Mother-son unmanned aerial vehicle

Abstract

The utility model discloses a mother-son unmanned aerial vehicle which comprises a mother machine and a son machine, first supports are fixedly installed on the two sides of the mother machine, blocking pieces are arranged at the front ends of the first supports, a second support is fixedly installed in the middle of the mother machine, an unlocking mechanism is installed in a machine body of the mother machine, a fixing locking ring is fixedly installed below the son machine, and the son machine is placed above the mother machine. The son aircraft wings are placed on the first support, the front edges of the son aircraft wings abut against the blocking pieces, the son aircraft body is placed on the second support, the second support abuts against the rear edges of the son aircraft wings, the front end of the middle of the mother aircraft is fixedly connected with the auxiliary support, the front end of the son aircraft body is placed on the auxiliary support, the fixing locking ring is connected to the unlocking mechanism, and the unlocking mechanism comprises an unlocking drive. The mother aircraft carries the son aircraft to lift off, the son aircraft is released in the air to serve as bait or target aircraft, the son aircraft adopts the gliding unmanned aerial vehicle, and the gliding unmanned aerial vehicle is low in cost and suitable for serving as the bait or target aircraft.

Description

Technical Field

[0001] The utility model belongs to the technical field of unmanned aerial vehicles and relates to a mother-and-son unmanned aerial vehicle. Background Art

[0002] With the development of unmanned aerial vehicle technology, unmanned aerial vehicles have gradually been applied in different fields such as agriculture, surveying, communication, and military fields. Especially in the military field, unmanned aerial vehicles can be used to perform dangerous tasks or as training target drones. During the process of acting as a target drone or performing tasks, once the unmanned aerial vehicle is shot down, it is likely to cause relatively large losses and the use cost is relatively high. Content of the Utility Model

[0003] In view of the above problems, the utility model provides a mother-and-son unmanned aerial vehicle, which well solves the problems in the prior art.

[0004] In order to achieve the above object, the technical scheme adopted by the utility model is as follows:

[0005] A mother-and-son unmanned aerial vehicle, comprising:

[0006] A mother aircraft, which is a fixed-wing unmanned aerial vehicle;

[0007] A son aircraft, which is a fixed-wing gliding unmanned aerial vehicle;

[0008] Two first brackets are respectively fixedly installed on both sides of the mother aircraft, and a blocking member is arranged at the front end of the first bracket;

[0009] A second bracket is fixedly installed in the middle of the mother aircraft, and a placement groove is formed at the upper end of the second bracket;

[0010] An unlocking mechanism is fixedly installed inside the fuselage of the mother aircraft;

[0011] A fixed lock ring is fixedly installed below the son aircraft;

[0012] Wherein, the son aircraft is placed above the mother aircraft, the wings of the son aircraft are respectively placed on the first brackets, and the leading edges of the wings of the son aircraft abut against the blocking member;

[0013] The fuselage of the son aircraft is placed in the placement groove of the second bracket, the second bracket abuts against the trailing edge of the wing of the son aircraft, and an auxiliary bracket is fixedly connected to the front end of the middle part of the mother aircraft, and the front end of the fuselage of the son aircraft is placed on the auxiliary bracket;

[0014] The fixed lock ring is connected to the unlocking mechanism, and the unlocking mechanism includes an unlocking drive, and the unlocking drive drives the unlocking mechanism to release the fixed lock ring.

[0015] Optionally, the unlocking mechanism further includes

[0016] A locking bracket, which is fixedly installed inside the fuselage of the mother aircraft;

[0017] A locking rod, which slidably penetrates through the locking bracket, and one end of the locking rod away from the locking bracket is connected to the unlocking drive output end;

[0018] Among them, the unlocking drive is a servo motor, the locking rod is an arc-shaped rod with an upward convex arc, during installation, the fixed locking ring is sleeved outside the locking rod, and the fixed locking ring is connected to the slave aircraft through a soft chain.

