A glide-guided aircraft adaptable to a variety of aerial delivery platforms

Abstract

The utility model relates to a kind of gliding guidance aircrafts suitable for multiple air drop platform, including hanger and glider, the upper end of hanger is equipped with upper connector, the lower end of hanger is equipped with lower connector and restraint, the upper end of glider is equipped with multiple lifting lugs, restraint is symmetrically arranged in the both sides of hanger, the both sides of glider are symmetrically articulated with spring wing, lifting lug is equipped on spring wing, drive mechanism is equipped in hanger, the output end of drive mechanism is connected with bolt and restraint, bolt is used to connect or separate lower connector and lifting lug, restraint is used to connect or release lifting lug. By connecting glider with hanger, the design constraint of carrier storebracket scheme to glider is simplified or even eliminated. In order to adapt to different carrier storebracket, only need to adjust the connection relationship of hanger and carrier storebracket, and glider is not affected, greatly reduce the difficulty of system modification design, use adjustment, significantly shorten modification design cycle, increase the application range of gliding guidance aircraft.

Description

Technical Field

[0001] This utility model relates to the field of gliding guided aircraft technology, specifically to a gliding guided aircraft adaptable to various airdrop platforms. Background Technology

[0002] Airdropped airborne glider-guided aircraft can be mainly divided into two types: pylon-launched and cargo-launched. Pylon-launched gliders require a pylon to be mounted on a carrier aircraft, which then carries them into flight. Upon reaching the designated airspace, the glider is released by controlling the pylon's release mechanism. During flight, the glider's wings are folded by its own mechanisms. After release, the glider's wings unfold using a special mechanism.

[0003] For a given glider-guided aircraft, the hardpoints on its glider body are fixed, including their location, size, and function. The hardpoints on the carrier aircraft's pylons impose clear usage constraints on the hardpoints on the glider-guided aircraft, making it impossible for existing glider-guided aircraft to directly utilize different types of pylons. Achieving compatible use between the glider body and different carrier aircraft pylons often requires redesigning the glider body's hardpoints, which may affect the reliability and flight performance of the already finalized glider-guided aircraft system.

[0004] The wing folding constraint mechanism or wing deployment drive mechanism increases the complexity of the glider structure. The glider's own mechanisms constrain wing folding or drive wing deployment, which have the following drawbacks:

[0005] 1) It increases the complexity of the glider structure design and reduces the reliability of the system. For some aircraft with limited space, it may be impossible to design a reasonable structure.

[0006] 2) The wing folding restraint mechanism or wing deployment drive mechanism is an ineffective load during flight and target destruction. With other system design elements remaining unchanged, increasing the ineffective load will reduce the glide vehicle's flight time and range, and will also reduce the warhead's explosive charge, thus affecting combat effectiveness.

[0007] 3) It may disrupt the aerodynamic shape of the glider and affect its flight performance. Utility Model Content

[0008] This invention addresses existing technical problems by providing a gliding guided aircraft adaptable to various airdrop platforms.

[0009] The technical solution of this utility model to solve the above-mentioned technical problems is as follows: A gliding guided aircraft adapted to various airdrop platforms includes a load-bearing device and a glider body. The upper end of the load-bearing device is provided with multiple upper connecting parts, and the lower end of the load-bearing device is provided with lower connecting parts and constraint parts. There are multiple lower connecting parts, and the constraint parts are symmetrically arranged on both sides of the load-bearing device. The upper end of the glider body is provided with multiple lifting lugs. The two sides of the glider body are symmetrically hinged with projectiles, and the projectiles are provided with lifting lugs. A drive mechanism is provided inside the load-bearing device. The output end of the drive mechanism is connected to a pin and the constraint parts. The pin is used to connect or separate the lower connecting parts and the lifting lugs, and the constraint parts are used to connect or release the lifting lugs.

[0010] Based on the above technical solution, the present invention can be further improved as follows:

[0011] Preferably, there are two lower connectors and two lifting lugs, and the pins include a first pin and a second pin, which are spaced apart along the length of the mount.

[0012] Preferably, the drive mechanism includes a first servo motor, a lever body, and a first rocker arm. The output end of the first servo motor is connected to the first rocker arm, and the other end of the first rocker arm is hinged to the lever body via a connecting rod. The constraint member, the first pin, and the second pin are mounted on the lever body.

