CN209875952U - Dynamic sealing device suitable for high speed and high pressure and aircraft - Google Patents
Dynamic sealing device suitable for high speed and high pressure and aircraft Download PDFInfo
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- CN209875952U CN209875952U CN201920314692.5U CN201920314692U CN209875952U CN 209875952 U CN209875952 U CN 209875952U CN 201920314692 U CN201920314692 U CN 201920314692U CN 209875952 U CN209875952 U CN 209875952U
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Abstract
The utility model relates to a sealed technical field, concretely relates to be suitable for high-speed high pressure to use dynamic seal device and airborne vehicle. The dynamic sealing device comprises a sealing shell and two cavities which are spaced to form a seal, and the sealing shell is provided with a through hole for communicating the two cavities; the rotating shaft can rotate and at least partially penetrates through the through hole; the liquid seal wheel is arranged on the rotating shaft, rotates along with the rotation of the rotating shaft and can form liquid seal with the sealing shell when rotating; and the heat-insulating sealing ring, the setting is between pivot and seal housing, and close on the setting of liquid seal wheel, and form the combined seal with the liquid seal wheel, and then high-speed pivoted pivot makes the liquid seal wheel form the liquid seal between seal housing and pivot, can play a retardation to high pressure, the heat-insulating sealing ring can play an interval effect to the high temperature, greatly reduced the high temperature to whole dynamic seal device's influence, and then at high rotational speed, high pressure, the great abominable operating mode such as temperature gradient has promoted dynamic seal device's reliability and life under the abominable operating mode.
Description
Technical Field
The utility model relates to a sealed technical field, concretely relates to be suitable for high-speed high pressure to use dynamic seal device and airborne vehicle.
Background
At present, the rocket engine enters the trend of the great development of commercial aerospace in the world, and the rocket engine with high reliability, low cost, repeated use and no pollution becomes the development direction of the liquid rocket engine. The liquid oxygen methane engine in the rocket has the advantages of good cooling performance, high combustion efficiency, difficult coking and higher specific impulse than a liquid oxygen kerosene engine, and the unit mass of methane fuel only has 1/3 of kerosene and 1/30 of liquid hydrogen, thereby obtaining wider application in the field of aerospace.
The methane pump is used as an important component of the liquid oxygen methane engine and is used for conveying low-temperature liquid methane required by the operation of the engine, and the methane pump is arranged close to the turbine cavity. Usually, a set of sealing device is arranged between a liquid rocket engine pump and a turbine, so that a medium side of the engine pump and a turbine cavity form sealing, the sealing device is influenced by high temperature generated by fuel combustion in the turbine cavity, and the temperature difference between the medium side of the sealing position and the turbine cavity is larger than or equal to 600K, so that the conventional sealing device cannot be applied. In contrast, in the prior art, there are two main types of seals used at home and abroad in a high-pressure and high-speed environment:
a non-contact seal, its principle is to adopt the local clearance of maze to realize reducing pressure and sealing step by step, such as floating ring, labyrinth seal, etc., the seal structure of this kind is simple, but the sealing performance is unsatisfactory, the leakage quantity of medium is greater while working, in order to improve the reliability of seal, still need to increase the high-pressure blowing system additionally;
the other type is a contact type mechanical seal, the principle is that an elastic element is utilized to enable a friction pair to be tightly attached to realize sealing, the sealing structure is mature, static sealing can be realized, and the leakage amount of a medium is small during dynamic work. However, the sealing device has the defects that the abrasion loss of a sealing surface of a friction pair is large in the starting and shutdown processes, and after the sealing device is used for many times, the sealing performance is reduced, even the sealing device fails, so that the sealing device can not meet the requirements of long service life, high reliability and repeated use of a turbine pump under severe working conditions of high rotating speed, ultrahigh pressure, large temperature gradient and the like.
SUMMERY OF THE UTILITY MODEL
A primary object of the utility model is to provide a sealing device and airborne vehicle to solve or alleviate among the prior art sealing device can't satisfy long-life, high reliability and used repeatedly's problem under the abominable operating mode such as high rotational speed, high pressure, temperature gradient are big at least.
