Liquid rocket test run launching integrated launching pad

Abstract

The invention provides a liquid rocket test run launching integrated launching pad, and belongs to the technical field of carrier rocket launching devices.The liquid rocket test run launching integrated launching pad comprises a launching pad body, a one-way fluid director, a switching device and a lifting device.In the test run state, a lifting platform of a lifter is located below the table top of a launching platform; and in a launching state, a lifting platform of the lifter extends out of the table top of the launching platform and is in contact with the L-shaped split flange plate. According to the liquid rocket test run launching integrated launching pad, a traditional test run platform and a launching pad of a launching site are integrally designed, and on the premise that the test function is met and the flight mission risk is reduced, the construction cost of the test run platform can be greatly saved, the transportation and transfer links are reduced, the transportation cost is saved, and the total launching period is shortened. Due to the overall modular design of the integrated launching pad, the launching pad has migration maneuverability and can meet the task requirements of different launching sites, the launching tasks of multiple sites are achieved through one set of equipment, and cost is saved.

Description

Technical Field

[0001] The present invention belongs to the technical field of carrier rocket launching devices, and more specifically, relates to an integrated launch platform for testing and launching liquid rockets. Background Art

[0002] With the development of commercial space launch vehicle technology, the demand for low-cost space access capabilities has become increasingly urgent. Liquid rockets have the advantages of high specific impulse, high thrust-to-weight ratio, low fuel cost, and reusability, and have become the main research product of various commercial aerospace companies.

[0003] In the traditional liquid rocket development process, before executing a flight mission, the power system will be tested on a professional test bench to verify the correct matching of the rocket body systems and the engine to reduce flight risks. After the power system test, the rocket body returns to the final assembly plant for inspection and assembly, and then transported to the launch site to perform the flight mission. This process requires the construction of an expensive test bench, and the product needs to be transported and transferred several times, which not only increases the cost and cycle, but also increases the risk of damage to the rocket body during transportation and transfer.

[0004] Therefore, it is of great significance to develop a launch pad that integrates a test bench and a launch pad. Summary of the invention

[0005] The purpose of the present invention is to provide an integrated launch pad for liquid rocket test and launch, which integrates the traditional test pad and the launch pad of the launch site into an integrated design. While meeting the test functions and reducing the risks of flight missions, it can greatly save the construction funds of the test pad, reduce transportation and transfer links, and shorten the total launch cycle.

[0006] To achieve the above-mentioned purpose, the present invention provides a liquid rocket test launch integrated launch platform, comprising:

[0007] A launching platform, comprising a launching platform and a plurality of columns for supporting the launching platform; a mounting hole is provided at the center of the launching platform;

[0008] A one-way deflector, comprising a deflector body and baffles connected to both sides of the deflector body, wherein the deflector body is provided with a one-way arcuate deflector surface; baffles on both sides are arranged on both sides of the one-way arcuate deflector surface; the one-way arcuate deflector surface is located directly below the mounting hole; a switching device, comprising a plurality of L-shaped split flanges evenly arranged along the periphery of the mounting hole; the L-shaped split flange comprises a horizontal plate and a vertical plate connected to each other, the horizontal plate is detachably connected to the launch platform, and the vertical plate is used to connect the rocket body; and,

[0009] A lifting device is used to adjust the height of at least part of the L-shaped split flange in the launching state.

[0010] Furthermore, the launching platform is provided with at least two symmetrical holes and slots, the lifting device is an elevator, each of the holes and slots is provided with the elevator, and each of the elevators is provided under the horizontal plate; in the test state, the lifting platform of the elevator is located under the table top of the launching platform; in the launching state, the lifting platform of the elevator extends out above the table top of the launching platform and contacts with the L-shaped split flange.

[0011] Furthermore, the distance between the top of the one-way deflector and the launching platform is not less than 1 m.

[0012] Furthermore, the one-way deflector has a height of 7-8m and a width of 7-8m; the baffle has a height of 1500-2000mm.

[0013] Furthermore, the transverse plate is connected to the launching platform via bolts.

[0014] Furthermore, the vertical plate is connected to the arrow body via bolts.

[0015] Furthermore, the launching platform includes a first part and a second part which are symmetrically arranged.

[0016] Furthermore, the first part and the second part are connected by bolts.

[0017] Furthermore, it also includes a plurality of cross beams, and both ends of each cross beam are connected to the columns on both sides thereof.

[0018] Furthermore, the lower end of each column is connected to the ground via bolts, and the upper end is connected to the launching platform via bolts.