[0013] Preferably, both the first pin and the second pin are L-shaped, and the first pin and the second pin pass through the bottom plate of the mounter and are connected to the rod body. The bottom plate is provided with a first elongated groove for the first pin and the second pin to pass through.

[0014] Preferably, the constraint element is a hook.

[0015] Preferably, a support shaft is installed at the bottom of the mount, the support shaft is vertically arranged, and a rotatable connecting plate is installed at the lower end of the support shaft. The two constraint members are respectively hinged to the two ends of the connecting plate through the connecting plate, and one of the constraint members is installed on the rod.

[0016] Preferably, a bolt is installed on the rod body, the bolt passes through the base plate of the mount and is hinged to the constraint member, and the base plate is provided with a second elongated groove for the bolt to pass through.

[0017] Preferably, it also includes a second servo motor, which is installed in the mount, and the output shaft of the second servo motor is equipped with a second rocker arm, which is used to block or release the stick.

[0018] The beneficial effects of this utility model are:

[0019] (1) By connecting the glider to the pylon, the design constraints of the aircraft pylon scheme on the glider can be greatly simplified or even eliminated. To adapt to different aircraft pylons, only the connection relationship between the pylon and the aircraft pylon needs to be adjusted, while the structural design, weight, size, shape, and aerodynamic performance of the glider remain unaffected. This greatly reduces the difficulty of system modification design and usage adjustment, significantly shortens the modification design cycle, and greatly increases the applicability of glider-guided aircraft.

[0020] (2) By setting up a load cell, the structural design of the glider can be significantly simplified, which is conducive to optimizing the weight and aerodynamic shape of the glider, reducing the ineffective load, ensuring the amount of warhead charge, and improving the combat effectiveness of the aircraft system. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the present utility model. Figure 1 ;

[0022] Figure 2 This is a schematic diagram of the glider and the mounting device of this utility model when connected;

[0023] Figure 3 This is a cross-sectional schematic diagram of the internal structure of the mounter of this utility model;

[0024] Figure 4 This is a schematic diagram of the missile wings of this utility model when they are retracted;

[0025] Figure 5 This is a schematic diagram of the first rocker arm and the rod body of this utility model.

[0026] Figure 6 This is a schematic diagram of the bottom of the mount of this utility model.

[0027] The attached diagram labels are recorded as follows:

[0028] 10. Aircraft carrier frame; 11. Frame connector;

[0029] 20. Mount; 21. Upper connector; 22. Lower connector; 23. Constraint; 23.1. Bolt; 24. First pin; 25. Second pin; 26. First rocker arm; 27. Rod; 28. First servo; 29. ​​Connecting plate; 29.1. Connecting plate;

[0030] 30. Glider; 31. Hanger; 32. Lug; 33. Projectile wing;

[0031] 40. Second servo motor; 41. Second rocker arm. Detailed Implementation

[0032] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the protection scope of the present invention.

[0033] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this utility model are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. The terms "vertical," "upper," "lower," "horizontal," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation; therefore, they should not be construed as limitations on this utility model.

