Low-altitude release self-adaptive stable posture and drag reduction aerial bomb tail wing mechanism and stabilizing method
By using a fully mechanical dynamic pressure adaptive tail fin mechanism, rapid attitude stabilization and high-speed drag reduction are achieved during low-altitude deployment. This solves the problems of attitude instability and excessive drag of existing tail fin mechanisms during low-altitude deployment, improves hit accuracy and ballistic control capabilities, and is suitable for low-altitude deployment by UAVs and fighter jets.
Patent Information
- Application Number
- CN202611511071.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2026-09-28
- Publication Date
- 2026-11-06
AI Technical Summary
Existing aerial bomb tail fin mechanisms cannot simultaneously achieve rapid attitude stabilization and high-speed drag reduction during low-altitude deployment, and the reliability of electronically controlled adaptive tail fins is poor, resulting in large ballistic drift and low hit accuracy, which cannot meet the high-precision requirements of low-altitude deployment.
The tail fin mechanism is a fully mechanical dynamic pressure adaptive tail fin mechanism. Through the sliding tail fin structure and the tail stabilizing ring, the tail fin angle is adaptively adjusted by the return spring and the circumferential transmission link. It is stable when the tail fin is fully open at low altitude and retracts to reduce drag at high speed. It simulates the telescopic transmission principle of the parachute rib link to achieve passive mechanical drive.
It can quickly stabilize the attitude when dropped at low altitudes, suppress missile oscillation, shorten flight time, improve hit accuracy, reduce aerodynamic drag, and enhance trajectory straightness and hit accuracy. It is highly adaptable, low in cost, and suitable for mass modification of existing aerial bombs.
Smart Images
Figure CN123045158A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of aerodynamic structure technology for aviation munitions, specifically to a mechanical attitude stabilization and drag reduction tail fin mechanism that can adaptively adjust the angle of the tail fin according to flight motion pressure. It is applicable to the high-precision ballistic stabilization scenarios of low-altitude delivery of aviation bombs by UAVs and low-altitude close-range support delivery by fighter jets, and is a low-altitude delivery adaptive attitude stabilization and drag reduction tail fin mechanism and stabilization method for aviation bombs. Background Technology
[0002] Most conventional aerial bombs currently use a fixed-angle tail fin structure, which has obvious technical shortcomings. Under low-altitude delivery conditions, the bomb body falls at a low altitude, has a short loiter time, a low initial flight speed, and low aerodynamic pressure. The fixed small-angle tail fin has insufficient stabilizing torque and cannot quickly suppress the pitch, yaw, and roll disturbances after the bomb body leaves the aircraft. The attitude does not have time to converge before hitting the ground, resulting in a large dispersion of the impact point and low hit accuracy.
[0003] If a fixed, large-angle tail fin is used, although it can improve low-altitude attitude stability, the missile will have a large frontal area and high aerodynamic drag throughout its descent. It will also have a slow descent speed and a long flight time, making it highly susceptible to crosswinds and turbulence. It will also have the problem of large trajectory drift. Furthermore, the long flight time will increase the probability of enemy early warning, evasion, and interception.
[0004] The existing small number of adaptive tail fins mostly use electronically controlled servos and sensor-driven adjustment, which are complex in structure, high in cost, poor in resistance to high overload, and have low reliability in long-term storage, making them unsuitable for mass application in conventional aircraft bodies.
[0005] In summary, the lack of a purely mechanical, passive, adaptive tail fin mechanism for bombs that can simultaneously achieve rapid attitude stabilization at low altitudes and high-speed drag reduction and acceleration is the core bottleneck restricting the improvement of accuracy when launching bombs at low altitudes. Summary of the Invention
[0006] To address the problems mentioned in the background art and overcome the shortcomings of existing fixed tail fins being incompatible with high and low altitude conditions and having poor reliability of electronically controlled adaptive tail fins, this invention provides a fully mechanical dynamic pressure adaptive bomb tail fin mechanism that enables automatic switching between wide-open attitude stabilization at low altitudes and low speeds and retraction and drag reduction at high speeds, thereby optimizing the overall ballistic performance of the bomb body during low-altitude deployment.
