Small-space rudder wing folding mechanism and using and mounting method thereof

Abstract

The small-space rudder wing folding mechanism is characterized by comprising an inclined stop block, a wing panel, a rudder wing seat, a rudder wing shaft, a rudder wing torsion spring and a rudder wing seat spring, an inclined stop block is arranged on the rudder wing seat, a rudder wing seat spring is arranged in the inclined stop block, a wing panel is arranged in front of the inclined stop block through a rudder wing shaft, and a rudder wing torsion spring is arranged below the wing panel through the rudder wing shaft; under the acting force of a rudder wing seat spring, a stop step with a trapezoidal cross section is arranged at the contact position of the inclined stop block and the root of the wing panel, and a step surface and an inclined surface are correspondingly arranged at the root of the wing panel; when the inclined stop block is pressed, the restraint of the stop step on the root of the wing panel can be relieved, and the wing panel can freely rotate along the rudder wing shaft; the device is simple in structure, small in number of parts, convenient to disassemble and maintain, reliable in structure, small in unlocking force and convenient to operate, repeated unfolding and folding of the fins are achieved through simple operation, time and labor are saved, and preparation time for missile launching is greatly shortened on the premise that repeated operation of a ground test is met.

Description

Technical Field

[0001] The invention relates to the technical field of missiles, in particular to a small-space rudder wing folding mechanism of a miniature missile and a use and installation method thereof. Background Art

[0002] Existing micro-missiles also have the aerodynamic shape structure of large airborne missiles. For the convenience of storage and transportation, the rudders can be folded during storage and unfolded during later use.

[0003] It has the following shortcomings and deficiencies in use, daily training and repeated ground tests:

[0004] The missile rudder folding mechanism has a complex structure and occupies a large radial space, which leads to a narrow remaining space structure in the missile servo compartment, thus greatly increasing the difficulty of the structural design and cabin layout of the electric servo.

[0005] After the rudder wings are released, deployed and locked, the traditional rudder wing deployment and locking mechanism has too much unlocking force or is for one-time use, which is not conducive to daily training and repeated ground tests.

[0006] After the existing rudder wings are fully deployed, they will still shake back and forth, and the shaking of the rudder wings will affect the stability of the subsequent missile launch flight process. Summary of the invention

[0007] In order to solve the defects and shortcomings in the above-mentioned prior art, the present invention provides a small-space rudder wing folding mechanism with simple structure, easy use, and stable performance of the rudder wing after being unfolded, as well as a use and installation method thereof.

[0008] The technical solution of the present invention is as follows: a small-space rudder wing folding mechanism comprises an inclined stopper, a wing, a rudder wing seat, a rudder wing shaft, a rudder wing torsion spring and a rudder wing seat spring; the rudder wing seat is provided with an inclined stopper, the rudder wing seat spring is provided inside the inclined stopper, the wing is arranged in front of the inclined stopper through the rudder wing shaft, and the rudder wing torsion spring is arranged below the wing through the rudder wing shaft; under the action of the rudder wing seat spring, a blocking step with a trapezoidal cross section is provided at the contact position between the inclined stopper and the root of the wing, and a step surface and an inclined surface are correspondingly provided at the root of the wing; pressing the inclined stopper can release the constraint of the blocking step on the root of the wing, and the wing can rotate freely along the rudder wing shaft;

[0009] When the wing is folded, the contact surface between the oblique stopper and the root of the wing is a plane on the step surface, and the oblique stopper is acted upward by the force of the rudder wing seat spring and contacts the root of the wing; when the wing is unfolded, the oblique stopper is pressed, and the constraint on the root of the wing on the step surface of the oblique stopper is released, and the wing can be rotated and unfolded along the rudder wing axis under the force of the rudder wing torsion spring. After the wing is unfolded to the full extent, the oblique stopper is released, and the contact surface between the oblique stopper and the root of the wing is a side inclined surface, and the wing is acted on by the rudder wing torsion spring and the rudder wing seat spring and contacts the oblique stopper.

[0010] Furthermore, a limiting protrusion is provided on one side of the inclined surface at the root of the wing; after the wing is unfolded, the limiting protrusion abuts against the rudder wing seat, and the inclined surface contact is achieved between the inclined stop block and the wing through the action force of the rudder wing torsion spring and the limiting effect of the limiting protrusion.

