A method and device for determining parameters of a launching ship deflector

Abstract

The application provides a method and device for determining parameters of a baffle of a launching ship, the method comprising: obtaining height information of a launching platform; determining the height of the baffle according to the height information of the launching platform; obtaining rocket nozzle information; and determining the width of the baffle according to the rocket nozzle information. The height and width of the baffle are determined, so that the baffle can block the heat flow generated when the rocket is launched, and the impact force borne by other equipment on the launching ship is reduced; meanwhile, the heat flow guided by the launching platform and the obliquely upward heat flow ejected from the guide groove can smoothly converge, so that the two heat flows inhibit each other, the heat flow speed is reduced, and the obliquely upward heat flow ejected from the guide groove can be prevented from affecting the rocket.

Description

Technical Field

[0001] This invention relates to the field of launch vessel technology, and in particular to a method and apparatus for determining the parameters of a launch vessel's baffle. Background Technology

[0002] Sea-based launches are gradually becoming a routine mode of rocket launches; sea-based satellite launches offer advantages such as high flexibility, good mission adaptability, and superior launch economy. While the flow channels on launch ships are generally arranged laterally, i.e., perpendicular to the launch ship, for longitudinally arranged flow channels, baffles should be installed at the edge of the flow channel outlet facing the bow to protect other equipment on the launch ship. This can block some of the impact of the heat flow and reduce the impact force on other equipment on the launch ship. Determining the appropriate size of the baffle is a problem that needs to be studied and solved. Summary of the Invention

[0003] This invention provides a method and apparatus for determining the parameters of a launch ship baffle. By determining the height and width of the baffle, it ensures that the baffle can block the heat flow generated during rocket launch, thereby reducing the impact force on other equipment on the launch ship. At the same time, it ensures that the heat flow guided by the launch pad and the upward-sloping heat flow ejected from the guide channel can smoothly merge, so that the two inhibit each other, reduce the heat flow velocity, and prevent the upward-sloping heat flow ejected from the guide channel from rolling inward and affecting the rocket.

[0004] To solve the above-mentioned technical problems, the technical solution of the present invention is as follows:

[0005] A method for determining the parameters of a launch ship's deflector includes:

[0006] Obtain the launch pad's altitude information;

[0007] The height of the baffle is determined based on the height information of the launch pad;

[0008] Obtain rocket nozzle information;

[0009] The width of the deflector is determined based on the rocket nozzle information.

[0010] Optionally, obtain the launch pad's altitude information, including:

[0011] Obtain the height difference between the surface of the launch pad and the surface of the launch ship.

[0012] Optionally, determining the height of the deflector based on the height information of the launch pad includes:

[0013] Based on the principle that the baffle should not obstruct the flow of the core area of ​​the gas tail flow: H≦h, the height of the baffle is determined.

[0014] Where H is the height of the baffle, and h is the height difference between the surface of the launch pad and the surface of the launch ship.

[0015] Optionally, obtain rocket nozzle information, including:

[0016] Obtain the diameter of the rocket nozzle and the distance between the two nozzles.

[0017] Optionally, determining the width of the deflector based on the rocket nozzle information includes:

[0018] Based on the principle of complete horizontal obstruction: W≧(D+L), determine the width of the baffle.

[0019] Where W is the width of the baffle, D is the diameter of the rocket nozzle, and L is the distance between the two nozzles.

[0020] Optionally, the method for determining the parameters of the launch vessel's deflector further includes:

[0021] The height and width of the baffle were verified through three-dimensional numerical simulation.

[0022] Optionally, the height and width of the baffle can be verified through three-dimensional numerical simulation, including:

[0023] The launch pad height, nozzle diameter, distance between the two nozzles, and height and width of the baffle were determined. Three-dimensional numerical simulations were used to obtain velocity cloud maps around the baffle at different launch heights to obtain the changes in heat flow velocity under the obstruction of the baffle. The results were used to verify whether the height and width of the baffle could provide impact protection for other equipment on the launch ship and to obtain the verification results on whether the height and width of the baffle were appropriate.

[0024] The present invention also provides a device for determining the parameters of a launch ship's deflector, comprising:

[0025] The acquisition module is used to acquire launch pad height information and rocket nozzle information.

[0026] The processing module is used to determine the height of the deflector based on the height information of the launch pad; and to determine the width of the deflector based on the rocket nozzle information.

[0027] The present invention also provides a computing device, comprising: a processor and a memory storing a computer program, wherein the computer program, when executed by the processor, performs the method described above.

[0028] The present invention also provides a computer-readable storage medium storing instructions that, when executed on a computer, cause the computer to perform the method described above.

