Valve isolation type multi-shot series-connection launching device

Abstract

According to the petal isolation type multi-shot series connection launching device, firstly, two rockets are reasonably stacked in the same launching cylinder in a vertical series connection mode, and maximum utilization of space is achieved; secondly, the middle flow guiding device is responsible for guiding high-temperature and high-pressure fuel gas flow generated by the first rocket, and the second rocket is protected against fuel gas impact and follow-up smooth launching; finally, through cooperation of a sealing ring and a valve guide plate, it is ensured that sealing of the cylinder section is completed before the second rocket is launched; the multi-shot series-connection launching method can be used for rocket launching and is also suitable for launching scenes such as series-connection shots and cannon-shooting unmanned aerial vehicles which generate high-pressure gas.

Description

Technical Field

[0001] The invention belongs to the technical field of launching devices, and in particular relates to a valve-isolated multiple-shot series-connected launching device. Background Art

[0002] Generally speaking, the slenderness ratio of a rocket should not be too large or too small. An excessively large slenderness ratio may cause the rocket's first-order elastic frequency to decrease, making the rocket more susceptible to external interference such as airflow disturbances during flight, thereby affecting the stability of its attitude control. At the same time, a large slenderness ratio will also significantly increase the bending moment load, ground lifting, transportation, and erection loads during flight, causing deformation or damage to the rocket structure, thereby affecting its reliability and safety. In addition, a module that is too long will also bring about problems such as increased difficulty in production and transportation. Li Pingqi et al. mentioned in a paper on the design research of the slenderness ratio of liquid launch vehicles that the current common rocket slenderness ratio is generally controlled within 17.

[0003] In order to maximize the use of space, designers need to coordinate and match the length, diameter, weight and other parameters of the rocket with the structure of the launch tube to ensure that the structure is stable and the thrust is effectively transmitted. At present, various platforms have reduced the size and weight of the launch device and improved the integration of the launch device through modularization, compactness and integration, so that more launch units can be carried in the same space.

[0004] With the development of information and intelligent models in the future, the launch system of the platform will gradually move towards automated launch and multi-tasking. Increasing the loading capacity of the launch device will help the platform play a greater role in a complex intelligent launch environment and support new launch requirements such as high density and high frequency in the future. At present, for a twin-mounted launch device, it usually refers to a launch platform with two missiles or weapons installed side by side. Its main advantages are simple structural design, fast launch preparation, and good firepower density. However, in essence, it is still a single rocket launch tube loaded with a single rocket, and the loading capacity per unit area has not increased. For launch scenarios such as ships where space is not abundant, there may be launch space with a large aspect ratio. If the launch device can vertically arrange more than two rockets with a reasonable aspect ratio, according to the current arrangement of loading one launch unit in one launch tube, there will be a lot of loading space waste, which greatly reduces its loading capacity. In order to make full use of space and increase the payload carried, multiple tandem missile launch tubes are an important research direction.

[0005] There are few studies on rocket serial launches at present. Among them, the projectiles have certain similarities with the research background and significance of the serial launch proposed in this invention due to their small length and the characteristics of being in a launch space with a large aspect ratio. Huang Xi et al. proposed a patent CN112432563B for a piston-type multi-projectile serial launch structure. The launch process is that the projectiles are connected together and separated after leaving the tube. Hang Yu et al. studied the serial launch of separate tubes in DOI: 10.13465 / j.cnki.jvs.2022.03.001, but the working model they proposed is relatively simple. The simulation experiment with simulated bombs is more inclined to the study of test methods, and the problem of handling the gas from the first launch is not considered.

[0006] With the continuous advancement of aerospace technology, launch technology is becoming more and more mature, and it can solve more refined launch needs. At present, for launch missions loaded in series, due to airflow interference, launch channel restrictions and other reasons, ensuring the safety and stability of the two rockets during the series launch has become an important technical problem. As for the current research mentioned earlier, there is little research on rocket series launch, and the series launch of projectiles only stays in the basic model and simulation bomb experiments, without considering the high-temperature and high-pressure gas generated in actual situations. For the rocket launch process, the impact of the high-temperature and high-pressure gas it generates cannot be ignored. The first rocket will generate a lot of heat during the launch process, which may cause the temperature of the next rocket to rise, affecting its performance and stability. The direct impact of the gas on the next rocket will cause pollution or physical damage, causing failures during the secondary launch, and even causing damage and explosion of the next rocket.

