CN114060292A - High-altitude unmanned aerial vehicle centrifugal compressor control method based on hydrogen-air fuel cell - Google Patents
High-altitude unmanned aerial vehicle centrifugal compressor control method based on hydrogen-air fuel cell Download PDFInfo
- Publication number
- CN114060292A CN114060292A CN202111366698.5A CN202111366698A CN114060292A CN 114060292 A CN114060292 A CN 114060292A CN 202111366698 A CN202111366698 A CN 202111366698A CN 114060292 A CN114060292 A CN 114060292A
- Authority
- CN
- China
- Prior art keywords
- pressure compressor
- compressor system
- altitude
- medium
- low
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000000446 fuel Substances 0.000 title claims abstract description 41
- 238000000034 method Methods 0.000 title claims abstract description 29
- 238000004891 communication Methods 0.000 claims description 6
- 238000007906 compression Methods 0.000 claims description 4
- 238000001816 cooling Methods 0.000 claims description 4
- 230000006835 compression Effects 0.000 claims description 3
- 239000000725 suspension Substances 0.000 claims description 3
- 238000001914 filtration Methods 0.000 claims description 2
- 238000005265 energy consumption Methods 0.000 abstract description 4
- 230000009194 climbing Effects 0.000 abstract description 3
- 239000007789 gas Substances 0.000 description 5
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 3
- 238000006073 displacement reaction Methods 0.000 description 3
- 239000001257 hydrogen Substances 0.000 description 3
- 229910052739 hydrogen Inorganic materials 0.000 description 3
- 230000001174 ascending effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000007791 dehumidification Methods 0.000 description 1
- 238000003487 electrochemical reaction Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000010349 pulsation Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000000967 suction filtration Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D17/08—Centrifugal pumps
- F04D17/10—Centrifugal pumps for compressing or evacuating
- F04D17/12—Multi-stage pumps
- F04D17/122—Multi-stage pumps the individual rotor discs being, one for each stage, on a common shaft and axially spaced, e.g. conventional centrifugal multi- stage compressors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D17/08—Centrifugal pumps
- F04D17/10—Centrifugal pumps for compressing or evacuating
- F04D17/12—Multi-stage pumps
- F04D17/14—Multi-stage pumps with means for changing the flow-path through the stages, e.g. series-parallel, e.g. side-loads
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/005—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids by changing flow path between different stages or between a plurality of compressors; Load distribution between compressors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/008—Stop safety or alarm devices, e.g. stop-and-go control; Disposition of check-valves
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M8/00—Fuel cells; Manufacture thereof
- H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
- H01M8/04082—Arrangements for control of reactant parameters, e.g. pressure or concentration
- H01M8/04089—Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants
- H01M8/04104—Regulation of differential pressures
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
- H01M8/00—Fuel cells; Manufacture thereof
- H01M8/04—Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids
- H01M8/04082—Arrangements for control of reactant parameters, e.g. pressure or concentration
- H01M8/04089—Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants
- H01M8/04111—Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02E60/30—Hydrogen technology
- Y02E60/50—Fuel cells
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Manufacturing & Machinery (AREA)
- Sustainable Development (AREA)
- Sustainable Energy (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Electrochemistry (AREA)
- General Chemical & Material Sciences (AREA)
- Fuel Cell (AREA)
Abstract
The invention discloses a high-altitude unmanned aerial vehicle centrifugal compressor control method based on a hydrogen-air fuel cell, which is characterized in that in the climbing process of an unmanned aerial vehicle from low altitude to medium altitude and then to high altitude, the starting sequence of a compressor system is sequentially started according to the sequence of a high-pressure compressor system, a medium-pressure compressor system and a low-pressure compressor system, and an air suction port effectively connected with the atmosphere of the environment follows the 'downward principle', namely: when the medium-pressure compressor system and the high-pressure compressor system are started simultaneously, an air suction port connected with the atmosphere in the environment is the medium-pressure compressor system; when the low-pressure compressor system, the medium-pressure compressor system and the high-pressure compressor system are started at the same time, an air suction port connected with the ambient atmosphere is the low-pressure compressor system; when only the high-pressure compressor system is started, the air suction port connected with the atmosphere is the high-pressure compressor system. The invention effectively solves the matching requirement of the flow rate and the pressure ratio of the compressor in different air suction environments, and optimizes the energy consumption requirement in the flight process; the device has the characteristics of simple layout, simple logic, compact structure and convenient matching.
