A variable configuration aircraft emulating the swift takeoff and landing of a peregrine falcon

Abstract

The application relates to a variable-structure aircraft capable of rapid take-off and landing like a falcon, and relates to the technical field of aircrafts. The application is mainly used for rapid take-off in a trench and the like narrow terrain and adaptive take-off in rugged terrain, and the aircraft can be directionally and rapidly intercepted and landed and has the function of autonomous reflight under the condition.

Description

Technical Field

[0001] The present 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] Traditional quadcopters use a symmetrical fixed-arm design in their structural design, and their landing gear is a simple rigid structure. During operation, they need to operate in a flat, relatively open area and slowly rise to a safe height before they can perform rapid movements. Similarly, during the landing phase, they need to find a suitable area, hover, and then slowly descend to the ground. They have problems such as slow take-off speed, poor concealment, difficulty in finding a suitable landing point, and long landing time.

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

[0005] The present invention aims to address the problems of slow takeoff speed, poor concealment, difficulty finding a suitable landing spot, and long landing times associated with aircraft with symmetrical fixed-arm designs. Furthermore, it provides a bionic falcon-like, variable-configuration aircraft capable of rapid takeoff and landing.

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

[0007] A bouncing platform is connected to the bottom of the frame via two symmetrically distributed bouncing energy storage mechanisms, wherein 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 to 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 includes 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 elastic bouncing energy storage mechanism comprises two symmetrical rocker arm groups and an energy storage member, each of the rocker arm groups comprises a first rocker arm and a second rocker arm connected in rotation, the top end of the first rocker arm is fixedly connected with a transmission shaft on the frame, the bottom end of the second rocker arm is rotatably connected with the bouncing platform, the energy storage member is connected between the two rocker arm groups, and the energy storage member has an elastic force to make the two rocker arm groups approach each other.

[0011] A second motor is mounted on the frame, the second motor is connected with the two rocker arm groups through a gear set, the second motor is used to drive the two rocker arm groups to move away from each other, the gear set comprises a first gear, a second gear set and a third gear, the first gear is mounted on the driving end of the second motor, the frame has an arc-shaped slot with the first gear as the center, a guide shaft is slidably mounted in the arc-shaped slot, the second gear set is mounted on the guide shaft and meshes with the first gear.

[0012] The frame has two transmission shafts arranged side by side, and a fourth gear is connected with each of the two transmission shafts, the two fourth gears mesh with each other, and the third gear is mounted on one of the transmission shafts, when the second motor drives the second gear set to move from the energy storage position to the energy release position through the first gear, the second gear set meshes with the third gear to realize power transmission, when the energy storage member makes the two rocker arm groups approach each other, the third gear drives the second gear set to move from the energy storage position to the energy release position, and the third gear and the second gear set are disengaged to realize power interruption.

[0013] Further, the second gear set comprises a second input gear and a second output gear, the diameter of the second input gear is greater than that of the second output gear, and the diameter of the second output gear is less than that of the third gear, the second input gear meshes with the first gear, and the second output gear meshes with the third gear when moving to the energy storage position.

[0014] Further, the hook structure has two symmetrical structures, the two hook structures are rotatably mounted on the bouncing platform and connected with the driving end of the first driving member respectively, the first driving member is used to drive the hook structure to rotate to adjust the take-off posture and capture the blocking net according to the opening and closing degree of the landing posture.

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

[0016] Further, one of the frame and the bouncing platform is connected with an electromagnetic buckle, and the other is connected with a clamping hook matched with the electromagnetic buckle.

[0017] Further, the device further comprises a stretching member connected between the arm and the frame body, the stretching member has a pulling force for unfolding the arm, the frame body is connected with a second driving member, a driving end of the second driving member is connected with the arm, and the second driving member is used for driving the arm to fold and shrink.

[0018] Further, the frame body is provided with a clamping pin capable of sliding in a horizontal direction, the arm is provided with a clamping groove matched with the clamping pin, when the arm rotates to a horizontal state, an opening of the clamping groove is opposite to the clamping pin, and an elastic member is connected between the clamping pin and the frame body, the elastic member has an elastic force for pushing the clamping pin to move towards the clamping groove.

[0019] Further, the second driving member is a second steering wheel, a first cam is fixedly connected with a driving end of the second steering wheel, a second cam is fixedly connected with the arm, a transmission lever is rotatably connected with the frame body, one end of the transmission lever is abutted with the first cam, and the other end of the transmission lever is abutted with the second cam.