[0019] Optionally, a connecting rope is fixedly connected to the fixed locking ring, a tightening disc is rotatably installed inside the fuselage of the slave aircraft, the connecting rope is wound around the tightening disc, and the tightening disc is connected with a locking mechanism for locking the tightening disc.

[0020] Optionally, the locking mechanism includes,

[0021] A ratchet wheel, which is fixedly installed on the tightening disc;

[0022] A pawl, which is rotatably installed on the fuselage of the slave aircraft, and the pawl is connected with a return spring;

[0023] A turning knob, which is rotatably installed outside the fuselage of the slave aircraft, and the turning knob penetrates through the slave aircraft and is fixedly connected to the pawl rotating shaft;

[0024] Among them, the tightening disc is also connected with one of the turning knobs.

[0025] Optionally, a locking hole is formed inside the fuselage of the mother aircraft, and the locking rod is inserted into the locking hole when locked.

[0026] Optionally, the wings of the slave aircraft are folding wings, the trailing edge of the wings of the slave aircraft is hinged to the fuselage of the slave aircraft near one end of the fuselage of the slave aircraft, a latching mechanism is arranged between the leading edge of the wings of the slave aircraft near one end of the fuselage of the slave aircraft and the fuselage of the slave aircraft, and a wing pulling spring is arranged between the fuselage of the slave aircraft and the wings.

[0027] Optionally, the latching mechanism includes,

[0028] A locking ring, which is fixedly installed on the fuselage of the slave aircraft;

[0029] A locking pin, which is slidably installed on the wings of the slave aircraft;

[0030] Among them, a locking spring is arranged between the locking pin and the wings of the slave aircraft, and one side of the locking pin facing the locking ring is set as an inclined surface.

[0031] Optionally, the locking ring is fixedly connected with an arc-shaped rail having an arc-shaped chute in the middle, and the locking pin is slidably installed in the chute of the arc-shaped rail.

[0032] Optionally, an ejection spring is installed between the master machine and the slave machine.

[0033] Optionally, a locking through hole for the fixed locking ring to pass through is provided above the master machine, a cover is hinged outside the locking through hole, and a torsion spring is installed between the cover and the master machine.

[0034] Compared with the prior art, the utility model has the following beneficial effects:

[0035] 1. The master machine carries the slave machine into the air and releases the slave machine in the air as a decoy or a target drone. The slave machine adopts a gliding drone, which has a low cost and is suitable for acting as a decoy or a target drone.

[0036] 2. The fixed locking ring is used to fix the vertical position of the slave machine. By setting the tightening disc, after the fixed locking ring is locked, the connecting rope is tightened through the tightening disc, so that the fixed locking ring and the unlocking mechanism provide a tensioning force for the slave machine, reducing the shaking of the slave machine during flight and making the flight more stable.

[0037] 3. By setting the folding wings, the wings of the slave machine are folded backward, reducing the interference to the master machine during flight. After detachment, the wings automatically recover, reducing the possibility of interfering with the flight of the master machine during detachment. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Figure 1 is a schematic diagram of the overall structure of an embodiment of the utility model;

[0039] Figure 2 is a schematic diagram of the overall structure of another embodiment of the utility model;

[0040] Figure 3 is a schematic diagram of the structure of the unlocking mechanism part of an embodiment of the utility model;

[0041] Figure 4 is a schematic diagram of the structure of the catch mechanism part of an embodiment of the utility model.

