Distributed power iron bird unmanned aerial vehicle for verifying vertical take-off and landing technology

Abstract

The utility model discloses a distributed power iron bird unmanned aerial vehicle for verifying a vertical take-off and landing technology. The distributed power iron bird unmanned aerial vehicle comprises a fuselage assembly, a rotor wing assembly and a tail assembly. The fuselage assembly is composed of an upper beam, a cross beam, a supporting rod and a loading plate, a light-weight and high-strength frame structure is formed, and avionics equipment, a battery and a balance weight are convenient to install and adjust. The rotor wing assembly is of a three-section truss structure, rotor wing arms are installed through adjustable fixing pieces, flexible deployment of the number and the length of the rotor wing arms and the positions of motors is supported, and motor bases with different inclination angles can be replaced. The tail assembly is composed of a tail cross rod and a tail vertical rod and is fixed to the fuselage through a connecting piece, and motor bases can be installed at the two ends of the tail cross rod. According to the utility model, through the modular design, the gravity center and the power system layout of the unmanned aerial vehicle can be quickly adjusted, vertical take-off and landing, hovering and low-speed flight tests are supported, and meanwhile, the test platform has the characteristics of convenience in disassembly and assembly and convenience in transportation, and an efficient and low-cost verification scheme is provided for the electric vertical take-off and landing aircraft.

Description

TECHNICAL FIELD

[0001] The utility model belongs to large -scale unmanned plane technical field especially, it is a multi rotor unmanned plane. BACKGROUND

[0002] In the research and development of electric vertical take-off and landing aircraft, early verification mainly relies on iron bird platform and prototype platform. The iron bird platform integrates system modules through the ground frame, has the advantages of efficient integration, safe testing and low cost, but cannot verify the complete performance in flight state. Although the prototype machine can fly, it has the problems of high cost, long manufacturing cycle and difficulty in adjusting the configuration design after solidification. For electric vertical take-off and landing aircraft, power, flight control, battery and other systems need to be coordinated in the vertical take-off and landing stage, and the safety risk is very high. The existing technology needs to rely on the iron bird platform for repeated testing and manufacture of multiple prototype machines for real flight iteration verification, resulting in a sharp increase in research and development cost and a prolonged cycle. Therefore, there is an urgent need for a test scheme that combines the rapid integration capability of the iron bird platform and the real flight verification advantage of the prototype machine to flexibly adjust the configuration design, reduce risk, improve iteration capability, verify efficiency and reduce research and development cost. CONTENT OF THE UTILITY MODEL

[0003] The utility model proposes a distributed power iron bird unmanned plane for verifying vertical take-off and landing technology for the verification demand of electric vertical take-off and landing aircraft vertical take-off and landing technology, and combines the advantages of iron bird platform and prototype platform to solve the defects of the prior art. The unmanned plane adopts a frame structure welded by aluminum square tubes and circular tubes, has the characteristics of efficient integration and low cost of the iron bird platform and the real flight test capability of the prototype machine: on the one hand, the metal frame body realizes the rapid layout and low-cost manufacturing of the avionics and power system; on the other hand, based on the restoration of power distribution according to the aircraft design principle, it supports real working condition testing of vertical take-off and landing, hovering and low-speed flight. At the same time, the frame structure is combined with adjustable fixing parts and replaceable motor seat design, which can flexibly adjust the position of the rotor arm, the installation angle of the power system and the center of gravity parameters, break through the limitations of traditional iron bird that cannot take off and fly, and the configuration of finished unmanned aircraft is solidified, significantly improve the adaptability to research and development models, support rapid configuration iteration, thereby reduce the verification cost and shorten the research and development cycle, and provide an efficient and low-cost vertical take-off and landing technology verification scheme for electric vertical take-off and landing aircraft.

[0004] The utility model discloses a technical scheme adopted is: a kind of distributed power iron bird unmanned aerial vehicle of verification vertical take-off and landing technology, including fuselage assembly, rotor assembly, tail assembly, fuselage assembly includes upper beam, multiple crossbeams are welded and installed in upper beam, multiple support rods, crossbeam and support rod constitute fuselage frame, multiple loading plates are riveted and installed on fuselage frame, horizontal bar is installed below first support rod, realize landing gear function, fuselage assembly upper installation rotor assembly, rotor assembly includes three truss structures by multiple groups of round pipes welding, using fixed part to install rotor arm on three truss structures, motor seat is installed on rotor arm, motor seat and rotor arm can be installed, disassembled, replaced, motor is installed on motor seat, and motor is provided with propeller. Upper beam rear end in fuselage assembly installation tail assembly, tail assembly is constituted by tail horizontal bar, tail vertical rod and motor seat, tail vertical rod and tail horizontal bar are welded and fixed, tail assembly is fixed with fuselage assembly by connecting piece, motor seat can be installed on tail horizontal bar.