[0020] Further, the arm is a four-bar linkage structure.

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

[0022] 1. The variable-structure aircraft for rapid take-off and landing of the bionic hawk falcon provided by the device can realize rapid take-off of the aircraft in a rugged and narrow environment through the bouncing energy storage mechanism and the bouncing platform, has lower requirements for the environment and stronger adaptability during take-off, is not affected by complex terrain during take-off, has faster take-off speed, can capture the blocking net through the hook structure, can realize rapid interception of the aircraft, effectively shortens the aircraft recovery time, reduces the exposure risk, and has a small ground projection area under the same load condition, so that the required take-off space is smaller.

[0023] 2、The variable-structure aircraft for rapid take-off and landing of the bionic eagle falcon provided by the application can store energy before take-off, the second motor is started, the first gear is driven to rotate by the second motor, the first gear is always in meshing state with the second gear set, the first gear generates a circumferential thrust on the second gear set, the second gear set and the guide shaft are moved from the energy storage position to the energy release position, at this time, the second gear set is also meshed with the third gear, and then power is transmitted to the two transmission shafts, so that the two swing arm groups are driven to move away from each other to store energy in the energy storage member, when bouncing and taking off, the third gear rotates in the opposite direction, generates a reverse thrust on the second gear set, and the second gear set returns to the energy release position, at this time, the second gear set and the second gear set are disengaged, the whole driving process does not need to additionally increase a power source, energy consumption is saved, and the second motor will not rotate in the opposite direction when taking off, so that the conditions of energy dissipation and burning of electronic components due to counter electromotive force are avoided.

[0024] 3、The variable-structure aircraft for rapid take-off and landing of the bionic eagle falcon provided by the application can realize rapid landing of the aircraft by using the blocking net, effectively improve the recovery efficiency, when the aircraft completes a task, if the return location is provided with the blocking net, the aircraft can identify the blocking net Apriltag code by using the high-definition holder, calculate the relative position of the aircraft and the blocking net, and solve the optimal landing attitude of the current flight state, then the aircraft can be aligned with the blocking net and rapidly descend at a large pitch angle, the front and rear hook structures are adjusted to capture the blocking net, and the aircraft is successfully recovered, the recovery time of the aircraft is effectively shortened, the exposure risk is reduced, and the design of capturing the blocking net can reduce the requirement of the aircraft on the landing environment.

[0025] 4、The variable-structure aircraft for rapid take-off and landing of the bionic eagle falcon provided by the application is flexible and has strong impact resistance, the bounce energy storage mechanism can be remotely controlled to store energy by using a spring, the design can be used to adjust the attitude and control the center of gravity during flight, secondly, if the bottom structure collides with the outside environment during flight, the spring structure can absorb the impact, and the bounce energy storage mechanism can be released in any case to resist the impact generated by rapid landing.

[0026] 5、The variable-structure aircraft for rapid take-off and landing of the bionic eagle falcon provided by the application has strong concealment and adaptability, the opening and closing angles of the front and rear hook structures are controlled to adjust the take-off attitude and the ejection angle of the aircraft, so that the aircraft can be ejected on an inclined surface, and the function of ejecting the aircraft on a rugged road surface is ensured.

[0027] 6、The variable-structure aircraft for rapid take-off and landing of the bionic eagle falcon provided by the application adopts a spring energy storage structure, can provide initial kinetic energy for the aircraft, bounces the aircraft with folded arms to a certain height to avoid obstacles, then the arms are rapidly unfolded, the rotors are rapidly rotated to provide lift, and the aircraft starts to perform flight operation. BRIEF DESCRIPTION OF DRAWINGS

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

[0029] Figure 2 Schematic diagram of the bionic falcon-like rapid 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 Partial exploded view;

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

[0033] Figure 6 yes Figure 1 Cross-sectional view of the middle machine arm;

[0034] Figure 7 yes Figure 2 Enlarged view of area A in the middle;

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

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

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

[0038] Figure 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. bouncing 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. latch; 33. slot; 34. elastic member; 35. first cam; 36. second cam; 37. transmission lever. DETAILED DESCRIPTION