Description
Technical Field
The invention belongs to the field of centrifugal compressors, and particularly relates to a control method of a centrifugal compressor of an aerial unmanned aerial vehicle based on a hydrogen-air fuel cell.
Background
The energy source of the high-altitude long-endurance unmanned aerial vehicle can be conventional power, solar power, hydrogen power, hybrid power and the like, the hydrogen power unmanned aerial vehicle has the characteristics of high conversion rate, high power-to-weight ratio, high energy density and the like due to the fuel cell for aviation, and meanwhile, compared with the solar power unmanned aerial vehicle in the aspect of structural design, the unmanned aerial vehicle does not need the design of super-large aspect ratio, so that the unmanned aerial vehicle structure is stronger. The air working medium required by the electrochemical reaction of the hydrogen-air fuel cell power system is realized by introducing air from the external ambient atmosphere and pressurizing through the air compressor. Compared with a positive displacement compressor, the speed type compressor has no inherent unbalance of a rotor structure, can work at a rotating speed far higher than that of the positive displacement compressor, enables the weight and the volume of the speed type compressor to be far smaller than that of the positive displacement compressor under the conditions of the same flow and the same pressure ratio, and has the advantages of small vibration and noise, continuous output airflow, small outlet pressure pulsation and the like.
The compressor is used as a core key component in a hydrogen fuel cell power system of the unmanned aerial vehicle, and the use working condition, the function requirement and the performance requirement of the compressor are similar to those of an aero-engine compressor. At present, an axial flow type or a type of axial flow and centrifugal mixed gas compressor is mostly adopted in an aeroengine or airplane auxiliary device unit, and in the field of high-altitude long-endurance unmanned aerial vehicles based on power supply of a fuel electric power system, a single-stage centrifugal gas compressor with high pressure ratio and high load is mainly used, but an effective implementation method is not provided for the condition that the single-stage centrifugal gas compressor with too high pressure ratio cannot meet the requirement.
Disclosure of Invention
The invention aims to provide a control method of a centrifugal compressor of an aerial unmanned aerial vehicle based on a hydrogen-air fuel cell, which is used for meeting different functional and performance requirements of the aerial unmanned aerial vehicle on the full altitude.
In order to achieve the purpose, the invention adopts the following technical scheme to realize the purpose:
a high-altitude unmanned aerial vehicle centrifugal compressor control method based on a hydrogen-air fuel cell is characterized in that a compressor multistage series system is arranged in a high-altitude unmanned aerial vehicle, and the system comprises a low-pressure compressor system, a medium-pressure compressor system and a high-pressure compressor system;
in low altitude, only starting the high-pressure compressor system, connecting an air suction port of the high-pressure compressor system with ambient atmosphere, and connecting an outlet of the high-pressure compressor system with a hydrogen-air fuel cell system;
in the hollow altitude, starting a medium-pressure compressor system and a high-pressure compressor system, wherein an air suction port of the medium-pressure compressor system is connected with the ambient atmosphere, an outlet of the medium-pressure compressor system is connected with the air suction port of the high-pressure compressor system, and an outlet of the high-pressure compressor system is connected with a hydrogen-air fuel cell system;
and when the high altitude is reached, starting the low-pressure compressor system, the medium-pressure compressor system and the high-pressure compressor system, wherein an air suction port of the low-pressure compressor system is connected with the ambient atmosphere, an air suction port of the medium-pressure compressor system is connected with an outlet of the medium-pressure compressor system, an air suction port of the high-pressure compressor system is connected with an outlet of the medium-pressure compressor system, and an outlet of the high-pressure compressor system is connected with the hydrogen-air fuel cell system.
Further, the compressor system is turned off and activated in the descending process from high altitude to medium altitude to low altitude in reverse order to the ascending process from low altitude to medium altitude to high altitude.
Further, the low pressure compressor system, the medium pressure compressor system and the high pressure compressor system each include: the air conditioner comprises an air suction filtering device, a dehumidifying device, a compressor device and a cooling device.
Further, the compressor device is in the form of a centrifugal compressor; the centrifugal compressor device is driven by direct-drive motors respectively or uniformly by the same direct-drive motor; centrifugal compressor devices are all one-stage compression.
Furthermore, the support in the centrifugal compressor device is supported by a magnetic bearing or an air bearing.
Furthermore, the low altitude is 0-6000 m altitude, the hollow altitude is 6000 m-12000 m altitude, and the high altitude is 12000 m-20000 m altitude.
