A bundled solid rocket assembly method and a bundled solid rocket

Abstract

The present invention discloses a bundled solid rocket assembly method and a bundled solid rocket, belonging to the field of rocket assembly technology, including transporting each structural section in the bundled solid rocket to an assembly site for independent assembly; independently testing each assembled structural section; transporting each tested structural section to an assembly site for assembly, thereby forming a bundled solid rocket assembly. The bundled solid rocket assembly method of the present invention is suitable for commercial aerospace requirements, can effectively assemble a bundled solid rocket, has high assembly efficiency, and has good stability of the assembled bundled solid rocket.

Description

Technical Field

[0001] The present invention relates to the technical field of rocket assembly, and in particular to a bundled solid rocket assembly method and a bundled solid rocket. Background Art

[0002] With the continuous development of commercial solid rockets, the form and specifications of rocket bodies are also changing. Unlike launch vehicles in the defense field, commercial solid rockets are mainly used for commercial aerospace transportation and to obtain economic benefits. They have strict restrictions on manufacturing, launching and operating costs. Many existing solutions for rocket manufacturing, launching and operating in the defense field cannot be applied to the field of commercial rocket bodies.

[0003] At the same time, with the continuous development of commercial rockets, the rocket production and launch cycle has been shortened, and the requirements for the assembly cycle have become increasingly higher. The existing rocket assembly methods in the defense field cannot meet the requirements of commercial rockets.

[0004] In view of this, it is necessary to provide a new technical solution to solve the above problems. Summary of the invention

[0005] In order to solve the above-mentioned technical problems, the present application provides a bundled solid rocket assembly method and a bundled solid rocket, which can realize the effective assembly of the bundled solid rocket, have high assembly efficiency, and the assembled bundled solid rocket has good stability.

[0006] A method for assembling a bundled solid rocket, comprising:

[0007] Transport each structural segment of the bundled solid rocket to the assembly site for independent assembly;

[0008] Conduct independent testing on each assembled structural section;

[0009] The various structural segments that have completed testing are transported to the final assembly site for final assembly to form a bundled solid rocket assembly.

[0010] Preferably, the structural segments include a booster stage, a core I stage, a core II stage, a core III stage and a star cover assembly.

[0011] Preferably, the star cover assembly includes a fairing and a bracket and a load arranged inside the fairing.

[0012] Preferably, the payload is a satellite, a manned spacecraft, a space station or an interplanetary probe.

[0013] Preferably, the fairing includes two petal-shaped half-cover bodies that can be combined.

[0014] Preferably, the method of transporting each structural segment of the bundled solid rocket to an assembly site for independent assembly includes:

[0015] Transport the various sections of the booster stage to the booster stage assembly site for assembly;

[0016] Transport the various sections of the core I stage to the core I stage assembly site for assembly;

[0017] Transport the various sections of the Core II stage to the Core II stage assembly site for assembly;

[0018] Transport the various sections of the Core III stage to the Core III stage assembly site for assembly;

[0019] The various sections of the star cover assembly are transported to the star cover assembly assembly site for assembly.

[0020] Preferably, when the various sections of the star cover assembly are transported to the star cover assembly assembly site for assembly, the fairing is divided into two half-covers, which are individually packaged and transported to the star cover assembly site, and then hoisted and assembled after the trusses are installed on site.

[0021] Preferably, when each structural segment in the bundled solid rocket is transported to the assembly site for independent assembly, the engines corresponding to the booster stage, core I stage, core II stage and core III stage are equipped with tooling private clothes on the tail nozzle for protection before transportation, and are loaded into an insulated box for transportation to the site.

[0022] Preferably, the independent testing of each assembled structural section includes:

[0023] After the booster stage is assembled, test the assembled booster stage;

[0024] After the core I stage is assembled, the assembled core I stage is tested;

[0025] After the core II stage is assembled, the assembled core II stage is tested;

[0026] After the core III stage is assembled, the assembled core III stage is tested;

[0027] After the star cover assembly is assembled, the assembled star cover assembly is tested.

[0028] Preferably, the independent testing of each assembled structural section includes:

[0029] After the booster stage, core stage I, core stage II, core stage III and star cover assembly are assembled, the booster stage, core stage I, core stage II, core stage III and star cover assembly are tested separately.

[0030] Preferably, the step of transporting the tested structural segments to the final assembly site for final assembly to form a bundled solid rocket final assembly includes:

[0031] The booster stage, core I stage, core II stage, core III stage and star cover assembly that have been assembled and tested separately are transported to the launch area;

[0032] Erect the booster stage and hoist it onto the launch pad;

[0033] Place the core I stage in the area enclosed by the booster, and fix the booster stage to the side of the core I stage;

[0034] Lift the core II stage vertically and hoist it above the core I stage, adjust the rolling angle, horizontal position and angle of the core II stage, and then dock and install it with the core I stage;

[0035] Lift the core III level vertically and hoist it above the core II level, adjust the rolling angle, horizontal position and angle of the core III level, and then dock and install it with the core II level;

[0036] The star cover assembly is vertically hoisted above the core III stage, and the fairing's roll angle, horizontal position and angle are adjusted before docking with the rocket.

[0037] Preferably, when the assembled and individually tested booster stage, core stage I, core stage II, core stage III and star cover assembly are transported to the launch area, the booster stage, core stage I, core stage II and core stage III are transported horizontally and the star cover assembly is transported vertically.

[0038] Preferably, after each assembled structural section is independently tested and before each tested structural section is transported to the final assembly site for final assembly, a full-arrow joint debugging test is also performed.