[0007] Therefore, in the launch mission of a rocket device with a large aspect ratio (length-to-diameter ratio), how to ensure the smooth launch of multiple rockets in a multi-launch series state, and design a launch system that can ensure the safe, rapid and reliable separation of the guide device and avoid interfering with the subsequent rocket launch trajectory has become a technical problem that needs to be solved urgently. Summary of the invention

[0008] In order to solve the above problems, the present invention provides a valve-isolated multiple-launch tandem launch device, which can improve the utilization rate of the launch space and effectively isolate and process high-temperature and high-pressure combustion gas. It is suitable for guiding the previous rocket during the rocket tandem launch process and ensuring that the launch path of the next rocket is unobstructed.

[0009] A valve-isolated multiple-shot tandem launch device, comprising an upper barrel section 1, a lower barrel section 2, an intermediate flow guide device, and a closed ring 4;

[0010] The intermediate flow guide device is located between the upper cylinder section 1 and the lower cylinder section 2, and the upper cylinder section 1 is used to accommodate the first rocket, and the lower cylinder section 2 is used to accommodate the second rocket; the end of the upper cylinder section 1 is provided with an exhaust port for conducting and discharging the gas generated during the launch of the first rocket;

[0011] The intermediate flow guide device is used to isolate the second rocket located in the lower cylinder section 2 before the first rocket is launched, so that it is not affected by the impact and ablation of the gas generated during the launch of the first rocket; at the same time, the intermediate flow guide device is also used to separate into two parts after the first rocket is launched, and the two parts slide along the bottom direction of the lower cylinder section 2 respectively, so as to completely clear the launch channel of the second rocket;

[0012] The closing ring 4 is sleeved on the end of the upper cylinder section 1, and is used to close the gap between the upper cylinder section 1 and the lower cylinder section 2 caused by the sliding of the intermediate guide device toward the bottom of the cylinder after the first rocket is launched, so as to isolate the gas flow generated during the launch of the second rocket.

[0013] Furthermore, the intermediate flow guide device includes two flow guide components, two flow guide plate rotating shafts 21 and a driving mechanism; wherein the flow guide components each include a flap flow guide plate 31, a connecting rod 32 and a traction member 33;

[0014] The two guide plate rotating shafts 21 are respectively fixed on the opposite sides of the end of the lower barrel section, and each of the two ends of the guide plate rotating shaft 21 is connected to a flap guide plate 31, so that the flap guide plate 31 can rotate with the guide plate rotating shaft 21 connected thereto as the axis; the connecting rod 32 connects the flap guide plate 31 and the traction member 33 through the rotating shafts at both ends, and the connections at both ends can rotate around the rotating shaft; the traction member 33 is connected to the driving mechanism, and the traction member 33 can slide along the launching direction under the control of the driving mechanism, and then the flap guide plate 31 is driven to open or close through the connecting rod 32.

[0015] Furthermore, the flap guide plate 31 is a partial spherical structure.

[0016] Furthermore, the height of the closing ring 4 is greater than the gap between the upper barrel section 1 and the lower barrel section 2, and after the first rocket is launched, the closing ring 4 can slide between the upper barrel section 1 and the lower barrel section 2 as the two valve guide plates 31 move aside, thereby completing the closure of the two barrel sections.

[0017] Furthermore, the working modes of the intermediate guide device are divided into a closed guide mode and a get-out-of-the-way launch mode;

[0018] In the launch preparation state, the intermediate guide device works in the closed guide mode; at this time, the traction member 33 is located at the uppermost end of the lower barrel section 2, and the two flap guide plates 31 are located between the upper barrel section 1 and the lower barrel section 2, and are kept closed under the support of the connecting rod 32; the closed ring 4 is blocked by the flap guide plates 31 at the bottom of the upper barrel section 1;

[0019] During the launch of the first rocket, the two closed flap guide plates 31 guide the gas generated by the first rocket and isolate the lower cylinder section 2, and the generated gas is guided to the outside through the gas exhaust port 11;

[0020] After the launch of the first rocket is completed, the intermediate guide device is switched from the closed guide mode to the clear launch mode; the driving device drives the traction member 33 to slide along the wall of the lower barrel section 2 toward the bottom of the lower barrel section 2, driving the two valve guide plates 31 to open to both sides under the action of their respective corresponding traction members 33 and connecting rods 32, and finally completely clear the launch channel; at the same time, the closed ring 4 above the valve guide plates 31 falls down as the two valve guide plates 31 make way, forming a closure for the upper barrel section 1 and the lower barrel section 2; at this time, the launch channel of the second rocket is opened, and the launch of the second rocket located in the lower barrel section 2 can continue.

