CN107364572A - Fixed Wing Vector UAV - Google Patents

Abstract

This fixed-wing vector unmanned plane proposed by the present invention,It has fuselage,Steering wheel,Flight control system,Propeller and brushless electric machine,Fuselage is made up of wing plate and upper and lower fuselage side plate,Front fuselage is fixed with motor fixing seat,Rotation bracing ring is installed by runing rest in motor fixing seat,Bracing ring is rotated to rotate around its longitudinal axis,Bracing ring is rotated built with cross runing rest,Brushless electric machine is installed in cross rotation,Propeller is installed on brushless electric machine axle,Installation deflection steering wheel and upper and lower deflection steering wheel in fuselage,Each steering wheel is connected with rotation bracing ring and cross runing rest respectively by ball-head tension rod,Control the deflection of propeller and brushless electric machine axial line,Flight control system includes remote controlled floor remote control,Remote-control receiver and APM on fuselage fly control device,With deflection steering wheel and up and down, deflection tiller room electrically connects flight control system.The vector of the present invention adaptive can rotate, and provide timely pulling force for different actions, reduction aircraft is liftoff and touchdown speed, shortens aircraft ground run distance, saves power consumption.

Description

Fixed Wing Vector UAV

technical field

The invention belongs to an unmanned aircraft technology, in particular to a fixed-wing vector unmanned aerial vehicle.

Background technique

In 1903, the Wright brothers of the United States successfully developed the first manned aircraft in human history. The exploration of the aircraft also started from here. Later, due to the backwardness of science and technology and the constraints of theoretical knowledge, the research on vector powered aircraft did not achieve good development. In recent years, with the advancement of scientific and technological theories, the United States has made major breakthroughs in vector thrust technology, and has already been far ahead of other countries in the world, becoming the country that has successfully developed vector-powered aircraft in the world. F-35B is the representative work of the famous American vector-powered aircraft.

The foreign vector-powered aircraft is a model version of the US military aircraft "F-35B", but the aircraft version F35-B only has strong ornamental value, poor maneuverability and stability, low practicability, and the fuselage structure is complete. Adopt ultra-light material, the cost is higher.

The "X-Hound" currently developed by my country's UAV company "Aoshi Technology" is also a vector UAV, consisting of four rotors.

Our country is still in the primary stage of development in terms of vector power technology. Due to the late start, the core technology has not yet been mastered, and it needs to continue to explore and learn from it. Facing the problem of core technology breakthrough, we need not only reverse research and development, but also the blooming of innovative spirit.

With the development of the aviation industry and breakthroughs in science and technology and aviation knowledge, various innovative aircraft models have sprung up, with a wide variety. At present, both domestic and foreign research on aircraft is mainly in conventional fixed-wing and multi-axis, such as: four-axis, six-axis, eight-axis and other aircraft, which have been marketed and commercialized. As far as the axis model is concerned, it has the advantages of long range, stable attitude and high energy efficiency. Fixed-wing model aircraft has gradually become a new product with novelty, stable flight and superior performance in the development, which makes the development of model aircraft enter a new research field.

However, due to the above obstacles in design and manufacturing, there is no vector UAV in the model aircraft, especially the fixed-wing UAV whose vector can be changed according to the flight needs, which restricts the improvement of the performance of the model aircraft. .

Contents of the invention

For this reason, the present invention proposes a fixed-wing vector unmanned aerial vehicle, so that it can change the drawback of the traditional fixed-wing unmanned aerial vehicle power motor with only a fixed direction of pulling force. Timely and accurate pull in different directions can reduce the speed of the aircraft from the ground and touchdown, shorten the distance of the aircraft's run, and save power consumption.