[0005] The above-mentioned distributed power iron bird unmanned aerial vehicle for verifying vertical take-off and landing technology, multiple crossbeams in fuselage assembly, support rods and loading plates constitute multiple frame partitions, and multiple frame partitions can install avionics equipment, batteries and counterweights according to design requirements.

[0006] The above-mentioned distributed power iron bird unmanned aerial vehicle for verifying vertical take-off and landing technology, rotor assembly includes three truss structures welded by first pipe and third pipe, second pipe and third pipe, two first pipes below middle truss structure are welded and fixed with upper beam in fuselage assembly, first pipe outside is provided with notch, second pipe part in left segment and right segment truss structure is milled, to form milling section, second pipe milling section can be inserted into first pipe, and first pipe notch is fastened using fastener, to prevent three trusses from falling off or shifting, and the tightness of fastener can be adjusted, and three trusses can be repeatedly disassembled and assembled. Fixed part is used to fix rotor arm and two first and second pipes below three truss structures, the fixed part is composed of buckle, fixing sheet and nut suitable for fixing square pipe and round pipe, the position of rotor arm is adjusted by adjusting fixed part, different length of rotor arm can be replaced according to requirements, lower motor seat is fixed on rotor arm using pull rivet, and lower motor seat and upper motor seat are fixed using bolt and nut, and upper motor seat of different inclination angle can be replaced.

[0007] The above-mentioned distributed power iron bird unmanned aerial vehicle for verifying vertical take-off and landing technology, tail assembly includes tail vertical rod and tail horizontal bar, tail vertical rod and upper beam of fuselage are fixed by using L-shaped plate and bolt and nut, and are fixed by using angle code and bolt and nut, tail vertical rod and fuselage are installed with reinforcing plate, tail vertical rod is fixed with tail horizontal bar by welding, and motor seat can be installed at both ends of tail horizontal bar.

[0008] The utility model discloses a beneficial effect is, adopt the frame type fuselage structure, by aluminium alloy square tube welding. This frame structure provides the very convenient integrated environment for avionics equipment, communication line and subsystem, and the unmanned plane is easy to whole machine check, equipment replacement, whole machine maintenance and data acquisition, on the other hand provides the lightweight, high -strength frame body structure, makes it can carry out flight test. The number of rotor arms, length and motor position can be flexibly arranged by using the fixed part to fix the rotor arm, and the detachable motor seat is suitable for different models of motor, and the fuselage loading plate cooperates with the counterweight and can adjust the weight of the unmanned plane, adjusts the gravity center of unmanned plane, and the three -segment truss structure in the rotor assembly can be disassembled, convenient transportation, and the utility model provides efficient, low -cost vertical take -off and landing technology verification scheme for electric vertical take -off and landing aircraft. BRIEF DESCRIPTION OF DRAWINGS

[0009] The utility model is further illustrated below in connection with the drawings and examples.

[0010] Figure 1 It is the schematic diagram of the utility model;

[0011] Figure 2 It is the side view of the utility model;

[0012] Figure 3 It is the front view of the utility model;

[0013] Figure 4 It is the schematic diagram of the utility fixed part;

[0014] Figure 5 It is the schematic diagram of the utility motor seat;

[0015] In the drawing, 1 is fuselage assembly, 101 is upper beam, 102 is crossbeam, 103 is first support rod, 104 is middle beam, 105 is front beam, 106 is cross rod, 107 is first loading plate, 108 is second support rod, 109 is second loading plate, 110 is fixed plate, 2 is rotor assembly, 201 is second round pipe, 202 is third round pipe, 203 is first round pipe, 204 is rotor arm, 206 is fixed part, 207 is fastener, 3 is tail assembly, 301 is tail vertical rod, 302 is tail cross rod, 303 is first reinforcing plate, 304 is second reinforcing plate, 5 is motor seat, 501 is upper motor seat, 502 is lower motor seat. DETAILED DESCRIPTION

