Single-seat electric multi-rotor ultra-light aircraft

Abstract

The invention discloses a single-seat electric multi-rotor ultra-light aircraft, and belongs to the field of ultra-light aircraft design. The fuselage is formed by welding a fuselage main structure with light high-strength hard aluminum alloy pipe beams and taking a large-range hollow light fuselage shell as a main body, the four sets of foldable coaxial double-paddle power supporting arms are arranged on the horizontal plane in the middle of the fuselage and symmetrically arranged front and back, and the skid type undercarriage is arranged at the bottom of the fuselage. The weight of an empty aircraft meets the weight requirement of an ultra-light aircraft, meanwhile, the main body adopts an aluminum alloy pipe beam welding structure, the cost is reduced, most drivers are located in a pipe frame structure, the gravity center of the whole aircraft is close to a rotor plane, and the driving experience is better.

Description

Technical Field

[0001] The invention relates to the field of ultralight aircraft design, in particular to a single-seat electric multi-rotor ultralight aircraft. Background Art

[0002] As a type of civil aircraft, ultralight aircraft mainly emphasizes safety, economy and comfort, and can be widely used in agriculture, forestry, animal husbandry, exploration, aerial photography, aviation sports and tourism. It is generally believed that the empty weight of a single-seat ultralight aircraft should not exceed 115 kilograms.

[0003] At present, most ultralight aircraft are fixed-wing aircraft and helicopters. Fixed-wing aircraft need a long runway for horizontal takeoff and landing, which limits their use. Most helicopters use fuel engines with large rotor diameters, which leads to obvious operating noise. In addition, the limited number of rotors makes it impossible to continue to operate when a single power fails. The rotor structure is complex and the maintenance cost is high. At the same time, with the development of electric aircraft in recent years, multi-rotor manned aircraft have been launched one after another, but most of them are heavy, which exceeds the use range of ultralight aircraft. In addition, the whole machine structure is complex, the system equipment is complex, and the price is high, which greatly limits their promotion and use among individual users. Most multi-rotor manned aircraft are mainly used for sightseeing and tourism. They do not have an on-board control and driving interface and no driving experience. At the same time, the rotors are mostly placed above or below the cockpit, the center of gravity is far away from the rotor plane, the maneuverability is low, and the driving experience and controllability are poor. Summary of the invention

[0004] The technical problem to be solved by the present invention is to provide a single-seat electric multi-rotor ultralight aircraft to reduce or avoid the above-mentioned problems.

[0005] In order to solve the above technical problems, the technical solution of the present invention is:

[0006] A single-seat electric multi-rotor ultralight aircraft comprises: a fuselage mainly composed of a lightweight and high-strength hard aluminum alloy tube beam welded fuselage main structure and a large-scale hollowed-out lightweight fuselage shell, four groups of foldable coaxial double-propeller power arms arranged symmetrically front and back on the horizontal plane in the middle of the fuselage, and a skid-type landing gear arranged at the bottom of the fuselage.

[0007] The empty weight of the aircraft meets the weight requirement of ultralight aircraft. At the same time, the main body adopts an aluminum alloy tube beam welded structure to reduce costs. Most of the pilot is located in the tube frame structure, and the center of gravity of the whole aircraft is close to the rotor plane, which provides a better driving experience.

[0008] Among them, four sets of foldable coaxial double-propeller power arms are connected to the fuselage by a root folding mechanism, connected by a fixed pin and a quick-release pin. The power arms can be quickly unfolded and folded by plugging and pulling out the quick-release pin, which is convenient for use, storage and transportation.

[0009] Power kits are set at the ends of four sets of foldable coaxial double-propeller power arms. There are eight power kits in total, each of which is equipped with a pair of coaxial reverse-propeller lift rotors. When a single rotor fails, emergency control is provided through the corresponding control strategy to ensure that the remaining power works together for a safe landing.

[0010] Among them, the front and rear parts of the fuselage are equipped with protruding beams to form a U-shaped protection structure, providing relatively safe structural protection for the pilot;

[0011] The fuselage is wrapped by a large-scale hollow lightweight fuselage shell, which can provide protection for key parts and reduce the drag of the whole machine while significantly reducing the weight of the whole machine. The front part of the fuselage is the equipment compartment, which is equipped with an equipment maintenance hatch for easy maintenance;

[0012] The cockpit is in the middle of the fuselage, with a multi-function touch screen in front, pedals in the front and bottom, a racing-grade lightweight seat and a five-point safety belt in the middle, a lightweight throttle lever on the left side of the front of both sides of the upper part of the cockpit, and a lightweight three-axis joystick on the right side;

[0013] Four parachute rope hanging points for the whole aircraft are set on the front and rear aluminum alloy tube beams on both sides of the upper part of the cockpit. The parachute ropes extend along the tube beams to the emergency whole aircraft parachute compartment at the rear part of the fuselage. A whole aircraft parachute ejection hatch is set above the parachute compartment. The whole aircraft parachute ejection hatch can automatically fall off due to the mechanical impact of the parachute when the parachute is ejected. In an emergency, the whole aircraft parachute can be quickly deployed at low altitude and low speed, reducing the landing speed of the whole aircraft and improving safety.

[0014] A push-pull replaceable power battery assembly is set under the front and rear seats. The side of the assembly is hollowed out to reduce weight and facilitate battery removal and installation. When removing and installing the battery, the battery assembly is fixed and removed by positioning quick-release pins combined with I-shaped slide rails. The structure is light and fast.

[0015] The skid-type landing gear is an aluminum alloy tube welded structure, consisting of two parallel left and right ground-connected tube beams that are bent upward and forward. The left and right tube beams are connected by two front and rear inverted U-shaped tube beams. The landing gear is fixed to the bottom of the fuselage frame by screws. It is light in weight and can raise the rotor plane to improve landing safety.