[0034] like Figures 1 to 6As shown, this utility model discloses a gliding guided aircraft adaptable to various airdrop platforms, including a load cell 20 and a glider 30. The upper end of the load cell 20 is provided with multiple upper connectors 21. The load cell 20 is connected to the pylon connector 11 of the carrier aircraft pylon 10 via the upper connectors 21, thus enabling the load cell 20 to be mounted on the carrier aircraft. The upper connectors 21 are adaptively designed according to the shape of the pylon connector 11 to ensure proper connection between the two. In this embodiment, the upper connector 21 is a protruding structure, and the pylon connector 11 has a U-shaped groove structure. The upper connector 21 is inserted into the U-shaped groove and fixed with bolts and nuts. The lower end of the mount 20 is provided with a lower connector 22 and a constraint member 23. There are multiple lower connectors 22, and the constraint members 23 are symmetrically arranged on both sides of the mount 20. The upper end of the glider 30 is provided with multiple lifting lugs 31, and the position and number of the lifting lugs 31 correspond to those of the lower connectors 22. The two sides of the glider 30 are symmetrically hinged with projectiles 33, and a return spring is provided between the projectiles 33 and the glider 30. Under the action of the return spring, the projectiles 33 are fixed. The glider 30 automatically deploys. The wing 33 is equipped with lugs 32. The mounting device 20 contains a drive mechanism. The output end of the drive mechanism is connected to pins and the constraint members 23. The number and position of the pins correspond to the number and position of the lower connecting members 22. The pins are used to connect or release the lower connecting members 22 and the lugs 31. When the pins are inserted into the lower connecting members 22 and the lugs 31, the glider 30 is connected to the mounting device 20. When the drive mechanism drives the pins to be withdrawn from the lower connecting members 22 and the lugs 31, gliding is achieved. The glider 30 separates from the mount 20. The constraint member 23 is used to connect or release the lug 32, thereby enabling the wing 33 to retract or deploy. The constraint member 23 is a C-shaped hook. When the glider 30 is mounted on the carrier aircraft, the constraint member 23 retracts the wing 33. When the glider 30 reaches the predetermined airspace, the drive mechanism drives the pin to be pulled out from the lower connector 22 and the lug 31, separating the glider 30 from the mount 20. Simultaneously, the constraint member 23 separates from the lug 32, and the constraint member 23 no longer constrains the wing 33, allowing the wing 33 to deploy and the glider 30 to glide. The drive mechanism controls the connection state between the glider 30 and the mount 20, as well as the state of the wing 33, ensuring the glider 30's gliding flight. The operation is simple and the control is convenient. When the glider 30 needs to be mounted on different types of aircraft pylons 10, only the structure of the upper connector 21 of the pylon 20 needs to be adjusted. The glider 30 remains unaffected, ensuring its flight performance, shortening the overall redesign cycle, and improving ease of use. The specific connection structure between the missile wing 33 and the glider 30, as well as other components of the glider 30 such as the battery, control system, and fasteners, utilize existing technology and will not be described in detail here.

[0035] In this embodiment, two lower connectors 22 and two lugs 31 are provided. The lower connector 22 is a U-shaped groove with an opening facing downwards. The pins include a first pin 24 and a second pin 25, which are spaced apart along the length of the mount 20. The first pin 24 and the second pin 25 are respectively inserted into the two lugs 31 and the two lower connectors 22 to connect the glider 30 and the mount 20, ensuring the stability of the connection.

[0036] Specifically, the drive mechanism includes a first servo motor 28, a rod 27, and a first rocker arm 26. The output end of the first servo motor 28 is connected to the first rocker arm 26, and the other end of the first rocker arm 26 is hinged to the rod 27 via a connecting rod. The constraint member 23, the first pin 24, and the second pin 25 are installed on the rod 27 to ensure that the glider 30 can be released normally and that the glider 30 can glide normally. The first pin 24 and the second pin 25 are both L-shaped. The upper ends of the first pin 24 and the second pin 25 pass through the bottom plate of the mount 20 and are fixedly connected to the rod 27 by nuts. The bottom plate of the mount 20 is provided with a first elongated groove for the first pin 24 and the second pin 25 to pass through, ensuring that the first pin 24 and the second pin 25 can move normally along the first elongated groove. During operation, the first servo motor 28 drives the first rocker arm 26 to rotate. The rotation of the rocker arm 26 causes displacement of the rod 27 via a connecting rod, which in turn causes the first pin 24 and the second pin 25 to move synchronously. This allows the first pin 24 and the second pin 25 to connect or release the lower connecting piece 22 and the lifting lug 31, thus connecting or separating the pylon 20 from the glider 30. Simultaneously, it causes the restraint piece 23 to engage or release the lifting lug 32, allowing the wings 33 to be retracted or deployed. By controlling the movement of the rod 27 via the first servo motor 28, the pylon 20 releases the glider 30 while the restraint piece 23 simultaneously releases the wings 33, ensuring that the glider 30 can glide and fly normally in the designated airspace. The control is simple and the operation is convenient.

[0037] Furthermore, a support shaft is installed at the bottom of the mounting device 20. The support shaft is vertically oriented, and a rotatable connecting plate 29.1 is installed at the lower end of the support shaft. Two constraint members 23 are respectively hinged to both ends of the connecting plate 29.1 via the connecting plate 29. One of the constraint members 23 is mounted on the rod 27. When the first servo motor 28 drives one of the constraint members 23 to move via the rod 27, the constraint member 23 pushes the connecting plate 29.1 to rotate, thereby driving the other constraint member 23 to move synchronously. This achieves synchronous connection or release of the lugs 32 on the two wings 33, ensuring that the two wings 33 move synchronously, guaranteeing the normal gliding of the glider 30 and ensuring safety during use.

