Installation tooling and installation method for parallel rocket engine

Abstract

The present invention discloses an installation tool and installation method for a parallel rocket engine, which solves the problem that the parallel rocket engine is difficult to place stably, resulting in difficulty in accurate docking and installation with the engine docking frame. Specifically, it includes a plurality of inclined pads and a horizontally arranged base plate assembly, the number of which is the same as the number of thrust chambers of the parallel rocket engine to be installed and corresponds one to one; the plurality of inclined pads are respectively distributed above the base plate assembly, the bottom surface of each inclined pad is parallel to the base plate assembly, and the top surface is an inclined surface; a plurality of spring tightening assemblies are evenly distributed between each inclined pad and the base plate assembly; the spring tightening assembly includes a hollow screw, a hollow nut and a spring; one end of the hollow screw is fixedly mounted on the base plate assembly, and the other end is vertically upward; the hollow nut is threadedly connected to the hollow screw, and its upper end is used to tighten the inclined pad; the spring is located in the hollow screw and the hollow nut, one end of which abuts the base plate assembly, and the other end abuts the corresponding inclined pad.

Description

Technical Field

[0001] The invention relates to the installation of a rocket engine, and in particular to an installation tool and an installation method for a parallel rocket engine. Background Art

[0002] In order to ensure the stability of the rocket engine during flight and the requirements for attitude adjustment, multiple engines are generally used in parallel, that is, multiple rocket engines are installed in parallel on the same rack, and the tail of the thrust chamber of each rocket engine is installed in an outward tilted manner. However, this will cause a certain angle between the bottom end surface of the thrust chamber of each engine and the horizontal plane, which makes it difficult for the entire parallel rocket engine to be placed stably, and even more difficult to transport it smoothly to the test bench and accurately dock it with the engine docking frame. Therefore, when placing and docking the parallel rocket engines, an inclined pad is generally set at the lower end of the thrust chamber of each engine, and a soft material such as rubber is laid on the surface of the inclined pad. Then, the thrust chamber of the engine is placed on the soft material to support the thrust chamber of the engine, so that the entire parallel rocket engine can be stably placed on the transport vehicle, and then it is stably transported to the rocket test bench, and the rack of the parallel rocket engine is docked with the engine docking frame above it.

[0003] However, during actual docking and installation, due to the differences in the dimensions of the thrust chambers of each engine, it is difficult for each inclined pad to ensure that all parallel engines can be placed stably. This, on the one hand, causes unstable transportation of the parallel rocket engine. On the other hand, when transported to the bottom of the engine docking frame, it is difficult to accurately dock and install the frame of the parallel rocket engine with the engine docking frame. During the docking and installation process, the entire parallel rocket engine needs to be continuously adjusted. Due to the large weight of the parallel rocket engine, the bottom of the thrust chamber of the rocket engine is easily squeezed and deformed during the adjustment process, and even causes deformation of the frame. Summary of the Invention

[0004] The purpose of the present invention is to provide an installation tool and installation method for a parallel rocket engine, so as to solve the technical problem that the existing parallel rocket engine is difficult to place stably, resulting in the parallel rocket engine frame being difficult to accurately dock and install with the engine docking frame above it during docking installation, causing the bottom of the thrust chamber and even the frame to be often squeezed and deformed.

[0005] In order to achieve the above-mentioned object, the present invention provides a parallel rocket engine installation tool, comprising a plurality of inclined pads, the number of which is the same as the number of thrust chambers of the parallel rocket engine to be installed and corresponding to each other, and the special feature of the tool is that it also includes a base plate assembly;

[0006] The base plate assembly is arranged horizontally;

[0007] The plurality of inclined pads are respectively distributed above the base plate assembly, the bottom surface of each inclined pad is parallel to the base plate assembly, and the top surface is an inclined surface, which is used to contact the bottom end of the corresponding thrust chamber;

[0008] A plurality of spring tightening assemblies are evenly distributed between each of the inclined pads and the bottom plate assembly;

[0009] The spring tightening assembly includes a hollow screw, a hollow nut and a spring; one end of the hollow screw is fixedly mounted on the base plate assembly, and the other end is vertically upward; the hollow nut is sleeved on the hollow screw and threadedly connected to it, and the upper end of the hollow nut is used to tighten the corresponding inclined pad; the spring is located in the center hole of the hollow screw and the hollow nut, one end of which abuts against the base plate assembly, and the other end abuts against the corresponding inclined pad.