[0016] Beneficial effects of the present invention: The four groups of arms described in the present invention can be folded toward the inside of the fuselage through the folding mechanism at the root of the fuselage, so as to facilitate transportation and storage. The whole machine adopts a lightweight design concept to minimize the empty weight, reduce the complexity of maintenance, and reduce the cost of the whole machine. Through the analysis of the load characteristics of the aircraft layout and the division of functional areas, the main frame structure of the present invention adopts a lightweight and high-strength rigid fuselage main structure aluminum alloy welded frame 121 tube beam main structure. Its structural layout maximizes the optimization of the force transmission route of the whole machine, and reduces the weight of the whole machine structure while providing sufficient design strength and rigidity. Through aluminum alloy welding, the use of structural connectors is significantly reduced, further reducing the cost of the fuselage structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the overall layout of a single-seat electric multi-rotor ultralight aircraft in an embodiment of the present invention;

[0018] Figure 2 This is a schematic diagram of the folded state of the single-seat electric multi-rotor ultralight aircraft in an embodiment of the present invention;

[0019] Figure 3 This is a schematic diagram of the main frame structure of a single-seat electric multi-rotor ultralight aircraft in an embodiment of the present invention;

[0020] Figure 4 It is a schematic diagram of a lightweight fuselage shell of a single-seat electric multi-rotor ultralight aircraft in an embodiment of the present invention;

[0021] Figure 5 It is a schematic diagram of an exploded view of a folding mechanism of a support arm of a single-seat electric multi-rotor ultralight aircraft in an embodiment of the present invention;

[0022] Figure 6 It is a schematic diagram of the folding state of the support arm folding mechanism of the single-seat electric multi-rotor ultralight aircraft in an embodiment of the present invention;

[0023] Figure 7 This is a schematic diagram of the battery arrangement of a single-seat electric multi-rotor ultralight aircraft in an embodiment of the present invention;

[0024] Figure 8 The battery pack of the single-seat electric multi-rotor ultralight aircraft in the embodiment of the present invention is arranged with an explosion Figure 1 Schematic diagram;

[0025] Fig. 9 The battery pack of the single-seat electric multi-rotor ultralight aircraft in the embodiment of the present invention is arranged with an explosion Figure 2 Schematic diagram;

[0026] Fig.10 It is a schematic cross-sectional view of the battery arrangement of a single-seat electric multi-rotor ultralight aircraft in an embodiment of the present invention.

[0027] In the figure: fuselage 1, No. 1 arm 21, No. 2 arm 22, No. 3 arm 23, No. 4 arm 24, skid landing gear 3, fuselage shell 111, equipment maintenance hatch 112, whole aircraft parachute ejection hatch 113, right headlight 114, left headlight 115, front GPS antenna 116, front GPS antenna 117, fuselage main structure 12, throttle lever 14, three-axis joystick 15, racing-grade lightweight seat 16, five-point safety belt 17, whole aircraft parachute 181, right front parachute rope hanging point 182, left front parachute rope hanging point 183, right rear parachute rope hanging point 184, left rear parachute rope hanging point 185, front battery compartment 191, rear battery compartment 192, front fuselage No. 2 arm connecting assembly 122, No. 2 arm power kit fixing structure 2231 , No. 2 arm power kit upper motor 2232, No. 2 arm power kit lower motor 2233, No. 2 arm power kit upper rotor 2234, No. 2 arm power kit lower rotor 2235, fuselage main structure aluminum alloy welding frame 121, front fuselage No. 2 arm connecting assembly 122, front fuselage arm connecting carbon fiber tube 123, front fuselage No. 1 arm connecting assembly 124, rear fuselage No. 4 arm connecting assembly 125, rear fuselage arm connecting carbon fiber tube 126, rear fuselage No. 3 arm connecting assembly 127, No. 1 arm carbon fiber tube 211, No. 1 arm folding mechanism assembly 212, No. 2 arm carbon fiber tube 221, No. 2 arm folding mechanism assembly 222, No. 3 arm carbon fiber tube 231, No. 3 arm folding mechanism assembly 23 2. Carbon fiber tube of No. 4 arm 241, folding mechanism assembly of No. 4 arm 242, aluminum alloy clamp of No. 2 arm connection assembly of front fuselage 1221, aluminum tube connector of No. 2 arm connection assembly of front fuselage 1222, fixing pin of folding mechanism of No. 2 arm connection assembly of front fuselage 1223, quick-release pin of folding mechanism of No. 2 arm connection assembly of front fuselage 1224, fixing screws of aluminum tube connector of No. 2 arm connection assembly of front fuselage 1225-1, 1225-2, 1225-3, 1225-4, anti-slip bolt of aluminum alloy clamp of carbon fiber tube machine of front fuselage 1226, clamping bolts of aluminum alloy clamp of No. 2 arm connection assembly of front fuselage 1227, 1228, clamping nut of aluminum alloy clamp of No. 2 arm connection assembly of front fuselage 1229, 1230, front fuselage support arm connected to carbon fiber tube machine aluminum alloy clamp anti-drop nut 1231, front fuselage support arm connected to carbon fiber tube 123, No. 2 support arm carbon fiber tube 221, No. 2 support arm folding mechanism assembly aluminum alloy clamp 2221, No. 2 support arm folding mechanism assembly aluminum alloy clamp carbon fiber tube anti-drop bolt 2222, No. 2 support arm folding mechanism assembly aluminum alloy clamp carbon fiber tube anti-drop nut 2223, No. 2 support arm folding mechanism assembly aluminum alloy clamp clamping nut 2224, 2225, No. 2 support arm folding mechanism assembly aluminum alloy clamp clamping bolt 2226, 2227, front battery compartment 191, rear battery compartment 192, front battery compartment battery pack 11911, front battery compartment battery pack 21912, front battery compartment fuselage slide rail 11913,Front battery compartment fuselage slide rail 21914, front battery compartment quick release pin 11915-1, front battery compartment quick release pin 1 rubber pad 1915-2, front battery compartment quick release pin 21916-1, front battery compartment quick release pin 2 rubber pad 1916-2, rear battery compartment battery pack 3 1921, rear battery compartment battery pack 4 1922, rear battery compartment fuselage slide rail 11923, rear battery compartment fuselage slide rail 21924, front battery compartment fuselage slide rail 1 fixed block 1917, front battery compartment fuselage slide rail 2 fixed block 1918, front battery compartment battery pack 1 battery module 19111, front battery compartment battery pack 1 battery module slide rail 119112, front battery compartment battery pack 1 battery module slide rail 219113. DETAILED DESCRIPTION

[0028] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0029] Figure 1 The schematic diagram of the deployment state of the whole machine of the single-seat electric multi-rotor ultralight aircraft in the embodiment of the present invention is shown, and the single-seat electric multi-rotor ultralight aircraft comprises a fuselage 1, a No. 1 arm 21, a No. 2 arm 22, a No. 3 arm 23, a No. 4 arm 24, and a skid landing gear 3. Specifically, the rotor centers of the four groups of power arm No. 1 arm 21, No. 2 arm 22, No. 3 arm 23, and No. 4 arm 24 are arranged at the front and rear symmetrical positions of the horizontal plane in the middle of the fuselage 1, and the center of the diagonal line formed by them is close to the center of gravity of the whole machine, which improves the maneuverability of the aircraft while providing balanced power load distribution.