[0016] A kind of verification vertical take-off and landing technology distributed power iron bird unmanned aerial vehicle includes fuselage component 1, rotor component 2 and tail component 3, fuselage component 1 includes upper beam 101, the upper beam 101 is aluminum profile, the upper beam 101 is welded with multiple cross beams 102, the cross beam 102 is aluminum square tube, the upper beam 101 is installed second loading plate 109, the antenna is installed on the loading plate 109, first support rod 103 is welded below the upper beam 101, transverse rod 106 is welded on the first support rod 103, the transverse rod 106 realizes landing gear function, second support rod 108 is welded on the upper beam 101, front beam 105 and middle beam 104 are welded below the first support rod 103 and second support rod 108, first loading plate 107 is fixed using rivet on the front beam 105, fixed plate 110 is installed on the front beam 105 and first support rod 103, multiple second support rods 108 are installed between the middle beam 104 and upper beam 101, multiple second support rods 108 divide the upper beam 101, middle beam 104 and first support rod 103 into multiple groups of partition frames, first loading plate 107 is arranged in multiple groups of partition frames, first loading plate 107 installed on the front beam 105 can place counterweight, multiple first loading plates 107 installed on the middle beam 104 can place battery, avionics equipment and counterweight respectively. In rotor component, first circular tube 203 and third circular tube 202 are welded to constitute middle section truss, two first circular tubes 203 are welded and installed below middle section truss and upper beam 101, the both ends of first circular tube 203 are provided with cutout, second circular tube 201 and third square tube 202 are welded to constitute left and right two section truss structures, the part of second circular tube 201 close to port end is milled to form milling section, the milling section of second circular tube 201 can be inserted into first circular tube 203, fastener 207 is installed at the cutout of first circular tube 203, fastener 207 fastens first circular tube 203 and second circular tube 201, to prevent three section trusses from falling off or displacement, three section trusses can be repeatedly disassembled. Fixed piece 206 is used to fix rotor arm 204 and first and second circular tubes below three section truss structures, the fixed piece 206 is composed of buckle and fixed sheet and nut suitable for square tube and circular tube fixation with thread. By adjusting fastener 207, left section and right section truss structures can be disassembled, different length truss structures can be replaced, left section and right section truss length can be flexibly adjusted, motor arm 204 position can be adjusted by adjusting fixed piece 206, different length motor arm 204 can also be replaced, lower motor base 502 is fixed with rotor arm 204 by rivet, upper motor base 501 is fixed with lower motor base 502 by bolt and nut. At the same time, upper motor base 501 with different inclination angles is also replaced, to realize flexible arrangement of power system, adapt to test model structure, and obtain more accurate test data.The tail assembly includes a tail vertical pole 301 and a tail horizontal pole 302, the tail vertical pole 301 and the tail horizontal pole 302 are aluminum profiles, the tail vertical pole 301 and the upper beam 101 of the machine body are fixed by using an L-shaped plate and a bolt and a nut, and are fixed by using an angle code and a bolt and a nut, the tail vertical pole 301 and the support pole 103 are provided with a first reinforcing plate 303, the tail vertical pole 301 is fixed with the tail horizontal pole 302 by welding, the tail vertical pole 301 is welded with a second reinforcing plate 304, and the tail horizontal pole 302 is provided with a motor seat 5 at both ends.

Claims

1. A VTOL distributed power iron bird drone comprising a fuselage assembly, a rotor assembly and a tail assembly, characterized in that, In the fuselage assembly, a plurality of first and second support rods are installed between the upper beam and the middle beam and the front beam, and a plurality of loading plates are installed on the front beam and the middle beam; the upper beam is welded with a first circular tube, the first circular tube is welded with a third circular tube to form a truss structure, a second circular tube is welded with the third circular tube to form a truss structure, and the second circular tube can be inserted into the first circular tube; the left and right trusses are used with a fixing member to install a rotor arm, and the rotor arm is installed with a motor seat; the upper beam is installed with a tail vertical rod, the tail vertical rod is welded with a tail horizontal rod, and the tail horizontal rod is installed with a motor seat.

2. The distributed powered iron bird drone of the vertical take-off and landing technology for verification according to claim 1, characterized in that, The first circular tube is provided with a cutout, and the second circular tube milling section can be inserted into the first circular tube, and the first circular tube cutout is fixed using fasteners.

3. The distributed powered iron bird drone of the vertical take-off and landing technology for verification according to claim 1, characterized in that, The rotor arm is fixed with the second circular tube or the first circular tube through the fixing member.

4. The distributed powered iron bird drone verifying the VTOL technology according to claim 1, wherein, The lower motor seat is fixedly installed with the rotor arm, and the upper motor seat is fixed with the lower motor seat using bolts and nuts.

5. The distributed powered iron bird drone verifying the VTOL technology according to claim 1, wherein, The tail vertical rod is installed with a first reinforcing plate.

6. The distributed powered iron bird drone verifying the VTOL technology according to claim 1, wherein, The loading plate is installed with an antenna, a battery, avionics and a counterweight.

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