In order to achieve the above object, the utility model provides a be suitable for high-speed high pressure to include with dynamic seal device:
the sealing shell is provided with a through hole communicated with the two cavities;
the rotating shaft can rotate and at least partially penetrates through the through hole;
the liquid seal wheel is arranged on the rotating shaft, rotates along with the rotation of the rotating shaft and can form liquid seal with the seal shell during rotation; and
and the heat insulation sealing ring is arranged between the rotating shaft and the sealing shell, is close to the liquid sealing wheel and forms combined sealing with the liquid sealing wheel.
Furthermore, the two cavities comprise a high-temperature cavity and a high-pressure cavity, the heat insulation sealing ring is close to the high-temperature cavity, and the liquid sealing wheel is close to the high-pressure cavity.
Further, the heat-insulating sealing ring comprises a graphite ring mounted on the rotating shaft.
Further, the number of graphite rings is two.
Furthermore, the dynamic sealing device also comprises a compensating piece sleeved outside the heat insulation sealing ring, and the compensating piece has a pre-pressing force for enabling the heat insulation sealing ring to contract inwards.
Furthermore, the compensation piece is a tension spring sleeved outside the heat insulation sealing ring.
Further, the dynamic sealing device also comprises a clearance adjusting piece arranged on the side edge of the heat insulation sealing ring.
Furthermore, the sealing blades in the liquid sealing wheel are arc-shaped and inclined along the radial direction.
Furthermore, one side of the liquid seal wheel is in clearance fit with a bearing arranged on the rotating shaft, and the other side and the outer circle of the liquid seal wheel are in clearance fit with the seal shell.
Further, the gap range is between 0.2 mm and 0.5 mm.
Further, the dynamic sealing device suitable for high speed and high pressure further comprises a gas blowing structure, and a channel communicated with the gas blowing structure is formed in the heat insulation sealing ring.
Further, the sealing device is used for sealing the medium side and the turbine cavity, and one end of the rotating shaft is communicated with the turbine cavity and can rotate along with the rotation of the turbine in the turbine cavity.
The utility model also provides an aircraft, including being suitable for high-speed high pressure to use the dynamic seal device, be suitable for high-speed high pressure to use the dynamic seal device to be as above be suitable for high-speed high pressure to use the dynamic seal device.
Further, the aircraft is a rocket.
The utility model discloses technical scheme has following advantage:
1. the utility model provides a be suitable for in high-speed high pressure is with dynamic seal device and airborne vehicle, at high rotational speed, ultrahigh pressure, under the abominable operating mode such as temperature gradient is big, liquid seal wheel and thermal-insulated sealing ring form the combination formula sealed, high-speed pivoted pivot makes liquid seal wheel form the liquid seal between seal shell and pivot, can play a retardation to the high pressure, the rotational speed is higher, the retardation to the high pressure is stronger more, and then greatly reduced the impact of high pressure to whole dynamic seal device, and between pivot and seal shell, and close on the thermal-insulated sealing ring that liquid seal wheel set up and can play a space effect to the high temperature, greatly reduced the influence of high temperature to whole dynamic seal device, and then at high rotational speed, high pressure, dynamic seal device's reliability and life have been promoted under the abominable operating mode such as temperature gradient is big.
2. The utility model provides a be suitable for in high-speed high-pressure dynamic seal device and airborne vehicle, dynamic seal device still establishes the compensator outside the graphite ring including the cover, the compensator has the packing force in advance that makes the graphite ring internal contraction, and then make the graphite ring when satisfying sealed front and back temperature interval, it is strong to systematic structure deformation and rotor adaptability of beating, and after split type graphite ring hole rotates the wearing and tearing because of the pivot is high-speed, graphite ring can automatic compensation under extension spring effort, guarantee that its performance of graphite ring does not reduce after repetitious usage, satisfy the requirement of engine used repeatedly, make dynamic seal device's reliability better, be applicable to the high environment of part requirement such as rocket.
