Unmanned Aerial Vehicle System with Separable Compound Wings for Vertical Takeoff

Abstract

The present invention belongs to the technical field of unmanned aerial vehicles, and discloses a detachable composite wing vertical take-off unmanned aerial vehicle system, including a body and a rotor unmanned aerial vehicle, a fixed wing is fixedly installed on the side of the body, a card slot is provided on the bottom surface of the fixed wing and the body, and a pushing mechanism is fixedly installed on the top surface of the rotor unmanned aerial vehicle. The present invention utilizes the card rod in the lifting mechanism to be sleeved with the card slot, so that the fixed-wing unmanned aerial vehicle is vertically lifted to a high altitude by utilizing the start and vertical rise of the rotor unmanned aerial vehicle, and the fixed-wing unmanned aerial vehicle is started in the high altitude and the rotor unmanned aerial vehicle is turned off at the same time, so that the fixed-wing unmanned aerial vehicle and the rotor unmanned aerial vehicle are separated at the same time, thereby getting rid of the dependence on the take-off track and the take-off auxiliary device in the case of a poor take-off environment, realizing vertical take-off in situ, the actual take-off and lift-off are stable, and the rotor unmanned aerial vehicle is easy to be recycled for vertical take-off after landing, which greatly increases the take-off adaptability.

Description

Technical Field

[0001] The present invention belongs to the technical field of unmanned aerial vehicles, and specifically relates to an unmanned aerial vehicle system with a detachable compound wing for vertical takeoff. Background Art

[0002] An unmanned aerial vehicle, abbreviated as "UAV" and with the English abbreviation "UAV", is an unpiloted aircraft that is controlled by a radio remote control device and a self - contained program control device, or is completely or intermittently autonomously operated by an on - vehicle computer. UAVs can be divided into military and civilian applications according to their application fields.

[0003] In the existing UAV systems, for a compound - wing (vertical takeoff) UAV system, hereinafter simply referred to as a vertical - takeoff UAV, its takeoff methods mainly include four types: catapult takeoff, ejection takeoff, runway takeoff, and rocket - assisted takeoff. Among the above four methods, catapult takeoff is only applicable to small or ultra - small UAVs, ejection takeoff relies on an ejection device, runway takeoff requires a runway that meets the requirements, and the rockets used in rocket - assisted takeoff have many restrictions during transportation and use (mainly in terms of safety). When the takeoff environment is poor and there is a lack of necessary takeoff runways and auxiliary equipment, it is difficult to achieve a stable and convenient vertical takeoff method, and the above four methods all have certain limitations, being overly dependent on environmental conditions and having poor practical effects.

[0004] In addition, in the existing UAV systems, after the vertical takeoff operation is completed and the UAV lands, due to limited landing environments, there are two landing methods: land landing and water landing. Usually, an airbag is added at the bottom of the UAV to ensure a stable floating effect during water landing. However, due to the poor stability of the floating airbag itself in the inflated state, when there are sharp objects at the land landing site, it is easy to cause the spare floating airbag to be punctured and leaked. When the inflated floating airbag ruptures, the floating airbag needs to be replaced, which actually increases the replacement frequency and the input cost, and the practical effect is not good. Summary of the Invention

[0005] The purpose of the present invention is to provide an unmanned aerial vehicle system with a detachable compound wing for vertical takeoff, so as to solve the problems raised in the above - mentioned background art.

[0006] To achieve the above object, the present invention provides the following technical solution: a separable composite-wing vertical takeoff UAV system, including an airframe and a rotor UAV. A fixed wing is fixedly installed on the side of the airframe. Card slots are provided on both the bottom surface of the fixed wing and the airframe. A pushing mechanism is fixedly installed on the top surface of the rotor UAV. A lifting mechanism is movably installed on the top surface of the pushing mechanism. The lifting mechanism includes a loop, a clamping rod, a sleeve rod, a sealing plate, a connecting rod, and a shielding ring. The clamping rod is fixedly connected to the top surface of the loop. The outer surface of the clamping rod is movably sleeved with the card slot. The sleeve rod is fixedly connected to the bottom surface of the loop. The sleeve rod is movably sleeved inside the pushing mechanism. A first control transceiver is fixedly installed on the bottom surface of the airframe. An inductor is fixedly installed on the bottom surface of the first control transceiver. The rotor UAV includes a rotor airframe, a cross, rotors, a base, and a second control transceiver. The rotor UAV is located directly below the airframe. The cross is fixedly installed on the top surface of the rotor airframe. The rotors are located on the top surface of the cross. A distribution sleeve is fixedly installed on the top surface of the cross. An air pump is fixedly installed on the top surface of the distribution sleeve. A first pipe is fixedly connected and communicated between the air pump and the distribution sleeve. A second pipe is fixedly connected and communicated between the distribution sleeve and the pushing mechanism.

