CN115930696A - Medium-large low-temperature carrier rocket test and launch system and implementation method - Google Patents
Medium-large low-temperature carrier rocket test and launch system and implementation method Download PDFInfo
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- CN115930696A CN115930696A CN202211706989.9A CN202211706989A CN115930696A CN 115930696 A CN115930696 A CN 115930696A CN 202211706989 A CN202211706989 A CN 202211706989A CN 115930696 A CN115930696 A CN 115930696A
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- 238000012546 transfer Methods 0.000 claims abstract description 68
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- 235000012633 Iberis amara Nutrition 0.000 claims abstract description 12
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Abstract
A medium-large low-temperature carrier rocket test and launch system and an implementation method thereof are provided, wherein the system comprises: transporting and transferring ground equipment, propellant filling ground equipment, launching ground equipment and temperature control equipment; the transportation and transshipment ground equipment is used for transferring the rocket bodies from the technical area to the launching area to complete transshipment work; the propellant filling ground equipment is used for filling fuel agents and propellants; the launching ground equipment is used for launching the rocket body, retreats and collects the rocket body after the rocket body is ignited to take off, and transfers the rocket body to other launching stations; the temperature control equipment is used for providing clean air into the rocket fairing; wherein the propellant charging ground equipment and/or launching ground equipment is mobile equipment. The invention is applied to medium-sized and large-sized liquid or solid-liquid hybrid rockets, and does not relate to transportation and launching equipment of small rockets and the like.
Description
Technical Field
The invention relates to the technical field of rocket launching, in particular to a medium-large low-temperature carrier rocket launching test system and an implementation method.
Background
At present, the common test and launch modes of carrier rockets in all countries of the world are mainly 3: one-plane two-plumb (rocket horizontal transfer, vertical assembly, vertical test), three-plumb (rocket vertical transfer, vertical assembly, vertical test) and three-plane (rocket horizontal transfer, horizontal assembly, horizontal test). The one-to-two vertical test mode has the advantages of simple technical area facilities, continuous test process in a transmitting area and no need of state conversion. The requirements on the launching pad are low, the rocket transportation conditions are low, and the operation is simple. However, the mode has high requirements on facilities in a launching area, a fully-closed tower with complete functions needs to be built for rocket hoisting and testing, the occupied time of the rocket in the launching area is long, and the time interval between every two launches is long. The three-vertical test launching mode has the advantages that the test environment is good, the same set of front-end test equipment can be used for testing the technical area and the launching area, the test state is not disconnected during transportation, the test state and the test result of the technical area are guaranteed to be effective, the working time of the rocket in the launching area is effectively shortened, and continuous launching is facilitated. However, the mode has high requirements on ground facility equipment, apart from constructing a high vertical assembly plant in a technical area, part of rockets also need to construct service towers in a launching area, and simultaneously, the mode has high requirements on movable launching platforms, and the whole ground facility equipment has large scale and high manufacturing cost. The three-dimensional vertical assembly test room has the advantages that a large vertical assembly test factory building can be prevented from being built in a technical area, ground facilities of a launch area are simple, requirements on a transport road are low, and transport vehicles used during transfer are economical compared with the three-dimensional vertical mode. The three test and launch modes have advantages and disadvantages respectively, and are applied to rocket launching processes at home and abroad.
The selection of the test and launch mode is related to the carrying capacity of the rocket and the position of a launch site, and the most appropriate test and launch mode needs to be selected through comprehensive evaluation in the aspects of task adaptability, environment adaptability, reliability, safety, economy and the like. The horizontal-vertical-two-vertical, vertical-three-vertical and vertical-three-vertical launching modes are applied to medium-sized low-temperature launch vehicles, but generally complete launching tasks in specific launching fields and fixed launching stations. Due to the characteristic that the low-temperature propellant is difficult to store for a long time, a low-temperature propellant filling tank or a filling storehouse is generally built on a launching field, and a filling hard pipe is laid to lead to a rocket launching station. The launching task needs more ground equipment and more launching equipment which is pre-built on a launching field level. If a low-temperature propellant filling tank or a filling storehouse is required to be built on a launching terrace, a filling hard pipe leading to a rocket is laid in advance, a launching tower is required to be built, a diversion trench is excavated underground on the terrace, and an air conditioner room is built. In the prior art, the medium-sized low-temperature carrier rocket needs more guarantee conditions, and a one-to-two-drop or three-drop mode test and launch process is more selected. A low-temperature propellant filling tank or a filling storehouse is built on a launching site, a filling hard pipe leading to a rocket is laid in advance, a launching tower is built, a diversion trench is dug underground on the site, an air conditioner room is built, a long construction period is needed, a large amount of construction cost needs to be invested, and rocket launching is limited to a certain fixed launching station or launching site.
