A catapult mechanism that assists air-to-wall amphibious aircraft in completing wall-to-air attitude transitions.

Abstract

This utility model discloses a catapult mechanism for assisting an air-to-wall amphibious aircraft in completing wall-to-air attitude transitions, relating to the field of unmanned aerial vehicle (UAV) technology. A fixed base has a receiving cavity, within which a cylinder is rotatably connected. A drive module for rotating the cylinder is connected to the cylinder. A push rod is slidably connected to the fixed base, with one end connected to a contact and the other end extending into the inner side of the cylinder and connecting to a protruding rod. One end of a spring is connected to the protruding rod, and the other end is connected to the bottom wall of the receiving cavity. An annular groove, comprising a spiral section, a horizontal section, and a vertical section, is also provided on the side wall of the cylinder to slide with the protruding rod. The catapult mechanism proposed in this utility model can launch the aircraft away from the wall and into the air at an angle of approximately 45°, thus achieving a smoother transition between wall and air attitudes.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and more specifically, to a catapult mechanism that assists an air-to-wall amphibious vehicle in completing wall-to-air attitude transitions. Background Technology

[0002] Existing air-to-wall amphibious vehicles cannot actively control their attitude transition from wall to air; they rely on gravity to tilt the vehicle before transitioning. This process lacks active control and is highly random, making it difficult to guarantee the vehicle's attitude transition. Furthermore, tilting via gravity results in high angular velocities and accelerations, making speed control during attitude transitions difficult and potentially leading to loss of control. Utility Model Content

[0003] In order to overcome the shortcomings of the existing technology, this utility model proposes an ejection mechanism to assist an air-to-wall amphibious aircraft in completing the wall-to-air attitude conversion. It can eject the aircraft away from the wall and fly into the air at an angle of nearly 45°, thereby completing the wall-to-air attitude conversion more smoothly.

[0004] To achieve this objective, the present invention adopts the following technical solution: This utility model provides an ejection mechanism to assist an air-to-wall amphibious vehicle in completing wall-to-air attitude transitions. The mechanism includes a fixed base, a cylinder, a drive module, a push rod, a contact, a protruding rod, and a spring. The fixed base has a receiving cavity, within which the cylinder is rotatably connected. A drive module is connected to the cylinder to drive its rotation. The push rod is slidably connected to the fixed base, with one end connected to the contact and the other end extending into the inner side of the cylinder and connecting to the protruding rod. One end of the spring is connected to the protruding rod, and the other end is connected to the bottom wall of the receiving cavity. An annular groove is also provided on the side wall of the cylinder, which slides with the protruding rod. The annular groove includes a helical section, a horizontal section, and a vertical section.

[0005] In a preferred embodiment of this invention, the drive module includes a drive motor, a drive gear, and a driven gear. A motor mounting slot is provided on one side of the receiving cavity, and a drive motor is installed in the motor mounting slot. The output end of the drive motor is connected to the drive gear, and the driven gear is coaxially fixed on the outer wall of the cylinder, with the drive gear and the driven gear meshing with each other.

[0006] In a preferred embodiment of this invention, the contact is a triangular block structure.

[0007] In a preferred embodiment of this invention, the contact is made of rubber material.

[0008] In a preferred embodiment of this invention, the fixing base is a hexagonal structure.

[0009] The beneficial effects of this utility model are as follows: 1. This device can eject the aircraft away from the wall and fly into the air at an angle of nearly 45°, thus completing the transition between wall and air attitudes more smoothly.

[0010] 2. This device controls the charging and ejection of the push rod through a cylinder. When the charging is complete, the drive motor can maintain the maximum charging state without being powered on. The ejection can be triggered by the rotation of the motor at a small angle, saving the energy required to control the motor.

[0011] 3. The contacts of this device are made of rubber materials, which can increase the friction coefficient between the contacts and the wall, prevent the push rod from slipping on the wall when it is pushed out, and at the same time, the contacts are in flexible contact with the wall, which increases the time for the force to act under the same impulse, reduces the magnitude of the force, and weakens the impact of the impact force on the structural strength. Attached Figure Description

[0012] Figure 1 This is a schematic diagram of the ejection mechanism for assisting an air-to-wall amphibious aircraft in completing wall-to-air attitude conversion, provided in a specific embodiment of this utility model.

