Double-slotted flap mechanism of light unmanned aerial vehicle

Abstract

The utility model discloses a double-slotted flap mechanism of a light unmanned aerial vehicle. The double-slotted flap mechanism comprises a main wing stabilizer, a steering engine, a connecting rod mechanism, a first-stage flap and a second-stage flap, the main wing stabilizer is fixedly connected with the steering engine in an embedded manner; the connecting rod mechanisms are distributed in a bilateral symmetry mode and are in transmission connection with the two ends of the main wing stabilizing plane, the steering engine, the first-stage flap and the second-stage flap in a hinged mode; the first-stage flap and the second-stage flap synchronously carry out retreating and downward-deviating composite motion along a preset track, a double-slotted pneumatic structure is formed, the boundary layer control capacity is effectively enhanced, airfoil airflow separation is delayed, the lift coefficient is increased, and especially under the low-speed short-distance take-off and landing working condition, the flow field regulation and control efficiency is remarkably superior to that of a traditional single-stage flap structure. By applying light materials and embedded installation design, the weight of the whole mechanism is much lighter than that of a traditional metal structure, meanwhile, the guide rails penetrating through the driving rods in the spanwise direction and the airfoil body are integrally arranged, the occupied space of the mechanism is greatly reduced, and the requirement for the compact aerodynamic shape of a light and small unmanned aerial vehicle is met.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane structure technical field, concretely relates to a double slit flap mechanism of light unmanned plane. BACKGROUND

[0002] As the core aerodynamic component of improving the lift and control performance of the unmanned plane, the flap is usually installed at the trailing edge of the wing of the fixed-wing unmanned plane, and when it is unfolded, the airflow separation of the wing surface can be delayed through airflow guiding, thereby significantly increasing the lift of the unmanned plane at the current airspeed. In recent years, with the rapid development of unmanned plane platforms towards miniaturization, lightweight and short take-off and landing, how to balance the fine flow field regulation and control and realize efficient driving of the flap mechanism in limited space has become the core to break through the design bottleneck of traditional flap structures.

[0003] Looking at the existing flap driving forms, they are mainly divided into flap mechanisms driven by joint motor sets-rack gears, slide rail roller driving mechanisms based on triangular hinged support rods, double slit flap mechanisms driven by driven screws, etc. The joint motor set-rack gear driving mechanism realizes flap movement control through built-in gear and rack cooperation with rail roller transmission, reduces aerodynamic resistance, and has simple structure and stable control. The slide rail roller mechanism based on the triangular hinged support rod enhances the unfolding stability through the triangular stable layout, and the bilateral symmetrical layout strengthens the anti-unbalance load capacity. The double slit flap mechanism driven by the driven screw realizes the failure redundancy mechanism through the design of the shear pin and the secondary connection, realizes the cooperative control of the double flap surfaces through the universal joint and the chain structure, and significantly improves the control accuracy and lift performance.

[0004] However, the joint motor set-rack driven flap mechanism has large volume and high weight of the motor set and multi-stage transmission structure, the gear and rack are prone to wear in frequent expansion and contraction, the maintenance cost is high, and it is difficult to adapt to the light and small unmanned plane with strict requirements on lightweight. The slide rail roller driving mechanism based on the triangular hinged support rod has high overall redundancy due to the layout of the support rod and multiple hinge points, which is not conducive to the integrated design in the limited space of the small unmanned plane, and the multiple openings on the wing and flap skin affect the aerodynamic integrity, the slit width is small, the movement lead is short, and the lift improvement effect is poor. The double slit flap mechanism driven by the driven screw has excessively high system complexity and cost for the pursuit of aerodynamic optimization. The screw transmission has very high processing precision requirement, which is difficult to meet the demand of low cost and easy maintenance; the structure relying on precision bearings and universal joints is prone to fatigue wear under high-speed and high-frequency operation, and has poor reliability. SUMMARY

[0005] In view of the problems existing in the above prior art solutions, the utility model aims to provide a double slit flap mechanism of light unmanned plane to solve the problems of high weight, complex structure, high processing difficulty and low aerodynamic efficiency of the slit flap.