This fixed-wing vector unmanned aerial vehicle proposed by the present invention has a fuselage, a steering gear, a flight control system, a propeller and a brushless motor, and is characterized in that the fuselage is composed of wing plates and upper and lower fuselage side panels, and the front end of the fuselage The motor fixing seat is fixed, and the rotating support ring is installed on the motor fixing seat through the rotating bracket. The rotating supporting ring rotates around its radial axis. The rotating supporting ring is equipped with a cross rotating bracket. The propeller is installed, and the left and right deflection steering gear and the up and down deflection steering gear are installed in the fuselage. The left and right deflection steering gear and the up and down deflection steering gear are respectively connected to the rotating support ring and the cross rotation bracket through the ball head rod to control the axis line of the propeller and the brushless motor. The flight control system includes the ground remote controller, the remote control receiver on the fuselage and the APM flight controller. The flight control system is electrically connected to the left and right deflection steering gear and the up and down deflection steering gear.

The fuselage has a middle reinforcing plate to strengthen the connection strength between the wing plate and the upper and lower fuselage side panels.

The motor fixing seat is a cross-shaped fork inserted and inserted on the middle reinforcement plate and the upper and lower fuselage side plates.

There is a connection cross between the motor fixing seat and the rotating bracket to strengthen the fixation.

The rotating bracket is a pair of right-angled brackets, and the connection between the right-angled brackets and the rotating support ring is a pin shaft connection.

The rotating support ring and the cross rotating bracket are also connected by a pin shaft.

The ball pull rods of the left and right deflection steering gear are arranged on the left and right sides of the upper side plate of the fuselage, and the ball pull rods of the up and down deflection steering gear are arranged on the upper and lower sides of the wing plate.

The rudder plates on the wings have corresponding servo connections.

The lower part of the fuselage is equipped with sliding wheels.

The working principle of the present invention is as follows:

After the propeller is activated, the flight control system automatically adjusts the pitch angle of the propeller to provide a forward and upward vector pull force for the fuselage, and the airflow difference between the upper and lower sides of the wing plate generates a lifting force on the fuselage, and the aircraft flies into the sky. When steering is required, the left and right deflection steering gear pulls the rotating support ring to rotate around its radial axis through the ball head rod, and the vector on the axis line of the motor and propeller turns left or right. When it needs to rise or fall, deflect the steering gear up and down Pull the cross rotation bracket to rotate around its axis through the ball head rod, and the vector on the axis line of the motor and the propeller will tilt up or down. When the left and right deflection servos and up and down deflection servos operate at the same time, the vector on the axis line of the motor and the propeller will rotate as required within the range of the deflection cone angle allowed in front to achieve different postures and different actions.

The fixed-wing vector unmanned aerial vehicle of the present invention is a new product of fixed-wing development, which breaks the characteristic that the fixed-wing power motor only has a fixed pulling force direction. The unique design of the vector rotation mechanism enables the vector rotation system to achieve synchronization for the aircraft to complete the corresponding actions, providing accurate pulling forces in different directions for the flight of the drone. The circular lift of the aircraft using the vector power technology is conducive to reducing the lift-off and grounding speed of the aircraft in the direction of the lift, and shortening the sliding distance of the aircraft. For places where the air is relatively thin (such as the Tibet Plateau), ordinary aircraft need a lot of speed and power to perform various series of flight actions, which is a waste of energy. The aircraft with a new vector rotation mechanism can directly change the pulling direction of the motor. take corresponding actions. The innovative design of the combination of the vector rotation system and the new fuselage enables the UAV to have dual-mode flight functions, that is, the aerobatic flight with four ailerons and the high-speed flight with delta wings. The rotation replaces the horizontal tail and vertical tail of the aircraft respectively, and can make a series of actions of the fixed wing to realize two flight modes of the drone.

In a word, the present invention changes the disadvantage of the traditional fixed-wing unmanned aerial vehicle’s power motor that only has a fixed direction of pulling force, and the vector mechanism can self-adaptively rotate the power motor, provide timely and accurate pulling force in different directions for the aircraft to complete different actions, and reduce the aircraft’s lift off the ground and grounding speed, shortening the running distance of the aircraft and saving power consumption.

Description of drawings

Fig. 1 is a schematic perspective view of the present invention.