Furthermore, the end parts of air suction pipelines of the low-pressure compressor system, the medium-pressure compressor system and the high-pressure compressor system are connected with the atmospheric environment, and a third air inlet valve, a second air inlet valve and a first air inlet valve are respectively arranged on the air suction pipelines of the three systems; the end parts of exhaust pipelines of the medium-pressure compressor system and the high-pressure compressor system are connected with the atmospheric environment, and a second exhaust valve and a first exhaust valve are respectively arranged on the exhaust pipelines of the two systems; the exhaust pipeline of the low-pressure compressor system is connected with the air suction pipeline of the medium-pressure compressor system and is provided with a first communicating valve, and the exhaust pipeline of the medium-pressure compressor system is connected with the air suction pipeline of the high-pressure compressor system and is provided with a second communicating valve; the exhaust pipeline of the high-pressure compressor system is connected with the inlet of the hydrogen-air fuel cell system.
Furthermore, the first air inlet valve, the second air inlet valve, the third air inlet valve, the first exhaust valve, the second exhaust valve, the first communicating valve and the second communicating valve are all electromagnetic valves and are driven and controlled by a valve driver in the compressor control system; the compressor control system is also provided with a compressor controller, a motor driver and a magnetic bearing driver, wherein the compressor controller is respectively connected with the low-pressure compressor system, the medium-pressure compressor system and the high-pressure compressor system and is used for controlling the working states of the three systems; the motor driver is used for driving the direct drive motor, and the magnetic bearing driver is used for driving and supporting a magnetic suspension bearing of the centrifugal compressor device.
Compared with the prior art, the invention has the following technical characteristics:
the invention solves the problem of matching of the gas compressor caused by different gas suction environments. The centrifugal compressor devices are connected in series, so that the requirement of high pressure ratio can be met by fewer compressor stages. Different compressor systems are used at different altitudes, so that the matching requirement of the flow rate and the pressure ratio of the compressor in different air suction environments is effectively met, and the energy consumption requirement is optimized in the flight process; in addition, by adopting the control mode, the system has simple layout, simple logic, compact structure and convenient matching, and realizes logic switching treatment among inlet pipelines.
Drawings
FIG. 1 is a schematic layout of a single multistage compressor air supply system in one embodiment of the present invention;
FIG. 2 is a schematic layout of a multi-stage compressor air supply system according to an embodiment of the present invention;
the reference numbers in the figures illustrate: the air compressor comprises a low-pressure compressor system, a medium-pressure compressor system, a high-pressure compressor system, a first air inlet valve 4, a second air inlet valve 5, a third air inlet valve 6, a first exhaust valve 7, a second exhaust valve 8, a first communication valve 9 and a second communication valve 10.
Detailed Description
The invention is described in detail below with reference to the figures and specific embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The embodiment of the invention provides a control method of a centrifugal compressor of an aerial unmanned aerial vehicle based on a hydrogen-air fuel cell, which realizes a compressor demand matching method of the aerial unmanned aerial vehicle aiming at different air suction environments in a full-altitude range, simplifies the structure, reduces the weight and the volume on the premise of ensuring the demands of pressure, flow, power and the like for the fuel cell, solves the series of problems of simple layout, compact structure, convenient matching and the like, and solves the compressor matching problem caused by different air suction environments.
