Variable-structure aircraft capable of quickly taking off and landing by simulating eagle tenons

Abstract

The invention discloses a variable-structure aircraft capable of quickly taking off and landing by simulating an eagle tenon, and relates to the technical field of aircrafts The problems that an existing aircraft is low in takeoff speed, poor in concealment, difficult to find a proper landing point and long in landing time are solved. The aircraft comprises the rack and the bouncing table, the aircraft can take off rapidly in a rugged and narrow environment through the bouncing energy storage mechanism and the bouncing table, the requirement for the environment is lower during take-off, adaptability is higher, take-off is not affected by complex terrains, the take-off speed is higher, the blocking net is captured through the hook claw structure, rapid interception of the aircraft can be achieved, and the aircraft can take off rapidly. The aircraft recovery time is effectively shortened, the exposure risk is reduced, the arms are folded before launching, the ground projection area is small under the same load condition, and the needed take-off space is smaller. The unmanned aerial vehicle is mainly used for rapid takeoff in narrow terrains such as trenches and adaptive takeoff in rugged terrains, and meanwhile, the unmanned aerial vehicle can directionally and rapidly intercept landing under the condition that conditions exist and has the autonomous re-flying function.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft, and in particular to a bionic falcon-like variable configuration aircraft capable of rapid take-off and landing. Background Art

[0002] A quadrotor is an aircraft with four rotating axes that uses rotors to provide lift. Due to its simple structure, flexible control, and strong carrying capacity, it has become one of the research hotspots in the field of aircraft in recent years and is widely used in civil and military fields such as rescue, reconnaissance, and exploration.

[0003] The structural design of traditional quadcopters adopts a symmetrical fixed-arm design, and the landing gear is a simple rigid structure. During operation, it needs to be in a flat, relatively open area, and slowly rise to a safe height before it can perform rapid movements. Similarly, during the landing phase, it needs to find a suitable area, hover, and then slowly descend to the ground. There are problems such as slow take-off speed, poor concealment, difficulty in finding a suitable landing point, and long landing time.

[0004] In summary, the existing aircraft with a symmetrical layout and fixed arms design have the problems of slow take-off speed, poor concealment, difficulty in finding a suitable landing point, and long landing time. Summary of the invention

[0005] The purpose of the present invention is to solve the problems of slow take-off speed, poor concealment, difficulty in finding a suitable landing point, and long landing time of aircraft with symmetrical fixed arms, and to provide a bionic falcon-like variable configuration aircraft with fast take-off and landing.

[0006] The technical solution of the present invention is: a bionic falcon fast take-off and landing variable configuration aircraft, comprising: a frame, on which a plurality of rotating mechanisms evenly distributed along the circumference are arranged, and the rotating mechanisms include a first motor and a rotor installed on the driving end of the first motor;

[0007] A bouncing platform is connected to the bottom of the frame through two symmetrically distributed bouncing energy storage mechanisms, and the bouncing energy storage mechanisms are used to push the frame and the bouncing platform away from each other to achieve bouncing takeoff;

[0008] The jumping platform is connected with a hook structure for capturing the blocking net, and the blocking net is captured by the hook structure to achieve rapid landing;

[0009] The frame comprises a frame body and an arm rotatably mounted on the frame body, the arm is connected to a base, and the first motor is fixedly mounted on the base.

[0010] Further, the bouncing energy storage mechanism includes two symmetrically distributed rocker arm groups and an energy storage member, the rocker arm group includes a first rocker arm and a second rocker arm that are rotatably connected, the top end of the first rocker arm is fixedly connected to the transmission shaft on the frame, the bottom end of the second rocker arm is rotatably connected to the bouncing platform, the energy storage member is connected between the two rocker arm groups, and the energy storage member has an elastic force that brings the two rocker arm groups closer to each other;

[0011] a second motor, mounted on the frame, the second motor being connected to the two rocker arm groups through a gear set, the second motor being used to drive the two rocker arm groups away from each other, the gear set comprising a first gear, a second gear set and a third gear, the first gear being mounted on the driving end of the second motor, the frame having an arc groove with the first gear as the center, a guide shaft being slidably mounted in the arc groove, the second gear set being mounted on the guide shaft and meshing with the first gear;