Figure 2 is an integrated perspective view of the brushless motor, the left and right deflection steering gear, the up and down deflection steering gear, the rotating support ring, and the motor fixing seat.

Fig. 3 is an integrated perspective view of the brushless motor, the cross rotating bracket, the rotating support ring, the rotating support and the motor fixing seat.

Fig. 4 is a front view of the cross rotation bracket.

Figure 5 is a left side view of the cross rotation bracket.

Fig. 6 is a top view of the cross rotation bracket.

Fig. 7 is a front view (partial section) of the rotating support ring.

Fig. 8 is a left side view (partial section) of the rotating support ring.

Fig. 9 is a connection diagram of various components of the present invention.

The vector deflection steering gear 1 and the vector deflection steering gear 2 in FIG. 9 respectively represent left and right deflection steering gears and up and down deflection steering gears.

The part numbers of each part in Figure 1-8 are as follows:

1-propeller; 2-brushless motor; 3-rotating support ring; 4-rotating support; 5-connecting cross; Wing rudder plate; 10- left and right deflection steering gear; 11- steering gear rocker arm; 12- ball head rod; 13- motor fixing seat; 14- middle reinforcing plate; 15- universal ball head; 17-Deflect the servo up and down.

In Fig. 1-3, the ball-joint rod marked with the ball represents the ball-joint rod of all the steering gears; the rotating support marked with 4 represents the upper and lower rotating supports; the rocker arm of the steering gear marked with 11 represents the rocker arm of all the steering gears.

detailed description

Below in conjunction with accompanying drawing and example further illustrate the present invention.

The wing plate 7 constituting the fuselage, the upper side plate 6 of the fuselage, the lower side plate 8 of the fuselage, and parts such as the middle reinforcing plate 14 are roughly the same as those of the existing general model machine, and the rudder plate 9 on the wing plate is also like this. The main changes are that the left and right deflection steering gear 10 and the up and down deflection steering gear 17 are left on the fuselage. Specifically, the left and right deflection steering gear is installed in the middle of the fuselage, and the up and down deflection steering gear is installed in the middle and front part of the fuselage. Of course, the steering gear that drives the rudder plate and the unmarked flight control system are installed on the aircraft similar to the situation of ordinary model aircraft. Not listed here.

Since the upper and lower side plates of the fuselage and the middle reinforcing plate form a cross shape, the motor fixing seat 13 is made into a corresponding cross sleeve structure, so that the motor fixing seat can be firmly inserted into the middle reinforcing plate and the upper and lower side plates of the fuselage and used Fastened with screws etc.

There is a connecting cross 5 fixed integrally with it at the front end of the motor fixing seat, and the upper and lower bars of the connecting cross bracket are longer to facilitate the installation of the rotating support 4.

As mentioned above, the rotating support is two parts of right angle structure, one side of the parts is fixed on the connecting cross, and the other side has a hole, and the rotating supporting ring 3 is installed through the pin shaft. The rotating supporting ring is a circular ring, and two pairs of mounting holes are arranged on the ring, up and down and left and right. The upper and lower pairs of mounting holes correspond to the rotating support, and the left and right pair of mounting holes correspond to the cross rotation bracket 16, and the installation mode of the cross rotation bracket and the rotation support ring is also a pin shaft. Brushless motor 2 is installed on the cross rotation support. After the brushless motor is installed, the propeller 1 is installed on the brushless motor shaft. In this way, the axis line of the brushless motor and the propeller can be deflected on the rotating support ring to form a change in the direction of the vector at the nose of the drone.

The connection between the left and right deflection steering gear and the rotating support ring, and the connection between the up and down deflection steering gear and the rotating bracket is realized through respective steering gear rocker arms 11 and ball joint rods 12 . Of course, there is also a universal ball joint 15 at both ends of the ball joint rod.