[0030] Specifically, the fuselage 1 includes a fuselage main structure 12 that can bear the load of the pilot located near the center of gravity and can transmit the lift load of four groups of power support arms, a lightweight large-area hollow fuselage shell 111 arranged around the fuselage main structure 12, an equipment maintenance hatch 112 located at the front of the fuselage, a whole machine parachute ejection hatch 113 located at the rear of the fuselage, a right headlight 114, a left headlight 115, a front GPS antenna 116, a front GPS antenna 117, and a throttle lever 111 arranged on the left side of the pilot. 4. A three-axis joystick 15 arranged on the right side of the pilot, a racing-grade lightweight seat 16 and its matching five-point safety belt 17 arranged in the middle of the main structure 12 of the fuselage, a whole-machine parachute 181 arranged at the rear of the fuselage, a right front parachute rope hanging point 182, a left front parachute rope hanging point 183, a right rear parachute rope hanging point 184, a left rear parachute rope hanging point 185, a front battery compartment 191 arranged at the lower front of the fuselage cockpit, and a rear battery compartment 192 arranged at the lower rear of the fuselage cockpit symmetrical to the front battery compartment 191. Specifically, through reasonable equipment layout, the center of gravity of the whole machine is basically coincident with the center of the rotor plane, ensuring the balance of power output and a good control experience.

[0031] Specifically, the middle part of the fuselage 1 is the cockpit, the front is a multi-function touch display screen, the front lower part is a foot pedal, and the middle part is provided with a racing-grade lightweight seat 16 and a five-point safety belt 17. The position of the racing-grade lightweight seat 16 basically coincides with the center of the rotor plane, and in order to cooperate with the pilot's posture during forward flight, the seat is provided with a larger rearward backrest tilt angle, thereby improving riding comfort.

[0032] Specifically, a lightweight throttle lever 14 is provided on the left side of the front of the cockpit, and the throttle lever is connected through the upper left pipe beam of the main fuselage structure 12, and the aircraft is lifted and lowered by pushing and pulling forward and backward. Specifically, a lightweight three-axis joystick 15 is provided on the right side of the front of the cockpit, and is connected through the upper right pipe beam of the main fuselage structure 12, and the aircraft pitch, roll and route are controlled by three-axis control.

[0033] Specifically, four parachute rope hanging points of the whole aircraft parachute 181 are arranged on the front and rear aluminum alloy tube beams on both sides of the upper part of the cockpit, namely the right front parachute rope hanging point 182, the left front parachute rope hanging point 183, the right rear parachute rope hanging point 184, and the left rear parachute rope hanging point 185. The parachute ropes extend along the tube beams to the emergency whole aircraft parachute compartment at the rear of the fuselage. A whole aircraft parachute ejection cabin cover 113 is arranged above the emergency whole aircraft parachute compartment. The whole aircraft parachute ejection cabin cover 113 can automatically fall off due to the mechanical impact of the whole aircraft parachute 181 when the whole aircraft parachute 181 is ejected. In an emergency, the whole aircraft parachute can be quickly deployed at low altitude and low speed, thereby reducing the grounding speed of the whole aircraft and improving safety.

[0034] Specifically, a push-pull type replaceable power battery assembly is arranged at the front and rear lower parts of the racing-grade lightweight seat 16, and the side body shell 111 of the replaceable power battery assembly is hollowed out to reduce the weight while facilitating the removal and installation of the battery.

[0035] Specifically, the skid-type landing gear 3 is an aluminum alloy tube welding structure, which is composed of two left and right parallel ground-connected tube beams that are bent and upturned front and back. The left and right tube beams are connected by two front and rear inverted U-shaped tube beams. The landing gear is fixed to the bottom of the fuselage 1 frame by screws. It is light in weight and can raise the rotor plane to improve landing safety.

[0036] Specifically, the No. 2 arm 22 and other arms are similar in composition and structure. Specifically, it includes the No. 2 arm power kit fixed structure 2231, the No. 2 arm power kit upper motor 2232, the No. 2 arm power kit lower motor 2233, the No. 2 arm power kit upper rotor 2234, and the No. 2 arm power kit lower rotor 2235. Specifically, the No. 2 arm power kit upper motor 2232 is combined with the No. 2 arm power kit upper rotor 2234, and the No. 2 arm power kit lower motor 2233 is combined with the No. 2 arm power kit lower rotor 2235. The two are coaxially installed above and below the No. 2 arm power kit fixed structure 2231, and the rotors rotate in opposite directions to offset the rotational torque. Specifically, the horizontal plane position of the No. 2 arm 22 is basically coincident with the center of gravity position, and at the same time, a safe distance is left between the rotor rotation plane and the ground to reduce the risk of the rotor touching the ground. The other arms are the same in composition and structure. Four sets of arm power kits form eight sets of power. When one of the power systems fails and stops, emergency control can be provided through the corresponding control strategy to ensure that the remaining power systems work together to land safely.

[0037] Specifically, Figure 2 The schematic diagram of the folding state of the single-seat electric multi-rotor ultralight aircraft in the embodiment of the present invention is shown. The four sets of arms can be folded toward the inside of the fuselage through the folding mechanism at the root of the fuselage, which is convenient for transportation and storage.

[0038] The whole machine adopts a lightweight design concept to minimize the empty weight, reduce maintenance complexity, and reduce the cost of the entire machine.