[0012] The frame has two transmission shafts arranged side by side, and the two transmission shafts are respectively connected with fourth gears, and the two fourth gears are meshed with each other. The third gear is installed on one of the transmission shafts. When the second motor drives the second gear group to move from the energy release position to the energy storage position through the first gear, the second gear group is meshed with the third gear to achieve power transmission. When the energy storage member makes the two rocker arm groups move closer to each other, the third gear drives the second gear group to move from the energy storage position to the energy release position, and the third gear is disengaged from the second gear group to achieve power interruption.

[0013] Further, the second gear set includes a second input tooth and a second output tooth, the diameter of the second input tooth is greater than the diameter of the second output tooth, the diameter of the second output tooth is smaller than the diameter of the third gear, the second input tooth is meshed with the first gear, and the second output tooth is meshed with the third gear when it moves to the energy storage position.

[0014] Furthermore, the two hook structures are symmetrically arranged, and the two hook structures are rotatably installed on the bouncing platform and are respectively connected to the driving ends of the first driving member. The first driving member is used to drive the hook structure to rotate to adjust the take-off posture and can adjust the opening and closing degree according to the landing posture to capture the arresting net.

[0015] Further, the first driving member is a first steering gear, a driving end of the first steering gear is connected to a fifth gear, the hook structure has a sixth gear meshing with the fifth gear, and a diameter of the sixth gear is greater than a diameter of the fifth gear.

[0016] Furthermore, one of the frame and the jumping platform is connected with an electromagnetic buckle, and the other is connected with a hook that matches the electromagnetic buckle.

[0017] Furthermore, it also includes: a stretching member connected between the arm and the frame, the stretching member has a pulling force to unfold the arm, a second driving member is connected to the frame, a driving end of the second driving member is connected to the arm, and the second driving member is used to drive the arm to fold and shrink.

[0018] Furthermore, the frame body has a latch pin that can slide in a horizontal direction, and the arm has a slot for cooperating with the latch pin. When the arm is rotated to a horizontal state, the opening of the slot faces the latch pin. An elastic member is connected between the latch pin and the frame body, and the elastic member has an elastic force that pushes the latch pin to move toward the slot.

[0019] Furthermore, the second driving member is a second servo, a driving end of the second servo is fixedly connected to a first cam, the arm is fixedly connected to a second cam, a transmission lever is rotatably connected to the frame, one end of the transmission lever abuts against the first cam, and the other end of the transmission lever abuts against the second cam.

[0020] Furthermore, the machine arm is a four-link structure.

[0021] Compared with the prior art, the present invention has the following effects:

[0022] 1. The bionic falcon-like variable configuration aircraft for rapid take-off and landing provided by the present invention can realize rapid take-off of the aircraft in rugged and narrow environments through a bouncing energy storage mechanism and a bouncing platform. The take-off has lower environmental requirements and stronger adaptability. The take-off is not affected by complex terrain and has a faster take-off speed. The arresting net is captured by a claw structure to achieve rapid interception of the aircraft, effectively shortening the aircraft recovery time and reducing exposure risks. The aircraft arm is folded before launch, and the ground projection area is small under the same load conditions, and the required take-off space is smaller.

[0023] 2. The bionic falcon-like variable-configuration aircraft for rapid takeoff and landing provided by the present invention starts the second motor when storing energy before takeoff, and the second motor drives the first gear to rotate. The first gear is always in a meshing state with the second gear group. The first gear will generate a circumferential thrust on the second gear group, so that the second gear group and the guide shaft move from the energy release position to the energy storage position. At this time, the second gear group is also meshed with the third gear, and then the power is transferred to the two transmission shafts, thereby driving the two swing arm groups away from each other to allow the energy storage member to store energy. During hopping takeoff, the third gear will rotate in the opposite direction, generating a reverse thrust on the second gear group, so that the second gear group returns to the energy release position. At this time, the second gear group and the second gear group are disengaged. The entire driving process does not require an additional power source, saving energy consumption, and the second motor will not be driven to rotate in the opposite direction during takeoff, avoiding the situation where the back electromotive force dissipates energy and burns electronic components.