[0029] The above-described solution of the present invention has at least the following beneficial effects:

[0030] The above-described solution of the present invention obtains the height information of the launch pad; determines the height of the baffle plate based on the height information of the launch pad; obtains the rocket nozzle information; and determines the width of the baffle plate based on the rocket nozzle information. This allows the determination of the height and width of the baffle plate, ensuring that the baffle plate can block the heat flow generated during rocket launch and reduce the impact force on other equipment on the launch vehicle. Simultaneously, it ensures that the heat flow guided by the launch pad and the upward-sloping heat flow ejected from the guide channel smoothly merge, allowing them to mutually inhibit each other. This reduces the heat flow velocity and prevents the upward-sloping heat flow ejected from the guide channel from rolling inward and affecting the rocket. Attached Figure Description

[0031] Figure 1 This is a flowchart of a method for determining the parameters of a launch ship's deflector provided in an embodiment of the present invention;

[0032] Figure 2 This is an example of an impact heat flow velocity cloud map provided by an embodiment of the present invention through three-dimensional numerical simulation of Example 1;

[0033] Figure 3 This is an example of an impact heat flow velocity cloud map provided by an embodiment of the present invention through three-dimensional numerical simulation of Example 2;

[0034] Figure 4 A schematic diagram of the distribution structure of the baffle and the launch pad provided in the embodiments of the present invention;

[0035] Figure 5 A schematic diagram of the distribution structure of the baffle and nozzle provided in the embodiments of the present invention;

[0036] Figure 6 A block diagram of the launch ship baffle parameter determination device provided in the embodiments of the present invention;

[0037] Figure 7 A schematic diagram illustrating the merging effect of the transverse heat flow guided by the launch pad and the upwardly angled heat flow ejected from the guide channel, provided in an embodiment of the present invention.

[0038] The annotations in the attached figures are explained as follows:

[0039] 21. Baffle; 22. Launch pad; 23. Nozzle. Detailed Implementation

[0040] Exemplary embodiments of the invention will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the invention are shown in the drawings, it should be understood that the invention may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this invention will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.

[0041] like Figure 1As shown, an embodiment of the present invention proposes a method for determining the parameters of a launch ship's baffle, including:

[0042] Step 11: Obtain the altitude information of launch pad 22;

[0043] Step 12: Determine the height of the baffle 21 based on the height information of the launch pad 22;

[0044] Step 13: Obtain information about rocket nozzle 23;

[0045] Step 14: Determine the width of the deflector 21 based on the information from the rocket nozzle 23.

[0046] In this embodiment, by acquiring the height information of the launch pad 22; determining the height of the baffle 21 based on the height information of the launch pad 22; acquiring the information of the rocket nozzle 23; and determining the width of the baffle 21 based on the information of the rocket nozzle 23, the height and width of the baffle 21 can be determined, ensuring that the baffle 21 can block the heat flow generated during rocket launch and reduce the impact force on other equipment on the launch ship; at the same time, it ensures that the heat flow guided by the launch pad 22 and the upward-sloping heat flow ejected from the guide channel can smoothly merge, so that the two inhibit each other, reduce the heat flow velocity, and prevent the upward-sloping heat flow ejected from the guide channel from rolling inward and affecting the rocket.

[0047] In an optional embodiment of the present invention, step 11 includes:

[0048] Step 111: Obtain the height difference between the surface of launch pad 22 and the surface of launch vessel.

[0049] In this embodiment, after the launch pad 22 is built, the height of the launch pad 22 is obtained by measuring the height difference between the surface of the launch pad 22 and the surface of the launch ship.

[0050] In an optional embodiment of the present invention, step 12 includes:

[0051] Step 121: Based on the principle that the baffle does not obstruct the flow of the core area of ​​the gas tail flow: H>h, determine the height of the baffle 21;

[0052] Where H is the height of the baffle 21, and h is the height difference between the surface of the launch pad 22 and the surface of the launch ship.

[0053] In this embodiment, as the rocket's altitude increases, some of the heat flow will be affected by the launch pad 22 and flow laterally. It will then merge with the oblique heat flow ejected from the guide channel outlet. The lateral and oblique heat flows mutually inhibit each other, thereby suppressing the inward entrainment of the heat flow ejected from the guide channel and slowing down the lateral flow velocity of the heat flow. This is achieved by setting a baffle 21, with the height of the baffle 21 being less than or equal to the height of the launch pad 22. Figure 4 and Figure 7As shown, the baffle 21 can block the heat flow, reducing the impact of the heat flow on other equipment on the launch ship. At the same time, it can smoothly merge the lateral heat flow guided by the launch pad 22 with the oblique heat flow ejected from the guide channel. The two heat flows inhibit each other to avoid the heat flow from being rolled in and affecting the rocket, thus achieving simultaneous protection for other equipment on the launch ship and the rocket.

