Target missile launching vehicle with stable support
By designing a target missile launch vehicle with stable support, and utilizing the adjustment of the rotating frame and the erection arm as well as the support of multiple supporting parts, the problem of unstable support of the launch vehicle was solved, and the flexibility of the launch vehicle and the launch accuracy were improved.
Patent Information
- Application Number
- CN202423198872.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-24
- Publication Date
- 2025-10-28
- Estimated Expiration
- 2034-12-24
AI Technical Summary
Most existing launch vehicles have an integrated chassis structure, which cannot adapt to the size and interface parameters of different new products, resulting in unstable support and possible launch offset problems.
A target missile launching vehicle with stable support is designed, which includes a slewing frame, an erection arm and a support. The direction of the target missile is adjusted by the rotation of the slewing frame and the swing of the erection arm. Multiple support members are used to provide stable support, thereby enhancing the stability and reliability of the erection arm when fixing the target missile.
It improves the flexibility and operational convenience of the launch vehicle, enhances the stability and launch accuracy when the target missile is fixed, reduces the launch errors and potential dangers caused by instability, and improves the transportation and launch efficiency.
Smart Images
Figure CN223484992U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of launch vehicle technology, specifically to a target missile launch vehicle with stable support. Background Technology
[0002] In recent years, my country's military and aerospace industry has seen an increasing number of new products and more frequent launch missions. The dimensions and interface parameters of these new products often vary significantly. Existing launch vehicles are mostly dedicated to specific applications, meaning each launch vehicle can only be used with one or a few product models, failing to achieve true universality. Most existing launch vehicles use integrated chassis structures, emphasizing off-road performance, which results in poor performance on ordinary roads, with lower high-speed performance and shorter range compared to conventional road vehicles. After years of development, the road network has made significant progress and improvements, significantly enhancing the overall capacity of road transportation. Developing a universal mobile launch vehicle suitable for road travel, integrating transfer, erection, and launch functions, is essential and can significantly improve the efficiency of product transportation and launch. Utility Model Content
[0003] This invention proposes a target launch vehicle with stable support, which solves the problem in related technologies where launch vehicles may deviate during launch preparation due to unstable support.
[0004] The technical solution of this utility model is as follows:
[0005] A target launcher with stable support includes:
[0006] Frame;
[0007] The slewing frame is rotatably mounted on the vehicle frame;
[0008] The erecting arm is hinged at one end to the rotating frame. After the rotating frame swings, the orientation of the erecting arm changes. The erecting arm is used to fix the target projectile.
[0009] A plurality of support members are rotatably mounted on the erecting arm. After rotation, the support members abut against or dismount from the frame. The support members are used to support the erecting arm.
[0010] As a further technical solution, the erecting arm has a groove, and the support member includes:
[0011] A first mounting base is provided on the erecting arm;
[0012] The support rod is hinged at one end to the first mounting base. After the support rod rotates, it enters or leaves the groove.
[0013] As a further technical solution, the erecting arm also has several sliding grooves, the support rod has several limiting grooves, and the support member further includes:
[0014] The slider is slidably disposed within the groove.
[0015] A second mounting base is provided on the slider;
[0016] The first connecting rod is hinged at one end to the erecting arm;
[0017] The second link has one end hinged to the other end of the first link and the other end hinged to the second mounting base. When the slider slides, the second link drives the first link to move.
[0018] A connecting rod, wherein a plurality of first connecting rods and a plurality of second connecting rods are hinged together;
[0019] A plurality of connecting blocks are rotatably mounted on the mating rod. The connecting blocks are slidably mounted in the limiting groove and are used to drive the support rod to rotate.
[0020] As a further technical solution, the slider has a screw hole and also includes:
[0021] A screw is rotatably disposed within the slide groove, and the screw is threadedly engaged with the screw hole. The screw is used to drive the slider to slide.
[0022] A rotation drive component is mounted on the erecting arm, and the rotation drive component is used to drive the screw to rotate.
[0023] As a further technical solution, it also includes:
[0024] The erecting cylinder is hinged at one end to the erecting arm and at the other end to the slewing frame. The erecting cylinder is used to drive the erecting arm to swing.
[0025] As a further technical solution, it also includes:
[0026] A locking device is provided on the frame, the locking device being used to lock or unlock the erecting arm.
[0027] As a further technical solution, it also includes:
[0028] Front and rear outriggers are mounted on the vehicle frame and are used to secure the vehicle frame when the launch vehicle is launched.