3. The utility model provides an in being suitable for high-speed high pressure to use dynamic seal device and aircraft, be provided with clearance adjustment spare on the side of graphite ring, concrete clearance adjustment spare is the spring, the setting is between two graphite rings, and then at the turbine of rocket in the start-up process, sealed shell or baffle take place the thermal deformation, clearance adjustment spare can play a clearance adjustment effect, avoid the graphite ring to become invalid by the crushing, further promoted the dynamic seal device reliability under high temperature high pressure service environment, the reliable operation of rocket has been guaranteed.
4. The utility model provides an in being suitable for high-speed high pressure to use dynamic seal device and aircraft, the sealing blade shape in the liquid seal wheel is circular-arc, along the slope of circumference direction, compare with current conventional linear type blade like this, this liquid seal wheel is sealed the in-process and can form the effort of a circumference direction, sealing performance is stronger, the relative linear type blade of step-down ability can 50% improve to 80%, has better step-down effect, make dynamic seal device in this embodiment more be applicable to high pressure environment.
5. The utility model provides an in being suitable for high-speed high pressure to use dynamic seal device and aircraft, one side of liquid seal wheel with install in the epaxial bearing clearance fit of rotating, the opposite side and excircle and the seal housing clearance fit of liquid seal wheel, liquid seal wheel and seal housing clearance fit, for non-contact is sealed, and then make the liquid seal wheel do not have wearing and tearing in the course of the work, longe-lived, the reliability is high, satisfies the requirement of engine used repeatedly.
6. The utility model provides an in being suitable for high-speed high pressure to use dynamic seal device and airborne vehicle, the liquid seal wheel is perhaps askew to be in the clearance scope between 0.2 ~ 0.5mm with the bearing, and then can control the medium pressure of the sealed internal diameter department of liquid seal wheel effectively.
7. The utility model provides a be suitable for in high-speed high pressure is with dynamic seal device and airborne vehicle, have on the heat-proof sealing ring with the passageway of gas blowdown structure intercommunication because the liquid seal wheel has good pressure-proof effect for gas pressure is less than medium pressure 0.03 ~ 0.05MPa, guarantees that the medium leaks the volume and does not exceed 5g/s, and liquid seal wheel and split type graphite ring combination formula are sealed, compact structure, and process gas stops the air feed at engine working process, and the system reduces with a wide margin with tolerance.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the technical solutions in the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts. In the drawings:
fig. 1 is a schematic sectional structure diagram of a dynamic sealing device in an embodiment of the present invention.
Fig. 2 is a schematic cross-sectional structural view of a liquid seal wheel in the dynamic sealing device shown in fig. 1.
Fig. 3 is a front view of a liquid seal wheel in the dynamic sealing device shown in fig. 1.
Wherein the reference numerals in the above figures are:
1. liquid seal wheel; 15. a seal blade; 2. a tension spring; 4. sealing the housing; 6. a graphite ring; 7. a baffle plate; 8. a shaft sleeve; 10. a gap adjusting member; 11. a bearing; 12. a rotating shaft; 13. and a gas blowing structure.
Detailed Description
The technical solution of the present invention will be described clearly and completely with reference to the accompanying drawings, and obviously, the described embodiments are some, but not all embodiments of the present invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
The dynamic sealing device suitable for high speed and high pressure in the embodiment is particularly applied between a methane pump and a turbine of a liquid rocket engine and used for sealing a cavity for storing two media, namely low-temperature liquid methane and high-temperature turbine working medium.
Of course, the dynamic sealing device in this embodiment is not limited to be applied to rockets, and may also be applied to rotating devices in the fields of aviation, weaponry and the like which are suitable for high speed and high pressure.