[0006] To achieve the above object, the utility model adopts the technical scheme that is

[0007] A double-slotted flap mechanism of a light unmanned aerial vehicle, comprising a main wing stabilizer, a rudder, a connecting rod mechanism, a primary flap and a secondary flap;

[0008] The main wing stabilizer comprises a rudder mounting hole, and the main wing stabilizer is fixedly connected with the rudder through the rudder mounting hole in an embedded manner; the pair of connecting rod mechanisms are symmetrically distributed left and right and are respectively drivingly connected with the two ends of the main wing stabilizer, the rudder, the primary flap and the secondary flap in a hinged manner; the primary flap and the secondary flap perform synchronous backward and downward compound motion along a predetermined track, forming a double-slotted aerodynamic configuration.

[0009] Optionally, the main wing stabilizer further comprises a wing surface body, a pair of main wing ribs symmetrically distributed on the left and right sides of the wing surface body, and a main beam rigidly connected with the main wing ribs in a penetrating manner; wherein the main wing ribs have a motion guide rail integrated at the trailing edge to constrain the motion track of the primary flap; the wing surface body is manufactured by PMI hot cutting integral forming, giving consideration to aerodynamic shape and light weight; and the main beam penetrates the front part of the wing surface body and forms a core load-bearing frame.

[0010] Optionally, the rudder comprises a rudder box, a rudder arm, a power output rod, an edgewise penetrating drive rod and a rudder arm pin; wherein the rudder box is fixedly embedded at the rear part of the wing surface body of the main wing stabilizer; the rudder arm and the power output rod are rigidly connected with the edgewise penetrating drive rod through the rudder arm pin to form a transmission pair, and the edgewise penetrating drive rod performs directional linear displacement along the penetrating rod motion guide rails symmetrically arranged on the two sides of the wing surface body of the main wing stabilizer.

[0011] The edgewise length of the edgewise penetrating drive rod matches the wing surface body of the main wing stabilizer, and the left and right ends of the edgewise penetrating drive rod extend into the penetrating rod motion guide rails on the two sides of the wing surface body to form a transmission mechanism driven by the rudder.

[0012] Optionally, the connecting rod mechanism comprises a plurality of connecting rods and pins; wherein the power is transmitted in stages by the design of the plurality of connecting rods symmetrically connected to the main wing stabilizer; and the pins fix and transmit the connecting rods and components such as the main wing stabilizer, the rudder, the primary flap and the secondary flap.

[0013] The connecting rod mechanism comprises L-shaped connecting rods and multi-stage hinged pins, and the connecting rods are CNC engraved and punched by 3K specification carbon fiber plates, which has the advantages of low processing difficulty, high precision, high strength and light weight; and the connecting rod mechanism forms a compound motion pair by cooperating with a guide rail through a moving pair, thereby ensuring the accurate synchronization of the backward and downward actions of the primary flap.

[0014] Optionally, the primary flap and the secondary flap each comprise a flap surface and a flap main beam; the primary flap and the secondary flap each adopt an integrated load-bearing structure, and the surface and the main beam are fixedly connected through a through hole; wherein the primary flap surface and the secondary flap surface are each manufactured by PMI hot cutting integrated molding, are light in weight, easy to process, and meanwhile, the aerodynamic shape is maintained.

[0015] Optionally, the primary flap main beam of the primary flap forms a moving pair with the connecting rod mechanism through a pin shaft, and drives the primary flap to perform a rearward and downward combined motion along a primary flap motion guide rail; the secondary flap main beam of the secondary flap is expanded and contracted along a secondary flap rail through a single-degree-of-freedom slider linkage mechanism connected rigidly.

[0016] Wherein, the primary flap motion guide rail is integrated into a main wing rib tail edge of a main wing stabilizer surface, and the secondary flap rail is symmetrically arranged at the tail of the primary flap surface, and the trajectory constraint and synchronous control of the double-stage flap are realized through the cooperation of the guide rail and the rigid connecting rod.

[0017] Optionally, the double-slit aerodynamic configuration is formed through the coordinated expansion of the primary flap and the secondary flap, and the lift coefficient and the boundary layer control efficiency are significantly improved.

[0018] Compared with the prior art, the utility model realizes the following specific beneficial effects through the following technical means:

[0019] 1、The utility model discloses a double-stage flap coordinated expansion mechanism, the primary flap and the secondary flap are retreated and downward combined motion along the predetermined rail synchronously, form double-slit aerodynamic configuration, effectively enhance the boundary layer control ability, delay the wing surface airflow separation, make the lift coefficient improve about 30% -45%, especially in low speed short take -off and landing condition, the flow field regulation and control efficiency is significantly superior to traditional single -stage flap structure.

