Tandem wing UAV with vertical take-off and landing

Abstract

The invention relates to the technical field of unmanned aerial vehicles, and in particular to a tandem-wing unmanned aerial vehicle for vertical take-off and landing, comprising a fuselage, a front wing, a rear wing, a propeller assembly and a vertical tail, wherein the propeller assembly comprises a propulsion propeller assembly and a take-off and landing propeller assembly, wherein the propulsion propeller assembly is arranged at the rear of the fuselage, a reinforcement assembly is arranged at the fuselage, the reinforcement assembly comprises two longitudinal rods symmetrically distributed about the center of the fuselage, and a transverse rod between the two longitudinal rods, the take-off and landing propeller assembly is arranged at the junction of the longitudinal rods and the transverse rods, the front end of the longitudinal rods extends to the bottom of the front wing, the front part of the longitudinal rods is connected to the front wing, the rear part of the longitudinal rods extends to the bottom of the rear wing, the rear part of the longitudinal rods is connected to the rear wing, a front wing reinforcement rod is arranged in the front wing, the front part of the longitudinal rods is connected to the front wing reinforcement rod, the rear wing is arranged in the rear wing, and the rear part of the longitudinal rods is connected to the rear wing reinforcement rod. The unmanned aerial vehicle has sufficient rigidity and good fall resistance, greatly reduces the loss after falling, and greatly improves the endurance.

Description

Technical Field

[0001] The invention relates to the technical field of unmanned aerial vehicles, and in particular to a tandem-wing unmanned aerial vehicle capable of vertical take-off and landing. Background Art

[0002] A drone is an unmanned aerial vehicle that is controlled by a radio remote control device and a self-contained program control device. It is widely used in surveying and mapping, aerial photography, agriculture, express delivery, disaster relief and other fields. Currently, drone technology is developing rapidly.

[0003] Drones can be divided into fixed-wing drones and rotary-wing drones based on the type of aircraft. The advantages of fixed-wing drones are: longer flight time, faster speed, high flight efficiency, and the ability to soar after losing power, reducing the descent speed and reducing crash losses. The disadvantages are that they require a dedicated open area for takeoff and landing, and cannot hover, and have high requirements for the operator's operating skills. The advantage of rotary-wing drones is that they are easier to control accurately, and stable hovering is an innate advantage. The disadvantage is that the flight efficiency is low and the endurance time is short. Different types of aircraft have different advantages. In order to meet the increasingly urgent use needs, people combine fixed-wing drones and rotary-wing drones to design fixed-wing vertical take-off and landing drones, which have the advantages of both fixed-wing drones and rotary-wing drones.

[0004] With the rapid development and widespread application of drone technology, people have more and more demands for the use of drones. Among them, the most urgent demand for the use of drones is high flight time, high endurance, and high mount. Although fixed-wing vertical take-off and landing drones have relatively comprehensive advantages, their endurance, mount capacity, and flight performance still have a lot of room for improvement. In order to extend the flight time of drones, enhance the endurance of drones and improve the mount capacity, the general practice is to increase the capacity of the drone's battery and replace it with a larger capacity battery, which brings new problems. The battery with large capacity is also large in mass. When the battery capacity increases, the weight of the drone also increases. Therefore, this method has a great limitation on the improvement of drone performance. When the battery capacity is expanded to a certain range, it will have an adverse effect on the performance of the drone, reduce the endurance and mount capacity, and greatly affect the performance of the drone, making it difficult to meet the demand. The weight of the drone is the "dead weight". The greater the "dead weight", the more prominent the impact on the drone's mount capacity and endurance.

[0005] In order to further improve the performance of UAVs, the approach currently adopted is to optimize the structure of UAVs, for example, adopt lightweight design to reduce "dead weight". Lightweight design will cause new problems. The rigidity of UAVs is insufficient. After an accidental drop or crash, UAVs are generally seriously damaged and suffer large losses. There is another problem with existing fixed-wing vertical take-off and landing UAVs. The propeller assembly of the vertical take-off and landing UAV generates large resistance when the UAV is flying level, and the turbulence generated will have an adverse effect on the fuselage and fixed wing, reducing the lift of the fixed wing. Summary of the invention

[0006] The technical problem to be solved by the present invention is to provide a vertical take-off and landing tandem-wing UAV in response to the above-mentioned defects. The UAV has sufficient rigidity, a stable structure, good fall resistance, greatly reduces the loss after the crash, has low resistance, and greatly improves the endurance, which can better meet the use requirements.

