CN114313207A - Pressure adjusting system of dual-redundancy aerostat - Google Patents
Pressure adjusting system of dual-redundancy aerostat Download PDFInfo
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- CN114313207A CN114313207A CN202111658317.0A CN202111658317A CN114313207A CN 114313207 A CN114313207 A CN 114313207A CN 202111658317 A CN202111658317 A CN 202111658317A CN 114313207 A CN114313207 A CN 114313207A
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Abstract
The invention discloses a pressure regulating system of a dual-redundancy aerostat, wherein a measurement and control computer, a main differential pressure sensor, an auxiliary differential pressure sensor, a valve, a fan, an emergency opening pressure switch and an emergency closing pressure switch are respectively connected to a power supply bus bar through a safety; the main differential pressure sensor and the auxiliary differential pressure sensor are connected to a data acquisition end of the measurement and control computer, and the valve and the fan are connected to a control end of the measurement and control computer; the first relay, the second relay and the third relay are respectively arranged among the valve, the emergency opening pressure switch, the emergency closing pressure switch, the fan and the power supply bus bar, and the control ends of the first relay and the third relay are connected to the measurement and control computer. The invention improves the reliability of data acquisition of the differential pressure sensor and the safety of the pressure control system, and controls the opening and closing of the fan in an emergency state by arranging the mechanical pressure switch, thereby adding a redundancy to the pressure control system and further improving the safety of the system.
Description
Technical Field
The invention relates to the field of aerostat pressure control, in particular to a dual-redundancy aerostat pressure adjusting system.
Background
The aerostat is an aircraft lighter than air, overcomes the self weight of the aerostat by means of buoyancy generated by gas lighter than air in a soft air bag to achieve air leaving, is long in air leaving time and good in use economy, and has wide military and civil application.
The pressure control system is an important component of the aerostat, and generally comprises a fan, a valve, a measurement and control computer, a differential pressure sensor and other components, and is used for controlling and adjusting the overpressure state of the aerostat so as to keep the good pneumatic appearance and rigidity of the aircraft. Whether the pressure control system works normally is safe in task execution and operation of the whole aerostat system.
In the prior art, a plurality of fans and valves are generally arranged on an aerostat, and a measurement and control computer adopts a dual-redundancy or multi-redundancy design mode to ensure the effective operation of a pressure control system. The prior art has the following two safety problems:
although a plurality of fans and valves are provided, only one set of differential pressure sensor is provided for acquiring pressure, and although the selection of the sensor is strictly screened and tested, once a certain sensor fails, the whole pressure control system fails, so that the risk is high.
The existing control system can operate the control logic only by electrifying the measurement and control computer, and once the computer is abnormally powered off or fails and has no output, the whole pressure control system is out of control, so that the risk is high.
Disclosure of Invention
The invention aims to provide a pressure regulating system of a dual-redundancy aerostat, which is used for solving the problem that the existing pressure control system is not high enough in safety.
In order to realize the task, the invention adopts the following technical scheme:
a dual-redundancy aerostat pressure regulation system, comprising: including survey control computer, main differential pressure sensor, supplementary differential pressure sensor, first relay, second relay, valve, third relay, fan, emergent pressure switch that opens, emergent pressure switch that closes, insurance and power busbar, wherein:
the measurement and control computer, the main differential pressure sensor, the auxiliary differential pressure sensor, the valve, the fan, the emergency opening pressure switch and the emergency closing pressure switch are respectively connected to the power supply bus bar through a fuse; the main differential pressure sensor and the auxiliary differential pressure sensor are connected to a data acquisition end of the measurement and control computer, and the valve and the fan are connected to a control end of the measurement and control computer; the first relay, the second relay and the third relay are respectively arranged among the valve, the emergency opening pressure switch, the emergency closing pressure switch, the fan and the power supply bus bar, and the control ends of the first relay and the third relay are connected to the measurement and control computer.
Furthermore, three main differential pressure sensors are arranged as main sensors and are respectively used for testing the pressure of the captive balloon air bag, the auxiliary air bag and the fairing; three auxiliary differential pressure sensors are also arranged and are used for respectively measuring the pressure difference of the air bag/auxiliary air bag, the air bag/fairing and the auxiliary air bag/fairing; when the main sensors are all normal, a control system in the measurement and control computer adopts data acquired by the main sensors; when the main sensor is abnormal, the calibration value is calculated according to the data collected by the main sensor and the auxiliary differential pressure sensor with normal functions, and the abnormal value is replaced to participate in pressure control.