Specifically, as shown in fig. 1 to 3, the dynamic sealing device suitable for high speed and high pressure in this embodiment includes a sealing housing 4, two cavities to be sealed are separated, and a through hole communicating the two cavities is formed on the sealing housing 4; a rotating shaft 12 which is rotatable and at least partially arranged through the through hole; the liquid seal wheel 1 is arranged on the rotating shaft 12, rotates along with the rotation of the rotating shaft 12 and can form liquid seal with the seal shell 4 during rotation; and the heat insulation sealing ring is arranged between the rotating shaft 12 and the sealing shell 4, is arranged close to the liquid seal wheel 1, and forms combined sealing with the liquid seal wheel 1. Further, by adopting the dynamic sealing device in the embodiment, under severe working conditions of high rotating speed, ultrahigh pressure, large temperature gradient and the like, the liquid seal wheel 1 and the heat insulation sealing ring form combined sealing, the liquid seal wheel 1 forms liquid seal between the sealing shell 4 and the rotating shaft 12 through the rotating shaft 12 rotating at high speed, a blocking effect on high pressure can be achieved, the higher the rotating speed is, the stronger the blocking effect on high pressure is, further the impact of the high pressure on the whole dynamic sealing device is greatly reduced, and between the rotating shaft 12 and the sealing shell 4, the heat insulation sealing ring arranged close to the liquid seal wheel 1 can play a role in separating high temperature, the influence of high temperature on the whole dynamic sealing device is greatly reduced, and further the reliability and the service life of the dynamic sealing device are improved under severe working conditions of high rotating speed, high pressure, large temperature gradient and the like.
Specifically, two cavitys in this implementation include a high temperature cavity and a high pressure cavity, and the medium side in the rocket is the high pressure cavity, and the turbine chamber in the rocket is the high temperature cavity, and the thermal-insulated sealing ring in this embodiment is close to the high temperature cavity setting, and liquid seal wheel 1 is close to the high pressure cavity setting, and then makes the dynamic seal device in this embodiment have better high pressure high temperature durability. The sealing device in this embodiment is used to seal the medium side from the turbine chamber, and one end of the shaft 12 is in communication with the turbine chamber and is rotatable as the turbine in the turbine chamber rotates.
With further reference to fig. 1, the heat-insulating sealing ring in this embodiment includes a graphite ring 6 fitted over the shaft 12. The graphite rings 6 are split graphite rings 6, the number of the graphite rings is two, and the graphite ring 6 on the left side mainly isolates the process gas from the medium in the precooling process of the engine; the graphite ring 6 mainly plays a role in throttling and pressure reduction in the operation process, and is beneficial to reducing the medium pressure at the right graphite ring 6, so that the aim of reducing medium leakage is fulfilled.
Preferably, the dynamic sealing device in this embodiment further includes a compensation member sleeved outside the graphite ring 6, and the compensation member is specifically a tension spring 2 sleeved outside the graphite ring 6. This embodiment is through set up the compensation piece outside graphite ring 6, the compensation piece has the packing force in advance that makes graphite ring 6 internal contraction, and then make graphite ring 6 when satisfying sealed front and back temperature interval, it is strong to system architecture deformation and rotor jump adaptability, and after split type graphite ring 6 hole is because of the 12 high-speed rotation wearing and tearing of pivot, graphite ring 6 can automatic compensation under 2 effort of extension spring, guarantee that its performance does not reduce after repetitious usage of graphite ring 6, satisfy the requirement of engine used repeatedly, make dynamic seal device's reliability better, be applicable to the environment that rocket etc. required the height to spare part.
In the embodiment, the graphite ring 6 is specifically mounted on the shaft sleeve 8 on the rotating shaft 12, and the side edges of the graphite ring are respectively matched with the sealing shell 4 and the baffle 7 fastened on the sealing shell 4 and are limited by a space formed by the sealing shell 4, the baffle 7 and the shaft sleeve 8, so that the graphite ring 6 can reliably operate in the space.
Preferably, clearance adjusting parts 10 are arranged on the side edges of the graphite rings 6 in the implementation, the clearance adjusting parts 10 are springs and are arranged between the two graphite rings 6, and then the sealing shell or the baffle 7 is subjected to thermal deformation in the starting process of the turbine of the rocket, the clearance adjusting parts 10 can play a clearance adjusting role, the graphite rings 6 are prevented from being crushed and losing efficacy, the reliability of the dynamic sealing device in a high-temperature and high-pressure use environment is further improved, and the reliable operation of the rocket is guaranteed.
