CN214729796U - Be used for carrier rocket driving system to try on and launch facility - Google Patents
Be used for carrier rocket driving system to try on and launch facility Download PDFInfo
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- CN214729796U CN214729796U CN202120057206.3U CN202120057206U CN214729796U CN 214729796 U CN214729796 U CN 214729796U CN 202120057206 U CN202120057206 U CN 202120057206U CN 214729796 U CN214729796 U CN 214729796U
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Abstract
The invention provides a test run and launch facility for a carrier rocket power system. Should be used for carrier rocket driving system to try on and launch the facility and include: diversion trench, stage body and spray tube. The platform body is arranged at the inlet of the diversion trench and is provided with a fixed end and a support end, the fixed end is fixedly arranged on the ground, the support end is used for supporting the carrier rocket to operate under various working conditions, and the spray pipes are arranged along the circumferential direction of the platform body and correspond to the injection ends of the carrier rocket and are used for laterally spraying cooling liquid to injection flames. The carrier rocket power system test run and launch facility provided by the invention has the advantages of simultaneously meeting the requirements of supporting carrier rocket launch and test run, saving stations and cost and the like.
Description
Technical Field
The invention relates to the technical field of carrier rockets, in particular to a device for trial run and launch of a carrier rocket power system.
Background
The rocket launching pad is a ground launching facility for launching a carrier rocket, and can meet the requirements of erecting and releasing the carrier rocket. The test bed is a ground facility for the carrier rocket to test the power system, and can meet the test ignition of each test stage of the carrier rocket. The existing launching pad and the test run pad can not simultaneously take into account launching and test run working conditions, the power system test run and the rocket launching of a carrier rocket are respectively completed on the test run pad and the launching pad, and the test run pad and the launching pad are respectively designed and built, so that the construction cost is high, the construction period is long, the repeated construction and the repeated investment are the most important problems in the prior art, and therefore, the ground facility which takes into account the test run and the rocket launching of the rocket power system is urgently needed to be provided.
Disclosure of Invention
Aiming at the technical problems in the related art, the invention provides a carrier rocket power system test run and launch facility, which has the advantages of simultaneously supporting the launch and test run of a carrier rocket, saving stations and cost and the like. The problem that the same ground facility cannot be used for rocket launching and test run is solved, repeated construction and repeated investment are avoided, and huge construction cost is saved.
The invention provides a test run and launch facility for a carrier rocket power system. Should be used for carrier rocket driving system to try on and launch the facility and include: diversion trench, stage body and spray tube. The diversion trench is arranged below the ground and is provided with a diversion trench inlet, a diversion trench outlet and a diversion trench internal channel; the platform body is arranged at the inlet of the diversion trench and is provided with a fixed end and a supporting end, the fixed end is fixedly arranged on the ground, and the supporting end is used for supporting the carrier rocket to operate under various working conditions; and the spray pipes are arranged along the circumferential direction of the platform body, are arranged corresponding to the injection ends of the carrier rocket and are used for spraying cooling liquid to the injection flames from the side direction.
The supporting end is used for supporting rocket launching or rocket power system test run, when the rocket is launched, the jet pipe is closed, the rocket is gradually lifted off after being separated from the platform body after being ignited, the flame sprayed into the diversion trench is gradually reduced until the flame disappears, the ablation time of the diversion trench is short, and the jet pipe is not required to spray cooling liquid to cool the flame. When the ground facility is used for rocket power system test, the test run time is long, the test run time is 200-1000 seconds different, the diversion trench is easy to damage due to long-time ablation, and then the spray pipe arranged in the circumferential direction of the platform body is opened.
In one embodiment, the supporting end of the table body is provided with a supporting interface for supporting the carrier rocket to be launched, the supporting interface is used for being in matched butt joint with the rocket feet of the carrier rocket to be launched, and the number of the supporting interfaces is correspondingly set according to the number and the position relation of the rocket feet of the carrier rocket to be launched.
In one embodiment, the supporting end of the platform body is provided with a first annular flange for fixing the carrier rocket to be tested, and the first annular flange is matched with a second annular flange arranged on the carrier rocket to be tested, so that the carrier rocket to be tested is firmly fixed on the platform body, and the carrier rocket is prevented from being separated from the platform body during test run.
