Missile and unmanned aerial vehicle body separation device and unmanned aerial vehicle

Abstract

The application discloses a missile and unmanned aerial vehicle body separation device and an unmanned aerial vehicle, and relates to the technical fields of unmanned aerial vehicles and missiles.The device comprises a missile body flange, one side of the missile body flange being used for being connected with the tail of a missile; a body flange, one side of the body flange being used for being connected with the end of an unmanned aerial vehicle body; a wrapping tape combination, the wrapping tape combination comprising a wrapping tape and a plurality of clamping blocks, the wrapping tape being connected to form a ring-shaped structure through a cuttable structure, the plurality of clamping blocks being distributed in a circumferential direction on the inner side of the ring-shaped structure when the wrapping tape forms the ring-shaped structure, and a clamping groove being arranged on the inner circumferential surface of the clamping blocks; a separation spring, the separation spring being arranged between the missile body flange and the body flange, the clamping groove being capable of accommodating the missile body flange and the body flange after the separation spring is compressed; and a pulling spring, the pulling spring being arranged between the wrapping tape combination and the end of the unmanned aerial vehicle body; the separation device realizes the quick separation of the missile and the unmanned aerial vehicle body through the cuttable structure, and realizes the quick attack function of the missile and unmanned aerial vehicle integrated aircraft.

Description

Technical Field

[0001] This invention belongs to the field of unmanned aerial vehicle (UAV) and missile technology, and more specifically, relates to a missile-to-UAV separation device and a UAV. Background Technology

[0002] Drones and missiles are widely used. Small drones have advantages such as portability, strong reconnaissance capabilities, strong environmental adaptability, and long flight time, but they also have disadvantages such as weak strike capabilities. Equipping drones with small missiles would improve strike capabilities, but this would result in shorter strike range and a lack of reconnaissance capabilities. Therefore, how to combine the advantages of drones and missiles to achieve integrated reconnaissance and strike capabilities in small aircraft is a technical challenge in the development of such aircraft. Summary of the Invention

[0003] The purpose of this invention is to address the shortcomings of existing technologies by providing a missile-drone separation device and a drone. This separation device achieves rapid separation of the missile and drone body through a severable structure, enabling the rapid strike capability of the integrated missile-drone aircraft.

[0004] To achieve the above objectives, the present invention provides a missile-to-UAV airframe separation device, comprising:

[0005] A missile body flange, one side of which is used to connect to the tail of the missile;

[0006] A body flange, one side of which is used to connect to the end of the UAV body;

[0007] A strap assembly includes a strap and multiple locking blocks. The strap is connected to form a ring structure through a cuttable structure. When the strap forms a ring structure, the multiple locking blocks are distributed circumferentially on the inner side of the ring structure. The inner circumference of each locking block is provided with a locking groove.

[0008] A separation spring is provided between the projectile flange and the body flange. When the separation spring is compressed, the slot can accommodate the projectile flange and the body flange.

[0009] A tension spring is disposed between the end of the strap assembly and the drone body.

[0010] Optionally, the cuttable structure includes an explosive bolt, with perforated pins connected to both ends of the explosive bolt, and the perforated pins being connected to the end of the strap.

[0011] Optionally, two straps are provided, each strap is semi-circular, and each end of the strap is provided with a pin sleeve. The perforated pin passes through the pin sleeve, and adjacent perforated pins are connected by the explosion bolt.

[0012] Optionally, the inner side of the strap is provided with multiple locking blocks, and the side of two adjacent locking blocks near the end of the drone body is connected to the pull spring.

[0013] Optionally, the perforated pin has a through hole, and the end of the explosion bolt passes through the through hole and extends to the outside of the strap.

[0014] Optionally, it also includes a fairing, which is tubular, with its two ends used for connecting the outer periphery of the missile's tail and the outer periphery of the UAV's body, respectively. The missile body flange, the body flange, and the strap assembly are disposed inside the fairing.

[0015] Optionally, the fairing includes two sub-fairings, each with a semi-circular cross-section, and the two sub-fairings are detachably connected.

[0016] Optionally, both the projectile flange and the body flange are hollow annular flanges.

[0017] Optionally, the other side of the projectile flange and the other side of the body flange are fitted together to form a V-shaped surface structure with a cross-section of 60°.

[0018] The present invention also provides a drone, including the aforementioned missile and drone body separation device.