[0054] In an optional embodiment of the present invention, step 13 includes:

[0055] Step 131: Obtain the diameter of the rocket nozzle 23 and the distance between the two nozzles 23.

[0056] In this embodiment, the distance L between the centers of the two nozzles 23 on the side closest to other equipment on the launch ship, and the diameter D of the two nozzles 23 are obtained.

[0057] In an optional embodiment of the present invention, step 14 includes:

[0058] Step 141: Based on the principle of complete horizontal obstruction: W≥(D+L), determine the width of the baffle 21;

[0059] Where W is the width of the baffle 21, D is the diameter of the rocket nozzle 23, and L is the distance between the two nozzles 23.

[0060] In this embodiment, to reduce the impact of the heat flow on other equipment on the transmitter, a baffle 21 is needed to block the heat flow core area. The width of the baffle 21 needs to be greater than the width of the heat flow core area. Figure 5 As shown, the hot flow is ejected from the rocket nozzle 23. The width of the hot flow core region depends on the distance between the centers of the two nozzles 23 and the diameter of the nozzle 23. Therefore, the width of the baffle 21 needs to satisfy: W≥(D+L).

[0061] Where W-(D+L)<1m.

[0062] In an optional embodiment of the present invention, the above-described determining method further includes:

[0063] The height and width of the baffle 21 were verified by two-dimensional numerical simulation.

[0064] In this embodiment, the height of the launch pad 22, the diameter of the nozzle 23, the distance between the two nozzles 23, and the height and width of the baffle 21 are determined. By using three-dimensional numerical simulation to obtain velocity cloud maps around the baffle 21 at different rocket launch heights, the change in heat flow velocity under the blocking effect of the baffle 21 is obtained. This verifies whether the height and width of the baffle 21 can provide impact protection for other equipment on the launch ship, and obtains the verification results of whether the height and width of the baffle 21 are appropriate.

[0065] To verify the above results, FLUENT was used to perform a three-dimensional numerical simulation to obtain the velocity cloud map of the impact heat flow, thereby determining the blocking effect of the baffle 21 on the heat flow.

[0066] Example 1: The diameter of the nozzle 23 is set to 1.56m, the distance between the two nozzles 23 is 3.5m, the height of the launch pad 22 is 3.0m, the rocket launch height is set to 15.6m, the height of the baffle 21 is 3.0m, and the width of the baffle 21 is 6.0m.

[0067] like Figure 2 As shown, the core area of ​​the jet after rocket launch mainly travels along the extended surface of the guide channel. When the rocket height is 15.6m, the baffle 21 effectively blocks the flow of heat, reducing the heat flow velocity from 56m / s to 26m / s.

[0068] Example 2: The diameter of the nozzle 23 is set to 1.56m, the distance between the two nozzles 23 is 3.5m, the height of the launch pad 22 is 3.0m, the rocket launch height is set to 31.2m, the height of the baffle 21 is 3.0m, and the width of the baffle 21 is 6.0m.

[0069] like Figure 3 As shown, when the rocket height is 31.2m, under the action of the baffle 21, the heat flow velocity drops from 100m / s to 16m / s. At the same time, the lateral heat flow guided by the launch pad 22 and the upward heat flow ejected from the guide channel converge above the baffle 21. The two inhibit each other, reducing the heat flow velocity above the baffle 21 to 50m / s, effectively preventing the upward heat flow ejected from the guide channel from rolling inward and affecting the rocket.

[0070] Verification shows that the size of the baffle 21 is set according to the above determination method. The baffle 21 suppresses the lateral diffusion of heat flow to a certain extent, thereby providing a certain protection for other equipment on the launch ship. At the same time, it can make the lateral heat flow guided by the launch pad 22 and the upward heat flow ejected from the guide channel merge smoothly, so that the two inhibit each other, reduce the heat flow velocity, and prevent the upward heat flow ejected from the guide channel from rolling inward and affecting the rocket.

[0071] like Figure 4 and Figure 7 As shown, a baffle 21 is arranged to block the heat flow, reducing its impact on other equipment on the launch vehicle, based on the principle that the baffle should not obstruct the flow of the core area of ​​the exhaust gas. Simultaneously, it allows the lateral heat flow guided by the launch pad 22 to smoothly merge with the upward-sloping heat flow ejected from the guide channel, thus mutually inhibiting each other and reducing the heat flow velocity. This also prevents the upward-sloping heat flow ejected from the guide channel from rolling inwards and affecting the rocket. Figure 5As shown, a baffle plate 21 is arranged to completely block the core area of ​​the heat flow formed by the heat flow ejected from the two nozzles 23 along its width direction, based on the principle of complete horizontal blocking, thereby reducing the impact of the heat flow on other equipment on the launch ship.

