Adjustable fuel gas jet flow guiding device for vehicle-mounted rocket

Abstract

The invention discloses an adjustable fuel gas jet flow guiding device for a vehicle-mounted rocket. The adjustable fuel gas jet flow guiding device comprises grid pieces, a first rotating mechanism, a second rotating mechanism and a connecting piece. The grid pieces are arranged on the first rotating mechanism and the second rotating mechanism. The connecting piece and the rotating mechanism are combined to achieve the rotating function so as to change the relative position of the flow guide grid. The grid piece can be combined with the first rotating mechanism and the second rotating mechanism and can rotate along with opening and closing of the top cover of the launching vehicle, so that the grid piece is tightly attached to the top cover, the grid piece can guide airflow and achieve the flow guiding function when the top cover is closed, and the grid piece can be folded and release space when the top cover is opened. And meanwhile, airflow flows through the grid pieces, so that the launching box is protected from being influenced by counterattack flow, and launching is guaranteed. In addition, the grid pieces can guide airflow to be exhausted upwards, the protection effect on rear equipment can be achieved at different direction angles, fuel gas impact on the rear equipment is reduced, and the protection function is achieved.

Description

Technical Field

[0001] The present invention belongs to the field of flow guiding devices for rockets and missiles, and particularly relates to an adjustable gas jet flow guiding device for vehicle-mounted rockets. Background Art

[0002] Vehicle-mounted weapon systems, with their excellent mobility, concealment, and protection, exhibit broad application prospects and development potential. However, with the continuous progress of modern weapon technologies, more stringent requirements have been imposed on the performance and functions of vehicle-mounted launch devices. The high-temperature and high-speed gas flow generated during the launch process can significantly affect the launch accuracy and the stability of the launch device. In particular, the existence of counterflow can directly erode the missile tail, and in severe cases, it may cause damage to the launch device. The flow guiding device is a key component of the gas jet thermal protection in missile launch technology, mainly used to withstand the impact of the gas jet and guide it to a direction and space conducive to missile launch, avoiding the ablation of important devices by the gas jet ejected from the rocket engine. The gas flow guiding device for vehicle-mounted rocket launch has the advantages of a compact structure, lightweight design, and rapid deployment, which can ensure the safe discharge of the gas flow during rocket launch and effectively protect the safety of vehicles and personnel.

[0003] Common vehicle-mounted hot launch gas flow guiding methods include unidirectional flow guiding devices and multi-directional flow guiding devices. The unidirectional flow guiding device discharges the gas in a single direction and has a simple structure, which is used for missiles with a fixed launch angle. The multi-directional flow guiding device discharges the gas in multiple directions to reduce the impact on the launch platform.

[0004] Traditional planar deflectors or single arc-shaped deflectors are prone to causing gas flow backspray during low-angle launches, damaging the missile tail or the launch device. For example, Patent CN201710535753.6, published on November 23, 2018, discloses a double-arc deflector for vehicle-mounted missile launches. Its planar deflector lacks a streamlined design when impacted by gas, causing a sudden change in the gas flow direction and forming a re-roll, which erodes the equipment. Although the double-arc deflector alleviates the horizontal thrust through the segmented design of the small arc segment and the large arc segment, its arc curvature still needs to be further optimized to reduce local turbulence. Traditional wedge-shaped and conical deflectors are relatively large in volume and difficult to meet the compactness requirements of vehicle-mounted launch devices. For example, in the literature "Influence of the Deflection Structure on the Impact Load of Rocket Launchers" [J]. Journal of Ordnance Equipment Engineering, 2022, 43(8): 74-79, 86. DOI: 10.11809 / bqzbgcxb2022.08.011., such devices need to withstand gas impacts in a limited space and are difficult to integrate into cluster launch devices. Existing flow deflection grids are installed inside the launch tube box. For example, in the literature "Research on the Influence of the Flow Deflection Grid on the Flow Field Environment inside the Launch Box" [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 restricted by the tube wall, easily forming a local high-pressure area, resulting in uneven force on the front cover. When the flow deflection grid is close to the engine nozzle, although it can improve the pressure wave propagation efficiency, it will exacerbate the turbulence intensity inside the tube. Summary of the Invention

[0005] The object of the present invention is to solve the problems existing in the existing gas jet deflection devices for vehicle-mounted rockets during use, such as gas flow re-roll and inability to be compactly installed, and to provide an adjustable gas jet deflection device for vehicle-mounted rockets that can effectively deflect the gas flow and change the gas flow direction.