Furthermore, the control end of the electric mechanism of the valve is respectively connected with the load end of the first relay, and the micro switch of the valve is respectively connected with the power bus bar and the measurement and control computer.
Furthermore, a mechanical switch control device is arranged in the dual-redundancy aerostat pressure regulating system and used as a supplementary measure of the existing pressure control system, and when the pressure is reduced to a certain value under the emergency conditions of failure, fault, manual misoperation and the like of the existing pressure control system, the emergency opening pressure switch and the emergency closing pressure switch are triggered to work, the corresponding fan is automatically controlled to be opened and closed, and the pressure of the air bag, the auxiliary air bag and the fairing is maintained within a set range.
Further, the mechanical switch control device comprises an emergency opening pressure switch, an emergency closing pressure switch and a second relay, wherein:
the control end of the second relay is connected in series between the emergency opening pressure switch and the power supply bus bar, and the load end of the second relay comprises a switching end, a contact end and a free end; the second relay can be switched to the switching end and respectively contacted with the contact end and the contact, or contacted with the free end and the contact; the emergency opening pressure switch and the emergency closing pressure switch are pressure control switches and respectively comprise a COM end, an NO end and an NC end, wherein the COM end can be switched to be in contact with the NO end or the NC end, and the NO end is a suspension end; when the pressure value monitored by the measurement and control computer is greater than the preset value, the COM end is conducted with the NO end, and the switch is switched off at the moment; when the pressure value is smaller than the preset value, the COM end is conducted with the NC end, and the switch state is conducted at the moment;
the switching end is connected between the control end and the power supply bus bar in series, and the switching end is grounded; the contact end is connected between the third relay and the power supply end of the fan, the contact end is connected with the COM end of the emergency closing pressure switch and the NC end of the emergency opening pressure switch, the COM end of the emergency opening pressure switch is connected with the control end of the second relay, and the NC end of the emergency closing pressure switch is grounded.
Further, if the threshold value of the emergency opening pressure switch is yz1 and the threshold value of the emergency closing pressure switch is yz2, yz2< yz1 exists.
Further, the mechanical switch control device controls the pressure of the air bag according to the following process:
when the pressure value of the air bag is monitored by the measuring and controlling computer to be lower than yz1 but larger than yz2, the pressure switch is turned on in an emergency, the pressure switch is turned off in an emergency, the control end of the second relay is suspended through the pressure switch in an emergency, the power end of the fan is connected with the contact end of the second relay in a suspended state, and the fan does not work.
Further, when the pressure value of the air bag is continuously reduced to be lower than yz2, the emergency opening pressure switch and the emergency closing pressure switch are both conducted, the control end of the second relay is grounded through the emergency opening pressure switch and the emergency closing pressure switch at the moment, the second relay is attracted, the contact end is grounded through the switching end, and the contact end is connected to the power bus bar through the switching end, so that the air bag is controlled to be inflated by the fan.
Further, when the pressure value of the air bag rises to be greater than yz1, the emergency opening pressure switch and the emergency closing pressure switch are both switched off, the control end of the second relay is suspended at the emergency opening pressure switch, the power supply end of the fan is not powered any more, and the fan is closed.
Further, the system has three control modes: an automatic pressure control mode, a remote control pressure control mode and an emergency pressure control mode;
in an automatic pressure control mode, a main differential pressure sensor collects the pressures of an air bag, an auxiliary air bag and a fairing, and a measurement and control computer automatically controls the opening and closing of a corresponding fan and a corresponding valve according to the collected pressure value and a preset value and maintains the pressure of the air bag, the auxiliary air bag and the fairing within a set range; under the remote control pressure control mode, an operator remotely controls each fan and each valve through a ground station according to the pressure value acquired in real time and the actual working condition requirement, and the pressure of the air bag, the auxiliary air bag and the pressure of the fairing are maintained within the required range; under the emergency pressure control mode, a mechanical switch control device automatically controls the corresponding fan to be turned on and off, and the pressure of the air bag, the auxiliary air bag and the pressure of the fairing are maintained within a set range; the mechanical switch control device cannot be controlled to be turned on or off by the ground station.