[0020] 2、The utility model discloses 3K specification carbon fiber plate CNC carving process is manufactured connecting rod mechanism and flap main beam, PMI ultra -light foam hot cutting is manufactured main wing stabilizer surface and primary, secondary flap, combines the embedded installation design of rudder, makes the overall mechanism weight far lighter than traditional metal structure, the rail integrated layout of driving rod and wing surface main body is greatly reduced the mechanism occupied space, adapts the compact aerodynamic shape demand of light small -size unmanned aerial vehicle.

[0021] 3、The utility model is based on the linkage design of symmetrical connecting rod transmission mechanism and guide rail, through the hinge constraint of pin and the linear guiding effect of primary flap motion guide rail, secondary flap rail, ensure that the motion trajectory of double-stage flap is strictly synchronous in the process of expansion and contraction, and the maximum angle deviation is not more than ± 1.5 °, which significantly improves the repeatability and reliability of the aerodynamic action.

[0022] 4. The utility model discloses a single degree of freedom slider linkage mechanism replaces traditional multistage transmission chain, reduces the quantity of redundant hinged point, all connecting rod assemblies adopt the numerical control processing of standardization carbon fiber plate, unify the aperture and the connecting pin specification, make the part processing error control within 0.1mm, compared with precision screw drive scheme greatly reduces the manufacturing cost, and need not complex assembly technology.

[0023] 5. The utility model discloses a connecting rod assembly adopts hinged and carbon fiber wear -resistant contact surface, abandon precision bearing and universal joint design, under the high -speed high -frequency action wear rate reduces greatly, simultaneously, modular connecting rod mechanism supports quick dismounting and maintenance, shortens the replacement time of single fault component, significantly improves the task continuity of unmanned plane under complex environment. ACCURACY

[0024] The accompanying drawings, which are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this specification, illustrate embodiments of the utility model and together with the description serve to explain the principles of the utility model.

[0025] Figure 1 It is the overall structure perspective drawing of the utility model;

[0026] Figure 2 It is the assembly relationship drawing of each part of the utility model;

[0027] Figure 3 It is the specific structure schematic diagram of main wing stabilizer in the utility model;

[0028] Figure 4 It is the specific structure schematic diagram of rudder in the utility model;

[0029] Figure 5 It is the specific structure schematic diagram of connecting rod mechanism in the utility model;

[0030] Figure 6 It is the specific structure schematic diagram of primary flap in the utility model;

[0031] Figure 7 It is the specific structure schematic diagram of secondary flap in the utility model.

[0032] Reference signs: main wing stabilizer 1, main wing rib 1-1, rib-main beam hole 1-1-1, primary flap movement guide rail 1-1-2, connecting rod pin joint hole 1-1-3, wing surface main body 1-2, wing surface-main beam hole 1-2-1, steering gear mounting hole 1-2-2, through rod movement guide rail 1-2-3, main beam 1-3, steering gear 2, steering gear box 2-1, steering arm 2-2, steering gear box-steering arm connecting hole 2-2-1, power output rod 2-3, steering arm-output rod connecting hole 2-3-1, output rod-through rod connecting hole 2-3-2, spanwise through driving rod 2-4, steering arm pin shaft 2-5, connecting rod mechanism 3, first connecting rod 3-1, second connecting rod 3-2, third connecting rod 3-3, fourth connecting rod 3-4, fifth connecting rod 3-5, sixth connecting rod 3-6, seventh connecting rod 3-7, first pin X1, second pin X2, …, to twelfth pin X12, primary flap 4, primary flap surface 4-1, primary flap surface main beam hole 4-1-1, flap connecting rod pin joint hole 4-1-2, secondary flap rail 4-1-3, primary flap main beam 4-2, secondary flap 5, secondary flap surface 5-1, secondary flap surface main beam hole 5-1-1, secondary flap main beam 5-2. DETAILED DESCRIPTION

[0033] The utility model will be described in further detail below in combination with the drawings and specific embodiments.

[0034] It can be understood that the specific embodiments described herein are only used to explain the related content, not to limit the utility model. In addition, it needs to be explained that only the parts related to the utility model are shown in the drawings for the convenience of description.

[0035] It needs to be explained that the embodiments in the utility model and the features in the embodiments can be combined with each other without conflict. The technical scheme of the utility model will be described in detail below in combination with the drawings and embodiments.