[0007] First Embodiment: As Figure 1 , Figure 2 , Figure 3 and Figure 4 shown, before vertical takeoff, place the airframe of the fixed-wing UAV on top of the rotor UAV, and add a lifting mechanism to the top of the rotor UAV, so that the clamping rod in the lifting mechanism is sleeved with the card slots at the bottom of the airframe and the fixed wing. Start the air pump, so that the air pump ventilates the distribution sleeve through the first pipe, and passes the gas into the fixed sleeve of the pushing mechanism through the second pipe. As the sleeve rod in the fixed sleeve rises, the lifting mechanism further rises, causing the airframe of the fixed-wing UAV above the lifting mechanism to rise. During vertical takeoff, start the rotor UAV, so that the rotors in the rotor UAV rotate, and the rotor UAV gradually rises and vertically lifts the fixed-wing UAV. When the fixed-wing UAV and the rotor UAV reach a certain speed and height, the engine in the airframe of the fixed-wing UAV starts, and it begins to fly relying on its own power. At the same time, the power of the rotor UAV is turned off, and the air pump is turned off at the same time, so that the lifting mechanism quickly descends, so that the clamping rod in the lifting mechanism quickly disengages from the card slot, and the rotor UAV automatically disengages from the airframe of the fixed-wing UAV. After disengagement, the fixed-wing UAV continues to fly until landing or recovery. After the rotor UAV disengages, it starts the rotors again and lands.

[0008] First, by opening clamping grooves on the fuselage of the fixed-wing UAV and at the bottom of the fixed wing, adding a pushing mechanism to the top of the rotary-wing UAV, and movably installing a lifting mechanism at the top of the pushing mechanism, the clamping rod in the lifting mechanism is sleeved with the clamping groove, so that the fixed-wing UAV is vertically lifted to a high altitude by the startup and vertical ascent of the rotary-wing UAV. By starting the fixed-wing UAV at high altitude and simultaneously turning off the rotary-wing UAV, the fixed-wing UAV and the rotary-wing UAV are separated. Thus, in the case of poor takeoff environment, the dependence on the takeoff track and takeoff assistor is eliminated, realizing vertical takeoff in place, with stable actual takeoff and ascent, and the rotary-wing UAV is convenient to be recycled for vertical takeoff after landing, greatly increasing the takeoff adaptability.

[0009] Preferably, the connecting rod is fixedly connected to the inner side surface of the loop, the outer surface of the shielding ring is fixedly connected to the connecting rod, and the shielding ring is located outside the first control transceiver. By using the position induction between the shielding ring and the sensor, the separation information is accurately obtained. When the sensor cannot sense the shielding ring, it indicates that the fixed-wing UAV and the rotary-wing UAV have completed separation, and the separation information is accurately obtained at high altitude.

[0010] Preferably, the pushing mechanism includes a fixed sleeve, a threaded sleeve, a spring and an air outlet pipe. The fixed sleeve is fixedly connected to the top surface of the cross, the outer surface of the threaded sleeve is threadedly sleeved on the top of the fixed sleeve, the bottom surface of the threaded sleeve is fixedly connected to the spring, the air outlet pipe is fixedly communicated with the outer surface of the fixed sleeve, the inner surface of the threaded sleeve is movably sleeved with a sleeve rod, the sealing plate is fixedly connected to the bottom surface of the sleeve rod, the top surface of the sleeve rod is fixedly connected to the spring, and the sealing plate is sleeved inside the fixed sleeve. By movably installing the pushing mechanism and the lifting mechanism, the lifting mechanism is lifted to a certain height during takeoff, and when separation is required, the position of the lifting mechanism is quickly lowered, thereby improving the separation effect between the fixed-wing UAV and the rotary-wing UAV.

