CN117602134A - Near space unmanned aerial vehicle with delivery system and flight method - Google Patents
Near space unmanned aerial vehicle with delivery system and flight method Download PDFInfo
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- CN117602134A CN117602134A CN202311470398.0A CN202311470398A CN117602134A CN 117602134 A CN117602134 A CN 117602134A CN 202311470398 A CN202311470398 A CN 202311470398A CN 117602134 A CN117602134 A CN 117602134A
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- 238000000034 method Methods 0.000 title claims abstract description 18
- 239000001257 hydrogen Substances 0.000 claims abstract description 271
- 229910052739 hydrogen Inorganic materials 0.000 claims abstract description 271
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims abstract description 268
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 103
- 239000001301 oxygen Substances 0.000 claims abstract description 103
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 103
- 239000000446 fuel Substances 0.000 claims abstract description 102
- 230000007246 mechanism Effects 0.000 claims abstract description 26
- 238000003860 storage Methods 0.000 claims description 74
- 239000007789 gas Substances 0.000 claims description 55
- 238000000926 separation method Methods 0.000 claims description 36
- 238000013461 design Methods 0.000 claims description 26
- 239000002808 molecular sieve Substances 0.000 claims description 26
- URGAHOPLAPQHLN-UHFFFAOYSA-N sodium aluminosilicate Chemical compound [Na+].[Al+3].[O-][Si]([O-])=O.[O-][Si]([O-])=O URGAHOPLAPQHLN-UHFFFAOYSA-N 0.000 claims description 26
- 238000005520 cutting process Methods 0.000 claims description 19
- 238000012546 transfer Methods 0.000 claims description 19
- 238000010438 heat treatment Methods 0.000 claims description 17
- 238000004891 communication Methods 0.000 claims description 16
- 230000001105 regulatory effect Effects 0.000 claims description 10
- 238000001514 detection method Methods 0.000 claims description 9
- 230000008569 process Effects 0.000 claims description 9
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- 229920000049 Carbon (fiber) Polymers 0.000 claims description 6
- 239000004917 carbon fiber Substances 0.000 claims description 6
- 230000005540 biological transmission Effects 0.000 claims description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 4
- 238000005265 energy consumption Methods 0.000 abstract description 5
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 10
- 150000002431 hydrogen Chemical class 0.000 description 8
- 238000007789 sealing Methods 0.000 description 8
- 239000000463 material Substances 0.000 description 7
- 229910052757 nitrogen Inorganic materials 0.000 description 5
- 229910021536 Zeolite Inorganic materials 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- HNPSIPDUKPIQMN-UHFFFAOYSA-N dioxosilane;oxo(oxoalumanyloxy)alumane Chemical compound O=[Si]=O.O=[Al]O[Al]=O HNPSIPDUKPIQMN-UHFFFAOYSA-N 0.000 description 4
- 238000004146 energy storage Methods 0.000 description 4
- 239000010457 zeolite Substances 0.000 description 4
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 3
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 3
- 238000007599 discharging Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 229910052744 lithium Inorganic materials 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000008929 regeneration Effects 0.000 description 3
- 238000011069 regeneration method Methods 0.000 description 3
- 230000001174 ascending effect Effects 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 230000018109 developmental process Effects 0.000 description 2
- 230000007613 environmental effect Effects 0.000 description 2
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- 125000006850 spacer group Chemical group 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- OLBVUFHMDRJKTK-UHFFFAOYSA-N [N].[O] Chemical compound [N].[O] OLBVUFHMDRJKTK-UHFFFAOYSA-N 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
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- 230000001706 oxygenating effect Effects 0.000 description 1
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Classifications
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- 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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02T90/40—Application of hydrogen technology to transportation, e.g. using fuel cells
Abstract
The invention relates to the technical field of aerospace, and particularly discloses an unmanned near space aircraft with a delivery system and a flight method, wherein the aircraft comprises an aircraft body and the delivery system connected with the aircraft body; the delivery system comprises a second equipment cabin, a hanging and releasing mechanism for connecting the second equipment cabin with the aircraft body, a second oxygen generation system, a second hydrogen supply system and a second hydrogen fuel cell system; the aircraft body comprises a first oxygen generation system, a first hydrogen supply system and a first hydrogen fuel cell system; when the aircraft is delivered, the delivery system is adopted for delivery, and after the aircraft enters a near space, the second equipment cabin and the aircraft body are powered by the first hydrogen fuel cell system, so that the energy consumption of the aircraft in a take-off stage is greatly reduced, limited energy can be directly used for cruising flight of the aircraft, the endurance of the aircraft is effectively improved, and long-endurance cruising flight is realized.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to an adjacent space unmanned aerial vehicle with a delivery system and a flight method.
Background
The adjacent space is an airspace with the height of 20 km-100 km, the air is thin, the air temperature is low, and the environmental condition is poor. Taking a 20km high-altitude environment as an example, the air density is about 1/14 of the ground, and the pressure is about 1/18 of the standard atmospheric pressure. The near space aircraft has the advantages of strong maneuverability, concealment and large load, and can realize ultra-long-time endurance by matching with proper power combination, so that the near space aircraft plays an important role in the fields of communication, information countermeasure, space attack and defense, weather environment monitoring and the like. Therefore, the solar-driven long-endurance unmanned aerial vehicle platform capable of flying around the clock can be used for carrying various application near space application devices such as remote communication, weather environment monitoring and the like, and has a wide market prospect.