[0013] Figure 2 yes Figure 1 A cross-sectional view along the AA direction; Figure 3 yes Figure 1 Schematic diagram of the middle cylinder; Figure 4 yes Figure 3 The left view; Figure 5 yes Figure 3 Schematic diagram of the structure of the central ring line groove; Figure 6 This is a schematic diagram of the installation structure of the push rod and the lead rod; Figure 7 yes Figure 6 The right view; Figure 8 This is a diagram of the aircraft's ejection process.

[0014] 1. Fixed base; 11. Receiving cavity; 12. Motor mounting slot; 2. Cylinder; 21. Annular slot; 211. Spiral section; 212. Horizontal section; 213. Vertical section; 3. Drive module; 31. Drive motor; 32. Drive gear; 33. Driven gear; 4. Push rod; 5. Contact; 6. Protruding rod; 7. Spring. Detailed Implementation

[0015] The technical solution of this utility model will be further described below with reference to the accompanying drawings and specific embodiments.

[0016] like Figure 1-7As shown, the embodiment provides an ejection mechanism to assist an air-to-wall amphibious vehicle in completing wall-to-air attitude transitions. The mechanism includes a fixed base 1, a cylinder 2, a drive module 3, a push rod 4, a contact 5, a protruding rod 6, and a spring 7. The fixed base 1 has a receiving cavity 11, within which the cylinder 2 is rotatably connected. The drive module 3, which drives the cylinder 2 to rotate, is connected to the cylinder 2. The push rod 4 is slidably connected to the fixed base 1. One end of the push rod 4 is connected to the contact 5, and the other end extends into the inner side of the cylinder 2 and connects to the protruding rod 6. One end of the spring 7 is connected to the protruding rod 6, and the other end is connected to the bottom wall of the receiving cavity 11. The side wall of the cylinder 2 also has an annular slot 21 that slides with the protruding rod 6. The annular slot 21 includes a helical section 211, a horizontal section 212, and a vertical section 213. In this embodiment, the fixed base 1 is mounted on the aircraft, and when the aircraft rotates to a vertical position and adheres to the wall, the side of the fixed base 1 is precisely in contact with the wall surface. The drive module 3 drives the cylinder 2 to rotate within the receiving cavity 11, causing one end of the protruding rod 6 to slide within the annular slot 21. For example, when one end of the protruding rod 6 is located in the spiral section 211, the protruding rod 6 moves vertically downwards, causing the push rod 4 to retract and compress the spring 7. When one end of the protruding rod 6 is located in the horizontal section 212, the position of the push rod 4 is fixed, and the spring 7 remains compressed. When one end of the protruding rod 6 is located in the vertical section 213, the spring 7 pushes the push rod 4 outwards. The push rod 4 is preferably a square tube to ensure that the push rod 4 can only slide up and down on the fixed base 1 and cannot rotate, thus preventing the cylinder 2 from driving the push rod 4 to rotate synchronously during rotation. The protruding rod 6 and the push rod 4 are arranged perpendicularly, and the push rod 4 is coaxial with the central axis of the cylinder 2. At the same time, the spring 7 is always in a compressed state to ensure that the pushing force of the spring 7 on the push rod 4 is sufficient to push the aircraft away from the wall.

[0017] Specifically, such as Figure 2-3 As shown, the drive module 3 includes a drive motor 31, a driving gear 32, and a driven gear 33. A motor mounting slot 12 is provided on one side of the receiving cavity 11, and the drive motor 31 is installed within the motor mounting slot 12. The output end of the drive motor 31 is connected to the driving gear 32. The driven gear 33 is coaxially fixed to the outer wall of the cylinder 2, and the driving gear 32 and driven gear 33 mesh with each other. In this embodiment, the motor mounting slot 12 and the receiving cavity 11 are connected. The drive motor 31 is a common commercial component used to drive the driving gear 32 to rotate. Because the driving gear 32 and driven gear 33 mesh, the drive motor 31 can drive the cylinder 2 to rotate, thereby controlling the extension and retraction of the push rod 4.