[0039] Specifically, Figure 3The main frame structure of the single-seat electric multi-rotor ultralight aircraft in the embodiment of the present invention is shown. The main frame structure of the single-seat electric multi-rotor ultralight aircraft includes a fuselage main structure aluminum alloy welded frame 121, a front fuselage No. 2 arm connection assembly 122, a front fuselage arm connection carbon fiber tube 123, a front fuselage No. 1 arm connection assembly 124, a rear fuselage No. 4 arm connection assembly 125, a rear fuselage arm connection carbon fiber tube 126, a rear fuselage No. 3 arm connection assembly 127, a No. 1 arm carbon fiber tube 211, a No. 1 arm folding mechanism assembly 212, a No. 2 arm carbon fiber tube 221, a No. 2 arm folding mechanism assembly 222, a No. 3 arm carbon fiber tube 231, a No. 3 arm folding mechanism assembly 232, a No. 4 arm carbon fiber tube 241, and a No. 4 arm folding mechanism assembly 242. The front part of the fuselage main structure aluminum alloy welded frame 121 is connected in sequence from left to right with No. 2 arm carbon fiber tube 221, No. 2 arm folding mechanism assembly 222, front fuselage No. 2 arm connecting assembly 122, front fuselage arm connecting carbon fiber tube 123, front fuselage No. 1 arm connecting assembly 124, No. 1 arm folding mechanism assembly 212, and No. 1 arm carbon fiber tube 211; the rear part is connected in sequence from left to right with No. 4 arm carbon fiber tube 241, No. 4 arm folding mechanism assembly 242, rear fuselage No. 4 arm connecting assembly 125, rear fuselage arm connecting carbon fiber tube 126, rear fuselage No. 3 arm connecting assembly 127, No. 3 arm folding mechanism assembly 232, and No. 3 arm carbon fiber tube 231;

[0040] Specifically, through the analysis of the load characteristics of the aircraft layout and the division of functional areas, the main frame structure adopts a lightweight, high-strength, rigid fuselage main structure aluminum alloy welded frame 121 tube beam main structure. Its structural layout maximizes the optimization of the whole machine's force transmission route, and reduces the weight of the whole machine structure while providing sufficient design strength and rigidity. Through aluminum alloy welding, the use of structural connectors is significantly reduced, further reducing the cost of the fuselage structure. The front and rear parts of the fuselage main structure aluminum alloy welded frame 121 are provided with protruding beams to form a U-shaped protection structure, providing relatively safe structural protection for the pilot. Specifically, the four groups of arms are all lightweight in design. The front fuselage arm connects the carbon fiber tube 123, the rear fuselage arm connects the carbon fiber tube 126, the No. 1 arm carbon fiber tube 211, the No. 2 arm carbon fiber tube 221, the No. 3 arm carbon fiber tube 231, and the No. 4 arm carbon fiber tube 241 are all lightweight, high-strength carbon fiber composite thin-walled round tubes, which can meet the use requirements of strong vibration environments, and are light in weight, simple in molding process, and reduce structural costs.

[0041] Figure 4The schematic diagram of the lightweight fuselage shell of a single-seat electric multi-rotor ultralight aircraft in an embodiment of the present invention is shown. Specifically, it includes a fuselage shell 111, an equipment maintenance hatch 112, a whole aircraft parachute ejection hatch 113, a right headlight 114, and a left headlight 115. Under the guidance of the lightweight design concept of the whole aircraft, in order to minimize the empty weight and reduce the cost of the whole aircraft. The fuselage shell 111 is formed by a large-scale hollow lightweight thin-wall carbon fiber foam sandwich process. Under the premise of ensuring the protection of key parts and the function of reducing the drag of the whole aircraft, the shell is cut significantly, a semi-open cockpit layout is adopted, and a large-scale hollow cutting is performed on the side of the fuselage to reduce the weight of the whole aircraft. The front part of the fuselage is provided with an equipment maintenance hatch 112 for easy maintenance, the rear part of the fuselage is provided with a whole aircraft parachute ejection hatch 113, and the nose is provided with a right headlight 114 and a left headlight 115 to provide dim environment lighting for the aircraft.

[0042] Figure 5 The exploded view of the unfolded state of the arm folding mechanism of a single-seat electric multi-rotor ultralight aircraft in an embodiment of the present invention is shown. The power arm is connected to the fuselage by a root folding mechanism, and is connected by a fixed pin and a quick-release pin. The power arm can be quickly unfolded and folded by plugging and pulling out the quick-release pin, which is convenient for use and storage and transportation; the No. 2 arm folding mechanism assembly 222 includes a front fuselage No. 2 arm connection assembly aluminum alloy clamp 1221, a front fuselage No. 2 arm connection assembly aluminum tube connector 1222, a front fuselage No. 2 arm connection assembly folding mechanism fixed pin 1223, a front fuselage No. 2 arm connection assembly folding mechanism quick-release pin 1224, a front fuselage No. 2 arm connection assembly aluminum tube connector fixing screws 1225-1, 1225-2, 1225-3, 1225-4, and a front fuselage arm connection carbon fiber tube machine aluminum alloy clamp Anti-slip bolt 1226, aluminum alloy clamp clamping bolt 1227, 1228 of front fuselage No. 2 arm connecting assembly, aluminum alloy clamp clamping nut 1229, 1230 of front fuselage No. 2 arm connecting assembly, aluminum alloy clamp clamp anti-slip nut 1231 of front fuselage arm connecting carbon fiber tube machine, aluminum alloy clamp 2221 of No. 2 arm folding mechanism assembly, aluminum alloy clamp carbon fiber tube anti-slip bolt 2222 of No. 2 arm folding mechanism assembly, aluminum alloy clamp carbon fiber tube anti-slip nut 2223 of No. 2 arm folding mechanism assembly, aluminum alloy clamp clamping nuts 2224, 2225 of No. 2 arm folding mechanism assembly, aluminum alloy clamp clamping bolts 2226, 2227 of No. 2 arm folding mechanism assembly.