[0040] Specific implementation one: combined Figures 1 to 4 In this embodiment, the embodiment includes a rack 1 and a bounce platform 5, the rack 1 is provided with a plurality of rotating mechanisms 2 uniformly distributed in the circumferential direction, the rotating mechanism 2 includes a first motor 3 and a rotor 4 mounted on the driving end of the first motor 3, the bounce platform 5 is connected to the bottom of the rack 1 through two bounce energy storage mechanisms symmetrically distributed, the bounce energy storage mechanism is used to push the rack 1 and the bounce platform 5 away from each other to realize bounce take-off, the bounce platform 5 is connected with a hook structure 21 for capturing a barrier net, the barrier net is captured through the hook structure 21 to realize rapid landing, the rack 1 includes a frame body 27 and a machine arm 28 rotatably connected to the frame body 27, the machine arm 28 is connected with a base 29, and the first motor 3 is fixedly installed on the base 29.

[0041] The rack 1 concentrates battery power supply and electronic components, including GPS module, flight main control module, remote control signal receiver, microcomputer, cloud platform hanging cabin, electronic speed regulator, etc., the barrier net is designed as a double-layer structure, the upper layer is a large-interval high-strength nylon net, responsible for blocking the aircraft landing and buffering and absorbing kinetic energy, the lower layer is a low-density high-strength plate, the top surface is drawn with a clear Apriltag code, which can provide accurate position information for the aircraft, the upper and lower layers are isolated by a support column, the whole barrier net is low-visibility camouflage, has strong concealment, if the return site is arranged with a barrier net, the aircraft can identify the barrier net Apriltag code by using the high-definition cloud platform, calculate the relative position of the aircraft and the barrier net and solve the optimal landing attitude of the current flight state, then the aircraft can align the barrier net and rapidly descend at a large pitch angle, capture the barrier net through the adjustment of the front and rear hook structures 21, and the aircraft stops successfully, effectively shortens the aircraft recovery time, reduces the exposure risk, the design of capturing the barrier net can reduce the requirements of the aircraft on the landing environment, when falling, the hook structure 21 captures the barrier net, the first motor 3 rapidly closes the throttle, the two hook structures 21 are tightened at the same time, the aircraft adjusts the attitude and stops after keeping stable, and the energy storage member 10 weakens the impact force on the aircraft in the vertical direction during the recovery process.

[0042] The variable-structure aircraft of the embodiment realizes the rapid take-off of the bionic hawk falcon in rugged and narrow environment through the bounce energy storage mechanism and the bounce platform, has lower requirements on the environment and stronger adaptability during take-off, is not affected by complex terrain during take-off, has faster take-off speed, captures the barrier net through the hook structure, can realize the rapid interception of the aircraft, effectively shortens the aircraft recovery time, reduces the exposure risk, the machine arm is folded before launching, has small ground projection area under the same load condition, and needs smaller take-off space.

[0043] Specific implementation two: combined Figure 5 , Figure 8 ,Figure 9 、 Figure 10 The present embodiment is described. The present embodiment differs 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 that are rotatably connected. The top end of the first rocker arm 7 is fixedly connected to the transmission shaft 9 on the frame 1, and 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. 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 Installed on the frame 1, 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 to a fourth gear 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 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 brings the two rocker arm groups 6 closer to each other, the third gear 15 drives the second gear set 14 from the energy storage position to the energy release position. In the energy-releasing 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 remains engaged with the first gear 13 and moves circumferentially around the first gear 13. When in the energy-releasing position, the second gear set 14 only engages with the first gear 13. When in the energy-storing position, the second gear set 14 engages with both the first gear 13 and the third gear 15. Through the movement of the second gear set 14, one-way power transmission can be achieved without the need for another power source. The other components and connection relationships are the same as those in the first 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 meshing with the second gear set 14. The first gear 13 will generate circumferential thrust on the second gear set 14, causing the second gear set 14 and the guide shaft 17 to 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 transfers power to the two transmission shafts 9, thereby driving the two swing arm groups away from each other to store energy in the energy storage member 10. During a bouncy takeoff, the third gear 15 will rotate in the opposite direction, generating a reverse thrust on the second gear set 14, causing the second gear set 14 to return to the energy release position. At this time, the second gear set 14 and the third gear 15 are disengaged. The entire driving process does not require an additional power source, saving energy consumption. In addition, during takeoff, the second motor 11 will not be driven to rotate in the opposite direction, avoiding the dissipation of back electromotive force and the burning of electronic components.