[0010] The above structural design can enable the parallel rocket engine to be installed to level itself under the interaction of its own gravity and the spring force, and finally tighten it, thereby improving the stability of the parallel rocket engine to be installed during placement and transportation, and thereby improving the accuracy of docking between the parallel rocket engine to be installed and the engine docking frame, and avoiding the bottom of the thrust chamber and the frame from being squeezed and deformed during adjustment due to misalignment.

[0011] Furthermore, in order to further improve the accuracy of docking between the frame and the engine docking frame, the present invention makes the following structural improvements:

[0012] Also included are guide rails arranged vertically;

[0013] The upper end of the guide rail is detachably connected to the external engine docking frame, and the lower end thereof is vertically downward, used to guide the docking installation path for the rack to be installed with the parallel rocket engine, and the rack is connected above the thrust chamber.

[0014] Furthermore, in order to facilitate fine-tuning of the parallel rocket engine to be installed, the present invention makes the following structural improvements:

[0015] The base plate assembly includes a base plate and a plurality of upper base plates;

[0016] The chassis is arranged horizontally;

[0017] The number of the upper base plates is the same as the number of the inclined pads and corresponds one to one;

[0018] The upper base plate is arranged parallel to the bottom plate and is detachably connected to the bottom plate; a plurality of rolling balls are evenly arranged between each upper base plate and the bottom plate;

[0019] One end of the hollow screw is fixedly mounted on the upper base plate.

[0020] Furthermore, in order to improve the smoothness of the rolling of the ball and prevent the ball from running around, the present invention has made the following structural improvements:

[0021] The upper surface of the chassis is provided with a plurality of arc-shaped grooves corresponding to the respective rolling balls and matching each other;

[0022] Each of the rolling balls is respectively arranged in a corresponding arc-shaped groove.

[0023] Furthermore, in order to facilitate the connection between the upper base plate and the chassis, the present invention makes the following structural improvements:

[0024] The chassis includes a lower base plate and a connecting plate;

[0025] The lower base plate is arranged horizontally;

[0026] The connecting plate is vertically connected to the lower base plate;

[0027] The upper base plate is arranged parallel to the lower base plate and is detachably connected to the connecting plate;

[0028] The rolling ball is arranged between the lower base plate and the upper base plate.

[0029] Furthermore, the upper base plate is detachably connected to the connecting plate via connecting bolts;

[0030] The connecting plate is provided with a first threaded hole;

[0031] The side surface of the upper base plate is provided with a second threaded hole corresponding to the first threaded hole;

[0032] The connecting bolt is inserted into the first threaded hole and the second threaded hole.

[0033] Furthermore, the hollow nut includes a nut body and a tightening ring;

[0034] The nut body is sleeved on the hollow screw and is threadedly connected to the hollow screw;

[0035] The tightening ring is sleeved on the outside of the spring, the lower end of the tightening ring is connected to the upper end of the nut body, and the upper end of the tightening ring is used to tighten the corresponding inclined pad.

[0036] The present invention also provides a method for installing a parallel rocket engine, which is based on the above-mentioned parallel rocket engine installation tooling, and is special in that it includes the following steps:

[0037] Step 1: Rotate the hollow nut in each spring tightening assembly to the lower end of the hollow screw, so that the spring is naturally released, and the top of the spring extends out of the hollow screw and the upper end of the hollow nut;

[0038] Step 2: Place a corresponding inclined pad on the top of each spring, with the inclined surface of the inclined pad facing upward and its inclination direction matching the inclination direction of the bottom end of each thrust chamber on the parallel rocket engine to be installed;

[0039] Step 3: Place the parallel rocket engine to be installed on the inclined pad so that the bottom end of each thrust chamber contacts the inclined surface of the corresponding inclined pad;

[0040] Step 4: After the parallel rocket engine to be installed is self-leveled under the action of its own gravity and the elastic force of the spring until it is stable, rotate each hollow nut upward so that its upper end contacts the bottom surface of the inclined pad;

[0041] Step 5: Transport the base plate assembly, tilt pad, spring tightening assembly, and the parallel rocket engine to be installed to the bottom of the engine docking frame;

[0042] Step 6: Lift the base plate assembly, the tilting pad, the spring tightening assembly, and the parallel rocket engine to be installed upwards, so that the frame on which the parallel rocket engine to be installed is docked with the engine docking frame;

[0043] Step 7: After the frame and the engine docking frame are installed, the bottom plate assembly, the inclined pad and the spring tightening assembly are removed.