[0042] Reference numerals: 11, master machine; 12, slave machine; 13, ejection spring; 14, locking through hole; 15, cover;

[0043] 21, first bracket; 211, blocking member; 22, second bracket; 23, auxiliary bracket;

[0044] 3. Unlocking mechanism; 31. Fixed locking ring; 311. Connecting rope; 312. Tightening disc; 313. Locking mechanism; 3131. Ratchet; 3132. Pawl; 3133. Rotating knob; 32. Unlocking drive; 33. Locking bracket; 34. Locking rod; 341. Locking hole;

[0045] 41. Latch mechanism; 411. Locking ring; 412. Locking pin; 413. Arc track. Specific embodiments

[0046] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with 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. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0047] Please refer to Figures 1 - 3 , a mother-and-child unmanned aerial vehicle disclosed in an embodiment of the present invention, including a mother aircraft 11 and a child aircraft 12. The mother aircraft 11 is a fixed-wing unmanned aerial vehicle, and the child aircraft 12 is a fixed-wing gliding unmanned aerial vehicle. First brackets 21 are fixedly installed on both sides of the mother aircraft 11, a blocking member 211 is provided at the front end of the first bracket 21, a second bracket 22 is fixedly installed in the middle of the mother aircraft 11, a placement groove is opened at the upper end of the second bracket 22, an unlocking mechanism 3 is installed in the fuselage of the mother aircraft 11, a fixed locking ring 31 is fixedly installed below the child aircraft 12, the child aircraft 12 is placed above the mother aircraft 11, the wings of the child aircraft 12 are respectively placed on the first brackets 21, the leading edges of the wings of the child aircraft 12 abut against the blocking member 211, the fuselage of the child aircraft 12 is placed in the placement groove of the second bracket 22, the second bracket 22 abuts against the trailing edges of the wings of the child aircraft 12, an auxiliary bracket 23 is fixedly connected to the front end of the middle of the mother aircraft 11, the front end of the fuselage of the child aircraft 12 is placed on the auxiliary bracket 23, the fixed locking ring 31 is connected to the unlocking mechanism 3, and the unlocking mechanism 3 includes an unlocking drive 32, and the unlocking drive 32 drives the unlocking mechanism 3 to release the fixed locking ring 31.

[0048] Specifically, the child aircraft 12 is arranged above the mother aircraft 11, and the child aircraft 12 is locked above the mother aircraft 11 through the first bracket 21, the second bracket 22 and the unlocking mechanism 3. When it is necessary to release the child aircraft 12, the fixed locking ring 31 is unlocked through the unlocking mechanism 3. The child aircraft 12 is a fixed-wing gliding unmanned aerial vehicle. After the unlocking mechanism 3 releases the lock, the child aircraft 12 breaks away from the mother aircraft 11 and glides freely.

[0049] In this way, the mother aircraft 11 carries the child aircraft 12 into the air and releases the child aircraft 12 in the air as a decoy or target aircraft. The child aircraft 12 uses a gliding unmanned aerial vehicle, which has a low cost and is suitable for acting as a decoy or target aircraft.

[0050] In some feasible ways, the first bracket 21 is a rod-shaped bracket, which is installed above the wing of the mother aircraft 11 to support the wing of the sub-aircraft 12. The blocking member 211 is a protrusion provided at the front end of the first bracket 21. The second bracket 22 is installed on the fuselage of the mother aircraft 11. A U-shaped groove adapted to place the fuselage of the sub-aircraft 12 is opened at the upper end of the second bracket 22. The second bracket 22 abuts against the trailing edge of the wing of the sub-aircraft 12 and the blocking member 211 abutting against the leading edge of the wing fix the horizontal position of the sub-aircraft 12. At the same time, the vertical position of the sub-aircraft 12 is fixed by the unlocking mechanism 3 and the fixing lock ring 31. During flight, the sub-aircraft 12 is fixed to the mother aircraft 11 and keeps the same speed as the mother aircraft 11. When it is necessary to release the sub-aircraft 12, the unlocking drive 32 drives the unlocking mechanism 3 to release the fixing lock ring 31. The sub-aircraft 12 flies upward at the speed provided by the mother aircraft 11, breaks away from the blocking member 211 and the second bracket 22, and glides freely. Then, the mother aircraft 11 is maneuvered away from the sub-aircraft 12.