Disclosure of Invention
In order to solve the technical problems, the invention provides a medium-large low-temperature carrier rocket test and launch system and an implementation method. The technical scheme adopted by the invention is as follows:
the invention provides a medium-large low-temperature carrier rocket test and launch system in a first aspect, wherein the system comprises: the system comprises transportation and transfer ground equipment, propellant filling ground equipment, launching ground equipment and temperature control equipment;
the transportation and transshipment ground equipment is used for transferring the arrow body from the technical area to the launching area to complete transshipment work;
propellant filling ground equipment is used for filling fuel agents and propellants;
the launching ground equipment is used for launching the rocket body, retreats and collects the rocket body after the rocket body is ignited to take off, and transfers the rocket body to other launching stations;
the temperature control equipment is used for providing clean air into the rocket fairing;
wherein the propellant charging ground equipment and/or the launching ground equipment are mobile equipment.
Further, the transportation and transshipment ground equipment comprises: a full-rocket transfer trolley, a full-rocket lifting appliance and a lorry-mounted crane;
the whole rocket transfer trolley is used for transferring the rocket bodies from the technical area to the launching area and comprises a transport flat car, the transport flat car is positioned at the rear part of the whole rocket transfer trolley and used for bearing and transporting the rocket bodies, and the head part of the whole rocket transfer trolley is provided with traction power by a tractor;
and in the arrow body transferring state, the full-rocket transfer trolley is parked at a position parallel to the launching rack in the launching ground equipment, the full-rocket hanger is connected to the arrow body, and the arrow body is transferred to the launching rack in the launching ground equipment from the full-rocket transfer trolley by using the cooperation of the lorry-mounted crane and the full-rocket hanger.
Further, the propellant filling ground equipment comprises a propellant filling vehicle, a propellant tank wagon, a propellant filling pipeline, a low-temperature propellant filling vehicle, a low-temperature propellant tank wagon, a low-temperature propellant filling pipeline, a supercooler vehicle, an air distribution trolley and an air supply pipeline;
the low-temperature propellant tank car is used for supplying low-temperature propellant, the plurality of sections of low-temperature propellant filling pipelines are used for conveying the low-temperature propellant, the subcooler car is used for conveying cryogen to the subcooler car, the gas distribution trolley is used for providing gas used in filling, and the gas supply pipeline is used for conveying gas.
Furthermore, liquid outlets of a plurality of low-temperature propellant tank cars are communicated with a liquid inlet of a low-temperature propellant filling car through a low-temperature propelling and filling pipeline, and liquid outlets of the low-temperature propellant filling car are communicated with a filling port of a rocket low-temperature propellant storage tank through the low-temperature propelling and filling pipeline;
the liquid outlets of the plurality of combustion agent tank cars are communicated with the liquid inlet of the combustion agent filling car through a combustion agent filling pipeline, and the liquid outlets of the combustion agent filling car are communicated with the filling port of the rocket combustion agent storage tank through a combustion agent filling pipeline.
Furthermore, a liquid outlet of the super-cooling agent vehicle conveys the super-cooling agent to a working medium liquid inlet of the super-cooling device vehicle through a low-temperature pipeline, and the super-cooling device vehicle cools the low-temperature propellant flowing through by evaporating the working medium, so that the low-temperature propellant is in a super-cooling state.
Furthermore, the low-temperature propellant flows out from a liquid outlet of the low-temperature propellant filling vehicle and then is divided, and the low-temperature propellant flows through a low-temperature propellant filling pipeline to a liquid inlet of the subcooler vehicle, is further cooled in the subcooler vehicle to be in a subcooled state, and is conveyed into the rocket low-temperature propellant storage tank through the low-temperature propellant filling pipeline.
Furthermore, the launching ground equipment comprises a launching frame, a launching platform and a fluid director;
the launcher is used for erecting the arrow body;
the launching platform is used for vertically supporting the arrow body after erecting;
the flow guider is used for guiding tail flame exhausted by the engine after the rocket is ignited.
The second aspect of the invention provides a medium-large low-temperature carrier rocket test and launch implementation method, which comprises the following steps:
horizontally transporting each substage of the rocket into a launching field, horizontally butting each substage to finish the general assembly of the whole rocket, carrying out a test in a horizontal state, and horizontally transferring the rocket to a whole rocket transfer trolley of ground transportation and transfer equipment after the test is finished;
the rocket body is horizontally transported to a launching field by a full rocket transfer vehicle, the rocket body is transferred to a launching frame by using a full rocket lifting tool and a lorry-mounted crane, the launching frame is erected, the rocket is in a vertical state and is butted with a launching platform, and air is supplied to a fairing by using temperature control equipment;
the low-temperature propellant filling vehicle fills the low-temperature propellant into the rocket storage tank, the rocket is lifted up and then is tilted down, the rocket is ignited and launched, and after the rocket is ignited and launched, the propellant filling vehicle and the low-temperature propellant filling vehicle are retracted.
Further, the arrow transfer trolley transfers the arrow bodies from the technical area to the launching area, the arrow transfer trolley transfers the arrow bodies from the arrow transfer trolley to the launching frame in the launching ground equipment, and after the arrow transfer work is completed, the arrow transfer trolley drives away from the launching terrace.