[0044] Furthermore, step 6 specifically includes:

[0045] Step 6.1, connect the upper end of the guide rail to the engine docking frame, and make the lower end correspond to the position of the frame;

[0046] Step 6.2: Lift the base plate assembly, tilting pad, spring tightening assembly, and the parallel rocket engine to be installed upward along the guide rails, so that the frame docks with the engine docking frame;

[0047] Step 7 specifically includes: after the frame and the engine docking frame are installed, the bottom plate assembly, the inclined pad, the spring tightening assembly and the guide rail are removed.

[0048] Furthermore, step 1 also includes the step of connecting the upper base plate, specifically including: connecting the upper base plate in the base plate assembly to the chassis;

[0049] Then step 6 specifically includes:

[0050] Step 6.1: Connect the upper end of the guide rail to the engine docking frame, then:

[0051] If the lower end of the guide rail is misaligned with the rack on which the parallel rocket engine is to be installed, proceed to step 6.2;

[0052] If the lower end of the guide rail corresponds to the position of the rack where the parallel rocket engine is to be installed, proceed to step 6.3;

[0053] Step 6.2: Disconnect the upper base plate from the chassis, fine-tune the upper base plate, and move the upper base plate on the rolling ball below it so that the rack and the guide rail are aligned, and then proceed to step 6.3;

[0054] Step 6.3: Lift the base plate assembly, the inclined pad, the spring tightening assembly, and the parallel rocket engine to be installed upward along the guide rail until the frame docks with the engine docking frame.

[0055] Beneficial effects of the present invention:

[0056] 1. The installation tool of the parallel rocket engine of the present invention is provided with a base plate assembly below the inclined pad, and a spring tightening assembly is provided between the inclined pad and the base plate assembly; when installing the rocket engine, the hollow nut in the spring assembly is rotated to the lower end of the hollow screw to leak out the spring, so that the inclined pad and the rocket engine above the inclined pad can self-level between their own gravity and the spring elastic force to eliminate the size difference between each thrust chamber, and then the hollow nut is rotated upward until it tightens the inclined pad, which can improve the stability of the placement of the rocket engine, and then the rocket engine can be smoothly transported to the bottom of the engine docking frame, thereby improving the accuracy of the docking between the frame and the engine docking frame, and reducing the probability of the engine thrust chamber or frame being squeezed and deformed.

[0057] 2. Since the rocket engine frame is too far away from the engine docking frame, the rocket engine is prone to shaking during the ascent process. Therefore, the present invention provides a guide rail under the engine docking frame so that the rocket engine frame can rise along the guide rail. The guide rail can prevent the rocket engine from shaking, improve the stability of the rocket engine during the ascent process, and thereby improve the accuracy of the docking installation between the frame and the engine docking frame.

[0058] 3. The upper base plate and the chassis of the present invention are detachably connected. Before the rocket engine is transported, the upper base plate and the chassis can be connected to each other to prevent the upper base plate from moving on the rolling ball. When the rocket engine is transported to the bottom of the engine docking frame, the connection between the upper base plate and the chassis can be disconnected, and the upper base plate can be fine-tuned to improve the accuracy of the docking between the frame and the engine docking frame.

[0059] 4. The base plate assembly of the present invention is provided with a chassis and an upper base plate, and a rolling ball is provided between the chassis and the upper base plate. When the frame of the rocket engine is misaligned with the guide rail, the upper base plate is fine-tuned, and the rolling ball can make the adjustment of the upper base plate easier.