In one embodiment, the inlet of the diversion trench is provided with an inclined surface facing to the outlet side, and the inclined surface is a straight inclined surface close to the inlet side of the diversion trench, so that flame directly enters the diversion trench; the outlet side of the inclined plane close to the diversion trench is a curved inclined plane, so that flame gradually changes the impact direction to enter the internal channel of the diversion trench and is finally discharged from the outlet of the diversion trench.
In one embodiment, the straight inclined plane has an angle of 30 degrees with the direction of gravity, so that the flame sprayed by the carrier rocket is transferred to the inner channel of the diversion trench and is discharged from the outlet of the diversion trench.
In one embodiment, the flame impact surface of the diversion trench is made of anti-ablation concrete and has a thickness of 20 cm to 35 cm, so that the long-time flame ablation of the test run of the power system of the carrier rocket is fully adapted.
In one embodiment, the jet pipe is detachably arranged on the platform body, the vertical distance between the jet pipe and the injection end of the carrier rocket is 0.9-1.2 meters, and the coolant is timely and laterally injected to the flame of the carrier rocket through the jet pipe, so that the flame of the carrier rocket is cooled.
In one embodiment, the lance has a spray head that is oriented obliquely downward from the flame to increase the contact area of the coolant with the flame.
In one embodiment, the included angle between the nozzle of the nozzle and the central axis of the carrier rocket arranged on the platform body is 45 degrees.
In one embodiment, the fixed end of the platform body is fixedly connected with the ground in an anchor bolt connection mode, so that the platform body is prevented from being driven to be separated from the ground when the launch vehicle performs a power system test.
In one embodiment, the inner channel of the diversion trench is arranged as an inclined plane near the exit of the diversion trench to ensure that the flame is discharged in a direction away from the carrier rocket.
According to the facility for the test run and the launching of the power system of the carrier rocket, provided by the embodiment of the invention, the supporting structure of the platform body is improved, the spray pipes capable of spraying the cooling liquid are added, and the structure of the diversion trench is improved, so that the launch of the carrier rocket and the test run of the power system can be carried out on the same station without independent construction, only the mechanical structure and the opening and closing of the spray pipes are required to be adjusted, the investment of fixed assets can be greatly saved, the construction projects of the test run station and the launching station are reduced, and raw materials and processes are saved. In addition, the launching facility provided by the embodiment is beneficial to reducing the technical barriers, shortening the technical coordination chain and improving the connection fluency of different links of rocket development by integrating the test run of the rocket engine and the rocket launching.
Those skilled in the art will recognize additional features and advantages upon reading the detailed description, and upon viewing the accompanying drawings.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a schematic diagram of the overall architecture of a commissioning and launch facility for a launch vehicle power system according to an embodiment of the present invention.
Fig. 2 is a schematic structural diagram of a flow guide groove according to an embodiment of the present invention.
Fig. 3 is a schematic structural view of a nozzle according to an embodiment of the present invention.
Detailed Description
The technical scheme of the invention is further explained by the specific implementation mode in combination with the attached drawings. Spatially relative terms such as "below," "… below," "lower," "above," "… above," "upper," and the like are used for convenience in describing the positioning of one element relative to a second element and are intended to encompass different orientations of the device in addition to different orientations than those illustrated in the figures. Further, for example, the phrase "one element is over/under another element" may mean that the two elements are in direct contact, or that there is another element between the two elements. Furthermore, terms such as "first", "second", and the like, are also used to describe various elements, regions, sections, etc. and should not be taken as limiting. Like terms refer to like elements throughout the description.
The utility model provides a be used for carrier rocket driving system to try on and launch facility. Referring to fig. 1, the utility model discloses a be used for carrier rocket driving system to try on and launch facility includes: diversion trench 1, stage body 2 and spray tube 3. The guide groove 1 is arranged below the ground and is provided with a guide groove inlet 11, a guide groove outlet 12 and a guide groove internal passage 13, and the flame sprayed by the carrier rocket enters through the guide groove inlet 11 and passes through the guide groove internal passage 13 and is finally discharged from the guide groove outlet 12. The platform body 2 is arranged at the inlet 11 of the diversion trench and is provided with a fixed end 21 and a supporting end 22, the fixed end 21 is fixedly arranged on the ground or the diversion trench 1, and the supporting end 22 is used for supporting the carrier rocket R to execute various working conditions. The jet pipes 3 are arranged along the circumferential direction of the platform body 2, are arranged corresponding to the jetting end of the carrier rocket R and are used for jetting cooling liquid to the jetting flame from the side direction.