[0019] This invention provides a missile-UAV separation device and a UAV, the advantages of which are: the separation device has a simple structure, the missile and the UAV are respectively equipped with a missile body flange and a UAV body flange, which form a V-shaped structure after docking and are connected by a strap assembly; a tension spring is used to realize the movement of the strap towards the body during the strap separation process, and a separation spring is used to realize the separation of the missile and the UAV body; the separation device has a compact structure, is easy to install, and can quickly complete the separation of the missile and the UAV body.

[0020] Other features and advantages of the present invention will be described in detail in the following detailed description section. Attached Figure Description

[0021] The above and other objects, features and advantages of the present invention will become more apparent from the more detailed description of exemplary embodiments of the invention in conjunction with the accompanying drawings, wherein the same reference numerals generally represent the same components in the exemplary embodiments of the invention.

[0022] Figure 1A schematic diagram of a missile-to-UAV separation device according to an embodiment of the present invention is shown.

[0023] Figure 2 A schematic diagram of the tail section of a missile according to an embodiment of the present invention is shown.

[0024] Figure 3 A schematic diagram of the end of a drone body according to an embodiment of the present invention is shown.

[0025] Figure 4 A schematic diagram of the structure of a strap assembly according to an embodiment of the present invention is shown.

[0026] Figure 5 A schematic diagram of the structure of a strap according to an embodiment of the present invention is shown.

[0027] Figure 6 A schematic diagram of the card block structure according to an embodiment of the present invention is shown.

[0028] Figure 7 A schematic diagram of a pin with a hole is shown according to an embodiment of the present invention.

[0029] Figure 8 A schematic diagram of the fairing structure according to an embodiment of the present invention is shown.

[0030] Explanation of reference numerals in the attached figures:

[0031] 1. Missile body flange; 2. Missile; 3. Airframe flange; 4. Packing tape assembly; 5. Packing tape; 6. Clamping block; 7. Clamping slot; 8. Separation spring; 9. Pulling spring; 10. Explosive bolt; 11. Pin with hole; 12. Fairing; 13. UAV airframe; 14. Pin sleeve; 15. Through hole. Detailed Implementation

[0032] Preferred embodiments of the invention will now be described in more detail. While preferred embodiments of the invention are described below, it should be understood that the invention can be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that the invention will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0033] This invention provides a missile-to-UAV airframe separation device, comprising:

[0034] The missile body flange has one side for connection to the tail of the missile.

[0035] Body flange, one side of which is used to connect to the end of the drone body;

[0036] The strap assembly includes a strap and multiple locking blocks. The strap is connected to form a ring structure through a cuttable structure. When the strap forms a ring structure, the multiple locking blocks are distributed circumferentially on the inner side of the ring structure. The locking blocks are provided with locking grooves on their inner circumference.

[0037] The separation spring is located between the projectile flange and the body flange. After the separation spring is compressed, the slot can accommodate both the projectile flange and the body flange.

[0038] A tension spring is installed between the end of the strap assembly and the drone body.

[0039] Specifically, when the missile is restricted by the tape assembly, the separation device uses a ring structure formed by the tape and the cuttable structure. Multiple locking blocks are located within this ring structure, and the inner side of all the locking blocks also forms a ring-shaped groove. The ring-shaped groove allows the connecting ends of the missile body flange and the fuselage flange to be locked and fixed in the groove when they are fitted together. When the cuttable structure disconnects the tape assembly, the pull spring can disconnect the tape assembly from the fitted connection between the missile body flange and the fuselage flange. In this way, the missile body flange and the fuselage flange are no longer restricted by the groove. The elastic potential energy of the separation spring can also quickly separate the missile body flange and the fuselage flange, realizing the rapid strike function of the missile and UAV integrated aircraft.

[0040] Optionally, the cuttable structure includes an explosive bolt, with perforated pins connected to both ends of the explosive bolt, and the perforated pins being connected to the end of the wrapping tape.

[0041] Specifically, the cuttable structure includes an explosive bolt, which is connected to the end of the strap via a pin with a hole. When the explosive bolt explodes, it can quickly disconnect the strap, thus preventing multiple clips from forming a ring structure. This prevents the clips from restricting the separation of the projectile flange and the fuselage flange, allowing the projectile flange and fuselage flange to quickly disintegrate under the action of the separation spring.

[0042] Optionally, two wrapping straps are provided. The wrapping straps are semi-circular and each end of the wrapping strap is provided with a pin sleeve. The perforated pins are inserted into the pin sleeves, and adjacent perforated pins are connected by expansion bolts.