[0021] Beneficial effects:

[0022] 1. The present invention provides a valve-isolated multiple-shot tandem launch device. First, two rockets are reasonably stacked in the same launch tube in a vertical series connection, thereby maximizing the use of space. Secondly, an intermediate guide device is used to guide the high-temperature and high-pressure gas flow generated by the first rocket to protect the second rocket from gas impact and subsequent smooth launch. Finally, the cooperation of a closed ring and a valve guide plate is used to ensure that the tube section is closed before the second rocket is launched. The multiple-shot tandem launch of the present invention can not only be used for rocket launch, but is also suitable for launch scenarios that generate high-pressure gas, such as tandem projectiles and gun-launched drones.

[0023] 2. The present invention provides a flap-isolated multiple-launch tandem launch device, and designs an autonomous separation mechanism for the intermediate guide device, so that after the first rocket is launched, the flap guide plate can be smoothly opened through an external drive device such as a motor drive to release the launch channel for the second rocket. This mechanism ensures the smooth separation between rockets, and can accurately control the launch process of the second rocket, avoiding interference or failure in complex environments.

[0024] 3. The present invention provides a flap-isolated multiple-shot serial launch device, in which the flap guide plates are designed as two spherical structures, which can rotate together with the guide plate rotating shaft. The flap guide plates are driven by a traction member to control the opening or closing of the flap guide plates, thereby achieving isolation and protection of serial launch in actual launch. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 A schematic diagram of a valve-isolated multiple-shot series-connected launching device provided by the present invention;

[0026] Figure 2 The deployment process of the flap-isolated multi-shot serial launch device provided by the present invention;

[0027] Figure 3 The cross section of the flap-isolated multiple-shot serial launch device in the closed diversion mode provided by the present invention;

[0028] Figure 4 The invention provides a cross section of a flap-isolated multiple-shot serial launch device in a release launch mode. DETAILED DESCRIPTION

[0029] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application.

[0030] like Figure 1 As shown, a valve-isolated multiple-shot tandem launcher comprises an upper barrel section 1, a lower barrel section 2, an intermediate flow guide device, and a closed ring 4; wherein the upper barrel section 1 and the lower barrel section 2 are both fixed to the outside;

[0031] The intermediate flow guide device is located between the upper cylinder section 1 and the lower cylinder section 2, and the upper cylinder section 1 is used to accommodate the first rocket, and the lower cylinder section 2 is used to accommodate the second rocket; the end of the upper cylinder section 1 is provided with an exhaust port for conducting and discharging the gas generated during the launch of the first rocket; the upper cylinder section 1 and the lower cylinder section 2 have the same cylindrical axis to ensure that the second rocket can continue to be launched after the first rocket is launched;

[0032] The intermediate flow guide device is used to isolate the second rocket located in the lower cylinder section 2 before the first rocket is launched, so that it is not affected by the impact and ablation of the gas generated during the launch of the first rocket; at the same time, the intermediate flow guide device is also used to separate into two parts after the first rocket is launched, and the two parts slide along the bottom direction of the lower cylinder section 2 respectively, so as to completely clear the launch channel of the second rocket;

[0033] The closed ring 4 is sleeved on the end of the upper barrel section 1, and is used to close the gap between the upper barrel section 1 and the lower barrel section 2 caused by the sliding of the intermediate flow guide device toward the barrel bottom after the first rocket is launched, and isolate the gas flow generated during the launch of the second rocket. It should be noted that the closed ring 4 can slide along the axis of the launch barrel before the rocket is launched, and its height is greater than the gap between the upper barrel section and the lower barrel section;

[0034] Furthermore, the intermediate flow guide device includes two flow guide components, two flow guide plate rotating shafts 21 and a driving mechanism; wherein the flow guide components each include a flap flow guide plate 31, a connecting rod 32 and a traction member 33;

[0035] like Figure 2As shown, the two guide plate rotating shafts 21 are respectively fixed on the opposite sides of the end of the lower barrel section, and the two ends of each guide plate rotating shaft 21 are respectively connected to a flap guide plate 31, so that the flap guide plate 31 can rotate with the guide plate rotating shaft 21 connected thereto as the axis; the connecting rod 32 connects the flap guide plate 31 and the traction member 33 through the rotating shafts at both ends, and the connections at both ends can rotate around the rotating shaft; the traction member 33 is connected to the driving mechanism, and the traction member 33 can slide along the launching direction under the control of the driving mechanism, and then the flap guide plate 31 is driven to open or close through the connecting rod 32.