[0007] The technical solution adopted by the present invention to solve the technical problem is as follows:

[0008] A tandem-wing UAV for vertical take-off and landing comprises a fuselage, a front wing, a rear wing, a propeller assembly and a vertical tail on the fuselage, wherein the height of the front wing is lower than the height of the rear wing, the propeller assembly comprises a propulsion propeller assembly for propelling the UAV forward and a take-off and landing propeller assembly for realizing vertical take-off and landing of the UAV, the propulsion propeller assembly is arranged at the tail of the fuselage, the center line of the propulsion propeller assembly coincides with the center line of the fuselage, a reinforcement assembly for strengthening the overall rigidity of the UAV is arranged on the outer periphery of the fuselage, the reinforcement assembly comprises longitudinal rods arranged along the front-to-back direction of the fuselage and evenly distributed on the left and right sides of the fuselage, and transverse rods arranged along the left-to-right direction of the fuselage, the transverse rod body intersects and connects with the longitudinal rod The transverse rods intersect and the rod bodies at the intersection are connected to each other. The take-off and landing propeller assembly is arranged at the intersection of the longitudinal rod and the transverse rod. The number of the take-off and landing propeller assemblies on the longitudinal rods on both sides of the fuselage is the same. The height of the take-off and landing propeller assembly is higher than the front wing and lower than the rear wing. A front wing reinforcement rod arranged along the length direction of the front wing is provided in the front wing. The front end of the longitudinal rod extends at least to the bottom of the front wing. The front rod body of the longitudinal rod is connected to the front wing reinforcement rod. A rear wing reinforcement rod arranged along the length direction of the rear wing is provided in the rear wing. The rear end of the longitudinal rod extends at least to the bottom of the rear wing. The rear rod body of the longitudinal rod is connected to the rear wing reinforcement rod. The vertical tail is connected to the rear end of the longitudinal rod.

[0009] Furthermore, the number of the longitudinal rods and the transverse rods are both two, and both of them are located on the bottom side of the machine body. The two longitudinal rods are symmetrical about the center line of the machine body, and the two ends of the transverse rods are respectively connected to the rod bodies at the corresponding positions of the longitudinal rods. The middle parts of the rod bodies of the two transverse rods intersect at the machine body, and the intersection of the transverse rods is connected at the bottom of the machine body.

[0010] Furthermore, the take-off and landing propeller assembly is disposed on the longitudinal rod in a left-right symmetrical distribution with respect to the center line of the fuselage.

[0011] Furthermore, the front end of the longitudinal rod extends to the bottom of the front wing, and the front end of the longitudinal rod is connected to the front wing reinforcement rod through a front connecting piece extending upward, and the rear end of the longitudinal rod extends to the bottom of the rear wing, and the rear end of the longitudinal rod is connected to the rear wing reinforcement rod through a rear connecting piece extending upward.

[0012] Furthermore, the front wing includes a front inner wing and a front outer wing outside the front inner wing, the front inner wing is an integral structure formed integrally with the fuselage, the front inner wing and the front outer wing are connected by a front wing connecting piece, and the front wing reinforcement rod is connected to the front wing connecting piece.

[0013] Furthermore, the rear wing includes a rear inner wing and a rear outer wing outside the rear inner wing, the rear inner wing is an integral structure formed integrally with the fuselage, the rear inner wing and the rear outer wing are connected by a rear wing connecting piece, and the rear wing reinforcement rod is connected to the rear wing connecting piece.

[0014] Furthermore, the longitudinal rod is connected to a support rod extending toward the bottom of the body.

[0015] Furthermore, the longitudinal rod is a metal square tube, and the transverse rod is a metal round tube.

[0016] Furthermore, the longitudinal rods and the transverse rods are connected at their junctions by a connecting piece, and the intersection of the transverse rod bodies is located in the middle of the fuselage between the front wing and the rear wing.

[0017] Furthermore, the longitudinal rods and transverse rods are in the same horizontal plane.

[0018] Furthermore, the height of the take-off and landing propeller assembly is higher than the front wing and lower than the rear wing.