[0072] like Figure 6 As shown, an embodiment of the present invention also provides a launch ship deflector parameter determination device 30, comprising:

[0073] The acquisition module 31 is used to acquire the altitude information of the launch pad 22 and the information of the rocket nozzle 23;

[0074] The processing module 32 is used to determine the height of the baffle 21 based on the height information of the launch pad 22, and to determine the width of the baffle 21 based on the information of the rocket nozzle 23.

[0075] Optionally, obtain the altitude information of launch pad 22, including:

[0076] Obtain the height difference between the surface of launch pad 22 and the surface of the launch ship.

[0077] Optionally, the height of the deflector 21 is determined based on the height information of the launch pad 22, including:

[0078] Based on the principle that the baffle does not obstruct the flow of the core area of ​​the gas tail flow: H≦h, the height of the baffle 21 is determined.

[0079] Where H is the height of the baffle 21, and h is the height difference between the surface of the launch pad 22 and the surface of the launch ship.

[0080] Optionally, obtain information about rocket nozzle 23, including:

[0081] Obtain the diameter of the rocket nozzle 23 and the distance between the two nozzles 23.

[0082] Optionally, the width of the deflector 21 is determined based on the information from the rocket nozzle 23, including:

[0083] Based on the principle of complete horizontal obstruction: W≧(D+L), determine the width of the baffle 21;

[0084] Where W is the width of the baffle 21, D is the diameter of the rocket nozzle 23, and L is the distance between the two nozzles 23.

[0085] Optionally, the aforementioned processing module 32 is also used for:

[0086] The height and width of the baffle 21 were verified by three-dimensional numerical simulation.

[0087] Optionally, the height and width of the baffle 21 can be verified through three-dimensional numerical simulation, including:

[0088] The height of launch pad 22, the diameter of nozzle 23, the distance between the two nozzles 23, and the height and width of baffle 21 are determined. By using three-dimensional numerical simulation, the velocity cloud map around the baffle is obtained when the rocket is launched at different heights. The change of heat flow velocity under the blocking effect of baffle 21 is obtained. The height and width of baffle 21 are verified to ensure that they can protect other equipment on the launch ship from impact. The verification results of whether the height and width of baffle 21 are appropriate are obtained.

[0089] It should be noted that this device is the same as the method described above. All implementations in the above method embodiments are applicable to the embodiments of this device and can achieve the same technical effect.

[0090] An embodiment of the present invention also provides a computing device, including: a processor and a memory storing a computer program, wherein the computer program, when executed by the processor, performs the method described in the above embodiments. All implementations in the above method embodiments are applicable to this embodiment and can achieve the same technical effect.

[0091] In this embodiment of the invention, a computer-readable storage medium is also provided, storing instructions that, when executed on a computer, cause the computer to perform the method described in the above embodiments. All implementations of the methods described in the above embodiments are applicable to this embodiment and can achieve the same technical effect.

[0092] Those skilled in the art will recognize that the units and algorithm steps of the various examples described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are implemented in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art can use different methods to implement the described functions for each specific application, but such implementations should not be considered beyond the scope of this invention.

[0093] Those skilled in the art will understand that, for the sake of convenience and brevity, the specific working processes of the systems, devices, and units described above can be referred to the corresponding processes in the foregoing method embodiments, and will not be repeated here.

[0094] In the embodiments provided by this invention, it should be understood that the disclosed apparatus and methods can be implemented in other ways. For example, the apparatus embodiments described above are merely illustrative. For instance, the division of units is only a logical functional division, and in actual implementation, there may be other division methods. For example, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Furthermore, the coupling or direct coupling or communication connection shown or discussed may be through some interfaces; the indirect coupling or communication connection between devices or units may be electrical, mechanical, or other forms.

[0095] The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the units can be selected to achieve the purpose of this embodiment according to actual needs.

[0096] In addition, the functional units in the various embodiments of the present invention can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit.

[0097] If the aforementioned functions are implemented as software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of this invention, essentially, or the part that contributes to the prior art, or a portion of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this invention. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, ROM, RAM, magnetic disks, or optical disks.