[0011] Preferably, the number of the fixed sleeves is four, and the four fixed sleeves are annularly distributed at equal intervals on the top surface of the cross, and the outer surface of the fixed sleeve is fixedly communicated with the second pipe.

[0012] Preferably, an inner hole is opened on the top surface of the cross, a control mechanism is arranged on the inner surface of the inner hole, a curved hole is opened inside the cross, the curved hole is communicated with the inner hole, and the inner hole is communicated with the distribution sleeve. By using the curved hole, the air in the distribution sleeve is introduced into the curved pipe, thereby realizing the inflation of the floating airbag.

[0013] Preferably, the control mechanism includes a sealing ring, a notch, an intermediate plate, and a telescopic rod. The sealing ring is sleeved inside the inner hole and the distribution sleeve. The intermediate plate is fixedly connected to the inner surface of the sealing ring. The telescopic rod is fixedly installed on the top surface of the rotor body and is located inside the inner hole. The top surface of the telescopic rod is fixedly connected to the intermediate plate. The notch is formed on the outer surface of the sealing ring and is located on one side of the first pipe. By moving the sealing ring up and down, the air supply direction of the air pump is changed, and the notch ensures that the air pump can always supply gas into the distribution sleeve during the switching adjustment, ensuring stable air supply.

[0014] Preferably, a curved pipe is fixedly connected to the bottom surface of the cross. The upper end of the curved pipe communicates with the curved hole. A floating airbag is fixedly installed on the bottom surface of the rotor UAV. The side surface of the floating airbag is fixedly communicated with the curved pipe. By temporarily inflating the floating airbag with an air pump, the inflation of the floating airbag is completed only when landing on the water surface is required, avoiding cutting the inflated spare floating airbag during land landing, improving the service life, and applying to different landing situations.

[0015] Preferably, the base is fixedly installed on the bottom surface of the rotor body, the second control transceiver is fixedly installed inside the rotor body, and the bottom surface of the rotor body is fixedly installed with the floating airbag. By using the second control transceiver and the first control transceiver, the control of the rotor UAV and the fixed-wing UAV is respectively realized, and combined with the control system on the ground, accurate vertical takeoff and landing control is completed.

[0016] Second Embodiment: As shown in Figure 1 、 Figure 3 、 Figure 5 、 Figure 6 and Figure 7 When the rotor UAV detaches, it restarts after a short shutdown and gradually descends. When there are many sundries on the bottom surface of the landing position, the air pump is restarted again, so that the air pump transports gas to the distribution sleeve through the first pipe, and is transported to the fixed sleeve of the pushing mechanism through the second pipe connected to the side of the distribution sleeve. As the gas is continuously introduced, the sealing plate of the lifting mechanism moves upward, and the air outlet pipe is opened. The incoming air blows vertically downward through the air outlet pipe, so that the sundries at the landing position are dispersed by the wind, enabling the rotor UAV to land stably; when it is necessary to land on the water surface, as the rotor UAV descends, the telescopic rod of the control mechanism is started, so that the telescopic rod pushes the sealing ring to rise. After the sealing ring rises, the small hole communicating with the second pipe in the distribution sleeve is blocked. At this time, the air pump is started, and the air pump inputs gas into the distribution sleeve through the first pipe. The air filled in the distribution sleeve flows through the curved hole to the curved pipe and is introduced into the floating airbag through the curved pipe. Before landing on the water surface, the floating airbag is filled with gas, and then the water surface landing is completed.

[0017] First, by using an air pump for air transportation, when landing on land, air is introduced and the sealing plate is pushed upward. First, the air outlet pipe is opened and connected, so that the air pump continuously ventilates the first air outlet pipe. In cooperation with the air outlet pipe vertically downward at the lower end, when about to land on land, multiple groups of air outlet pipes are used to blow high-speed air towards the ground to be landed, so as to blow away the impurities on the ground to be landed, so that the base of the rotary-wing unmanned aerial vehicle lands stably, improving the actual landing stability of the rotary-wing unmanned aerial vehicle and avoiding tilting during landing.