As shown in fig. 2 and 3, for the liquid seal wheel 1 in the present embodiment, it is preferable that the shape of the sealing blade 15 in the liquid seal wheel 1 in the present embodiment is circular arc, and the sealing blade is inclined along the circumferential direction, so that compared with the existing conventional linear blade, an acting force in the circumferential direction can be formed in the sealing process of the liquid seal wheel 1, the sealing capability is stronger, the pressure reduction capability can be improved to 80% relative to the linear blade by 50%, and a better pressure reduction effect is achieved, so that the dynamic sealing device in the present embodiment is more suitable for a high-pressure environment.
Further referring to fig. 1, one side of the liquid seal wheel 1 is in clearance fit with a bearing 11 installed on a rotating shaft 12, the other side and the outer circle are in clearance fit with a sealing shell 4, the liquid seal wheel 1 is in clearance fit with the sealing shell 4 and is sealed in a non-contact mode, so that the liquid seal wheel 1 is free of abrasion in the working process, the service life is long, the reliability is high, the requirement for repeated use of an engine is met, meanwhile, the liquid seal wheel 1 rotates at a high speed with a rotor under the high-speed rotating condition, surrounding media are thrown out through the centrifugal force effect, the pressure of the media in the axial direction is greatly reduced, and the pressure of the media at the position of the split type graphite ring 6 can be reduced. Wherein, the clearance range is between 0.2-0.5 mm, and then can effectively control the medium pressure of liquid seal wheel 1 sealed internal diameter department.
Further referring to fig. 1, the dynamic seal device further comprises a gas blowing structure 13, a channel communicated with the gas blowing structure 13 is arranged on the heat insulation sealing ring, and the liquid seal wheel 1 has a good pressure insulation effect, so that the gas pressure is lower than the medium pressure by 0.03-0.05 MPa, the medium leakage amount is not more than 5g/s, the liquid seal wheel 1 and the split graphite ring 6 are sealed in a combined mode, the structure is compact, the process gas stops supplying gas in the working process of the engine, and the gas consumption of the system is greatly reduced.
The present invention further provides an aircraft, including a dynamic seal device suitable for high-speed and high-pressure use, where the dynamic seal device suitable for high-speed and high-pressure use is the dynamic seal device described above, and further, the dynamic seal device in this embodiment has advantages.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications can be made without departing from the scope of the invention.
Claims (14)
1. A dynamic seal device suitable for high speed and high pressure applications, comprising:
the sealing device comprises a sealing shell (4) and a sealing cover, wherein two sealed cavities are formed at intervals, and a through hole communicated with the two cavities is formed in the sealing shell (4);
a rotating shaft (12) which can rotate and is at least partially arranged through the through hole;
the liquid seal wheel (1) is arranged on the rotating shaft (12), rotates along with the rotation of the rotating shaft (12), and can form liquid seal with the seal shell (4) when rotating; and
and the heat insulation sealing ring is arranged between the rotating shaft (12) and the sealing shell (4), is close to the liquid seal wheel (1), and forms combined sealing with the liquid seal wheel (1).
2. The dynamic sealing device suitable for high speed and high pressure according to claim 1, wherein the two cavities comprise a high temperature cavity and a high pressure cavity, the heat insulation sealing ring is arranged adjacent to the high temperature cavity, and the liquid seal wheel (1) is arranged adjacent to the high pressure cavity.
3. The dynamic seal device for high speed and high pressure according to claim 1, wherein the heat insulating seal ring comprises a graphite ring (6) mounted on the shaft (12).
4. A dynamic sealing device suitable for high speed and high pressure according to claim 3, characterised in that the number of graphite rings (6) is two.
5. The dynamic seal device for high speed and high pressure according to claim 1, further comprising a compensator member sleeved outside the heat insulating seal ring, wherein the compensator member has a pre-pressing force for retracting the heat insulating seal ring.
6. The dynamic sealing device suitable for high speed and high pressure according to claim 5, wherein the compensation member is a tension spring (2) sleeved outside the heat insulation sealing ring.