[0098] Furthermore, it should be noted that in the apparatus and method of the present invention, it is obvious that the components or steps can be decomposed and / or recombined. These decompositions and / or recombinations should be considered equivalent solutions of the present invention. Moreover, the steps performing the above-described series of processes can naturally be executed in the order described, but are not necessarily required to be executed in chronological order; some steps can be executed in parallel or independently of each other. Those skilled in the art will understand that all or any step or component of the method and apparatus of the present invention can be implemented in any computing device (including processors, storage media, etc.) or network of computing devices, in hardware, firmware, software, or a combination thereof. This is something that those skilled in the art can achieve by using their basic programming skills after reading the description of the present invention.

[0099] Therefore, the object of the present invention can also be achieved by running a program or a set of programs on any computing device. The computing device can be a known general-purpose device. Therefore, the object of the present invention can also be achieved simply by providing a program product containing program code implementing the method or apparatus. That is, such a program product also constitutes the present invention, and the storage medium storing such a program product also constitutes the present invention. Obviously, the storage medium can be any known storage medium or any storage medium developed in the future. It should also be noted that in the apparatus and method of the present invention, it is obvious that the components or steps can be decomposed and / or recombined. These decompositions and / or recombinations should be considered equivalent to the present invention. Furthermore, the steps performing the above series of processes can naturally be performed in the order described, but are not necessarily required to be performed in chronological order. Some steps can be performed in parallel or independently of each other.

[0100] The above description represents the preferred embodiments of the present invention. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A method for determining the parameters of a launch ship's baffle plate, characterized in that, The guide channel on the launch ship is a longitudinally arranged guide channel, and the method includes: Obtain the launch pad's altitude information; The height of the baffle is determined based on the height information of the launch pad; Obtain rocket nozzle information; The width of the deflector is determined based on the rocket nozzle information; Among these, obtaining the launch pad's altitude information includes: Obtain the height difference between the surface of the launch pad and the surface of the launch ship; Determining the height of the baffle based on the height information of the launch pad includes: Based on the principle that the baffle should not obstruct the flow of the core area of ​​the gas tail flow: H≦h, the height of the baffle is determined. Where H is the height of the baffle, and h is the height difference between the surface of the launch pad and the surface of the launch ship; This includes obtaining rocket nozzle information, including: Obtain the diameter of the rocket nozzles and the distance between the two nozzles; Determining the width of the deflector based on the rocket nozzle information includes: Based on the principle of complete horizontal obstruction: W≧(D+L), determine the width of the baffle. Where W-(D+L)<1m, W is the width of the baffle, D is the diameter of the rocket nozzle, and L is the distance between the two nozzles.

2. The method for determining the parameters of the launch vessel's baffle plate according to claim 1, characterized in that, Also includes: The height and width of the baffle were verified through three-dimensional numerical simulation.

3. The method for determining the parameters of the launch vessel's baffle plate according to claim 2, characterized in that, The height and width of the baffle were verified through three-dimensional numerical simulation, including: The launch pad height, nozzle diameter, distance between the two nozzles, and height and width of the baffle were determined. Three-dimensional numerical simulations were used to obtain velocity cloud maps around the baffle at different launch heights to obtain the changes in heat flow velocity under the obstruction of the baffle. The results were used to verify whether the height and width of the baffle could provide impact protection for other equipment on the launch ship and to obtain the verification results on whether the height and width of the baffle were appropriate.

4. A device for determining the parameters of a launch vessel's deflector, characterized in that, The flow channel on the launch vessel is a longitudinally arranged flow channel, and the device includes: The acquisition module is used to acquire launch pad height information and rocket nozzle information. The processing module is used to determine the height of the deflector based on the height information of the launch pad; and to determine the width of the deflector based on the rocket nozzle information. Among them, obtaining the height information of the launch pad includes: obtaining the height difference between the surface of the launch pad and the surface of the launch ship; The determination of the baffle height based on the launch pad height information includes: determining the baffle height based on the principle that the baffle does not obstruct the flow of the core area of ​​the gas wake: H≦h; where H is the height of the baffle and h is the height difference between the surface of the launch pad and the surface of the launch vessel. Among these, obtaining rocket nozzle information includes: obtaining the diameter of the rocket nozzle and the distance between the two nozzles; The determination of the baffle width based on the rocket nozzle information includes: determining the baffle width according to the principle of complete horizontal obstruction: W≧(D+L); W-(D+L)<1m, where W is the width of the baffle, D is the diameter of the rocket nozzle, and L is the distance between the two nozzles.

5. A computing device, characterized in that, include: A processor, a memory storing a computer program, wherein the computer program, when executed by the processor, performs the method as described in any one of claims 1 to 3.

6. A computer-readable storage medium, characterized in that, The system stores instructions that, when executed on a computer, cause the computer to perform the method as described in any one of claims 1 to 3.

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