[0019] The beneficial effects of the present invention are: by adopting the above scheme,

[0020] 1. It can take off and land vertically, has low requirements on the site and operators, and is easy to use;

[0021] 2. The overall rigidity of the drone is sufficient, and it has the advantages of both fixed-wing drones and rotary-wing drones. It is easy to control the flight, and the flight control is more stable. The performance of the drone is greatly improved. The "protective bar"-like reinforced structure can protect the drone from damage after it falls, protect the important components in the body, and greatly reduce the loss of the crash;

[0022] 3. The turbulence generated by the take-off and landing propeller assembly will not affect the rear wing, reducing the flight resistance of the drone. The drone has a better aerodynamic layout, and the endurance is increased by 30%-40%, which improves the performance of the drone.

[0023] 4. Multiple take-off and landing propeller assemblies are fixed on a reinforced structure with a stable structure, so that the UAV has better controllability. Through the individual control of the take-off and landing propeller assemblies, the UAV can be better stabilized, and the UAV can be rescued from out of control and prevented from crashing, which greatly improves the safety of UAV use. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The foregoing and other objects, features and advantages of the present invention will become more apparent from the following detailed description taken in conjunction with the accompanying drawings.

[0025] Figure 1 The figure is a schematic structural diagram of an embodiment of the present invention.

[0026] Figure 2 A bottom view of an embodiment of the present invention.

[0027] Figure 3 A side view of an embodiment of the present invention.

[0028] Figure 4 It is a side view of the fitting parts of the front wing, the take-off and landing propeller assembly, and the rear wing in one embodiment of the present invention.

[0029] Figure 5 It is a schematic diagram of a reinforcement structure in an embodiment of the present invention.

[0030] Figure 6 It is a schematic diagram of the structure of the fuselage, front wing and rear wing in one embodiment of the present invention.

[0031] Figure 7 The figure is a schematic diagram of the connection structure between the longitudinal rod and the front outer wing and the rear outer wing in one embodiment of the present invention.

[0032] Figure 8 The figure is a schematic diagram of the connection structure between the longitudinal rod and the body in one embodiment of the present invention.

[0033] Fig. 9 The figure is a schematic diagram of the local structure of the connection between the front wing connecting member and the longitudinal rod in one embodiment of the present invention.

[0034] Fig.10 The figure is a schematic diagram of the local structure of the connection between the rear wing connecting member and the longitudinal rod in one embodiment of the present invention.

[0035] Fig.11 This is a schematic diagram of the structure of Example 2 of the present invention.

[0036] Fig.12 It is a schematic diagram of the local structure of the longitudinal rod in Example 3 of the present invention.

[0037] Fig.13Schematic diagram of the connection structure between the longitudinal rod and the transverse rod in Example 4 of the present invention.

[0038] Among them: 1 is the fuselage, 2 is the front wing, 21 is the front inner wing, 22 is the front outer wing, 23 is the front wing connecting piece, 24 is the front outer wing reinforcement rod, 3 is the rear wing, 31 is the rear inner wing, 32 is the rear outer wing, 33 is the rear wing connecting piece, 34 is the rear outer wing reinforcement rod, 4 is the vertical tail, 5 is the propulsion propeller assembly, 51 is the take-off and landing propeller assembly, 6 is the longitudinal rod, 61 is the front connecting piece, 62 is the rear connecting piece, 7 is the transverse rod, 71 is the connecting sleeve rod, 8 is the front wing reinforcement rod, 9 is the rear wing reinforcement rod, and 10 is the support rod. DETAILED DESCRIPTION

[0039] The present invention will be further described below in conjunction with the accompanying drawings.

