Quick-release rudder wing and aircraft comprising same

Abstract

The utility model discloses a quick-release rudder wing and an aircraft comprising the same, which belong to the technical field of control surfaces and comprise a rudder shaft, a control surface and a clamping structure, a slot with a circular cross section is formed in the tip part of the rudder shaft, and an insertion block matched with the slot is arranged at the root part of the rudder surface; the clamping structure comprises a clamping block, a clamping groove and a spring; the clamping block is arranged on the side wall of the inserting block, the clamping groove is formed in the side wall of the inserting groove, the spring is arranged between the rudder shaft and the rudder surface, and the spring is used for providing elastic force enabling the inserting block to be away from the inserting groove; the clamping groove comprises a notch, a guide groove and a bayonet which are connected in sequence, the notch is used for guiding the clamping block to enter the clamping groove under the action of resisting axial thrust of the spring, the guide groove is used for guiding the clamping block to the bayonet under the action of circumferential torque, and the bayonet is used for locking the clamping block under the action of elastic force of the spring. According to the utility model, the control surface can be quickly disassembled when not in use and can be quickly assembled when in use, so that the size of the aircraft can be quickly adjusted, and the storage and transportation requirements are reduced.

Description

Technical Field

[0001] This utility model relates to the field of control surface technology, and in particular to a quick-release multi-faceted device and an aircraft containing it. Background Technology

[0002] Control surfaces are components installed on aircraft to change the aircraft's flight attitude. Control surfaces are usually installed on the surface of the aircraft. Unless for maintenance, control surfaces are usually installed on the surface of the aircraft in a non-removable manner, such as the control surfaces of an airplane. When the aircraft is in normal use, the control surfaces installed on its surface do not affect the normal operation of the aircraft.

[0003] However, the control surfaces of some aircraft can significantly increase the operational burden during transportation and storage. For example, the control surfaces of missiles. The transportation and storage of missiles have high size requirements, and the size of their control surfaces is significantly larger than the size of the missile. Therefore, in the existing technology, the control surfaces of missiles are usually designed to be foldable to reduce the size of transportation and storage. The control surfaces are unfolded when the missile is in flight.

[0004] However, such foldable control surfaces have the disadvantages of complex structure and high manufacturing cost. Therefore, a control surface design that can be quickly disassembled is a new approach that can solve the above problems. Summary of the Invention

[0005] In view of the problem that the control surfaces in the prior art are reduced in size through complex folding designs, the purpose of this utility model is to provide a quick-release control wing and an aircraft containing it, so as to at least partially solve the above-mentioned problems.

[0006] To achieve the above objectives, the technical solution of this utility model is as follows:

[0007] In one aspect, the present invention provides a quick-release rudder wing, including a rudder shaft, a rudder surface, and a snap-fit ​​structure; the tip of the rudder shaft is provided with a slot with a circular cross-section, and the root of the rudder surface is provided with a plug that is adapted to the slot;

[0008] The snap-fit ​​structure includes a snap-fit ​​block, a snap-fit ​​groove, and a spring; the snap-fit ​​block is disposed on the side wall of the insert block, the snap-fit ​​groove is formed on the side wall of the slot, and the spring is disposed between the rudder shaft and the rudder surface, and the spring is used to provide an elastic force to move the insert block away from the slot;

[0009] The slot includes a notch, a guide groove, and a latch connected in sequence. The notch is used to guide the block into the slot under the resistance of the axial thrust of the spring. The guide groove is used to guide the block towards the latch under the action of the circumferential torque. The latch is used to lock the block under the action of the spring force.

[0010] In some preferred embodiments, the slot is annular, and the rudder shaft is also coaxially provided with a mounting groove located inside the slot, the mounting groove being provided with a spring block and the spring; the spring block is used to provide elastic force to the rudder surface under the action of the spring, causing the insert block on it to move away from the slot.

[0011] In some preferred embodiments, the tip of the spring block protrudes from the mounting groove, and the root of the rudder surface has a groove adapted to the tip of the spring block.

[0012] In some preferred embodiments, a limiting structure is provided between the spring block and the mounting groove to prevent the spring block from disengaging.

[0013] In some preferred embodiments, the limiting structure includes a limiting step disposed on the side wall of the spring block, and a limiting flange disposed at the opening of the mounting groove for blocking the limiting step.

[0014] In some preferred embodiments, the spring is sleeved on the outside of the spring block, and the two ends of the spring abut against the bottom of the mounting groove and the limiting step, respectively.

[0015] In some preferred embodiments, the mounting groove extends through the root end face of the rudder shaft, and a plug is detachably connected to the bottom of the mounting groove.

[0016] In some preferred embodiments, there are multiple card blocks arranged circumferentially at intervals on the sidewall of the insertion block, and the corresponding card slots are arranged in the same number and in the same distribution on the sidewall of the slot.

[0017] In some preferred embodiments, there are three card blocks arranged evenly around the circumference.

[0018] Secondly, this utility model also provides an aircraft, including a control compartment, on which the quick-release rudder wing described above and a servo motor for driving the rudder shaft are installed.