Referring to the attached drawings, the high-altitude unmanned aerial vehicle centrifugal compressor control method based on the hydrogen-air fuel cell is characterized in that a compressor multistage series system is arranged in the high-altitude unmanned aerial vehicle, and the system comprises a low-pressure compressor system 1, a medium-pressure compressor system 2 and a high-pressure compressor system 3;
in low altitude (0-6000 m altitude), only starting the high-pressure compressor system 3, connecting an air suction port of the high-pressure compressor system 3 with ambient atmosphere, and connecting an outlet with a hydrogen-air fuel cell system;
when the air conditioner is at a hollow altitude (the altitude is 6000 m-12000 m), starting a medium-pressure compressor system 2 and a high-pressure compressor system 3, wherein an air suction port of the medium-pressure compressor system 2 is connected with ambient atmosphere, an outlet of the medium-pressure compressor system is connected with an air suction port of the high-pressure compressor system 3, and an outlet of the high-pressure compressor system 3 is connected with a hydrogen-air fuel cell system;
when the altitude is high (12000 m-20000 m), starting a low-pressure compressor system 1, a medium-pressure compressor system 2 and a high-pressure compressor system 3, wherein an air suction port of the low-pressure compressor system 1 is connected with ambient atmosphere, an outlet of the low-pressure compressor system is connected with the medium-pressure compressor system 2, an outlet of the medium-pressure compressor system 2 is connected with the high-pressure compressor system 3, and an outlet of the high-pressure compressor system 3 is connected with a hydrogen-air fuel cell system;
in the climbing process from low altitude to medium altitude and then to high altitude, the starting sequence of the compressor system is sequentially started according to the sequence of the high-pressure compressor system 3, the medium-pressure compressor system 2 and the low-pressure compressor system 1, and an air suction port effectively connected with the ambient atmosphere (the effective here means a part for leading the ambient atmosphere to enter the actual compression process) follows a 'downward principle', namely: when the medium-pressure compressor system 3 and the high-pressure compressor system 3 are started simultaneously, an air suction port connected with the ambient atmosphere is the medium-pressure compressor system 2; when the low-pressure compressor system 3, the medium-pressure compressor system 3 and the high-pressure compressor system are started simultaneously, an air suction port connected with the ambient atmosphere is the low-pressure compressor system 1; when only the high-pressure compressor system 3 is started, an air suction port connected with the atmosphere of the environment is the high-pressure compressor system 3;
in the climbing process from low altitude to medium altitude and then to high altitude, because the air suction port effectively connected with the atmosphere follows the principle of descending, the switching between inlet pipelines is required when a new compressor system is started.
In the descending process from high altitude to medium altitude and then to low altitude, the closing and starting sequence of the compressor system is opposite to the above process, and the air suction port effectively connected with the atmosphere still follows the 'downward principle'; for example, from high altitude to hollow altitude, the low-pressure compressor system 1 is switched off and the inlet of the medium-pressure compressor system 2 is connected to the ambient atmosphere.
The low-pressure compressor system 1, the intermediate-pressure compressor system 2 and the high-pressure compressor system 3 comprise, as required and not limited to, the following devices: suction filtration devices, dehumidification devices, compressor devices, cooling devices, etc.;
the compressor devices contained in the low-pressure compressor system 1, the medium-pressure compressor system 2 and the high-pressure compressor system 3 are in the form of centrifugal compressors;
the centrifugal compressor devices used in the low-pressure compressor system 1, the medium-pressure compressor system 2 and the high-pressure compressor system 3 are respectively driven by direct drive motors or are uniformly driven by the same direct drive motor; when driving respectively, required motor power is less, and to the user demand of high rotational speed, the motor volume also can be controlled littleer, is convenient for the lectotype of motor to the limited space in unmanned aerial vehicle inside, and cooling system is more convenient for arrange.
The centrifugal compressor devices used in the low-pressure compressor system 1, the medium-pressure compressor system 2 and the high-pressure compressor system 3 are all primary compression.
The supports in the centrifugal compressor devices used in the low-pressure compressor system 1, the medium-pressure compressor system 2 and the high-pressure compressor system 3 are supported by magnetic bearings or air bearings.
Example 1:
as shown in fig. 1, a method for implementing a centrifugal compressor for a high-altitude long-endurance unmanned aerial vehicle based on a hydrogen-air fuel cell power system is provided, which comprises a low-pressure compressor system 1, a medium-pressure compressor system 2 and a high-pressure compressor system 3, wherein driving systems used in the three systems are uniformly driven by the same direct-drive motor, and a mounting shaft of the three systems is supported by a magnetic bearing, wherein:
the end parts of air suction pipelines of the low-pressure compressor system 1, the medium-pressure compressor system 2 and the high-pressure compressor system 3 are connected with the atmospheric environment, and a third air inlet valve 6, a second air inlet valve 5 and a first air inlet valve 4 are respectively arranged on the air suction pipelines of the three systems; the end parts of exhaust pipelines of the medium-pressure compressor system 2 and the high-pressure compressor system 3 are connected with the atmospheric environment, and a second exhaust valve 8 and a first exhaust valve 7 are respectively arranged on the exhaust pipelines of the two systems; an exhaust pipeline of the low-pressure compressor system 1 is connected with an air suction pipeline of the medium-pressure compressor system 2 and is provided with a first communicating valve 9, and an exhaust pipeline of the medium-pressure compressor system 2 is connected with an air suction pipeline of the high-pressure compressor system 3 and is provided with a second communicating valve 10; the exhaust line of the high-pressure compressor system 3 is connected to the inlet of the hydrogen-air fuel cell system.