[0040] Example 1: Reference Figure 1-Figure 4A tandem wing UAV for vertical take-off and landing comprises a fuselage 1, a front wing 2, a rear wing 3, a propeller assembly and a vertical tail 4 on the fuselage 1, the front wing 2 is located at the front end of the fuselage 1, the rear wing 3 is located at the rear end of the fuselage 1, the height of the front wing 2 is lower than the height of the rear wing 3, the length of the front wing 2 is smaller than the length of the rear wing 3, the tandem wing structure composed of the front wing and the rear wing enables the UAV to have a relatively good lift, the front wing does not produce airflow influence on the rear wing, the resistance of the UAV in flight is reduced, and the UAV has a longer endurance, two metal longitudinal rods 6 are arranged on both sides of the fuselage 1 along the front and rear directions of the fuselage, the two longitudinal rods 6 are symmetrically distributed about the center of the fuselage 1, two metal transverse rods 7 are arranged between the two longitudinal rods 6, and the two transverse rods The end of 7 is provided with a connecting sleeve rod 71 connecting the longitudinal rod, the inner end of the connecting sleeve rod 71 is sleeved and connected to the end of the transverse rod, and the other end of the connecting sleeve rod 71 is connected to the longitudinal rod, and the rod bodies of the transverse rods 7 intersect in the middle, and the intersection is connected by the intersection connecting sleeve rod, the intersection of the rod bodies of the transverse rods is in the middle of the body between the front wing and the rear wing, and the transverse rods and the longitudinal rods are in the same horizontal plane. Preferably, the longitudinal rods and the transverse rods are on the bottom side of the body, and the intersection of the transverse rod bodies is embedded in the bottom of the body, and the corresponding bottom of the body is provided with an intersection groove matching the intersection of the transverse rods. The metal longitudinal rods and transverse rods have relatively reliable rigidity, and the longitudinal rods and the transverse rods form a relatively rigid "protective bar" structure for reinforcement on the outside of the bottom of the body. The protective bar protects the fuselage in the protective space it forms. When the UAV collides or falls accidentally, the protective bar can prevent the fuselage from suffering direct impact, and then play a relatively reliable protective role for the fuselage, effectively protecting the relatively expensive flight control components installed in the fuselage from slot impact, improving safety, and greatly reducing the losses caused by collisions or falls. The UAV's drop resistance, fall resistance and collision resistance are greatly improved. The longitudinal rod and the transverse rod are in a horizontal plane at the bottom of the fuselage. When the UAV is in flight, the windward surface of the protective bar is small and the resistance generated is small. On the premise of providing rigidity and protection, the impact on the resistance of the UAV is reduced, and the impact on the endurance of the UAV is minimized. In other words, under the same machine conditions, Under the conditions of parts and use environment, compared with the existing drones, the present drone has sufficient rigidity and small resistance, which not only directly improves the effect of anti-falling, but also directly prolongs the flight time, thereby improving the performance of the drone. The connection point between the transverse rod and the longitudinal rod is preferably located at the third division of the longitudinal rod, and the intersection of the transverse rod is located at the center of the fuselage between the front wing and the rear wing, so that the center of gravity of the protective bar coincides with the center of gravity of the drone, thereby stabilizing the center of gravity of the drone and promoting the improvement of the performance of the drone. The protective bar structure is located on the bottom side of the fuselage, which makes the center of gravity of the drone lower, so that after the drone loses control, the bottom of the fuselage contacts the obstacle first, thereby improving the protection of the bottom of the fuselage, giving full play to the protection function, and reducing the loss of the drone.

[0041] The front end of the longitudinal rod 6 extends to the bottom of the front wing 2, and the front end of the longitudinal rod 6 is connected to the front wing 2 by extending the front connecting piece 61 toward the upper part of the fuselage. The rear end of the longitudinal rod 6 extends to the bottom of the rear wing 3, and the rear end of the longitudinal rod 6 is connected to the rear wing 3 by extending the rear connecting piece 62 upward. The longitudinal rod covers the front side of the UAV to the rear side of the UAV, with a wide coverage range and a large area, which provides better protection for the UAV body. At the same time, the longitudinal rod is connected to the front wing and the rear wing to form a bottom support. On the one hand, the protection bar structure is more closely connected to the UAV, thereby improving the overall stability and protection of the protection bar. On the other hand, the protection bar structure supports the bottom of the wing, strengthens the load resistance of the front wing and the rear wing, improves the strength of the front wing and the rear wing, improves the lift of the UAV, and improves the UAV. The flight performance and control performance are improved, which promotes the improvement of the UAV's mounting capacity and the improvement of the UAV's performance. In addition, the impact on the protective bar structure can be transmitted to the wing, and the damage to the wing can be used to buffer and absorb the huge impact energy. The damage to the wing can be used to buffer the impact on the protective bar mechanism and the impact on the fuselage, so that the UAV has a dual protection mechanism of rigid protection of the protective bar + self-damage unloading force, which further improves the protection of the fuselage, has better drop resistance, better maintains the integrity of the fuselage, and effectively avoids damage to the fuselage and the flight control components in the fuselage. The longitudinal rod and the transverse rod are at the bottom of the fuselage, and the interference airflow generated will not have an adverse effect on the fuselage, which leads to small resistance during flight, improves the flight performance of the UAV, and improves the endurance of the UAV.