[0036] Unless otherwise specified, the exemplary embodiments / instances shown will be understood to provide exemplary features of various details that can implement the technical concept of the utility model in practice. Therefore, unless otherwise specified, the features of various embodiments / instances can be additionally combined, separated, interchanged and / or rearranged without departing from the technical concept of the utility model.

[0037] In the drawings, the size and relative size of the components can be exaggerated for the sake of clarity and / or descriptive purposes. When the exemplary embodiments can be implemented differently, the specific process sequence can be performed in an order different from that described. For example, two continuously described processes can be performed substantially simultaneously or in an order opposite to that described. In addition, the same reference signs represent the same components.

[0038] When a component is referred to as being "on" or "on top of", "connected to", or "coupled to" another component, it can be directly on, directly connected to, or directly coupled to the other component, or intervening components can be present. However, when a component is referred to as being "directly on", "directly connected to", or "directly coupled to" another component, there are no intervening components present. To this end, the term "connected" can refer to a physical connection, an electrical connection, etc., with or without intervening components.

[0039] When the terms "comprising" and / or "including" and variations thereof as used in the present specification are used, it is to be understood that such terms are used inclusively and not exclusively, that is, there being no exclusion of additional, unrecited members, ingredients, components, steps, operations, parts, assemblies, and / or groups thereof. It is also to be noted that, as used herein, the terms "substantially", "approximately", and other similar terms are used as terms of approximation and not as terms of degree, and as such, they are used to account for inherent deviations in measurements, calculations, and / or provided values that would be recognized by those of ordinary skill in the art.

[0040] In one embodiment, the utility model provides a double-slotted flap mechanism of light unmanned aerial vehicle, including main wing stabilizer, steering gear, connecting rod mechanism, primary flap and secondary flap,

[0041] The main wing stabilizer includes a steering gear mounting hole, and the main wing stabilizer is fixedly connected with the steering gear through the steering gear mounting hole; the pair of connecting rod mechanisms are symmetrically distributed left and right and are respectively in transmission connection with the two ends of the main wing stabilizer, the steering gear, the primary flap and the secondary flap through hinged connection; the primary flap and the secondary flap perform synchronous backward and downward compound motion along a predetermined track to form a double-slotted aerodynamic configuration.

[0042] Optionally, the main wing stabilizer further includes a wing surface body, a pair of main wing ribs symmetrically distributed on the left and right sides of the wing surface body, and a main beam rigidly connected with the main wing ribs in a penetrating manner; wherein, the main wing ribs are integrated with a motion guide rail at the tail edge to constrain the motion track of the primary flap; the wing surface body is manufactured by PMI hot cutting integral forming, and aerodynamic shape and light weight are considered; the main beam penetrates the front part of the wing surface body and forms a core load-bearing frame.

[0043] Optionally, the steering gear includes a steering gear box, a steering arm, a power output rod, an edgewise penetrating drive rod and a steering arm pin; wherein, the steering gear box is embeddedly fixed at the rear part of the wing surface body of the main wing stabilizer; the steering arm and the power output rod form a transmission pair with the edgewise penetrating drive rod through rigid hinged connection of the steering arm pin, to drive the edgewise penetrating drive rod to perform directional linear displacement along the motion guide rail of the penetrating rod symmetrically arranged on the two sides of the wing surface body of the main wing stabilizer.

[0044] The span length of the span-through driving rod matches the wing surface main body span length of the main wing stabilizer, and the left and right ends extend into the through-rod motion guide rails on both sides of the wing surface main body to form a rocking lever transmission mechanism driven by the rudder.

[0045] Optionally, the connecting rod mechanism comprises a plurality of connecting rods and pins, wherein the power is transmitted in stages by the multi-connecting rod transmission design symmetrically connected to the main wing stabilizer on both sides; and the pins are used to fix and transmissionally connect the connecting rods with the main wing stabilizer, the rudder, the primary flap, the secondary flap and other components.

[0046] The connecting rod mechanism comprises L-shaped connecting rods and multi-stage hinged pins, the connecting rods are CNC engraved and punched by 3K carbon fiber plates, which has low processing difficulty, high precision, high strength and light weight; and the connecting rod mechanism forms a composite kinematic pair by cooperating with the guide rail through a moving pair, thereby ensuring the accurate synchronization of the primary flap retraction and downward deflection.