[0060] 5. The present invention also provides arc-shaped grooves on the chassis corresponding to each ball. The balls are arranged in the arc-shaped grooves. On the one hand, it can prevent the balls from rolling randomly and causing imbalance of the upper base plate. On the other hand, it can also improve the smoothness of the balls rolling when fine-tuning the upper base plate, making the adjustment of the upper base plate easier. BRIEF DESCRIPTION OF THE DRAWINGS

[0061] Figure 1 is a schematic structural diagram of a parallel rocket engine to be installed in an embodiment of the present invention;

[0062] Figure 2 This is a structural schematic diagram of a parallel rocket engine mounting tool according to the present invention, in which a parallel rocket engine frame is docked and mounted with an engine docking frame;

[0063] Figure 3 This is a diagram showing a state in which a mounting tool for a parallel rocket engine of the present invention matches a frame to be mounted with the lower end of a guide rail;

[0064] Figure 4 This is a schematic structural diagram of two thrust chambers of a parallel rocket engine to be installed in an embodiment of the present invention being installed on the installation tool provided by the present invention;

[0065] Figure 5 yes Figure 4 A partial enlarged view of point A in the middle;

[0066] Figure 6 2 is a schematic structural diagram of a spring tightening assembly connected between a base plate assembly and an inclined pad in an embodiment of the present invention;

[0067] Figure Number:

[0068] 1-parallel rocket engine to be installed, 11-thrust chamber, 12-frame; 2-tilted pad; 3-base plate assembly, 31-chassis, 311-lower base plate, 312-connecting plate, 32-upper base plate, 33-roller ball, 34-connecting bolt; 4-spring tightening assembly, 41-hollow screw, 42-hollow nut, 421-nut body, 422-tightening ring, 43-spring; 5-guide rail; 6-engine docking frame. DETAILED DESCRIPTION

[0069] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0070] Figure 1Schematic diagram of the structure of the parallel rocket engine to be installed in the embodiment of the present invention; Figure 1 As shown, the parallel rocket engine 1 to be installed includes a frame 12 and multiple rocket engines connected in parallel below the frame 12. A thrust chamber 11 is provided below each rocket engine, that is, it includes multiple thrust chambers 11. It should be noted that there are many other components distributed between the frame 12 and the thrust chamber 11. Since they are less related to the present invention, the drawings of the present invention have been simplified to highlight the technical features of the present invention. The embodiment of the present invention is introduced by taking a 180kN liquid oxygen / kerosene engine dual parallel rocket engine as an example. That is to say, the parallel rocket engine to be installed has two thrust chambers 11. Due to the need to adjust the rocket's flight attitude, the two thrust chambers 11 are tilted outward by 3° respectively, resulting in the parallel rocket engine 1 to be installed being unable to be placed stably. In order to enable it to be placed stably, the embodiment of the present invention provides a parallel rocket engine installation tool.

[0071] Figure 2 This is a structural diagram of a parallel rocket engine mounting tool according to the present invention, in which the parallel rocket engine frame is docked and mounted with the engine docking frame. Figure 3 This is a state diagram of the parallel rocket engine installation tool of the present invention, in which the frame to be installed with the parallel rocket engine is matched with the lower end of the guide rail, combined with Figure 2 and Figure 3 As shown, a parallel rocket engine installation tool includes two inclined pads 2, a base plate assembly 3 and a guide rail 5;

[0072] Figure 4 This is a schematic structural diagram of two thrust chambers of a parallel rocket engine to be installed in an embodiment of the present invention installed on the installation tool provided by the present invention. Figure 5 yes Figure 4 A partial enlarged view of the middle A, combined with Figure 4 and Figure 5 As shown, the base plate assembly 3 includes a base plate 31 and two upper base plates 32; the base plate 31 includes a lower base plate 311 and a connecting plate 312; the lower base plate 311 is arranged horizontally; the connecting plate 312 is vertically connected to the lower base plate 311; the two upper base plates 32 are respectively arranged parallel to each other above the lower base plate 311 and are detachably connected to the connecting plates 312 via connecting bolts 34. The specific connection method is as follows: a first threaded hole is provided on the connecting plate 312; a second threaded hole corresponding to the first threaded hole is provided on the side of the upper base plate 32; and the connecting bolts 34 are inserted into the first threaded hole and the second threaded hole. In this embodiment of the present invention, the lower base plate 311 is a rectangular structure, and the connecting plate 312 is arranged around the edge of the lower base plate 311. The two upper base plates 32 are respectively arranged near the connecting plates 312 on opposite sides and are detachably connected to the adjacent connecting plates 312 via connecting bolts 34.