[0042] The propeller assembly includes a propulsion propeller assembly 5 for propelling the UAV forward, and four take-off and landing propeller assemblies 51 for controlling the UAV to take off and land vertically. The propulsion propeller assembly 5 includes a propulsion propeller and a propulsion motor for driving the propulsion propeller to rotate. The take-off and landing propeller assembly 51 includes a take-off and landing propeller and a take-off and landing motor for driving the take-off and landing propeller to rotate. The propulsion propeller assembly 5 is arranged at the tail of the fuselage 1, and the propulsion motor base of the propulsion propeller assembly is installed at the tail of the fuselage. The center line of the propulsion propeller assembly 5 coincides with the center line of the fuselage 1. The propulsion propeller assembly 5 pushes the UAV forward at the tail of the fuselage. To realize the flight of the UAV, the base of the take-off and landing motor of the take-off and landing propeller assembly 51 is fixed on the longitudinal rod, and the distribution positions of the four take-off and landing propeller assemblies on the two longitudinal rods correspond to each other. The positions of the take-off and landing propeller assemblies on both sides are symmetrical about the center of the body, so that the center of gravity of the UAV is at the center, which is convenient for controlling the posture of the UAV and improving the maneuverability of the UAV. The UAV can take off and land vertically, reducing and eliminating the restrictions on the use site and the restrictions on the operator, and improving the use performance of the UAV. The base of the take-off and landing motor is fixed on the longitudinal rod at the connecting sleeve rod, and the base of the take-off and landing motor is connected and fixed On the connecting sleeve rod, the connecting sleeve rod is the junction of the longitudinal rod and the transverse rod, and the support at this place is better. The take-off and landing propeller assembly is supported by the longitudinal rod and the transverse rod, making the take-off and landing propeller assembly more stable, thereby improving the flight stability of the drone during take-off and landing. The height of the take-off and landing propeller is higher than the height of the front wing and lower than the height of the rear wing. This structure ensures that when the drone is in level flight, the interfering airflow generated by the take-off and landing propeller assembly will not affect the rear wing, and the take-off and landing propeller assembly will not have an adverse effect on the drone's level flight, thereby reducing the resistance of the drone during flight, improving flight performance, and further The endurance of the UAV is extended, so that the endurance of the UAV is greatly enhanced under the same mount and condition, and the endurance is increased by 30%-40%, which greatly improves the operation capability of the UAV. The setting structure of the take-off and landing propeller assembly is reasonable and does not affect the level flight of the UAV. The two transverse rods intersect in the middle of the fuselage between the front wing and the rear wing and coincide with the center of the fuselage. The setting of the take-off and landing propeller assembly makes the overall center of gravity of the UAV in the middle of the fuselage. This structure makes the structure of the UAV stable. During vertical take-off and landing, the posture of the UAV is stable, and the impact on the aircraft performance during take-off and landing is greatly reduced.

[0043] The take-off and landing propeller assembly is fixed on the longitudinal rod, that is, the take-off and landing propeller assembly is fixed on the protective bar structure with a stable structure. Since the protective bar structure has sufficient rigidity, the role of the four take-off and landing propeller assemblies can be fully exerted. When the flight attitude of the UAV is out of control, the four take-off and landing propeller assemblies can be used to rescue the UAV in time. The four take-off and landing propeller assemblies cooperate with the reinforced structure, so that the UAV has the characteristics of a multi-axis rotor UAV, can rescue the UAV in time, stabilize the fuselage, avoid falling, and improve the safety of the use of the UAV.