[0024] 3. The bionic falcon-like fast take-off and landing variable-configuration aircraft provided by the present invention can use the arresting net to achieve rapid landing of the aircraft, effectively improving the recovery efficiency. After the aircraft completes the mission, if there is an arresting net arranged at the return location, the aircraft can use the high-definition gimbal to identify the Apriltag code of the arresting net, calculate its relative position with the arresting net and solve the optimal landing posture for the current flight state. The aircraft can then aim at the arresting net and quickly descend at a large pitch angle. The intercepting net can be captured by adjusting the front and rear claw structures, and the aircraft can be successfully recovered while the propellers are stopped, effectively shortening the recovery time of the aircraft and reducing the exposure risk. The design of capturing the arresting net can reduce the aircraft's requirements for the landing environment.

[0025] 4. The bionic falcon-like fast take-off and landing variable-configuration aircraft provided by the present invention has high flexibility and strong impact resistance. The bouncing energy storage mechanism can be remotely controlled to store energy through autonomous tension springs. This design can be used to adjust the posture and control the center of gravity during flight. Secondly, if the bottom structure collides with the outside world during flight, the tension spring structure can absorb the impact. Then, the bouncing energy storage mechanism can be released when the aircraft is recovered under any circumstances, and its antagonism can be used to resist the impact caused by rapid landing.

[0026] 5. The bionic falcon-like variable configuration aircraft for rapid take-off and landing provided by the present invention has an overall structural design with strong concealment and adaptability. By controlling the opening and closing angles of the front and rear hook structures, the aircraft's preparatory take-off posture and ejection angle are adjusted to ensure that the aircraft can be ejected on an inclined surface, thereby ensuring the function of ejecting the aircraft on a rugged road surface.

[0027] 6. The bionic falcon-like fast take-off and landing variable configuration aircraft provided by the present invention adopts a tension spring energy storage structure, which can provide initial kinetic energy for the aircraft, bounce the aircraft with its arms in a folded state to a certain height to avoid obstructions, and then quickly unfold the arms and rotate the rotors rapidly to provide lift, and the aircraft begins to perform flight operations. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a schematic diagram of the bionic falcon rapid take-off and landing variable configuration aircraft of the present invention in a rapid landing state;

[0029] Figure 2 It is a schematic diagram of the bionic falcon fast take-off and landing variable configuration aircraft of the present invention in a bouncing take-off state;

[0030] Figure 3 yes Figure 1 Side view of

[0031] Figure 4 yes Figure 1 A partial exploded view of

[0032] Figure 5 yes Figure 4 Schematic diagram of the other side;

[0033] Figure 6 yes Figure 1 A cross-sectional view of the middle arm;

[0034] Figure 7 yes Figure 2 A magnified image of area A;

[0035] Figure 8 yes Figure 4 Enlarged view of area B;

[0036] Fig. 9 yes Figure 4 Enlarged view of the middle C area;

[0037] Fig.10 yes Figure 5 Enlarged view of area D in the middle;

[0038] Fig.11 yes Figure 6 Magnified view of area E in the middle.

[0039] In the figure: 1, frame; 2, rotating mechanism; 3, first motor; 4, rotor; 5, jumping platform; 6, rocker arm group; 7, first rocker arm; 8, second rocker arm; 9, transmission shaft; 10, energy storage member; 11, second motor; 12, gear group; 13, first gear; 14, second gear group; 15, third gear; 16, arc groove; 17, guide shaft; 18, fourth gear; 19, second input tooth; 20, second output tooth; 21, claw structure; 22, first driving member; 23, fifth gear; 24, sixth gear; 25, electromagnetic buckle; 26, hook; 27, frame; 28, machine arm; 29, base; 30, stretching member; 31, second driving member; 32, bayonet; 33, slot; 34, elastic member; 35, first cam; 36, second cam; 37, transmission lever. DETAILED DESCRIPTION