The first air inlet valve 4, the second air inlet valve 5, the third air inlet valve 6, the first exhaust valve 7, the second exhaust valve 8, the first communicating valve 9 and the second communicating valve 10 are all electromagnetic valves and are driven and controlled by a valve driver in the air compressor control system; the compressor control system is also provided with a compressor controller, a motor driver and a magnetic bearing driver, wherein the compressor controller is respectively connected with the low-pressure compressor system 1, the medium-pressure compressor system 2 and the high-pressure compressor system 3 and is used for controlling the working states of the three systems; the motor driver is used for driving the direct drive motor, and the magnetic bearing driver is used for driving the magnetic suspension bearing.
At low altitude (0-6000 m altitude), only the high-pressure compressor system 3 is started, at the moment, the first air inlet valve 4, the second air inlet valve 5, the third air inlet valve 6, the first exhaust valve 7 and the second exhaust valve 8 are all in an open state, the first communicating valve 9 and the second communicating valve 10 are in a closed state, the two ends of the low-pressure compressor system 1 and the medium-pressure compressor system 2 are all connected with ambient atmosphere, an air suction port of the high-pressure compressor system 3 is connected with the ambient atmosphere, an outlet is connected with the hydrogen-air fuel cell system, at the moment, the low-pressure compressor system 1 and the medium-pressure compressor system 2 are in a low-energy-consumption non-working state, and the high-pressure compressor system 3 is in a working state. As altitude increases, flow and pressure ratio requirements are maintained by the compressor regulation system.
When the altitude is hollow (6000 m-12000 m), the medium-pressure compressor system 2 and the high-pressure compressor system 3 are started, when the altitude reaches 6000m, the medium-pressure compressor system 2 immediately enters a working state, at the moment, the first air inlet valve 4 and the first air outlet valve 7 are closed, the second communicating valve 10 is opened, the states of other valves are unchanged, two ends of the low-pressure compressor system 1 are both connected with ambient atmosphere, an air suction port of the medium-pressure compressor system 2 is connected with the ambient atmosphere, an outlet of the medium-pressure compressor system 2 is connected with the high-pressure compressor system 3, an outlet of the high-pressure compressor system 3 is connected with the hydrogen-air fuel cell system, at the moment, the low-pressure compressor system 1 is in a low-energy-consumption non-working state, and the medium-pressure compressor system 2 and the high-pressure compressor system 3 are in a working state. As altitude increases, flow and pressure ratio requirements are maintained by the compressor regulation system.
When the altitude is high (12000 m-20000 m), the low-pressure compressor system 1, the medium-pressure compressor system 2 and the high-pressure compressor system 3 are started, when the altitude reaches 12000m, the low-pressure compressor system 1 is immediately enabled to enter a working state, at the moment, the second air inlet valve 5 and the second air outlet valve 8 are closed, the first communication valve 9 is opened, the states of other valves are unchanged, an air suction port of the low-pressure compressor system 1 is connected with the ambient atmosphere, an outlet of the low-pressure compressor system 1 is connected with the medium-pressure compressor system 2, an outlet of the medium-pressure compressor system 2 is connected with the high-pressure compressor system 3, the high-pressure compressor system 3 is connected with the hydrogen-air fuel cell system, and at the moment, the three compressor systems are all in the working state. As altitude increases, flow and pressure ratio requirements are maintained by the compressor regulation system.
In the descent from high altitude to medium altitude to low altitude, the compressor system is turned off and on in reverse order to the above-described sequence, and the air intake port, which is effectively connected to the ambient atmosphere, still follows the aforementioned "downward principle".
Example 2:
as shown in fig. 2, the method for implementing the centrifugal compressor for the high-altitude long-endurance unmanned aerial vehicle based on the hydrogen-air fuel cell power system comprises a low-pressure compressor system 1, a medium-pressure compressor system 2 and a high-pressure compressor system 3, wherein driving systems used in the three systems are respectively driven by respective direct-drive motors.
At low altitude (0-6000 m altitude), only the high-pressure compressor system 3 is started, the first air inlet valve 4 is in an open state, other valves are in a closed state, an air suction port of the high-pressure compressor system 3 is connected with ambient atmosphere, an outlet of the high-pressure compressor system is connected with a hydrogen-air fuel cell system, the low-pressure compressor system 1 and the medium-pressure compressor system 2 do not work, and the high-pressure compressor system 3 is in a working state. As altitude increases, flow and pressure ratio requirements are maintained by the compressor regulation system.
