Adjustable gas jet deflector for vehicle-mounted rockets

Abstract

The application discloses an adjustable gas jet flow guide device for a vehicle-mounted rocket, which comprises a grid sheet, rotating mechanisms one and two and a connecting piece. The grid sheet is arranged on the rotating mechanisms one and two. The connecting piece is combined with the rotating mechanisms to realize the rotating function, so that the relative position of the flow guide grid is changed. The grid sheet can be combined with the rotating mechanisms one and two and can rotate with the opening and closing of the roof of the launching vehicle, so that the grid sheet is tightly attached to the roof, and then the grid sheet can guide the airflow when the roof is closed, the flow guide function is realized, and the grid sheet can be folded when the roof is opened, and the space is released. Meanwhile, the airflow flows through the grid sheet, the launching box is protected from the backflow, and the launching is ensured. In addition, the grid sheet can guide the airflow to be discharged upward, the protection effect on the rear equipment can be realized under different direction angles, the gas impact on the rear equipment is reduced, and the protection function is realized.

Description

Technical Field

[0001] This invention belongs to the field of rocket and missile guide devices, and in particular an adjustable gas jet guide device for vehicle-mounted rockets. Background Technology

[0002] Vehicle-mounted weapon systems, with their excellent mobility, concealment, and protection, demonstrate broad application prospects and development potential. However, with the continuous advancement of modern weapon technology, more stringent requirements are being placed on the performance and functionality of vehicle-mounted launch devices. The high-temperature, high-speed exhaust gas generated during launch significantly affects launch accuracy and the stability of the launch device. In particular, the presence of the backdraft can directly erode the missile's tail, potentially causing damage to the launch device in severe cases. The gas deflector is a crucial component of thermal protection for the exhaust jet in missile launch technology. It primarily withstands the impact of the exhaust jet and guides it in a direction and space favorable for missile launch, preventing the exhaust jet from the rocket engine from ablating critical components. Vehicle-mounted rocket launch exhaust deflectors offer advantages such as compact structure, lightweight design, and rapid deployment, ensuring the safe discharge of exhaust gas during rocket launch and effectively protecting the vehicle and personnel.

[0003] Common vehicle-mounted hot launch gas deflection devices include unidirectional and multidirectional devices. Unidirectional devices exhaust gas in a single direction, have a simple structure, and are used for missiles with a fixed launch angle. Multidirectional devices exhaust gas in multiple directions to reduce the impact on the launch platform.

[0004] Traditional planar or single-arc surface deflectors are prone to causing backflow of exhaust gas during low-angle launches, damaging the missile's tail or launch device. For example, patent CN201710535753.6 (2018-11-23) discloses a dual-arc deflector for vehicle-mounted missile launchers. Its planar deflector, lacking streamlined design, causes abrupt changes in exhaust gas direction during exhaust gas impact, resulting in backflow and erosion of the equipment. While the dual-arc deflector mitigates horizontal thrust through segmented design with small and large arc segments, its curvature still needs further optimization to reduce local turbulence. Traditional wedge-shaped and cone-shaped deflectors are large in size and cannot meet the compact requirements of vehicle-mounted launchers, such as the influence of deflector structure on the impact load of rocket artillery [J]. Journal of Ordnance Equipment Engineering, 2022, 43(8):74-79,86.DOI:10.11809 / bqzbgcxb2022.08.011. Such devices need to withstand the impact of gas in a limited space and are difficult to integrate into cluster launchers. The existing flow guide grid is installed inside the launch tube box, as shown in the literature Research on the Influence of Flow Guide Grid on the Flow Field Environment inside the Launch Tube [J]. Ship Science and Technology, 2022, 44(20):71-77.DOI:10.3404 / j.issn.1672-7649.2022.20.014. The gas jet inside the launch tube is constrained by the tube wall, which easily forms a local high pressure zone, resulting in uneven stress on the front cover. When the flow guide grid is close to the engine nozzle, although it can improve the pressure wave propagation efficiency, it will aggravate the turbulence intensity inside the tube. Summary of the Invention

[0005] The purpose of this invention is to solve the problems of gas flow rewinding and inability to install compactly in existing vehicle-mounted rocket gas jet guiding devices during use, and to provide an adjustable gas jet guiding device for vehicle-mounted rockets that can effectively guide gas flow and change the direction of gas flow.