[0036] The working modes of the intermediate flow guiding device of the present invention are divided into a closed flow guiding mode and a clear launch mode; the processes of the two working modes are as follows:

[0037] In the launch preparation state, the intermediate guide device 3 is in the closed guide mode. Figure 3 As shown, the traction member 33 is located at the uppermost end, and the two flap guide plates 31 are located between the upper barrel section 1 and the lower barrel section 2, and are kept closed under the support of the connecting rod 32. The closed ring 4 is blocked at the bottom of the upper barrel section 1 by the flap guide plates 31. When the rocket located at the upper barrel section 1 is launched, the rocket ignites to generate high-temperature and high-pressure combustion gas, and the closed flap guide plates 31 guide the combustion gas generated by the rocket and form an isolation for the lower barrel section, and the generated combustion gas is guided to the outside through the combustion gas exhaust port 11.

[0038] After the first rocket is launched, the intermediate flow guide device 3 switches from the closed flow guide mode to the clear launch mode. The external drive device such as the motor drives the traction member 33 to slide along the launch tube wall toward the bottom of the tube, driving the flap guide plate 31 to open to both sides under the action of the traction member 33 and the connecting rod 32, and finally completely clear the launch channel. Figure 4 At the same time, the sealing ring 4 above the flap guide plate 31 drops a certain distance as the two flap guide plates 31 move away, forming a seal for the upper barrel section 1 and the lower barrel section 2. In this state, the launch channel for the next rocket is opened, and the launch process of the rocket located in the lower barrel section 2 can continue.

[0039] It should be noted that if the present invention needs to arrange multiple rockets, the lower part thereof is selected to have the same design as the upper tube section 1, so that multiple sections of the launch tube are connected in series. At this time, each time a rocket is launched, the tube section where the uppermost rocket is located is the upper tube section, and the tube section where the next-stage rocket is located is the lower tube section. The traction member 33 is connected to a driving mechanism such as a motor, and can slide along the launch direction, and then drive the valve guide plate 31 to open or close through the connecting rod 32. The driving mechanism can be pneumatic, hydraulic or other reliable driving methods. The sliding along the launch direction is to reduce the occupation of the space outside the tube. When there is sufficient space in the middle part, it is not necessary to move completely along the launch direction, and it can be within the range allowed by the rotating shaft.

[0040] In summary, the advantages of the present invention over the prior art are as follows:

[0041] First, the current twin-mounted launch device usually arranges two rockets side by side, but its structural design is still based on a single launch tube loaded with a single rocket, that is, each launch tube can only accommodate one rocket. This leads to low launch space utilization, especially in launch scenarios with limited space and large aspect ratios such as ships. The present invention reasonably stacks two rockets in the same launch tube by vertically connecting them in series, thereby maximizing the use of space; this design method significantly improves the load-bearing capacity in a space with a large aspect ratio, and is particularly suitable for launch platforms with limited space.

[0042] Second, some existing multiple-shot serial launch devices usually simply connect multiple projectiles together and separate them during launch, without fully considering the impact of the high-temperature and high-pressure gas generated by the launch of the first projectile (rocket) on the second projectile (rocket). Many idealized research models and experiments do not involve the issue of how to effectively handle these gases, which may cause the temperature of subsequent rockets to rise, performance to decline, and even physical damage. The present invention places special emphasis on the effective diversion and isolation of high-temperature and high-pressure gases. Through the intermediate diversion device (including the valve guide plate and the closed ring), the present invention can effectively guide the gas generated by the launch of the first rocket to the outside to avoid adverse effects on the second rocket. This design significantly improves the safety of the rocket during the serial launch process.

[0043] Third, although some current tandem launch studies have some simulation experiments, most of them remain at the stage of simple models or basic tests, and have not explored in depth how to achieve isolation and protection of tandem launches in actual launches. The present invention designs an autonomous separation mechanism for the intermediate guide device, so that after the first rocket is launched, the valve guide plate can be smoothly opened through an external drive device such as a motor drive to release the launch channel for the second rocket. This mechanism ensures the smooth separation between rockets and can accurately control the launch process of the second rocket, avoiding interference or failure in complex environments.