[0019] The beneficial effects of this utility model by adopting the above technical solution are as follows: Through the setting of the rudder shaft, rudder surface and snap-fit ​​structure, the snap-fit ​​structure can perform circumferential and axial positioning of the rudder shaft and rudder surface, so that the rudder surface can not only be quickly disassembled and assembled relative to the rudder shaft, but also be locked under the elastic force of the spring. This allows the rudder surface to be quickly disassembled when not in use and quickly installed when in use, thereby enabling the size of the aircraft to be quickly adjusted, thereby reducing storage and transportation requirements. Attached Figure Description

[0020] Figure 1 This is an exploded view of the present invention.

[0021] Figure 2 This is a partial sectional view of the present invention.

[0022] Figure 3 This is a schematic diagram of the rudder surface in this utility model.

[0023] Figure 4 This is a schematic diagram of the rudder shaft in this utility model.

[0024] Figure 5 This is another structural schematic diagram of the rudder shaft in this utility model.

[0025] Figure 6 This is a front view of the rudder shaft in this utility model.

[0026] Figure 7 This is a schematic diagram of the structure of the spring block in this utility model.

[0027] Figure 8 This is a schematic diagram of the control compartment in this utility model.

[0028] In the diagram: 1-rudder shaft, 11-slot, 2-rudder surface, 21-insertion block, 3-block, 4-slot, 41-notch, 42-guide slot, 43-jaw, 5-spring, 6-mounting slot, 61-limiting flange, 7-spring block, 71-limiting step, 8-control compartment. Detailed Implementation

[0029] The specific embodiments of this utility model will be further described below with reference to the accompanying drawings. It should be noted that these descriptions are for the purpose of aiding understanding of this utility model, but do not constitute a limitation thereof. Furthermore, the technical features involved in the various embodiments of this utility model described below can be combined with each other as long as they do not conflict with each other.

[0030] It should be noted that in the description of this utility model, the terms "upper", "lower", "left", "right", "front", "rear", etc., indicate the orientation or positional relationship based on the description of the structure of this utility model shown in the accompanying drawings. They are only for the convenience of describing this utility model 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.

[0031] The terms "first" and "second" in this technical solution are merely designations for corresponding structures that are identical or similar, or that perform similar functions. They do not represent an arrangement of the importance of these structures, nor do they imply any ranking, comparison of size, or other meaning.

[0032] Furthermore, unless otherwise explicitly specified and limited, the terms "installation" and "connection" should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be a connection within two structures. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the overall concept and the specific context of the solution.

[0033] Example 1

[0034] A quick-release rudder, such as Figure 1-7 As shown, it includes a rudder shaft 1, a rudder surface 2, and a snap-fit ​​structure.

[0035] The tip of the rudder shaft 1 has a slot 11, which is annular and coaxial with the rudder shaft 1. The root of the rudder surface 2 has a corresponding insert 21, which is also annular and its size is similar to that of the slot 11. This allows the rudder surface 2 to engage with the slot 11 on the rudder shaft 1 via the insert 21, so that the root of the rudder surface 2 can move circumferentially and axially relative to the tip of the rudder shaft 1.

[0036] The snap-fit ​​structure includes a snap-fit ​​block 3, a snap-fit ​​slot 4, and a spring 5.

[0037] The locking block 3 is disposed on the outer side wall of the insert block 21, and the locking groove 4 is formed on the side wall of the slot 11, for example, the locking groove 4 is disposed in a through shape on the side wall of the slot 11. The spring 5 is disposed between the rudder shaft 1 and the rudder surface 2, and the spring 5 is used to provide elastic force to move the insert block 21 away from the slot 11.

[0038] The slot 4 includes a notch 41, a guide groove 42, and a latch 43 connected in sequence. The notch 41 is arranged along the axial direction of the rudder shaft 1 and is used to guide the block 3 into the slot 4 under the axial thrust of the spring 5. The guide groove 42 is arranged along the circumferential direction of the slot 11 and is used to guide the block 3 toward the latch 43 under the action of the circumferential torque. The latch 43 is also arranged along the axial direction of the rudder shaft 1, and the latch 43 and the notch 41 are both located on the same side of the guide groove 42 (the side closer to the tip). The latch 43 is used to lock the block 3 under the elastic force of the spring 5.

[0039] In this embodiment, the snap-fit ​​structure enables the rudder surface 2 and the rudder shaft 1 to achieve concentric positioning and withstand the bending moment of the rudder surface 2. In addition, the elastic force provided by the spring 5 can eliminate any misalignment between the rudder surface 2 and the rudder shaft 1, thereby allowing the snap-fit ​​block 3 to be stably engaged in the snap-fit ​​slot 43.

[0040] It is easy to understand that there can be multiple card blocks 3, such as 3, and the 3 card blocks 3 are evenly spaced around the outer wall of the insert block 21. Correspondingly, there are also 3 card slots 4, which are also evenly spaced around the side wall of the slot 11.