[0047] Optionally, the primary flap and the secondary flap each comprise a flap surface and a flap main beam; the primary flap and the secondary flap each adopt an integrated load-bearing structure, and the surface and the main beam are fixedly connected through a through hole; wherein the primary and secondary flap surfaces are manufactured by PMI hot cutting and integrated molding, which is light in weight, easy to process and capable of maintaining the aerodynamic shape.

[0052] Optionally, the primary flap main beam of the primary flap forms a moving pair with the connecting rod mechanism through a pin shaft, thereby driving the primary flap to perform a retraction and downward deflection compound motion along the primary flap motion guide rail; and the secondary flap main beam of the secondary flap is synchronously unfolded / folded along the secondary flap track through a single-degree-of-freedom slider linkage mechanism connected rigidly.

[0049] The primary flap motion guide rail is integrated into the main wing rib tail edge of the main wing stabilizer, and the secondary flap track is symmetrically arranged at the tail of the primary flap surface, thereby realizing the trajectory constraint and synchronous control of the double-stage flaps through the cooperation of the guide rail and the rigid connecting rod.

[0050] Optionally, the double-opening slit aerodynamic configuration forms a multi-stage flow channel through the coordinated unfolding of the primary flap and the secondary flap, thereby significantly improving the lift coefficient and the boundary layer control efficiency.

[0051] In one embodiment, as shown in FIG. 1, the primary flap 1 is arranged on the main wing stabilizer 2, and the secondary flap 3 is arranged on the primary flap 1. Figure 1 and Figure 2The utility model provides a double slit flap of light unmanned plane, include: main wing stabilizer 1, rudder 2, connecting rod mechanism 3, primary flap 4, secondary flap 5. Main wing stabilizer 1, primary flap 4 and secondary flap 5 are sequentially connected through connecting rod mechanism 3, main wing stabilizer 1, rudder 2 are embeddedly fixed through rudder mounting hole 1-2-2, a pair of connecting rod mechanism 3 is left and right symmetrical distribution, is hinged with the leftmost, the rightmost end of main wing stabilizer 1 through second pin X2 respectively, connecting rod mechanism 3 is formed left and right symmetrical type transmission connection through the spread through drive rod 2-4 and first pin X1 with rudder 2, connecting rod mechanism 3 and primary flap 4 are hinged through sixth pin X6, further form leading edge transmission connection through primary flap main beam 4-2 and fifth pin X5, connecting rod mechanism 3 and secondary flap 5 form leading edge transmission connection through secondary flap main beam 5-2 and tenth pin X10, further through sixth connecting rod 3-6 rigid connection.

[0052] As Figure 2 , Figure 3 and Figure 5 The main wing stabilizer 1 adopts left-right symmetrical structure, including main wing rib 1-1, wing surface main body 1-2 and main beam 1-3. Among them, two main wing ribs 1-1 are symmetrically distributed at the leftmost and rightmost ends of the main wing stabilizer 1, and the main wing rib 1-1 is connected with the main beam 1-3 through the rib-main beam hole 1-1-1 to form a through rigid connection; the main beam 1-3 extends through the wing surface-main beam hole 1-2-1 at the central axis of the front part of the wing surface main body 1-2 to form a main wing structure core load-bearing frame. The main wing rib 1-1 tail edge region is provided with a connecting rod pin connection hole 1-1-3, which is hinged and driven with the first connecting rod 3-1 through the second pin X2; a primary flap movement guide rail 1-1-2 is integrated behind the connecting rod pin connection hole 1-1-3, which is used to constrain the sliding trajectory of the second connecting rod 3-2 and ensure the directional movement of the primary flap 4. The rear part of the wing surface main body 1-2 is provided with a rudder mounting hole 1-2-2, and the rudder box 2-1 is embeddedly fixed through the rudder mounting hole 1-2-2; a through rod movement guide rail 1-2-3 is arranged on the rear side of the rudder mounting hole 1-2-2, and the spread through drive rod 2-4 is connected with the first connecting rod 3-1 through the first pin X1 and performs reciprocating linear displacement along the through rod movement guide rail 1-2-3, and the rear part of the wing surface main body 1-2 is provided with a thin groove to accommodate the first connecting rod 3-1, realizing power transmission and motion conversion. Among them, the wing surface main body 1-2 is manufactured by PMI hot cutting integral forming, the technology is mature, and the aerodynamic shape of the airfoil surface and lightweight manufacturing are considered.

