Empennage mechanism capable of adjusting posture without power

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By designing a tail mechanism with no power adjustment posture, the automatic expansion of the wings and streamers are used to offset the initial disturbance, the problem of unstable flight status of the unpowered projectile is solved, static and dynamic stability is achieved, and the application scope of the tail mechanism is expanded.

CN119594808APending Publication Date: 2025-03-11JIANGSU NORTH ELECTRONIC CO LTD

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Patent Information

Application Number: CN202411775982.1
Authority / Receiving Office: CN · China
Patent Type: Applications(China)
Current Assignee / Owner
Filing Date: 2024-12-05
Publication Date: 2025-03-11

AI Technical Summary

Technical Problem

The existing unpowered projectiles have a large movement angle during flight, resulting in unstable flight status. The traditional method of adding fixed wings has high restrictions on use and cannot be promoted.

Method used

A tail wing mechanism with no power adjustment posture is designed, including the main housing, base, wings, pins, thrust torsion springs and streamers. Static stability is achieved through the automatic deployment of the wings. The streamers cancel the initial disturbance in the high-speed state, and the thrust torsion spring defines the vibration of the wings.

Benefits of technology

The static and dynamic stability of the bullet body is achieved, the use and application scope of the tail wing mechanism is expanded, the functional defects of the fixed wing are improved, and the application requirements of different bullet bodies are adapted through parameterized design.

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Abstract

The invention discloses an empennage mechanism capable of adjusting postures without power. The empennage mechanism comprises a main shell, a base, fins, pin shafts, thrust torsion springs and ribbons. The center of the fin is connected with the base through a pin shaft, and the thrust torsion spring is sleeved on the pin shaft and fixed in a sliding groove of the base. A mounting hole is formed in one end of the ribbon, and the mounting hole of the ribbon is connected with the mounting hole in the base through a fixing screw; a step surface is arranged at one end of the base, mounting holes are formed in the periphery of the step surface, and the step surface of the base and the step holes in one end of the main shell are positioned and mounted and are connected through screws. According to the invention, traditional functional parts are integrated, transformed and innovated, and the fins are automatically unfolded to realize the function of static stability; a ribbon is additionally arranged at the tail end of the base, so that dynamic stability can be realized; thrust torsion springs are installed between the fins so as to solve the problem of fin flutter.

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Description

Technical Field

[0001] The invention relates to the technical field of attitude adjustment, and in particular to a tail mechanism for adjusting attitude without power. Background Art

[0002] With the promotion of the use of unpowered projectiles, researchers have put forward higher requirements for the stability of the flight state of unpowered projectiles; the basic requirement for ensuring the stability of the motion state of unpowered projectiles is to keep the nutation angle small enough over the entire trajectory. The velocity deflection angle and the projectile axis swing angle based on the ideal trajectory will also be small, and the changes in other motion parameters will also be small.

[0003] The factors that affect the nutation angle are: static stability, dynamic stability and wing flutter. The current flight stability of unpowered projectiles is generally achieved by adding fixed wings, but the use of this technology has high restrictions and cannot be promoted. Due to the special application field of this technology and the high research cost, there are few studies and technical inventions. Summary of the invention

[0004] The object of the present invention is to provide a tail mechanism for adjusting attitude without power, so as to solve the problems in the background technology.

[0005] In order to solve the above technical problems, the present invention provides a tail wing mechanism for adjusting attitude without power, comprising: a main shell, a base, a wing, a pin shaft, a thrust torsion spring and a streamer;

[0006] The center of the wing is connected to the base through the pin shaft, and the thrust torsion spring is sleeved on the pin shaft and fixed in the slide groove of the base;

[0007] A mounting hole is provided at one end of the streamer, and the mounting hole of the streamer is connected to the mounting hole on the base by a fixing screw;

[0008] A step surface is provided at one end of the base, and mounting holes are provided around the step surface. The step surface of the base is positioned and installed with the step hole at one end of the main shell, and are connected by screws.

[0009] In one embodiment, the wing is unfolded under the torsion of the thrust torsion spring, and a side wall of the slide groove in the base is used as a limiting portion of the wing so that its working stroke will not exceed the tolerance; after the wing is unfolded, the thrust torsion spring uses lateral elastic force to push the wing toward the positioning groove on one side of the base to limit the vibration of the wing.

[0010] In one embodiment, the wing flap realizes the backward shift of the center of pressure of the projectile after being deployed, satisfying the distance difference between the center of mass and the center of pressure required for the static stability of the projectile; and the adjustment of the length and width parameters of the wing flap realizes the adjustment of the center of pressure of various projectiles.

[0011] In one embodiment, the streamer instantly offsets the initial disturbance of the projectile when it leaves the barrel after being deployed, thereby optimizing the disturbance environment required for the dynamic stability of the projectile; the adjustment of the length and width parameters of the streamer enables rapid convergence of the projectile posture with different current conditions and different initial velocities.

[0012] In one embodiment, the pin is cylindrical.