[0041] In this embodiment, a mounting groove 6 is coaxially formed on the rudder shaft 1. The mounting groove 6 is located inside the slot 11. A spring block 7 is provided in the mounting groove 6, and a spring 5 is also arranged in the mounting groove 6. This allows the spring block 7 to provide a spring force to the rudder surface 1 under the action of the spring 5, causing the insert block 21 on it to move away from the slot 11. For example, the tip of the spring block 7 protrudes from the mounting groove 6, and a groove adapted to the tip of the spring block 7 is formed at the root of the rudder surface 1.

[0042] The spring block 7 is provided with a limiting structure between it and the mounting groove 6 to prevent it from detaching from the mounting groove 6. This limiting structure includes a limiting step 71 on the side wall of the spring block 7 and a limiting flange 61 at the opening of the mounting groove 6 to block the limiting step 71. The spring 5 is specifically sleeved on the outside of the spring block 7, with its two ends abutting against the bottom of the mounting groove 6 and the limiting step 71, respectively. The mounting groove 6 extends through the root end face of the rudder shaft 1, and a plug 8 is detachably connected to the bottom of the mounting groove 6, for example, the plug 8 is threaded into the mounting groove 6. It is easy to understand that when the spring block 7 abuts against the rudder surface 2, the limiting step 71 of the spring block 7 has not yet contacted the limiting flange 61 on the mounting groove 6; that is, the limiting structure between the spring block 7 and the mounting groove 6 does not affect the spring 5's provision of elastic force to the rudder surface 2 through the spring block 7.

[0043] Example 2

[0044] This utility model also provides an aircraft, such as a missile or rocket, which includes a control compartment 9, such as... Figure 8 As shown, for example, it is a cylindrical structure, and the control compartment 9 is equipped with the quick-release rudder provided in the above embodiment on its side wall, for example, so that the rudder shaft 1 is rotatably connected to the shaft hole opened on the side wall of the control compartment 9.

[0045] Typically, the control section 9 is equipped with multiple quick-release rudders, such as four. These four quick-release rudders are arranged at 90° intervals around the circumference and are positioned on the same circumference. In addition, the control section 9 is also equipped with servos (not shown in the figure). The number of servos is the same as the number of quick-release rudders, and the output of each servo is connected to the rudder shaft 1 in the corresponding quick-release rudder.

[0046] The embodiments of this utility model have been described in detail above with reference to the accompanying drawings, but this utility model is not limited to the described embodiments. For those skilled in the art, various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and spirit of this utility model, and these variations still fall within the protection scope of this utility model.

Claims

1. A quick-release rudder, characterized in that: It includes a rudder shaft, a rudder surface, and a snap-fit ​​structure; the tip of the rudder shaft has a slot with a circular cross-section, and the root of the rudder surface has a plug that fits into the slot; The snap-fit ​​structure includes a snap-fit ​​block, a snap-fit ​​groove, and a spring; the snap-fit ​​block is disposed on the side wall of the insert block, the snap-fit ​​groove is formed on the side wall of the slot, and the spring is disposed between the rudder shaft and the rudder surface, and the spring is used to provide an elastic force to move the insert block away from the slot; The slot includes a notch, a guide groove, and a latch connected in sequence. The notch is used to guide the block into the slot under the resistance of the axial thrust of the spring. The guide groove is used to guide the block towards the latch under the action of the circumferential torque. The latch is used to lock the block under the action of the spring force.

2. The quick-release rudder according to claim 1, characterized in that: The slot is annular, and the rudder shaft is also coaxially provided with a mounting groove located inside the slot. The mounting groove is provided with a spring block and the spring. The spring block is used to provide elastic force to the rudder surface under the action of the spring, so that the insert on it moves away from the slot.

3. The quick-release rudder according to claim 2, characterized in that: The tip of the projectile protrudes from the mounting groove, and the root of the rudder surface has a groove that matches the tip of the projectile.

4. The quick-release rudder according to claim 2, characterized in that: A limiting structure is provided between the spring block and the mounting groove to prevent the spring block from detaching.

5. The quick-release rudder according to claim 4, characterized in that: The limiting structure includes a limiting step disposed on the side wall of the spring block, and a limiting flange disposed at the opening of the mounting groove for blocking the limiting step.

6. The quick-release rudder according to claim 5, characterized in that: The spring is sleeved on the outside of the spring block, and the two ends of the spring abut against the bottom of the mounting groove and the limiting step, respectively.

7. The quick-release rudder according to claim 6, characterized in that: The mounting groove extends through the root end face of the rudder shaft, and a plug is detachably connected to the bottom of the mounting groove.

8. The quick-release rudder according to claim 1, characterized in that: The card blocks are arranged in multiples and circumferentially spaced on the side wall of the insertion block, and the corresponding card slots are arranged in the same number and in the same distribution on the side wall of the slot.

9. The quick-release rudder according to claim 8, characterized in that: There are three card blocks, which are evenly arranged circumferentially.

10. An aircraft, characterized in that: It includes a control compartment, on which a quick-release rudder as described in any one of claims 1-9 and a servo motor for driving the rudder shaft are installed.

Images