Further, a combustion agent filling vehicle fills combustion agent into a rocket combustion agent storage box in a pump type or extrusion type mode, the combustion agent tank wagon supplies the combustion agent, a combustion agent filling pipeline conveys the combustion agent, at least one combustion agent tank wagon is used for conveying the combustion agent to a launching field, the low-temperature propellant filling vehicle, the low-temperature propellant tank wagon, the low-temperature propellant filling pipeline, the super-cooling agent vehicle and the super-cooling device vehicle are arranged as required, and the low-temperature propellant filling function is completed by the low-temperature propellant filling vehicle, the low-temperature propellant tank wagon, the low-temperature propellant filling pipeline, the super-cooling agent vehicle and the super-cooling device vehicle;
the low-temperature propellant is filled into the rocket low-temperature storage tank through a pump type or an extrusion type, the low-temperature propellant tank wagon is used for supplying the low-temperature propellant, a plurality of sections of low-temperature propellant filling pipelines are used for conveying the low-temperature propellant, at least one low-temperature propellant tank wagon is used for conveying the low-temperature propellant to a launching field ground, and the low-temperature propellant is arranged as required; the subcooler vehicle is used for conveying a refrigerant to the subcooler vehicle to serve as a working medium, a liquid outlet of the subcooler vehicle is used for conveying the subcooler to a working medium inlet of the subcooler vehicle through a low-temperature pipeline, and the subcooler vehicle is used for cooling a low-temperature propellant flowing through by evaporating the working medium to enable the low-temperature propellant to be in a subcooled state; part of the low-temperature propellant flows out of a liquid outlet of the low-temperature propellant filling vehicle and then is distributed, and the low-temperature propellant flows through a low-temperature propellant filling pipeline to a liquid inlet of the subcooler vehicle, is further cooled in the subcooler vehicle to be in a subcooled state, and is conveyed to a storage tank of the rocket low-temperature propellant through a low-temperature propelling filling pipeline;
the launcher in the launching ground equipment erects and then vertically supports the rocket body, after the rocket is ignited, the deflector guides the tail flame discharged by the engine, and the launching equipment is retracted after the rocket is ignited and takes off.
Compared with the prior art, the invention has the following beneficial technical effects:
1. the three-translation-mode launch measurement implementation method can be used for medium and large low-temperature carrier rockets, and can meet the requirements of the medium and large low-temperature carrier rockets on quick and low-cost launch;
2. the invention uses the general transport vehicle to finish the transfer work of the whole rocket from the technical area to the launching field, does not need to develop a special whole rocket transport vehicle, greatly reduces the cost of rocket launching, does not depend on the special whole rocket transport vehicle any more, can realize the transfer at any time, and is convenient for the improvement of the launching efficiency;
3. the invention uses the general lorry-mounted crane to complete the transshipment work from the transport vehicle to the launcher without using special hoisting equipment, simplifies the number of independent equipment required by the transshipment and the complexity of coordination and cooperation among the equipment, can complete the transshipment work, simplifies the field regulation and control flow and saves the transshipment time and cost.
4. The propellant is filled by using the movable tank car, a fixed propellant filling tank or a filling storehouse is not required to be built on a terrace, the filling equipment is repeatedly utilized in multiple launching tasks, and the manufacturing cost is greatly amortized; in addition, as the filling equipment is changed from fixed to movable, the device does not need to survey and cover related equipment on a launching site in advance, so that the limitation on the site environment of the launching site is greatly reduced, the rocket launching task can be quicker and more flexible, and the launching requirement in the field of commercial aerospace is met.
5. The movable launching equipment placed on the ground of the launching site is used, a fixed launching tower does not need to be built, and a diversion trench does not need to be excavated, so that the launching equipment realizes the repeated utilization of multiple areas and fields on one hand, and a large amount of capital is not needed to be spent on building the fixed launching equipment independently in a certain launching site, thereby greatly saving the cost and time; on the other hand, the launching site of the rocket is flexibly selected according to the factors of the environment, the wind direction, the sunshine and the like of the launching site, so that the window period of rocket launching is greatly prolonged.
6. And movable temperature control equipment is used, and an air conditioner room is not required to be built.
7. After all ground equipment are used, the ground equipment can be automatically transported or transported to other launching stations after being disassembled, and the ground equipment does not depend on a certain fixed launching station.
Drawings
FIG. 1 is a flow chart of the test of the present invention;
FIG. 2 is a diagram of the transport transshipment floor equipment of the present invention;
FIG. 3 is a diagram of the propellant-filled surface equipment of the present invention;
FIG. 4 is a diagram of the launching ground equipment of the present invention;
fig. 5 is a diagram of a temperature control device of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail with reference to the accompanying drawings in combination with the embodiments. It should be understood that the description is intended to be exemplary only, and is not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
The invention is described in further detail below with reference to the figures and the examples.