[0043] Specifically, the fuselage main structure aluminum alloy welded frame 121 is connected above the front fuselage No. 2 arm connecting assembly aluminum alloy clamp 1221 through the front fuselage No. 2 arm connecting assembly aluminum tube connector 1222 and four groups of front fuselage No. 2 arm connecting assembly aluminum tube connector fixing screws 1225-1, 1225-2, 1225-3, and 1225-4 by snapping. Specifically, one end of the front fuselage arm connected carbon fiber tube 123 is sleeved in the front fuselage arm No. 2 connecting assembly aluminum alloy clamp 1221, and is positioned with the front fuselage arm No. 2 connecting assembly aluminum alloy clamp 1221 through the front fuselage arm connected carbon fiber tube machine aluminum alloy clamp anti-detachment bolt 1226 and the front fuselage arm connected carbon fiber tube machine aluminum alloy clamp anti-detachment nut 1231 to prevent axial and circumferential movement. At the same time, the front fuselage arm No. 2 connecting assembly aluminum alloy clamp clamping bolts 1227, 1228 and the front fuselage arm No. 2 connecting assembly aluminum alloy clamp clamping nuts 1229, 1230 are used to tighten the semi-open narrow groove of the front fuselage arm No. 2 connecting assembly aluminum alloy clamp 1221 so that it is clamped and fixed to the front fuselage arm connected carbon fiber tube 123. Specifically, one end of the No. 2 arm carbon fiber tube 221 and the No. 2 arm folding mechanism assembly aluminum alloy chuck 2221 are positioned by the No. 2 arm folding mechanism assembly aluminum alloy chuck carbon fiber tube anti-detachment bolt 2222 and the No. 2 arm folding mechanism assembly aluminum alloy chuck carbon fiber tube anti-detachment nut 2223 to prevent axial and circumferential movement. At the same time, the No. 2 arm folding mechanism assembly aluminum alloy chuck clamping nuts 2224, 2225 and the No. 2 arm folding mechanism assembly aluminum alloy chuck clamping bolts 2226, 2227 are tightened at the semi-open narrow groove of the No. 2 arm folding mechanism assembly aluminum alloy chuck 2221 to clamp it and fix it to the No. 2 arm carbon fiber tube 221. Specifically, in the realization of the folding function, the other end of the aluminum alloy clamp 1221 of the front fuselage No. 2 arm connection assembly and the other end of the aluminum alloy clamp 2221 of the No. 2 arm folding mechanism assembly are penetrated from top to bottom through the front fuselage No. 2 arm connection assembly folding mechanism fixing pin 1223 to realize the hinge on one side, so as to realize the vertical fixation and horizontal swing of the No. 2 arm. Figure 6 The schematic diagram of the folding state of the arm folding mechanism of a single-seat electric multi-rotor ultralight aircraft in an embodiment of the present invention is shown. The No. 2 arm is fixed by inserting the quick-release pin shaft 1224 of the No. 2 arm connection assembly folding mechanism of the front fuselage into the connection between the other end of the aluminum alloy clamp 1221 of the No. 2 arm connection assembly of the front fuselage on the other side and the other end of the aluminum alloy clamp 2221 of the No. 2 arm folding mechanism assembly. The concave-convex structure at the interface between the aluminum alloy clamp 1221 of the No. 2 arm connection assembly of the fuselage and the aluminum alloy clamp 2221 of the No. 2 arm folding mechanism assembly realizes reliable moment transmission. A square opening is provided at the interface of the folding mechanism to facilitate the passage of power cables and signal cables.

[0044] Specifically, Figure 7The schematic diagram of the battery pack layout of a single-seat electric multi-rotor ultralight aircraft in an embodiment of the present invention is shown. When removing and installing the battery, the battery assembly is fixed and removed by positioning the quick-release pins combined with the I-shaped slide rails, and the structure is light and fast. Specifically, the front battery compartment 191 and the rear battery compartment 192 are respectively located at the front and rear lower parts of the main structure aluminum alloy welded frame 121 of the fuselage. Specifically, Figure 8 The battery pack arrangement of the single-seat electric multi-rotor ultralight aircraft in the embodiment of the present invention is shown. Figure 1 Schematic diagram. The front battery compartment 191 includes a front battery compartment battery pack 11911, a front battery compartment battery pack 21912, a front battery compartment fuselage slide rail 11913, a front battery compartment fuselage slide rail 21914, a front battery compartment quick release pin 11915-1, a front battery compartment quick release pin 1 rubber pad 1915-2, a front battery compartment quick release pin 21916-1, and a front battery compartment quick release pin 2 rubber pad 1916-2. Specifically, the front battery compartment fuselage slide rail 11913 and the front battery compartment fuselage slide rail 21914 are transversely fixed in parallel to the front part of the fuselage main structure aluminum alloy welded frame 121, and the rear battery compartment fuselage slide rail 11923 and the rear battery compartment fuselage slide rail 21924 are transversely fixed to the rear part of the fuselage main structure aluminum alloy welded frame 121. Specifically, during the battery pack installation process, the front battery compartment battery pack 11911 and the front battery compartment battery pack 21912 slide into the fuselage through the front battery compartment fuselage slide rail 11913 and the front battery compartment fuselage slide rail 21914 in turn, and the positioning in the sliding direction is achieved by inserting the front battery compartment quick release pin 11915-1 and the front battery compartment quick release pin 21916-1 which are respectively perpendicular to the front battery compartment fuselage slide rail 11913 and the front battery compartment fuselage slide rail 21914 to achieve the positioning in the sliding direction. The rear battery compartment battery pack 31921 and the rear battery compartment battery pack 41922 are connected to the rear battery compartment fuselage slide rail 11923 and the rear battery compartment fuselage slide rail 21924 in the same manner. Specifically, Fig. 9 The battery pack arrangement of the single-seat electric multi-rotor ultralight aircraft in the embodiment of the present invention is shown. Figure 2 Schematic diagram, the end position of the sliding direction is controlled by the fixed block 1917 of the front battery compartment fuselage slide rail 1 and the fixed block 1918 of the front battery compartment fuselage slide rail 2. Specifically, the rubber pad 1915-2 of the front battery compartment quick release pin 1 and the rubber pad 1916-2 of the front battery compartment quick release pin 2 are elastic components, which can provide flexible control of the clamping of the gap between the quick release pin and the battery pack. Specifically, Fig.10 The schematic diagram of the cross-sectional view of the battery pack arrangement of the single-seat electric multi-rotor ultralight aircraft in an embodiment of the present invention is shown. The sliding mechanism mainly includes a front battery compartment battery pack 1 battery module slide rail 119112, a front battery compartment battery pack 1 battery module slide rail 2 19113, a front battery compartment fuselage slide rail 11913, and a front battery compartment fuselage slide rail 21914. The I-shaped cooperation of the two sets of slide rails realizes motion constraints other than the axial direction.