[0006] The technical solution to achieve the object of the present invention is as follows:

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

[0008] A first rotating mechanism and a second rotating mechanism symmetrically installed on the left and right of the launch vehicle roof cover, each comprising a first rotating base, a fixing plate, a connecting rod, and a second rotating base; the first rotating base is fixed to the launch vehicle roof cover, and the second rotating base is fixed to the launch vehicle backboard; one end of the connecting rod is hinged to the upper end of the fixing plate, and the other end is hinged to the second rotating base; the lower end of the fixing plate is hinged to the first rotating base;

[0009] A connecting member for connecting the first rotating mechanism and the second rotating mechanism to make the first rotating mechanism and the second rotating mechanism rotate synchronously;

[0010] The grid plate is fixed between the fixed plates of the first rotating mechanism and the second rotating mechanism, and is used to guide the air flow to be discharged upward;

[0011] The adjustable gas jet diversion device can rotate with the opening and closing of the launch vehicle top cover. When the launch vehicle top cover is opened, it can be closely attached to the top cover to release space. When the launch vehicle top cover is closed, it can guide the air flow to realize the diversion function and protect the launch box from the impact of the counter flow.

[0012] Compared with the prior art, the remarkable advantages of the present invention are:

[0013] By adopting the symmetrically arranged first rotating mechanism and the second rotating mechanism, and using the connecting piece to realize the linkage between the two, the whole diversion device can flexibly adjust the angle, enhancing the applicability and stability of the device; at the same time, the design of the rectangular grid plate significantly improves the diversion efficiency, providing guarantee for the stable launch of the vehicle-mounted rocket. At the same time, the fixed plate can change the angle with the opening and closing of the launch vehicle top cover, making reasonable use of the roof space. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a schematic structural diagram of the adjustable gas jet diversion device of the present invention;

[0015] Figure 2 It is a schematic structural diagram of the adjustable gas jet diversion device of the present invention in the use state;

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

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

[0018] Figure 5 It is a schematic structural diagram of the rotating base of the adjustable gas jet diversion device of the present invention;

[0019] Figure 6 It is a schematic structural diagram of the fixed plate of the adjustable gas jet diversion device of the present invention;

[0020] Figure 7 It is a schematic structural diagram of the connecting rod of the adjustable gas jet diversion device of the present invention.

[0021] Reference numerals: 1 - grid plate, 2 - first rotating mechanism, 3 - connecting piece, 4 - second rotating mechanism, 5 - first rotating base, 6 - fixed plate, 7 - connecting rod, 8 - second rotating base, 9 - first threaded hole, 10 - second fixed threaded hole, 11 - first connecting hole, 12 - discharge groove, 13 - main board, 14 - second connecting hole, 15 - third connecting hole, 16 - sleeve, 17 - pin, 18 - fourth connecting hole, 19 - fifth connecting hole, 20 - third threaded hole, 21 - launch vehicle top cover, 22 - launch vehicle back panel. Detailed implementation manners

[0022] In order to illustrate the technical solution and technical purpose of the present invention, the present invention will be further introduced below with reference to the accompanying drawings and specific embodiments.

[0023] First, in combination with Figure 1 the embodiments of the present application will be introduced.

[0024] Figure 1 The figure shows a schematic structural diagram of an adjustable gas jet deflector device, and an adjustable gas jet deflector device for a vehicle-mounted rocket applicable to the embodiments of the present application is exemplarily shown therein, which includes: a grid plate 1, a first rotating mechanism 2, a connecting member 3, and a second rotating mechanism 4.