[0019] Furthermore, the one-way arc-shaped guide surface includes an impact surface, a transition surface and an extension surface which are connected in sequence from top to bottom.

[0020] Compared with the prior art, the present invention has the following technical effects:

[0021] The integrated launch platform for testing and launching of a liquid rocket of the present invention is provided with a one-way guide directly below the launch platform. The baffles on both sides of the one-way guide can ensure that the gas flow can only be flushed and drained along the one-way arc guide surface, effectively controlling the temperature environment of the other three surfaces, ensuring that the long-term ablation of the power system test will not cause damage to the ground facilities, and can meet the high-temperature gas flow drainage requirements of the engine during the power system test phase; and the adapter device detachably connected to the launch platform and the rocket body can bear both tension and pressure, ensuring that the rocket body does not leave the platform during the test, and can meet the requirements of the rocket body fixation during the power system test phase; and in the launch phase, the lifting device can level the rocket body to meet the requirements of the rocket body support and vertical adjustment during the flight mission. The integrated launch platform for testing and launching of a liquid rocket of the present invention integrates the traditional test platform and the launch platform of the launch site. On the premise of meeting the test function and reducing the risk of the flight mission, it can avoid the back and forth transportation of the rocket body caused by the different locations of the power system test platform and the launch site, greatly saving the construction funds of the test platform, reducing the transportation and transfer links, saving transportation costs and shortening the total launch cycle.

[0022] The liquid rocket test launch integrated launch platform of the present invention adopts a launch platform and a one-way deflector made of modular steel structure, which can avoid the construction of large-scale special infrastructure such as reinforced concrete test platforms and guide troughs, and greatly reduce construction costs and construction periods.

[0023] The integrated launch pad for test launch of a liquid rocket of the present invention adopts a modular launch pad and a one-way deflector. This overall modular design enables the launch pad to have mobility and adapt to the mission requirements of different launch sites. One set of equipment can solve launch missions in multiple locations, saving costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0025] Figure 1 A schematic diagram of the overall structure of a liquid rocket test launch integrated launch platform provided by an embodiment of the present invention;

[0026] Figure 2 A schematic diagram of the structure of a launch platform provided by an embodiment of the present invention;

[0027] Figure 3 A schematic structural diagram of another launch platform provided in an embodiment of the present invention.

[0028] Among them, the reference numerals in the figure are:

[0029] 1. launching platform, 2. one-way deflector, 3. adapter, 4. elevator, 11. launching platform, 12. column, 13. beam, 201. deflector body, 202. baffle, 203. one-way arc-shaped deflector surface, 301. L-shaped split flange, 1101. mounting hole, 1102. hole groove, 1103. first part, 1104. second part. DETAILED DESCRIPTION

[0030] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0031] In the present invention, the term "and / or" describes the association relationship of associated objects, indicating that there may be three relationships. For example, A and / or B can represent: A exists alone, A and B exist at the same time, and B exists alone. A and B can be singular or plural. The character " / " generally indicates that the associated objects before and after are in an "or" relationship.

[0032] It should be noted that when an element is referred to as being "fixed to" or "disposed on" another element, it can be directly on the other element or indirectly on the other element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or indirectly connected to the other element.

[0033] It should be understood that the orientation or position relationship indicated by terms such as "length", "up", "down", "vertical", "horizontal", "top", "bottom", "inside" and "outside" are based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0034] The terms used in the embodiments of the present invention are only for the purpose of describing specific embodiments, and are not intended to limit the present invention. The singular forms "a", "said" and "the" used in the embodiments of the present invention and the appended claims are also intended to include plural forms, unless the context clearly indicates other meanings.

[0035] The terms "first" and "second" are used only for descriptive purposes to distinguish objects such as substances from each other, and should not be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. For example, without departing from the scope of the embodiments of the present invention, the first XX may also be referred to as the second XX, and similarly, the second XX may also be referred to as the first XX. Thus, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features.

[0036] See also Figure 1-Figure 3 Now, a liquid rocket test and launch integrated launch platform provided in an embodiment of the present invention is described.