[0043] Specifically, the strap can be set to one or more. When there are two straps, the strap is semi-circular. The two ends of the strap form pin sleeves and can accommodate perforated pins in the pin sleeves. The two ends of the explosive bolt are respectively connected to two adjacent perforated pins. This ensures that when the strap is connected by a cuttable structure, the connection between the missile and the end of the UAV can be fixed by the formed groove, thus ensuring the stability of the connection between the missile and the end of the UAV body.

[0044] Optionally, the inner side of the strap is provided with multiple locking blocks, and the side of two adjacent locking blocks near the end of the drone body is connected to the pull spring.

[0045] Specifically, after the explosive bolts detonate, the two straps move in a direction of separation. The tension spring moves the straps towards the end of the drone, and the locking blocks connect to the inside of the straps. In this way, the annular grooves on the inside of the multiple locking blocks no longer limit the connection between the missile body flange and the fuselage flange, enabling the missile to separate quickly from the drone body. In addition, the tension spring connects the end of the drone to the straps. After the drone launches the missile, the tension spring, straps, and locking blocks will remain at the end of the drone, facilitating the installation and fixation of the missile and reducing the cost of missile launch.

[0046] Optionally, the pin with holes has a through hole, and the end of the explosion bolt passes through the through hole and extends to the outside of the wrapping.

[0047] Specifically, the perforated pins have through holes. When the explosive bolts connect two adjacent perforated pins, the center lines of the through holes of the two perforated pins are on the same straight line. The explosive bolts can quickly connect the two perforated pins, improving the ease of installation of the separation device.

[0048] Optionally, it also includes a fairing, which is tubular, with its two ends used for connecting the outer periphery of the missile's tail and the outer periphery of the UAV's fuselage, respectively. The missile body flange, fuselage flange, and wrapping tape assembly are located inside the fairing.

[0049] Optionally, the fairing includes two sub-fairings, each with a semi-circular cross-section, and the two sub-fairings are detachably connected.

[0050] Specifically, the separation device also includes a fairing, which is composed of two semi-circular sub-fairings joined together. This fairing encloses the missile body flange, fuselage flange, and strap assembly on the inside, ensuring that the strap assembly is not easily damaged and guaranteeing a stable connection and normal launch of the missile.

[0051] Optionally, both the projectile flange and the fuselage flange are hollow annular flanges.

[0052] Optionally, the other side of the projectile flange and the other side of the fuselage flange are fitted together to form a V-shaped surface structure with a cross section of 60°.

[0053] Specifically, both the missile body flange and the fuselage flange are outward-facing V-shaped flanges. After the missile body flange and the fuselage flange are joined, a V-shaped surface with a cross-section of 60° is formed. The groove formed by the splicing of multiple clips of the strap assembly can clamp and fix the V-shaped surface structure formed by the missile body flange and the fuselage flange. Then, two explosive bolts are used to tighten the strap to achieve the fixation of the missile and the UAV fuselage.

[0054] The present invention also provides a drone, including the aforementioned missile and drone body separation device.

[0055] Specifically, the missile-UAV separation mechanism is simple in design. Both the missile and UAV fuselages are equipped with flanges, and they are connected using a strap assembly after docking. A tension spring is used to move the strap towards the UAV fuselage during separation, and a separation spring achieves separation of the missile and UAV fuselage. The entire separation device is compact, easy to install, and can quickly complete the separation of the missile and UAV fuselage.

[0056] Example

[0057] like Figures 1 to 8 As shown, the present invention provides a missile and unmanned aerial vehicle (UAV) separation device, comprising:

[0058] Missile body flange 1, one side of which is used to connect to the tail of missile 2;

[0059] Body flange 3, one side of body flange 3 is used to connect to the end of the UAV body 13;

[0060] The strap assembly 4 includes a strap 5 and multiple locking blocks 6. The strap 5 is connected by a cuttable structure to form a ring structure. When the strap 5 forms a ring structure, the multiple locking blocks 6 are distributed circumferentially on the inner side of the ring structure. The locking blocks 6 are provided with locking grooves 7 on their inner circumference.

[0061] The separation spring 8 is located between the projectile flange 1 and the body flange 3. After the separation spring 8 is compressed, the slot 7 can accommodate the projectile flange 1 and the body flange 3.

[0062] Pull spring 9 is disposed between the end of the strap assembly 4 and the drone body 13.