[0018] Specifically, such as Figure 3-4 As shown, contact 5 has a triangular block structure.

[0019] Specifically, such as Figure 3-4As shown, the contact 5 is made of rubber. In this embodiment, using rubber increases the coefficient of friction between the contact 5 and the wall, preventing the push rod 4 from slipping against the wall when it is pushed out. At the same time, the contact 5 makes flexible contact with the wall, increasing the time for the force to act under the same impulse, reducing the magnitude of the force, and weakening the impact of the impact force on the structural strength.

[0020] Specifically, such as Figure 1 As shown, the fixing base 1 has a hexagonal structure.

[0021] like Figure 8 As shown, during use, the drive motor 31 drives the drive gear 32 to rotate clockwise. The rotation of the drive gear 32 drives the driven gear 33 and the cylinder 2 to rotate counterclockwise. At this time, the protruding rod 6 slides in the spiral section 211 of the annular slot 21. Since the push rod 4 can only move up and down and cannot rotate, it moves downward under the action of the protruding rod 6 and compresses the spring 7 to store force until the protruding rod 6 moves from the spiral section 211 to the horizontal section 212. At this time, the push rod 4 remains stationary, thus completing the movement of the force storage stage. When the aircraft is launched, the drive motor 31 drives the cylinder 2 to continue rotating, causing the protruding rod 6 to move from the horizontal section 212 to the vertical section 213. At this time, the spring 7 releases its elastic force to push the push rod 4 out, which in turn causes the contact 5 to contact the wall and generate an upward reaction force to push the aircraft away from the wall, thus completing the movement of the ejection stage.

[0022] This utility model has been described through preferred embodiments. Those skilled in the art will understand that various changes or equivalent substitutions can be made to these features and embodiments without departing from the spirit and scope of this utility model. This utility model is not limited to the specific embodiments disclosed herein; other embodiments falling within the scope of the claims of this application are all within the protection scope of this utility model.

Claims

1. A catapult mechanism for assisting an air-to-wall amphibious aircraft in completing wall-to-air attitude transitions, characterized in that: The device includes a fixed base (1), a cylinder (2), a drive module (3), a push rod (4), a contact (5), a protruding rod (6), and a spring (7). The fixed base (1) has a receiving cavity (11), and the cylinder (2) is rotatably connected inside the receiving cavity (11). The drive module (3) that drives the cylinder (2) to rotate is connected to the cylinder (2). The push rod (4) is slidably connected to the fixed base (1). One end of the push rod (4) is connected to the contact (5), and the other end of the push rod (4) extends into the inner side of the cylinder (2) and is connected to the protruding rod (6). One end of the spring (7) is connected to the protruding rod (6), and the other end of the spring (7) is connected to the bottom wall of the receiving cavity (11). The cylinder (2) also has an annular groove (21) that slides with the protruding rod (6) on its side wall. The annular groove (21) includes a spiral section (211), a horizontal section (212), and a vertical section (213).

2. The catapult mechanism for assisting an air-to-wall amphibious vehicle in completing wall-to-air attitude transition according to claim 1, characterized in that: The drive module (3) includes a drive motor (31), a drive gear (32) and a driven gear (33). A motor mounting slot (12) is provided on one side of the receiving cavity (11). The drive motor (31) is installed in the motor mounting slot (12). The output end of the drive motor (31) is connected to the drive gear (32). The driven gear (33) is coaxially fixed on the outer wall of the cylinder (2), and the drive gear (32) and the driven gear (33) mesh with each other.

3. The catapult mechanism for assisting an air-to-wall amphibious vehicle in completing wall-to-air attitude transition according to claim 1, characterized in that: The contact (5) has a triangular block structure.

4. The catapult mechanism for assisting an air-to-wall amphibious vehicle in completing wall-to-air attitude transition according to claim 1, characterized in that: The contact (5) is made of rubber material.

5. The catapult mechanism for assisting an air-to-wall amphibious vehicle in completing wall-to-air attitude transition according to claim 1, characterized in that: The fixed base (1) has a hexagonal structure.

Images