[0006] The technical solution to achieve the purpose of this invention is as follows:

[0007] An adjustable gas jet guide device for vehicle-mounted rockets, comprising:

[0008] Rotating mechanism one and rotating mechanism two are symmetrically installed on the top cover of the launch vehicle. Each includes rotating base one, fixed plate, connecting rod, and rotating base two. Rotating base one is fixed to the top cover of the launch vehicle, and rotating base two is fixed to the back plate of the launch vehicle. One end of the connecting rod is hinged to the upper end of the fixed plate, and the other end is hinged to rotating base two. The lower end of the fixed plate is hinged to rotating base one.

[0009] A connecting component is used to connect rotating mechanism one and rotating mechanism two, so that rotating mechanism one and rotating mechanism two rotate synchronously;

[0010] The grid plate is fixed between the fixed plates of rotating mechanism one and rotating mechanism two, and is used to guide the airflow upwards.

[0011] The adjustable gas jet guide device can rotate with the opening and closing of the launch vehicle's top cover, so that when the launch vehicle's top cover is open, it can fit tightly against the top cover to release space, and when the launch vehicle's top cover is closed, it can guide the airflow to achieve the guiding function and protect the launch box from the impact of the counter-current.

[0012] The significant advantages of this invention compared to existing technologies are:

[0013] By employing symmetrically arranged rotating mechanisms one and two, and using connecting parts to achieve linkage between the two, the entire flow guiding device can flexibly adjust its angle, enhancing the device's applicability and stability. At the same time, the design of the rectangular grid plate significantly improves the flow guiding efficiency, ensuring the stable launch of the vehicle-mounted rocket. Additionally, the fixing plate can change its angle as the launch vehicle's roof opens and closes, making reasonable use of the roof space. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the adjustable gas jet guiding device of the present invention;

[0015] Figure 2 This is a schematic diagram of the adjustable gas jet guide device of the present invention in use.

[0016] Figure 3 This is a schematic diagram of the adjustable gas jet guide device of the present invention in the closed state;

[0017] Figure 4 This is a schematic diagram of the rotating mechanism of the adjustable gas jet guide device of the present invention;

[0018] Figure 5 This is a schematic diagram of the rotating base structure of the adjustable gas jet guide device of the present invention;

[0019] Figure 6 This is a schematic diagram of the fixed plate structure of the adjustable gas jet guiding device of the present invention;

[0020] Figure 7 This is a schematic diagram of the connecting rod structure of the adjustable gas jet guiding device of the present invention.

[0021] Reference numerals: 1—Grid plate, 2—Rotating mechanism one, 3—Connector, 4—Rotating mechanism two, 5—Rotating base one, 6—Fixed plate, 7—Connecting rod, 8—Rotating base two, 9—Threaded hole one, 10—Fixed threaded hole two, 11—Connecting hole one, 12—Discharge groove, 13—Main board, 14—Connecting hole two, 15—Connecting hole three, 16—Sleeve, 17—Pin, 18—Connecting hole four, 19—Connecting hole five, 20—Threaded hole three, 21—Launch vehicle top cover, 22—Launch vehicle back plate. Detailed Implementation

[0022] To illustrate the technical solution and objectives of this invention, the invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0023] First, combine Figure 1 The embodiments of this application will be described.

[0024] Figure 1 The diagram shown is a structural schematic of an adjustable gas jet guide device, which exemplifies an adjustable gas jet guide device for a vehicle-mounted rocket applicable to the embodiments of this application. It includes: a grid plate 1, a rotating mechanism 1 2, a connecting member 3, and a rotating mechanism 2 4.

