CN207000812U - Double duct unmanned aerial vehicles that a kind of secondary transmission engine lap siding can generate electricity with loading - Google Patents

Abstract

Double duct unmanned aerial vehicles that a kind of secondary transmission engine lap siding can generate electricity with loading, including fuselage, transmission component, electrification component, rotor assemblies, rudder face component, flight control assembly, the symmetrical layout of complete machine, fuselage is made up of metallic plate, two engines of transmission component are longitudinally arranged on fuselage, and rotor assemblies lateral arrangement is in fuselage both sides；On the one hand the rotary motion of engine is passed to rotor assemblies by transmission component by timing belt and synchronizing wheel, on the other hand pass to electrification component；Rudder face component adjusts rudder face angle by steering wheel；Flight control assembly receives the operational order of operator and is sent to each component.The utility model uses cross layout structure and timing belt secondary transmission, and increase from the mode for making power supply, reduce fuselage body vibration frequency, alleviate deadweight, its endurance and endurance are added, enhances the navigation stability of unmanned plane, simultaneously, body upper can carry various goods and materials as article carrying platform.

Description

Double duct unmanned aerial vehicles that a kind of secondary transmission engine lap siding can generate electricity with loading

Technical field

The utility model belongs to unmanned air vehicle technique field, and in particular to a kind of secondary transmission engine lap siding can generate electricity and Double duct unmanned aerial vehicles of loading.

Background technology

Unmanned plane is that a kind of build is smaller, unmanned, can realize autonomous flight in the air and perform certain task Aircraft.Unmanned plane also represents because its unique application all obtains extensive use and rapid development in Military and civil fields in recent years For an important development direction of following aviation.

In unmanned plane application process, because its is unmanned, its payload is bigger, can install more equipment and such as take the photograph Camera is taken photo by plane or load-carrying carries out goods and materials transport, and therefore, the efficiency and reliability that task is completed to it requires higher, and it is tied It is more that conformational space utilization rate and lift and pose convert considering for flexibility.And in the prior art, majority is using increase power Drive device quantity or using the main power system such as fuel engines lifting unmanned plane lift, increases its lifting capacity, but more than Method makes in-flight vibration frequency rise influence unmanned plane stability, deadweight increase, adds its energy consumption, complex structural designs, Pose conversion flexibility is had a greatly reduced quality, while makes unmanned plane overall structure size increase, not compact, the winged control performance of unmanned plane by Gradual change is low.

Meanwhile for unmanned air vehicle technique, how on the premise of its loading capacity and deadweight is ensured, increase its endurance It is a critical index for indicating its performance, the parameter phase such as endurance and engine behavior, flying height, flying speed Close, and in the prior art, majority uses the modes of on-board batteries, and for unmanned plane, other provide electric energy with electrical component, on-board batteries Energy ratio decides the endurance of unmanned plane, under same volume or loading condition, how to obtain more electric energy, improves energy Source utilization rate, turn into another research direction for solving the problems, such as unmanned plane endurance.

Utility model content

The purpose of this utility model is to provide double ducts that a kind of secondary transmission engine lap siding can generate electricity with loading Unmanned plane, the double duct unmanned aerial vehicles of solution tradition, which are moved, and posture is highly coupled, on-board batteries electricity and its weight are adapted causes Flight control system is complicated, frequency of oscillation is high, stability is poor, low space utilization, not compact, endurance is short, from it is great, lift is inadequate, A series of problems, such as loading capacity is small, cost is high.