When the altitude is hollow (6000 m-12000 m), the medium-pressure compressor system 2 and the high-pressure compressor system 3 are started, when the altitude reaches 6000m, the medium-pressure compressor system 2 immediately enters a working state, at the moment, the first air inlet valve 4 is closed, the second air inlet valve 5 and the second communicating valve 10 are opened, the states of other valves are unchanged, an air suction port of the medium-pressure compressor system 2 is connected with the ambient atmosphere, an outlet of the medium-pressure compressor system is connected with the high-pressure compressor system 3, an outlet of the high-pressure compressor system 3 is connected with the hydrogen-air fuel cell system, at the moment, the low-pressure compressor system 1 does not work, and the medium-pressure compressor system 2 and the high-pressure compressor system 3 are in the working state. As altitude increases, flow and pressure ratio requirements are maintained by the compressor regulation system.
When the altitude is high (12000 m-20000 m), the low-pressure compressor system 1, the medium-pressure compressor system 2 and the high-pressure compressor system 3 are started, when the altitude reaches 12000m, the low-pressure compressor system 1 is immediately enabled to enter a working state, at the moment, the second air inlet valve 5 is closed, the third air inlet valve 6 and the first communication valve 9 are opened, the states of other valves are unchanged, an air suction port of the low-pressure compressor system 1 is connected with the ambient atmosphere, an outlet of the low-pressure compressor system is connected with the medium-pressure compressor system 2, an outlet of the medium-pressure compressor system 2 is connected with the high-pressure compressor system 3, the high-pressure compressor system 3 is connected with the hydrogen-air fuel cell system, and at the moment, the three compressor systems are all in the working state. As altitude increases, flow and pressure ratio requirements are maintained by the compressor regulation system.
In the descent from high altitude to medium altitude to low altitude, the compressor system is turned off and on in reverse order to the above-described sequence, and the air intake port, which is effectively connected to the ambient atmosphere, still follows the aforementioned "downward principle".
The above embodiments are only used for illustrating the technical solutions of the present application, and not for limiting 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 equally 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 (8)
1. A high-altitude unmanned aerial vehicle centrifugal compressor control method based on a hydrogen-air fuel cell is characterized in that a compressor multistage series system is arranged in the high-altitude unmanned aerial vehicle, and the system comprises a low-pressure compressor system (1), a medium-pressure compressor system (2) and a high-pressure compressor system (3);
in low altitude, only starting the high-pressure compressor system (3), connecting an air suction port of the high-pressure compressor system (3) with ambient atmosphere, and connecting an outlet with a hydrogen-air fuel cell system;
in the hollow altitude, starting a medium-pressure compressor system (2) and a high-pressure compressor system (3), wherein an air suction port of the medium-pressure compressor system (2) is connected with the ambient atmosphere, an outlet of the medium-pressure compressor system is connected with an air suction port of the high-pressure compressor system (3), and an outlet of the high-pressure compressor system (3) is connected with a hydrogen-air fuel cell system;
when the high altitude is reached, the low-pressure compressor system (1), the medium-pressure compressor system (2) and the high-pressure compressor system (3) are started, an air suction port of the low-pressure compressor system (1) is connected with the ambient atmosphere, an outlet of the low-pressure compressor system is connected with an air suction port of the medium-pressure compressor system (2), an outlet of the medium-pressure compressor system (2) is connected with an air suction port of the high-pressure compressor system (3), and an outlet of the high-pressure compressor system (3) is connected with a hydrogen-air fuel cell system.
2. The centrifugal compressor control method for high altitude unmanned aerial vehicles based on hydrogen-air fuel cell as claimed in claim 1, wherein the turn-off and turn-on sequence of the compressor system is reversed during descent from high altitude to medium altitude to low altitude, and vice versa.
3. The high altitude unmanned aerial vehicle centrifugal compressor control method based on hydrogen-air fuel cell according to claim 1, characterized in that the low pressure compressor system (1), the medium pressure compressor system (2) and the high pressure compressor system (3) each comprise: the air conditioner comprises an air suction filtering device, a dehumidifying device, a compressor device and a cooling device.