[0044] Reference Figure 5 , Figure 6 The front wing 2 includes a front inner wing 21 and a front outer wing 22 outside the front inner wing 21. The front inner wing 21 is an integral structure formed integrally with the body 1. The front inner wing 21 and the front outer wing 22 are connected by a front wing connecting member 23. Figure 8 The front wing connecting piece 23 is an injection molded part. The cross-sectional structure of the front wing connecting piece 23 is consistent with the cross-sectional structure of the front wing. Connecting cavities are provided on both sides of the front wing connecting piece 23. The ends of the front inner wing 21 and the front outer wing 22 are correspondingly inserted into the connecting cavities to achieve connection with the front wing connecting piece. The connection is then bonded with an adhesive or fixed with connecting screws. A front wing reinforcement rod 8 arranged along the length direction of the front wing 2 is provided inside the front inner wing 21. The ends of the front wing reinforcement rod 8 pass through the front wing connecting piece and extend to the inside of the front outer wing 22. Correspondingly, a front embedded cavity 24 that cooperates with the front wing reinforcement rod is provided at the same position inside the front inner wing 21 and the front outer wing 22. A matching front wing connection 23 is provided at a corresponding position. The front wing reinforcement rod 8 is connected with the matching hole of the front wing reinforcement rod 8. On the one hand, the front wing reinforcement rod 8 is convenient for the assembly and splicing of the split front wing, improves the matching accuracy, and improves the reliability of the connection between the front inner wing 21, the front outer wing 22 and the front wing connecting piece. On the other hand, as a skeleton, it supports the front wing internally, improves the rigidity of the front wing, allows the front wing to withstand greater pressure, and improves the flight performance of the UAV. At the same time, the front wing reinforcement rod is connected to the front connecting piece 61, so that the front wing reinforcement rod is connected to the reinforcement structure, and the front wing reinforcement rod forms a part of the protective bar structure. The rear wing 3 includes a rear inner wing 31 and a rear outer wing 32 outside the rear inner wing 31. The rear inner wing 31 is an integrated structure integrally formed with the body 1. Fig. 9 The rear inner wing 31 and the rear outer wing 32 are connected by a rear wing connecting piece 33. The two sides of the rear wing connecting piece 33 are respectively provided with connecting cavities for connecting the rear inner wing 31 and the rear outer wing 32. The ends of the rear inner wing 31 and the rear outer wing 32 are correspondingly inserted into the connecting cavities of the rear wing connecting piece 33, and then bonded by an adhesive or fixed by screws. The cross-sectional structure of the rear wing connecting piece 33 is consistent with the cross-sectional structure of the rear wing. The interior of the rear inner wing 32 is provided with a rear wing reinforcement rod 9 arranged along its length direction. The rear wing reinforcement rod 9 is provided in a rear wing reinforcement rod 9 arranged along its length direction. The two ends of the rod 9 respectively pass through the rear connecting piece and extend to the inside of the rear outer wing 32. Correspondingly, the rear inner wing 31 and the rear outer wing 32 are provided with a rear embedding cavity 34 for setting the rear wing reinforcement rod. The corresponding part of the rear wing connection is provided with a matching hole for matching the rear wing reinforcement rod, so as to strengthen the structure of the rear wing, improve the pressure bearing capacity of the rear wing, and improve the flight performance of the UAV. At the same time, the rear wing reinforcement rod serves as a supporting skeleton of the rear wing, which is convenient for splicing the rear wing and maintaining the shape of the rear wing. The rear wing reinforcement rod is connected to the rear connecting piece. Figure 4The rear wing reinforcement rod, the front wing reinforcement rod, the longitudinal rod and the transverse rod form a closed "protective bar" structure outside the fuselage, which reliably protects the fuselage inside, can effectively resist impact, protect the fuselage from damage, and achieve the purpose of protecting the fuselage and the flight control components, so that the UAV has a relatively good anti-fall performance. The front inner wing and the rear inner wing are an integrated structure with the fuselage and are located inside the reinforcement structure. This structure is convenient for the production, assembly, transportation and storage of the UAV. More importantly, it improves the protection of the UAV by wing collapse when the collision occurs. The front outer wing and the rear outer wing on the outside of the reinforcement structure collapse when the collision occurs. This part is detachably connected to the front wing connector or the rear wing connector, and is a replaceable component with low cost. It can be damaged and can be replaced after damage. The local damage buffers most of the impact to achieve the purpose of protecting the fuselage, so that the UAV has a good anti-fall performance. After the crash, the fuselage and the flight control components in the fuselage are not damaged, reducing the loss and reducing the cost of using the UAV.