[0025] The first rotating mechanism 2 and the second rotating mechanism 4 are symmetrically installed on the launch vehicle top cover 21 left and right, and are linked through the connecting member 3.

[0026] Figure 2 The figure is a schematic installation diagram of the adjustable gas jet deflector device on the launch vehicle. The two rotating mechanisms are installed on the launch vehicle top cover 21 through a first rotating base 5. The symmetry axes of the first rotating mechanism 2 and the second rotating mechanism 4 coincide with the center line in the vehicle body length direction (i.e., the z-axis direction). The installation of the first rotating mechanism 2 and the second rotating mechanism 4 avoids the position of the rocket engine. The connecting member 3 adopts a high-strength alloy connecting rod, and both ends are fixedly connected to the threaded holes three 20 in the middle of the two rotating mechanisms to ensure that the synchronous movement precision error ≤ 0.5°.

[0027] Figure 4 The figure is a schematic diagram of the rotating mechanism of the adjustable gas jet deflector device. The rotating mechanism includes the following core components: a first rotating base 5, a fixing plate 6, a connecting rod 7, and a second rotating base 8.

[0028] Figure 5 The figure is a schematic structural diagram of the rotating base of the adjustable gas jet deflector device of the present invention. The fixing threaded hole one 9 and the fixing threaded hole two 10 of the first rotating base 5 are connected to the embedded parts of the launch vehicle top cover 21 by using M16 high-strength bolts. A laser calibration reference surface is arranged on the surface of the first rotating base, and the installation flatness error ≤ 0.1 mm. The second rotating base 8 is rigidly connected to the embedded parts of the launch vehicle back plate 22 through M16 high-strength bolts.

[0029] Figure 6 The figure is a schematic structural diagram of the fixing plate 6 of the adjustable gas jet deflector device. The main board 13 has dimensions of 1200 mm × 400 mm × 50 mm, and 13 groups of discharge grooves 12 are opened on the surface. The groove width is 7 mm, the spacing is 10 mm, and the inclination angle with the z-axis direction is 36°. Connecting holes two 14 and connecting holes three 15 are arranged at both ends of the main board 13, with a diameter of 12 mm. The connecting holes three 15 are used for hinged connection with the connecting rod 7, and the connecting holes two 14 are used for hinged connection with the first rotating base 5.

[0030] The grid sheet 1 has dimensions of 200mm × 100mm × 5mm and is made of a high-temperature resistant ceramic matrix composite material with a temperature resistance of ≥1800°C. It is welded to the surface of the discharge groove 12 of the fixed plate 6 in a parallel arrangement. The installation technical requirements are as follows:

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

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

[0033] Figure 7 It is a schematic structural diagram of the connecting rod 7 of the adjustable gas jet diversion device, including two articulated connecting rods. One end of the connecting rod 7 is provided with a connection hole four and is connected to the fixed plate 6 through a sleeve 16 and a dowel pin 17. The other end is provided with a connection hole five 19 for articulation with the rotating base two 8. The middle part is provided with a threaded hole three 20 and locked with the connecting piece 3, enabling an angle adjustment range of 0° to 77°.

[0034] The connecting piece 3 adopts a double-headed screw structure, and both ends are connected to the threaded hole three 20 of the rotating mechanism one 2 and the rotating mechanism two 4 through universal joints to achieve synchronous angle adjustment of the two mechanisms.

[0035] The fixed plate 6 is articulated with the rotating base one 5 through the connection hole one 11 and can be folded with the car roof cover at 36° to 80°.

[0036] Example of the working process.

[0037] During the gas discharge stage, the car roof cover 21 is in the closed state. The length direction of the fixed plate 6 of the diversion device forms an 80° angle with the upper end face of the car roof cover. After the rocket is ignited, when the high-temperature gas flows through the discharge groove 12, it is divided into multiple laminar flows by the grid sheet 1. Compared with the traditional flat diversion plate, the impact of the countercurrent on the launch device is reduced.