[0011] Furthermore, the bevel angles of the bevel contact surface of the wing and the bevel contact surface of the corresponding bevel stopper are not greater than 15 degrees.

[0012] Furthermore, by pressing the oblique stopper, the wing can freely rotate along the rudder wing axis to an angle of 0-90 degrees.

[0013] Furthermore, it also includes a retaining ring arranged on one side of the rudder wing shaft, which is used to prevent the rudder wing torsion spring from deviating on the rudder wing shaft.

[0014] A method for operating a small space rudder wing folding mechanism, the specific method is:

[0015] When the missile is in use, the inclined stopper is pressed, and the constraint on the root of the wing blade facing the upper step of the inclined stopper is released. The wing blade is rotated and opened along the rudder wing axis by the force of the rudder wing torsion spring. After the wing blade is fully unfolded, the inclined stopper is released. The contact surface between the inclined stopper and the root of the wing blade is a side inclined surface, and the root of the wing blade is in conflict with the inclined stopper due to the force of the rudder wing torsion spring.

[0016] When the missile is retracted and stored during ground testing or training, press the oblique stop, manually rotate the wing and fold it into the servo cabin, then release the oblique stop. At this time, the rotation angle between the wing and the rudder wing seat is 0 degrees, the rudder wing torsion spring is in a compressed energy storage state, the contact surface between the oblique stop and the root of the wing is a plane on the step surface, and the oblique stop is acted on upward by the force of the rudder wing seat spring and contacts the wing.

[0017] Furthermore, the rotation angle of the wing after being fully deployed is 90 degrees.

[0018] A method for installing a small-space rudder wing folding mechanism as described in any one of claims 1 to 5, characterized in that the specific method is: install the rudder wing torsion spring into the inclined block, then flip the inclined block equipped with the rudder wing seat spring into the rudder wing seat, insert the rudder wing shaft, install the rudder wing torsion spring and wing on the rudder wing shaft in sequence, adjust the position of the rudder wing torsion spring and wing to ensure that the wing can rotate freely along the rudder wing shaft, and finally rotate and install a retaining ring on the end of the rudder wing shaft, and the overall mechanism is installed.

[0019] Compared with the prior art, the present invention has the following beneficial effects:

[0020] The present invention adopts a long shaft and a retaining ring to fix the torsion spring, which effectively saves space for fixing the torsion spring.

[0021] The present invention adopts the inclined surface limiting design of the inclined stopper and the wing in the unfolded state, which reduces the height of the entire folding mechanism, requires a smaller unlocking force, saves radial space in the cabin, and can also achieve repeated opening and closing during repeated ground tests.

[0022] When the wing of the present invention is unfolded and unlocked, the wing is ejected with the help of a torsion spring, which reduces the difficulty of unlocking and saves a certain amount of time for missile launch preparation.

[0023] In summary, the present invention has a simple structure, a small number of parts, and is convenient for disassembly and maintenance. Under the requirements of miniaturization and lightweight of missiles, it saves precious space and weight for the entire cabin section. In addition, the structure is reliable, the unlocking force is small, and the operation is convenient. The wing flaps can be repeatedly unfolded and folded through simple operations, which saves time and effort. On the premise of meeting the repeated operations of ground tests, the preparation time for missile launch is greatly shortened. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a schematic diagram of the structure of the unfolded state of the present invention.

[0025] Figure 2 It is a schematic diagram of the structure of the present invention in a folded state.

[0026] Figure 3 It is a cross-sectional view of the present invention in an unfolded state.

[0027] Figure 4 It is a cross-sectional view of the present invention in a folded state.

[0028] Figure markings: 1- oblique stopper, 2- blocking step, 3- wing, 4- rudder wing seat, 5- rudder wing shaft, 6- rudder wing torsion spring, 7- rudder wing seat spring, 8- limiting protrusion. DETAILED DESCRIPTION

[0029] The present invention will be further described in detail below in conjunction with the accompanying drawings, but this does not limit the protection scope of the present invention.

[0030] Embodiment 1 of the present invention:

[0031] A small-space rudder wing folding mechanism comprises an inclined stopper, a wing, a rudder wing seat, a rudder wing shaft, a rudder wing torsion spring and a rudder wing seat spring; the rudder wing seat is provided with an inclined stopper, the rudder wing seat is provided with a rudder wing seat spring, the wing is arranged in front of the inclined stopper through the rudder wing shaft, and the rudder wing torsion spring is arranged below the wing through the rudder wing shaft; under the action of the rudder wing seat spring, a blocking step with a trapezoidal cross section is provided at the contact position between the inclined stopper and the root of the wing, and a step surface and an inclined surface are correspondingly provided at the root of the wing; pressing the inclined stopper can release the constraint of the blocking step on the root of the wing, and the wing can rotate freely along the rudder wing shaft;

[0032] Wherein, the bevel angle of the bevel contact surface of the wing and the bevel contact surface of the corresponding bevel stopper is not greater than 15 degrees.

[0033] When the oblique stopper is pressed, the wing can freely rotate along the rudder wing axis to an angle of 0-90 degrees.

[0034] It also includes a retaining ring arranged on one side of the rudder wing shaft. The retaining ring is a standard part and is used to prevent the rudder wing torsion spring from deviating on the rudder wing shaft.

[0035] When the wing is folded, the contact surface between the oblique stopper and the root of the wing is a plane on the step surface, and the oblique stopper is acted upward by the force of the rudder wing seat spring to contact the root of the wing;

[0036] When the wing is unfolded, the inclined stopper is pressed, and the constraint on the root of the wing by the upper step of the inclined stopper is released. The wing can be rotated and unfolded along the rudder wing axis by the force of the rudder wing torsion spring. After the wing is fully unfolded, the inclined stopper is released, and the contact surface between the inclined stopper and the root of the wing is a side inclined surface. The wing is subjected to the force of the rudder wing torsion spring and the rudder wing seat spring and contacts the inclined stopper. At this time, the force of the rudder wing seat spring and the force of the rudder wing torsion spring cancel each other out.

[0037] Embodiment 2:

[0038] As a further improvement, a limiting protrusion is further provided on one side of the inclined surface at the root of the wing; after the wing is fully deployed, the limiting protrusion abuts against the rudder wing seat, and the inclined surface of the inclined stopper and the wing are in contact with each other through the force of the rudder wing torsion spring and the limiting effect of the limiting protrusion. The setting of the limiting protrusion further ensures the stability of the wing after deployment. After the wing is deployed, the wing is limited forward by the limiting protrusion, and backward by the force of the rudder wing torsion spring. The bottom is also affected by the upward force of the rudder wing seat spring and the rudder wing seat. Therefore, compared with the first embodiment, the wing is more stable after deployment.

[0039] A method for operating a small space rudder wing folding mechanism, the specific method is:

[0040] When the missile is in use, the inclined stopper is pressed, and the constraint on the root of the wing blade facing the upper step of the inclined stopper is released. The wing blade is rotated and opened along the rudder wing axis by the force of the rudder wing torsion spring. After the wing blade is fully unfolded, the inclined stopper is released. The contact surface between the inclined stopper and the root of the wing blade is a side inclined surface, and the root of the wing blade is in conflict with the inclined stopper due to the force of the rudder wing torsion spring.

[0041] When the missile is retracted and stored during ground testing or training, press the oblique stop, manually rotate the wing and fold it into the servo cabin, then release the oblique stop. At this time, the rotation angle between the wing and the rudder wing seat is 0 degrees, the rudder wing torsion spring is in a compressed energy storage state, the contact surface between the oblique stop and the root of the wing is a plane on the step surface, and the oblique stop is acted on upward by the force of the rudder wing seat spring and contacts the wing.

[0042] Furthermore, the rotation angle of the wing after being fully deployed is 90 degrees.

[0043] A method for installing a small-space rudder wing folding mechanism as described in any one of claims 1 to 5, characterized in that the specific method is: install the rudder wing torsion spring into the inclined block, then flip the inclined block equipped with the rudder wing seat spring into the rudder wing seat, insert the rudder wing shaft, install the rudder wing torsion spring and wing on the rudder wing shaft in sequence, adjust the position of the rudder wing torsion spring and wing to ensure that the wing can rotate freely along the rudder wing shaft, and finally rotate and install a retaining ring on the end of the rudder wing shaft, and the overall mechanism is installed.

[0044] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A small space rudder wing folding mechanism, characterized in that: It comprises an inclined stopper, a wing, a rudder wing seat, a rudder wing shaft, a rudder wing torsion spring and a rudder wing seat spring; the rudder wing seat is provided with an inclined stopper, the rudder wing seat spring is provided inside the inclined stopper, the wing is arranged in front of the inclined stopper through the rudder wing shaft, and the rudder wing torsion spring is arranged below the wing through the rudder wing shaft; under the action of the rudder wing seat spring, a blocking step with a trapezoidal cross section is provided at the contact position between the inclined stopper and the root of the wing, and a step surface and an inclined surface are correspondingly provided at the root of the wing; pressing the inclined stopper can release the constraint of the blocking step on the root of the wing, and the wing can rotate freely along the rudder wing shaft; When the wing is folded, the contact surface between the oblique stopper and the root of the wing is a plane on the step surface, and the oblique stopper is acted upward by the force of the rudder wing seat spring and contacts the root of the wing; when the wing is unfolded, the oblique stopper is pressed, and the constraint on the root of the wing on the step surface of the oblique stopper is released, and the wing can be rotated and unfolded along the rudder wing axis under the force of the rudder wing torsion spring. After the wing is unfolded to the full extent, the oblique stopper is released, and the contact surface between the oblique stopper and the root of the wing is a side inclined surface, and the wing is acted on by the rudder wing torsion spring and the rudder wing seat spring and contacts the oblique stopper.

2. The small space rudder wing folding mechanism according to claim 1, characterized in that: A limiting protrusion is also provided on one side of the inclined surface at the root of the wing; after the wing is unfolded, the limiting protrusion abuts against the rudder wing seat, and the inclined surface contact is achieved between the inclined stopper and the wing through the action force of the rudder wing torsion spring and the limiting effect of the limiting protrusion.

3. The small space rudder wing folding mechanism according to claim 1, characterized in that: The bevel angles of the bevel contact surface of the wing and the bevel contact surface of the corresponding bevel stopper are no greater than 15 degrees.

4. The small space rudder wing folding mechanism according to claim 2, characterized in that: By pressing the oblique stopper, the wing can rotate freely along the rudder wing axis to an angle of 0-90 degrees.

5. The small space rudder wing folding mechanism according to claim 1, characterized in that: It also includes a retaining ring arranged on one side of the rudder wing shaft, which is used to prevent the rudder wing torsion spring from deviating on the rudder wing shaft.

6. A method for operating the small space rudder wing folding mechanism according to any one of claims 1 to 5, characterized in that: The specific method is: When the missile is in use, the inclined stopper is pressed, and the constraint on the root of the wing blade facing the upper step of the inclined stopper is released. The wing blade is rotated and opened along the rudder wing axis by the force of the rudder wing torsion spring. After the wing blade is fully unfolded, the inclined stopper is released. The contact surface between the inclined stopper and the root of the wing blade is a side inclined surface, and the root of the wing blade is in conflict with the inclined stopper due to the force of the rudder wing torsion spring. When the missile is retracted and stored during ground testing or training, press the oblique stop, manually rotate the wing and fold it into the servo cabin, then release the oblique stop. At this time, the rotation angle between the wing and the rudder wing seat is 0 degrees, the rudder wing torsion spring is in a compressed energy storage state, the contact surface between the oblique stop and the root of the wing is a plane on the step surface, and the oblique stop is acted on upward by the force of the rudder wing seat spring and contacts the wing.

7. The method for operating the small space rudder wing folding mechanism according to claim 6, characterized in that: The wing has a rotation angle of 90 degrees after it is fully deployed.

8. A method for installing a small space rudder wing folding mechanism according to any one of claims 1 to 5, characterized in that: The specific method is: first install the rudder wing torsion spring into the inclined block, then turn over and install the inclined block with the rudder wing seat spring into the rudder wing seat, insert the rudder wing shaft, install the rudder wing torsion spring and wing on the rudder wing shaft in turn, adjust the position of the rudder wing torsion spring and wing to ensure that the wing can rotate freely along the rudder wing shaft, and finally rotate and install the retaining ring at the end of the rudder wing shaft, and the overall mechanism is installed.

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