[0025] Rotating mechanism 1 2 and rotating mechanism 2 4 are symmetrically installed on the top cover 21 of the launch vehicle and are linked together through connecting piece 3.

[0026] Figure 2 This is a schematic diagram of the installation of the adjustable gas jet guide device on the launch vehicle. Two rotating mechanisms are mounted on the launch vehicle roof 21 via rotating base 5. The axes of symmetry of rotating mechanism 2 and rotating mechanism 4 coincide with the centerline of the vehicle's length direction (i.e., the z-axis direction). The installation of rotating mechanism 2 and rotating mechanism 4 avoids the location of the rocket engine. Connector 3 uses a high-strength alloy connecting rod, with both ends fixedly connected to the threaded holes 20 in the middle of the two rotating mechanisms, ensuring that the synchronous action accuracy error is ≤0.5°.

[0027] Figure 4 This is a schematic diagram of the rotating mechanism of the adjustable gas jet guide device. The rotating mechanism includes the following core components: rotating base 1 5, fixed plate 6, connecting rod 7, and rotating base 2 8.

[0028] Figure 5 This is a schematic diagram of the rotating base structure of the adjustable gas jet guide device of the present invention. M16 high-strength bolts are used to connect the first fixed threaded hole 9 and the second fixed threaded hole 10 of the rotating base 5 to the embedded part of the launch vehicle top cover 21. A laser calibration reference surface is set on the surface of the rotating base 5, and the installation flatness error is ≤0.1mm. The second rotating base 8 is rigidly connected to the embedded part of the launch vehicle back plate 22 via M16 high-strength bolts.

[0029] Figure 6 The diagram shows the structure of the fixed plate 6 of the adjustable gas jet guide device. The main plate 13 has dimensions of 1200mm×400mm×50mm and 13 sets of discharge grooves 12 with a groove width of 7mm and a spacing of 10mm. The inclination angle with the z-axis is 36°. The main plate 13 has a second connection hole 14 and a third connection hole 15 with a diameter of 12mm at both ends. The third connection hole 15 is used to hinge with the connecting rod 7, and the second connection hole 14 is used to hinge with the rotating base 5.

[0030] The grid panels 1 are 200mm × 100mm × 5mm in size, made of high-temperature resistant ceramic matrix composite material, with a temperature resistance of ≥1800℃, and are welded to the surface of the discharge groove 12 of the fixing plate 6 in a parallel arrangement. The installation technical requirements are as follows:

[0031] The grid panel 1 is fixed by welding. Each grid panel is spot welded by argon arc welding. The weld length is ≥8mm, the weld leg height is ≥3mm, and the grid panel spacing error is ≤±1mm.

[0032] Angle calibration: After installation, the uniformity of the grid sheet tilt angle is verified by a laser rangefinder. The angle deviation between adjacent sheets is ≤0.5°, and the overall flatness error of the guide surface is ≤2mm.

[0033] Figure 7 The diagram shows the structure of the connecting rod 7 of the adjustable gas jet guide device. It includes two hinged connecting rods. One end of the connecting rod 7 is provided with a connecting hole 4 and is connected to the fixed plate 6 through a sleeve 16 and a pin 17. The other end is provided with a connecting hole 5 19 for hinged connection with the rotating base 2 8. The middle part is provided with a threaded hole 3 20 to lock with the connecting piece 3, which can realize the angle adjustment range of 0° to 77°.

[0034] The connector 3 adopts a double-headed screw structure, and its two ends are connected to the threaded holes 20 of the rotating mechanism 1 and the rotating mechanism 2 through universal joints to realize the synchronous angle adjustment of the two mechanisms.

[0035] The fixed plate 6 is hinged to the rotating base 5 through the connecting hole 11, and can be folded with the roof at 36° to 80°.

[0036] Workflow example.

