Empennage folding mechanism of patrolling bomb
By designing a cruise missile tail folding mechanism including tail wing, servo, rocker and elastic parts, the problems of folding and rapid deployment in a small space are solved, the stability and control of cruise missiles are achieved, the structure is simplified and improved. Battery endurance.
Patent Information
- Application Number
- CN202421694419.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-07-17
- Publication Date
- 2024-12-27
- Estimated Expiration
- 2034-07-17
AI Technical Summary
The existing cruise missile tail folding mechanism is difficult to realize the rapid deployment of the existing cruise missile after folding and launching in a narrow space, which affects the stability and control of the cruise missile.
A folding mechanism including a tail wing, a servo, a rocker and an elastic member is designed. Using the main hinge ring, a guide slider, a guide slide curved surface, a limit surface, a spring and other components, the guide slider is driven along the guide slide through the elastic member. The curved surface moves, which drives the tail wing to rotate about the mandrel, and automatically folds and unfolds the tail wing through the secondary articulation ring and limit rod.
It realizes efficient folding and rapid expansion in a narrow space, simplifies the cruise missile structure, reduces weight and power consumption, improves battery life, and controls the rocker arm to drive the tail to achieve flight attitude adjustment.
Smart Images
Figure CN222257962U_ABST
Abstract
Description
Technical Field
[0001] The utility model belongs to the technical field of cruise missile tail fins, and in particular relates to a cruise missile tail fin folding mechanism for barrel-type launching. Background Art
[0002] The tail folding mechanism of the cruise missile is a key technical design, which aims to enable the cruise missile to quickly and stably unfold its tail after being launched from the launch tube, so as to ensure the stability and accuracy of the cruise missile during flight. In this case, the tail structure of the cruise missile (including the tail) must be able to transform from a retracted state to a fully unfolded state in a short time to support the flight and control of the cruise missile.
[0003] Tail fins are crucial to the stability and maneuverability of cruise missiles. They control the attitude and flight path of cruise missiles by changing aerodynamic forces and torques during flight. The design of folding tail fins allows cruise missiles to be launched in confined spaces, while also being able to be quickly deployed after leaving the launch tube, ensuring that the cruise missile can fly along the designed trajectory.
[0004] Typical tail folding mechanisms may include spring drive, electric drive, or a hybrid drive system. These mechanisms are triggered by preset signals or conditions to quickly unfold the tail and ensure that it is locked in the appropriate position, thereby maintaining the stable flight state of the cruise missile. However, the diameter and length of the launch tube limit the design space of the tail folding mechanism, requiring the mechanism to achieve a compact and efficient folding and unfolding process in a limited space.
[0005] How to achieve the folding of the tail wing of the cruise missile in a small space and its rapid unfolding after launch is a problem that needs to be solved. Utility Model Content
[0006] The technical problem to be solved by the utility model is to provide a cruise missile tail folding mechanism in view of the deficiencies in the above-mentioned prior art, so as to realize the folding of the cruise missile tail in a narrow space and the rapid unfolding after launching.
[0007] In order to solve the above technical problems, the technical solution adopted by the utility model is: a cruise missile tail folding mechanism, including a tail, a steering gear, a rocker arm and an elastic member;
[0008] The rocker arm is mounted on the servo, and a main hinge ring is provided on the connecting end of the tail wing, and the main hinge ring is sleeved on the main shaft of the rocker arm. A guide slider is connected to one side of the main hinge ring, and a guide slider curved surface and a limit surface are provided on the main shaft. The elastic member is mounted on the rocker arm, and the elastic member is used to drive the guide slider to move along the guide slider curved surface until it is in contact with the limit surface. When the guide slider moves along the guide slider curved surface, the tail wing is driven to rotate around the main shaft.
[0009] In this embodiment, the connecting end of the tail wing further has a secondary hinge ring, the secondary hinge ring is sleeved on a limit rod, and the limit rod is installed on a rocker arm.
[0010] In this embodiment, the limiting rod is a plug screw.
[0011] In this embodiment, the elastic member is a spring, the spring is sleeved on the limiting rod, and the two ends of the spring are respectively supported on the rocker arm and the auxiliary hinge ring.
[0012] In this embodiment, the spindle is provided with a spiral boss, and the guide sliding curved surface and the limiting surface are on the spiral boss.
[0013] In this embodiment, the spiral boss is provided with a limiting groove. When the guide sliding block moves along the guide sliding curved surface until it is in contact with the limiting surface, the elastic member drives the guide sliding block to insert into the limiting groove.
[0014] Compared with the prior art, the utility model has the following advantages: the rocker arm of the servo is directly used as the rotating spindle of the foldable tail wing. When the tail wing is folded on both sides of the cruise missile in a rotating manner, the space occupied by the tail wing is reduced, the storage and transportation space of the cruise missile is reduced, and the storage, transportation and launch of the cruise missile in the launch tube are convenient. When the tail wing needs to be unfolded, it only needs to be taken out of the storage tube to automatically unfold, or when it is released by launching, the tail wing is automatically unfolded by elastic force, so that the tail wing can be quickly unfolded without the need for other control components, simplifying the structure of the cruise missile, reducing the flight weight of the cruise missile, reducing the power consumed by the cruise missile, and improving the endurance of the cruise missile; further, the servo can drive the rocker arm to rotate, and the rocker arm can drive the tail wing to rotate, so as to realize the control of the flight posture of the cruise missile. In the content of this application, the locking force of the elastic member on the tail wing is in the opposite direction of the flight, and the wind force acting on the tail wing during flight is consistent with the direction of the elastic force.
