A valve isolation type multi-launching series launching device

Abstract

The application provides a valve isolation type multi-launching series launching device, which realizes maximum utilization of space by reasonably stacking two rockets in the same launching cylinder in a vertical series mode; the intermediate flow guide device is responsible for guiding the high-temperature and high-pressure gas flow generated by the first rocket, protecting the second rocket from gas impact and ensuring smooth launching; finally, the cooperation of the closed ring and the valve flow guide plate ensures the closure of the cylinder section before the launching of the second rocket; the multi-launching series launching device can be used for rocket launching, and is also applicable to the launching scene of series projectiles, cannon-launched unmanned aerial vehicles and other high-pressure gas generating scenes.

Description

Technical Field

[0001] The present invention belongs to the technical field of launch devices, and in particular relates to a valve-isolated multi-launch serial launch 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, an excessively long module will also bring about problems such as increased difficulty in production, manufacturing, and transportation. Li Pingqi et al. mentioned in a paper on the design research of the slenderness ratio of liquid carrier rockets that the current common rocket slenderness ratio is generally controlled within 17.

[0003] To maximize space utilization, designers must coordinate and match parameters such as the rocket's length, diameter, and weight with the launch tube's structure to ensure structural stability and effective thrust transmission. Currently, various platforms are reducing the size and weight of launchers through modularization, compactness, and integration, while increasing their integration, allowing them to accommodate more launch units within the same space.

[0004] With the future development of information-based and intelligent models, the platform's launch system will gradually move towards automated launch and multi-tasking. Increasing the launcher's payload capacity will help the platform play a greater role in complex intelligent launch environments and support future high-density, high-frequency launch requirements. Currently, twin-mounted launchers, typically referring to launch platforms with two missiles or weapons mounted side by side, offer the primary advantages of simple structural design, rapid launch preparation, and high firepower density. However, they are essentially still single rocket launch tubes loaded with a single rocket, resulting in no increase in payload per unit area. For launch scenarios with limited space, such as ships, there may be launch spaces with high aspect ratios. If a launcher can vertically arrange two or more rockets with a reasonable aspect ratio, the current arrangement of one launch tube per launch unit would result in significant waste of payload space and significantly reduce payload capacity. To maximize space utilization and increase payload capacity, multiple tandem missile launch tubes are a key research direction.

[0005] Currently, there are few studies on tandem rocket launches. The characteristics of projectiles due to their small length and being in a launch space with a large aspect ratio are similar to the research background and significance of the tandem launch proposed in this invention. Huang Xi et al. proposed a patent CN112432563B for a piston-type multi-projectile tandem launch structure. During the launch process, the projectiles are connected together and separated after exiting the tube. Hang Yu et al. studied the tandem launch of separate tubes in DOI: 10.13465 / j.cnki.jvs.2022.03.001, but the working model they proposed was relatively simple. The simulation experiment using a simulated bomb was more inclined to the study of the test method, and did not consider the problem of handling the gas from the first launch.

[0006] With the continuous advancement of aerospace technology, launch technology is becoming increasingly mature, capable of meeting more sophisticated launch requirements. Currently, for tandem launch missions, ensuring the safety and stability of the two rockets during the tandem launch process has become a major technical challenge due to airflow interference, launch channel limitations, and other factors. Regarding the previously mentioned current research, there is little research on tandem rocket launches, and when projectiles are launched in tandem, the research is limited to basic models and simulation experiments, without considering the high-temperature, high-pressure gas generated in actual situations. The impact of the high-temperature, high-pressure gas generated during the rocket launch process is not negligible. The first rocket generates a large amount of heat during launch, 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 can cause contamination or physical damage, triggering failures during the second launch, or even 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 multi-launch serial 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 serial launch process and ensuring that the launch path of the next rocket is unobstructed.

[0009] A valve-isolated multiple-launch tandem launcher comprises an upper barrel section 1, a lower barrel section 2, an intermediate flow guide device, and a sealing 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, thereby completely clearing the launch channel for 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, thereby isolating 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 cylinder section, and each guide plate rotating shaft 21 is connected to a flap guide plate 31 at both ends, so that the flap guide plate 31 can be rotated with the guide plate rotating shaft 21 connected to it 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 drive the flap guide plate 31 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, completing the closure of the two barrel sections.

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

[0018] In the launch-ready state, the intermediate guide device operates in the closed guide mode. At this point, 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 held closed by 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.

[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. The generated gas is directed to the outside through the gas exhaust port 11.

[0020] After the launch of the first rocket is completed, the intermediate guide device switches 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 cylinder section 2 toward the bottom of the lower cylinder 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 plate 31 falls as the two valve 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.

[0021] Beneficial effects:

[0022] 1. The present invention provides a valve-isolated multiple-launch serial launch device. First, two rockets are reasonably stacked in the same launch tube in a vertical series manner, 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, protecting the second rocket from gas impact and subsequent smooth launch. Finally, the cooperation between the closed ring and the valve guide plate ensures that the tube section is closed before the second rocket is launched. The multiple-launch serial launch of the present invention can be used not only for rocket launch, but also for launch scenarios that generate high-pressure gas such as tandem projectiles and gun-launched drones.