Compared with the prior art, the invention has the following technical characteristics:
the auxiliary differential pressure sensor is arranged, so that the reliability of data acquired by the differential pressure sensor and the safety of the pressure control system are improved, the mechanical pressure switch is arranged to control the fan to be turned on and off in an emergency state, the redundancy is added to the pressure control system, and the safety of the system is further improved.
Drawings
FIG. 1 is a schematic diagram of the electrical connections of the conditioning system of the present invention.
The reference numbers in the figures illustrate: the system comprises a measurement and control computer 1, a main differential pressure sensor 2, an auxiliary differential pressure sensor 3, a first relay 41, a second relay 42, a valve 5, a third relay 6, a fan 7, a pressure switch opened in emergency 8, a pressure switch closed in emergency 9 and a safety device 10.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the embodiments and features of the embodiments in the present application may be arbitrarily combined with each other without conflict.
Referring to the attached drawings, the invention provides a dual-redundancy aerostat pressure control system for solving the problem that the existing pressure control system is not high enough in safety, and the dual-redundancy aerostat pressure control system is provided with a set of wind pressure transmitting sensor and a set of mechanical pressure switch, so that the system safety is improved, and the use risk is further reduced.
As shown in fig. 1, the dual-redundancy aerostat pressure control system of the present invention includes a measurement and control computer 1, a main differential pressure sensor 2, an auxiliary differential pressure sensor 3, a first relay 41, a second relay 42, a valve 5, a third relay 6, a blower 7, an emergency opening pressure switch 8, an emergency closing pressure switch 9, a safety 10, and a power bus bar for providing 28V power, wherein:
the measurement and control computer 1, the main differential pressure sensor 2, the auxiliary differential pressure sensor 3, the valve 5, the fan 7, the emergency opening pressure switch 8 and the emergency closing pressure switch 9 are respectively connected to a power supply bus bar through a fuse 10; the main differential pressure sensor 2 and the auxiliary differential pressure sensor 3 are connected to a data acquisition end of the measurement and control computer 1, and the valve 5 and the fan 6 are connected to a control end of the measurement and control computer 1; first relay 41, second relay 42, third relay 6 set up respectively between valve 5, emergent pressure switch 8 and the emergent pressure switch 9 of opening, fan 7 and the power busbar, and the control end of first relay 41, third relay 6 all is connected to the survey control computer.
Specifically, the control end of the electric mechanism of the valve 5 is connected to the load end of the first relay 41, and the micro switch of the valve 5 is connected to the power bus bar and the measurement and control computer 1.
In the scheme, three main differential pressure sensors 2 are arranged as main sensors and are respectively used for testing the pressure of a captive balloon air bag, an auxiliary air bag and a fairing; three auxiliary differential pressure sensors 3 are also provided, which measure the pressure difference of the airbag/ballonet, the airbag/fairing and the ballonet/fairing, respectively. When the main sensors are all normal, a control system in the measurement and control computer 1 adopts data acquired by the main sensors; when the main sensor is abnormal, the calibration value is calculated according to the data collected by the main sensor and the auxiliary differential pressure sensor 3 with normal functions, and the abnormal value is replaced to participate in pressure control.
The invention also provides a mechanical switch control device for the fan 7, which is used as a supplementary measure of the existing pressure control system, and under the emergency conditions of failure, manual misoperation and the like of the existing pressure control system, when the pressure is reduced to a certain value, the pressure switches (the emergency opening pressure switch 8 and the emergency closing pressure switch 9) are triggered to work, the corresponding fan is automatically controlled to be opened and closed, and the pressure of the air bag, the auxiliary air bag and the fairing is maintained within a set range.
Referring to fig. 1, the mechanical switching control device includes an emergency opening pressure switch 8, an emergency closing pressure switch 9, and a second relay 42, wherein:
the control terminals 13 and 14 of the second relay 42 are connected in series between the emergency opening pressure switch 8 and the power bus bar, and the load terminal of the second relay 42 comprises switching terminals 9 and 12, contact terminals 5 and 8, and free terminals 1 and 4; the second relay 42 can be switched to contact the switching terminals 9 and 12 with the contact terminals 5 and 8, respectively, or with the free terminals 1 and 4. The emergency opening pressure switch 8 and the emergency closing pressure switch 9 are pressure control switches and respectively comprise a COM end, an NO end and an NC end, wherein the COM end can be switched to be in contact with the NO end or the NC end, and the NO end is a suspension end; when the pressure value monitored by the measurement and control computer 1 is greater than the preset value, the COM end is conducted with the NO end, and the switch is switched off at the moment; when the pressure value is smaller than the preset value, the COM end is conducted with the NC end, and the switch state is conducted at the moment. If the threshold value of the emergency opening pressure switch 8 is yz1 and the threshold value of the emergency closing pressure switch 9 is yz2, yz2< yz1 exists. Wherein, the pressure value can be the pressure value of the air bag, the auxiliary air bag and the fairing; correspondingly, the controlled fan 7 is a fan that replenishes air to the airbags, ballonets and fairings.
The switching end 9 is connected in series between the control end 13 and the power bus bar, and the switching end 12 is grounded; the contact terminal 5 is connected between the third relay 6 and the power supply terminal of the fan 7, the contact terminal 8 is connected with the COM terminal of the emergency closing pressure switch 9 and the NC terminal of the emergency opening pressure switch 8, the COM terminal of the emergency opening pressure switch 8 is connected with the control terminal 14 of the second relay 42, and the NC terminal of the emergency closing pressure switch 9 is grounded.
The control process of the mechanical switch control device on the pressure of the air bag is as follows:
1. when the measurement and control computer 1 monitors that the pressure value of the air bag is reduced to be lower than yz1 but larger than yz2, the emergency opening pressure switch 8 is switched on, the emergency closing pressure switch 9 is switched off, the control end 14 of the second relay 42 is suspended through the emergency closing pressure switch 9 at the moment, the power end of the fan 7 is connected with the contact end 5 of the second relay 42, the state is suspended, and the fan does not work.
2. When the pressure value of the air bag is continuously reduced to be lower than yz2, the emergency opening pressure switch 8 and the emergency closing pressure switch 9 are both conducted, at the moment, the control end 14 of the second relay 42 is grounded through the emergency opening pressure switch 8 and the emergency closing pressure switch 9, the second relay 42 is attracted, the contact end 8 is grounded through the switching end 12, and the contact end 5 is connected to the power bus bar through the switching end 9, so that the fan 7 is controlled to be started to inflate the air bag.
3. When the pressure value of the air bag rises to be larger than yz1, the emergency opening pressure switch 8 and the emergency closing pressure switch 9 are both switched off, the control end 14 of the second relay 42 is suspended at the emergency opening pressure switch 8, the power supply end of the fan 7 is not powered any more, and the fan 7 is closed.
Through the above control process, the pressure of the airbag can be controlled in the range of yz2 to yz 1. The pressure control method of the ballonet and the fairing is the same as the process, and is not described in detail herein.
The invention has three control modes: an automatic pressure control mode, a remote pressure control mode, and an emergency pressure control mode.
In an automatic pressure control mode, a main differential pressure sensor 2 collects the pressure of an air bag, an auxiliary air bag and a fairing, and a measurement and control computer 1 automatically controls the opening and closing of a corresponding fan 7 and a corresponding valve 5 according to the collected pressure value and a preset value, so as to maintain the pressure of the air bag, the auxiliary air bag and the fairing within a set range; under the remote control pressure control mode, an operator remotely controls each fan 7 and each valve 5 through a ground station according to the pressure value acquired in real time and the actual working condition requirement, and the pressure of the air bag, the auxiliary air bag and the pressure of the fairing are maintained within the required range; under the emergency pressure control mode, a mechanical switch control device automatically controls the corresponding fan 7 to be opened and closed, and the pressure of the air bag, the auxiliary air bag and the pressure of the fairing are maintained within a set range; the mechanical switch control device cannot be controlled to be turned on or off by the ground station.
The invention is applied to certain type captive balloon project, has normal function and good performance, and practically improves the reliability and safety of the pressure control system and meets the safety requirement of the whole system through the evaluation and examination of experts in the industry.
The above embodiments are only used to illustrate the technical solutions of the present application, and not to limit the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not substantially depart from the spirit and scope of the embodiments of the present application and are intended to be included within the scope of the present application.