[0053] As Figure 2 and Figure 4As shown, the rudder box 2 includes a rudder box body 2-1, a rudder arm 2-2, a power output rod 2-3, a spanwise through drive rod 2-4 and a rudder arm pin shaft 2-5. The rudder box body 2-1 is embeddedly fixed through the rudder installation hole 1-2-2 of the airfoil body 1-2, and the power output end thereof is rigidly connected with the root of the rudder arm 2-2 through the rudder box-rudder arm connecting hole 2-2-1 to realize power input; the outer end of the rudder arm 2-2 is connected with the first end of the power output rod 2-3 through the rudder arm pin shaft 2-5 on the rudder arm-output rod connecting hole 2-3-1, the second end of the power output rod 2-3 is connected with the spanwise through drive rod 2-4 through the output rod-through rod connecting hole 2-3-2 to form a transmission pair, and power is transmitted to the spanwise through drive rod 2-4. The spanwise length of the spanwise through drive rod 2-4 matches the span length of the airfoil body 1-2, and the left and right ends of the spanwise through drive rod 2-4 respectively extend into the symmetrically arranged through rod movement guide rails 1-2-3 on both sides of the airfoil body 1-2 to form a crank slider transmission mechanism, which drives the spanwise through drive rod 2-4 to perform directional linear displacement along the through rod movement guide rail 1-2-3.

[0054] As Figure 2 , Figure 5 , Figure 6 and Figure 7As shown, the connecting rod mechanism 3 includes: seven connecting rods 3-1 to 3-7, and twelve pins X1 to X12. The first connecting rod 3-1 is connected to the connecting rod pin hole 1-1-3 of the main wing rib 1-1 through the second pin X2, and is connected to the spanwise through rod 2-4 of the steering engine 2 through the first pin X1 to input power. The second connecting rod 3-2 is L-shaped, one end of which is connected to the first connecting rod 3-1 through the fourth pin X4, the middle corner of which is connected to the fourth connecting rod 3-4 through the seventh pin X7, and the other end of which is connected to the primary flap 4 through the fifth pin X5 and the sixth pin X6, respectively, thereby fixing the second connecting rod 3-2 and the primary flap 4, and the fifth pin X5 cooperates with the primary flap movement guide rail 1-1-2 of the main wing rib 1-1 to form a moving pair. One end of the third connecting rod 3-3 is connected to the first connecting rod 3-1 through the third pin X3, and the other end is connected to the fourth connecting rod 3-4 through the eighth pin X8. The fourth connecting rod 3-4 is connected to the fifth connecting rod 3-5 through the sixth pin X9, and the fifth connecting rod 3-5 is connected to the secondary flap 5 through the tenth pin X10, thereby transmitting motion to the secondary flap 5. The sixth connecting rod 3-6 and the seventh connecting rod 3-7 are symmetrically arranged on the transverse sides of the secondary flap track 4-1-3 and are rigidly connected to the secondary flap 5-1, and the eleventh pin X11 and the twelfth pin X12 are located on the longitudinal sides of the secondary flap track 4-1-3 and are connected to the sixth connecting rod 3-6 and the seventh connecting rod 3-7, thereby forming a slider linkage mechanism with a single degree of freedom. The connecting rod mechanism 3 transmits motion through multiple components to accurately limit the deployment and retraction of the primary flap 4 and the secondary flap 5 along the predetermined track. All connecting rods are made of 3K carbon fiber plates CNC engraved and punched, which has mature technology, low processing difficulty, high processing precision, high strength and light weight.

[0055] As Figure 2 and Figure 6As shown, the primary flap 4 comprises a primary flap surface 4-1 and a primary flap main beam 4-2. The primary flap surface 4-1 is integrally connected with the primary flap main beam 4-2 through a primary surface main beam hole 4-1-1, forming an integrated load-bearing structure. The primary flap surface 4-1 is hingedly connected with the second connecting rod 3-2 at a flap connecting rod pin hole 4-1-2 through a sixth pin X6. The second flap track 4-1-3 is an outward track distributed on the leftmost and rightmost ends of the primary flap surface 4-1, thereby restricting the movement track of the secondary flap 5. The primary flap main beam 4-2 is hingedly connected with the second connecting rod 3-2 and the main wing rib 1-1 through a fifth pin X5, and the driving force of the connecting rod mechanism 3 is transmitted to the leading edge of the primary flap 4 to drive the primary flap 4 to perform a rearward and downward combined movement along the primary flap movement guide track 1-1-2 of the main wing rib 1-1, ensuring the accuracy of the movement track and the reliability of the action. The primary flap surface 4-1 is made of PMI foam by hot cutting and integral molding, which is light in weight and smooth in surface.