[0040] Specific implementation method 1: Combination Figures 1 to 4 The present embodiment is described. The present embodiment includes a frame 1 and a bouncing platform 5. The frame 1 is provided with a plurality of rotating mechanisms 2 evenly distributed along the circumferential direction. The rotating mechanism 2 includes a first motor 3 and a rotor 4 installed on the driving end of the first motor 3. The bouncing platform 5 is connected to the bottom of the frame 1 through two symmetrically distributed bouncing energy storage mechanisms. The bouncing energy storage mechanisms are used to push the frame 1 and the bouncing platform 5 away from each other to achieve a bouncing takeoff. The bouncing platform 5 is connected with a hook structure 21 for capturing an arresting net. The arresting net is captured by the hook structure 21 to achieve a rapid landing. The frame 1 includes a frame body 27 and an arm 28 rotatably connected to the frame body 27. The arm 28 is connected with a base 29. The first motor 3 is fixedly mounted on the base 29.

[0041] The battery power supply and electronic components are concentrated on the frame 1, including GPS module, flight main control module, remote control signal receiver, microcomputer, gimbal pod, electronic speed governor, etc. The arresting net is a double-layer structure design. The upper layer is a large-interval high-strength nylon net, which is responsible for blocking the landing of the aircraft and buffering and absorbing kinetic energy. The lower layer is a low-density high-strength plate with a clear Apriltag code on the top surface, which can provide accurate location information for the aircraft. The upper and lower layers are separated by pillars. The arresting net is painted with low-visibility camouflage as a whole, which has strong concealment. If there is an arresting net at the return location, the aircraft can use the high-definition gimbal to identify the arresting net Ap riltag code, calculates its relative position with the arresting net and solves the optimal landing posture for the current flight state, then the aircraft can aim at the arresting net and quickly descend at a large pitch angle, and by adjusting the front and rear claw structures 21 to capture the arresting net and the aircraft stops propellers to successfully recover the aircraft, effectively shortening the aircraft recovery time and reducing the risk of exposure. The design of capturing the arresting net can lower the aircraft's requirements for the landing environment. When falling, after the claw structure 21 captures the arresting net, the first motor 3 quickly reduces the throttle, and the two claw structures 21 are tightened at the same time. The aircraft adjusts its posture to remain stable and then stops. During the recovery process, the energy storage component 10 weakens the impact force on the body in the vertical direction.

[0042] The bionic falcon-like variable configuration aircraft for rapid take-off and landing in this embodiment can achieve rapid take-off in rugged and narrow environments through a bouncing energy storage mechanism and a bouncing platform. It has lower environmental requirements and stronger adaptability during take-off. It is not affected by complex terrain and has a faster take-off speed. The arresting net is captured by a claw structure, which can achieve rapid interception of the aircraft, effectively shortening the aircraft recovery time and reducing exposure risks. The arms are folded before launch, and the ground projection area is small under the same load conditions, and the required take-off space is smaller.