[0037] During the gas exhaust phase, the roof 21 is closed, and the length of the fixed plate 6 of the flow guide device is at an 80° angle to the upper surface of the roof. After the rocket ignites, the high-temperature gas flows through the exhaust trough 12 and is divided into multiple laminar flows by the grid plate 1. Compared with the traditional planar flow guide plate, this reduces the impact of the counterflow on the launch device.

[0038] After launch, the roof cover 21 opens, and the flow guiding device moves synchronously with the roof cover via the gas spring-assisted rotating mechanism 2 and the rotating mechanism 4. The angle of the rotating mechanism is linearly related to the opening and closing angle of the roof cover. Finally, the length of the fixing plate 6 forms a 36° angle with the upper surface of the roof cover, facilitating driver entry and exit. The connecting piece 3 ensures the linkage between the two rotating mechanisms, improving the stability and reliability of the device.

[0039] This invention discloses an adjustable gas jet guiding device for a vehicle-mounted rocket. The grid can be integrated with a support structure and rotates with the opening and closing of the launch vehicle's roof, ensuring the grid adheres tightly to the roof. This allows the grid to guide airflow when the roof is closed, and to retract when the roof is open, freeing up space. Simultaneously, the airflow passing through the grid effectively reduces the frontal reflection of the shock wave and the backflow effect of the gas jet during launch, protecting the launch box from the backflow and ensuring successful launch. Furthermore, the grid guides airflow upwards, providing protection for downstream equipment at various directional angles, reducing gas impact on downstream equipment and achieving a protective function.

Claims

1. An adjustable gas jet guide device for vehicle-mounted rockets, characterized in that, include: Rotating mechanism one and rotating mechanism two are symmetrically installed on the top cover of the launch vehicle. Each includes rotating base one, fixed plate, connecting rod, and rotating base two. Rotating base one is fixed to the top cover of the launch vehicle, and rotating base two is fixed to the back plate of the launch vehicle. One end of the connecting rod is hinged to the upper end of the fixed plate, and the other end is hinged to rotating base two. The lower end of the fixed plate is hinged to rotating base one. A connector is used to connect rotating mechanism one and rotating mechanism two, so that rotating mechanism one and rotating mechanism two rotate synchronously. The connector adopts a double-headed screw structure, and both ends are connected to rotating mechanism one and rotating mechanism two through universal joints. The grid plate is fixed between the fixed plates of rotating mechanism one and rotating mechanism two to guide the airflow upward. Multiple sets of discharge slots are opened on the fixed plate, and the slot direction is inclined at an angle of 36° with the length direction of the vehicle body. The grid plate is welded to the discharge slots of the fixed plate in a parallel arrangement. The grid plate is made of high temperature resistant ceramic matrix composite material with a temperature resistance of ≥1800℃. The adjustable gas jet guide device can rotate with the opening and closing of the launch vehicle's roof, so that when the launch vehicle's roof is open, it can fit tightly against the roof to release space, and when the launch vehicle's roof is closed, it can guide the airflow to achieve the guiding function and protect the launch box from the impact of the counterflow. Specifically, when the roof is closed, the length direction of the guide device's fixing plate is at 80° with the upper surface of the roof; when the roof is open, the length direction of the fixing plate is at 36° with the upper surface of the roof.

2. The adjustable gas jet guiding device according to claim 1, characterized in that, Multiple sets of discharge slots are opened on the fixed plate, and a laser calibration reference surface is set on one surface of the rotating base. After the grid is installed, the consistency of the grid tilt angle is verified by a laser rangefinder.

3. The adjustable gas jet guiding device according to claim 1, characterized in that, The flatness error of the rotating base is ≤0.1mm, the angular deviation between adjacent grid plates is ≤0.5°, and the flatness error of the overall guide surface is ≤2mm.

4. The adjustable gas jet guiding device according to claim 1, characterized in that, The connecting rod is connected to the fixed plate via a sleeve and a pin.

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