[0063] In this embodiment, the cuttable structure includes an explosive bolt 10, with a perforated pin 11 connected to each end of the explosive bolt 10, and the perforated pin 11 connected to the end of the wrapping strap 5.

[0064] In this embodiment, two straps 5 are provided. The straps 5 are semi-circular and each end of the strap 5 is provided with a pin sleeve 14. A perforated pin 11 is inserted into the pin sleeve, and adjacent perforated pins 11 are connected by an explosion bolt 10.

[0065] In this embodiment, a plurality of locking blocks 6 are provided on the inner side of the strap 5, and the side of two adjacent locking blocks 6 near the end of the drone body is connected to a tension spring 9.

[0066] In this embodiment, the pin 11 with holes has a through hole 15, and the end of the explosion bolt 10 passes through the through hole 15 and extends to the outside of the wrapping strap 5.

[0067] In this embodiment, a fairing 12 is also included. The fairing 12 is tubular, and its two ends are used for connecting the outer periphery of the tail of the missile 2 and the outer periphery of the end of the UAV body 13, respectively. The missile body flange 1, the body flange 3 and the strap assembly 4 are disposed inside the fairing 12.

[0068] In this embodiment, the fairing 12 includes two sub-fairings, each with a semi-circular cross-section, and the two sub-fairings are detachably connected.

[0069] In this embodiment, both the projectile flange 1 and the body flange 3 are hollow annular flanges.

[0070] In this embodiment, the other side of the projectile flange 1 and the other side of the body flange 3 are fitted together to form a V-shaped surface structure with a cross section of 60°.

[0071] The present invention also provides a drone, including the aforementioned missile and drone body separation device.

[0072] In summary, when the separation device receives the command to separate the missile 2 from the UAV body 13, the fairing 12 separates and falls off; subsequently, the explosive bolt 10 explodes, the two straps 5 of the strap assembly 4 separate, and under the pulling force of the tension spring 9, the straps 5 move rapidly toward the end of the UAV body 13, the straps and the locking blocks are fully opened, and the annular locking groove no longer fixes and limits the V-shaped surface structure; under the action of the separation spring 8, the missile 2 and the UAV body 13 are separated.

[0073] The various embodiments of the present invention have been described above. These descriptions are exemplary and not exhaustive, nor are they limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. A missile-to-UAV separation device, characterized in that, include: A missile body flange, one side of which is used to connect to the tail of the missile; A body flange, one side of which is used to connect to the end of the UAV body; A strap assembly includes a strap and multiple locking blocks. The strap is connected to form a ring structure through a cuttable structure. When the strap forms a ring structure, the multiple locking blocks are distributed circumferentially on the inner side of the ring structure. The inner circumference of each locking block is provided with a locking groove. A separation spring is disposed between the projectile flange and the body flange. When the separation spring is compressed, the slot can accommodate the projectile flange and the body flange. A tension spring is disposed between the end of the strap assembly and the drone body; The inner side of the strap is provided with multiple locking blocks, and the side of two adjacent locking blocks near the end of the drone body is connected to the pull spring. The fairing is tubular, with its two ends used for connecting the outer periphery of the missile's tail and the outer periphery of the UAV's body, respectively. The missile body flange, the body flange, and the strap assembly are disposed inside the fairing. The fairing includes two sub-fairings, each with a semi-circular cross-section, and the two sub-fairings are detachably connected.

2. The missile and UAV body separation device according to claim 1, characterized in that, The cuttable structure includes an explosive bolt, with a perforated pin connected to each end of the explosive bolt, and the perforated pin is connected to the end of the wrapping tape.

3. The missile and UAV body separation device according to claim 2, characterized in that, Two straps are provided, each strap is semi-circular, and each end of the strap is provided with a pin sleeve. The perforated pin passes through the pin sleeve, and adjacent perforated pins are connected by the explosion bolt.

4. The missile and UAV body separation device according to claim 2, characterized in that, The perforated pin has a through hole, and the end of the explosive bolt passes through the through hole and extends to the outside of the strap.

5. The missile and UAV body separation device according to claim 1, characterized in that, Both the projectile flange and the body flange are hollow annular flanges.

6. The missile and UAV body separation device according to claim 1, characterized in that, The other side of the projectile flange and the other side of the body flange are fitted together to form a V-shaped surface structure with a cross-section of 60°.

7. A drone, characterized in that, Includes the missile and UAV body separation device according to any one of claims 1-6.

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