[0043] Specific implementation method 2: Combination Figure 5 , Figure 8 , Fig. 9 , Fig.10 The present embodiment is described. The present embodiment is different from the first embodiment in that the bouncing energy storage mechanism includes two symmetrically distributed rocker arm groups 6 and an energy storage member 10. The rocker arm group 6 includes a first rocker arm 7 and a second rocker arm 8 which are rotatably connected. The top end of the first rocker arm 7 is fixedly connected to a transmission shaft 9 on a frame 1. The bottom end of the second rocker arm 8 is rotatably connected to a bouncing platform 5. The energy storage member 10 is connected between the two rocker arm groups 6. The energy storage member 10 has an elastic force that brings the two rocker arm groups 6 closer to each other. The energy storage member 10 can be a spring. The second motor 11 The second motor 11 is installed on the frame 1, and the second motor 11 is connected to the two rocker arm groups 6 through the gear group 12. The second motor 11 is used to drive the two rocker arm groups 6 away from each other. The gear group 12 includes a first gear 13, a second gear group 14 and a third gear 15. The first gear 13 is installed on the driving end of the second motor 11. The frame 1 has an arc groove 16 with the first gear 13 as the center. A guide shaft 17 is slidably installed in the arc groove 16. The second gear group 14 is installed on the guide shaft 17 and meshes with the first gear 13. The frame 1 has There are two transmission shafts 9 arranged side by side, and the two transmission shafts 9 are respectively connected with fourth gears 18, and the two fourth gears 18 are meshed with each other. The third gear 15 is installed on one of the transmission shafts 9. When the second motor 11 drives the second gear set 14 to move from the energy release position to the energy storage position through the first gear 13, the second gear set 14 is meshed with the third gear 15 to realize power transmission. When the energy storage member 10 makes the two rocker arm groups 6 move closer to each other, the third gear 15 drives the second gear set 14 to move from the energy storage position to the energy release position. The third gear 15 is disengaged from the second gear set 14 to achieve power interruption. It should be noted that the second gear set 14 always maintains a meshing state with the first gear 13 and moves circumferentially around the first gear 13. When in the energy release position, the second gear set 14 is only meshed with the first gear 13. When in the energy storage position, the second gear set 14 is meshed with the first gear 13 and the third gear 15 at the same time. Through the movement of the second gear set 14, one-way power transmission can be achieved without using other power sources. Other components and connection relationships are the same as those in the first specific embodiment.

[0044] When storing energy before takeoff, the second motor 11 is started, and the second motor 11 drives the first gear 13 to rotate. The first gear 13 is always in a meshing state with the second gear set 14. The first gear 13 will generate a circumferential thrust on the second gear set 14, so that the second gear set 14 and the guide shaft 17 move from the energy release position to the energy storage position. At this time, the second gear set 14 is also meshed with the third gear 15, and then the power is transferred to the two transmission shafts 9, thereby driving the two swing arm groups away from each other to enable the energy storage member 10 to store energy. When bouncing and taking off, the third gear 15 will rotate in the opposite direction, generating a reverse thrust on the second gear set 14, so that the second gear set 14 returns to the energy release position. At this time, the second gear set 14 and the second gear set 14 are disengaged. The entire driving process does not require an additional power source, saving energy consumption, and the second motor 11 will not be driven to rotate in the opposite direction during takeoff, avoiding the situation where the back electromotive force dissipates energy and burns electronic components.

[0045] Specific implementation method three: Combination Figure 8 This embodiment is described. The difference between this embodiment and the second embodiment is that the second gear set 14 includes a second input tooth 19 and a second output tooth 20. The diameter of the second input tooth 19 is larger than the diameter of the second output tooth 20. The diameter of the second output tooth 20 is smaller than the diameter of the third gear 15. The second input tooth 19 is meshed with the first gear 13. When the second output tooth 20 moves to the energy storage position, it is meshed with the third gear 15. In this embodiment, the first gear 13 and the third gear 15 are staggered. By adjusting the ratio of the second input tooth 19 and the second output tooth 20, it is equivalent to adding a first-stage reduction ratio. On the basis of being able to realize unidirectional power transmission, it can also realize the function of deceleration, making the rotation of the transmission shaft 9 more stable and having a better use effect. Other components and connection relationships are the same as those of the second embodiment.

[0046] Specific implementation method four: Combination Figure 4 , Figure 5This embodiment is described. The difference between this embodiment and the first embodiment is that the hook structure 21 has two symmetrically arranged hook structures 21. The two hook structures 21 are rotatably mounted on the jumping platform 5 and are respectively connected to the driving ends of the first driving member 22. The first driving member 22 is used to drive the hook structure 21 to rotate to adjust the take-off posture and can adjust the opening and closing degree according to the landing posture to capture the arresting net. The number of the first driving members 22 is two, and one first driving member 22 corresponds to one hook structure 21. The first driving member 22 is also mounted on the jumping platform 5. The jumping platform 5 is close to the ground, so the hook structure 21 is smaller in size, which can reduce the overall weight and reduce the load of the aircraft, thereby ensuring the navigation distance. The hook structure 21 is driven to rotate by the first driving member 22. The hook structure 21 can be supported on an uneven surface or inclined surface, so that the frame 1 is evenly stressed, so that the aircraft can take off smoothly in different venues, and the use scenario is wider. Other components and connection relationships are the same as those of the first embodiment.