[0039] Preferably, the full arrow joint debugging test includes:

[0040] Connect the core level I and core level II and connect the electrical interface to verify the mechanical and electrical interface performance between the two;

[0041] Connect the core III level with the core II level and connect the electrical interface to verify the mechanical and electrical interface performance between the two;

[0042] Connect the electrical interface between the booster stage and the core I stage to verify the electrical interface performance between the two.

[0043] Preferably, the step of docking the core level I with the core level II and connecting the electrical interface to verify the mechanical interface performance and electrical interface performance therebetween includes:

[0044] Push the core I and II level support frame vehicles to dock the assembled core I and II level to verify the mechanical interface performance;

[0045] Connect the cable connector between core I and core II through the operating hole of the interstage section of core I to verify the performance of the electrical interface.

[0046] Preferably, the step of docking the core III level with the core II level and connecting the electrical interface to verify the mechanical interface performance and electrical interface performance therebetween includes:

[0047] Park the core III level horizontally on the core III level driving vehicle, move the core III level driving vehicle to dock the assembled core III level with the core II level, and verify the mechanical interface performance;

[0048] Connect the cable connector between core II and core III from the operating hole of the core II interstage section to verify the performance of the electrical interface.

[0049] Preferably, the step of connecting the electrical interface between the booster stage and the core I stage and verifying the electrical interface performance therebetween includes:

[0050] Move the booster stage vehicle carrying the booster stage frame to the side of the core I stage engine, place the tails of the assembled booster engines facing each other and close to the tail of the core I stage engine, connect the cable connector between the core I stage and the booster stage, and verify the performance of the electrical interface.

[0051] Preferably, placing the core I stage in the area enclosed by the booster and fixing the booster stage to the side of the core I stage includes:

[0052] After transporting the booster to the intended location on the sea launch vehicle, the booster is erected on the launch pad using the booster erector;

[0053] After leveling the booster, use the lifting device to lift the horizontally placed core stage I. During the lifting process, rotate it 90° so that the head of the core stage I is kept vertically upward, and slowly put it into the area enclosed by the booster;

[0054] After the core stage I is hoisted to a predetermined height, the upper and lower binding mechanisms between the core stage I and the booster stage are connected;

[0055] Fix the connecting cable between the core I stage and the booster stage on the lower bundling mechanism, assemble the cable box, and lock the connectors at both ends of the cable.

[0056] Preferably, the transporting of the sections of the booster stage to the booster stage assembly site for assembly includes:

[0057] Transport the booster stage's oblique nose cone fairing, booster stage engine, and booster stage tail end to the booster stage assembly site and unload them;

[0058] The oblique head cone finishing cover is hoisted horizontally onto the parking rack using a special hoist for the oblique head cone finishing cover and a small general crane;

[0059] Install a packaging box hoist on the booster-stage engine packaging box, unload it to the ground using a large general-purpose crane, and then use the engine hoist to lift it onto the vehicle after unpacking;

[0060] The rear end of the booster stage is hoisted onto the parking rack using a general purpose hoist and a small general purpose crane;

[0061] Install the components and avionics equipment of each section of the booster stage;

[0062] The tooling servo at the end of the booster stage engine was replaced with a servo mechanism;

[0063] Install avionics equipment and brackets at the rear head of the booster stage engine;

[0064] Connect the cables in the fixed tail end;

[0065] The upper bundled structure booster part is installed on the oblique nose cone fairing, and the lower bundled structure booster part is installed on the tail end of the booster stage;

[0066] Use a small general-purpose crane to lift the oblique nose cone fairing and the tail end of the booster stage separately, flip them 90°, lift them, and dock them with the booster stage engine.

[0067] Preferably, transporting the segments of the core I stage to the core I stage assembly site for assembly includes:

[0068] Transport the core I stage interstage, core I stage engine, and core I stage tail end of the core I stage to the core I stage assembly site and unload them;

[0069] Use a general-purpose hoist and a small general-purpose crane to hoist the core I stage interstage and the core I stage tail end horizontally onto the parking rack;

[0070] Install the packaging box hoist on the core I level engine packaging box, use a large general crane to unload it to the ground, unpack and install the core I level engine hoist, and then lift it onto the vehicle;

[0071] Install the components and avionics equipment belonging to each section of the Core I stage;

[0072] Replace the tooling servo at the end of the core I stage engine with a servo mechanism;

[0073] Install avionics equipment and brackets at the rear head of the core I stage engine;

[0074] Connect the cables in the tail end of the fixed core I;

[0075] Install the lashing structure core stage part outside the core II stage interstage;

[0076] Install the Core I stage avionics equipment inside the Core II stage and connect the internal cables of the Core II stage interstage;

[0077] Install the lower bundling structure core stage part on the outside of the core I stage tail end, and install the camera device and cables on the inside of the core I stage tail end;

[0078] Use a small general-purpose crane to lift the oblique core I stage interstage and the core I stage tail end respectively, flip them 90 degrees, and then lift them to dock with the core I stage engine;

[0079] After locking the core I stage interstage and the core I stage tail end to the core I stage engine, connect the connecting cables of the front and rear heads and install the core I stage cable cover.

[0080] Preferably, transporting the sections of the core II stage to the core II stage assembly site for assembly includes:

[0081] The Core II stage engines and the Core II stage tail end are transported to the assembly site and unloaded;

[0082] Install the packaging box hoist on the Core II engine packaging box, unload it to the ground using a medium-sized general-purpose crane, unpack and install the engine hoist, and then hoist it onto the vehicle;

[0083] The tail end of the core II stage is hoisted horizontally onto the parking rack using a general purpose hoist and a small general purpose crane;

[0084] Install the components and avionics equipment belonging to each section;

[0085] The tooling servo at the end of the Core II stage engine was replaced with a servo mechanism;

[0086] Install the corresponding avionics equipment and brackets at the rear head of the Core II engine;

[0087] Connect the cables in the tail end of the fixed core II;

[0088] Avionics equipment including a secondary switch and secondary integrated controller are installed inside the tail end of the Core II stage and connected with cables;

[0089] Use a small general-purpose crane to lift the tail end of the core II stage, flip it 90 degrees, and then lift it to dock with the core II stage engine;

[0090] After locking the core II level tail section, connect the connecting cables of the front and rear heads and install the core II level cable cover engine part.

[0091] Preferably, transporting the sections of the core III level to the core III level assembly site for assembly includes:

[0092] The instrument compartment of the Core III stage, the Core III stage engine and the interstage of the Core II stage are transported to the assembly site and unloaded;

[0093] Lift the core II interstage section onto the parking frame using a general-purpose lifting device and a small general-purpose crane;

[0094] The instrument compartment is hoisted horizontally onto the parking rack using a special hoist for the instrument compartment and a small general crane;

[0095] Install the packaging box sling on the core III engine packaging box and use a small general crane to unload it to the ground;

[0096] After parking the core II interstage and instrument compartment on the parking rack, assemble the corresponding parts and avionics equipment respectively;

[0097] Install avionics equipment including terminal repair system, flight control combination, and inertial unit in the instrument compartment, and connect cables for testing;

[0098] The camera device and the interstage section of the core II stage cable cover are installed outside the core II stage interstage;

[0099] The instrument compartment and the core III stage engine are hoisted above the core II stage interstage in sequence;

[0100] The core II interstage section is kept horizontally parked, and a small general crane is used to horizontally lift the instrument cabin section and dock it with the core II interstage section;

[0101] The Core III engine is unpacked, a special hoist is installed, and a small general-purpose crane is used to flip it to a vertical state, and it is hoisted into the instrument compartment for connection.

[0102] Preferably, the step of transporting the segments of the star cover assembly to a star cover assembly assembly site for assembly includes:

[0103] Place the satellite bracket horizontally on the work surface, and hoist the satellites onto the bracket one by one for installation;

[0104] The fairing is divided into two half-covers and enters the site horizontally. After entering the site, trusses are installed on the two half-covers respectively. After installation, the fairing trusses are hoisted to a vertical state;

[0105] Lift up half fairing I and half fairing III respectively, and move the crane horizontally to complete the fairing assembly.

[0106] According to another aspect of the present invention, there is also provided a bundled solid rocket, which is assembled by the bundled solid rocket assembly method and includes: a booster stage assembly, a core I stage assembly, a core II stage assembly, a core III stage assembly and a star cover assembly.

[0107] Preferably, the booster stage assembly includes a booster tail section assembly, a booster engine, a booster self-destruct device and a booster oblique nose cone.

[0108] Preferably, the core I stage assembly includes a core I stage tail section assembly, a core I stage engine, a core I stage interstage section assembly and a booster self-destruct device.

[0109] Preferably, the core II stage assembly includes a core II stage tail section assembly, a core II stage engine, a core II stage interstage assembly and a booster self-destruct device.

[0110] Preferably, the core III stage assembly includes a core III stage engine and an instrument cabin assembly.

[0111] Preferably, the satellite cover assembly includes a fairing I half-cover assembly, a fairing III half-cover assembly, an adapter ring, a satellite adapter assembly and a satellite.

[0112] Compared with the prior art, this application has at least the following beneficial effects:

[0113] 1. The method for assembling a bundled solid rocket of the present invention is suitable for commercial aerospace requirements, can effectively assemble a bundled solid rocket, has high assembly efficiency, and the assembled bundled solid rocket has good stability.

[0114] 2. The bundled solid rocket assembly method of the present invention transfers the assembly site to the launch site, effectively improving the flexibility of transporting the rocket booster stage, core stage and star cover assembly, and greatly improving the assembly efficiency of the rocket.

[0115] 3. In the bundled solid rocket assembly method of the present invention, each assembled structural segment is independently tested to ensure the stability of each structural segment.

[0116] 4. In the assembly method of the bundled solid rocket of the present invention, a full-rocket joint adjustment test is carried out to ensure the overall connection performance and overall stability of each structural segment of the bundled solid rocket, thereby further improving the stability of the bundled solid rocket. BRIEF DESCRIPTION OF THE DRAWINGS

[0117] Hereinafter, some specific embodiments of the present invention will be described in detail in an exemplary and non-limiting manner with reference to the accompanying drawings. The same reference numerals in the accompanying drawings indicate the same or similar components or parts. It should be understood by those skilled in the art that these drawings are not necessarily drawn to scale.

[0118] In the figure:

[0119] Figure 1 It is a schematic diagram of the overall process of the bundled solid rocket assembly method of the present invention;

[0120] Figure 2 This is a schematic diagram of the approach of the booster stage section of the present invention;

[0121] Figure 3 This is a schematic diagram of the installation of the booster stage section accessories of the present invention;

[0122] Figure 4 This is a schematic diagram of the approach of the core I stage section of the present invention;

[0123] Figure 5 This is a schematic diagram of the installation of the accessories of the core I stage section of the present invention;

[0124] Figure 6 This is a schematic diagram of the approach of the core II stage section of the present invention;

[0125] Figure 7 This is a schematic diagram of the installation of the accessories of the core II stage section of the present invention;

[0126] Figure 8 It is a schematic diagram of the approach of the core III stage section and the core II stage interstage section of the present invention;

[0127] Fig. 9 This is a schematic diagram of the installation of the accessories of the core III stage section of the present invention;

[0128] Fig.10 This is a schematic diagram of the assembly of the core III stage segment of the present invention;

[0129] Fig.11 This is a schematic diagram of the assembly of the satellite and fairing of the present invention;

[0130] Fig.12 This is a side view of the full arrow joint adjustment of the present invention;

[0131] Fig.13 This is a top view of the full arrow combination adjustment of the present invention;

[0132] Fig.14 This is a schematic diagram of the assembly of the booster stage and the core I stage of the present invention.

[0133] Fig.15 It is a schematic diagram of the assembly of the core I level and the core II level of the present invention;

[0134] Fig.16 It is a schematic diagram of assembling the core II and core III of the present invention;

[0135] Fig.17 It is a schematic diagram of the assembly of the star cover assembly and the core III stage of the present invention;

[0136] Fig.18 It is a schematic diagram of the structure of the bundled solid rocket of the present invention.

[0137] The above drawings include the following reference numerals:

[0138] 100. Booster stage assembly, 200. Core I stage assembly, 300. Core II stage assembly, 400. Core III stage assembly, 500. Star cover assembly. DETAILED DESCRIPTION

[0139] In order to make the purpose, technical solution and advantages of the present application clearer, the technical solution of the present application will be clearly and completely described below in combination with the specific embodiments of the present application and the corresponding drawings. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present application.

[0140] like Figure 1 As shown, a method for assembling a bundled solid rocket comprises the following steps:

[0141] Step S1, transport each structural segment of the bundled solid rocket to the assembly site for independent assembly.

[0142] Among them, the structural sections include a booster stage, a core I stage, a core II stage, a core III stage and a star cover assembly.

[0143] The star cover assembly includes a fairing and a bracket and a payload arranged inside the fairing. The payload is preferably a satellite, a manned spacecraft, a space station or an interplanetary probe. The fairing includes two petal-shaped half-cover bodies that can be combined. The fairing is arranged outside the payload.

[0144] When each structural segment of the bundled solid rocket is transported to the assembly site for independent assembly, the corresponding engines of the booster stage, core I stage, core II stage and core III stage are equipped with tooling private clothes on the tail nozzle for protection before transportation, and are loaded into insulated boxes for transportation to the site.

[0145] Specifically, each structural segment of the bundled solid rocket is transported to the assembly site for independent assembly, including:

[0146] Step S101: transport the various sections of the booster stage to the booster stage assembly site for assembly.

[0147] Specifically, Figure 2 and Figure 3 As shown, including:

[0148] Transport the booster stage's oblique nose cone fairing, booster stage engine, and booster stage tail end to the booster stage assembly site and unload them;

[0149] The oblique head cone finishing cover is hoisted horizontally onto the parking rack using a special hoist for the oblique head cone finishing cover and a small general crane;

[0150] Install a packaging box hoist on the booster-stage engine packaging box, unload it to the ground using a large general-purpose crane, and then use the engine hoist to lift it onto the vehicle after unpacking;

[0151] The rear end of the booster stage is hoisted onto the parking rack using a general purpose hoist and a small general purpose crane;

[0152] Install the components and avionics equipment of each section of the booster stage;

[0153] The tooling servo at the end of the booster stage engine was replaced with a servo mechanism;

[0154] Install avionics equipment and brackets at the rear head of the booster stage engine;

[0155] Connect the cables in the fixed tail end;

[0156] The upper bundled structure booster part is installed on the oblique nose cone fairing, and the lower bundled structure booster part is installed on the tail end of the booster stage;

[0157] Use a small general-purpose crane to lift the oblique nose cone fairing and the tail end of the booster stage separately, flip them 90°, lift them, and dock them with the booster stage engine.

[0158] Step S102, transporting each section of the core I stage to the core I stage assembly site for assembly;

[0159] Specifically, Figure 4 and Figure 5 As shown, including:

[0160] Transport the core I stage interstage, core I stage engine, and core I stage tail end of the core I stage to the core I stage assembly site and unload them;

[0161] Use a general-purpose hoist and a small general-purpose crane to hoist the core I stage interstage and the core I stage tail end horizontally onto the parking rack;

[0162] Install the packaging box hoist on the core I level engine packaging box, use a large general crane to unload it to the ground, unpack and install the core I level engine hoist, and then lift it onto the vehicle;

[0163] Install the components and avionics equipment belonging to each section of the Core I stage;

[0164] Replace the tooling servo at the end of the core I stage engine with a servo mechanism;

[0165] Install avionics equipment and brackets at the rear head of the core I stage engine;

[0166] Connect the cables in the tail end of the fixed core I;

[0167] Install the lashing structure core stage part outside the core II stage interstage;

[0168] Install the Core I stage avionics equipment inside the Core II stage and connect the internal cables of the Core II stage interstage;

[0169] Install the lower bundling structure core stage part on the outside of the core I stage tail end, and install the camera device and cables on the inside of the core I stage tail end;

[0170] Use a small general-purpose crane to lift the oblique core I stage interstage and the core I stage tail end respectively, flip them 90 degrees, and then lift them to dock with the core I stage engine;

[0171] After locking the core I stage interstage and the core I stage tail end to the core I stage engine, connect the connecting cables of the front and rear heads and install the core I stage cable cover.

[0172] Step S103, transporting each section of the core II level to the core II level assembly site for assembly;

[0173] like Figure 6 and Figure 7 As shown, the sections of the core II stage are assembled, and the core II stage interstage is placed in the core III substage for assembly in combination with the structural assembly and test requirements. Therefore, the sections of the core II stage assembly are only the core II stage engine and the core II stage tail section. Specifically, they include:

[0174] The Core II stage engines and the Core II stage tail end are transported to the assembly site and unloaded;

[0175] Install the packaging box hoist on the Core II engine packaging box, unload it to the ground using a medium-sized general-purpose crane, unpack and install the engine hoist, and then hoist it onto the vehicle;

[0176] The tail end of the core II stage is hoisted horizontally onto the parking rack using a general purpose hoist and a small general purpose crane;

[0177] Install the components and avionics equipment belonging to each section;

[0178] The tooling servo at the end of the Core II stage engine was replaced with a servo mechanism;

[0179] Install the corresponding avionics equipment and brackets at the rear head of the Core II engine;

[0180] Connect the cables in the tail end of the fixed core II;

[0181] Avionics equipment including a secondary switch and secondary integrated controller are installed inside the tail end of the Core II stage and connected with cables;

[0182] Use a small general-purpose crane to lift the tail end of the core II stage, flip it 90 degrees, and then lift it to dock with the core II stage engine;

[0183] After locking the core II level tail section, connect the connecting cables of the front and rear heads and install the core II level cable cover engine part.

[0184] Step S104, transporting each section of the core III level to the core III level assembly site for assembly;

[0185] Specifically, Figures 8 to 10 As shown, including:

[0186] The instrument compartment of the Core III stage, the Core III stage engine and the interstage of the Core II stage are transported to the assembly site and unloaded;

[0187] Lift the core II interstage section onto the parking frame using a general-purpose lifting device and a small general-purpose crane;

[0188] The instrument compartment is hoisted horizontally onto the parking rack using a special hoist for the instrument compartment and a small general crane;

[0189] Install the packaging box sling on the core III engine packaging box and use a small general crane to unload it to the ground;

[0190] After parking the core II interstage and instrument compartment on the parking rack, assemble the corresponding parts and avionics equipment respectively;

[0191] Install avionics equipment including terminal repair system, flight control combination, and inertial unit in the instrument compartment, and connect cables for testing;

[0192] The camera device and the interstage section of the core II stage cable cover are installed outside the core II stage interstage;

[0193] The instrument compartment and the core III stage engine are hoisted above the core II stage interstage in sequence;

[0194] The core II interstage section is kept horizontally parked, and a small general crane is used to horizontally lift the instrument cabin section and dock it with the core II interstage section;

[0195] The Core III engine is unpacked, a special hoist is installed, and a small general-purpose crane is used to flip it to a vertical state, and it is hoisted into the instrument compartment for connection.

[0196] Step S105: transport the various sections of the star cover assembly to the star cover assembly assembly site for assembly.

[0197] Specifically, Fig.11 As shown, when assembling the star cover assembly, the satellite and the satellite bracket are vertically docked at the satellite assembly site, and the two half covers are vertically assembled on the vehicle to form a star cover assembly; the star cover assembly is vertically transported to the rocket assembly test site, including:

[0198] Place the satellite bracket horizontally on the work surface, and hoist the satellites onto the bracket one by one for installation;

[0199] The fairing is divided into two half-covers and enters the site horizontally. After entering the site, trusses are installed on the two half-covers respectively. After installation, the fairing trusses are hoisted to a vertical state;

[0200] Lift up half fairing I and half fairing III respectively, and move the crane horizontally to complete the fairing assembly.

[0201] During this process, the fairing is divided into two half-covers, which are individually packaged and transported to the star-cover assembly site. After the trusses are installed on site, they are lifted and assembled.

[0202] In some other embodiments of the present invention, the order of steps S101-S105 can also be adjusted according to the actual assembly situation, as long as the corresponding assembly process is completed before the booster stage, core I stage, core II stage, core III stage and star cover assembly are assembled before step S2.

[0203] Step S2: Conduct independent testing on each assembled structural segment.

[0204] Specifically include:

[0205] Step S201, after the booster stage is assembled, testing the assembled booster stage;

[0206] Step S202: After the core I level is assembled, the assembled core I level is tested;

[0207] Step S203, after the core II level is assembled, testing the assembled core II level;

[0208] Step S204, after the core III level is assembled, testing the assembled core III level;

[0209] Step S205: After the star cover assembly is assembled, the assembled star cover assembly is tested.

[0210] In some other embodiments of the present invention, a centralized testing method may be adopted, that is, after the booster stage, core stage I, core stage II, core stage III and star cover assembly are assembled, the booster stage, core stage I, core stage II, core stage III and star cover assembly are tested separately.

[0211] Step S3: transport the tested structural sections to the final assembly site for final assembly to form a bundled solid rocket assembly.

[0212] Specifically, Figure 14-17 As shown, including:

[0213] Step S301, transporting the booster stage, core I stage, core II stage, core III stage and star cover assembly that have been assembled and tested separately to the launch area;

[0214] Step S302, erecting the booster stage and hoisting it onto the launch pad;

[0215] Step S303: place the core I stage in the area enclosed by the booster, and fix the booster stage to the side of the core I stage.

[0216] Specifically include:

[0217] After transporting the booster to the intended location on the sea launch vehicle, the booster is erected on the launch pad using the booster erector;

[0218] After leveling the booster, use the lifting device to lift the horizontally placed core stage I. During the lifting process, rotate it 90° so that the head of the core stage I is kept vertically upward, and slowly put it into the area enclosed by the booster;

[0219] After the core stage I is hoisted to a predetermined height, the upper and lower binding mechanisms between the core stage I and the booster stage are connected;

[0220] Fix the connecting cable between the core I stage and the booster stage on the lower bundling mechanism, assemble the cable box, and lock the connectors at both ends of the cable.

[0221] Step S304, erect the core II stage and hoist it above the core I stage, adjust the rolling angle and horizontal position and angle of the core II stage, and then dock and install it with the core I stage.

[0222] Step S305, erect the core III level and hoist it above the core II level, adjust the rolling angle and horizontal position and angle of the core III level, and then dock and install it with the core II level.

[0223] Step S306, vertically hoist the star cover assembly to the top of the core III stage, adjust the roll angle and horizontal position and angle of the fairing, and then dock with the rocket.

[0224] Among them, when the various structural sections that have completed the test are transported to the final assembly site for final assembly, the booster stage, core I stage, core II stage, and core III stage are transported horizontally, and the star cover assembly is transported vertically.

[0225] In this embodiment, there are four booster stages, which are evenly distributed on the sides of the core I stage.

[0226] In another embodiment of the present invention, between step S2 and step S3, the following is further included: step S20, performing a full-arrow joint debugging test.

[0227] like Fig.12 and Fig.13 As shown, the specific steps include:

[0228] Step S21, docking the core level I with the core level II and connecting the electrical interface to verify the mechanical interface performance and electrical interface performance between the two.

[0229] Specifically, the core level I and core level II support frame vehicles are pushed to dock the assembled core level I with the core level II to verify the mechanical interface performance;

[0230] Connect the cable connector between core I and core II through the operating hole of the interstage section of core I to verify the performance of the electrical interface.

[0231] Step S22: dock the core III level with the core II level and connect the electrical interface to verify the mechanical interface performance and electrical interface performance between the two.

[0232] Specifically, the core III level is parked horizontally on the core III level driving vehicle, and the core III level driving vehicle is moved to dock the assembled core III level with the core II level to verify the mechanical interface performance;

[0233] Connect the cable connector between core II and core III from the operating hole of the core II interstage section to verify the performance of the electrical interface.

[0234] Step S23, connecting the electrical interface between the booster stage and the core I stage to verify the electrical interface performance between the two.

[0235] Specifically, the booster stage vehicle carrying the booster stage frame is moved to the side of the core I stage engine, the tails of the assembled booster engines are placed two by two facing each other and close to the tail of the core I stage engine, the cable connector between the core I stage and the booster stage is connected to verify the performance of the electrical interface.

[0236] like Fig.18 As shown, a bundled solid rocket is assembled by the bundled solid rocket assembly method, including: 4 booster stage assemblies 100, 1 core I stage assembly 200, 1 core II stage assembly 300, 1 core III stage assembly 400 and 1 star cover assembly 500.

[0237] Preferably, the booster stage assembly 100 includes a booster tail section assembly, a booster engine, a booster self-destruct device and a booster oblique nose cone.

[0238] The booster tail section assembly includes a booster tail section shell and a booster lower end binding connecting rod. The booster oblique nose cone assembly includes a booster oblique nose cone shell and a booster upper end binding connection mechanism.

[0239] Preferably, the core I stage 200 assembly includes a core I stage tail section assembly, a core I stage engine, a core I stage interstage section assembly and a booster self-destruct device.

[0240] The core I stage tail section assembly includes the core I stage tail section housing and the binding connecting rod at the lower end of the core I stage. The core I stage interstage section assembly includes the core I stage interstage section housing and the core I stage upper end binding mechanism.

[0241] Preferably, the core II stage assembly 300 includes a core II stage tail section assembly, a core II stage engine, a core II stage interstage assembly and a booster self-destruct device.

[0242] The core II stage tail section assembly includes a core II stage separation ring and a core II stage tail section casing. The core II stage interstage section assembly includes a core II stage interstage section casing.

[0243] Preferably, the core III stage assembly 400 includes a core III stage engine and an instrument cabin assembly.

[0244] The instrument cabin assembly includes an instrument cabin final repair assembly and an instrument cabin separation ring. The instrument cabin final repair assembly includes an instrument cabin shell and a final repair attitude control power system.

[0245] Preferably, the satellite cover assembly 500 includes a fairing I half-cover assembly, a fairing III half-cover assembly, an adapter ring, a satellite adapter assembly and a satellite.

[0246] Among them, the star cover assembly includes the fairing I half-cover assembly, the fairing III half-cover assembly, the adapter ring, the satellite adapter assembly and the satellite.

[0247] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0248] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0249] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the numbers used in this way can be interchanged where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein.

[0250] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A method for assembling a bundled solid rocket, characterized in that: include: Transport each structural segment of the bundled solid rocket to the assembly site for independent assembly; Conduct independent testing on each assembled structural section; The various structural sections that have been tested are transported to the final assembly site for final assembly to form a bundled solid rocket assembly; The structural sections include a booster stage, a core I stage, a core II stage, a core III stage and a star cover assembly; The method of transporting each structural segment of the bundled solid rocket to an assembly site for independent assembly includes: Transport the various sections of the booster stage to the booster stage assembly site for assembly; Transport the various sections of the core I stage to the core I stage assembly site for assembly; Transport the various sections of the Core II stage to the Core II stage assembly site for assembly; Transport the various sections of the Core III stage to the Core III stage assembly site for assembly; Transporting the various sections of the star cover assembly to the star cover assembly assembly site for assembly; The transporting of the various sections of the booster stage to the booster stage assembly site for assembly includes: Transport the booster stage's oblique nose cone fairing, booster stage engine, and booster stage tail end to the booster stage assembly site and unload them; The oblique nose cone fairing is hoisted horizontally onto the parking rack using a special hoist for the oblique nose cone fairing and a small general crane; Install a packaging box hoist on the booster-stage engine packaging box, unload it to the ground using a large general-purpose crane, and then use the engine hoist to lift it onto the vehicle after unpacking; The rear end of the booster stage is hoisted onto the parking rack using a general purpose hoist and a small general purpose crane; Install the components and avionics equipment of each section of the booster stage; The tooling servo at the end of the booster stage engine was replaced with a servo mechanism; Install avionics equipment and brackets at the rear head of the booster stage engine; Connect the cables in the fixed tail end; The upper bundled structure booster part is installed on the oblique nose cone fairing, and the lower bundled structure booster part is installed on the tail end of the booster stage; Use a small general-purpose crane to lift the oblique nose cone fairing and the booster stage tail end respectively, flip them 90 degrees, lift them, and dock them with the booster stage engine; The transporting of the sections of the core I stage to the core I stage assembly site for assembly includes: Transport the core I stage interstage, core I stage engine, and core I stage tail end of the core I stage to the core I stage assembly site and unload them; Use a general-purpose hoist and a small general-purpose crane to hoist the core I stage interstage and the core I stage tail end horizontally onto the parking rack; Install the packaging box hoist on the core I level engine packaging box, use a large general crane to unload it to the ground, unpack and install the core I level engine hoist, and then lift it onto the vehicle; Install the components and avionics equipment belonging to each section of the Core I stage; Replace the tooling servo at the end of the core I stage engine with a servo mechanism; Install avionics equipment and brackets at the rear head of the core I stage engine; Connect the cables in the tail end of the fixed core I; Install the lashing structure core stage part outside the core I stage interstage; Install the core I stage avionics equipment inside the core I stage and connect the internal cables of the core I stage interstage; Install the lower bundling structure core stage part on the outside of the core I stage tail end, and install the camera device and cables on the inside of the core I stage tail end; Use a small general-purpose crane to lift the oblique core I stage interstage and the core I stage tail end respectively, flip them 90 degrees, and then lift them to dock with the core I stage engine; After locking the core I stage interstage and the core I stage tail end to the core I stage engine, connect the connecting cables of the front and rear heads and install the core I stage cable cover.

2. The method for assembling a bundled solid rocket according to claim 1, characterized in that: The star cover assembly comprises a fairing and a bracket and a load arranged inside the fairing.

3. The method for assembling a bundled solid rocket according to claim 2, characterized in that: The payload is a satellite, a manned spacecraft, a space station or an interplanetary probe.

4. The method for assembling a bundled solid rocket as claimed in claim 3, characterized in that: The fairing includes two petal-shaped half-cover bodies that can be combined.

5. The method for assembling a bundled solid rocket according to claim 1, characterized in that: When the various sections of the star cover assembly are transported to the star cover assembly assembly site for assembly, the fairing is divided into two half-covers, which are individually packaged and transported to the star cover assembly site, and then hoisted and assembled after the trusses are installed on site.

6. The method for assembling a bundled solid rocket according to claim 1, characterized in that: When each structural segment of the bundled solid rocket is transported to the assembly site for independent assembly, the corresponding engines of the booster stage, core I stage, core II stage and core III stage are equipped with tooling servos on the tail nozzles for protection before transportation, and are loaded into insulated boxes for transportation to the site.

7. The method for assembling a bundled solid rocket according to claim 1, characterized in that: The independent testing of each assembled structural section includes: After the booster stage is assembled, test the assembled booster stage; After the core I stage is assembled, the assembled core I stage is tested; After the core II stage is assembled, the assembled core II stage is tested; After the core III stage is assembled, the assembled core III stage is tested; After the star cover assembly is assembled, the assembled star cover assembly is tested.

8. The method for assembling a bundled solid rocket according to claim 1, characterized in that: The independent testing of each assembled structural section includes: After the booster stage, core stage I, core stage II, core stage III and star cover assembly are assembled, the booster stage, core stage I, core stage II, core stage III and star cover assembly are tested separately.

9. The method for assembling a bundled solid rocket according to claim 1, characterized in that: The above-mentioned transporting the tested structural sections to the final assembly site for final assembly to form a bundled solid rocket final assembly includes: The booster stage, core I stage, core II stage, core III stage and star cover assembly that have been assembled and tested separately are transported to the launch area; Erect the booster stage and hoist it onto the launch pad; Place the core I stage in the area enclosed by the booster stage, and fix the booster stage to the side of the core I stage; Lift the core II stage vertically and hoist it above the core I stage, adjust the rolling angle, horizontal position and angle of the core II stage, and then dock and install it with the core I stage; Lift the core III level vertically and hoist it above the core II level, adjust the rolling angle, horizontal position and angle of the core III level, and then dock and install it with the core II level; The star cover assembly is vertically hoisted above the core III stage, and the fairing's roll angle, horizontal position and angle are adjusted before docking with the rocket.

10. The method for assembling a bundled solid rocket according to claim 9, characterized in that: When the assembled and individually tested booster stage, core stage I, core stage II, core stage III and star cover assembly are transported to the launch area, the booster stage, core stage I, core stage II and core stage III are transported horizontally and the star cover assembly is transported vertically.

11. The method for assembling a bundled solid rocket according to claim 9, characterized in that: After each assembled structural section has been independently tested, the entire arrow is also tested before being transported to the final assembly site for final assembly.

12. The method for assembling a bundled solid rocket according to claim 11, characterized in that: The full arrow joint debugging test includes: Connect the core level I and core level II and connect the electrical interface to verify the mechanical and electrical interface performance between the two; Connect the core III level with the core II level and connect the electrical interface to verify the mechanical and electrical interface performance between the two; Connect the electrical interface between the booster stage and the core I stage to verify the electrical interface performance between the two.

13. The method for assembling a bundled solid rocket according to claim 12, characterized in that: The step of docking the core level I with the core level II and connecting the electrical interface to verify the mechanical interface performance and electrical interface performance between the two includes: Push the core level I and core level II support frame vehicle to dock the assembled core level I with the core level II to verify the mechanical interface performance; Connect the cable connector between core I and core II through the operating hole of the interstage section of core I to verify the performance of the electrical interface.

14. The method for assembling a bundled solid rocket according to claim 12, characterized in that: The step of docking the core III level with the core II level and connecting the electrical interface to verify the mechanical interface performance and electrical interface performance between the two includes: Park the core III level horizontally on the core III level driving vehicle, move the core III level driving vehicle to dock the assembled core III level with the core II level, and verify the mechanical interface performance; Connect the cable connector between core II and core III from the operating hole of the core II interstage section to verify the performance of the electrical interface.

15. The method for assembling a bundled solid rocket according to claim 12, characterized in that: Connecting the electrical interface between the booster stage and the core I stage and verifying the electrical interface performance therebetween includes: Move the booster stage carriage carrying the booster stage to the side of the core I stage engine, place the tails of the assembled booster stage engines facing each other and close to the tail of the core I stage engine, connect the cable connector between the core I stage and the booster stage, and verify the performance of the electrical interface.

16. The method for assembling a bundled solid rocket according to claim 9, characterized in that: Placing the core I stage in the area enclosed by the booster stage, and fixing the booster stage to the side of the core I stage, comprises: After transporting the booster stage to the intended location of the sea launch vehicle, the booster stage erection frame is used to erect the booster stage onto the launch pad; After leveling the booster stage, use the hoist to lift the horizontally placed core stage I. During the lifting process, rotate it 90° so that the head of the core stage I is kept vertically upward, and slowly place it into the area enclosed by the booster stage; After the core stage I is hoisted to a predetermined height, the upper and lower binding mechanisms between the core stage I and the booster stage are connected; Fix the connecting cable between the core I stage and the booster stage on the lower bundling mechanism, assemble the cable box, and lock the connectors at both ends of the cable.

17. The method for assembling a bundled solid rocket according to claim 1, characterized in that: The transporting of the sections of the core II stage to the core II stage assembly site for assembly includes: The Core II stage engines and the Core II stage tail end are transported to the assembly site and unloaded; Install the packaging box hoist on the Core II engine packaging box, unload it to the ground using a medium-sized general-purpose crane, unpack and install the engine hoist, and then hoist it onto the vehicle; The tail end of the core II stage is hoisted horizontally onto the parking rack using a general purpose hoist and a small general purpose crane; Install the components and avionics equipment belonging to each section; The tooling servo at the end of the Core II stage engine was replaced with a servo mechanism; Install the corresponding avionics equipment and brackets at the rear head of the Core II engine; Connect the cables in the tail end of the fixed core II; Avionics equipment including a secondary switch and secondary integrated controller are installed inside the tail end of the Core II stage and connected with cables; Use a small general-purpose crane to lift the tail end of the core II stage, flip it 90 degrees, and then lift it to dock with the core II stage engine; After locking the core II level tail section, connect the connecting cables of the front and rear heads and install the core II level cable cover engine part.

18. The method for assembling a bundled solid rocket according to claim 1, characterized in that: The transporting of the sections of the core III stage to the core III stage assembly site for assembly includes: The instrument compartment of the Core III stage, the Core III stage engine and the interstage of the Core II stage are transported to the assembly site and unloaded; Lift the core II interstage section onto the parking frame using a general-purpose lifting device and a small general-purpose crane; The instrument compartment is hoisted horizontally onto the parking rack using a special hoist for the instrument compartment and a small general crane; Install the packaging box sling on the core III engine packaging box and use a small general crane to unload it to the ground; After parking the core II interstage and instrument compartment on the parking rack, assemble the corresponding parts and avionics equipment respectively; Install avionics equipment including terminal repair system, flight control combination, and inertial unit in the instrument compartment, and connect cables for testing; The camera device and the interstage section of the core II stage cable cover are installed outside the core II stage interstage; The instrument compartment and the core III stage engine are hoisted above the core II stage interstage in sequence; The core II interstage section is kept horizontally parked, and a small general crane is used to horizontally lift the instrument cabin section and dock it with the core II interstage section; The Core III engine is unpacked, a special hoist is installed, and a small general-purpose crane is used to flip it to a vertical state, and it is hoisted into the instrument compartment for connection.

19. The method for assembling a bundled solid rocket according to claim 1, characterized in that: The transporting of the segments of the star cover assembly to the star cover assembly assembly site for assembly includes: Place the satellite bracket horizontally on the work surface, and hoist the satellites onto the bracket one by one for installation; The fairing is divided into two half-covers and enters the site horizontally. After entering the site, trusses are installed on the two half-covers respectively. After installation, the fairing trusses are hoisted to a vertical state; Lift up half fairing I and half fairing III respectively, and move the crane horizontally to complete the fairing assembly.

20. A bundled solid rocket, characterized in that: It is assembled by the bundled solid rocket assembly method described in any one of claims 1 to 19, and includes: a booster stage assembly, a core I stage assembly, a core II stage assembly, a core III stage assembly and a star cover assembly.

21. The strapped solid rocket according to claim 20, characterized in that: The booster stage assembly includes a booster stage tail section assembly, a booster stage engine, a booster self-destruct device and a booster stage oblique nose cone.

22. The strapped solid rocket according to claim 20, characterized in that: The core I stage assembly includes a core I stage tail section assembly, a core I stage engine, a core I stage interstage section assembly and a booster self-destruct device.

23. The strapped solid rocket according to claim 20, characterized in that: The core II stage assembly includes a core II stage tail section assembly, a core II stage engine, a core II stage interstage assembly and a booster self-destruct device.

24. The strapped solid rocket according to claim 20, characterized in that: The core III stage assembly includes a core III stage engine and an instrument cabin assembly.

25. The strapped solid rocket according to claim 20, characterized in that: The satellite cover assembly comprises a fairing I half-cover assembly, a fairing III half-cover assembly, a switching ring, a satellite adapter assembly and a satellite.

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