7. The dynamic seal device for high speed and high pressure according to claim 1, further comprising a gap adjuster (10) provided on a side edge of the heat insulating seal ring.
8. The dynamic seal device for high speed and high pressure according to any one of claims 1 to 7, wherein the seal blade (15) in the hydraulic seal wheel (1) has a circular arc shape and is inclined in a radial direction.
9. The dynamic sealing device suitable for high speed and high pressure according to any one of claims 1 to 7, wherein one side of the hydraulic seal wheel (1) is in clearance fit with a bearing (11) mounted on the rotating shaft (12), and the other side and the outer circle are in clearance fit with the seal housing (4).
10. The dynamic sealing device suitable for high speed and high pressure according to claim 9, wherein the clearance is in the range of 0.2-0.5 mm.
11. A dynamic sealing device for high speed and high pressure according to any one of claims 1 to 7, characterized in that it further comprises a gas blow-off structure (13), and the heat insulating sealing ring has a passage thereon communicating with the gas blow-off structure (13).
12. The dynamic seal device for high speed and high pressure according to any one of claims 1 to 7, wherein the seal device is used for sealing a medium side with a turbine chamber, and one end of the rotating shaft (12) is communicated with the turbine chamber and can rotate with the rotation of a turbine in the turbine chamber.
13. An aircraft comprising a dynamic seal device suitable for high speed and high pressure, characterized in that the dynamic seal device suitable for high speed and high pressure is the dynamic seal device suitable for high speed and high pressure according to any one of claims 1 to 12.
14. The aircraft of claim 13, wherein the aircraft is a rocket.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920314692.5U CN209875952U (en) | 2019-03-12 | 2019-03-12 | Dynamic sealing device suitable for high speed and high pressure and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920314692.5U CN209875952U (en) | 2019-03-12 | 2019-03-12 | Dynamic sealing device suitable for high speed and high pressure and aircraft |
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| Publication Number | Publication Date |
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| CN209875952U true CN209875952U (en) | 2019-12-31 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201920314692.5U Active CN209875952U (en) | 2019-03-12 | 2019-03-12 | Dynamic sealing device suitable for high speed and high pressure and aircraft |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110030381A (en) * | 2019-03-12 | 2019-07-19 | 北京星际荣耀空间科技有限公司 | One kind being suitable for high speed and high pressure dynamic sealing device and aircraft |
| CN111636930A (en) * | 2020-04-22 | 2020-09-08 | 中国核动力研究设计院 | High-temperature-resistant supercritical carbon dioxide turbine dry gas sealing device |
| CN112431788A (en) * | 2020-10-29 | 2021-03-02 | 北京航天动力研究所 | High-speed low-leakage liquid seal wheel floating ring combined sealing device |
-
2019
- 2019-03-12 CN CN201920314692.5U patent/CN209875952U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110030381A (en) * | 2019-03-12 | 2019-07-19 | 北京星际荣耀空间科技有限公司 | One kind being suitable for high speed and high pressure dynamic sealing device and aircraft |
| CN111636930A (en) * | 2020-04-22 | 2020-09-08 | 中国核动力研究设计院 | High-temperature-resistant supercritical carbon dioxide turbine dry gas sealing device |
| CN111636930B (en) * | 2020-04-22 | 2021-11-30 | 中国核动力研究设计院 | High-temperature-resistant supercritical carbon dioxide turbine dry gas sealing device |
| CN112431788A (en) * | 2020-10-29 | 2021-03-02 | 北京航天动力研究所 | High-speed low-leakage liquid seal wheel floating ring combined sealing device |
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Address after: 100045 1-14-214, 2nd floor, 136 Xiwai street, Xicheng District, Beijing Patentee after: Beijing Star glory Space Technology Co.,Ltd. Address before: 329, floor 3, building 1, No. 9, Desheng South Street, Daxing Economic and Technological Development Zone, Beijing 100176 Patentee before: BEIJING XINGJIRONGYAO SPACE TECHNOLOGY Co.,Ltd. |