Claims

1. A single-seat electric multi-rotor ultralight aircraft, characterized in that: The empty weight of the aircraft meets the weight requirements of ultralight aircraft; it includes: a fuselage mainly composed of an aluminum alloy tube beam welded fuselage main structure and a large-scale hollowed-out lightweight fuselage shell, four sets of foldable coaxial double-propeller power arms arranged symmetrically in front and back on the horizontal plane in the middle of the fuselage, and a skid-type landing gear arranged at the bottom of the fuselage; Four sets of foldable coaxial twin-propeller power arms are connected to the fuselage by a root folding mechanism, and are connected by a fixed pin shaft and a quick-release pin. The power arms can be quickly unfolded and folded by plugging and pulling out the quick-release pins, which is convenient for use, storage and transportation. The ends of the four sets of foldable coaxial twin-propeller power arms are provided with power kits, with a total of eight sets of power kits. Each set is provided with a pair of coaxial reverse-propeller lift rotors. When a single rotor fails, emergency control is provided through the corresponding control strategy to ensure that the remaining power works together to land safely. The front and rear parts of the fuselage are equipped with protruding beams to form a U-shaped protection structure, providing relatively safe structural protection for the pilot; the fuselage is wrapped by a large-scale hollow lightweight fuselage shell, which can provide protection for key parts and reduce the drag of the whole machine while greatly reducing the weight of the whole machine. The front part of the fuselage is the equipment compartment, which is equipped with an equipment maintenance hatch for easy maintenance; the middle part of the fuselage is the cockpit, with a multi-function touch display in front, pedals in the front and lower part, a racing-grade lightweight seat and a five-point safety belt in the middle, a lightweight throttle lever on the left side of the front of the upper part of the cockpit, and a lightweight three-axis joystick on the right side; four The parachute rope hanging point of the whole aircraft extends along the tube beam to the emergency whole aircraft parachute compartment at the rear of the fuselage. The whole aircraft parachute ejection compartment cover is set above the parachute compartment. The whole aircraft parachute ejection compartment cover can automatically fall off due to the mechanical impact of the parachute when the parachute is ejected. In an emergency, the whole aircraft parachute can be quickly deployed at low altitude and low speed, reducing the grounding speed of the whole aircraft and improving safety; push-pull type replaceable power battery components are set at the front and rear lower parts of the front and rear seats, and the side of the fuselage shell of the component is hollowed out to reduce the weight and facilitate the removal and installation of the battery; when removing and installing the battery, the positioning quick release pin is combined with the I-shaped slide rail to achieve the fixation and removal of the battery component, and the structure is light and fast; The skid-type landing gear is an aluminum alloy tube welded structure, consisting of two parallel left and right ground-connected tube beams that are bent upward and forward. The left and right tube beams are connected by two front and rear inverted U-shaped tube beams. The landing gear is fixed to the bottom of the fuselage frame by screws. It is light in weight and can raise the rotor plane to improve landing safety.