[0037] In one embodiment of the present invention, a liquid rocket test launch integrated launch platform of the embodiment of the present invention includes a launch platform 1, a one-way deflector 2, a switching device 3 and a lifting device. Among them, the launch pad 1 includes a launch platform 11 and a plurality of columns 12 for supporting the launch platform 11; a mounting hole 1101 is provided in the center of the launch platform 11, and the mounting hole 1101 is used to install a liquid rocket to be tested or launched; the one-way deflector 2 includes a deflector body 201 and baffles 202 connected on both sides of the deflector body 201, and the deflector body 201 is provided with a one-way arc-shaped deflector surface 203; the baffles 202 on both sides are arranged on both sides of the one-way arc-shaped deflector surface 203; the one-way arc-shaped deflector surface 203 is located directly below the mounting hole 1101 to effectively drain the high-temperature combustion gas flow at the tail of the rocket body; the adapter 3 includes a plurality of L-shaped split flanges 301 evenly arranged along the periphery of the mounting hole 1101; the L-shaped split flange 301 includes a horizontal plate and a vertical plate connected to each other, the horizontal plate is detachably connected to the launch platform 11, and the vertical plate is used to connect the rocket body. The lifting device is used to adjust the height of at least part of the L-shaped split flange 301 in the launching state.

[0038] In a specific embodiment, the launch platform 11 is provided with at least two symmetrical holes 1102, and the lifting device is an elevator 4. An elevator 4 is provided in each hole 1102, and each elevator 4 is provided below the horizontal plate of the L-shaped split flange 301. In the test state, the lifting platform of the elevator 4 is located below the table top of the launch platform 11. At this time, the L-shaped split flange 301 is fixedly connected to the launch platform 11 through its horizontal plate, and the elevator 4 is not enabled; in the launch state, the connecting fixings between the horizontal plate of the L-shaped split flange 301 and the launch platform 11 are removed, so that the L-shaped split flange 301 is only placed on the launch platform 11 but no longer fixedly connected, and then the elevator 4 is enabled, so that the lifting platform of the elevator 4 extends above the table top of the launch platform 11 and contacts the L-shaped split flange 301, so that the height of the L-shaped split flange 301 can be adjusted.

[0039] In a specific embodiment, the lower side of the launch platform 11 is connected to four columns 12, the adapter 3 includes eight L-shaped split flanges 301 evenly arranged around the mounting hole 1101, and the launch platform 11 is provided with four symmetrical holes 1102, such as Figure 1-3 When performing the power system test, the vertical plates of the eight L-shaped split flanges 301 and the rocket body can be fixed by bolts, and the horizontal plates of the eight L-shaped split flanges 301 and the launch platform 11 can also be fixed by bolts. The eight L-shaped split flanges 301 and the bolts have sufficient strength to ensure that the rocket body will not separate from the launch platform 11 during the test. When performing a flight mission (i.e., launching), in order to prevent the rocket body from drifting during takeoff, four of the symmetrical L-shaped split flanges 301 are removed, and a lift 4 is provided at the bottom of the horizontal plate of the remaining four symmetrical L-shaped split flanges 301, that is, the lift is hidden in the launch platform 11, and by adjusting the height of the lift platform of the lift 4, the lift platform of the lift 4 can be extended above the table of the launch platform 11, that is, the upper end of the lift platform of the lift 4 can be extended outside the hole 1102, so that the L-shaped split flange 301 placed above the lift 4 and then the rocket body placed on the L-shaped split flange 301 can be leveled to meet the adjustment requirements of the verticality of the rocket body during the flight mission. The lift 4 can adopt any existing lifting device with a telescopic lifting rod and a lifting platform connected to the end of the telescopic lifting rod.

[0040] The one-way deflector 2 of the embodiment of the present invention needs to meet the requirements of long-term gas flow ablation during power system test and reduce the impact of gas flow on surrounding facilities, and also meet the requirements of smooth gas flow drainage during launch. The deflector of traditional launches generally adopts double-sided or conical deflector surfaces, which is conducive to the balanced lateral force of the rocket body during takeoff, but the gas flow is scattered, causing great scouring and ablation effects on surrounding facilities. The embodiment of the present invention takes into account that ground facilities need to continue to work during power system test, and minimizes the impact of high-temperature gas flow on ground facilities around the deflector. Therefore, the deflector of the launch pad in the embodiment of the present invention adopts a one-way deflector 2 with a single-sided deflector surface. In addition, baffles 202 are provided on both sides of the one-way guide vane 2 of the embodiment of the present invention, so that the discharge direction of the high-temperature gas flow is limited to the one-way arc guide surface 203 between the baffles 202 on both sides, ensuring that the gas flow is flushed and discharged from only one side (i.e., the one-way arc guide surface 203), effectively controlling the temperature environment of the other three sides, and ensuring that long-term ablation during the power system test will not cause damage to the ground facilities, so as not to affect the test.

[0041] Although the deflector of the launch pad in the embodiment of the present invention adopts a unidirectional deflector 2 with a single-sided guide surface, the on-rocket control system configured on the rocket body can effectively overcome the takeoff lateral force generated by the single-sided guide, so that the unidirectional deflector 2 can also meet the instantaneous gas flow diversion requirements when the rocket body is launched.