[0038] After the launch is completed, the car roof cover 21 is opened. The diversion device rotates synchronously with the car roof cover through the gas spring-assisted rotating mechanism one 2 and the rotating mechanism two 4. Its angle has a linear relationship with the opening and closing angle of the car roof cover. Finally, the length direction of the fixed plate 6 forms a 36° angle with the upper end face of the car roof cover, facilitating the driver's entry and exit. The connecting piece 3 ensures the linkage of the two rotating mechanisms, improving the stability and reliability of the device.

[0039] An adjustable gas jet diversion device for vehicle-mounted rockets according to the present invention. The grid plates can be combined with the support structure and can rotate with the opening and closing of the launch vehicle top cover, so that the diversion grid is closely attached to the top cover. Thus, the diversion grid can guide the airflow when the top cover is closed to achieve the diversion function, and can be retracted when the top cover is opened to release space. At the same time, by the airflow flowing through the diversion grid, the positive reflection of the shock wave and the re-rolling effect of the gas jet during the launch process can be effectively improved, protecting the launch box from the impact of the counter-flow and ensuring the progress of the launch. In addition, the diversion grid can guide the airflow to be discharged upward, and the protection effect on the rear equipment can be achieved at different direction angles, reducing the gas impact on the rear equipment and realizing the protection function.

Claims

1. An adjustable gas jet diversion device for a vehicle-mounted rocket, characterized in that, Including: Rotating mechanism 1 and rotating mechanism 2 symmetrically installed on the left and right of the launcher roof cover, each including a rotating base 1, a fixing plate, a connecting rod, and a rotating base 2; the rotating base 1 is fixed to the launcher roof cover, and the rotating base 2 is fixed to the launcher backboard; one end of the connecting rod is hinged to the upper end of the fixing plate, and the other end is hinged to the rotating base 2; the lower end of the fixing plate is hinged to the rotating base 1; A connecting piece for connecting rotating mechanism 1 and rotating mechanism 2 to make rotating mechanism 1 and rotating mechanism 2 rotate synchronously; Grid plates fixed between the fixing plates of rotating mechanism 1 and rotating mechanism 2 for guiding the airflow to be discharged upward; The adjustable gas jet flow guiding device can rotate with the opening and closing of the launcher roof cover, so that when the launcher roof cover is opened, it can closely adhere to the roof cover to release space, and when the launcher roof cover is closed, it can guide the airflow to achieve the flow guiding function and protect the launch box from the impact of the countercurrent.

2. The adjustable gas jet diversion device according to claim 1, characterized in that, Multiple groups of discharge grooves are opened on the fixing plate, and the opening direction is inclined at an angle of 36° to the length direction of the vehicle body. The grid plates are welded in the discharge grooves of the fixing plate in a parallel arrangement.

3. The adjustable gas jet deflector device according to claim 2, characterized in that, Multiple groups of discharge grooves are opened on the fixing plate, and a laser calibration reference surface is arranged on the surface of the rotating base 1. After the grid plates are installed, the inclination angle consistency of the grid plates is verified by a laser rangefinder.

4. The adjustable gas jet flow guiding device according to claim 1, wherein, The flatness error of the installation plane of the rotating base 1 ≤ 0.1 mm, the angular deviation between adjacent grid plates ≤ 0.5°, and the flatness error of the overall flow guiding surface ≤ 2 mm.

5. The adjustable gas jet flow guiding device according to claim 1, characterized in that, The connecting piece adopts a double-headed screw structure, and both ends are connected to rotating mechanism 1 and rotating mechanism 2 through universal joints.

6. The adjustable gas jet flow guiding device according to claim 1, characterized in that When the roof cover is in the closed state, the length direction of the fixing plate of the flow guiding device forms an 80° angle with the upper end surface of the roof cover; when the roof cover is in the open state, the length direction of the fixing plate forms a 36° angle with the upper end surface of the roof cover.

7. The adjustable gas jet flow guiding device according to claim 1, wherein, The connecting rod is connected to the fixing plate 6 through a sleeve 16 and a pin 17.

8. The adjustable gas jet flow guiding device according to claim 1, characterized in that, The grid plates are made of a high-temperature resistant ceramic matrix composite material with a temperature resistance ≥ 1800 °C.

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