4. The high altitude unmanned aerial vehicle centrifugal compressor control method based on hydrogen-air fuel cell of claim 3, characterized in that the compressor device is in the form of a centrifugal compressor; the centrifugal compressor device is driven by direct-drive motors respectively or uniformly by the same direct-drive motor; centrifugal compressor devices are all one-stage compression.
5. The control method of the centrifugal compressor of the high altitude unmanned aerial vehicle based on the hydrogen-air fuel cell as claimed in claim 3, wherein the support in the centrifugal compressor device is supported by a magnetic bearing or an air bearing.
6. The centrifugal compressor control method for high altitude unmanned aerial vehicles based on hydrogen-air fuel cell as claimed in claim 1, wherein the low altitude is 0-6000 m altitude, the hollow altitude is 6000 m-12000 m altitude and the high altitude is 12000 m-20000 m altitude.
7. The high-altitude unmanned aerial vehicle centrifugal compressor control method based on the hydrogen-air fuel cell is characterized in that the end parts of air suction pipelines of the low-pressure compressor system (1), the medium-pressure compressor system (2) and the high-pressure compressor system (3) are connected with the atmosphere environment, and a third air inlet valve (6), a second air inlet valve (5) and a first air inlet valve (4) are respectively arranged on the air suction pipelines of the three systems; the end parts of exhaust pipelines of the medium-pressure compressor system (2) and the high-pressure compressor system (3) are connected with the atmospheric environment, and a second exhaust valve (8) and a first exhaust valve (7) are respectively arranged on the exhaust pipelines of the two systems; an exhaust pipeline of the low-pressure compressor system (1) is connected with an air suction pipeline of the medium-pressure compressor system (2) and is provided with a first communicating valve (9), and an exhaust pipeline of the medium-pressure compressor system (2) is connected with an air suction pipeline of the high-pressure compressor system (3) and is provided with a second communicating valve (10); the exhaust pipeline of the high-pressure compressor system (3) is connected with the inlet of the hydrogen-air fuel cell system.
8. The high altitude unmanned aerial vehicle centrifugal compressor control method based on the hydrogen-air fuel cell of claim 7, wherein the first air inlet valve (4), the second air inlet valve (5), the third air inlet valve (6), the first exhaust valve (7), the second exhaust valve (8), the first communication valve (9) and the second communication valve (10) are all electromagnetic valves and are driven and controlled by a valve driver in a compressor control system; the compressor control system is also provided with a compressor controller, a motor driver and a magnetic bearing driver, wherein the compressor controller is respectively connected with the low-pressure compressor system (1), the medium-pressure compressor system (2) and the high-pressure compressor system (3) and is used for controlling the working states of the three systems; the motor driver is used for driving the direct drive motor, and the magnetic bearing driver is used for driving and supporting a magnetic suspension bearing of the centrifugal compressor device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111366698.5A CN114060292B (en) | 2021-11-18 | 2021-11-18 | Control method of centrifugal compressor of high-altitude unmanned aerial vehicle based on hydrogen-air fuel cell |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111366698.5A CN114060292B (en) | 2021-11-18 | 2021-11-18 | Control method of centrifugal compressor of high-altitude unmanned aerial vehicle based on hydrogen-air fuel cell |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114060292A true CN114060292A (en) | 2022-02-18 |
| CN114060292B CN114060292B (en) | 2024-06-18 |
Family
ID=80278400
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111366698.5A Active CN114060292B (en) | 2021-11-18 | 2021-11-18 | Control method of centrifugal compressor of high-altitude unmanned aerial vehicle based on hydrogen-air fuel cell |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114060292B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4266432A1 (en) * | 2022-04-19 | 2023-10-25 | Volvo Truck Corporation | An air management system and a method for controlling intake air pressure and exhaust back pressure of a fuel cell system |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060016197A1 (en) * | 2004-07-21 | 2006-01-26 | Epstein Stanley W | Onboard supplemental power system at varying high altitudes |