[0018] In addition, by opening an inner hole on the top surface of the cross and adding a control mechanism in the inner hole, when it is necessary to land on the water surface, the telescopic rod in the control mechanism is driven to drive the sealing ring to rise, sealing the second pipe outside the distribution sleeve. In cooperation with the curved hole in the cross, the input air of the air pump is introduced into the floating air bag through the curved pipe, so that the floating air bag only restarts and bulges when it is necessary to land on the water surface to complete water surface floating. And when landing on land, it effectively avoids the floating air bag that is inflated and inflated from being cut by foreign objects, improves the service life of the floating air bag, and avoids accidental damage, with good practical effects.

[0019] The beneficial effects of the present invention are as follows:

[0020] 1. In the present invention, by opening a card slot at the bottom of the fuselage of the fixed-wing unmanned aerial vehicle and the fixed wing, and adding a pushing mechanism at the top of the rotary-wing unmanned aerial vehicle, and movably installing a lifting mechanism at the top of the pushing mechanism, the clamping rod in the lifting mechanism is sleeved with the card slot, so that the rotary-wing unmanned aerial vehicle is started and vertically lifted, and the fixed-wing unmanned aerial vehicle is vertically lifted to a high altitude. By starting the fixed-wing unmanned aerial vehicle at a high altitude and simultaneously turning off the rotary-wing unmanned aerial vehicle, the fixed-wing unmanned aerial vehicle and the rotary-wing unmanned aerial vehicle are separated at the same time, so as to get rid of the dependence on the take-off track and the take-off assistor in the case of a poor take-off environment, realize vertical take-off in place, the actual take-off and lift-off are stable, and the rotary-wing unmanned aerial vehicle is convenient to be recycled for vertical take-off after landing, greatly increasing the take-off adaptability.

[0021] 2. In the present invention, by using an air pump for air transportation, when landing on land, air is introduced and the sealing plate is pushed upward. First, the air outlet pipe is opened and connected, so that the air pump continuously ventilates the first air outlet pipe. In cooperation with the air outlet pipe vertically downward at the lower end, when about to land on land, multiple groups of air outlet pipes are used to blow high-speed air towards the ground to be landed, so as to blow away the impurities on the ground to be landed, so that the base of the rotary-wing unmanned aerial vehicle lands stably, improving the actual landing stability of the rotary-wing unmanned aerial vehicle and avoiding tilting during landing.

[0022] 3. In the present invention, an inner hole is opened on the top surface of the cross, and a control mechanism is added in the inner hole. When it is necessary to lower the water surface, the telescopic rod in the control mechanism drives the sealing ring to rise, sealing the second pipe outside the distribution sleeve. Cooperating with the curved hole in the cross, the input air of the air pump is introduced into the floating air bag through the curved pipe, so that the floating air bag only restarts to inflate when it is necessary to lower the water surface to complete water surface floating. Moreover, when landing on land, it effectively avoids the inflated floating air bag being cut by foreign objects, improves the service life of the floating air bag, and avoids accidental damage, with good practical effects. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 is a schematic structural diagram of the present invention;

[0024] Figure 2 is a schematic diagram of the body of the present invention;

[0025] Figure 3 is a schematic diagram of the rotary-wing unmanned aerial vehicle of the present invention;

[0026] Figure 4 is a schematic diagram of the lifting mechanism of the present invention;

[0027] Figure 5 is a schematic diagram of the pushing mechanism of the present invention;

[0028] Figure 6 is a schematic cross-sectional view of the cross of the rotary-wing unmanned aerial vehicle of the present invention;

[0029] Figure 7 is an exploded schematic diagram of the cross of the rotary-wing unmanned aerial vehicle of the present invention.