[0045] Specific implementation method three: Combination Figure 8 This embodiment differs from the second embodiment in 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, and the diameter of the second output tooth 20 is smaller than the diameter of the third gear 15. The second input tooth 19 meshes with the first gear 13, and the second output tooth 20 meshes with the third gear 15 when it moves to the energy storage position. In this embodiment, the first gear 13 and the third gear 15 are staggered. By adjusting the ratio of the second input tooth 19 to the second output tooth 20, the reduction ratio is increased by one stage. This not only enables one-way power transmission but also reduces speed, making the rotation of the transmission shaft 9 more stable and providing better performance. The 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 differs from the first embodiment in that it comprises two symmetrically arranged hook structures 21. These two hook structures 21 are rotatably mounted on the springboard 5 and are respectively connected to the drive ends of the first drive member 22. The first drive member 22 is used to drive the hook structures 21 to rotate to adjust the takeoff attitude and to adjust the degree of opening and closing according to the landing attitude to capture the arresting net. There are two first drive members 22, one for each hook structure 21. The first drive members 22 are also mounted on the springboard 5. The springboard 5 is closer to the ground, so the hook structures 21 are smaller in size, which can reduce the overall weight and the load of the aircraft, thereby ensuring the flight range. The first drive member 22 drives the hook structures 21 to rotate, allowing the hook structures 21 to support uneven surfaces or inclined planes, ensuring uniform force on the frame 1, enabling the aircraft to take off smoothly in different locations and a wider range of applications. The other components and connection relationships are the same as those of the first embodiment.

[0047] Specific implementation method five: Combination Figure 9 This embodiment differs from the fourth embodiment in that the first driving member 22 is a first servo, the driving end of which is connected to a fifth gear 23. The hook structure 21 is connected to a sixth gear 24 that meshes with the fifth gear 23. The diameter of the sixth gear 24 is larger than that of the fifth gear 23. By adjusting the ratio of the sixth gear 24 to the fifth gear 23, the reduction ratio can be increased by one stage, reducing the rotation speed of the hook structure 21 and achieving more stable operation. The remaining components and connections are the same as those in the fourth embodiment.

[0048] Specific implementation method six: combination Figure 3 This embodiment differs from the first embodiment in that one of the frame 1 and the jumping platform 5 is connected to an electromagnetic snap 25, and the other is connected to a hook 26 that cooperates with the electromagnetic snap 25. In this embodiment, the electromagnetic snap 25 is provided on the jumping platform 5, and the hook 26 is provided on the frame 1. When the energy storage member 10 is stretched by the two rocker arm assemblies 6 to complete energy storage, the electromagnetic snap 25 and the hook 26 engage. The electromagnetic snap 25 and the snap are rigidly connected, used to lock, connecting the jumping platform 5 and the frame 1 as a whole, with the center of gravity closer to the plane of the rotor 4 to prevent shaking in the air. The other components and connection relationships are the same as those in the first embodiment.

[0049] Specific implementation method seven: combination Figure 4 、 Figure 7 、 Figure 11This embodiment differs from the first embodiment in that it further includes a tensioning member 30 connected between the arm 28 and the frame 27. The tensioning member 30 exerts a pulling force to cause the arm 28 to unfold. A second driving member 31 is connected to the frame 1. The driving end of the second driving member 31 is connected to the arm 28 and is used to drive the arm 28 to fold and retract. The tensioning member 30 is a pull cord. The interaction between the pull cord and the second driving member 31 enables the folding and unfolding of the arm 28. Other components and connections are the same as those in the first embodiment.

[0050] Specific implementation method eight: combination Figure 4 、 Figure 7 、 Figure 11 This embodiment is described. This embodiment differs from the seventh embodiment in that the frame 27 includes a horizontally sliding latch 32. Specifically, the frame 27 includes a horizontally disposed slide groove, within which the latch 32 slides. The arm 28 includes a slot 33 for engaging with the latch 32. When the arm 28 rotates to a horizontal position, 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 toward the slot 33. The elastic member 34 is a spring. Under the push of the elastic member 34, the latch 32 is inserted into the slot 33, thereby limiting the rotation of the arm 28 and locking the arm 28 to maintain the extended position. 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 differs from the seventh embodiment in that the second driving member 31 is a second servo. A first cam 35 is fixedly connected to the driving end of the second servo. A second cam 36 is fixedly connected to the arm 28. A transmission lever 37 is rotatably connected to the frame 27. One end of the transmission lever 37 abuts the first cam 35, and the other end of the transmission lever 37 abuts the second cam 36. By rotating the cam driven by the second servo, the arm 28 can be expanded under the action of the tensioning member 30. The transmission lever 37 serves as an intermediate connecting component to transmit the applied force. The remaining components and connections are the same as those of the seventh embodiment.