[0047] Specific implementation method five: Combination Fig. 9 This embodiment is described. The difference between this embodiment and the fourth embodiment is that the first driving member 22 is a first steering gear, the driving end of the first steering gear is connected to the fifth gear 23, the hook structure 21 is connected to the sixth gear 24 meshing with the fifth gear 23, the diameter of the sixth gear 24 is greater than the diameter of the fifth gear 23, and by adjusting the ratio of the sixth gear 24 to the fifth gear 23, the first reduction ratio can be increased, the rotation speed of the hook structure 21 can be reduced, and the operation is more stable. Other components and connection relationships are the same as those of the fourth embodiment.

[0048] Specific implementation method six: Combination Figure 3 This embodiment is described. The difference between this embodiment and the first embodiment is that one of the frame 1 and the jumping platform 5 is connected with an electromagnetic buckle 25, and the other is connected with a hook 26 that matches the electromagnetic buckle 25. In this embodiment, the electromagnetic buckle 25 is set on the jumping platform 5, and the hook 26 is set on the frame 1. When the energy storage member 10 is stretched by the two rocker groups 6 to complete the energy storage, the electromagnetic buckle 25 is connected with the hook 26. The electromagnetic buckle 25 and the buckle are rigidly connected to lock, so that the jumping platform 5 and the frame 1 are connected as a whole, and the center of gravity is closer to the plane of the rotor 4 to avoid shaking in the air. The other components and connection relationships are the same as those of the first embodiment.

[0049] Specific implementation method seven: Combination Figure 4 , Figure 7 , Fig.11This embodiment is described. The difference between this embodiment and the first embodiment is that it also includes: a tension member 30 connected between the machine arm 28 and the frame 27. The tension member 30 has a pulling force to unfold the machine arm 28. The frame 1 is connected with a second driving member 31. The driving end of the second driving member 31 is connected to the machine arm 28. The second driving member 31 is used to drive the machine arm 28 to fold and shrink. The tension member 30 is a pull rope. Through the interaction between the pull rope and the second driving member 31, the folding and unfolding of the machine arm 28 is realized. Other components and connection relationships are the same as those of the first embodiment.

[0050] Specific implementation method eight: Combination Figure 4 , Figure 7 , Fig.11 This embodiment is described. The difference between this embodiment and the seventh embodiment is that the frame 27 has a latch 32 that can slide in the horizontal direction. Specifically, the frame 27 has a slide groove that is arranged in the horizontal direction. The latch 32 is slidably installed in the slide groove. The machine arm 28 has a slot 33 for cooperating with the latch 32. When the machine arm 28 rotates to a horizontal state, the opening of the slot 33 faces the latch 32. An elastic member 34 is connected between the latch 32 and the frame 27. The elastic member 34 has an elastic force that pushes the latch 32 to move toward the slot 33. The elastic member 34 is a spring. The latch 32 is inserted into the slot 33 under the push of the elastic member 34 to limit the rotation of the machine arm 28, lock the machine arm 28, and keep the machine arm 28 in the unfolded state. The elastic member can also be an electric telescopic rod. Other components and connection relationships are the same as those of the seventh embodiment.

[0051] Specific implementation method nine: Combination Figure 6 , Figure 7 This embodiment is described. The difference between this embodiment and the seventh embodiment is that the second driving member 31 is a second steering gear, the driving end of the second steering gear is fixedly connected to the first cam 35, the second cam 36 is fixedly connected to the arm 28, and the frame 27 is rotatably connected to a transmission lever 37, one end of the transmission lever 37 abuts against the first cam 35, and the other end of the transmission lever 37 abuts against the second cam 36. The cam is driven to rotate by the second steering gear, and the arm 28 can be unfolded under the action of the stretching member 30. The transmission lever 37 is a middle connecting component to transmit the force. Other components and connection relationships are the same as those of the seventh embodiment.