[0030] In the figure: 1, body; 2, rotary-wing unmanned aerial vehicle; 21, rotary-wing body; 22, cross; 23, rotary wing; 24, base; 25, second control transceiver; 3, pushing mechanism; 31, fixed sleeve; 32, threaded sleeve; 33, spring; 34, air outlet pipe; 4, lifting mechanism; 41, loop; 42, clamping rod; 43, sleeve rod; 44, sealing plate; 45, connecting rod; 46, shielding ring; 5, fixed wing; 6, card slot; 7, first control transceiver; 8, sensor; 9, distribution sleeve; 10, air pump; 11, first pipe; 12, second pipe; 13, inner hole; 14, control mechanism; 141, sealing ring; 142, notch; 143, intermediate plate; 144, telescopic rod; 15, curved hole; 16, curved pipe; 17, floating air bag. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0031] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0032] As Figures 1 to 7 shown, in the embodiment of the present invention, a separable composite-wing vertical take-off unmanned aerial vehicle system includes a fuselage 1 and a rotary-wing unmanned aerial vehicle. A fixed wing 5 is fixedly installed on the side surface of the fuselage 1. Card slots 6 are opened on both the bottom surface of the fixed wing 5 and the fuselage 1. A pushing mechanism 3 is fixedly installed on the top surface of the rotary-wing unmanned aerial vehicle 2. A lifting mechanism 4 is movably installed on the top surface of the pushing mechanism 3. The lifting mechanism 4 includes a loop 41, a clamping rod 42, a sleeve rod 43, a sealing plate 44, a connecting rod 45, and a shielding ring 46. The top surface of the loop 41 is fixedly connected to the clamping rod 42. The outer surface of the clamping rod 42 is movably sleeved with the card slot 6. The sleeve rod 43 is fixedly connected to the bottom surface of the loop 41. The sleeve rod 43 is movably sleeved inside the pushing mechanism 3. A first control transceiver 7 is fixedly installed on the bottom surface of the fuselage 1. An inductor 8 is fixedly installed on the bottom surface of the first control transceiver 7. The rotary-wing unmanned aerial vehicle 2 includes a rotary-wing fuselage 21, a cross 22, rotary wings 23, a base 24, and a second control transceiver 25. The rotary-wing unmanned aerial vehicle 2 is located directly below the fuselage 1. The cross 22 is fixedly installed on the top surface of the rotary-wing fuselage 21. The rotary wings 23 are located on the top surface of the cross 22. A distribution sleeve 9 is fixedly installed on the top surface of the cross 22. An air pump 10 is fixedly installed on the top surface of the distribution sleeve 9. A first pipe 11 is fixedly connected and communicated between the air pump 10 and the distribution sleeve 9. A second pipe 12 is fixedly connected and communicated between the distribution sleeve 9 and the pushing mechanism 3.

[0033] First embodiment: As Figure 1 、 Figure 2 、 Figure 3 and Figure 4As shown in the figure, before vertical takeoff, the fuselage 1 of the fixed-wing UAV is located on top of the rotary-wing UAV 2, and a lifting mechanism 4 is added to the top of the rotary-wing UAV 2. The clamping rod 42 in the lifting mechanism 4 is sleeved with the clamping grooves 6 at the bottom of the fuselage 1 and the fixed wing 5. The air pump 10 is started, so that the air pump 10 ventilates the distribution sleeve 9 through the first pipe 11 and introduces the gas into the fixed sleeve 31 of the pushing mechanism 3 through the second pipe 12. As the sleeve rod 43 in the fixed sleeve 31 rises, the lifting mechanism 4 is further lifted, so that the fuselage 1 of the fixed-wing UAV above the lifting mechanism 4 rises. During vertical takeoff, the rotary-wing UAV 2 is started, so that the rotors 23 in the rotary-wing UAV 2 rotate, and the rotary-wing UAV 2 gradually rises and vertically lifts the fixed-wing UAV. When the fixed-wing UAV and the rotary-wing UAV reach a certain speed and altitude, the engine in the fuselage 1 of the fixed-wing UAV is started, and it begins to fly relying on its own power. At the same time, the power of the rotary-wing UAV 2 is turned off, and the air pump 10 is turned off at the same time, so that the lifting mechanism 4 quickly descends, so that the clamping rod 42 in the lifting mechanism 4 quickly disengages from the clamping groove 6, and the rotary-wing UAV 2 automatically disengages from the fuselage 1 of the fixed-wing UAV. After disengagement, the fixed-wing UAV continues to fly until landing or recovery. After the rotary-wing UAV 2 disengages, the rotor 23 is started again and it lands.