A first aspect of the invention provides a medium-large low-temperature launch vehicle test system, which comprises: transportation reprints ground equipment, propellant filling ground equipment, launches ground equipment and temperature control equipment.
As shown in fig. 2, the transportation transfer ground device includes: the system comprises a full rocket transfer trolley 11, a full rocket hanger 12 and a lorry-mounted crane 13.
A full arrow transfer trolley 11 for transferring arrow bodies from a technical area to a launch area. The all-arrow transfer trolley 11 comprises a transport flat car which is positioned at the rear part of the all-arrow transfer trolley 11 and is used for bearing and transporting arrow bodies, and the head part of the all-arrow transfer trolley 11 is provided with traction power by a tractor. In the arrow body transfer state, the all-arrow transfer trolley 11 is parked at a position parallel to the launcher 31 in the launch ground equipment, the all-arrow hanger 12 is connected to the arrow body, and the vehicle-mounted crane 13 is used to cooperate with the all-arrow hanger 12 to transfer the arrow body from the all-arrow transfer trolley 11 to the launcher 31 in the launch ground equipment. In general, because the arrow body length is longer, use 2 platform lorry crane to accomplish the work of transshipping.
After the whole rocket transfer work is finished, the whole rocket hanger 12 is retracted, and the whole rocket transfer trolley 11 and the lorry-mounted crane 13 are driven away from the launching field level ground.
As shown in fig. 3, the propellant filling ground equipment comprises a propellant filling vehicle 21, a propellant tank vehicle 22, a propellant filling pipeline 23, a low-temperature propellant filling vehicle 24, a low-temperature propellant tank vehicle 25, a low-temperature propellant filling pipeline 26, a super-cooling agent vehicle 27, a super-cooling device vehicle 28, a gas distribution trolley 29 and a gas supply pipeline (not shown in the figure).
The combustion agent filling vehicle 21, the combustion agent tank vehicle 22 and the combustion agent filling pipeline 23 complete the function of filling the combustion agent. The combustion agent filling vehicle 21 is used for filling combustion agent into a rocket combustion agent storage tank through a pump type or a squeezing type, the combustion agent tank wagon 22 is used for supplying the combustion agent, and a plurality of sections of combustion agent filling pipelines 23 are used for conveying the combustion agent. Several fuel tanker vehicles 22 are used to transport the fuel by road to the launch site, arranged as desired. Liquid outlets of a plurality of combustion agent tank wagons 22 are communicated with a liquid inlet of a combustion agent filling wagon 21 through a combustion agent filling pipeline 23, and a liquid outlet of the combustion agent filling wagon 21 is communicated with a filling port of a rocket combustion agent storage tank through the combustion agent filling pipeline 23. The low-temperature propellant charging vehicle 24, the low-temperature propellant tank wagon 25, the low-temperature propellant charging pipeline 26, the super-cooling agent vehicle 27 and the super-cooling device vehicle 28 complete the low-temperature propellant charging function. The low-temperature propellant filling vehicle 24 is used for filling low-temperature propellant into a rocket low-temperature storage tank in a pump type or extrusion type, the low-temperature propellant tank wagon 25 is used for supplying the low-temperature propellant, and a plurality of sections of low-temperature propellant filling pipelines 26 are used for conveying the low-temperature propellant. Several cryogenic propellant tankers 24 are used to transport cryogenic propellant by road to the launch site, arranged as required. Liquid outlets of a plurality of low-temperature propellant tank wagons 24 are communicated with a liquid inlet of a low-temperature propellant filling wagon 25 through a low-temperature propelling filling pipeline 26, and liquid outlets of the low-temperature propellant filling wagon 24 are communicated with a filling port of a rocket low-temperature propellant storage tank through the low-temperature propelling filling pipeline 26.
The supercooling vehicle 27 is used to deliver the supercooling as a working medium to the supercooler vehicle 28, and the working medium is usually liquid nitrogen. The liquid outlet of the refrigerant passing vehicle 27 transmits the subcooler to the working medium inlet of the subcooler vehicle 28 through a low-temperature pipeline, and the subcooler vehicle 28 cools the low-temperature propellant flowing through by evaporating the working medium, so that the low-temperature propellant is in a subcooled state. Part of the low-temperature propellant flows out from a liquid outlet of the low-temperature propellant filling vehicle 24 and then is shunted, and is led to a liquid inlet of the subcooler vehicle 28 through the low-temperature propellant filling pipeline 26, is further cooled in the subcooler vehicle 28 to be in a subcooled state, and is conveyed to the rocket low-temperature propellant storage tank through the low-temperature propellant filling pipeline 26.
The gas distribution trolley 29 is used to provide the gas used in the filling, typically nitrogen or helium. The gas supply pipeline is used for gas delivery. After the propellant filling work is finished, equipment used for propellant filling is retracted and driven away from a launching field.
As shown in fig. 4, the launching ground equipment includes a launching frame 31, a launching platform 32, and a deflector 33. The launcher 31 is used for erecting the rocket body, the launching platform 32 is used for vertically supporting the rocket body after erecting, and the deflector 33 is used for discharging tail flames discharged by an engine after the rocket is ignited. The launching equipment is withdrawn after the rocket is ignited to take off and can be transferred to other launching stations.