[0052] Specific implementation method ten: Combination Figure 1 , Figure 2 The present embodiment is described. The difference between the present embodiment and the first embodiment is that the arm 28 is a four-link structure, which has better stability, making the overall strength of the aircraft higher and the use effect better. The other components and connection relationships are the same as those of the first embodiment.

[0053] How to use this implementation:

[0054] Before takeoff, the arm 28 is in a folded state. First, the second motor 11 is started, and the second motor 11 drives the first gear 13 to rotate. The first gear 13 drives the second input tooth 19 to rotate and applies a circumferential force to the second input tooth 19, pushing the second input tooth 19, the guide shaft 17 and the second output tooth 20 from the energy release position to the energy storage position. At this time, the second output tooth 20 is engaged with the third gear 15, and the power can be transmitted to rotate the transmission shaft 9. The two transmission shafts 9 are rotated in the opposite direction through the engagement of the fourth gear 18, thereby driving the two rocker arm groups 6 away from each other, stretching the energy storage member 10 to store energy, and after the energy storage is completed, the electromagnetic buckle 25 is engaged with the hook 26 to lock it.

[0055] At the same time, the first steering gear can be started, and the first steering gear drives the hook structure 21 to rotate, so that the hook structure 21 is supported on the ground, and the take-off attitude of the aircraft is adjusted. Then, the electromagnetic buckle 25 is controlled to separate the electromagnetic buckle 25 from the hook 26, and the energy storage component will pull the two rocker arm groups 6 closer to each other, thereby pushing the aircraft to bounce. After the aircraft reaches a certain height, the second steering gear is started, and the second steering gear drives the first cam 35 to rotate. The arm 28 is unfolded under the action of the stretching member 30 until the opening of the slot 33 is opposite to the pin 32. The pin 32 is inserted into the slot 33 driven by the elastic member 34 to lock the arm 28, and then the first motor 3 is started to drive the rotor 4 to rotate, and the aircraft flies.

[0056] The content of the present invention is not limited to the content of the above-mentioned embodiments. The combination of one or several specific embodiments can also achieve the purpose of the invention.

Claims

1. A bionic falcon-like variable configuration aircraft for rapid take-off and landing, characterized in that: include: A frame (1), wherein the frame (1) is provided with a plurality of rotating mechanisms (2) evenly distributed in the circumferential direction, and the rotating mechanisms (2) include a first motor (3) and a rotor (4) mounted on a driving end of the first motor (3); A bouncing platform (5) is connected to the bottom of the frame (1) via two symmetrically distributed bouncing energy storage mechanisms, wherein the bouncing energy storage mechanisms are used to push the frame (1) and the bouncing platform (5) away from each other to achieve bouncing takeoff; The jumping platform (5) is connected to a hook structure (21) for capturing the blocking net, and the blocking net is captured by the hook structure (21) to achieve rapid landing; The frame (1) comprises a frame body (27) and a machine arm (28) rotatably mounted on the frame body (27); the machine arm (28) is connected to a base (29); and the first motor (3) is fixedly mounted on the base (29).

2. The bionic falcon-like rapid take-off and landing variable configuration aircraft according to claim 1, characterized in that: The bouncing energy storage mechanism comprises two symmetrically distributed rocker arm groups (6) and an energy storage member (10); the rocker arm group (6) comprises a first rocker arm (7) and a second rocker arm (8) which are rotatably connected; the top end of the first rocker arm (7) is fixedly connected to a transmission shaft (9) on the frame (1); the bottom end of the second rocker arm (8) is rotatably connected to the bouncing platform (5); the energy storage member (10) is connected between the two rocker arm groups (6); and the energy storage member (10) has an elastic force that causes the two rocker arm groups (6) to move closer to each other; a second motor (11) mounted on the frame (1); the second motor (11) is connected to the two rocker arm groups (6) via a gear group (12); the second motor (11) is used to drive the two rocker arm groups (6) to move away from each other; the gear group (12) comprises a first gear (13), a second gear group (14) and a third gear (15); the first gear (13) is mounted on a driving end of the second motor (11); the frame (1) has an arc groove (16) with the first gear (13) as a center; a guide shaft (17) is slidably mounted in the arc groove (16); the second gear group (14) is mounted on the guide shaft (17) and meshes with the first gear (13); The frame (1) has two transmission shafts (9) arranged side by side, and the two transmission shafts (9) are respectively connected with fourth gears (18), and the two fourth gears (18) are meshed with each other. The third gear (15) is installed on one of the transmission shafts (9). When the second motor (11) drives the second gear set (14) to move from an energy release position to an energy storage position through the first gear (13), the second gear set (14) is meshed with the third gear (15) to achieve power transmission. When the energy storage member (10) causes the two rocker arm groups (6) to move closer to each other, the third gear (15) drives the second gear set (14) to move from the energy storage position to the energy release position, and the third gear (15) is disengaged from the second gear set (14) to achieve power interruption.