[0029] The working principle and beneficial effects of this utility model are as follows:
[0030] In this invention, the slewing frame is rotatably mounted on the vehicle frame, allowing the erecting arm to be adjusted horizontally, increasing the launch vehicle's flexibility and ease of operation. The erecting arm is hinged to the slewing frame, enabling it to swing and change the target projectile's orientation to adapt to different launch requirements. Multiple support members are rotatably mounted on the erecting arm; when these members rotate and abut against the vehicle frame, they provide stable support, enhancing the arm's stability and reliability when fixing the target projectile. When not in use, the support members can be folded back, no longer supporting the vehicle frame, and do not interfere with the launch vehicle's normal launch operation. The support members' role in supporting the erecting arm helps improve launch accuracy and safety, reducing launch errors and potential hazards caused by erecting arm instability. Attached Figure Description
[0031] The preferred embodiments will be described below in a clear and easy-to-understand manner, in conjunction with the accompanying drawings, to further explain the above-mentioned characteristics, technical features, advantages and implementation methods of this utility model.
[0032] Figure 1 This is a schematic diagram of the structure of this utility model;
[0033] Figure 2 This is a schematic diagram of the structure of this utility model from another perspective;
[0034] Figure 3 This is a schematic diagram of the structure of the vertical arm and support member in this utility model;
[0035] Figure 4 This is a structural schematic diagram of another form of the vertical arm and support member in this utility model;
[0036] Figure 5 This is a structural schematic diagram of the vertical arm and support member in this utility model from another perspective and form.
[0037] Figure 6 For this utility model Figure 5 A partial enlarged view of point A in the middle;
[0038] Figure 7 For this utility model Figure 5 A magnified view of a section at point B in the middle.
[0039] In the diagram: 1. Frame, 2. Slewing frame, 3. Erecting arm, 4. Support component, 5. Groove, 6. First mounting seat, 7. Support rod, 8. Slide groove, 9. Limiting groove, 10. Slider, 11. Second mounting seat, 12. First connecting rod, 13. Second connecting rod, 14. Matching rod, 15. Connecting block, 16. Screw hole, 17. Screw, 18. Rotation drive component, 19. Erecting cylinder, 20. Front outrigger, 21. Rear outrigger. Detailed Implementation
[0040] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the specific implementation methods of this utility model will be described below with reference to the accompanying drawings. Obviously, the accompanying drawings described below are merely some embodiments of this utility model. For those skilled in the art, they can be understood as further technical solutions without creative effort. In some drawings, components with the same structure or function are only schematically illustrated, or only one is marked. In this document, "a" not only means "only one," but can also mean "more than one," and "several" includes "two" and "more than two."
[0041] In this document, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.
[0042] Furthermore, in the description of this application, the terms "first," "second," etc., are used only to distinguish descriptions and should not be construed as indicating or implying relative importance.
[0043] Reference Figures 1-7 A target launch vehicle with stable support is proposed, comprising: a rotating frame 2 rotatably mounted on a frame 1; an erecting arm 3 with one end hinged to the rotating frame 2, the orientation of the erecting arm 3 changes after the rotating frame 2 swings, and the erecting arm 3 is used to fix the target projectile; and several support members 4 rotatably mounted on the erecting arm 3, the support members 4 abutting or disattaching to the frame 1 after rotation, and the support members 4 are used to support the erecting arm 3.
[0044] In this embodiment, the slewing frame 2 is rotatably mounted on the chassis 1, allowing the erecting arm 3 to adjust its angle in the horizontal direction, increasing the flexibility and ease of operation of the launch vehicle. The erecting arm 3 is hinged to the slewing frame 2, enabling it to swing and change the orientation of the target projectile to adapt to different launch requirements. Multiple support members 4 are rotatably mounted on the erecting arm 3. When the support members 4 rotate and abut against the chassis 1, they provide stable support for the erecting arm 3, enhancing its stability and reliability when fixing the target projectile. The support members 4 can be folded back when not in use, no longer supporting the chassis 1, and do not affect the normal launch of the launch vehicle. The supporting effect of the support members 4 on the erecting arm 3 helps improve launch accuracy and safety, reducing launch errors and potential hazards caused by instability of the erecting arm 3.
[0045] As a further technical solution, the erecting arm 3 has a groove 5, and the support member 4 includes: a first mounting seat 6 disposed on the erecting arm 3; one end of the support rod 7 is hinged to the first mounting seat 6, and after the support rod 7 rotates, it enters or leaves the groove 5.
[0046] In this embodiment, the groove 5 on the erecting arm 3 provides storage space for the support rod 7. When the support rod 7 is not needed, it can rotate into the groove 5, reducing space occupation, making the erecting arm 3 look neater, and also reducing the risk of the support rod 7 being damaged by collision when not supported. The first mounting base 6 provides a stable mounting foundation for the support rod 7, ensuring that the support rod 7 can withstand greater pressure and impact during operation, guaranteeing the stability of the support. One end of the support rod 7 is hinged to the first mounting base 6, allowing the support rod 7 to rotate flexibly, achieving contact and separation with the vehicle frame 1, which is convenient to operate and responds quickly. The support rod 7 can quickly extend out of the groove 5 and function when support is needed, and can be retracted in time when not needed, improving the working efficiency and adaptability of the launch vehicle.
[0047] As a further technical solution, the erecting arm 3 also has several sliding grooves 8, the support rod 7 has several limiting grooves 9, and the support member 4 also includes: a slider 10 slidably disposed in the sliding groove 8; a second mounting seat 11 disposed on the slider 10; one end of the first connecting rod 12 is hinged to the erecting arm 3; one end of the second connecting rod 13 is hinged to the other end of the first connecting rod 12, and the other end is hinged to the second mounting seat 11. When the slider 10 slides, the second connecting rod 13 drives the first connecting rod 12 to move; a cooperating rod 14 is used to hinge several first connecting rods 12 and several second connecting rods 13; several connecting blocks 15 are rotatably disposed on the cooperating rod 14, and the connecting blocks 15 are slidably disposed in the limiting grooves 9. The connecting blocks 15 are used to drive the support rod 7 to rotate.
[0048] In this embodiment, the cooperation between the slide groove 8 and the slider 10 provides guidance and constraint for the movement of the second mounting base 11, ensuring the smoothness and accuracy of its movement. The linkage mechanism formed by the first connecting rod 12, the second connecting rod 13, and the cooperating rod 14 can convert the linear motion of the slider 10 into the rotational motion of the connecting block 15, thereby driving the rotation of the support rod 7, realizing the effective transmission and conversion of force and motion. The cooperation between the multiple connecting blocks 15 and the limiting groove 9 makes the rotation of the support rod 7 more stable and synchronized, avoiding the jamming and asynchronous phenomena during the rotation of the support rod 7. This complex but ingenious support component 4 structure design improves the accuracy and controllability of the rotation of the support rod 7, and can accurately adjust the contact state between the support rod 7 and the frame 1 according to actual needs. The entire support component 4 has a compact structure, occupies little space, and can achieve efficient support function in a limited space, improving the space utilization rate of the target missile launcher.
[0049] As a further technical solution, the slider 10 has a screw hole 16 and also includes: a screw 17 rotatably disposed in the slide groove 8, the screw 17 being threadedly engaged with the screw hole 16, the screw 17 being used to drive the slider 10 to slide; and a rotation drive 18 disposed on the lifting arm 3, the rotation drive 18 being used to drive the screw 17 to rotate.
[0050] In this embodiment, the screw 17 transmission has a self-locking property. After the rotation drive 18 stops, the slider 10 can remain in its current position, thereby ensuring that the support rod 7 is stably and reliably supported and will not slip unexpectedly due to external factors. The rotation drive 18 allows the support 4 to be operated remotely or under centralized control, improving the automation level and operational safety of the entire target launch vehicle.
[0051] As a further technical solution, it also includes: one end of the erecting cylinder 19 is hinged to the erecting arm 3, and the other end is hinged to the slewing frame 2. The erecting cylinder 19 is used to drive the erecting arm 3 to swing.
[0052] In this embodiment, the erecting cylinder 19 provides powerful and stable power for the swing of the erecting arm 3, enabling rapid and accurate angle adjustment of the erecting arm 3 and improving operational efficiency. The smooth transmission of the cylinder effectively reduces vibration and impact during the swing of the erecting arm 3, protecting the equipment and the target projectile. The hinged installation of the erecting cylinder 19 allows it to adapt to the relative movement between the erecting arm 3 and the slewing frame 2 during operation, reducing stress concentration between mechanical components and extending the service life of the equipment.
[0053] As a further technical solution, it also includes: a locking device is installed on the frame 1, and the locking device is used to lock or unlock the erecting arm 3.
[0054] In this embodiment, the locking device can securely lock the erecting arm 3 after it has been adjusted to the appropriate position, preventing it from moving or shaking unexpectedly and ensuring the safety of the launch vehicle during transportation or parking. When it is necessary to operate or adjust the erecting arm 3, the locking device can be released, allowing the erecting arm 3 to move freely, increasing operational flexibility. Effective locking can protect the erecting arm 3 and related components from unnecessary vibration and impact, extending the service life of the equipment.
[0055] As a further technical solution, it also includes: front outrigger 20 and rear outrigger 21 are mounted on the frame 1, and the front outrigger 20 and rear outrigger 21 are used to fix the frame 1 when the launch vehicle is launched.
[0056] In this embodiment, the front outrigger 20 and rear outrigger 21 increase the contact points between the chassis 1 and the ground, allowing for a more even distribution of the reaction force borne by the chassis 1 during launch, thus improving the stability of the chassis 1. They effectively prevent the chassis 1 from shifting, tilting, or swaying due to recoil during launch, ensuring the accuracy and safety of the launch. When the launch vehicle operates on uneven ground, the front outrigger 20 and rear outrigger 21 can be independently adjusted in height to keep the chassis 1 level, providing a stable foundation for launch.
[0057] It should be noted that the above embodiments are only used to illustrate the technical solution of this utility model and are not intended to limit it. Although this utility model has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solution of this utility model without departing from the spirit and scope of the technical solution of this utility model, and all such modifications or substitutions should be covered within the scope of the claims of this utility model.
Claims
1. A target launch vehicle with stable support, characterized in that, include: Frame (1); The slewing frame (2) is rotatably mounted on the frame (1); The erecting arm (3) is hinged at one end to the rotating frame (2). After the rotating frame (2) swings, the orientation of the erecting arm (3) changes. The erecting arm (3) is used to fix the target projectile. A number of support members (4) are rotatably mounted on the erecting arm (3). After the support members (4) rotate, they abut against or disabut against the frame (1). The support members (4) are used to support the erecting arm (3).
2. The target launch vehicle with stable support according to claim 1, characterized in that, The erecting arm (3) has a groove (5), and the support member (4) includes: The first mounting base (6) is disposed on the erecting arm (3); The support rod (7) is hinged at one end to the first mounting base (6). After the support rod (7) rotates, it enters or leaves the groove (5).
3. The target launch vehicle with stable support according to claim 2, characterized in that, The erecting arm (3) also has several sliding grooves (8), the support rod (7) has several limiting grooves (9), and the support member (4) further includes: The slider (10) is slidably disposed within the groove (8); A second mounting base (11) is disposed on the slider (10); The first connecting rod (12) is hinged at one end to the erecting arm (3); The second link (13) is hinged at one end to the other end of the first link (12) and at the other end to the second mounting base (11). When the slider (10) slides, the second link (13) drives the first link (12) to move. A connecting rod (14) is used to hinge a plurality of first connecting rods (12) and a plurality of second connecting rods (13); A number of connecting blocks (15) are rotatably disposed on the mating rod (14). The connecting blocks (15) are slidably disposed in the limiting groove (9). The connecting blocks (15) are used to drive the support rod (7) to rotate.
4. A target launch vehicle with stable support according to claim 3, characterized in that, The slider (10) has a screw hole (16) and also includes: The screw (17) is rotatably disposed in the slide groove (8), the screw (17) is threadedly engaged with the screw hole (16), and the screw (17) is used to drive the slider (10) to slide. A rotation drive (18) is provided on the erecting arm (3), and the rotation drive (18) is used to drive the screw (17) to rotate.
5. A target launch vehicle with stable support according to claim 1, characterized in that, Also includes: The erecting cylinder (19) is hinged at one end to the erecting arm (3) and at the other end to the slewing frame (2). The erecting cylinder (19) is used to drive the erecting arm (3) to swing.
6. A target launch vehicle with stable support according to claim 1, characterized in that, Also includes: A locking device is provided on the frame (1) for locking or unlocking the erecting arm (3).
7. A target launch vehicle with stable support according to claim 1, characterized in that, Also includes: Front outrigger (20) and rear outrigger (21) are mounted on the frame (1) and are used to fix the frame (1) when the launch vehicle is launched.