[0015] The technical solution of the utility model is further described in detail below through the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS
[0016] Figure 1 The structure of the utility model is shown in FIG. Figure 1 .
[0017] Figure 2 The structure of the utility model is shown in FIG. Figure 2 .
[0018] Figure 3 This is a state diagram of the utility model after it is unfolded.
[0019] Description of reference numerals:
[0020] DETAILED DESCRIPTION
[0021] like Figure 1 — Figure 3 As shown, the working principle and structure of the folding mechanism of the cruise missile tail wing 1 are demonstrated.
[0022] 1. Component composition:
[0023] 1. Tail 1: A component used to provide flight stability and control torque.
[0024] 2. Servo 2: responsible for driving the rotation of tail 1 to adjust the flight attitude.
[0025] 3. Rocker arm 3: connects the servo 2 and the tail wing 1 to transmit power.
[0026] 4. Elastic member 4: in this embodiment, it is a spring, used to provide power to achieve the folding and unfolding of the tail wing 1.
[0027] 5. Main hinge ring 5: a part of the connecting end of the tail wing 1, which is sleeved on the spindle 7 of the rocker arm 3 and allows the tail wing 1 to rotate around the spindle 7.
[0028] 6. Guide sliding block 6: connected to the main hinge ring 5, and moves along the guide sliding surface 10 on the central shaft 7.
[0029] 7. Central shaft 7: The central shaft 7 of the rocker arm 3, having a guide curved surface 10 and a limit surface 11.
[0030] 8. Limit rod 8: installed on the rocker arm 3, cooperates with the secondary hinge ring 9 to limit the rotation range of the tail wing 1.
[0031] 9. Secondary hinge ring 9: another part of the connecting end of the tail wing 1, sleeved on the limiting rod 8.
[0032] Structural design:
[0033] The connection end of the tail wing 1 is designed with two hinged rings: a main hinged ring 5 and a secondary hinged ring 9 .
[0034] The main hinge ring 5 is sleeved on the spindle 7 of the rocker arm 3 , allowing the tail wing 1 to rotate around the spindle 7 .
[0035] A spiral boss is designed on the spindle 7, and the guide curved surface 10 and the limiting surface 11 are both located on the spiral boss.
[0036] The guide slider 6 is connected to one side of the main hinge ring 5 . When driven by the elastic member 4 (spring), the guide slider 6 moves along the guide curved surface 10 and stops when reaching the limit surface 11 .
[0037] A limiting groove 12 is provided on the spiral boss. After the guide slider 6 moves to fit the limiting surface 11 , it is driven by a spring to insert into the limiting groove 12 to lock the position of the tail wing 1 .
[0038] 2. Workflow:
[0039] 1. Unfolding process:
[0040] The spring releases its elastic force to apply an axial force to the tail 1 , and the guide slider 6 moves toward the limit surface 11 along the guide curved surface 10 of the spindle 7 .
[0041] When the guide slide block 6 reaches the limit surface 11, the tail wing 1 rotates around the spindle 7 to the deployed position.
[0042] The guide slide block 6 is inserted into the limiting groove 12 on the spiral boss to lock the unfolded state of the tail wing 1.
[0043] 2. Folding process:
[0044] The spring is compressed, and the guide slide block 6 withdraws from the limiting groove 12 along the guide curved surface 10 and moves in the opposite direction.
[0045] The tail wing 1 rotates around the spindle 7 to a folded position and is placed into the launch tube to maintain the folded state.
[0046] 3. Features:
[0047] The spring is used as the elastic member 4 to realize automatic deployment of the tail wing 1 .
[0048] The design of the spiral boss and the limiting groove 12 increases the stability and locking accuracy of the mechanism.
[0049] The limit rod 8 is installed by plug screws, which improves the compactness and reliability of the structure.
[0050] The above is only a preferred embodiment of the present invention and does not constitute any limitation to the present invention. Any simple modification, change and equivalent structural change made to the above embodiments according to the technical essence of the present invention shall still fall within the protection scope of the technical solution of the present invention.
Claims
1. A loitering missile tail fin folding mechanism, characterized in that: Including tail wing, servo, rocker arm and elastic parts; The rocker arm is mounted on the servo, and a main hinge ring is provided on the connecting end of the tail wing, and the main hinge ring is sleeved on the main shaft of the rocker arm. A guide slider is connected to one side of the main hinge ring, and a guide slider curved surface and a limit surface are provided on the main shaft. The elastic member is mounted on the rocker arm, and the elastic member is used to drive the guide slider to move along the guide slider curved surface until it is in contact with the limit surface. When the guide slider moves along the guide slider curved surface, the tail wing is driven to rotate around the main shaft.
2. A loitering missile tail fin folding mechanism according to claim 1, characterized in that: The connecting end of the tail wing also has a secondary hinge ring, the secondary hinge ring is sleeved on a limit rod, and the limit rod is installed on a rocker arm.
3. A loitering missile tail fin folding mechanism according to claim 2, characterized in that: The limiting rod is a plug screw.
4. A loitering missile tail fin folding mechanism according to claim 2 or 3, characterized in that: The elastic member is a spring, which is sleeved on the limiting rod, and two ends of the spring are respectively supported on the rocker arm and the auxiliary hinge ring.
5. A loitering missile tail fin folding mechanism according to claim 1, characterized in that: The spindle is provided with a spiral boss, and the guide sliding curved surface and the limiting surface are on the spiral boss.
6. A loitering missile tail fin folding mechanism according to claim 5, characterized in that: The spiral boss is provided with a limiting groove. When the guide slider moves along the guide slider curved surface until it is in contact with the limiting surface, the elastic member drives the guide slider to insert into the limiting groove.