[0073] A plurality of rolling balls 33 are provided between the upper base plate 32 and the lower base plate 311; the plurality of rolling balls 33 are evenly distributed so that the upper base plate 32 and the lower base plate are parallel to each other; arc-shaped grooves corresponding to and matching each rolling ball 33 are provided on the upper surface of the lower base plate 32, and each rolling ball 33 is respectively arranged in the corresponding arc-shaped groove, which on the one hand prevents the rolling balls 33 from running around and causing unevenness, and on the other hand also improves the smoothness of the rolling of the rolling balls 33.

[0074] The 180kN liquid oxygen / kerosene engine targeted in the embodiment of the present invention weighs approximately 800kg, so 10 balls 33 with a diameter of 12mm can be set on each lower base plate, the distance between each ball 33 and the adjacent balls can be 300mm, and the depth of the arc groove corresponding to each ball 33 can be 2mm.

[0075] The two inclined pads 2 are respectively arranged above the two upper base plates 32, and the two inclined pads 2 correspond one by one to the two thrust chambers 11 of the parallel rocket engine 1 to be installed; the bottom surface of the inclined pad 2 is parallel to the upper base plate 32, and the top surface of the inclined pad 2 is an inclined surface, which is used to contact the bottom end of the corresponding thrust chamber 11, and can correct the entire parallel rocket engine 1 to be installed to a horizontal state, so that it can be placed stably above the base plate assembly 3.

[0076] The inclined pad 2 in the embodiment of the present invention may be circular, and a plurality of spring tightening assemblies 4 are provided between the inclined pad 2 and the upper base plate 32 ; the plurality of spring tightening assemblies 4 may be evenly distributed circumferentially around the inclined pad 2 . Figure 6 FIG. 1 is a schematic diagram of a structure in which a spring tensioning assembly is connected between a base plate assembly and an inclined pad in an embodiment of the present invention. Figure 6As shown, the spring tightening assembly 4 includes a hollow screw 41, a hollow nut 42 and a spring 43; one end of the hollow screw 41 is fixedly mounted on the upper base plate 32, and the other end is vertically upward; the hollow nut 42 includes a nut body 421 and a tightening ring 422; the nut body 421 is sleeved on the hollow screw 41 and threadedly connected to it; the lower end of the tightening ring 422 is connected to the upper end of the nut body 421, and its upper end is used to tighten the corresponding inclined pad 2; the spring 43 is inserted into the center hole of the hollow screw 41, the nut body 421 and the tightening ring 422, the lower end of the spring 43 abuts against the upper surface of the base plate assembly 3, and the upper end of the spring 43 is used to abut against the corresponding inclined pad 2. It is worth noting that when the nut body 421 and the tightening ring 422 are rotated together to the lower end of the hollow screw 41, the upper end of the spring 43 can extend out of the hollow screw 41 and the upper end of the tightening ring 422. In this way, before the tightening ring 422 tightens the inclined pad 2, the inclined pad 2 and the parallel rocket engine 1 to be installed above it can be leveled by themselves under the action of their own gravity and the elastic force of the spring 43. When the inclined pad 2 and the parallel rocket engine 1 to be installed above it are stable, the nut body 421 and the tightening ring 422 are rotated upward so that the top end of the tightening ring 422 presses the inclined pad 2, thereby improving the stability of the placement of the parallel rocket engine 1 to be installed. Even if the bottom surface of the inclined pad 2 is not flat enough, the parallel rocket engine 1 to be installed can be placed stably. For an 800kg parallel rocket engine, the elastic force of the spring 43 is set to withstand 80kg / 10mm, so as to ensure that the unevenness of the force provided to the thrust chamber 11 is no more than 80kg. When the parallel rocket engine to be installed is gradually compressed to 10mm, and after it is fully fitted, the nut body 421 and the tightening ring 422 are rotated upward to tighten the inclined pad 2 to ensure the uniformity of the tightening.