[0045] In order to enhance the load-bearing capacity of the front outer wing and the rear outer wing during flight, refer to Figure 7 A front outer wing support rod 24 is provided inside the front outer wing 21, and the front outer wing support rod 24 is arranged along the length direction of the front outer wing 21. The inner end of the front outer wing support rod 24 is connected to the front wing connecting piece 23. In order to better cooperate with the front wing reinforcement rod, the front outer wing support rod 24 is arranged at the bottom of the rod body where the front wing reinforcement rod is inside the front outer wing, and the front outer wing support rod 24 is provided with an arc groove that matches the front wing reinforcement rod. The tight structure of the two promotes to reduce space occupancy, reduce the volume of the front outer wing, improve the rigidity and load resistance of the front outer wing, and ensure the maneuverability of the UAV. A rear outer wing support rod 34 is provided inside the rear outer wing 31, and the rear outer wing support rod 44 is arranged along the length direction of the rear outer wing 31. The inner end of the rear outer wing support rod 34 is connected to the rear wing connecting piece 33, and the rear outer wing support rod is arranged at the bottom of the rod body where the rear wing reinforcement rod is inside the rear outer wing. The rear outer wing support rod is provided with an arc groove that matches the rear wing reinforcement rod, which improves the rigidity and load resistance of the rear outer wing and ensures the maneuverability of the UAV.

[0046] The vertical tail 4 is connected to the rear end of the longitudinal rod 6, and the longitudinal rod 6 is connected to a support rod 10 extending to the bottom of the fuselage. The support rod 10 forms a support frame for supporting the UAV. When the UAV is placed on the bottom, the fuselage maintains a certain distance from the bottom to protect the fuselage, and a downwardly protruding protective frame is formed to resist the impact from the bottom of the fuselage when the drone falls, thereby protecting the fuselage.

[0047] The longitudinal rod 6 is made of a metal pipe with a square cross section, and the transverse rod is made of a metal pipe with a circular cross section. The square metal pipe is rigid enough to meet the rigid reinforcement requirements in the front and rear directions of the UAV, and the front collision area is small, which reduces resistance. The circular transverse rod can reduce resistance and extend the endurance of the UAV.

[0048] Example 2: Reference Fig.10 The difference between this embodiment and embodiment 1 is that the front end of the longitudinal rod 6 extends to the front side of the front wing 2, the front part of the longitudinal rod 6 is connected to the front wing reinforcement rod 8 in the front wing 2 through the front connecting piece 61, the rear end of the longitudinal rod 6 extends to the rear side of the rear wing 3, and the rear rod body of the longitudinal rod 6 is connected to the rear wing reinforcement rod 9 in the rear wing 2 through the rear connecting piece. The front end and the rear end of the longitudinal rod are respectively located at the front side and the rear side of the body. On the one hand, it can protect the nose and the tail and expand the buffer space of the nose and the tail. On the other hand, it can adjust the overall center of gravity of the UAV, which helps to improve the controllability of the UAV.

[0049] Example 3: Reference Fig.11 The difference between this embodiment and embodiment 1 is that an upper longitudinal rod 101 is provided at the same vertical position above the fuselage, the upper longitudinal rod 101 is connected to the longitudinal rod 6 by a vertical connecting rod 102, an upper transverse rod 103 is provided between the rod bodies of the upper longitudinal rod 101, the end of the upper transverse rod 103 is connected to the upper longitudinal rod 101, the rod bodies of the upper transverse rod 103 intersect and are connected at the intersection, the take-off and landing propeller assembly is between the upper longitudinal rod and the lower longitudinal rod, and the take-off and landing propeller assembly is also protected, the upper longitudinal rod 101, the upper transverse rod 103, the longitudinal rod 6, the transverse rod 7, and the connecting rod 102 constitute a frame-type protective structure surrounding the outside of the fuselage, and an anti-collision beam is formed on the outside of the outer fuselage, which provides all-round protection for the fuselage, can effectively protect the fuselage from impact, improve the anti-fall ability, and reduce the loss of the crash.

[0050] Embodiment 4: The difference between this embodiment and embodiment 1 is that, referring to Fig.12 The transverse rod 7 is placed horizontally between the two longitudinal rods 6. The rod bodies of the transverse rod 7 are parallel to each other. The ends of the transverse rods can extend to the outside of the longitudinal rods. The middle rod body of the transverse rod 7 is connected to the bottom of the body, which expands the coverage area of ​​the transverse rod, increases the protection area of ​​the protective bar structure, and improves the safety of the use of the drone.