[0034] First, by opening the clamping grooves 6 at the bottom of the fuselage 1 of the fixed-wing UAV and the fixed wing 5, adding a pushing mechanism 3 to the top of the rotary-wing UAV 2, and movably installing a lifting mechanism 4 on the top of the pushing mechanism 3, and using the clamping rod 42 in the lifting mechanism 4 to be sleeved with the clamping groove 6, the fixed-wing UAV is vertically lifted to a high altitude by starting and vertically rising the rotary-wing UAV 2. By starting the fixed-wing UAV at a high altitude and turning off the rotary-wing UAV 2 at the same time, the fixed-wing UAV and the rotary-wing UAV 2 are disengaged at the same time, so that in the case of poor takeoff environment, the dependence on the takeoff track and the takeoff assistor is eliminated, and vertical takeoff in place is realized. The actual takeoff and lift-off are stable, and the rotary-wing UAV 2 is convenient for recycling for vertical takeoff after landing, greatly increasing the takeoff adaptability.

[0035] Among them, the connecting rod 45 is fixedly connected to the inner side surface of the sleeve 41, the outer surface of the shielding ring 46 is fixedly connected to the connecting rod 45, the shielding ring 46 is located outside the first control transceiver 7, and by using the position induction between the shielding ring 46 and the sensor 8, the disengagement information is accurately obtained. When the sensor 8 cannot sense the shielding ring 46, it indicates that the fixed-wing UAV and the rotary-wing UAV 2 have completed disengagement, and the disengagement information is accurately obtained at a high altitude.

[0036] Among them, the pushing mechanism 3 includes a fixed sleeve 31, a threaded sleeve 32, a spring 33, and an air outlet pipe 34. The fixed sleeve 31 is fixedly connected to the top surface of the cross 22. The outer surface of the threaded sleeve 32 is threadedly sleeved on the top of the fixed sleeve 31. The bottom surface of the threaded sleeve 32 is fixedly connected to the spring 33. The air outlet pipe 34 is fixedly communicated with the outer surface of the fixed sleeve 31. The inner surface of the threaded sleeve 32 is movably sleeved with a sleeve rod 43. The sealing plate 44 is fixedly connected to the bottom surface of the sleeve rod 43. The top surface of the sleeve rod 43 is fixedly connected to the spring 33. The sealing plate 44 is sleeved inside the fixed sleeve 31. The pushing mechanism 3 is movably installed with the lifting mechanism 4 to lift the lifting mechanism 4 to a certain height during takeoff, and when detachment is required, quickly lower the position of the lifting mechanism 4, thereby improving the separation effect between the fixed-wing UAV and the rotary-wing UAV 2.

[0037] Among them, the number of the fixed sleeves 31 is four. The four fixed sleeves 31 are annularly distributed at equal intervals on the top surface of the cross 22. The outer surface of the fixed sleeve 31 is fixedly communicated with the second pipe 12.

[0038] Among them, an inner hole 13 is opened on the top surface of the cross 22. A control mechanism 14 is provided on the inner surface of the inner hole 13. A curved hole 15 is opened inside the cross 22. The curved hole 15 is communicated with the inner hole 13. The inner hole 13 is communicated with the distribution sleeve 9. By using the curved hole 15, the air in the distribution sleeve 9 is introduced into the curved pipe 16, thereby realizing the inflation of the floating airbag 17.

[0039] Among them, the control mechanism 14 includes a sealing ring 141, a notch 142, an intermediate plate 143, and a telescopic rod 144. The sealing ring 141 is sleeved inside the inner hole 13 and the distribution sleeve 9. The intermediate plate 143 is fixedly connected to the inner surface of the sealing ring 141. The telescopic rod 144 is fixedly installed on the top surface of the rotary-wing airframe 2 and is located inside the inner hole 13. The top surface of the telescopic rod 144 is fixedly connected to the intermediate plate 143. The notch 142 is opened on the outer surface of the sealing ring 141. The notch 142 is located on one side of the first pipe 11. By moving the sealing ring 141 up and down, the air supply direction of the air pump 10 is changed, and the notch 142 ensures that when switching and adjusting, the air pump 10 is always allowed to introduce gas into the distribution sleeve 9 to ensure stable air supply.

[0040] Among them, a curved pipe 16 is fixedly connected to the bottom surface of the cross 22. The upper end of the curved pipe 16 is communicated with the curved hole 15. A floating airbag 17 is fixedly installed on the bottom surface of the rotary-wing UAV 2. The side surface of the floating airbag 17 is fixedly communicated with the curved pipe 16. By using the air pump 10 to temporarily inflate the floating airbag 17, the inflation of the floating airbag 17 is completed only when water landing is required, avoiding cutting the inflated spare floating airbag 17 during land landing, improving the service life, and adapting to different landing situations.