[0077] like Figure 3 As shown, since the rack 12 on which the parallel rocket engine 1 is to be mounted is typically far from the engine docking frame 6, it is easily misaligned due to shaking, causing the rack 12 to lose alignment with the engine docking frame 6. Therefore, this embodiment of the present invention also provides a guide rail 5. The guide rail 5 utilizes a relatively thin guide rod to guide the rack 12 when there is a significant positional deviation between the rack 12 and the docking holes on the engine docking frame 6. The upper end of the guide rail 5 is detachably connected to the external engine docking frame 6, and its lower end is vertically downward, used to guide the docking installation path of the rack 12 on which the parallel rocket engine 1 is to be mounted. In other words, the rack 12 on which the parallel rocket engine 1 is to be mounted is allowed to rise along the guide rail 5. Due to the presence of the guide rail 5, the parallel rocket engine 1 can adaptively move during the ascent, achieving automatic alignment. Furthermore, due to the presence of the rolling ball 33, its movement is also very smooth. It should be noted that after the docking installation is completed, the guide rail 5 needs to be removed.

[0078] An embodiment of the present invention provides a method for installing a parallel rocket engine, based on the above-mentioned parallel rocket engine installation tool, and specifically includes the following steps:

[0079] Step 1: Rotate the hollow nut 42 in each spring tightening assembly 4 to the lower end of the hollow screw 41, that is, rotate the nut body 421 and the tightening ring 422 together to the lower end of the hollow screw 41, so that the spring 43 is naturally released, and the top end of the spring 43 extends out of the upper end of the hollow screw 41 and the tightening ring 422; at the same time, connect the upper base plate 32 in the base plate assembly 3 to the connecting plate 312 on the chassis 31 through the connecting bolts 34;

[0080] Step 2: Place a corresponding inclined pad 2 on top of each spring 43, with the inclined surface of the inclined pad 2 facing upward. Its inclination direction matches the inclination direction of each thrust chamber 11 on the parallel rocket engine 1 to be installed, usually inclined toward the center of the parallel rocket engine 1 to be installed.

[0081] Step 3: Place the parallel rocket engine 1 to be installed on top of each inclined pad 2, so that the bottom end of each thrust chamber 11 is in contact with the inclined surface of the corresponding inclined pad 2;

[0082] Step 4: After the parallel rocket engine 1 to be installed is self-leveled and stable under the action of its own gravity and the elastic force of the spring 43, each hollow nut 42 is rotated upward, that is, the nut body 421 and the tightening ring 422 are rotated upward together, so that the upper end of the tightening ring 422 contacts and tightens the bottom surface of the inclined pad 2;

[0083] Step 5: Use a transport vehicle to transport the base plate assembly 3, the tilting pad 2, the spring tightening assembly 4, and the parallel rocket engine 1 to be installed to the bottom of the engine docking frame 6; the transport vehicle can move in one direction along the transport guide rails, and the central portion of the transport vehicle has the ability to lift upward, but does not have the ability to move in other directions;

[0084] Step 6: Connect the upper end of the guide rail 5 to the engine docking frame 6, then:

[0085] If the lower end of the guide rail 5 is misaligned with the frame 12 on which the parallel rocket engine 1 is to be installed, execute step 7;

[0086] If the lower end of the guide rail 5 corresponds to the position of the rack 12 on which the parallel rocket engine 1 is to be installed, execute step 8;

[0087] Step 7: Disconnect the upper base plate 32 from the chassis 31, that is, remove the connecting bolts 34, fine-tune the upper base plate 32, and move the upper base plate 32 on the balls 33 below it so that the rack 12 and the guide rail 5 are aligned. Then, proceed to step 8.

[0088] Step 8: Lift the base plate assembly 3, the tilting pad 2, the spring tightening assembly 4, and the parallel rocket engine 1 to be installed upward along the guide rail 5 until the frame 12 docks with the engine docking frame 6;

[0089] Step 9: After installing the frame 12 and the engine docking frame 6, remove the bottom plate assembly 3, the inclined pad 2, the spring tightening assembly 4 and the guide rail 5.

[0090] In addition, in order to more accurately dock the frame 12 with the engine docking frame 6, in step 8, when the base plate assembly 3, the inclined pad 2, the spring tightening assembly 4 and the parallel rocket engine 1 to be installed are raised together along the guide rail 5 to the adjacent engine docking frame 6, the guide rail can also be replaced, that is, replaced with a guide rail that can more accurately dock with the docking bolt holes on the engine docking frame 6, and then the frame 12 continues to rise along the replaced guide rail, so that the frame 12 can be more accurately docked and installed with the engine docking frame 6.

[0091] The installation tooling and installation method of the parallel rocket engine provided by the present invention have a simple and effective installation tooling structure, which can greatly improve the installation efficiency of the parallel rocket engine and bring more convenience to the installation work.

[0092] Through the description of the above implementation methods, technical personnel in the relevant field can clearly understand that for the convenience and simplicity of description, only the division of the above-mentioned functional modules is used as an example. In actual applications, the above-mentioned functions can be assigned to different functional modules as needed, that is, the internal structure of the device can be divided into different functional modules to complete all or part of the functions described above.

[0093] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions within the technical scope disclosed by the present invention shall be covered by the scope of protection of the present invention. Therefore, the scope of protection of the present invention shall be subject to the scope of protection of the claims.

Claims

1. A parallel rocket engine installation tool, comprising a plurality of inclined pads (2) whose number is the same as the number of thrust chambers (11) of the parallel rocket engine (1) to be installed and which correspond one to one, characterized in that: It also includes a base plate assembly (3) and a vertically arranged guide rail (5); The bottom plate assembly (3) is arranged horizontally; the bottom plate assembly (3) includes a chassis (31) and a plurality of upper bottom plates (32); the chassis (31) is arranged horizontally; the upper bottom plates (32) are arranged parallel to the chassis (31) and are detachably connected to the chassis (31); the number of the upper bottom plates (32) is the same as the number of the inclined pads (2) and corresponds one to one; a plurality of rolling balls (33) are evenly arranged between each of the upper bottom plates (32) and the chassis (31); the plurality of inclined pads (2) are respectively distributed above the bottom plate assembly (3), the bottom surface of each inclined pad (2) is parallel to the upper bottom plate (32), and the top surface is an inclined surface, and the inclined surface is used to contact the bottom end of the corresponding thrust chamber (11); A plurality of spring tightening assemblies (4) are evenly distributed between each of the inclined pads (2) and the bottom plate assembly (3); The spring tightening assembly (4) includes a hollow screw (41), a hollow nut (42) and a spring (43); one end of the hollow screw (41) is fixedly mounted on the upper base plate (32), and the other end is vertically upward; the hollow nut (42) is sleeved on the hollow screw (41) and is threadedly connected thereto, and the upper end of the hollow nut (42) is used to tighten the corresponding inclined pad (2); the spring (43) is located in the center hole of the hollow screw (41) and the hollow nut (42), one end of which abuts against the base plate assembly (3), and the other end abuts against the corresponding inclined pad (2); The upper end of the guide rail (5) is detachably connected to the external engine docking frame (6), and the lower end thereof is vertically downward, and is used to guide the docking installation path for the frame (12) to be installed with the parallel rocket engine (1), and the frame (12) is connected to the thrust chamber (11).

2. The parallel rocket engine installation tool according to claim 1, characterized in that: The upper surface of the chassis (31) is provided with a plurality of arc-shaped grooves corresponding to the respective rolling balls (33) and matching each other; Each of the rolling balls (33) is respectively arranged in a corresponding arc-shaped groove.

3. The parallel rocket engine installation tool according to claim 2, characterized in that: The chassis (31) includes a lower base plate (311) and a connecting plate (312); The lower base plate (311) is arranged horizontally; The connecting plate (312) is vertically connected above the lower base plate (311); The upper base plate (32) is arranged parallel to and above the lower base plate (311), and is detachably connected to the connecting plate (312); The rolling ball (33) is arranged between the lower base plate (311) and the upper base plate (32).

4. The parallel rocket engine installation tool according to claim 3, characterized in that: The upper base plate (32) is detachably connected to the connecting plate (312) via connecting bolts (34); The connecting plate (312) is provided with a first threaded hole; A second threaded hole corresponding to the first threaded hole is provided on the side surface of the upper base plate (32); The connecting bolt (34) is inserted into the first threaded hole and the second threaded hole.

5. The parallel rocket engine installation tool according to claim 1, characterized in that: The hollow nut (42) includes a nut body (421) and a tightening ring (422); The nut body (421) is sleeved on the hollow screw (41) and is threadedly connected thereto; The tightening ring (422) is sleeved outside the spring (43), and its lower end is connected to the upper end of the nut body (421), and its upper end is used to tighten the corresponding inclined pad (2).

6. A method for installing a parallel rocket engine, based on the installation tool for the parallel rocket engine according to any one of claims 1 to 5, characterized in that: The following steps are involved: Step 1: Rotate the hollow nut (42) in each spring tightening assembly (4) to the lower end of the hollow screw (41), so that the spring (43) is naturally released, and the top of the spring (43) extends out of the upper end of the hollow screw (41) and the hollow nut (42); Step 2: placing a corresponding inclined pad (2) on the top of each spring (43), with the inclined surface of the inclined pad (2) facing upward and its inclined direction matching the inclined direction of the bottom end of each thrust chamber (11) on the parallel rocket engine (1) to be installed; Step 3: Place the parallel rocket engine (1) to be installed on the inclined pad (2) so that the bottom end of each thrust chamber (11) contacts the inclined surface of the corresponding inclined pad (2); Step 4: After the parallel rocket engine (1) to be installed is leveled by itself under the action of its own gravity and the elastic force of the spring (43) until it is stable, each hollow nut (42) is rotated upward so that its upper end contacts the bottom surface of the inclined pad (2); Step 5: transport the base plate assembly (3), the tilting pad (2), the spring tightening assembly (4) and the parallel rocket engine (1) to be installed to the bottom of the engine docking frame (6); Step 6: Lift the base plate assembly (3), the tilting pad (2), the spring tightening assembly (4), and the parallel rocket engine (1) to be installed upward, so that the frame (12) of the parallel rocket engine (1) to be installed is docked with the engine docking frame (6); Step 7: After the frame (12) and the engine docking frame (6) are installed, the base plate assembly (3), the inclined pad (2) and the spring tightening assembly (4) are removed.

7. The method for installing a parallel rocket engine according to claim 6, characterized in that: Step 6 specifically includes: Step 6.1, connect the upper end of the guide rail (5) to the engine docking frame (6), and make the lower end thereof correspond to the position of the frame (12); Step 6.2, raising the base plate assembly (3), the inclined pad (2), the spring tightening assembly (4) and the parallel rocket engine (1) to be installed upward along the guide rail (5), so that the frame (12) is docked with the engine docking frame (6); Step 7 specifically comprises: after the frame (12) is installed with the engine docking frame (6), the bottom plate assembly (3), the tilting pad (2), the spring tightening assembly (4) and the guide rail (5) are removed.

8. The method for installing a parallel rocket engine according to claim 6, characterized in that: Step 1 also includes the step of connecting the upper base plate (32), specifically comprising: connecting the upper base plate (32) in the base plate assembly (3) to the chassis (31); Then step 6 specifically includes: Step 6.1: Connect the upper end of the guide rail (5) to the engine docking frame (6), and then: If the lower end of the guide rail (5) is misaligned with the frame (12) on which the parallel rocket engine is to be installed, step 6.2 is executed; If the lower end of the guide rail (5) corresponds to the position of the rack (12) on which the parallel rocket engine is to be installed, step 6.3 is executed; Step 6.2, disconnect the upper base plate (32) from the chassis (31), fine-tune the upper base plate (32), and move the upper base plate (32) on the rolling ball (33) below it so that the position of the frame (12) and the guide rail (5) correspond to each other, and then execute step 6.3; Step 6.3, lift the base plate assembly (3), the inclined pad (2), the spring tightening assembly (4) and the parallel rocket engine to be installed upward along the guide rail (5) until the frame (12) is docked with the engine docking frame (6).

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