[0023] 2. This invention provides a valve-separated, multiple-rocket tandem launcher with an autonomous separation mechanism for the intermediate guide device. This mechanism allows the valve guide plates to open smoothly after the first rocket launches, using an external drive such as a motor, freeing the launch path for the second rocket. This mechanism ensures smooth separation between the rockets and precisely controls the launch of the second rocket, avoiding interference or malfunctions in complex environments.

[0024] 3. The present invention provides a flap-isolated multi-shot serial launch device. The flap guide plate is designed as two spherical structures, which can rotate together with the guide plate rotation axis. The flap guide plate is driven by a traction member to control the opening or closing of the flap guide plate, 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 multi-launch serial launch device provided by the present invention;

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

[0027] Figure 3 This is a cross section of the valve-isolated multiple-launch series launcher in the closed diversion mode provided by the present invention;

[0028] Figure 4 The present invention provides a cross section of a flap-isolated multiple-shot serial launch device in a release 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-launch tandem launcher comprises an upper barrel section 1, a lower barrel section 2, an intermediate flow guide device, and a sealing 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 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, thereby completely clearing the launch channel for the second rocket.

[0033] The sealing ring 4 is placed on the end of the upper barrel section 1. After the first rocket is launched, it closes the gap between the upper barrel section 1 and the lower barrel section 2 caused by the intermediate flow guide device sliding toward the barrel bottom, isolating the gas flow generated during the launch of the second rocket. It should be noted that before the rocket is launched, the sealing ring 4 can slide along the axis of the launch barrel and has a height greater than the gap between the upper and lower barrel sections.

[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 cylinder 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 be rotated with the guide plate rotating shaft 21 connected to it 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 drive the flap guide plate 31 to open or close through the connecting rod 32.

[0036] The working modes of the intermediate guide device of the present invention are divided into closed guide mode and 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 two flap deflectors 31 are positioned between the upper and lower barrel sections 1 and 2, held closed by connecting rods 32. The sealing ring 4 is blocked at the bottom of the upper barrel section 1 by the flap deflectors 31. When a rocket in the upper barrel section 1 is launched, it ignites and generates high-temperature, high-pressure combustion gases. The closed flap deflectors 31 guide the combustion gases and isolate the lower barrel section. The generated combustion gases are then directed to the exterior through the gas exhaust port 11.

[0038] After the first rocket is launched, the intermediate guide device 3 switches from the closed guide mode to the clear launch mode. An external drive device such as a motor drives the traction member 33 to slide along the launch tube wall toward the bottom of the tube, driving the valve 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 As shown, the sealing ring 4 above the flap guide plate 31 simultaneously drops a certain distance as the two flap guide plates 31 move aside, sealing the upper and lower cylinder sections 1 and 2. This opens the launch channel for the next rocket, allowing the launch process of the rocket in the lower cylinder section 2 to continue.

[0039] It should be noted that if the present invention needs to arrange multiple rockets, its lower portion 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 drive mechanism such as a motor and can slide along the launch direction, thereby driving the valve guide plate 31 to open or close through the connecting rod 32. The drive mechanism can be pneumatic, hydraulic or other reliable drive methods. The ability to slide along the launch direction is to reduce the space occupied outside the tube. When there is ample space in the middle part, it is not necessary to move completely along the launch direction, and can be moved 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, current twin-launch systems typically use two rockets arranged side by side, but their structural design is still based on a single launch tube loaded with a single rocket, meaning each launch tube can only accommodate one rocket. This results in low launch space utilization, especially in launch scenarios with limited space and a large aspect ratio, such as ships. The present invention maximizes space utilization by vertically cascading two rockets in the same launch tube. This design significantly improves the load-bearing capacity in spaces with a large aspect ratio, making it particularly suitable for launch platforms with limited space.

[0042] Second, some existing multi-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 address 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 particularly emphasizes the effective diversion and isolation of high-temperature and high-pressure gas. 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, avoiding adverse effects on the second rocket. This design significantly improves the safety of the rocket during the serial launch process.

[0043] Third, while some current tandem launch research has included some simulations, most remain at the simple model or basic testing stage and lack in-depth exploration of how to achieve isolation and protection during actual tandem launches. This invention incorporates an autonomous separation mechanism for the intermediate deflector. This mechanism enables the smooth opening of the flaps and deflectors after the launch of the first rocket, using an external drive such as a motor, to clear the path for the second rocket. This mechanism ensures smooth separation between the rockets and precisely controls the launch of the second rocket, avoiding interference or malfunctions 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 of course 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 serial launch device, 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, thereby completely clearing the launch channel of the second rocket; 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 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 cylinder 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 the driving mechanism, and the traction member (33) can slide along the launching direction under the control of the driving mechanism, and then drive the flap guide plate (31) to be opened or closed 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. The valve-isolated multiple-shot serial launch device according to 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) move away, thereby completing the closure of the two barrel sections.

5. The valve-isolated multiple-shot serial launch device according to claim 2, characterized in that: The working modes of the intermediate diversion device are divided into closed diversion mode and clear launch mode; In the launch preparation state, the intermediate guide device operates in a 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 at the bottom of the upper barrel section (1) by the flap guide plates (31); 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); After the launch of the first rocket is completed, the intermediate guide device switches 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 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 their 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 flap guide plates (31) falls 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 for 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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