3. The bionic falcon-like rapid take-off and landing variable configuration aircraft according to claim 2, characterized in that: The second gear set (14) comprises a second input tooth (19) and a second output tooth (20); the diameter of the second input tooth (19) is greater than the diameter of the second output tooth (20); the diameter of the second output tooth (20) is smaller than the diameter of the third gear (15); the second input tooth (19) is meshed with the first gear (13); and the second output tooth (20) is meshed with the third gear (15) when it moves to the energy storage position.

4. The bionic falcon-like rapid take-off and landing variable configuration aircraft according to claim 1, characterized in that: The hook structures (21) have two symmetrically arranged hook structures (21), which are rotatably mounted on the jumping platform (5) and are respectively connected to the driving ends of the first driving member (22), and the first driving member (22) is used to drive the hook structures (21) to rotate to adjust the take-off posture and to adjust the opening and closing degree according to the landing posture to capture the arresting net.

5. The bionic falcon-like rapid take-off and landing variable configuration aircraft according to claim 4, characterized in that: The first driving member (22) is a first steering gear, the driving end of the first steering gear is connected to a fifth gear (23), the hook structure (21) has a sixth gear (24) meshing with the fifth gear (23), and the diameter of the sixth gear (24) is greater than the diameter of the fifth gear (23).

6. The bionic falcon-like rapid take-off and landing variable configuration aircraft according to claim 1, characterized in that: One of the frame (1) and the jumping platform (5) is connected with an electromagnetic buckle (25), and the other is connected with a hook (26) matched with the electromagnetic buckle (25).

7. A bionic falcon-like fast take-off and landing variable configuration aircraft according to any one of claims 1 to 6, characterized in that: Also includes: A stretching member (30) is connected between the machine arm (28) and the frame (27), and the stretching member (30) has a pulling force that causes the machine arm (28) to unfold. A second driving member (31) is connected to the frame (1), and a driving end of the second driving member (31) is connected to the machine arm (28). The second driving member (31) is used to drive the machine arm (28) to fold and shrink.

8. The bionic falcon-like rapid take-off and landing variable configuration aircraft according to claim 7, characterized in that: The frame (27) has a latch (32) that can slide in a horizontal direction, and the machine arm (28) has a slot (33) for cooperating with the latch (32). When the machine arm (28) rotates to a horizontal state, the opening of the slot (33) faces the latch (32). An elastic member (34) is connected between the latch (32) and the frame (27), and the elastic member (34) has an elastic force that pushes the latch (32) to move toward the slot (33).

9. The bionic falcon-like rapid take-off and landing variable configuration aircraft according to claim 7, characterized in that: The second driving member (31) is a second steering gear, the driving end of the second steering gear is fixedly connected to a first cam (35), the machine arm (28) is fixedly connected to a second cam (36), the frame body (27) is rotatably connected to a transmission lever (37), one end of the transmission lever (37) is in contact with the first cam (35), and the other end of the transmission lever (37) is in contact with the second cam (36).

10. A bionic falcon-like fast take-off and landing variable configuration aircraft according to any one of claims 1 to 6, characterized in that: The machine arm (28) is a four-link structure.

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