2. A single-seat electric multi-rotor ultralight aircraft, characterized in that: The single-seat electric multi-rotor ultralight aircraft comprises a fuselage (1), a No. 1 support arm (21), a No. 2 support arm (22), a No. 3 support arm (23), a No. 4 support arm (24), and a skid landing gear (3); the centers of the four groups of power support arm rotors, namely, the No. 1 support arm (21), the No. 2 support arm (22), the No. 3 support arm (23), and the No. 4 support arm (24), are arranged at front and rear symmetrical positions on a horizontal plane in the middle of the fuselage (1), and the center of the diagonal line formed by them is close to the center of gravity of the whole aircraft; The fuselage (1) comprises a fuselage main structure (12) capable of bearing the load of a pilot located near the center of gravity and capable of transmitting the lift load of four groups of power support arms, a lightweight and large-area hollow fuselage shell (111) arranged around the fuselage main structure (12), an equipment maintenance hatch (112) located at the front of the fuselage, a whole-machine parachute ejection hatch (113) located at the rear of the fuselage, a right headlight (114), a left headlight (115), a front GPS antenna (116), a front GPS antenna (117), a throttle lever (14) arranged on the left side of the pilot, a three-axis joystick (15) arranged on the right side of the pilot, and a control lever (117) arranged on the fuselage. A racing-grade lightweight seat (16) and a matching five-point safety belt (17) in the middle of the main structure (12), a whole-machine parachute (181) arranged at the rear of the fuselage, a right front parachute rope hanging point (182), a left front parachute rope hanging point (183), a right rear parachute rope hanging point (184), a left rear parachute rope hanging point (185), a front battery compartment (191) arranged at the lower front of the fuselage cockpit, and a rear battery compartment (192) arranged at the lower rear of the fuselage cockpit symmetrically to the front battery compartment (191); through reasonable equipment arrangement, the center of gravity of the whole machine is basically coincident with the center of the rotor plane, thereby ensuring balanced power output and a good control experience; The middle part of the fuselage (1) is a cockpit, the front part is a multifunctional touch display screen, the front lower part is a foot pedal, and the middle part is provided with a racing-grade lightweight seat (16) and a five-point safety belt (17). The position of the racing-grade lightweight seat (16) is substantially coincident with the center of the rotor plane, and in order to match the pilot's posture during forward flight, the seat is provided with a large backrest tilt angle, thereby improving riding comfort; A lightweight throttle lever (14) is arranged on the left side of the front part of the cockpit, and the throttle lever is connected to the upper left pipe beam of the main fuselage structure (12), and the aircraft can be lifted and lowered by pushing and pulling forward and backward; a lightweight three-axis joystick (15) is arranged on the right side of the front part of the cockpit, and the joystick is connected to the upper right pipe beam of the main fuselage structure (12), and the aircraft can be manipulated in pitch, roll and route by three-axis manipulation; Four parachute rope hanging points of the whole aircraft parachute (181) are arranged on the front and rear aluminum alloy tube beams on both sides of the upper part of the cockpit, which are respectively a right front parachute rope hanging point (182), a left front parachute rope hanging point (183), a right rear parachute rope hanging point (184), and a left rear parachute rope hanging point (185). The parachute ropes extend along the tube beams to the emergency whole aircraft parachute compartment at the rear of the fuselage. A whole aircraft parachute ejection cabin cover (113) is arranged above the emergency whole aircraft parachute compartment. The whole aircraft parachute ejection cabin cover (113) can be automatically dropped due to the mechanical impact of the whole aircraft parachute (181) when the whole aircraft parachute (181) is ejected. In an emergency, the whole aircraft parachute can be quickly deployed at low altitude and low speed, reducing the grounding speed of the whole aircraft and improving safety. A push-pull type replaceable power battery assembly is arranged at the front and rear lower parts of the racing-grade lightweight seat (16), and the side body shell (111) of the replaceable power battery assembly is hollowed out to reduce the weight and facilitate the removal and installation of the battery; The skid-type landing gear (3) is an aluminum alloy tube welding structure, which is composed of two parallel left and right ground-connected tube beams that are bent and upturned. The left and right tube beams are connected by two front and rear inverted U-shaped tube beams. The landing gear is fixed to the bottom of the fuselage (1) frame by screws. It is light in weight and can raise the rotor plane to improve landing safety. The No. 2 support arm (22) includes a No. 2 support arm power kit fixing structure (2231), a No. 2 support arm power kit upper motor (2232), a No. 2 support arm power kit lower motor (2233), a No. 2 support arm power kit upper rotor (2234), and a No. 2 support arm power kit lower rotor (2235); the No. 2 support arm power kit upper motor (2232) and the No. 2 support arm power kit upper rotor (2234) are combined, and the No. 2 support arm power kit lower motor (2233) and the No. 2 support arm power kit lower rotor (2235) are combined. The two are coaxially installed above and below the No. 2 arm power kit fixed structure (2231), and the rotors rotate in opposite directions to offset the rotation torque; the horizontal plane position of the No. 2 arm (22) is basically coincident with the center of gravity position, and at the same time, a safe distance is left between the rotor rotation plane and the ground to reduce the risk of the rotor touching the ground, and the other arms have the same composition and structure; the four arm power kits form eight sets of power, and when one of the power systems fails and stops, emergency control can be provided through the corresponding control strategy to ensure that the remaining powers work together to land safely; The main frame structure of the single-seat electric multi-rotor ultralight aircraft comprises a fuselage main structure aluminum alloy welded frame (121), a front fuselage No. 2 arm connection assembly (122), a front fuselage arm connection carbon fiber tube (123), a front fuselage No. 1 arm connection assembly (124), a rear fuselage No. 4 arm connection assembly (125), a rear fuselage arm connection carbon fiber tube (126), a rear fuselage No. 3 arm connection assembly (127), a No. 1 arm carbon fiber tube (211), a No. 1 arm folding mechanism assembly (212), a No. 2 arm carbon fiber tube (221), a No. 2 arm folding mechanism assembly (222), a No. 3 arm carbon fiber tube (231), a No. 3 arm folding mechanism assembly (232), a No. 4 arm carbon fiber tube (241), and a No. 4 arm folding mechanism assembly (242); The front part of the fuselage main structure aluminum alloy welded frame (121) is connected in sequence from left to right with a No. 2 support arm carbon fiber tube (221), a No. 2 support arm folding mechanism assembly (222), a front fuselage No. 2 support arm connecting assembly (122), a front fuselage support arm connecting carbon fiber tube (123), a front fuselage No. 1 support arm connecting assembly (124), a No. 1 support arm folding mechanism assembly (212), and a No. 1 support arm carbon fiber tube (211); the rear part is connected in sequence from left to right with a No. 4 support arm carbon fiber tube (241), a No. 4 support arm folding mechanism assembly (242), a rear fuselage No. 4 support arm connecting assembly (125), a rear fuselage support arm connecting carbon fiber tube (126), a rear fuselage No. 3 support arm connecting assembly (127), a No. 3 support arm folding mechanism assembly (232), and a No. 3 support arm carbon fiber tube (231); The front and rear parts of the fuselage main structure aluminum alloy welded frame (121) are provided with protruding beams to form a U-shaped protection structure, providing relatively safe structural protection for the pilot; the front fuselage support arm connecting carbon fiber tube (123), the rear fuselage support arm connecting carbon fiber tube (126), the No. 1 support arm carbon fiber tube (211), the No. 2 support arm carbon fiber tube (221), the No. 3 support arm carbon fiber tube (231), and the No. 4 support arm carbon fiber tube (241) are all lightweight and high-strength carbon fiber composite material thin-walled round tubes; The fuselage shell (111) is formed by a large-scale hollowing out lightweight thin-wall carbon fiber foam sandwich process; under the