The supporting end of the platform body is used for supporting launch of the carrier rocket or supporting test run of a power system of the carrier rocket. When the rocket is launched, the spray pipe can be closed, the rocket is ignited and gradually ascends to the air after being separated from the platform body, so that the flame sprayed into the diversion trench is gradually reduced until the flame disappears, the ablation time of the flame of the carrier rocket to the diversion trench is short, and the spray pipe is not needed to spray cooling liquid to cool the flame. And when carrying out rocket driving system test through the ground facility of this application, because the time of taking a trial run is long, is 200 seconds to 1000 seconds usually, so long-time ablation easily causes the guiding gutter to damage, and then needs to make the spray tube that sets up in stage body circumference and open to spout by the spray tube and annotate the coolant liquid and cool down flame. Because the jet flow speed of the rocket engine is extremely high, the cooling liquid is difficult to jet into the flame, most of the cooling liquid can be brought into the guide groove by the flame, and the cooling liquid cools the flame along with the advancing process of the flame, so that the temperature of the flame impacting on the surface of the ablation-resistant concrete is reduced.
In one embodiment, in order to meet the launching requirements of the carrier rocket, the supporting end of the platform body is provided with a supporting interface for supporting the carrier rocket to be launched, the supporting interface is used for being in matched butt joint with the rocket feet of the carrier rocket to be launched, and the number of the supporting interfaces is correspondingly set according to the number and the position relation of the rocket feet of the carrier rocket to be launched. For example, the carrier rocket has four rocket legs, and the support end is correspondingly provided with four support interfaces, so that the carrier rocket can be erected and reliably supported.
Further, in order to meet the test-run requirement of a carrier rocket power system and avoid the carrier rocket from separating from the platform body, a first annular flange for fixing the carrier rocket to be tested is arranged at the supporting end of the platform body and is used for being matched with a second annular flange arranged on the carrier rocket to be tested, the first annular flange and the second annular flange are fixedly connected through bolts, the carrier rocket to be tested is guaranteed to be vertically fixed on the platform body, and the carrier rocket is prevented from separating from the platform body during test-run. The specific number and specification of the bolts can be calculated according to the weight and the thrust of the rocket.
The utility model discloses a be used for carrier rocket driving system to try on and launch facility, through the butt joint structure that the support end at the stage body designs respectively and is used for rocket transmission and rocket driving system to try on with the function set of launch pad and test bed on a station, can stay the rocket system after the ignition at the stage body when trying on promptly, can release the rocket when the transmission.
Referring to fig. 2, in one embodiment, the gutter inlet 11 has an inclined surface facing the outlet side, the side of the inclined surface near the gutter inlet 11 being a straight inclined surface to ensure that the flame can enter the gutter directly, and the side of the inclined surface near the gutter outlet 12 being a curved inclined surface to ensure that the flame can gradually turn its direction of impact and enter the gutter internal passage and finally exit the gutter outlet. The inlet of the diversion trench is an inclined plane, the inner channel of the diversion trench is a plane, and a curved surface is arranged between the inclined plane and the plane for transition butt joint, so that the impact force of flame in the steering process can be reduced, and the damage to the inner wall above the diversion trench is avoided.
Specifically, as a preferred embodiment, the included angle between the straight inclined plane and the gravity direction may be set to 30 degrees, so as to sufficiently ensure that the flame sprayed by the carrier rocket is gradually transferred to the inner channel of the diversion trench and finally discharged from the outlet of the diversion trench.
Further, in order to prevent the flame in the inner channel 13 of the guiding gutter from flowing back to the inlet 11 of the guiding gutter to cause the arrow ablation, a baffle plate can be arranged on the inner wall of the upper end of the inner channel 13 of the guiding gutter, close to the inlet end of the guiding gutter, and the baffle plate can effectively block the flame from flowing back.
In order to enable the flame to be discharged rapidly, the flame can be simultaneously guided out by arranging a plurality of guide groove outlets so as to increase the discharge efficiency of the flame.