[0051] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any form. Any simple modification or equivalent changes made to the above embodiments based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. A tandem-wing UAV for vertical take-off and landing, comprising a fuselage, a front wing, a rear wing, a propeller assembly and a vertical tail on the fuselage, wherein the height of the front wing is lower than the height of the rear wing, and the propeller assembly comprises a propulsion propeller assembly for propelling the UAV forward and a take-off and landing propeller assembly for realizing vertical take-off and landing of the UAV, characterized in that: The propulsion propeller assembly is arranged at the tail of the fuselage, and the center line of the propulsion propeller assembly coincides with the center line of the fuselage. The outer periphery of the fuselage is provided with a reinforcement assembly for strengthening the overall rigidity of the UAV. The reinforcement assembly includes longitudinal rods arranged along the front and rear directions of the fuselage and evenly distributed on the left and right sides of the fuselage, and transverse rods arranged along the left and right directions of the fuselage. The transverse rod bodies intersect and are connected with the longitudinal rods, and the transverse rods intersect and the rod bodies at the intersections are connected to each other. The take-off and landing propeller assembly is arranged at the intersection of the longitudinal rods and the transverse rods. The number of take-off and landing propeller assemblies on the longitudinal rods on both sides of the body is the same, the height of the take-off and landing propeller assemblies is higher than the front wing and lower than the rear wing, the front wing is provided with a front wing reinforcement rod arranged along the length direction of the front wing, the front end of the longitudinal rod at least extends to the bottom of the front wing, the front rod body of the longitudinal rod is connected to the front wing reinforcement rod, the rear wing is provided with a rear wing reinforcement rod arranged along the length direction of the rear wing, the rear end of the longitudinal rod at least extends to the bottom of the rear wing, the rear rod body of the longitudinal rod is connected to the rear wing reinforcement rod, and the vertical tail is connected to the rear end of the longitudinal rod; The number of the longitudinal rods and the number of the transverse rods are both two, and both of them are located at the bottom side of the machine body. The two longitudinal rods are symmetrical about the center line of the machine body. The two ends of the transverse rods are respectively connected to the rod bodies at the corresponding positions of the longitudinal rods. The middle parts of the rod bodies of the two transverse rods intersect at the machine body, and the intersection of the transverse rods is connected at the bottom of the machine body. The front end of the longitudinal rod extends to the bottom of the front wing, the front end of the longitudinal rod is connected to the front wing reinforcement rod through a front connecting piece extending upward, the rear end of the longitudinal rod extends to the bottom of the rear wing, and the rear end of the longitudinal rod is connected to the rear wing reinforcement rod through a rear connecting piece extending upward; The front wing comprises a front inner wing and a front outer wing outside the front inner wing. The front inner wing is an integral structure formed integrally with the fuselage. The front inner wing and the front outer wing are connected by a front wing connecting piece. The front wing reinforcement rod is connected to the front wing connecting piece.

2. The vertical take-off and landing tandem-wing UAV according to claim 1, characterized in that: The position of the take-off and landing propeller assembly on the longitudinal rod is symmetrically distributed with respect to the center line of the fuselage.

3. The vertical take-off and landing tandem-wing UAV according to claim 1, characterized in that: The rear wing comprises a rear inner wing and a rear outer wing outside the rear inner wing, the rear inner wing is an integral structure formed integrally with the fuselage, the rear inner wing and the rear outer wing are connected by a rear wing connecting piece, and the rear wing reinforcement rod is connected to the rear wing connecting piece.

4. The vertical take-off and landing tandem-wing UAV according to claim 1, characterized in that: The longitudinal rod is connected with a supporting rod extending toward the bottom of the machine body.

5. The vertical take-off and landing tandem-wing UAV according to claim 1, characterized in that: The longitudinal rod is a metal square tube, and the transverse rod is a metal round tube.

6. The vertical take-off and landing tandem-wing UAV according to claim 1, characterized in that: The longitudinal rod and the transverse rod are connected by a connecting piece, and the intersection of the transverse rod bodies is located in the middle of the body between the front wing and the rear wing.

7. The vertical take-off and landing tandem-wing UAV according to claim 1, characterized in that: The longitudinal rods and transverse rods are in the same horizontal plane.

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