[0041] Among them, the base 25 is fixedly installed on the bottom surface of the rotor body 21, the second control transceiver 25 is fixedly installed inside the rotor body 21, the bottom surface of the rotor body 21 is fixedly installed with the floating airbag 17, and the control of the rotor UAV 2 and the fixed-wing UAV is respectively realized by using the second control transceiver 25 and the first control transceiver 7. Cooperating with the control system on the ground, accurate vertical takeoff and landing control is completed.

[0042] Second Embodiment: As Figure 1 , Figure 3 , Figure 5 , Figure 6 and Figure 7 shown, when the rotor UAV 2 detaches, it restarts after a short stop and gradually descends. When there are many sundries on the bottom surface of the landing position, the air pump 10 is restarted again, so that the air pump 10 transports gas to the distribution sleeve 9 through the first pipe 11, and is transported to the fixed sleeve 31 of the pushing mechanism 3 through the second pipe 12 connected to the side of the distribution sleeve 9. As the gas is continuously introduced, the sealing plate 44 of the lifting mechanism 4 moves upward, and the air outlet pipe 34 is opened. The incoming air blows vertically downward through the air outlet pipe 34, so that the sundries at the position to be landed are scattered by the wind force, and the rotor UAV 2 lands stably; when it must land on the water surface, as the rotor UAV 2 descends, the telescopic rod 144 of the control mechanism 14 is started, so that the telescopic rod 144 pushes the sealing ring 141 to rise. After the sealing ring 141 rises, the small hole connected to the second pipe 12 in the distribution sleeve 9 is blocked. At this time, the air pump 10 is started, and the air pump 10 inputs gas into the distribution sleeve 9 through the first pipe 11. The air filled in the distribution sleeve 9 flows to the curved pipe 16 through the curved hole 15 and is introduced into the floating airbag 17 through the curved pipe 16. Before landing on the water surface, the floating airbag 17 is filled with gas, and then the water surface landing is completed.

[0043] First of all, by using the air pump 10 to transport air, when landing on land, by feeding air and pushing the sealing plate 44 to move upward, first the opening and connection of the air outlet pipe 34 are realized. Thus, by continuously ventilating the air outlet pipe 34 with the air pump 10, and cooperating with the vertically downward air outlet pipe 34 at the lower end, when about to land on land, multiple air outlet pipes 34 are used to blow high-speed air to the ground to be landed, so that the impurities on the ground to be landed are scattered, so that the base 24 of the rotor UAV 2 lands stably, improving the actual landing smoothness of the rotor UAV 2 and avoiding tilting during landing.

[0044] In addition, by opening an inner hole 13 on the top surface of the cross 22 and adding a control mechanism 14 in the inner hole 13, when the water surface needs to descend, the telescopic rod 144 in the control mechanism 14 drives the sealing ring 141 to rise, sealing the second pipe 12 outside the distribution sleeve 9. In cooperation with the curved hole 15 in the cross 22, the input air of the air pump 10 is introduced into the floating airbag 17 through the curved pipe 16, enabling the floating airbag to restart and inflate only when the water surface needs to descend to complete water surface floating. Moreover, when landing on land, it effectively prevents the inflated floating airbag from being cut by foreign objects, improves the service life of the floating airbag 17, avoids accidental damage, and has good practical effects.

[0045] It should be noted that in this article, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the term "comprising", "including" or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements not only includes those elements but also includes other elements not explicitly listed, or further includes elements inherent to such process, method, article or device.

