.</span>}\mathrm{<span\; class="notranslate">\; 0</span>}}<span\; class="notranslate">\; +</span>{\mathrm{<span\; class="notranslate">\; <figure-callout\; id="2"\; label="AC\; L"\; filenames="HSA00000482298400012.png,HSA00000482298400032.png"\; state="\{\{state\}\}">AC</figure-callout></span><figure-callout\; id="2"\; label="AC\; L"\; filenames="HSA00000482298400012.png,HSA00000482298400032.png"\; state="\{\{state\}\}">\; </figure-callout>}}_{\mathrm{<span\; class="notranslate">\; </span>}}^{\mathrm{<span\; class="notranslate">L</span>}}$

where C _D0 is the zero-lift drag, which is a function of the wing area, and A is the induced drag factor, which is a function of the aspect ratio.

The change rate of the wing area of the large aspect ratio and small aspect ratio layout reaches nearly 35%, and if the change rate of the exposed area is considered, the change rate of the exposed area reaches 45%. Therefore, the zero-lift drag of a small aspect ratio layout is smaller than that of a large aspect ratio. On the other hand, the induced drag factor of the aerodynamic layout with small aspect ratio is larger than that with large aspect ratio. As a result, when flying at high speed, the required lift coefficient is small, C _D0 dominates, and the lift-drag ratio of the small aspect ratio layout is relatively large. When flying at low speed, the required lift coefficient is large, the induced drag is dominant, and the lift-drag ratio of the layout with a large aspect ratio is relatively large. Analysis shows that one of the characteristics of small aspect ratio is that the position of maximum lift-to-drag ratio appears at a small angle of attack. The advantage of a large aspect ratio is that it can provide a larger lift coefficient while providing the largest lift-to-drag ratio.

On the premise of ensuring the superior lift-to-drag ratio, reasonable static stability margins are designed for high-speed and low-speed flight by adjusting and optimizing the plane shape of the wing. The high-speed configuration and small aspect ratio layout require fast arrival and ground attack missions, which requires strong maneuverability and a small static stability margin of about 5%. The low-speed configuration is used for hovering reconnaissance and suppression, so its static stability margin is set at a maximum of 10%. In order to meet this requirement, the UAV adopts a forward-swept telescopic wing layout, and the final layout form and parameters are determined through optimization. As shown in Figures 5 and 6, in the range of Ma=0.2 and 0.4, when the UAV is flying at low speed, the lift-to-drag ratio of the aerodynamic layout with a large aspect ratio is more than 20% higher than that with a small aspect ratio. The aspect ratio of the aerodynamic layout cruise lift-drag ratio is about 15% higher than that of the large aspect ratio. Compared with the fixed-wing aircraft of the same magnitude, the telescopic and deformable aircraft of the present invention can increase the flight range by 10%. It also has Ma0.2 and Ma0.4 cruise The ability to fly.

The present invention as shown in Figure 1, 2, is made up of five major parts such as fuselage 1, canard 2, forward-swept inner wing 3, forward-swept retractable outer wing 4 and vertical tail 5. A retractable mechanism is installed inside the forward-swept inner wing 3 to drive the forward-swept retractable outer wing 4 to expand and contract infinitely. Small aspect ratio, suitable for high-speed flight. When cruising at low speed, extend the forward-swept retractable outer wing 4 to maximize the aspect ratio of the wing and adapt to low-speed flight. Aerodynamic requirements for flight combat missions.

As shown in Figure 3, the telescopic mechanism includes a drive mechanism, a hinge link mechanism, a telescopic guide rail 67 and an outer wing connecting frame 64, and the telescopic guide rail 67, the hinge link mechanism and the outer wing connecting frame 64 are symmetrically distributed on both sides of the driving mechanism. , the driving mechanism includes a motor 61, two synchronous gears 62 and a support 63, the telescopic guide rail 67 is a guide rail groove directly processed on the double beam of the forward-swept inner wing 3, and the hinge linkage mechanism is composed of several hinges 65 and struts 66 The rhombus mechanism, the protruding rod 68 is installed on the pole 66 at the end of the prismatic mechanism, the protruding rod 68 is stuck in the telescopic guide rail 67, the outer wing connecting frame 64 is fixedly installed at the end of the prismatic mechanism, and the outer wing connecting frame 64 is installed before Sweep the retractable outer wing 4, the strut at the front end of the prismatic mechanism is connected with the synchronous gear 62 gears, and the two synchronous gears 62 are kneaded with each other, and one of the synchronous gears 62 is connected with the drive shaft of the motor 61, and the motor 61 and the two synchronous gears 62 is fixedly installed bearing 63, and bearing 63 is fixedly installed on the symmetry axis of fuselage 1, and telescopic guide rail 67 front end is installed stopper, limits the retractable outer wing 4 stretching positions of sweeping forward.