In one embodiment, the flame impact surface of the diversion trench is made of anti-ablation concrete, the thickness of the flame impact surface is 20 cm-35 cm, and the flame impact surface can be fully suitable for long-time flame ablation of a carrier rocket power system test run. Specifically, in order to ensure that the diversion trench can withstand long-time ablation in the test run of the rocket power system and save the construction cost of the diversion trench, as a preferred embodiment, the flame impact surface of the diversion trench can be prepared by using 30 cm-thick anti-ablation concrete.
Meanwhile, because the reliability of the engine in the test run of the rocket power system is prolonged by 1000 seconds, that is, the diversion trench needs to be subjected to thermal ablation for 1000 seconds, in order to effectively cool the flame and slow down the ablation degree of the flame to the diversion trench, the distance between the lower bottom surface of the inner channel of the diversion trench and the ground can be set to be 14 meters or 14.5 meters. The cooling liquid in the spray pipe continuously cools the flame along with the flame until the flame is completely vaporized, and the distance of 14 meters to 14.5 meters in the embodiment can further reduce the temperature of the flame.
In the above embodiments, the flame impact surface of the guiding groove may also be made of a steel plate.
In one embodiment, because the thrust of each rocket is different and the impact force of the ejected flame is different, the actual position of the nozzle can be set according to the thrust of the rocket, so that the position of the nozzle is different every time. For example, can make the spray tube detachably set up in the stage body, not only be convenient for the adjustment position in order to adapt to the operating mode of different thrust carrier rockets, still make things convenient for the maintenance and the maintenance in later stage. Specifically, the vertical distance between the spray pipe and the injection end of the carrier rocket can be adjusted between 0.9 meter and 1.2 meters according to thrust calculation of various types of carrier rockets, so that the cooling liquid can be timely and laterally injected to the flame of the carrier rocket through the spray pipe, and the flame of the carrier rocket is timely cooled.
Specifically, in the trial run and launch facility provided by the embodiment of the invention, the plurality of spray pipes are arranged around the platform body and are arranged on the platform body in a flange connection or hoop connection mode, and when the positions of the spray pipes need to be changed, the positions of the spray pipes can be changed by loosening the connection relationship between the spray pipes and the platform body and shifting.
Referring to fig. 3, in an embodiment, the nozzle 3 has a nozzle 31, and the nozzle 31 is disposed toward an oblique lower side of the flame, so that on one hand, the coolant can be effectively prevented from splashing on the injection port of the carrier rocket, and on the other hand, the contact area between the coolant and the flame can be increased, thereby improving the cooling efficiency.
For example, one nozzle 3 may be provided along the circumferential direction of the stage body, the nozzle 3 may have a plurality of nozzles 31, and the nozzles 31 may be provided in an obliquely downward direction, so that the plurality of nozzles 31 may be simultaneously opened to inject the coolant obliquely downward from the outside of the flame to the outside of the flame during the test of the rocket power system, thereby achieving the effect of reducing the temperature. Alternatively, a plurality of nozzles 3 may be arranged along the circumferential direction of the stage body, and each nozzle 3 has one nozzle head 31 to increase the injection pressure of each nozzle head.
As a preferred embodiment, the spray head of the spray pipe is obliquely arranged downwards and forms an included angle of 45 degrees with the central axis of the carrier rocket arranged on the platform body.
Referring to fig. 1, in one embodiment, the guiding gutter 1 is located below the ground 0-0 plane and is a reinforced concrete structure, and the fixed end 21 of the platform body 2 is fixedly connected with the guiding gutter 1 by an anchor bolt connection manner so as to prevent the platform body from being separated from the ground when the launch vehicle performs a power system test, wherein the number of the anchor bolts is calculated according to the launch weight of the launch vehicle, the launch thrust and the wind load.
In one embodiment, to prevent the flames and hot gases discharged through the exit of the guiding gutter from affecting the normal operation of the rocket, the inner channel of the guiding gutter near the exit of the guiding gutter may be set as an inclined plane, so that the flames are discharged in a direction away from the carrier rocket.
In the above embodiment, the cooling liquid ejected from the conduit may be water or liquid nitrogen. For example, the cooling liquid sprayed out of the conduit is water, fire-fighting water can be communicated to the spray pipe, and the fire-fighting water is utilized to realize thermal protection on test run of the rocket power system.