[0056] As shown in Figure 2 and Figure 7 As shown, the secondary flap 5 comprises a secondary flap surface 5-1 and a secondary flap main beam 5-2. The secondary flap surface 5-1 is integrally connected with the secondary flap main beam 5-2 through a secondary surface main beam hole 5-1-1, forming an integrated load-bearing structure. The secondary flap surface 5-1 is rigidly connected with the sixth connecting rod 3-6 and the seventh connecting rod 3-7 arranged symmetrically on the longitudinal sides of the second flap track 4-1-3 arranged at the tail of the primary flap surface 4-1, forming a single-degree-of-freedom slider linkage mechanism. The secondary flap main beam 5-2 is pin-connected with the fifth connecting rod 3-5 through a tenth pin X10, and the power is transmitted to the leading edge of the secondary flap 5 to drive the secondary flap 5 to perform a synchronous unfolding and folding movement along the second flap track 4-1-3, ensuring the accuracy of the movement track and effectively preventing excessive deflection or mechanical jamming. The secondary flap surface 5-1 is made of PMI foam by hot cutting molding technology, which is low in processing difficulty and high in finished product lightness.

[0057] The working process of the double-slotted flap mechanism of the light unmanned aerial vehicle is as follows.

[0058] As shown in Figure 1As shown, after the double-slotted flap mechanism of the light unmanned aerial vehicle is assembled, the primary flap 4 and the secondary flap 5 are both in the fully retracted position in the initial state. When the flap deployment command is triggered, the servo 2 drives the servo arm 2-2 to rotate around the shaft, drives the spanwise through drive rod 2-4 to move along the through rod movement guide rail 1-2-3 of the wing body 1-2 through the power output rod 2-3, and then the linkage mechanism 3 performs the transmission action. The linkage mechanism 3 drives the primary flap main beam 4-2 to perform the rearward and downward combined motion along the primary flap movement guide rail 1-1-2 through the sixth pin X6, and at the same time, the secondary flap 5 main beam is driven to complete the same phase deployment action along the secondary flap track 4-1-3 through the rigid connection of the sixth linkage 3-6 and the seventh linkage 3-7, so that the primary flap and the secondary flap are synchronized to the maximum deployment angle, forming a double-slotted aerodynamic configuration, and significantly improving the lift coefficient and flow field control efficiency. When the flap retraction command is triggered, the servo 2 reversely drives the servo arm 2-2 to rotate, and the spanwise through drive rod 2-4 reversely moves along the through rod movement guide rail 1-2-3, forcing the linkage mechanism 3 to drive the primary flap and the secondary flap main beam to move in the reverse direction along the deployment path, until the primary flap 4 and the secondary flap 5 are completely reset to the initial retracted state, restoring the integrity of the wing aerodynamic shape. In this process, the primary flap 4 and the secondary flap 5 are cooperatively deployed and retracted along the predetermined track, the motion trajectory is controlled accurately, and the transmission efficiency is relatively high.

[0059] In the description of the present specification, the description of the terms "one embodiment / way", "some embodiments / ways", "example", "specific example", or "some examples" means that the specific features, structures, materials or characteristics described in connection with the embodiment / way or example are included in at least one embodiment / way or example of the present application. In the present specification, the illustrative description of the above terms does not necessarily refer to the same embodiment / way or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments / ways or examples in a suitable manner. In addition, the skilled in the art can combine and combine the different embodiments / ways or examples described in the present specification and the features of the different embodiments / ways or examples without contradiction.

[0060] In addition, the terms "first", "second" are only for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of indicated technical features. Therefore, the features defined with "first", "second" can explicitly or implicitly include at least one of the features. In the description of the present application, the meaning of "multiple" is at least two, such as two, three, etc., unless otherwise specifically limited.

[0061] Those skilled in the art should understand that the above embodiments are only for clearly illustrating the present application, and are not intended to limit the scope of the present application. Based on the above disclosure, other changes or modifications can be made by those skilled in the art, and these changes or modifications are still within the scope of the present application.