As shown in fig. 5, the temperature control device is used for providing clean air into the rocket fairing, and the air temperature can be adjusted according to the use requirement. The temperature control device comprises an air conditioner main machine 41, a hard air pipe 42, a soft air pipe 43 and a filter box 44. The starting end of the air supply pipeline is connected with an air outlet of the air conditioner main unit, the air supply pipeline comprises a hard air pipe 42 and a soft air pipe 43, the hard air pipe and the soft air pipe are laid towards the head along the tail part of the launching cradle, and are led to the rocket head fairing and are connected with an air inlet of the rocket fairing through the filter box. The air-conditioning host computer is removed from the launching field before launching.
As shown in fig. 1, a second aspect of the present invention provides a method for implementing medium and large-sized low-temperature launch vehicles, where the method includes:
s100, horizontally transporting each sublevel of the rocket into a launching site, unloading in a technical plant of the launching site, horizontally butting each sublevel to finish the general assembly work of the whole rocket, carrying out test work in a horizontal state, and horizontally transferring the rocket to a whole rocket transfer trolley for transporting and transferring ground equipment by using a truss crane of the technical plant after the test is finished;
s200, horizontally transporting the rocket to a launching field by the full rocket transfer trolley, transferring the rocket body to a launching frame by using a full rocket lifting appliance and a lorry-mounted crane, erecting the launching frame, butting the rocket with a launching platform in a vertical state, and supplying air to a fairing by using temperature control equipment according to the requirement of an effective load in a fairing of the rocket;
and S300, a combustion agent filling vehicle fills a combustion agent into the rocket storage tank, a low-temperature propellant filling vehicle fills a low-temperature propellant into the rocket storage tank, the rocket carries out inspection work before launching, the rocket is turned over after a vertical arm is raised, the rocket is ignited to launch, and after the rocket is ignited to launch, the ground equipment is retracted.
Specifically, in step S200, the all-arrow transfer vehicle transfers the arrow body from the technical area to the launch area. The transportation flat car in the full rocket transfer car is used for bearing and transporting the rocket bodies, and the lorry-mounted crane is matched with the full rocket hanger to transfer the rocket bodies from the full rocket transfer car to the launching frame in the launching ground equipment; after the whole arrow transfer work is finished, the whole arrow hanger is withdrawn, and the whole arrow transfer trolley and the lorry-mounted crane are driven away from the launching field platform.
Specifically, in step S200, the temperature control device provides clean air into the rocket fairing, and the air temperature can be adjusted according to the use requirement.
Specifically, in step S300, a combustion agent filling vehicle fills a combustion agent into a rocket combustion agent storage tank in a pump type or extrusion type, a combustion agent tank car supplies the combustion agent, a plurality of sections of combustion agent filling pipelines convey the combustion agent, a plurality of combustion agent tank cars are used for transporting the combustion agent to a launching site through roads, the combustion agent tank cars are arranged as required, and a low-temperature propellant filling vehicle, a low-temperature propellant tank car, a low-temperature propellant filling pipeline, a super-cooling agent vehicle and a super-cooling device vehicle are used for completing the low-temperature propellant filling function.
Specifically, in step S300, a low-temperature propellant filling handle is used for filling the low-temperature propellant into the rocket low-temperature storage tank through a pump type or an extrusion type, a low-temperature propellant tank car is used for supplying the low-temperature propellant, a plurality of sections of low-temperature propellant filling pipelines are used for conveying the low-temperature propellant, and the low-temperature propellant is conveyed to a launching site through a road by using a plurality of low-temperature propellant tank cars and is arranged as required; the supercooler vehicle conveys a supercooled agent to the supercooler vehicle to serve as a working medium, a liquid outlet of the supercooler vehicle conveys the supercooled agent to a working medium inlet of the supercooler vehicle through a low-temperature pipeline, and the supercooler vehicle cools a low-temperature propellant flowing through by evaporating the working medium to enable the low-temperature propellant to be in a supercooled state; and part of the low-temperature propellant flows out of a liquid outlet of the low-temperature propellant filling vehicle and then is distributed, and is led to a liquid inlet of the subcooler vehicle through a low-temperature propellant filling pipeline, is further cooled in the subcooler vehicle to be in a subcooled state, and is conveyed to a low-temperature propellant storage tank of the rocket through a low-temperature propelling filling pipeline.
Specifically, in step S300, the launcher in the launching ground equipment erects and then vertically supports the rocket body, the deflector guides the tail flame exhausted by the engine after the rocket is ignited, and the launching equipment is retracted after the rocket is ignited and takes off and can be transferred to other launching stations.