The above embodiments may be combined with each other with corresponding technical effects.
The device for the test run and the launching of the power system of the carrier rocket, provided by the invention, can realize that the launch of the carrier rocket and the test run of the power system are carried out on the same station, and the launching device and the test run device do not need to be independently constructed, so that the investment of fixed assets can be greatly saved, the construction projects of the test run station and the launching station are reduced, and raw materials and working procedures are saved. Power trial run and rocket launching in the rocket development stage are integrated into a ground system, so that the technical barriers are reduced, and the technical coordination chain is shortened.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (10)
1. A facility for commissioning and launching a launch vehicle power system, comprising:
the diversion trench is arranged below the ground and is provided with a diversion trench inlet, a diversion trench outlet and a diversion trench internal channel;
the platform body is arranged at the inlet of the diversion trench and is provided with a fixed end and a supporting end;
the spray pipes are arranged along the circumferential direction of the platform body, correspond to the injection ends of the carrier rocket and are used for laterally spraying cooling liquid to the injection flames;
the supporting end is used for supporting rocket launching or supporting engine test run, the spray pipe is closed when the rocket launching is carried out, and the spray pipe is opened when the engine test run is carried out, so that the temperature reduction of the engine test run process is realized.
2. The facility for commissioning and launching a launch vehicle power system of claim 1 wherein said support end has a support interface for supporting a launch vehicle to be launched, said support interface for mating docking with a launch foot of the launch vehicle to be launched.
3. The launch vehicle powertrain system test and launch facility of claim 1 wherein the support end has a first annular flange for securing a launch vehicle to be tested; the first annular flange is matched with a second annular flange arranged on the carrier rocket to be tested, and the carrier rocket to be tested is fixed on the platform body.
4. The launch vehicle power system test run and launch facility of claim 1 wherein said guideway entrance has an inclined plane facing an exit side, said inclined plane being a straight inclined plane adjacent said guideway entrance side and said inclined plane being a curved inclined plane adjacent said guideway exit side.
5. The launch vehicle power system commissioning and launching facility of claim 4, wherein said straight incline is angled 30 degrees from the direction of gravity to deliver the rocket jet flames to said guideway interior passage and out of said guideway exit.
6. The launch vehicle power system test run and launch facility of claim 1 wherein said flow-directing trench flame impingement surface is fabricated from ablation resistant concrete and has a thickness of between 20 cm and 35 cm.
7. The launch vehicle power system commissioning and launching facility of claim 1, wherein said nozzle is removably positioned on said platform, said nozzle being positioned at a vertical distance of between 0.9 m and 1.2 m from the launch vehicle injection end to ensure timely lateral injection of coolant through said nozzle to cool the launch vehicle flame.
8. The launch vehicle power system commissioning and launching facility of claim 7, wherein said nozzle has a spray head positioned obliquely downward toward the flame to increase the contact area of the coolant with the flame.
9. The facility as claimed in claim 1, wherein the platform is fixed to the ground by an anchor bolt to prevent the platform from being detached from the ground during the test of the power system of the launch vehicle.
10. The launch vehicle power system commissioning and launching facility of claim 1, wherein said guideway internal passage is configured as a slanted plane proximate to said guideway exit to ensure that the flame is discharged away from the launch vehicle.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120057206.3U CN214729796U (en) | 2021-01-11 | 2021-01-11 | Be used for carrier rocket driving system to try on and launch facility |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202120057206.3U CN214729796U (en) | 2021-01-11 | 2021-01-11 | Be used for carrier rocket driving system to try on and launch facility |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116280292A (en) * | 2023-02-20 | 2023-06-23 | 北京坤飞装备科技有限公司 | Integral steel slag diversion cone and preparation method thereof |
-
2021
- 2021-01-11 CN CN202120057206.3U patent/CN214729796U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116280292A (en) * | 2023-02-20 | 2023-06-23 | 北京坤飞装备科技有限公司 | Integral steel slag diversion cone and preparation method thereof |
| CN116280292B (en) * | 2023-02-20 | 2024-01-23 | 北京坤飞装备科技有限公司 | Integral steel slag diversion cone and preparation method thereof |
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