[0038] The rod 27 is fitted with a bolt 23.1, which passes through the base plate of the mount 20 and is hinged to the constraint member 23. The base plate has a second elongated groove through which the bolt 23.1 passes. This ensures that the constraint member 23 can move normally along the second elongated groove, allowing it to properly engage or disengage the lug 32, thus ensuring that the glider 30 can glide normally.

[0039] The gliding guided aircraft also includes a second servo 40, which is installed inside the mount 20. The second servo 40 is arranged adjacent to the first servo 28. A second rocker arm 41 is mounted on the output shaft of the second servo 40. The second rocker arm 41 is used to block or release the stick 27. Specifically, when the mount 20 is connected to the glider 30 via the lower connector 22 and the constraint member 23, the second rocker arm 41 is perpendicular to the bottom surface of the mount 20. Figure 5 As shown, at this time, the second rocker arm 41 is located on the movement path of the stick 27, thus preventing the stick 27 from moving. When the mount 20 needs to separate from the glider 30, the second rocker arm 41 rotates to be parallel to the bottom surface of the mount 20, and the second rocker arm 41 leaves the movement path of the stick 27. At this time, the stick 27 can move under the action of the first servo 28 and the first rocker arm 26, so that the mount 20 and the glider 30 can separate normally. By blocking or releasing the stick 27 with the second rocker arm 41, the possibility of the first servo 28 malfunctioning is prevented, further improving the safety during use.

[0040] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A glide-guided aircraft adapted to multiple aerial delivery platforms, characterized in that, The device includes a mount (20) and a glider (30). The upper end of the mount (20) is provided with multiple upper connectors (21), and the lower end of the mount (20) is provided with a lower connector (22) and a restraint (23). The lower connector (22) is provided with multiple components, and the restraint (23) is symmetrically arranged on both sides of the mount (20). The upper end of the glider (30) is provided with multiple lugs (31). The two sides of the glider (30) are symmetrically hinged with wings (33). The wings (33) are provided with lugs (32). The mount (20) is provided with a drive mechanism. The output end of the drive mechanism is connected to a pin and the restraint (23). The pin is used to connect or separate the lower connector (22) from the lugs (31), and the restraint (23) is used to connect or release the lugs (32).

2. The gliding guided flying vehicle adapted to multiple aerial delivery platforms of claim 1, wherein, The lower connector (22) and the lifting lug (31) are provided in twos respectively. The pin includes a first pin (24) and a second pin (25). The first pin (24) and the second pin (25) are spaced apart along the length direction of the mount (20).

3. The gliding guided flying vehicle adapted to multiple aerial delivery platforms of claim 2, wherein, The drive mechanism includes a first servo motor (28), a rod (27) and a first rocker arm (26). The output end of the first servo motor (28) is connected to the first rocker arm (26). The other end of the first rocker arm (26) is hinged to the rod (27) via a connecting rod. The constraint member (23), the first pin (24) and the second pin (25) are mounted on the rod (27).

4. The gliding guided aircraft adapted to various airdrop platforms according to claim 3, characterized in that, The first pin (24) and the second pin (25) are both L-shaped. The first pin (24) and the second pin (25) pass through the bottom plate of the mount (20) and are connected to the rod (27). The bottom plate is provided with a first long groove for the first pin (24) and the second pin (25) to pass through.

5. The gliding guided flying vehicle adapted to multiple aerial delivery platforms of claim 3, wherein, The constraint (23) is a hook.

6. The gliding guided flying vehicle adapted to multiple aerial delivery platforms of claim 5, wherein, The bottom of the mount (20) is equipped with a support shaft, which is vertically arranged. A rotatable connecting plate (29.1) is installed at the lower end of the support shaft. Two constraint members (23) are respectively hinged to the two ends of the connecting plate (29.1) through the connecting plate (29). One of the constraint members (23) is installed on the rod (27).

7. The gliding guided aircraft adapted to various airdrop platforms according to claim 6, characterized in that, Bolts (23.1) are installed on the rod (27). The bolts (23.1) pass through the bottom plate of the mount (20) and are hinged to the constraint (23). The bottom plate is provided with a second long slot for the bolts (23.1) to pass through.

8. The gliding guided aircraft adapted to various airdrop platforms according to claim 3, characterized in that, It also includes a second servo (40), which is installed in the mount (20), and the output shaft of the second servo (40) is equipped with a second rocker arm (41), which is used to block or release the rod (27).

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