[0042] A liquid rocket test launch integrated launch platform in an embodiment of the present invention is provided with a one-way deflector 2 directly below the launch platform 11. The baffles 202 on both sides of the one-way deflector 2 can ensure that the gas flow can only be flushed and drained along the one-way arc-shaped guide surface 203, effectively controlling the temperature environment of the other three surfaces, ensuring that long-term ablation during the power system test will not cause damage to ground facilities, and can meet the high-temperature gas flow drainage requirements of the engine during the power system test stage; and the adapter 3 detachably connected to the launch platform 11 and the rocket body can bear both tension and pressure, ensuring that the rocket body does not leave the platform during the test, and can meet the need for fixing the rocket body during the power system test stage; and in the launch stage, the elevator 4 arranged in the launch platform 11 can level the rocket body to meet the requirements of rocket body support and vertical adjustment during the flight mission. A liquid rocket test and launch integrated launch platform in an embodiment of the present invention integrates the traditional test platform and the launch platform of the launch site into an integrated design. Under the premise of meeting the test functions and reducing the flight mission risks, it can avoid the back and forth transportation of the rocket body caused by the power system test platform and the launch site being in different locations, thereby greatly saving the construction funds of the test platform, reducing the transportation and transfer links, saving transportation costs and shortening the total launch cycle.

[0043] Furthermore, in this embodiment, the launch platform 1 is elevated so that the distance between the top of the one-way deflector 2 and the launch platform 11 is not less than 1m, so as to reduce the degree of ablation of the guide surface of the one-way deflector 2 by the high-temperature gas flow at the tail of the rocket body during the long-term test run. Specifically, the height of the one-way deflector 2 can be set to 7-8m. When the height of the one-way deflector 2 is 8m, the height of the launch platform 11 can be 10m. Under the condition of comprehensively considering the cost of controlling the launch platform 1, the risk of personnel climbing, and reducing the difficulty of the hoisting operation of the rocket body onto the platform, it is ensured that the launch platform 1 can meet both the load requirements and the drainage requirements of the high-temperature gas flow.

[0044] In addition, in this embodiment, the width of the one-way deflector 2 can be widened and the baffle of the one-way deflector 2 can be raised to better ensure that the gas flow is flushed and drained only from one side, better control the temperature environment of the other three sides, and better ensure that long-term ablation during the power system test will not cause damage to ground facilities. Generally, the width of the deflector is 4-6m, and the height of the baffle is 300-500mm, while the width of the one-way deflector 2 of this embodiment is widened to 7-8m, and the height of the baffle 202 is raised to 1500-2000mm. The height of the baffle 202 refers to the height of the upper side of the baffle 202 at each location exceeding the edge of the one-way arc guide surface 203.

[0045] Furthermore, the launch platform 11 of the embodiment of the present invention includes a first part 1103 and a second part 1104 that are symmetrically arranged. Figure 3As shown, the launch platform 11 is composed of two halves, and the launch platform 11 designed in such a block manner is more convenient for transportation or maintenance. Specifically, the first part 1103 and the second part 1104 can overlap each other through the stepped interface groove on each side, and then be connected into one by bolts, which is simple and convenient to assemble.

[0046] Furthermore, the launch platform 1 of the embodiment of the present invention further comprises a plurality of beams 13, and both ends of each beam 13 are connected to the columns 12 on both sides thereof. Figure 1 By providing the crossbeam 13, the stability of the overall structure of the launch platform 1 can be enhanced, so that it has better tensile or compressive bearing performance.

[0047] In a specific embodiment, the launch pad 1 is assembled in a modular manner. The main body of the launch platform 11 is a plate-welded box-type structure, and the left and right halves are connected by bolts. The columns 12 and the crossbeams 13 are both circular steel pipes. The lower ends of the columns 12 are connected and fixed to the ground by bolts, and the upper ends are connected and fixed to the launch platform 11 by bolts. The overall mass of the launch pad 1 is 500 tons, which can withstand a tensile force of 300 tons to ensure that the rocket ground ignition test does not leave the ground. The main body of the one-way deflector 2 is a steel structure welded part, and the fire-facing surface is a one-way arc-shaped guide surface 203. The one-way arc-shaped guide surface 203 includes an impact surface, a transition surface and an extension surface connected in sequence from top to bottom. The surface of the one-way arc-shaped guide surface 203 is coated with ablation-resistant material, which can guide the high-temperature gas flow during rocket ignition in a fixed direction to avoid rewinding and damaging the rocket body.