The transportation process of transporting the whole rocket horizontally to the launching site uses the universal transport vehicle, and a special whole rocket transport vehicle does not need to be developed; a general lorry-mounted crane is used in the process of transferring the launching field rocket to the launching frame, and special hoisting equipment is not needed; in the low-temperature propellant filling process, a mobile filling vehicle, a tank car and a super-cooling agent vehicle are used, and a low-temperature propellant filling tank or a filling storehouse is not required to be built; the launching rack used in the launching process is in butt joint with the launching pad in advance and is debugged, and the launching rack does not need to be in butt joint with the launching pad on the launching day. The temperature control equipment uses movable temperature control equipment, and an air conditioner room does not need to be built. And the filter box is arranged on the launcher and close to the rocket fairing, so that the cleanliness of air blown into the fairing is guaranteed.
The method for realizing the test launch can be used for medium and large-sized low-temperature carrier rockets and meets the requirements of the medium and large-sized low-temperature carrier rockets on quick launch and low cost. The invention uses the general transport vehicle to finish the transfer work of the whole rocket from the technical area to the launching field, does not need to develop a special whole rocket transport vehicle, greatly reduces the cost of rocket launching, does not depend on the special whole rocket transport vehicle any more, can realize the transfer at any time and is convenient for improving the launching efficiency. The invention uses the general lorry-mounted crane to complete the transshipment work of the whole rocket from the transport vehicle to the launching cradle, does not need to use special hoisting equipment, simplifies the number of independent equipment required by the transshipment and the complexity of coordination and coordination among the equipment, can complete the transshipment work, simplifies the field regulation and control flow and saves the transshipment time and cost. The propellant is filled by using the movable tank car, a fixed propellant filling tank or a filling storehouse is not required to be built on the terrace, the filling equipment is recycled in multiple launching tasks, and the manufacturing cost is greatly amortized; in addition, as the filling equipment is changed from fixed to movable, the device does not need to survey and cover related equipment on a launching site in advance, so that the limitation on the site environment of the launching site is greatly reduced, the rocket launching task can be quicker and more flexible, and the launching requirement in the field of commercial aerospace is met. The movable launching equipment placed on the ground of the launching site is used, a fixed launching tower does not need to be built, and a diversion trench does not need to be excavated, so that the launching equipment realizes the repeated utilization of multiple areas and fields on one hand, and a large amount of capital is not needed to be spent on building the fixed launching equipment independently in a certain launching site, thereby greatly saving the cost and time; on the other hand, the launching site of the rocket is flexibly selected according to the factors of the environment, the wind direction, the sunshine and the like of the launching site, so that the window period of rocket launching is greatly prolonged. And movable temperature control equipment is used, and an air conditioner room is not required to be built. After all ground equipment is used, the ground equipment can be automatically transported or disassembled and then transported to other launching stations without depending on a certain fixed launching station.
In conclusion, the invention is applied to medium and large liquid or solid-liquid hybrid rockets, and does not relate to transportation and launching equipment of small rockets and the like. The medium-sized low-temperature carrier rocket launching site in a certain business does not have facilities such as a fixed launching tower and the like, a usable fixed low-temperature propellant filling tank or a filling storehouse, or an air conditioner room, only one launching site is available, and ground equipment can be transported to other launching sites after launching. The method does not need to develop a special full rocket transport vehicle, does not need to use special hoisting equipment, does not depend on a fixed tower, does not depend on a low-temperature propellant filling tank or a filling storehouse, does not need to build an air conditioner room, and can transfer the ground equipment to other launching stations after launching and using.
It is to be understood that the above-described embodiments of the present invention are merely illustrative of or explaining the principles of the invention and are not to be construed as limiting the invention. Therefore, any modifications, equivalents, improvements and the like which are made without departing from the spirit and scope of the present invention shall be included in the protection scope of the present invention. Further, it is intended that the appended claims cover all such variations and modifications as fall within the scope and boundary of the appended claims, or the equivalents of such scope and boundary.
Claims (10)
1. A medium and large-sized low-temperature carrier rocket test launching system is characterized by comprising: transporting and transferring ground equipment, propellant filling ground equipment, launching ground equipment and temperature control equipment;
the transportation and transfer ground equipment is used for transferring the rocket bodies from the technical area to the launching area to complete transfer work;
the propellant filling ground equipment is used for filling fuel agents and propellants;
the launching ground equipment is used for launching the rocket body, withdrawing the rocket body after the rocket body is ignited to take off, and transferring the rocket body to other launching stations;
the temperature control equipment is used for providing clean air for the rocket fairing;
wherein the propellant charging surface equipment and/or launching surface equipment is mobile.
2. The medium to large cryogenic launch vehicle test and launch system of claim 1 wherein the transport transshipment ground equipment comprises: a full-rocket transfer trolley (11), a full-rocket hanger (12) and a lorry-mounted crane (13);
the all-arrow transfer trolley (11) is used for transferring arrow bodies from a technical area to a launching area, the all-arrow transfer trolley (11) comprises a transport flat car, the transport flat car is positioned at the rear part of the all-arrow transfer trolley (11) and used for carrying and transporting the arrow bodies, and the head part of the all-arrow transfer trolley (11) is provided with traction power by a tractor;
in the arrow body transfer state, the whole arrow transfer trolley (11) is parked at a position parallel to a launching rack (31) in launching ground equipment, a whole arrow lifting appliance (12) is connected to the arrow body, and the arrow body is transferred from the whole arrow transfer trolley (11) to the launching rack (31) in the launching ground equipment by using a lorry-mounted crane (13) to be matched with the whole arrow lifting appliance (12).