[0052] Specific implementation method ten: Combination Figure 1 、 Figure 2 This embodiment differs from the first embodiment in that the arm 28 is a four-bar linkage structure. This four-bar linkage provides greater stability, resulting in higher overall strength and improved performance. The remaining components and connections are the same as those in the first embodiment.

[0053] The use method of the embodiment:

[0054] Before taking off, the arm 28 is in a folded state, first start the second motor 11, the second motor 11 drives the first gear 13 to rotate, the first gear 13 drives the second input tooth 19 to rotate at the same time and applies a circumferential force to the second input tooth 19, pushes the second input tooth 19, the guide shaft 17 and the second output tooth 20 to move from the energy releasing position to the energy storage position, at this time the second output tooth 20 is engaged with the third gear 15, the power can be transmitted to make the transmission shaft 9 rotate, the two transmission shafts 9 are reversely rotated through the engagement of the fourth gear 18, and then drive the two rocker arm groups 6 to move away from each other, stretch the energy storage member 10 to store energy, after the energy storage is completed, the electromagnetic buckle 25 is connected with the hook 26, and the locking is performed.

[0055] At the same time, the first steering engine can be started, the first steering engine drives the hook claw structure 21 to rotate, the hook claw structure 21 is supported on the ground, the take-off attitude of the aircraft is adjusted, then the electromagnetic buckle 25 is controlled, the electromagnetic buckle 25 is separated from the hook 26, the energy storage member pulls the two rocker arm groups 6 to move close to each other, so as to push the aircraft to bounce, after the aircraft reaches a certain height, the second steering engine is started, the second steering engine 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 clamping groove 33 is opposite to the clamping pin 32, the clamping pin 32 is inserted into the clamping groove 33 under the drive of the elastic member 34 to lock the arm 28, then the first motor 3 is started to drive the rotor 4 to rotate, and the aircraft flies.

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

Claims

1. A bionic falcon-like rapid take-off and landing variable configuration aircraft, characterized in that: include: A frame (1), wherein the frame (1) is provided with a plurality of rotating mechanisms (2) uniformly distributed along the circumference, 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); The bouncing energy storage mechanism comprises two symmetrically distributed rocker arm groups (6) and an energy storage member (10), wherein 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), and the bottom end of the second rocker arm (8) is rotatably connected to the bouncing platform (5), and 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) being connected to the two rocker arm groups (6) via a gear group (12), the second motor (11) being used to drive the two rocker arm groups (6) away from each other, the gear group (12) comprising a first gear (13), a second gear group (14) and a third gear (15), the first gear (13) being mounted on a driving end of the second motor (11), the frame (1) having an arcuate groove (16) with the first gear (13) as a center, a guide shaft (17) being slidably mounted in the arcuate groove (16), the second gear group (14) being mounted on the guide shaft (17) and meshing 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 to a fourth gear (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 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.

2. The bionic falcon-like rapid take-off and landing adaptable aircraft according to claim 1, 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 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), and the second output tooth (20) is meshed with the third gear (15) when it moves to the energy storage position.

3. 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). 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 blocking net.

4. The bionic falcon-like rapid take-off and landing variable configuration aircraft according to claim 3, 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 larger than the diameter of the fifth gear (23).

5. The bionic falcon-like rapid take-off and landing adaptable 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).

6. A bionic falcon-like rapid take-off and landing adaptable aircraft according to any one of claims 1 to 5, 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 to cause 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.

7. The bionic falcon-like rapid take-off and landing variable configuration aircraft according to claim 6, 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).

8. The bionic falcon-like rapid take-off and landing adaptable aircraft according to claim 6, 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 the first cam (35), the machine arm (28) is fixedly connected to the second cam (36), and the frame (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).

9. A bionic falcon-like rapid take-off and landing adaptable aircraft according to any one of claims 1 to 5, characterized in that: The machine arm (28) is a four-link structure.

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