The power consumption of the brushless motor, each steering gear, flight control system, etc. is provided by the lithium battery. The lithium battery and corresponding accessories, as well as the remote control receiver and APM flight controller in the flight control system are also installed on the fuselage. The system is electrically connected to the left and right deflection steering gear and the up and down deflection steering gear, and the rest including the sliding wheels under the fuselage are the same as the existing fixed-wing model aircraft.

The APM flight controller is an existing aircraft model controller. It is equipped with a fixed-wing program, which can realize the self-stabilizing control of the aircraft and reduce the accident rate of the flight. It can also manually control and mobilize the motors for each steering gear through the remote controller on the ground Vector rotation, quickly and accurately pull the aircraft in different directions for each series of actions. The switch between delta wing mode and quad aileron mode is controlled by the two-stage switch of the ground remote controller. The main function of the ground station is to realize real-time monitoring and parameter adjustment of the overall flight status of the fixed-wing vector UAV through the data transmission module.

The program on the APM flight controller can be designed or adjusted by the user himself or entrusted by the relevant developer according to the specific needs.

Parameters such as fuselage, brushless motor of the present invention, and the power specification size of propeller are determined according to the textbook of existing aircraft design. The brushless motor in this example is Langyu 2814/1450Kv motor, and the propeller is 9060 propeller with a diameter of 9 inches, a pitch of 6 inches, and a reduction ratio of 0.6. The shape and size of the corresponding cross rotation bracket and rotation support ring are shown in Figure 4-8.

Through the test and measurement of the physical prototype made by the unit, the fixed-wing vector UAV of the present invention has stable flying attitude, fast flying speed, timely and accurate vector adjustment, small turning radius, and short take-off and gliding distance, and has been well received by relevant institutions.

Claims (9)

1. a kind of fixed-wing vector unmanned plane, it has fuselage, steering wheel, flight control system, propeller and brushless electric machine, it is characterised in that Fuselage is made up of wing plate and upper and lower fuselage side plate, and front fuselage is fixed with motor fixing seat, passes through rotation branch in motor fixing seat Frame installation rotation bracing ring, rotation bracing ring rotate around its longitudinal axis, and rotation bracing ring is built with cross runing rest, cross Brushless electric machine is installed in rotation, propeller is installed on brushless electric machine axle, installation deflection steering wheel deflects rudder with upper and lower in fuselage Machine, up and down deflection steering wheel and deflection steering wheel are connected with rotation bracing ring and cross runing rest respectively by ball-head tension rod, The deflection of propeller and brushless electric machine axial line is controlled, flight control system includes the remote control reception on remote controlled floor remote control, fuselage Machine and APM fly control device, and with deflection steering wheel and up and down, deflection tiller room electrically connects flight control system.

2. fixed-wing vector unmanned plane according to claim 1, it is characterised in that have middle reinforcing plate on fuselage.

3. fixed-wing vector unmanned plane according to claim 1, it is characterised in that motor fixing seat is that a cross fork is inserted, Sleeve is in middle reinforcing plate and upper and lower fuselage side plate.

4. fixed-wing vector unmanned plane according to claim 1, it is characterised in that have one between motor fixing seat and runing rest Individual connection cross.

5. fixed-wing vector unmanned plane according to claim 1, it is characterised in that runing rest is a pair of bracket of right angle type, directly Connection between angular support frame and rotation bracing ring connects for bearing pin.

6. fixed-wing vector unmanned plane according to claim 1, it is characterised in that between rotation bracing ring and cross runing rest Connected for bearing pin.

7. fixed-wing vector unmanned plane according to claim 1, it is characterised in that the ball-head tension rod of deflection steering wheel is set In the left and right sides of fuselage epipleural, the ball-head tension rod for deflecting steering wheel up and down is arranged on the both sides up and down of wing plate.

8. fixed-wing vector unmanned plane according to claim 1, it is characterised in that the rudder plate on wing plate has corresponding steering wheel to connect Connect.

9. according to one of the claim 1-8 fixed-wing vector unmanned planes, it is characterised in that underbelly is equipped with sliding wheel.