premise of ensuring the protection of key parts and the function of reducing the drag of the whole machine, the shell is greatly cut, a semi-open cockpit layout is adopted, and the fuselage side is hollowed out in a large area to reduce the weight of the whole machine. The No. 2 arm folding mechanism assembly (222) comprises an aluminum alloy clamp (1221) of the front fuselage No. 2 arm connection assembly, an aluminum tube connection piece (1222) of the front fuselage No. 2 arm connection assembly, a fixing pin shaft (1223) of the folding mechanism of the front fuselage No. 2 arm connection assembly, a quick-release pin shaft (1224) of the folding mechanism of the front fuselage No. 2 arm connection assembly, fixing screws (1225-1, 1225-2, 1225-3, 1225-4) of the aluminum tube connection piece of the front fuselage No. 2 arm connection assembly, an aluminum alloy clamp anti-drop bolt (1226) of the front fuselage No. 2 arm connection assembly, and a clamping bolt (1227) of the aluminum alloy clamp of the front fuselage No. 2 arm connection assembly 1227, 1228), aluminum alloy chuck clamping nut (1229, 1230) of the front fuselage No. 2 support arm connection assembly, aluminum alloy chuck anti-dropping nut (1231) of the front fuselage support arm connecting carbon fiber tube machine, aluminum alloy chuck (2221) of the No. 2 support arm folding mechanism assembly, aluminum alloy chuck carbon fiber tube anti-dropping bolt (2222) of the No. 2 support arm folding mechanism assembly, aluminum alloy chuck carbon fiber tube anti-dropping nut (2223) of the No. 2 support arm folding mechanism assembly, aluminum alloy chuck clamping nut (2224, 2225) of the No. 2 support arm folding mechanism assembly, aluminum alloy chuck clamping bolt (2226, 2227) of the No. 2 support arm folding mechanism assembly; The fuselage main structure aluminum alloy welding frame (121) is connected to the front fuselage No. 2 support arm connection assembly aluminum alloy clamp (1221) through the front fuselage No. 2 support arm connection assembly aluminum tube connector (1222) and four groups of front fuselage No. 2 support arm connection assembly aluminum tube connector fixing screws (1225-1, 1225-2, 1225-3, 1225-4) by snapping; one end of the front fuselage support arm connection carbon fiber tube (123) is sleeved in the front fuselage No. 2 support arm connection assembly aluminum alloy clamp (1221), and is connected to the front fuselage No. 2 support arm connection assembly aluminum alloy clamp (1221) through the front fuselage support arm connection carbon fiber tube machine aluminum alloy clamp anti-drop bolt (1226), the front fuselage support arm connection carbon fiber tube machine aluminum alloy clamp The alloy chuck anti-slip nut (1231) is used for positioning to prevent axial and circumferential movement. At the same time, the aluminum alloy chuck clamping bolts (1227, 1228) of the front fuselage No. 2 support arm connection assembly and the aluminum alloy chuck clamping nuts (1229, 1230) of the front fuselage No. 2 support arm connection assembly are used to tighten the semi-open narrow slot of the aluminum alloy chuck (1221) of the front fuselage No. 2 support arm connection assembly so that it is clamped and fixed with the front fuselage support arm connecting carbon fiber tube (123); the No. 2 support arm carbon fiber tube (221) and one end of the No. 2 support arm folding mechanism assembly aluminum alloy chuck (2221) are connected by the No. 2 support arm folding mechanism assembly aluminum alloy chuck carbon fiber tube anti-slip bolts (2222) and the No. 2 support arm folding mechanism assembly aluminum alloy chuck carbon fiber tube anti-slip bolts (2222) The aluminum alloy clamp head carbon fiber tube anti-dropping nut (2223) of the No. 2 support arm folding mechanism assembly is used for positioning to prevent axial and circumferential movement. At the same time, the No. 2 support arm folding mechanism assembly aluminum alloy clamp head clamping nut (2224, 2225) and the No. 2 support arm folding mechanism assembly aluminum alloy clamp head clamping bolt (2226, 2227) are used to tighten the No. 2 support arm folding mechanism assembly aluminum alloy clamp head (2221) at the semi-open narrow slot so that it is clamped and fixed with the No. 2 support arm carbon fiber tube (221); in the realization of the folding function, the other end of the No. 2 support arm connection assembly aluminum alloy clamp head (1221) of the front fuselage and the other end of the No. 2 support arm folding mechanism assembly aluminum alloy clamp head (2221) are connected to the No. 2 support arm folding mechanism assembly aluminum alloy clamp head (2221) through the front fuselage No. 2 support arm connection assembly folding mechanism fixing pin The shaft (1223) penetrates from top to bottom to realize hinge connection on one side, thereby realizing vertical fixation and horizontal swing of the No. 2 arm; the No. 2 arm is fixed by inserting the quick-release pin shaft (1224) of the folding mechanism of the No. 2 arm connecting assembly of the front fuselage into the connection between the other end of the aluminum alloy clamp (1221) of the No. 2 arm connecting assembly of the front fuselage and the other end of the aluminum alloy clamp (2221) of the No. 2 arm folding mechanism assembly on the other side, thereby realizing the fixation of the No. 2 arm; the concave-convex structure at the butt joint surface between the aluminum alloy clamp (1221) of the No. 2 arm connecting assembly of the fuselage and the aluminum alloy clamp (2221) of the No. 2 arm folding mechanism assembly realizes reliable moment transmission; a square opening is provided at the butt joint surface of the folding mechanism to facilitate the passage of power cables and signal cables; The front battery compartment (191) and the rear battery compartment (192) are respectively located at the front and rear lower parts of the fuselage main structure aluminum alloy welded frame (121); the front battery compartment (191) comprises a front battery compartment battery pack 1 (1911), a front battery compartment battery pack 2 (1912), a front battery compartment fuselage slide rail 1 (1913), a front battery compartment fuselage slide rail 2 (1914), a front battery compartment quick release pin 1 (1915-1), a front battery compartment quick release pin 1 rubber pad (1915-2), a front battery compartment quick release pin 2 (1916-1), and a front battery compartment quick release pin 2 rubber pad (1916-2) The front battery compartment fuselage slide rail 1 (1913) and the front battery compartment fuselage slide rail 2 (1914) are transversely and parallelly fixed to the front part of the fuselage main structure aluminum alloy welding frame (121); the rear battery compartment fuselage slide rail 1 (1923) and the rear battery compartment fuselage slide rail 2 (1924) are transversely fixed to the rear part of the fuselage main structure aluminum alloy welding frame (121); the front battery compartment battery group 1 (1911) and the front battery compartment battery group 2 (1912) slide into the fuselage through the front battery compartment fuselage slide rail 1 (1913) and the front battery compartment fuselage slide rail 2 (1914) in sequence, so as to realize positioning except in the sliding direction. The positioning in the sliding direction is achieved by inserting the front battery compartment quick release pin 1 (1915-1) and the front battery compartment quick release pin 2 (1916-1) which are respectively perpendicular to the front battery compartment fuselage slide rail 1 (1913) and the front battery compartment fuselage slide rail 2 (1914). The connection structure of the rear battery compartment battery pack 3 (1921) and the rear battery compartment battery pack 4 (1922) is the same as that of the rear battery compartment fuselage slide rail 1 (1923) and the rear battery compartment fuselage slide rail 2 (1924). The end position in the sliding direction is determined by the fixed stopper (1917) of the front battery compartment fuselage slide rail 1 and the fixed stopper (1917) of the front battery compartment fuselage slide rail 2. The fixed block (1918) is controlled; the front battery compartment quick release pin 1 rubber pad (1915-2) and the front battery compartment quick release pin 2 rubber pad (1916-2) are elastic components that can provide flexible control of clamping for the gap between the quick release pin and the battery pack; the sliding mechanism mainly includes the front battery compartment battery pack 1 battery module slide rail 1 (19112), the front battery compartment battery pack 1 battery module slide rail 2 (19113), the front battery compartment fuselage slide rail 1 (1913), and the front battery compartment fuselage slide rail 2 (1914), and the I-shaped cooperation of the two sets of slide rails can realize the motion constraint except the axial direction.

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