Claims (10)
1. A dual-redundancy aerostat pressure regulation system, comprising: including survey control computer (1), main differential pressure sensor (2), supplementary differential pressure sensor (3), first relay (41), second relay (42), valve (5), third relay (6), fan (7), emergent pressure switch (8) of opening, emergent pressure switch (9), insurance (10) and power busbar of closing, wherein:
the control computer (1), the main differential pressure sensor (2), the auxiliary differential pressure sensor (3), the valve (5), the fan (7), the emergency opening pressure switch (8) and the emergency closing pressure switch (9) are respectively connected to the power supply bus bar through a fuse (10); the main differential pressure sensor (2) and the auxiliary differential pressure sensor (3) are connected to a data acquisition end of the measurement and control computer (1), and the valve (5) and the fan (6) are connected to a control end of the measurement and control computer (1); first relay (41), second relay (42), third relay (6) set up respectively between valve (5), emergent pressure switch (8) and emergent pressure switch (9), fan (7) and the power busbar of opening, and the control end of first relay (41), third relay (6) all is connected to the survey and control computer.
2. The dual-redundancy aerostat pressure regulating system according to claim 1, wherein said primary differential pressure sensors (2) are provided in three as primary sensors, for testing the pressure of the captive balloon envelope, the secondary envelope and the fairing, respectively; three auxiliary differential pressure sensors (3) are also arranged and are used for respectively measuring the pressure difference of the air bag/auxiliary air bag, the air bag/fairing and the auxiliary air bag/fairing; when the main sensors are all normal, a control system in the measurement and control computer (1) adopts data acquired by the main sensors; when the main sensor is abnormal, the calibration value is calculated according to the data collected by the main sensor and the auxiliary differential pressure sensor (3) with normal functions, and the abnormal value is replaced to participate in pressure control.
3. The dual-redundancy aerostat pressure regulating system according to claim 1, wherein the control ends of the electric mechanisms of the valves (5) are respectively connected with the load ends of the first relays (41), and the micro switches of the valves (5) are respectively connected with the power bus bar and the measurement and control computer (1).
4. The dual-redundancy aerostat pressure regulating system according to claim 1, wherein a mechanical switch control device is arranged in the dual-redundancy aerostat pressure regulating system, as a supplementary measure for the existing pressure control system, in case of emergency such as failure, malfunction and artificial misoperation of the existing pressure control system, when the pressure is reduced to a certain value, the emergency opening pressure switch (8) and the emergency closing pressure switch (9) are triggered to operate, the corresponding fan is automatically controlled to be opened and closed, and the pressure of the air bag, the auxiliary air bag and the fairing is maintained within a set range.
5. A dual-redundancy aerostat pressure regulating system according to claim 4, wherein said mechanical switch control means comprise an emergency opening pressure switch (8), an emergency closing pressure switch (9) and a second relay (42), wherein:
the control ends (13) and (14) of the second relay (42) are connected in series between the emergency opening pressure switch (8) and the power supply bus bar, and the load end of the second relay (42) comprises switching ends (9) and (12), contact ends (5) and (8) and free ends (1) and (4); the second relay (42) can be switched to the switching ends (9) and (12) to be respectively contacted with the contact ends (5) and (8) or contacted with the free ends (1) and (4); the emergency opening pressure switch (8) and the emergency closing pressure switch (9) are pressure control switches and respectively comprise a COM end, an NO end and an NC end, wherein the COM end can be switched to be in contact with the NO end or the NC end, and the NO end is a suspension end; when the pressure value monitored by the measurement and control computer (1) is greater than the preset value, the COM end is conducted with the NO end, and the switch is switched off at the moment; when the pressure value is smaller than the preset value, the COM end is conducted with the NC end, and the switch state is conducted at the moment;
the switching end (9) is connected in series between the control end (13) and the power supply bus bar, and the switching end (12) is grounded; the contact end (5) is connected between the power supply ends of the third relay (6) and the fan (7), the contact end (8) is connected with the COM end of the emergency closing pressure switch (9) and the NC end of the emergency opening pressure switch (8), the COM end of the emergency opening pressure switch (8) is connected with the control end (14) of the second relay (42), and the NC end of the emergency closing pressure switch (9) is grounded.
6. A dual-redundancy aerostat pressure regulating system according to claim 5, wherein noting that the threshold for the emergency opening pressure switch (8) is yz1, and the threshold for the emergency closing pressure switch (9) is yz2, there is yz2< yz 1.