[0046] Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A separable compound-wing vertical takeoff unmanned aerial vehicle system, comprising an airframe (1) and a rotary-wing unmanned aerial vehicle, characterized in that: On the side of the described airframe (1), a fixed wing (5) is fixedly installed. Slots (6) are provided on both the bottom surface of the fixed wing (5) and the airframe (1). On the top surface of the rotary-wing UAV (2), a pushing mechanism (3) is fixedly installed. On the top surface of the pushing mechanism (3), a lifting mechanism (4) is movably installed. The lifting mechanism (4) includes a loop (41), a clamping rod (42), a sleeve rod (43), a sealing plate (44), a connecting rod (45), and a shielding ring (46). The top surface of the loop (41) is fixedly connected to the clamping rod (42). The outer surface of the clamping rod (42) is movably sleeved in the slot (6). The sleeve rod (43) is fixedly connected to the bottom surface of the loop (41). The sleeve rod (43) is movably sleeved inside the pushing mechanism (3). On the bottom surface of the airframe (1), a first control transceiver (7) is fixedly installed. On the bottom surface of the first control transceiver (7), a sensor (8) is fixedly installed. The rotary-wing UAV (2) includes a rotary-wing airframe (21), a cross (22), rotors (23), a base (24), and a second control transceiver (25). The rotary-wing UAV (2) is located directly below the airframe (1). The cross (22) is fixedly installed on the top surface of the rotary-wing airframe (21). The rotors (23) are located on the top surface of the cross (22). On the top surface of the cross (22), a distribution sleeve (9) is fixedly installed. On the top surface of the distribution sleeve (9), an air pump (10) is fixedly installed. A first pipe (11) is fixedly connected between the air pump (10) and the distribution sleeve (9). A second pipe (12) is fixedly connected between the distribution sleeve (9) and the pushing mechanism (3). An inner hole (13) is provided on the top surface of the cross (22). A control mechanism (14) is provided on the inner surface of the inner hole (13). A curved hole (15) is opened inside the cross (22). The curved hole (15) is connected to the inner hole (13). The inner hole (13) is connected to the distribution sleeve (9). The control mechanism (14) includes a sealing ring (141), a notch (142), an intermediate plate (143), and a telescopic rod (144). The sealing ring (141) is sleeved inside the inner hole (13) and the distribution sleeve (9). The intermediate plate (143) is fixedly connected to the inner surface of the sealing ring (141). The telescopic rod (144) is fixedly installed on the top surface of the rotary-wing airframe (21) and is located inside the inner hole (13). The top surface of the telescopic rod (144) is fixedly connected to the intermediate plate (143). The notch (142) is opened on the outer surface of the sealing ring (141). The notch (142) is located on one side of the first pipe (11).

2. The separable composite-wing vertical takeoff UAV system according to claim 1, characterized in that: The connecting rod (45) is fixedly connected to the inner side surface of the loop (41). The outer surface of the shielding ring (46) is fixedly connected to the connecting rod (45). The shielding ring (46) is located outside the first control transceiver (7).

3. The separable composite-wing vertical takeoff UAV system according to claim 1, characterized in that: The driving mechanism (3) includes a fixed sleeve (31), a threaded sleeve (32), a spring (33) and an air outlet pipe (34). The fixed sleeve (31) is fixedly connected to the top surface of the cross (22). The outer surface of the threaded sleeve (32) is threadedly sleeved on the top of the fixed sleeve (31). The bottom surface of the threaded sleeve (32) is fixedly connected to the spring (33). The air outlet pipe (34) is fixedly communicated with the outer surface of the fixed sleeve (31). The inner surface of the threaded sleeve (32) is movably sleeved with a sleeve rod (43). The sealing plate (44) is fixedly connected to the bottom surface of the sleeve rod (43). The top surface of the sleeve rod (43) is fixedly connected to the spring (33). The sealing plate (44) is sleeved inside the fixed sleeve (31).

4. The separable composite-wing vertical take-off UAV system according to claim 3, characterized in that: The number of the fixed sleeves (31) is four. The four fixed sleeves (31) are annularly distributed at equal intervals on the top surface of the cross (22). The outer surface of the fixed sleeve (31) is fixedly communicated with the second pipe (12).

5. The separable composite-wing vertical takeoff UAV system according to claim 1, wherein: The bottom surface of the cross (22) is fixedly connected with a curved pipe (16). The upper end of the curved pipe (16) is communicated with a curved hole (15). The bottom surface of the rotary-wing unmanned aerial vehicle (2) is fixedly installed with a floating airbag (17). The side surface of the floating airbag (17) is fixedly communicated with the curved pipe (16).

6. The separable composite-wing vertical takeoff UAV system according to claim 1, characterized in that: The base (24) is fixedly installed on the bottom surface of the rotary-wing airframe (21). The second control transceiver (25) is fixedly installed inside the rotary-wing airframe (21). The bottom surface of the rotary-wing airframe (21) is fixedly installed with the floating airbag (17).

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