Claims

1. A dual-slotted flap mechanism for a light unmanned aerial vehicle, characterized by, The main wing stabilizer, the steering engine, the connecting rod mechanism, the first flap and the second flap are included. The main wing stabilizer and the steering engine are fixedly connected by embedding; a pair of the connecting rod mechanisms are symmetrically distributed and are respectively in transmission connection with the two ends of the main wing stabilizer, the steering engine, the first flap and the second flap by hinging; the first flap and the second flap perform synchronous backward and downward compound motion along a predetermined track to form a double-slit aerodynamic configuration.

2. A dual-slotted flap mechanism for a light unmanned aerial vehicle as claimed in claim 1, wherein, The main wing stabilizer includes a wing surface body, a pair of symmetrically distributed main wing ribs on the left and right sides of the wing surface body and a main beam rigidly connected with the main wing ribs; the tail edge of the main wing rib is integrated with a motion guide rail to constrain the motion track of the first flap; the wing surface body is manufactured by PMI hot cutting integral forming; the main beam penetrates the front part of the wing surface body and forms a core load-bearing frame.

3. A dual-slotted flap mechanism for a light unmanned aerial vehicle as claimed in claim 1, wherein, The steering engine includes a steering engine box, a steering arm, a power output rod, a spanwise penetrating drive rod and a steering arm pin; the steering engine box is fixedly embedded in the rear part of the wing surface body of the main wing stabilizer; the steering arm and the power output rod are rigidly hinged with the spanwise penetrating drive rod to form a transmission pair, which drives the spanwise penetrating drive rod to perform directional linear displacement along the penetrating rod motion guide rail symmetrically arranged on the two sides of the wing surface body of the main wing stabilizer.

4. A double-slotted flap mechanism for a light unmanned aerial vehicle according to claim 3, wherein, The spanwise length of the spanwise penetrating drive rod matches the span of the wing surface body of the main wing stabilizer, and the left and right ends of the spanwise penetrating drive rod extend into the penetrating rod motion guide rails on the two sides of the wing surface body to form a steering engine driven rocker transmission mechanism.

5. The dual-slotted flap mechanism of claim 1, wherein, The connecting rod mechanism includes a plurality of connecting rods and pins, and the multi-rod transmission design of the connecting rod mechanism symmetrically connected to the main wing stabilizer realizes power step transmission; the pins realize the fixed and transmission hinging of the connecting rods with the main wing stabilizer, the steering engine, the first flap and the second flap.

6. A dual-slotted flap mechanism for a light unmanned aerial vehicle as claimed in claim 5, wherein, The connecting rod mechanism includes L-shaped connecting rods and multi-stage hinged pins, the connecting rods are CNC engraved and punched by 3K specification carbon fiber plate, and the connecting rod mechanism forms a compound motion pair by cooperating with the guide rail through a moving pair to ensure the accurate synchronization of the backward and downward actions of the first flap.

7. The dual-slotted flap mechanism of claim 1, wherein, The first flap and the second flap both adopt an integrated load-bearing structure, and the rudder surface and the main beam are fixedly connected through penetrating holes; wherein, the first flap rudder surface and the second flap rudder surface are both manufactured by PMI hot cutting integral forming, which is light in weight, easy to process and maintains the aerodynamic shape.

8. A double-slotted flap mechanism for a light unmanned aerial vehicle according to claim 7, wherein, The first flap main beam of the first flap forms a moving pair with the connecting rod mechanism through the pin to drive the first flap to perform backward and downward compound motion along the first flap motion guide rail; the second flap main beam of the second flap performs synchronous unfolding and folding along the second flap track through the single-degree-of-freedom slider linkage mechanism rigidly connected.

9. A double-slotted flap mechanism for a light unmanned aerial vehicle according to claim 8, wherein, The first flap motion guide rail is integrated in the tail edge of the main wing rib of the main wing stabilizer, and the second flap track is symmetrically arranged at the tail of the first flap rudder surface to realize the track constraint and synchronous control of the double-stage flaps through the cooperation of the guide rail and the rigid connecting rod.

10. The dual-slotted flap mechanism of a light unmanned aerial vehicle according to claim 1, wherein, The double-slit aerodynamic configuration forms a multi-stage flow channel through the coordinated unfolding of the first flap and the second flap, which significantly improves the lift coefficient and the boundary layer control efficiency.

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