The utility model is achieved like this, double ducts that a kind of secondary transmission engine lap siding can generate electricity with loading Unmanned plane, including fuselage, transmission component, electrification component, rotor assemblies, rudder face component, flight control assembly, it is characterised in that The symmetrical layout of complete machine, wherein, two engines of transmission component are longitudinally arranged on fuselage, rotor assemblies lateral arrangement in Fuselage both sides；Every engine drives two propellers to turn at a high speed round about by a set of timing belt and synchronizing wheel respectively It is dynamic, moment of torsion of cancelling out each other, and required ascending air is produced in duct；Transmission component is secondary transmission structure, and it passes through same On the one hand the rotary motion of engine is passed to rotor assemblies by step band and synchronizing wheel, on the other hand by the rotary motion of engine Electrification component is passed to, electric power is produced and is used for unmanned plane other assemblies；Rudder face component adjusts rudder face angle by steering wheel, changes Airflow direction and then direction and the posture for changing unmanned plane during flying；Flight control assembly receives the operational order of operator and transmission To each component, the state of flight of unmanned plane is controlled.

Preferably, described fuselage include bottom plate, side plate, top plate, foreboard, pipe clamp, undercarriage, bottom plate, top plate and side plate, Foreboard is connected by screw respectively, forms a frame structure, provides protection and support for intraware, pipe clamp has been clamped in Fall on the pipe of frame, and be connected by screw with bottom plate, provided a supporting role when being unmanned plane takeoff and landing.

Preferably, the transmission component also include the first synchronizing wheel, the second synchronizing wheel, the 3rd synchronizing wheel, the 4th synchronizing wheel, 5th synchronizing wheel, the 6th synchronizing wheel, power transmission shaft, the first timing belt, the second timing belt, the 3rd timing belt, idle pulley, rotor shaft；Its In, two engines, one formal dress of transmission component, an anti-dress, running part all same.

Preferably, the primary transmission of the transmission component is：First synchronizing wheel is fixed by screws in engine output end Face, the first synchronizing wheel engage with the flute profile of the first timing belt and power are transferred into the second synchronizing wheel, and the second synchronizing wheel passes through key Rotation is passed into power transmission shaft；Secondary transmission is divided into two aspects：On the one hand, rotation is passed to the 3rd synchronously by power transmission shaft by key Wheel, the 3rd synchronizing wheel is meshed with the flute profile of the second timing belt, while the second timing belt is tensioned by four idle pulleys, and power is transmitted To the 4th synchronizing wheel, rotation is passed to rotor shaft by the 4th synchronizing wheel by key, so as to drive the rotation of propeller；The opposing party Rotation is passed to the 5th synchronizing wheel by face, power transmission shaft by Top fastening screw, and the 5th synchronizing wheel engages with the flute profile of the 3rd timing belt And power is transferred to the 6th synchronizing wheel, the 6th synchronizing wheel is connected by Top fastening screw with the output shaft of generator, drives output Axle rotates, so as to which generator generates electric power.

Preferably, described electrification component includes, generator, vertical columns, and complete machine includes two generators, respectively by two Platform driven by engine, vertical columns one end are fixed by nut and generator, the other end by screw respectively with bottom plate and top plate Connection, by the rotation of output shaft so as to produce electric power, powered for other assemblies.

Preferably, described rotor assemblies include rotor bearing diagonal, rotor arm, duct supporting plate, synchronizing wheel installing plate, spiral shell Oar, upper rotor geometrical clamp, lower rotor geometrical clamp, girder, duct, pipe are revolved, rotor bearing diagonal uses screw, one end and top Plate is connected, and one end is connected with synchronizing wheel installing plate, and rotor arm uses screw, and one end is connected with side plate, and one end is installed with synchronizing wheel Plate connects, and rotor shaft clamping is between upper and lower synchronizing wheel installing plate, and wherein one end is connected by key with upper rotor geometrical clamp, on Rotor geometrical clamp and lower rotor geometrical clamp are fixed by screws in the upper and lower end face of propeller, three flight support plates respectively One end is connected with synchronizing wheel installing plate, and one end is connected with girder, and supports duct, meanwhile, girder passes through screws clamp pipe.