[0013] The present invention provides a tail mechanism with non-powered attitude adjustment, which integrates and innovates traditional functional components, automatically unfolds the wing to achieve the function of static stability; adds streamers to the tail end of the base to achieve dynamic stability; and installs thrust torsion springs between the wing to solve the problem of wing flutter. These functions expand the use and application scope of the present invention and improve some functional defects of the current fixed wing. In addition, the structural design of the present invention adopts a parametric design mode, which can adapt to the application requirements of different missiles by building different parameters, and improve the adaptability of the tail mechanism application to cope with the obstacles and pressures brought to the structural layout of the missile by various factors of various missiles. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a front view structural schematic diagram of a tail wing mechanism for adjusting attitude without power provided by the present invention;

[0015] Figure 2 is a rear view structural diagram of the tail wing mechanism of the present invention;

[0016] Figure 3 It is a side structural diagram of the tail wing mechanism of the present invention. DETAILED DESCRIPTION

[0017] The following is a further detailed description of a tail wing mechanism for adjusting attitude without power proposed by the present invention in combination with the accompanying drawings and specific embodiments. The advantages and features of the present invention will become clearer according to the following description. It should be noted that the accompanying drawings are all in a very simplified form and are not in precise proportions, and are only used to conveniently and clearly assist in explaining the purpose of the embodiments of the present invention.

[0018] The present invention provides a tail wing mechanism for adjusting posture without power, such as Figure 1 As shown, it includes a main housing 1, a base 2, a wing 3, a pin 4, a thrust torsion spring 5 and a streamer 6. The center of the wing 3 is connected to the base 2 through a columnar pin 4, and the outer ring of the pin 4 is equipped with a thrust torsion spring 5 and fixed in a slide groove of the base 2.

[0019] Through the above technical solution, the wing 3 is unfolded under the torsion of the thrust torsion spring 5, and the side wall of the slide groove of the base 2 is used as the limit part of the wing 3, so that its working stroke will not exceed the tolerance. After the wing 3 is unfolded, the pressure center of the projectile is moved backward, thereby satisfying the distance difference between the center of mass and the pressure center required for the static stability of the projectile. After the wing 3 is unfolded, the thrust torsion spring 5 uses the lateral elastic force to push the wing 3 to the positioning groove on one side of the base 2 to limit the vibration of the wing 3. The adjustment of the length and width parameters of the wing 3 can realize the pressure center adjustment of various projectiles.

[0020] like Figure 2 As shown, a mounting hole is provided at one end of the streamer 6, and the mounting hole is fixedly connected to the mounting hole on the base 2 by fixing screws.

[0021] Through the above technical solution, the mounting hole at one end of the streamer 6 is fixedly connected to the mounting hole on the base 2 by fixing screws, which can ensure that the streamer 6 is connected to the base 2 at high speed, and at the same time, the friction force received can be fed back to the projectile. The streamer 6 instantly offsets the initial disturbance of the projectile when it leaves the barrel after being unfolded, thereby optimizing the disturbance environment required for the dynamic stability of the projectile. Adjustment of the length and width parameters of the streamer 6 can achieve rapid convergence of the projectile posture with different initial velocities in different states.

[0022] like Figure 3 As shown, a step surface is provided at one end of the base 2, and mounting holes are provided around it. The step surface is positioned and installed with the step hole at one end of the main shell 1, and is fixedly connected by screws.

[0023] Through the above technical solution, it can be ensured that the tail wing mechanism and the main housing 1 are accurately positioned and reliably locked. This connection method can realize that the tail wing mechanism meets the use of bombs with different structures.

[0024] The above description is only a description of the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention. Any changes or modifications made by a person skilled in the art in the field of the present invention based on the above disclosure shall fall within the scope of protection of the claims.

Claims

1. A tail mechanism for adjusting attitude without power, characterized in that: include: A main housing (1), a base (2), a wing (3), a pin (4), a thrust torsion spring (5) and a streamer (6); The center of the wing (3) is connected to the base (2) through the pin shaft (4), and the thrust torsion spring (5) is sleeved on the pin shaft (4) and fixed in the slide groove of the base (2); One end of the streamer (6) is provided with a mounting hole, and the mounting hole of the streamer (6) is connected to the mounting hole on the base (2) by a fixing screw; One end of the base (2) is provided with a step surface, and mounting holes are provided around the step surface. The step surface of the base (2) is positioned and mounted with the step hole at one end of the main shell (1), and connected by screws.

2. The tail wing mechanism for adjusting attitude without power according to claim 1, characterized in that: The wing (3) is unfolded under the torsion of the thrust torsion spring (5), and a side wall of the slide groove in the base (2) is used as a limiting portion of the wing (3) so that its working stroke will not exceed the tolerance; after the wing (3) is unfolded, the thrust torsion spring (5) uses the lateral elastic force to push the wing (3) toward the positioning groove on one side of the base (2) to limit the vibration of the wing (3).

3. The tail wing mechanism for adjusting attitude without power according to claim 2, characterized in that: After being deployed, the wing (3) realizes the rearward shift of the center of pressure of the projectile, thereby satisfying the distance difference between the center of mass and the center of pressure required for the static stability of the projectile; and the adjustment of the length and width parameters of the wing (3) realizes the adjustment of the center of pressure of various projectiles.

4. The tail wing mechanism for adjusting attitude without power according to claim 1, characterized in that: The streamer (6) instantly offsets the initial disturbance of the projectile when it leaves the barrel after being deployed, thereby optimizing the disturbance environment required for the dynamic stability of the projectile; and the adjustment of the length and width parameters of the streamer (6) enables rapid convergence of the projectile posture at different current conditions and different initial velocities.

5. The tail wing mechanism for adjusting attitude without power according to claim 1, characterized in that: The pin shaft (4) is columnar.