[0048] The size design of the one-way deflector 2 mainly considers the impact surface pressure and heat flux density. Based on the empirical formula, the impact angle α is 30° to 45°, and the impact height H c (0.6~2)d e , the turning radius R is (0.7~2)d e , the width B of the one-way deflector 2 c (1.2~2)d e , d e The diameter of the rocket engine nozzle is used to form the baseline size, and then the specific structural parameters of the one-way guide 2 are obtained by iterating the gas flow simulation surface size according to the target pressure and heat flux density.

[0049] The launching platform 1 and the one-way deflector 2 of the integrated launching platform for testing and launching a liquid rocket in an embodiment of the present invention can be made of steel structural parts, avoiding the construction of large-scale special infrastructure such as reinforced concrete test benches and guide troughs, thereby greatly reducing construction costs and construction periods.

[0050] An integrated launch platform for test launch of a liquid rocket in an embodiment of the present invention adopts a modular launch platform 1 and a one-way deflector 2. This overall modular design enables the integrated launch platform to have migration mobility and can adapt to the mission requirements of different launch sites. One set of equipment can solve launch missions in multiple locations, saving costs.

[0051] A liquid rocket test and launch integrated launch platform in an embodiment of the present invention can not only conduct a power system test before liquid rocket launch, verify the correctness of the matching of each system, and reduce the risk of flight missions, but also meet the requirements for support and vertical adjustment of the rocket body before flight ignition.

[0052] The above embodiments only express several implementation methods of the present invention, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the present invention. It should be pointed out that, for a person of ordinary skill in the art, several modifications and improvements can be made without departing from the concept of the present invention, and these all belong to the protection scope of the present invention. Therefore, the protection scope of the present invention patent shall be subject to the attached claims.

Claims

1. A liquid rocket test launch integrated launch platform, characterized in that: include: A launching platform, comprising a launching platform and a plurality of columns for supporting the launching platform; a mounting hole is provided at the center of the launching platform; A one-way flow guide, comprising a flow guide body and baffles connected to both sides of the flow guide body, wherein the flow guide body is provided with a one-way arcuate flow guide surface; the baffles on both sides are respectively arranged on both sides of the one-way arcuate flow guide surface; the one-way arcuate flow guide surface is located directly below the mounting hole; A transfer device, comprising a plurality of L-shaped split flanges evenly arranged along the periphery of the mounting hole; the L-shaped split flanges comprising a horizontal plate and a vertical plate connected to each other, the horizontal plate being detachably connected to the launch platform, and the vertical plate being used to connect to the rocket body; and, A lifting device is used to adjust the height of at least part of the L-shaped split flange in the launching state.

2. The liquid rocket test launch integrated launch platform according to claim 1, characterized in that: The launch platform is provided with at least two symmetrical holes and slots, the lifting device is a lift, each hole and slot is provided with the lift, and each lift is provided below the horizontal plate; in the test state, the lifting platform of the lift is located below the table surface of the launch platform; In the launching state, the lifting platform of the lifting machine extends above the table surface of the launching platform and contacts with the L-shaped split flange.

3. The liquid rocket test launch integrated launch platform as claimed in claim 2, characterized in that: The distance between the top of the one-way deflector and the launching platform is not less than 1m; and / or the height of the one-way deflector is 7-8m, and the width is 7-8m; the height of the baffle is 1500-2000mm.

4. The liquid rocket test launch integrated launch platform according to claim 1, characterized in that: The transverse plate is connected to the launching platform via bolts.

5. The liquid rocket test launch integrated launch platform according to claim 1, characterized in that: The vertical plate is connected to the arrow body through bolts.

6. The liquid rocket test launch integrated launch platform according to claim 1, characterized in that: The launching platform comprises a first part and a second part which are symmetrically arranged.

7. The liquid rocket test launch integrated launch platform according to claim 6, characterized in that: The first part and the second part are connected by bolts.

8. The liquid rocket test launch integrated launch platform according to claim 1, characterized in that: It also includes a plurality of cross beams, and both ends of each cross beam are connected to the columns on both sides thereof.

9. The liquid rocket test launch integrated launch platform according to claim 1, characterized in that: The lower end of each column is connected to the ground through bolts, and the upper end is connected to the launching platform through bolts.

10. A liquid rocket test launch integrated launch platform as claimed in any one of claims 1 to 9, characterized in that: The one-way arc-shaped guide surface comprises an impact surface, a transition surface and an extension surface which are connected in sequence from top to bottom.

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