7. The dual-redundancy aerostat pressure regulating system according to claim 6, wherein said mechanical switch control means controls the air bag pressure as follows:
when the pressure value of the air bag is monitored by the measurement and control computer 1 to be lower than yz1 but larger than yz2, the emergency opening pressure switch (8) is conducted, the emergency closing pressure switch (9) is cut off, the control end (14) of the second relay (42) is suspended through the emergency closing pressure switch (9), the power end of the fan (7) is connected with the contact end (5) of the second relay (42) in a suspended state, and the fan does not work.
8. The dual-redundancy aerostat pressure regulating system according to claim 6, wherein when the pressure value of the air bag continues to decrease below yz2, both the emergency opening pressure switch (8) and the emergency closing pressure switch (9) are turned on, at this time, the control terminal (14) of the second relay (42) is grounded through the emergency opening pressure switch (8) and the emergency closing pressure switch (9), the second relay (42) is attracted, the contact terminal (8) is grounded through the switching terminal (12), and the contact terminal (5) is connected to a power supply bus bar through the switching terminal (9), so that the fan (7) is controlled to start to inflate the air bag.
9. The dual-redundancy aerostat pressure regulating system according to claim 6, wherein when the pressure value of the air bag rises to be greater than yz1, both the emergency opening pressure switch (8) and the emergency closing pressure switch (9) are switched off, the control terminal (14) of the second relay (42) is suspended at the emergency opening pressure switch (8), the power supply terminal of the fan (7) is no longer powered, and the fan (7) is closed.
10. The dual-redundancy aerostat pressure regulation system according to claim 1, wherein the system has three control modes: an automatic pressure control mode, a remote control pressure control mode and an emergency pressure control mode;
in an automatic pressure control mode, a main differential pressure sensor (2) collects the pressure of an air bag, an auxiliary air bag and a fairing, and a measurement and control computer (1) automatically controls the opening and closing of a corresponding fan (7) and a corresponding valve (5) according to the collected pressure value and a preset value, so as to maintain the pressure of the air bag, the auxiliary air bag and the fairing within a set range; under the remote control pressure control mode, an operator remotely controls each fan (7) and each valve (5) through a ground station according to the pressure value acquired in real time and the actual working condition requirement, and the pressure of the air bag, the auxiliary air bag and the pressure of the fairing are maintained within the required range; under the emergency pressure control mode, a mechanical switch control device automatically controls the corresponding fan 7 to be opened and closed, and the pressure of the air bag, the auxiliary air bag and the pressure of the fairing are maintained within a set range; the mechanical switch control device cannot be controlled to be turned on or off by the ground station.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111658317.0A CN114313207B (en) | 2021-12-30 | 2021-12-30 | Dual-redundancy aerostat pressure regulating system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111658317.0A CN114313207B (en) | 2021-12-30 | 2021-12-30 | Dual-redundancy aerostat pressure regulating system |
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| CN114313207A true CN114313207A (en) | 2022-04-12 |
| CN114313207B CN114313207B (en) | 2024-01-12 |
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| US20060000945A1 (en) * | 2003-09-09 | 2006-01-05 | Voss Paul B | System and method for altitude control |
| CN201350970Y (en) * | 2008-12-30 | 2009-11-25 | 北京龙圣联成航空科技有限公司 | Pressure control device for airship capsule |
| CN103438267A (en) * | 2013-08-30 | 2013-12-11 | 北京航空航天大学 | Dual-redundancy valve device applied to stratosphere aerostat |
| CN206278253U (en) * | 2016-12-16 | 2017-06-27 | 中国电子科技集团公司第三十八研究所 | One kind is used for captive balloon emergency pressure control device |
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2021
- 2021-12-30 CN CN202111658317.0A patent/CN114313207B/en active Active
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| US20060000945A1 (en) * | 2003-09-09 | 2006-01-05 | Voss Paul B | System and method for altitude control |
| CN201350970Y (en) * | 2008-12-30 | 2009-11-25 | 北京龙圣联成航空科技有限公司 | Pressure control device for airship capsule |
| CN103438267A (en) * | 2013-08-30 | 2013-12-11 | 北京航空航天大学 | Dual-redundancy valve device applied to stratosphere aerostat |
| CN206278253U (en) * | 2016-12-16 | 2017-06-27 | 中国电子科技集团公司第三十八研究所 | One kind is used for captive balloon emergency pressure control device |
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| CN114313207B (en) | 2024-01-12 |
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