[0051] In some feasible ways, the unlocking mechanism 3 can be selected as a bolt, and the unlocking drive 32 can be selected as an electric push rod. The fixing lock ring 31 is sleeved outside the bolt, and the fixing lock ring 31 is disengaged by pulling the bolt through the electric push rod.

[0052] As a specific implementation manner of a mother-daughter unmanned aerial vehicle provided by the application, please refer to Figure 3 , the unlocking mechanism 3 further includes a locking frame 33 and a locking rod 34. The locking frame 33 is fixedly installed inside the fuselage of the mother aircraft 11. The locking rod 34 slidably penetrates through the locking frame 33. One end of the locking rod 34 away from the locking frame 33 is connected to the output end of the unlocking drive 32. Among them, the unlocking drive 32 is a servo motor, and the locking rod 34 is an arc-shaped rod with an upward convex arc. During installation, the fixing lock ring 31 is sleeved outside the locking rod 34, and the fixing lock ring 31 is connected to the sub-aircraft 12 through a soft chain.

[0053] Generally speaking, the locking rod 34 is set as an arc-shaped rod, and the servo motor rotates to drive the locking rod 34 to slide along the locking frame 33, so that the fixing lock ring 31 is disengaged. A soft chain is provided between the fixing lock ring 31 and the sub-aircraft 12. Cooperating with the arc-shaped locking rod 34, it is convenient for the fixing lock ring 31 to slide out of the locking rod 34 during unlocking, reducing the possibility that the fixing lock ring 31 cannot be disengaged due to the locking rod 34 not being driven in place.

[0054] In some feasible ways, the locking frame 33 is a rectangular plate, a through hole is opened on the locking frame 33, the locking rod 34 penetrates through the through hole, and the fixing lock ring 31 is a circular ring.

[0055] Furthermore, a locking hole 341 is opened inside the fuselage of the mother aircraft 11, and the locking rod 34 is inserted into the locking hole 341 when locked.

[0056] It should be understood that by providing the locking hole 341, the free end of the locking rod 34 is inserted into the locking hole 341 when in the locked position, reducing the possibility of the fixed locking ring 31 coming off during flight.

[0057] As another specific embodiment of the mother-daughter UAV provided by the application, a connecting rope 311 is fixedly connected to the fixed locking ring 31. A winding disc 312 is rotatably installed inside the fuselage of the daughter UAV 12. The connecting rope 311 is wound around the winding disc 312. The winding disc 312 is connected with a locking mechanism 313 for locking the winding disc 312.

[0058] Combined with the specific usage scenario, the fixed locking ring 31 is used to fix the vertical position of the daughter UAV. By providing the winding disc 312, after the fixed locking ring 31 is locked, the connecting rope 311 is tightened by the winding disc 312, so that the fixed locking ring 31 and the unlocking mechanism 3 provide a pulling force for the daughter UAV 12, reducing the shaking of the daughter UAV 12 during flight and making the flight more stable.

[0059] Furthermore, the locking mechanism 313 includes a ratchet wheel 3131 and a ratchet pawl 3132. The ratchet wheel 3131 is fixedly installed on the winding disc 312. The ratchet pawl 3132 is rotatably installed on the fuselage of the daughter UAV 12. The ratchet pawl 3132 is connected with a return spring. Two turning buttons 3133 are rotatably installed on the outer side of the fuselage of the daughter UAV 12. The turning buttons 3133 penetrate the fuselage of the daughter UAV 12 and are respectively fixedly connected to the rotating shaft of the ratchet pawl 3132 and the rotating shaft of the winding disc 312.

[0060] It should be understood that by providing the ratchet wheel 3131 and the ratchet pawl 3132, during the process of tightening the winding disc 312 by rotating the turning button 3133, the winding disc 312 rotates unidirectionally in part, facilitating the fixing of the position of the winding disc 312. When it is necessary to release the winding disc 312, by rotating the turning button 3133 of the ratchet pawl 3132, the ratchet wheel 3131 and the ratchet pawl 3132 are temporarily disengaged.