[0007] The present invention provides the following technical solution: a tail fin mechanism for low-altitude delivery adaptive attitude stabilization and drag reduction aerial bombs, including a bomb body base, a sliding tail fin structure and a tail stabilizing ring; the bomb body base is fixedly connected to the aerial bomb body, the tail stabilizing ring is fixedly connected to the bomb body base, and the sliding tail fin structure is disposed on the bomb body base. The sliding tail fin structure includes a tail fin mounting base, a slip ring, a return spring, multiple sets of circumferential transmission links, a winglet, and a front limiting step. The tail fin mounting base is fixedly connected to the projectile base. The slip ring and return spring are sleeved on the projectile base. The front limiting step is located between the tail fin mounting base and the slip ring to limit the maximum stroke of the return spring. The return spring is located between the slip ring and the tail stabilizing ring to provide force to the slip ring. One end of the winglet is movably connected to the tail fin mounting base, and the other end is movably connected to the slip ring through the circumferential transmission links. The return spring pushes the slider to slide in the axial direction, thereby pushing the winglet to open or close.
[0008] Preferably, the tail fin mounting base is provided with a mounting boss A, and the wing is mounted on the mounting boss A through a through pin A and a wing hole A, with the other end of the wing opening or closing around the through pin A.
[0009] Preferably, the slip ring is provided with a mounting boss B, one end of the circumferential transmission connecting rod is mounted on the mounting boss B via a through pin B, and the other end is connected to the vane hole B. Preferably, the number of winglets and circumferential transmission links is 3-6 sets, which are evenly distributed along the circumference of the tail fin mounting base and slip ring.
[0010] A stabilization method for the tail fin mechanism of a low-altitude-deployed adaptive attitude-stabilized and drag-reducing aerial bomb, comprising the following steps: S1. In the initial state, the external environmental force of the aerial bomb warhead is 0. The return spring pushes the slider to the front limit step. The slider drives the circumferential transmission link to push the wing to open around the tail fin fixed seat. At this time, the wing is at its maximum opening angle. S2. During the initial attitude stabilization phase of low-altitude drop, the aerial bomb has just left the aircraft. Its flight speed is low and its dynamic pressure is small. The thrust from the wind is insufficient to overcome the preload of the return spring. The slip ring remains at the front limit step position, and the circumferential transmission link pushes the wing to maintain the maximum opening angle. At this time, the maximum stabilizing torque is output, which can quickly converge the body oscillation and straighten the trajectory attitude in a short time, suppressing the aerial bomb's tumbling and nutation. S3. During the high-altitude, high-speed descent and drag reduction phase, the flight speed of the aerial bomb continuously increases, and the aerodynamic pressure and wind resistance continue to increase. The windward pressure surface of the wing is subjected to aerodynamic force to overcome the preload of the return spring, which drives the circumferential transmission link to push the slip ring to slide backward, compressing the return spring to the rear limit. During the sliding process, the circumferential transmission link simultaneously pulls the wing to retract inward, reducing the wing opening angle and windward area, reducing the overall wind resistance of the bomb, increasing the descent speed, and shortening the flight time.
[0011] Furthermore, in the S2 state, the entire tail fin mechanism can be straightened by the tail stabilizing ring to suppress vortex separation between the aircraft body and the entire tail fin mechanism.
[0012] Compared with the prior art, the beneficial effects achieved by the present invention are: 1. This invention solves the problem of attitude instability during low-altitude delivery: it outputs a large stable torque at a large angle during the initial delivery stage, quickly suppresses the tumbling and nutation of the projectile, and rapidly completes attitude convergence under a short trajectory, reducing the initial trajectory dispersion of the munition from the source and significantly improving the accuracy of low-altitude delivery.
[0013] 2. This invention also solves the problem of automatic drag reduction and acceleration during the fall of aerial bombs, compressing the dispersion of impact points. After the attitude stabilizes, the tail fins automatically retract, reducing the overall wind resistance of the bomb, increasing the fall speed, shortening the flight time, significantly reducing the duration of crosswinds and turbulence, significantly improving the straightness of the trajectory, and greatly improving the accuracy of the hit.