| US20150211539A1 (en) * | 2014-01-24 | 2015-07-30 | Air Products And Chemicals, Inc. | Systems and methods for compressing air |
| CN107985607A (en) * | 2017-11-02 | 2018-05-04 | 成都飞机工业（集团）有限责任公司 | A kind of unmanned plane icing protective device |
| CN108899889A (en) * | 2018-09-11 | 2018-11-27 | 东汉太阳能无人机技术有限公司 | Power supply system and aircraft |
| CN110318864A (en) * | 2018-03-29 | 2019-10-11 | 潍柴动力股份有限公司 | Two-step supercharging system aperture modification method and two-step supercharging system based on height above sea level |
| CN112849412A (en) * | 2021-02-08 | 2021-05-28 | 陕西北斗金箭航空科技有限公司 | Hydrogen-electricity nacelle body integrated scouting and batting unmanned aerial vehicle |
| CN113571739A (en) * | 2021-09-24 | 2021-10-29 | 天津航天瑞莱科技有限公司 | Low-temperature low-pressure performance test device and method for hydrogen fuel cell system of unmanned aerial vehicle |
-
2021
- 2021-11-18 CN CN202111366698.5A patent/CN114060292B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060016197A1 (en) * | 2004-07-21 | 2006-01-26 | Epstein Stanley W | Onboard supplemental power system at varying high altitudes |
| US20150211539A1 (en) * | 2014-01-24 | 2015-07-30 | Air Products And Chemicals, Inc. | Systems and methods for compressing air |
| CN107985607A (en) * | 2017-11-02 | 2018-05-04 | 成都飞机工业（集团）有限责任公司 | A kind of unmanned plane icing protective device |
| CN110318864A (en) * | 2018-03-29 | 2019-10-11 | 潍柴动力股份有限公司 | Two-step supercharging system aperture modification method and two-step supercharging system based on height above sea level |
| CN108899889A (en) * | 2018-09-11 | 2018-11-27 | 东汉太阳能无人机技术有限公司 | Power supply system and aircraft |
| CN112849412A (en) * | 2021-02-08 | 2021-05-28 | 陕西北斗金箭航空科技有限公司 | Hydrogen-electricity nacelle body integrated scouting and batting unmanned aerial vehicle |
| CN113571739A (en) * | 2021-09-24 | 2021-10-29 | 天津航天瑞莱科技有限公司 | Low-temperature low-pressure performance test device and method for hydrogen fuel cell system of unmanned aerial vehicle |
Non-Patent Citations (1)
| Title |
|---|
| 施新;李文祥;: "匹配二级顺序增压系统的柴油机高原特性仿真", 兵工学报, no. 04, pages 397 - 402 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4266432A1 (en) * | 2022-04-19 | 2023-10-25 | Volvo Truck Corporation | An air management system and a method for controlling intake air pressure and exhaust back pressure of a fuel cell system |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114060292B (en) | 2024-06-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109372775B (en) | Two-stage compressed air supply system of fuel cell | |
| US11749818B2 (en) | Multi-stage turbocharging compressor for fuel cell systems | |
| CN110985215B (en) | Integrated system for starting of micro turbojet engine | |
| CN109167087B (en) | Fuel cell air management system | |
| CN105626266A (en) | Anti-surge air escape energy recycling system of gas turbine | |
| CN103016364B (en) | Centrifugal compressor | |
| CN114060292B (en) | Control method of centrifugal compressor of high-altitude unmanned aerial vehicle based on hydrogen-air fuel cell | |
| CN111224130A (en) | Fuel cell and air supply system thereof | |
| CN111441960A (en) | Magnetic suspension centrifugal air compressor two-stage compression system | |
| EP3496244B1 (en) | Compressed air turbine direct current generator system | |
| US20190363380A1 (en) | Device For The Air Supply Of A Fuel Cell | |
| CN105966624A (en) | Cabin air return system driven through pressurizing and working of airplane cabin exhausted air | |
| CN104153979A (en) | Operation control method of power air compressor and compressor thereof | |
| CN217270899U (en) | Pneumatic cooling fan for compressor | |
| CN207441869U (en) | A kind of fuel cell compressed air induction system of hydraulic drive | |
| CN211995088U (en) | Air conditioner compressor for double-power vehicle | |
| CN107946613A (en) | A kind of fuel cell compressed air induction system of hydraulic drive | |
| CN212360226U (en) | Magnetic suspension centrifugal air compressor two-stage compression system | |
| CN113606161A (en) | Split type turbocharged air compressor and hydrogen fuel cell system | |
| JP4232033B2 (en) | Air conditioner for aircraft | |
| CN103967856B (en) | Gas drive on angle combiner is surged power system | |
| CN111231643A (en) | Power system and driving method for pneumatic vehicle for underground coal mine transportation | |
| CN221002883U (en) | Superfluid carbon dioxide motor system | |
| CN221462411U (en) | Hydrogen fuel engine system and hydrogen fuel vehicle | |
| CN211969154U (en) | Power device for pneumatic vehicle for underground transportation of coal mine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |