Aircraft launcher system capable of being adjusted in large range and rapidly positioned

Abstract

The aircraft launcher system comprises a supporting frame and a bracket and further comprises a base, a rotary bearing is arranged on the top face of the base, a rotary table is rotatably arranged on the surface of the rotary bearing, one side of the top face of the rotary table is rotatably connected with the surface of the supporting frame through a rear trunnion, and the other side of the top face of the rotary table is rotatably connected with the surface of the bracket through a rear trunnion. And a fixing frame is arranged on the other side of the top face of the rotary table, a first threaded sleeve is rotationally arranged in the fixing frame, and a first threaded rod is in threaded connection with the interior of the first threaded sleeve. The aircraft launcher system capable of being adjusted in a large range and rapidly positioned is high in safety, lateral force resistance is improved, the anti-overturning capacity is more than five times that of a traditional structure, the aircraft launcher system can still keep stable in a strong wind environment, deviation risks caused by shaking of a supporting frame when an aircraft is launched are avoided, the structure is flexible, assistance of a crane is not needed, erecting adjustment in the range of 0-50 degrees can be achieved, and the aircraft launcher system can be widely applied to the field of aircraft launching. And a stepless rotation device is arranged.

Description

Technical Field

[0001] This invention relates to the field of aircraft launch technology, specifically to an aircraft launcher system with a wide range of adjustable and rapid positioning capabilities. Background Technology

[0002] The aircraft launcher system is deployed on the loading platform and is a key structure used to provide precise guidance for the aircraft before launch, supporting its rigidity, strength, and stable launch.

[0003] Existing rocket launcher positioning technology has significant shortcomings in terms of accuracy, reliability, environmental adaptability, and anti-interference capability, specifically:

[0004] (1) There are many bottlenecks in positioning technology. Traditional positioning systems are difficult to meet the needs of modern high-precision launches. Traditional positioning systems rely on foreign technology, which poses data security risks and makes it difficult to guarantee the autonomy and security of the national aerospace strategy.

[0005] (2) Traditional positioning methods have insufficient signal coverage in complex terrains such as mountainous areas and plateaus, and positioning signals are easily interrupted or delayed.

[0006] (3) In the modern electronic warfare environment, enemy strong electromagnetic interference, GPS deception and other means will cause traditional positioning systems to fail or make positioning errors. At the same time, traditional positioning systems have slow response speed and are difficult to meet the operational requirements of rapid mobile launch and real-time multi-target strike.

[0007] (4) In forest fire fighting operations, dense vegetation can block positioning signals, resulting in inaccurate positioning of the rocket launcher and the inability to accurately deliver fire extinguishing bombs to the center of the fire. In high-rise building rescue scenarios, signal reflection and multipath effects in urban building clusters can cause positioning deviations, affecting the accuracy and timeliness of rescue material delivery and delaying rescue opportunities.

[0008] Therefore, in view of the above-mentioned shortcomings, the present invention makes the following improvements. Summary of the Invention

[0009] To address the shortcomings of existing technologies, this invention provides an aircraft launcher system that can be adjusted over a wide range and positioned quickly, thus solving the problems mentioned in the background art.

[0010] To achieve the above objectives, the present invention provides the following technical solution: a large-range adjustable and rapidly positioning aircraft launcher system, comprising a support frame and a bracket, and a base, wherein a slewing bearing is provided on the top surface of the base, and a rotary table is rotatably provided on the surface of the slewing bearing. One side of the top surface of the rotary table is rotatably connected to the surface of the support frame via a rear trunnion, and a fixed frame is provided on the other side of the top surface of the rotary table. A first threaded sleeve is rotatably provided inside the fixed frame, and a first threaded rod is threadedly connected inside the first threaded sleeve. A front trunnion is rotatably provided at one end of the first threaded rod, and the top surface of the front trunnion is rotatably connected to the surface of the support frame via a support rod. A guide rail assembly is fixedly connected to the top surface of the support frame by bolts. Beidou devices are provided on both sides of the top surface of the support frame, and a projectile deflector mechanism is provided on one side of the support frame.

[0011] Preferably, the top surface of the rotary table is provided with a protective cover, and the front trunnion is slidably disposed on the top surface of the rotary table and located inside the protective cover.

[0012] Preferably, the guide rail assembly consists of a guide rail and a guide rail pressure plate, and the top surface of the guide rail has a notch for hoisting the aircraft.

[0013] Preferably, a first bevel gear is fixedly provided on the surface of the first threaded sleeve, a rotating shaft is rotatably provided on the front of the fixed frame, and a second bevel gear that meshes with the first bevel gear is fixedly provided at one end of the rotating shaft inside the fixed frame, and a handwheel is fixedly provided at the other end of the rotating shaft.

[0014] Preferably, the support frame is a truss structure, formed by welding profiles.

[0015] Preferably, the rotary table has a base plate on its front side and a mounting bracket on its top surface. A second threaded sleeve is fixedly installed inside the mounting bracket, and a second threaded rod is threadedly connected to the inside of the second threaded sleeve.

[0016] Preferably, one end of the second threaded rod is rotatably provided with a pin, and the top end of the pin is rotatably connected to one side of the bottom surface of the rotary table.

[0017] Preferably, the Beidou device consists of a Beidou satellite and a mounting base, and is installed in a T-slot on a guide rail. The bottom side of the mounting base and the bottom side of the guide rail are positioning mating surfaces to ensure the mechanical accuracy of the measurement position.

[0018] Beneficial effects

[0019] This invention provides an aircraft launcher system with a wide range of adjustable and rapid positioning capabilities. Compared with existing technologies, it has the following advantages:

[0020] (1) It has high safety, improved resistance to lateral forces, and its anti-overturning ability is more than 5 times that of traditional structures. It can still maintain stability in strong wind environments and avoid the risk of deviation caused by the swaying of the support frame when the aircraft is launched.

[0021] (2) The structure is flexible and does not require the assistance of a crane. It can achieve vertical adjustment within the range of 0-50° and has a stepless slewing device.

[0022] (3) Precise positioning: Beidou positioning requires no external equipment and the azimuth angle measurement accuracy reaches 0.08°, solving the problems of cumbersome operation and unstable accuracy of traditional measurement. Attached Figure Description

[0023] Figure 1 This is a perspective view of the structure of the present invention;

[0024] Figure 2 This is a front view of the structure of the present invention;

[0025] Figure 3 This is a schematic diagram of the rotary table structure of the present invention.

[0026] In the diagram: 1. Support frame; 2. Bracket; 3. Base; 4. Slewing bearing; 5. Rotary table; 6. Rear trunnion; 7. Fixing frame; 8. Pin; 9. First threaded rod; 10. Front trunnion; 11. Support rod; 12. Guide rail assembly; 13. Beidou device; 14. Bullet deflector mechanism; 15. Protective cover; 16. Rotating shaft; 17. Handwheel; 18. Base plate; 19. Mounting bracket; 20. Threaded sleeve; 21. Second threaded rod. Detailed Implementation

[0027] 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.

[0028] Example 1

[0029] Please see Figures 1 to 3As shown, a large-range adjustable and rapidly positioning aircraft launcher system includes a support frame 1 and a bracket 2. The support frame 1 is a truss structure, welded from profiles. The support frame 1 is corrosion-resistant and has strong anti-overturning capability. It also includes a base 3, with a slewing bearing 4 mounted on its top surface. A slewing platform 5 and the surface of the slewing bearing 4 have several corresponding insertion holes. The slewing platform 5 is rotatably mounted on the surface of the slewing bearing 4. One side of the top surface of the slewing platform 5 is rotatably connected to the surface of the support frame 1 via a rear trunnion 6. The other side of the top surface of the slewing platform 5... A fixed frame 7 is provided on one side, and a first threaded sleeve is rotatably mounted inside the fixed frame 7. A first bevel gear is fixedly mounted on the surface of the first threaded sleeve. A rotating shaft 16 is rotatably mounted on the front of the fixed frame 7, and a second bevel gear that meshes with the first bevel gear is fixedly mounted at one end of the rotating shaft 16 inside the fixed frame 7. A handwheel 17 is fixedly mounted at the other end of the rotating shaft 16. A first threaded rod 9 is threadedly connected inside the first threaded sleeve, and a front trunnion 10 is rotatably mounted at one end of the first threaded rod 9. A protective cover is provided on the top surface of the rotary table 5. The protective cover 15 houses the front trunnion 10, which is slidably mounted on the top surface of the rotary table 5 and located inside the protective cover 15. The top surface of the front trunnion 10 is rotatably connected to the surface of the support frame 1 via a support rod 11. The top surface of the support frame 1 is bolted to a guide rail assembly 12. The bolted connection ensures the connection strength between the guide rail assembly 12 and the support frame 1, providing precise guidance for launch. The guide rail assembly 12 consists of a guide rail and a guide rail pressure plate. The guide rail surface is coated to prevent rust and burning, extending its service life. The top surface of the guide rail... A notch is provided for hoisting the aircraft. After hoisting, a hoisting plug is used to restore the integrity of the guide rail. Both sides of the top surface of the support frame 1 are equipped with Beidou devices 13. The Beidou device 13 consists of Beidou and a mounting base, and is installed in a T-slot on the guide rail. The bottom side of the mounting base and the bottom side of the guide rail are positioning mating surfaces to ensure the mechanical accuracy of the measurement position. During measurement, the left Beidou is inserted from the front end of the guide rail and the wing screw is tightened to fix it. The right Beidou is inserted from the guide rail cover plate and the wing screw is tightened to fix it. A bullet-blocking mechanism 14 is provided on one side of the support frame 1.

[0030] Example 2

[0031] Based on Example 1, see Figures 1 to 3 As shown, the rotary table 5 has a base plate 18 on its front side, and a mounting bracket 19 on the top surface of the base plate 18. A second threaded sleeve 20 is fixedly installed inside the mounting bracket 19, and a second threaded rod 21 is threadedly connected inside the second threaded sleeve 20. A pin 8 is rotatably installed at one end of the second threaded rod 21, and the top end of the pin 8 is rotatably connected to one side of the bottom surface of the rotary table 5.

[0032] Working principle: First, rotate the second threaded rod 21, so that the second threaded rod 21 rotates and moves inside the second threaded sleeve 20. At this time, the pin 8 drives the rotary table 5 to rotate along the surface of the rotary bearing 4 during the movement of the second threaded rod 21, thereby adjusting the azimuth angle of the support frame 1. The azimuth angle data is read in real time by the Beidou device 13. After the predetermined azimuth angle is reached, the pin is inserted into the corresponding insertion hole of the rotary table 5 and the rotary bearing 4 to lock the rotary table 5. Then, the status of the guide rail is checked. With the assistance of personnel, the tail slider of the aircraft is accurately embedded into the notch opened in the guide rail and pushed along the guide rail to the bullet blocking mechanism 14 to achieve the limit. After that, the plug is installed back at the tail of the guide rail by screw connection to restore the complete force and guiding structure of the guide rail.

[0033] During erection, the operator turns the handwheel 17, which drives the rotating shaft 16 to rotate. This, in turn, drives the first threaded sleeve to rotate via the first and second bevel gears. During rotation, the first threaded rod 9 can drive the front trunnion 10 to slide on the top surface of the rotary table 5. As the front trunnion 10 slides, in conjunction with the rotation of both ends of the support rod 11, the right side of the support frame 1 can rotate along the surface of the rear trunnion 6, thus achieving the erection action. The pitch angle can be adjusted from 0 to 50°. After the angle is determined, the front trunnion 10 is locked in place using fastening bolts, thereby completing the final setting of the aircraft's launch attitude.

[0034] Furthermore, any content not described in detail in this specification is existing technology known to those skilled in the art.

[0035] The embodiments of the invention have been described in detail above, but the content described is only a preferred embodiment of the invention and should not be considered as limiting the scope of the invention. All equivalent changes and improvements made within the scope of the claims of this invention should still fall within the patent coverage of this invention.

Claims

1. A large-range adjustable and rapidly positioning aircraft launcher system, comprising a support frame (1) and a bracket (2), characterized in that: It also includes a base (3), and a slewing bearing (4) is provided on the top surface of the base (3). A rotary table (5) is rotatably provided on the surface of the slewing bearing (4). One side of the top surface of the rotary table (5) is rotatably connected to the surface of the support frame (1) through a rear trunnion (6). A fixed frame (7) is provided on the other side of the top surface of the rotary table (5). A first threaded sleeve is rotatably provided inside the fixed frame (7). A first threaded rod (9) is threadedly connected inside the first threaded sleeve. A front trunnion (10) is rotatably provided at one end of the first threaded rod (9). The top surface of the front trunnion (10) is rotatably connected to the surface of the support frame (1) through a support rod (11). A guide rail assembly (12) is fixedly connected to the top surface of the support frame (1) by bolts. A Beidou device (13) is provided on both sides of the top surface of the support frame (1). A bullet-blocking mechanism (14) is provided on one side of the support frame (1).

2. The aircraft launcher system with a wide range of adjustable and rapid positioning according to claim 1, characterized in that: The top surface of the rotary table (5) is provided with a protective cover (15), and the front trunnion (10) is slidably disposed on the top surface of the rotary table (5) and located inside the protective cover (15).

3. The aircraft launcher system with a wide range of adjustable and rapid positioning according to claim 1, characterized in that: The guide rail assembly (12) consists of a guide rail and a guide rail pressure plate, and the top surface of the guide rail has a notch for hoisting the aircraft.

4. The aircraft launcher system with a wide range of adjustable and rapid positioning according to claim 1, characterized in that: The first threaded sleeve is fixedly provided with a first bevel gear, the front of the fixed frame (7) is rotatably provided with a rotating shaft (16), and one end of the rotating shaft (16) located inside the fixed frame (7) is fixedly provided with a second bevel gear that meshes with the first bevel gear, and the other end of the rotating shaft (16) is fixedly provided with a handwheel (17).

5. The aircraft launcher system with a wide range of adjustable and rapid positioning according to claim 1, characterized in that: The support frame (1) is a truss structure, which is formed by welding profiles.

6. The aircraft launcher system with a wide range of adjustable and rapid positioning according to claim 1, characterized in that: The rotary table (5) has a base plate (18) on its front side, and a mounting bracket (19) is provided on the top surface of the base plate (18). A second threaded sleeve (20) is fixedly provided inside the mounting bracket (19), and a second threaded rod (21) is threadedly connected inside the second threaded sleeve (20).

7. The aircraft launcher system with a wide range of adjustable and rapid positioning according to claim 6, characterized in that: One end of the second threaded rod (21) is rotatably provided with a pin (8), and the top end of the pin (8) is rotatably connected to one side of the bottom surface of the rotary table (5).

8. The aircraft launcher system with a wide range of adjustable and rapid positioning according to claim 1, characterized in that: The Beidou device (13) consists of Beidou and a mounting base, and is installed in a T-slot on the guide rail. The bottom side of the mounting base and the bottom side of the guide rail are positioning mating surfaces to ensure the mechanical accuracy of the measurement position.

Images