[0014] 3. This invention adopts a multi-tail fin synchronization, with no additional ballistic deviation: the circumferential linkage synchronous transmission structure ensures that the opening angle of the multiple tail fins is completely consistent, ensuring the aerodynamic symmetry of the ammunition throughout the entire process, with no unilateral offset torque, effectively avoiding additional ballistic yaw.
[0015] 4. This invention adopts a purely mechanical structure, which is highly reliable and suitable for harsh military scenarios: it has no circuits, no chips, no servo motors, and no batteries. It achieves self-adaptive function by relying on a purely mechanical structure. It is resistant to vibration, high overload, high and low temperatures, and can be stored for a long time, fully meeting the requirements for use in aviation ammunition.
[0016] In summary, this invention offers adaptive compatibility for both high and low altitude conditions, broadening the delivery envelope of aerial bombs and munitions: a single mechanism simultaneously meets the requirements for low-altitude attitude stability and high-speed drag reduction, resolving the dilemma of traditional fixed-tail fins being "slow when stable, drifting when fast," adapting to low-altitude delivery conditions at different altitudes and speeds, and exhibiting extremely high versatility; enhancing the tactical penetration capability of munitions: shortening the overall flight time of munitions, compressing the enemy's early warning, maneuver evasion, and close-in defense interception windows, significantly improving the effectiveness of low-altitude penetration strikes. High adaptability and low modification cost: only the tail fin mechanism is optimized, without modifying the core structures of the munition's warhead, explosive charge, fuse, and detonation sequence, allowing direct adaptation to existing standard aerial bombs for retrofitting, resulting in low cost for mass application. Attached Figure Description
[0017] Figure 1 This is a schematic diagram of the overall structure of the present invention mounted on an aerial bomb; Figure 2 This is a schematic diagram of the entire front and rear of the present invention mounted on an aerial bomb; Figure 3 This is a schematic diagram of the tail fin mechanism of the present invention; Figure 4 This is a cross-sectional view of the tail fin mechanism of the present invention; Figure 5 This is a working diagram of the tail wing mechanism of the present invention at the large opening angle of the winglets in low-altitude state; Figure 6 This is a diagram showing the wing retraction mechanism of the tail wing in high-speed drag reduction mode according to the present invention. Figure 7 This is an overall cross-sectional view of the invention mounted on an aerial bomb; Figure 8 This is a diagram of the wing structure in an embodiment of the present invention; Figure 9 This is a structural diagram of the circumferential transmission connecting rod in an embodiment of the present invention; Figure 10 This is a structural diagram of the tail fin mounting bracket in an embodiment of the present invention; Figure 11 This is a diagram of the slip ring structure in an embodiment of the present invention; Reference numerals: 1-Tail fin mounting base, 2-Projectile base, 3-Front limit step, 4-Slip ring, 5-Circumferential transmission link, 6-Flange, 7-Return spring, 8-Tail stabilizing ring, 9-Mounting boss A, 10-Mounting boss B, 11-Through pin A, 12-Through pin B, 13-Fuse, 14-Projectile body, 15-Fasting screw, 16-Flange hole A, 17-Flange hole B, 18-Connecting hole A, 19-Connecting hole B. Detailed Implementation
[0018] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. 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 are within the scope of protection of the present invention.
[0019] The working principle of this invention is as follows: A passive mechanical structure consisting of a tail fin mounting base 1, an axial sliding ring 3, multiple circumferentially articulated links, and an adaptive tail fin, simulates the telescopic transmission principle of a parachute rib link, enabling adaptive adjustment of the tail fin's opening angle according to flight dynamic pressure. In the initial low-altitude deployment phase, with low flight speed and small aerodynamic load, the return spring 7 pushes the sliding ring 3 backward, driving the tail fin to maintain a large opening angle via the link, quickly establishing aerodynamic stabilizing torque, and rapidly correcting the projectile's attitude and suppressing tumbling oscillations within a short time. As the projectile's descent speed increases, aerodynamic drag and dynamic pressure increase, and the windward aerodynamic force pushes the sliding ring 3 forward to overcome the spring preload, causing the link to simultaneously retract multiple tail fins, reducing the tail fin's windward area and overall projectile aerodynamic drag, increasing descent speed, shortening flight time, and reducing wind disturbance deviation and landing point dispersion. This invention features a fully mechanical, passive drive system that requires no electronic control or sensors. It boasts a reliable structure and strong environmental adaptability, effectively resolving the technical contradiction that traditional fixed tail fins cannot simultaneously achieve low-altitude attitude stability and high-speed drag reduction. This significantly improves the accuracy and combat envelope of low-altitude, close-range projectiles.