3. The medium-large low-temperature launch vehicle test and launch system according to claim 1,
the propellant charging ground equipment comprises a propellant charging vehicle (21), a propellant tank car (22), a propellant charging pipeline (23), a low-temperature propellant charging vehicle (24), a low-temperature propellant tank car (25), a low-temperature propellant charging pipeline (26), a super-cooling agent vehicle (27), a super-cooling device vehicle (28), a gas distribution trolley (29) and a gas supply pipeline;
the low-temperature propellant tank car is characterized in that the combustion agent filling car (21) is used for filling combustion agents into a rocket combustion agent storage tank, the combustion agent tank car (22) is used for supplying the combustion agents, the combustion agent filling pipeline (23) is used for conveying the combustion agents, the low-temperature propellant filling car (24) is used for filling low-temperature propellants into the rocket low-temperature storage tank, the low-temperature propellant tank car (25) is used for supplying the low-temperature propellants, the low-temperature propellant filling pipeline (26) is used for conveying the low-temperature propellants, the super-cooling agent car (27) is used for conveying the refrigerants to the super-cooling device car (28), the gas distribution trolley (29) is used for providing gas used in filling, and the gas supply pipeline is used for gas conveying.
4. The medium-large low-temperature carrier rocket test and launch system according to claim 3, wherein a plurality of low-temperature propellant tank car liquid outlets are communicated with a low-temperature propellant filling car liquid inlet through a low-temperature propelling and filling pipeline, and a low-temperature propellant filling car liquid outlet is communicated with a rocket low-temperature propellant storage tank filling port through a low-temperature propelling and filling pipeline;
the liquid outlets of the plurality of combustion agent tank cars are communicated with the liquid inlet of the combustion agent filling car through a combustion agent filling pipeline, and the liquid outlets of the combustion agent filling car are communicated with the filling port of the rocket combustion agent storage tank through a combustion agent filling pipeline.
5. The medium and large-sized low-temperature launch vehicle launching system according to claim 4, wherein the liquid outlet of the cryogen tanker conveys the subcooler to the working medium liquid inlet of the subcooler tanker through a low-temperature pipeline, and the subcooler tanker cools the low-temperature propellant flowing through by evaporating the working medium, so that the low-temperature propellant is in a subcooled state.
6. The launch measuring system for medium and large low-temperature carrier rockets according to claim 5, wherein the low-temperature propellant flows out from a liquid outlet of the low-temperature propellant charging vehicle and then is divided, and the divided flow is led to a liquid inlet of the subcooler vehicle through the low-temperature propellant charging pipeline, is further cooled in the subcooler vehicle to be in a subcooled state, and is then conveyed into the rocket low-temperature propellant storage tank through the low-temperature propellant charging pipeline.
7. The medium or large cryogenic launch vehicle test and launch system of claim 6 wherein the launch ground equipment comprises a launcher, a launch pad, a deflector;
the launcher is used for erecting a vertical arrow body;
the launching platform is used for vertically supporting the arrow body after being erected;
the flow guider is used for discharging tail flame discharged by the engine after the rocket is ignited.
8. A medium-large low-temperature carrier rocket test and launch implementation method is characterized by comprising the following steps:
s100, horizontally transporting each substage of the rocket into a launching field, horizontally butting each substage to complete the general assembly of the rocket, carrying out a test in a horizontal state, and horizontally transferring the rocket to a full rocket transfer trolley of ground transportation and transfer equipment after the test is completed;
step S200, the rocket transfer vehicle horizontally transports the rocket to a launching field, the rocket body is transferred to a launching frame by using a rocket spreader and a lorry-mounted crane, the launching frame is erected, the rocket is in a vertical state and is in butt joint with a launching platform, and air is supplied to a fairing by using temperature control equipment;
and step S300, a combustion agent filling vehicle fills the combustion agent into the rocket storage tank, a low-temperature propellant filling vehicle fills the low-temperature propellant into the rocket storage tank, the rocket is tilted after a vertical arm is lifted, the rocket is ignited and launched, and the combustion agent filling vehicle and the low-temperature propellant filling vehicle are retracted after the rocket is ignited and launched.
9. The method for implementing launch measurement of a medium-large low-temperature carrier rocket as claimed in claim 8, wherein in step S200, the whole rocket transfer vehicle transports the rocket bodies from the technical area to the launching area, the whole rocket transfer vehicle transfers the rocket bodies from the whole rocket transfer vehicle to the launching frame in the launching ground equipment, and after the whole rocket transfer vehicle finishes the launch operation, the whole rocket transfer vehicle drives away from the launching pad.