[0044] Of course, the present invention may have many other embodiments. Without departing from the spirit and essence of the present invention, those skilled in the art may certainly make various corresponding changes and modifications based on the present invention, but these corresponding changes and modifications should all fall within the scope of protection of the claims attached to the present invention.

Claims

1. A valve-isolated multiple-shot tandem launcher, characterized in that: It comprises an upper cylinder section (1), a lower cylinder section (2), an intermediate flow guide device, and a closed ring (4); The intermediate flow guide device is located between an upper cylinder section (1) and a lower cylinder section (2), and the upper cylinder section (1) is used to accommodate a first rocket, and the lower cylinder section (2) is used to accommodate a second rocket; an exhaust port is provided at the end of the upper cylinder section (1) for conducting and discharging the gas generated during the launch of the first rocket; The intermediate flow guide device is used to isolate the second rocket located in the lower cylinder section (2) before the first rocket is launched, so that the second rocket is not affected by the impact and ablation of the gas generated during the launch of the first rocket; at the same time, the intermediate flow guide device is also used to separate into two parts after the first rocket is launched, and the two parts slide along the bottom direction of the lower cylinder section (2) respectively, so as to completely clear the launch channel of the second rocket; The closed ring (4) is sleeved on the end of the upper cylinder section (1) and is used to close the gap between the upper cylinder section (1) and the lower cylinder section (2) caused by the sliding of the intermediate flow guide device toward the cylinder bottom after the first rocket is launched, thereby isolating the gas flow generated during the launch of the second rocket.

2. A valve-isolated multiple-shot serial launch device as claimed in claim 1, characterized in that: The intermediate flow guide device comprises two flow guide components, two flow guide plate rotating shafts (21) and a driving mechanism; wherein the flow guide components each comprise a flap flow guide plate (31), a connecting rod (32) and a traction member (33); Two guide plate rotating shafts (21) are respectively fixed on opposite sides of the end of the lower barrel section, and the two ends of each guide plate rotating shaft (21) are respectively connected to a flap guide plate (31), so that the flap guide plate (31) can rotate with the guide plate rotating shaft (21) connected thereto as an axis; the connecting rod (32) connects the flap guide plate (31) and the traction member (33) through the rotating shafts at both ends, and the connections at both ends can rotate around the rotating shaft; the traction member (33) is connected to a driving mechanism, and the traction member (33) can slide along the launching direction under the control of the driving mechanism, and then the flap guide plate (31) is driven to open or close through the connecting rod (32).

3. A valve-isolated multiple-shot serial launch device as claimed in claim 2, characterized in that: The flap guide plate (31) is a partial spherical structure.

4. A valve-isolated multiple-shot serial launch device as claimed in claim 2, characterized in that: The height of the closed ring (4) is greater than the gap between the upper barrel section (1) and the lower barrel section (2), and after the first rocket is launched, the closed ring (4) can slide down between the upper barrel section (1) and the lower barrel section (2) as the two flap guide plates (31) are moved away, thereby completing the closure of the two barrel sections.

5. A valve-isolated multiple-shot serial launch device as claimed in claim 2, characterized in that: The working modes of the intermediate diversion device are divided into closed diversion mode and make way launch mode; In the launch preparation state, the intermediate flow guide device operates in a closed flow guide mode; at this time, the traction member (33) is located at the uppermost end of the lower barrel section (2), and the two flap flow guide plates (31) are located between the upper barrel section (1) and the lower barrel section (2), and are kept closed under the support of the connecting rod (32); the closed ring (4) is blocked at the bottom of the upper barrel section (1) by the flap flow guide plates (31); During the launch of the first rocket, two closed flap guide plates (31) guide the gas generated by the first rocket and isolate the lower cylinder section (2), and the generated gas is guided to the outside through the gas exhaust port (11); After the launch of the first rocket is completed, the intermediate flow guide device is switched from the closed flow guide mode to the clear launch mode; the driving device drives the traction member (33) to slide along the wall of the lower cylinder section (2) toward the bottom of the lower cylinder section (2), driving the two flap guide plates (31) to open to both sides under the action of the corresponding traction members (33) and the connecting rod (32), and finally completely clear the launch channel; at the same time, the closed ring (4) above the flap guide plates (31) falls down as the two flap guide plates (31) clear, forming a closure for the upper cylinder section (1) and the lower cylinder section (2); at this time, the launch channel of the second rocket is opened, and the launch of the second rocket located in the lower cylinder section (2) can continue.

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