[0020] Example
[0021] The present invention includes a projectile base 2, a sliding tail fin structure and a tail stabilizing ring 8; the projectile base 2 is fixedly connected to the aerial bomb body, the sliding tail stabilizing ring 8 is fixedly connected to the projectile base 2, and the sliding tail fin structure is disposed on the projectile base 2. The sliding tail fin structure includes a tail fin mounting base 1, a slip ring 3, a return spring 7, multiple sets of circumferential transmission links 5, a winglet 6, and a front limiting step 3. The tail fin mounting base 1 is fixedly connected to the projectile base 2. The slip ring 3 and the return spring 7 are sleeved on the projectile base 2. The front limiting step 3 is located between the tail fin mounting base 1 and the slip ring 3 to limit the maximum stroke of the return spring 7. The return spring 7 is located between the slip ring 3 and the tail stabilizing ring 8 to provide force to the slip ring 3. One end of the winglet 6 is movably connected to the tail fin mounting base 1, and the other end is movably connected to the slip ring 3 through the circumferential transmission links 5. The return spring 7 pushes the slider to slide in the axial direction, thereby pushing the winglet 6 to open or close.
[0022] Preferably, the tail fin mounting base 1 is provided with a mounting boss A9, and the wing 6 is mounted on the mounting boss A9 through a through pin A11. The other end of the wing 6 opens or closes around the through pin A11.
[0023] Preferably, the wing 6 is provided with a mounting boss B10, and the circumferential transmission link 5 is mounted on the mounting boss B10 through a through pin B12. The circumferential transmission link 5 moves up and down around the through pin B12 and pushes the wing 6 to open or close around the connecting shaft.
[0024] Preferably, the number of winglets 6 and circumferential transmission links 5 is 3-6 sets, which are evenly distributed along the circumference of the tail fin mounting base 1 and the slip ring 3.
[0025] Our organization's work process is divided into two adaptive phases: 1) Initial attitude stabilization phase of low-altitude delivery: As soon as the missile leaves the aircraft, the flight speed is low and the dynamic pressure is small. The thrust from the wind is insufficient to overcome the spring preload. The slip ring 3 is kept in the front limit position, and the connecting rod pushes the tail fin to maintain the maximum opening angle, which greatly improves the aerodynamic restoring torque. In a very short time of loiter, the missile oscillation is quickly converged and the trajectory attitude is corrected, solving the problems of low-altitude attitude instability and large initial disturbance.
[0026] 2) High-speed descent drag reduction stage: As the missile continues to fall, the flight speed increases continuously, and the aerodynamic pressure and wind resistance continue to increase. The aerodynamic force on the windward pressure surface overcomes the preload of the return spring 7 and pushes the slip ring 3 to slide backward, maintaining force balance with the return spring 7 until the rear limit. During the sliding process, the connecting rod synchronously pulls the multiple tail fins to retract inward, reducing the tail fin angle and windward area, significantly reducing the overall aerodynamic drag of the missile, increasing the descent speed and shortening the flight time.
[0027] The annular tail stabilizing ring 8 at the rear of the tail fin increases the aerodynamic righting effect in the low-pressure area at low altitude and low speed; suppresses vortex separation at the tail of the missile body and reduces short-trajectory attitude instability; and works with the adaptive tail fin to form a dual attitude stabilization system of "main fin + auxiliary ring".
[0028] This invention achieves complete passive self-adaptation through a purely mechanical structure, automatically matching the optimal tail fin angle based on the real-time flight pressure of the projectile, without manual intervention or electronic control adjustment, thus comprehensively optimizing the ballistic performance of low-altitude delivery.
[0029] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.
Claims
1. A tail fin mechanism for low-altitude delivery adaptive attitude stabilization and drag reduction aerial bombs, characterized in that: It includes a missile body base, a sliding tail fin structure, and a tail stabilizing ring; the missile body base is fixedly connected to the aerial bomb body, the tail stabilizing ring is fixedly connected to the missile body base, and the sliding tail fin structure is located on the missile body base. The sliding tail fin structure includes a tail fin mounting base, a slip ring, a return spring, multiple sets of circumferential transmission links, a winglet, and a front limiting step. The tail fin mounting base is fixedly connected to the projectile base. The slip ring and return spring are sleeved on the projectile base. The front limiting step is located between the tail fin mounting base and the slip ring to limit the maximum stroke of the return spring. The return spring is located between the slip ring and the tail stabilizing ring to provide force to the slip ring. One end of the winglet is movably connected to the tail fin mounting base, and the other end is movably connected to the slip ring through the circumferential transmission links. The return spring pushes the slider to slide in the axial direction, thereby pushing the winglet to open or close.
2. The tail fin mechanism for low-altitude delivery adaptive attitude stabilization and drag reduction of aerial bombs according to claim 1, characterized in that: The tail fin mounting base is provided with a mounting boss A. The wing is mounted on the mounting boss A through a through pin A and a wing hole A. The other end of the wing opens or closes around the through pin A.
3. The tail fin mechanism for low-altitude delivery adaptive attitude stabilization and drag reduction of aerial bombs according to claim 2, characterized in that: The slip ring is provided with a mounting boss B. One end of the circumferential transmission link is set on the mounting boss B through the through pin B, and the other end is connected to the vane hole B. The circumferential transmission link moves up and down around the through pin B, and pushes the vane to open or close around the connecting shaft.
4. The tail fin mechanism for low-altitude delivery adaptive attitude stabilization and drag reduction aerial bombs according to any one of claims 1-3, characterized in that: The number of winglets and circumferential transmission links is 3-6 sets, which are evenly distributed along the circumference of the tail fin mount and slip ring.
5. A stabilization method for the tail fin mechanism of a low-altitude adaptive attitude stabilization and drag reduction aerial bomb as described in claim 4, characterized in that: Includes the following steps: S1. In the initial state, the external environmental force of the aerial bomb warhead is 0. The return spring pushes the slider to the front limit step. The slider drives the circumferential transmission link to push the wing to open around the tail fin fixed seat. At this time, the wing is at its maximum opening angle. S2. During the initial attitude stabilization phase of low-altitude drop, the aerial bomb has just left the aircraft. Its flight speed is low and its dynamic pressure is small. The thrust from the wind is insufficient to overcome the preload of the return spring. The slip ring remains at the front limit step position, and the circumferential transmission link pushes the wing to maintain the maximum opening angle. At this time, the maximum stabilizing torque is output, which can quickly converge the body oscillation and straighten the trajectory attitude in a short time, suppressing the aerial bomb's tumbling and nutation. S3. During the high-altitude, high-speed descent and drag reduction phase, the flight speed of the aerial bomb continuously increases, and the aerodynamic pressure and wind resistance continue to increase. The windward pressure surface of the wing is subjected to aerodynamic force to overcome the preload of the return spring, which drives the circumferential transmission link to push the slip ring to slide backward, compressing the return spring to the rear limit. During the sliding process, the circumferential transmission link simultaneously pulls the wing to retract inward, reducing the wing opening angle and windward area, reducing the overall wind resistance of the bomb, increasing the descent speed, and shortening the flight time.
6. The method for deploying a low-altitude adaptive attitude-stabilized drag-reducing aerial bomb tail fin mechanism according to claim 5, characterized in that: In the S2 state, the entire tail fin mechanism can also be straightened by the tail stabilizing ring to suppress vortex separation between the aircraft body and the entire tail fin mechanism.