Preferably, described rudder face component includes rudder face, the first rudder face connecting plate, the second rudder face connecting plate, connecting rod, steering wheel Mounting bracket, steering wheel, steering wheel pull bar, steering wheel rocking arm, the first rudder face connecting plate are clamped in two end face highlights of rudder face, and respectively It is connected with the second rudder face connecting plate and connecting rod by ball pivot, the second rudder face connecting plate is connected by screw with pipe geometrical clamp, is made Obtain rudder face component to be suspended on below duct, steering wheel mounting bracket one end is fixed by screws on pipe geometrical clamp, one end connection rudder Machine, steering wheel output axis connection steering wheel rocking arm, steering wheel rocking arm is connected with steering wheel pull bar again, it is achieved thereby that the angle swinging of rudder face.

Preferably, described flight control assembly includes flying control box fixed mount, flight control box, flies control box vibration damper plate, flies Control box fixed mount is connected by screw with top plate, and flight control box is connected by screw with flying control vibration damper plate again, Ke Yi Play a part of shock-absorbing protecting in flight course.

Preferably, the top plate can be used as article carrying platform, can up place the goods and materials for needing to carry, such as agricultural chemicals, urgency Rescue apparatus, water tank etc..

Preferably, the fuselage is made up of metallic plate, and protection and supporting role are provided for whole unmanned plane.

Compared with prior art, the utility model has the advantage of：

Application scheme is longitudinally arranged on fuselage using two engines, rotor assemblies lateral arrangement in fuselage both sides, Power Component is by the way of secondary transmission, two engines, one formal dress, and an anti-dress, every engine is respectively by a set of Timing belt drives two propellers high-speed rotation round about, torsion of cancelling out each other by a set of timing belt and synchronizing wheel respectively Square, and required ascending air is produced in duct, meanwhile, servos control rudder face swings certain angle to change the stream of air-flow Dynamic direction, is changed into laminar flow by turbulent flow, and then unmanned plane is flown according to the direction needed for operator, posture；Meanwhile engine is also Two generators have been driven to rotate by another set of timing belt and synchronizing wheel, so as to generate the other assemblies that electric current supplies unmanned plane The mode used, it specify that power set arrange relative position relation, spatial design is compact, and utilization rate is high；And use two electricity Machine provides power, and increases from the mode for making power supply, reduces fuselage body vibration frequency, alleviates deadweight, add Its endurance and endurance, enhance the navigation stability of unmanned plane；Swung by rudder face, change airflow direction, body is navigated During row, pose, inclination angle and course direction, Power Component, generating set can flexibly be changed according to the control operation of operating personnel Part, rotor assemblies, rudder face modular construction are mutually coupled, and realize double duct unmanned aerial vehicle lift, strong stability, heavy－duty, endurance Long, it is compact-sized, space availability ratio is high, energy utilization rate is high, pose conversion flexibly etc. technique effect.

Brief description of the drawings

Fig. 1 can generate electricity for the application secondary transmission engine lap siding to be shown with the agent structure of double duct unmanned aerial vehicles of loading It is intended to；

Fig. 2 is the main schematic diagram of the application unmanned plane structure

Fig. 3 is the main schematic diagram of airframe structure of the application unmanned plane

Fig. 4 is the section transmission component structure diagram of the application unmanned plane

Fig. 5 is the part rotor assemblies structural representation of the application unmanned plane

Fig. 6 is the part rudder face component structure diagram of the application unmanned plane

Fig. 7 is the flight control assembly structural representation of the application unmanned plane

Fig. 8 is the transmission component overall structure and rotor direction schematic diagram of the application unmanned plane

Embodiment

The utility model is described in detail below in conjunction with the accompanying drawings.

As shown in Figure 1, 2, double duct unmanned aerial vehicles that a kind of secondary transmission engine lap siding can generate electricity with loading, including machine Body, transmission component, electrification component, rotor assemblies, rudder face component, flight control assembly, the symmetrical layout of complete machine, fuselage is by gold Belong to plate to form, protection and supporting role are provided for whole unmanned plane；Wherein, two engines of transmission component are longitudinally arranged in machine With, rotor assemblies lateral arrangement is in fuselage both sides；Transmission component is by timing belt and synchronizing wheel by the rotary motion of engine On the one hand rotor assemblies are passed to, produce the ascending air needed for flight, on the other hand pass to electrification component, electric power is produced and supplies Unmanned plane other assemblies use；Rudder face component adjusts rudder face angle by steering wheel, changes airflow direction and then change unmanned plane flies Capable direction and posture；Flight control assembly receives the operational order of operator and is sent to each component, controls unmanned plane State of flight.

As shown in Fig. 1,3,5, described fuselage includes bottom plate 1, side plate 2, top plate 3, foreboard 4, pipe clamp 5, undercarriage 6, bottom Plate 1, top plate 3 and side plate 2, foreboard 4 are connected by screw respectively, form a frame structure, protection is provided for intraware And support, pipe clamp 5 are clamped on the pipe 31 of undercarriage 6, and it is connected by screw with bottom plate 1, takes off and drop for unmanned plane Provided a supporting role when falling, top plate 3 can be used as article carrying platform, can up place the goods and materials for needing to carry, such as agricultural chemicals, first aid Apparatus, water tank etc..

As shown in Fig. 4,8, described transmission component is divided into secondary transmission, including engine 7, the first synchronizing wheel 8, second are same The 9, the 3rd synchronizing wheel 10 of step wheel, the 4th synchronizing wheel 11, the 5th synchronizing wheel 12, the 6th synchronizing wheel 13, power transmission shaft 14, the first timing belt 15th, the second timing belt 16, the 3rd timing belt 17, idle pulley 18, rotor shaft 19, complete machine include two engines, 7 one formal dress, one Anti- dress, running part all same, primary transmission are：First synchronizing wheel 8 is fixed by screws in the output end face of engine 7, and first Synchronizing wheel 8 engages with the flute profile of the first timing belt 15 and power is transferred into the second synchronizing wheel 9, and the second synchronizing wheel 9 will by key Rotation passes to power transmission shaft 14；Secondary transmission is divided into two aspects：On the one hand, it is same by key to be passed to the 3rd by power transmission shaft 14 for rotation Step wheel 10, the 3rd synchronizing wheel 10 is meshed with the flute profile of the second timing belt 16, while the second timing belt 16 is opened by four idle pulleys 18 Tightly, power is transferred to the 4th synchronizing wheel 11, rotation is passed to rotor shaft 19 by the 4th synchronizing wheel 11 by key, so as to drive The rotation of propeller 20；On the other hand, rotation is passed to the 5th synchronizing wheel 12 by power transmission shaft 14 by Top fastening screw, and the 5th is synchronous Wheel 12 engages with the flute profile of the 3rd timing belt 17 and power is transferred into the 6th synchronizing wheel 13, and the 6th synchronizing wheel 13 is by holding out against spiral shell Nail is connected with the output shaft of generator 21, drives output shaft rotation, so as to which generator 21 generates electric power.

As shown in Fig. 4,8, described electrification component includes, generator 21, vertical columns 22, and complete machine includes two generators 21, driven respectively by two engines 7, the one end of vertical columns 22 is fixed by nut and generator 21, and the other end passes through screw It is connected with bottom plate 1 and top plate 3, by the rotation of output shaft so as to produce electric power, is powered for other assemblies respectively.

As shown in Figure 1,5, described rotor assemblies include rotor bearing diagonal 23, rotor arm 24, the supporting plate 25 of duct 30, same Step wheel installing plate 26, propeller 20, upper rotor geometrical clamp 27, lower rotor geometrical clamp 28, girder 29, duct 30, pipe 31, Rotor bearing diagonal 23 uses screw, and one end is connected with top plate 3, and one end is connected with synchronizing wheel installing plate 26, and rotor arm 24 uses spiral shell Nail, one end are connected with side plate 2, and one end is connected with synchronizing wheel installing plate 26, and the clamping of rotor shaft 19 is in upper and lower synchronizing wheel installing plate 26 Between, wherein one end is connected by key with upper rotor geometrical clamp 27, upper rotor geometrical clamp 27 and lower rotor geometrical clamp 28 The upper and lower end face of propeller 20 is fixed by screws in respectively, three flight support plate one end are connected with synchronizing wheel installing plate 26, One end is connected with girder 29, and supports duct 30, meanwhile, girder 29 passes through screws clamp pipe 31.

As a shown in Figure 6, described rudder face component is symmetrically mounted on fuselage both sides, rudder face component include forward and backward rudder face 32, First rudder face connecting plate 33, the second rudder face connecting plate 34, connecting rod 35, the mounting bracket 36 of steering wheel 37, steering wheel 37, steering wheel pull bar 38, rudder Machine rocking arm 39, the first rudder face connecting plate 33 are clamped in two end face highlights of rudder face 32, and respectively with the second rudder face connecting plate 34 are connected with connecting rod 35 by ball pivot, and the second rudder face connecting plate 34 is connected by screw with the geometrical clamp of pipe 31 so that rudder face 32 Component is suspended on the lower section of duct 30, and the one end of 37 mounting bracket of steering wheel 36 is fixed by screws on the geometrical clamp of pipe 31, one end connection Steering wheel 37, steering wheel 37 export axis connection steering wheel rocking arm 39, and steering wheel rocking arm 39 is connected with steering wheel pull bar 38 again, it is achieved thereby that rudder face 32 angle swinging.

As shown in Fig. 1,7, described flight control assembly includes flying control box fixed mount 40, flight control box 41, flies control box Vibration damper plate 42, fly control box fixed mount 40 and be connected by screw with top plate 3, flight control box 41 is again by screw with flying control damping Plate is connected, and can play a part of shock-absorbing protecting in flight course.

Two engines 7 are longitudinally arranged, and drive two propellers 20 to opposite by a set of timing belt and synchronizing wheel respectively Direction high-speed rotation, moment of torsion of cancelling out each other, and required ascending air is produced in duct 30, steering wheel 37 controls rudder face 32 to swing Certain angle, so as to change the flow direction of air-flow, and then unmanned plane is flown according to the direction needed for operator.Together When, engine 7 has also driven two generators 21 to rotate by another set of timing belt and synchronizing wheel, so as to generate electric current for flying Row control system uses.

Scheme described in the embodiment of the present application, it is longitudinally arranged using two engines on fuselage, rotor assemblies are horizontal Fuselage both sides are arranged in, Power Component is by the way of secondary transmission, two engines, one formal dress, an anti-dress, every hair Motivation drives two propellers high speed round about by a set of timing belt and synchronizing wheel respectively by a set of timing belt respectively Rotate, moment of torsion of cancelling out each other, and required ascending air is produced in duct, meanwhile, servos control rudder face swings certain angle Turbulent flow is changed into laminar flow, and then unmanned plane is flown according to the direction needed for operator, posture by degree to change the flow direction of air-flow OK；Meanwhile engine has also driven two generators to rotate by another set of timing belt and synchronizing wheel, supplied so as to generate electric current The mode that the other assemblies of unmanned plane use, it specify that power set arrange relative position relation, spatial design is compact, utilization rate It is high；And power is provided using two motors, and increase from the mode for making power supply, fuselage body vibration frequency is reduced, is subtracted Light deadweight, adds its endurance and endurance, enhances the navigation stability of unmanned plane；Swung by rudder face, change gas Direction is flowed, during making body navigation, pose, inclination angle and course direction can flexibly be changed according to the control operation of operating personnel, Power Component, electrification component, rotor assemblies, rudder face modular construction are mutually coupled, and realize double duct unmanned aerial vehicle lift, Qiang Wen Fixed, heavy－duty, endurance is long, compact-sized, space availability ratio is high, energy utilization rate is high, pose converts the technique effect such as flexible.

Unmanned plane in application scheme can be used for plant protection, shooting, military affairs etc. multi-field.

Certainly, the utility model can also have other various embodiments, without departing substantially from the utility model spirit and its essence In the case of, those skilled in the art work as can make various corresponding changes and deformation according to the utility model, but these Corresponding change and deformation should all belong to the scope of the claims appended by the utility model.

Claims (13)

1. double duct unmanned aerial vehicles that a kind of secondary transmission engine lap siding can generate electricity with loading, including fuselage, transmission component, hair Electrical component, rotor assemblies, rudder face component, flight control assembly, the symmetrical layout of complete machine, it is characterised in that：Fuselage uses frame Frame structure, two engines are longitudinally arranged uses synchronous drive power transfer mode and secondary transmission in fuselage interior, transmission component Form, electrification component can be driven generator to produce electric power by secondary transmission structure and be powered for other assemblies, symmetrical rotation Wing component lateral arrangement has each other in both sides outside fuselage, complete machine into cross structure, steadily of centre of gravity, rotor assemblies both sides propeller Opposite direction of rotation, counteracting propeller is anti-twisted, and rudder face component is located at below rotor, passes through servos control control surface deflection position and adjusts Whole UAV Attitude and direction, the flight control assembly after encapsulation are provided with shock-damping structure.

2. double duct unmanned aerial vehicles that a kind of secondary transmission engine lap siding according to claim 1 can generate electricity with loading, It is characterized in that：Described fuselage includes bottom plate (1), side plate (2), top plate (3), foreboard (4), pipe clamp (5), undercarriage (6).

3. double duct unmanned aerial vehicles that a kind of secondary transmission engine lap siding according to claim 2 can generate electricity with loading, It is characterized in that pipe clamp (5) is clamped on the pipe (31) of undercarriage (6), the pipe clamp is connected on bottom plate.

4. double duct unmanned aerial vehicles that a kind of secondary transmission engine lap siding according to claim 1 can generate electricity with loading, It is characterized in that：The transmission component also includes the first synchronizing wheel (8), the second synchronizing wheel (9), the 3rd synchronizing wheel (10), the 4th Synchronizing wheel (11), the 5th synchronizing wheel (12), the 6th synchronizing wheel (13), power transmission shaft (14), the first timing belt (15), the second timing belt (16), the 3rd timing belt (17), idle pulley (18), rotor shaft (19).

5. double duct unmanned aerial vehicles that a kind of secondary transmission engine lap siding according to claim 4 can generate electricity with loading, Wherein, (7) formal dress of two engines of transmission component, an anti-dress, running part all same.

6. double duct unmanned aerial vehicles that a kind of secondary transmission engine lap siding according to claim 4 can generate electricity with loading, It is characterized in that：The primary transmission of the transmission component is：First synchronizing wheel (8) is fixed by screws in engine (7) output End face, the first synchronizing wheel (8) engage with the flute profile of the first timing belt (15) and power are transferred into the second synchronizing wheel (9), and second Rotation is passed to power transmission shaft (14) by synchronizing wheel (9) by key；Secondary transmission is divided into two aspects：On the one hand, power transmission shaft (14) is logical Cross key and rotation is passed into the 3rd synchronizing wheel (10), the 3rd synchronizing wheel (10) is meshed with the flute profile of the second timing belt (16), together When the second timing belt (16) be tensioned by four idle pulleys (18), power is transferred to the 4th synchronizing wheel (11), the 4th synchronizing wheel (11) Rotation is passed to by rotor shaft (19) by key, so as to drive the rotation of propeller (20)；On the other hand, power transmission shaft (14) is logical Cross Top fastening screw and rotation is passed into the 5th synchronizing wheel (12), the 5th synchronizing wheel (12) engages with the flute profile of the 3rd timing belt (17) And power is transferred to the 6th synchronizing wheel (13), the 6th synchronizing wheel (13) passes through Top fastening screw and the output shaft phase of generator (21) Even, output shaft rotation is driven, so as to which generator (21) generates electric power.

7. double duct unmanned aerial vehicles that a kind of secondary transmission engine lap siding according to claim 1 can generate electricity with loading, It is characterized in that：Described electrification component includes, generator (21), vertical columns (22), and complete machine includes two generators (21), Driven respectively by two engines (7), vertical columns (22) one end is fixed by nut and generator (21), and the other end passes through spiral shell Nail is connected with bottom plate (1) and top plate (3) respectively, by the rotation of output shaft so as to produce electric power, is powered for other assemblies.

8. double duct unmanned aerial vehicles that a kind of secondary transmission engine lap siding according to claim 1 can generate electricity with loading, It is characterized in that：Described rotor assemblies include rotor bearing diagonal (23), rotor arm (24), duct (30) supporting plate (25), same Step wheel installing plate (26), propeller (20), upper rotor geometrical clamp (27), lower rotor geometrical clamp (28), girder (29), duct (30), pipe (31), rotor bearing diagonal (23) use screw, and one end is connected with top plate (3), one end and synchronizing wheel installing plate (26) Connection, rotor arm (24) use screw, and one end is connected with side plate (2), and one end is connected with synchronizing wheel installing plate (26), rotor shaft (19) clamping is between upper and lower synchronizing wheel installing plate (26), and wherein one end is connected by key with upper rotor geometrical clamp (27), on Rotor geometrical clamp (27) and lower rotor geometrical clamp (28) are fixed by screws in the upper and lower end face of propeller (20) respectively, and three Individual flight support plate one end is connected with synchronizing wheel installing plate (26), and one end is connected with girder (29), and supports duct (30), together When, girder (29) passes through screws clamp pipe (31).

9. double duct unmanned aerial vehicles that a kind of secondary transmission engine lap siding according to claim 1 can generate electricity with loading, It is characterized in that：Described rudder face component include rudder face (32), the first rudder face connecting plate (33), the second rudder face connecting plate (34), Connecting rod (35), steering wheel (37) mounting bracket (36), steering wheel (37), steering wheel pull bar (38), steering wheel rocking arm (39), the first rudder face connecting plate (33) two end face highlights of rudder face (32) are clamped in, and pass through ball with the second rudder face connecting plate (34) and connecting rod (35) respectively It is hinged, the second rudder face connecting plate (34) is connected by screw with pipe (31) geometrical clamp so that rudder face (32) component is suspended on Below duct (30), steering wheel (37) mounting bracket (36) one end is fixed by screws on pipe (31) geometrical clamp, one end connection rudder Machine (37), steering wheel (37) output axis connection steering wheel rocking arm (39), steering wheel rocking arm (39) and be connected with steering wheel pull bar (38), so as to reality The angle swinging of rudder face (32) is showed.

10. double duct unmanned aerial vehicles that a kind of secondary transmission engine lap siding according to claim 1 can generate electricity with loading, It is characterized in that：Described flight control assembly includes flying control box fixed mount (40), flight control box (41), flies control box vibration damper plate (42), fly control box fixed mount (40) by screw with top plate (3) to be connected, flight control box (41) is subtracted by screw and winged control again Shake plate is connected, and can play a part of shock-absorbing protecting in flight course.

11. double duct unmanned aerial vehicles that a kind of secondary transmission engine lap siding according to claim 2 can generate electricity with loading, It is characterized in that：The top plate (3) can be used as article carrying platform, can up place the goods and materials for needing to carry.

12. double duct unmanned aerial vehicles that a kind of secondary transmission engine lap siding according to claim 1 can generate electricity with loading, It is characterized in that：Two engines (7) are longitudinally arranged in fuselage interior, and rotor assemblies lateral arrangement is in both sides outside fuselage, two Engine (7) is each via a set of timing belt and synchronizing wheel, by gearratio 1:1~1:Between 3, two generator (21) rotations are driven Turn.

13. double duct unmanned aerial vehicles that a kind of secondary transmission engine lap siding according to claim 9 can generate electricity with loading, It is characterized in that：Each rudder face component contains two rudder faces (32), and two rudder faces (32) are kept by parallel four-bar linkage Its state that is parallel to each other.