[0061] As a specific embodiment of the mother-daughter UAV provided by the application, please refer to Figure 2 and Figure 4 , the wing of the daughter UAV 12 is a folding wing. One end of the trailing edge of the wing of the daughter UAV 12 close to the fuselage of the daughter UAV 12 is hinged to the fuselage of the daughter UAV 12. A snap lock mechanism 41 is provided between one end of the leading edge of the wing of the daughter UAV 12 close to the fuselage of the daughter UAV 12 and the fuselage of the daughter UAV 12. A wing-pulling spring is provided between the fuselage of the daughter UAV 12 and the wing.

[0062] In combination with a specific usage scenario, during flight, the slave aircraft 12 is located above the master aircraft 11 and follows the master aircraft 11 in flight. The lift generated by the wings of the slave aircraft 12 may affect the flight state of the master aircraft 11. At the same time, the relatively large wings may also interfere with the flight of the master aircraft 11 when the slave aircraft is released. By setting up folding wings, the wings of the slave aircraft 12 are folded backward to reduce interference with the master aircraft 11 during flight. After detachment, the wings automatically recover to reduce the possibility of interfering with the flight of the master aircraft 11 during detachment.

[0063] Furthermore, the snap lock mechanism 41 includes a locking ring 411 and a locking pin 412. The locking ring 411 is fixedly installed on the fuselage of the slave aircraft 12, and the locking pin 412 is slidably installed on the wing of the slave aircraft 12. A locking spring is arranged between the locking pin 412 and the wing of the slave aircraft 12, and one side of the locking pin 412 facing the locking ring 411 is set as an inclined surface.

[0064] It should be understood that by setting up the locking ring 411 and the locking pin 412, after the wing is reset, through collision, the locking pin 412 is snapped into the locking ring 411 to complete the locking.

[0065] Furthermore, the locking ring 411 is fixedly connected with an arc-shaped rail 413 with an arc-shaped chute arranged in the middle, and the locking pin 412 is slidably installed in the chute of the arc-shaped rail 413.

[0066] It should be understood that by setting up the arc-shaped rail 413, during the process of the wing resetting, the movement of the locking pin 412 along the chute of the arc-shaped rail 413 reduces the possibility that the locking ring 411 and the locking pin 412 cannot collide and lock accurately.

[0067] In some feasible ways, the wing pulling spring can be selected as a torsion spring installed at the position of the wing hinge shaft. The first bracket 21 is installed on both sides of the fuselage of the master aircraft 11, and the blocking member 211 restricts the wing to keep the wing in a folded state.

[0068] As a specific implementation manner of a mother-daughter unmanned aerial vehicle provided by the application, please refer to Figure 2 , an ejection spring 13 is installed between the master aircraft 11 and the slave aircraft 12.

[0069] It should be understood that by setting up the ejection spring 13, when the slave aircraft 12 detaches, the slave aircraft 12 is quickly separated from the master aircraft 11 through the ejection spring 13 to reduce the interference of the slave aircraft 12 on the flight of the master aircraft 11.

[0070] As a specific implementation manner of a mother-daughter unmanned aerial vehicle provided by the application, please refer to Figure 3 , a locking through hole 14 for the fixed lock ring 31 to pass through is arranged above the master aircraft 11. A cover 15 is hinged outside the locking through hole 14, and a torsion spring is installed between the cover 15 and the master aircraft 11.

[0071] It should be understood that by setting the cover 15, after the slave unit 12 is detached, the cover 15 automatically resets to cover the locking through hole 14, preventing foreign objects from falling in.

[0072] Although the present utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or perform equivalent replacements on some of the technical features. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. A mother-and-child drone, characterized in that: include: A mother machine, wherein the mother machine is a fixed-wing UAV; A sub-machine, wherein the sub-machine is a fixed-wing gliding UAV; A first bracket, wherein two first brackets are fixedly mounted on both sides of the mother machine, and a blocking member is disposed at the front end of the first bracket; A second bracket, the second bracket is fixedly installed in the middle of the mother machine, and a placement slot is opened at the upper end of the second bracket; An unlocking mechanism, the unlocking mechanism is fixedly installed in the body of the mother machine; A fixed locking ring, the fixed locking ring is fixedly installed below the sub-machine; The sub-machine is placed above the mother machine, the wings of the sub-machine are respectively placed on the first brackets, and the leading edges of the wings of the sub-machine are against the blocking member; The fuselage of the sub-machine is placed in the placement groove of the second bracket, the second bracket is against the trailing edge of the wing of the sub-machine, the front end of the middle part of the mother machine is fixedly connected to an auxiliary bracket, and the front end of the fuselage of the sub-machine is placed on the auxiliary bracket; The fixed locking ring is connected to the unlocking mechanism, and the unlocking mechanism includes an unlocking drive, and the unlocking drive drives the unlocking mechanism to release the fixed locking ring.

2. The mother-child drone according to claim 1, characterized in that: The unlocking mechanism further comprises: A locking frame, the locking frame is fixedly installed in the mother machine body; A locking rod, the locking rod slidably passing through the locking frame, and one end of the locking rod away from the locking frame is connected to the unlocking drive output end; Among them, the unlocking drive is a steering gear, and the locking rod is an arc-shaped rod with an upward convex arc. During installation, the fixed locking ring is sleeved on the outside of the locking rod, and the fixed locking ring is connected to the sub-machine through a soft chain.

3. The mother-child drone according to claim 1, characterized in that: The fixed lock ring is fixedly connected with a connecting rope, a tightening disk is rotatably installed in the fuselage of the sub-machine, the connecting rope is wound around the tightening disk, and the tightening disk is connected with a locking mechanism for locking the tightening disk.

4. The mother-child drone according to claim 3, characterized in that: The locking mechanism comprises: A ratchet wheel, the ratchet wheel being fixedly mounted on the tightening disc; A pawl, the pawl being rotatably mounted on the sub-machine body and connected to a return spring; A rotating button, the rotating button is rotatably mounted on the outside of the sub-machine body, the rotating button passes through the sub-machine and is fixedly connected to the pawl rotating shaft; Wherein, the tightening disk is also connected to a rotating knob.

5. The mother-child drone according to claim 2, characterized in that: A locking hole is provided on the inner side of the mother machine body, and the locking rod is inserted into the locking hole when being locked.

6. The mother-child drone according to claim 1, characterized in that: The sub-machine wing is a folding wing, the trailing edge of the sub-machine wing is hinged to the sub-machine fuselage near one end of the sub-machine fuselage, a latch mechanism is arranged between the leading edge of the sub-machine wing near one end of the sub-machine fuselage and the sub-machine fuselage, and a wing pulling spring is arranged between the sub-machine fuselage and the wing.

7. The mother-child drone according to claim 6, characterized in that: The latch mechanism comprises: A locking ring, the locking ring being fixedly mounted on the sub-unit body; A locking pin, the locking pin being slidably mounted on the wing of the sub-machine; Wherein, a locking spring is arranged between the locking pin and the wing of the sub-machine, and a side of the locking pin facing the locking ring is arranged as an inclined surface.

8. The mother-child drone according to claim 7, characterized in that: The locking ring is fixedly connected to an arc-shaped rail with an arc-shaped sliding groove in the middle, and the locking pin is slidably installed in the sliding groove of the arc-shaped rail.

9. A mother-child drone according to any one of claims 1 to 8, characterized in that: A ejection spring is installed between the main machine and the sub-machine.

10. A mother-child drone according to any one of claims 1 to 8, characterized in that: A locking through hole for a fixed locking ring to pass through is arranged above the mother machine, a cover is hingedly connected to the outer side of the locking through hole, and a torsion spring is installed between the cover and the mother machine.

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