The telescopic movement mechanism of the telescopic mechanism:

The telescopic mechanism adopts the integrated design of the wing and fuselage. Three sets of diamond-shaped mechanisms are used to achieve the required telescopic movement of about 580mm stroke. The connecting rods at the two hinges at the root of the main wing realize synchronous movement through gear meshing, and the motor drives the connecting rod at one of the hinges to rotate to drive the entire mechanism. Perform telescopic deformation.

Mechanism principle: 1) telescopic guide rail. Directly open guide rail grooves on the main wing double girders, which can be realized without increasing the structural weight; 2) The hinge linkage mechanism is shown in Figure 4. Left and right symmetrical, the symmetrical plane is installed on the symmetrical plane of the fuselage, and the outer side is directly connected to the outer wing. The connection between the mechanism and the telescopic guide rail is realized by a small protruding rod installed on the front and rear edges of the outer wing root, and the protruding rod is stuck in the telescopic guide rail groove. Thus, the movement of the outer wing in the stretching direction is realized, and the degree of freedom of bending and torsion in several other directions is limited; 3) the driver. A stepping motor mounted on the body is adopted.

The retractable mechanism can be in other forms, not limited by the above-mentioned mechanism, as long as the forward-swept retractable outer wing 4 can be stretched and retracted in the forward-swept inner wing 3 .

Parts not described in detail in the present invention belong to the common knowledge of those skilled in the art.

Claims (2)

1. a canard-type forward-swept variable stretch wing aerodynamic layout of long wing area, comprising fuselage (1), canard (2), wing and vertical tail (5), is characterized in that: described wing It includes a forward-swept inner wing (3) and a forward-swept retractable outer wing (4). When the Mach number is 0.2, the telescopic mechanism stretches to extend the forward-swept retractable outer wing (4) to the outside of the forward-swept inner wing (3). The telescopic outer wing (4) shrinks inside the forward-swept inner wing (3), wherein the area ratio of the forward-swept retractable outer wing (4) to the forward-swept inner wing (3) is 0.25-0.45. 2. The telescoping wing aerodynamic layout of a kind of canard forward-swept variable-length wing area according to claim 1, characterized in that: the telescoping mechanism includes a drive mechanism, a hinge link mechanism, a telescopic guide rail (67) and The outer wing connecting frame (64), the telescopic guide rail (67), the hinge linkage mechanism and the outer wing connecting frame (64) are symmetrically distributed on both sides of the driving mechanism, and the driving mechanism includes a motor (61), two synchronous gears (62) and The support (63), the telescopic guide rail (67) are guide rail grooves processed directly on the double beams of the forward-swept inner wing (3), and the hinge linkage mechanism is a diamond-shaped mechanism composed of several hinges (65) and struts (66). , the protruding rod (68) is installed on the pole (66) at the end of the prismatic mechanism, the protruding rod (68) is stuck in the telescopic guide rail (67), the outer wing connecting frame (64) is fixedly installed at the end of the prismatic mechanism, and the outer wing The forward-swept retractable outer wing (4) is installed on the wing connecting frame (64), and the strut at the front end of the prismatic mechanism is connected with the synchronous gear (62) gear, and two synchronous gears (62) are kneaded mutually, and one of them synchronous gear ( 62) be connected with the power transmission shaft of motor (61), motor (61) and two synchronous gears (62) are fixedly installed bearing (63), and bearing (63) is fixedly installed on the symmetrical axis of fuselage (1).

Images