10. The method for implementing launch test of medium and large-sized low-temperature carrier rockets according to claim 9,
the method is characterized in that in step S300, a combustion agent filling vehicle fills combustion agent into a rocket combustion agent storage box in a pump type or extrusion type mode, a combustion agent tank car supplies the combustion agent, a combustion agent filling pipeline conveys the combustion agent, at least one combustion agent tank car is used for conveying the combustion agent to a launching field, the low-temperature propellant filling vehicle, the low-temperature propellant tank car, the low-temperature propellant filling pipeline, a super-cooling agent vehicle and a super-cooling device vehicle are arranged as required, and the low-temperature propellant filling function is completed;
the low-temperature propellant is filled into the rocket low-temperature storage tank through a pump type or an extrusion type, the low-temperature propellant tank wagon is used for supplying the low-temperature propellant, a plurality of sections of low-temperature propellant filling pipelines are used for conveying the low-temperature propellant, at least one low-temperature propellant tank wagon is used for conveying the low-temperature propellant to a launching field ground, and the low-temperature propellant is arranged as required; the subcooler vehicle is used for conveying a refrigerant to the subcooler vehicle to serve as a working medium, a liquid outlet of the subcooler vehicle is used for conveying the subcooler to a working medium inlet of the subcooler vehicle through a low-temperature pipeline, and the subcooler vehicle is used for cooling a low-temperature propellant flowing through by evaporating the working medium to enable the low-temperature propellant to be in a subcooled state; part of the low-temperature propellant flows out of a liquid outlet of the low-temperature propellant filling vehicle and then is distributed, and the low-temperature propellant flows through a low-temperature propellant filling pipeline to a liquid inlet of the subcooler vehicle, is further cooled in the subcooler vehicle to be in a subcooled state, and is conveyed to a storage tank of the rocket low-temperature propellant through a low-temperature propelling filling pipeline;
the launcher in the launching ground equipment erects and then vertically supports the rocket body, after the rocket is ignited, the deflector guides the tail flame discharged by the engine, and the launching equipment is retracted after the rocket is ignited and takes off.
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| CN202211706989.9A CN115930696A (en) | 2022-12-29 | 2022-12-29 | Medium-large low-temperature carrier rocket test and launch system and implementation method |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205002683U (en) * | 2015-06-23 | 2016-01-27 | 上海航天测控通信研究所 | Adopt carrier rocket power of for military use shelter structure to survey accuse system of sending out |
| CN109630316A (en) * | 2018-12-13 | 2019-04-16 | 西安航天动力研究所 | A kind of dynamical system for carrier rocket Upper Stage and orbit transfer vehicle |
| CN110953940A (en) * | 2018-12-20 | 2020-04-03 | 中国人民解放军63921部队 | Method for assembling, erecting and withdrawing binding type carrier rocket |
| CN113154944A (en) * | 2021-04-29 | 2021-07-23 | 贵州航天天马机电科技有限公司 | Carrier rocket erection launching system without supporting transportation |
| CN113336080A (en) * | 2021-06-17 | 2021-09-03 | 星河动力(北京)空间科技有限公司 | Hoisting device and hoisting method for carrier rocket |
| CN113443174A (en) * | 2021-07-28 | 2021-09-28 | 格兰立方能源科技(江苏)有限公司 | Mobile rocket fairing blowing-off constant temperature and humidity device |
| CN114459287A (en) * | 2021-08-30 | 2022-05-10 | 北京天兵科技有限公司 | Ground launching system and method for medium-sized liquid carrier rocket |
-
2022
- 2022-12-29 CN CN202211706989.9A patent/CN115930696A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205002683U (en) * | 2015-06-23 | 2016-01-27 | 上海航天测控通信研究所 | Adopt carrier rocket power of for military use shelter structure to survey accuse system of sending out |
| CN109630316A (en) * | 2018-12-13 | 2019-04-16 | 西安航天动力研究所 | A kind of dynamical system for carrier rocket Upper Stage and orbit transfer vehicle |
| CN110953940A (en) * | 2018-12-20 | 2020-04-03 | 中国人民解放军63921部队 | Method for assembling, erecting and withdrawing binding type carrier rocket |
| CN113154944A (en) * | 2021-04-29 | 2021-07-23 | 贵州航天天马机电科技有限公司 | Carrier rocket erection launching system without supporting transportation |
| CN113336080A (en) * | 2021-06-17 | 2021-09-03 | 星河动力(北京)空间科技有限公司 | Hoisting device and hoisting method for carrier rocket |
| CN113443174A (en) * | 2021-07-28 | 2021-09-28 | 格兰立方能源科技(江苏)有限公司 | Mobile rocket fairing blowing-off constant temperature and humidity device |
| CN114459287A (en) * | 2021-08-30 | 2022-05-10 | 北京天兵科技有限公司 | Ground launching system and method for medium-sized liquid carrier rocket |
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