The main problems faced in the development of long-haul aircraft include the need for more than 400Wh/kg for all-weather stable flight under solar cell single power source conditions as the "heart" of the near-space aircraft, which far exceeds the current energy storage density limits of solar cell materials. The design of the combined energy supply system of the hydrogen energy system and the solar energy generation energy source can solve the problem of low specific energy of the energy system of the unmanned aerial vehicle, but the design also faces great challenges in the development requirements of the unmanned aerial vehicle with high effective load and long voyage. Therefore, reducing the overall weight of the aircraft system becomes an important means of increasing aircraft endurance and aircraft payload;
In the prior art, an unmanned aircraft in the near space with a delivery system is lack, which can solve high load and realize long-endurance flight.
Disclosure of Invention
The invention aims to solve the technical problem of providing an unmanned aircraft in the near space with a delivery system; the delivery system is used for delivering the fuel to the nearby space for self-flying, the fuel in the aircraft body is not consumed before the aircraft flies to the nearby space, and the fuel in the aircraft body can be consumed only when the aircraft flies by itself, so that long-endurance flying is effectively realized;
the invention solves the technical problems by adopting the following solution:
an unmanned near space aircraft with a delivery system comprises an aircraft body and the delivery system connected with the aircraft body;
the delivery system comprises a second equipment cabin which is arranged on the aircraft body and is provided with a rotor wing at the outer side, a hydrogen storage container which is connected with the second equipment cabin and is positioned above the second equipment cabin, a hooking and releasing mechanism which is used for connecting the aircraft body and the second equipment cabin, a second hydrogen supply system which is communicated with the inside of the hydrogen storage container and is arranged in the second equipment cabin, a second hydrogen fuel cell system which is positioned in the second equipment cabin and is connected with the second hydrogen supply system, a second oxygen generation system which is arranged in the second equipment cabin and is used for supplying oxygen to the second hydrogen fuel cell system, and a second fuel control module which is respectively connected with the hooking and releasing mechanism, the second hydrogen supply system, the second hydrogen fuel cell system and the second oxygen generation system;
The aircraft body comprises a wing, two groups of first equipment cabins which are arranged at the bottom of the wing and are symmetrically arranged along the course, a flight cabin which is positioned between the two groups of first equipment cabins and is used as a hydrogen storage pressure container, a hydrogen energy supply system connected with the flight cabin, a first oxygen generation system connected with the hydrogen energy supply system, a first fuel control module respectively connected with the hydrogen energy supply system and the first oxygen generation system, a flight airborne system, a first equipment cabin pressure regulation system and a pressure control module connected with the first equipment cabin pressure regulation system;
the hydrogen energy supply system, the first oxygen generation system and the first fuel control module are positioned in the same first equipment cabin;
the flight airborne system and the first equipment cabin pressure regulation and control system are positioned in another group of first equipment cabins;
the hydrogen energy supply system comprises a first hydrogen fuel cell system and a first hydrogen supply system which is connected with the first hydrogen fuel cell system and supplies hydrogen for the first hydrogen fuel cell system, and the first hydrogen supply system is connected with the flight cabin.
In some possible embodiments, the first hydrogen supply system and the second hydrogen supply system are identical in structure;
the device comprises an automatic control valve, a gas transfer pump connected with the automatic control valve, an automatic control valve connected with the gas transfer pump, a hydrogen pressure sensor arranged on a connecting pipeline of the automatic control valve and the gas transfer pump, and a pressure reducing valve connected with the gas transfer pump in parallel.
In some possible embodiments, the hydrogen storage container comprises a hydrogen storage container body mounted on the second equipment compartment, and a gas pipe with two ends communicating with the hydrogen storage container body and the second hydrogen supply system.
In some possible embodiments, the hydrogen storage container body and the flight cabin are both made of carbon fiber, and the working pressure is 5MPa-30MPa, and the gas leakage rate is high<1×10 -7 a.m 3 .s -1 ；
The external pressure bearing capacities of the hydrogen storage container body and the flight cabin are deltaP, deltaP=P External pressure -P internal pressure>0.15MPa；
The volume of the hydrogen storage container body is 20m 3 -50m 3 The volume of the flight chamber is 5m 3 -30m 3 ；
Wherein P is External pressure Is the outside pressure, P Internal pressure of Is the pressure of the inner side.
In some possible embodiments, the hydrogen storage vessel body is a balloon in communication with a gas conduit; the device comprises a balloon body arranged on a second equipment cabin connecting plate, a tensioning motor arranged in the balloon body, a ring wheel in transmission connection with the tensioning motor, and a tensioning assembly, wherein one end of the tensioning assembly is connected with the ring wheel, and the other end of the tensioning assembly is connected with the top of the balloon body;
the tensioning assembly comprises a tensioning switch and a tensioning wire used for the tensioning switch and the ring wheel and the tensioning switch and the balloon body.
In some possible embodiments, the first and second oxygen generation systems are identical in structure;
The oxygen concentration detection device comprises an oxygen separation assembly for supplying oxygen, a heating assembly connected with the oxygen separation assembly, a gas pump connected with the heating assembly, and an oxygen concentration detection sensor arranged at the output end of the oxygen separation assembly;
in some possible embodiments, the oxygen separation assembly is a molecular sieve oxygen separation device;
the molecular sieve oxygen separation device comprises at least two groups of molecular sieve oxygen separation pieces which are connected in parallel and are respectively connected with the gas pump; the other end of the molecular sieve oxygen separator is in communication with the oxygen inlet of the first hydrogen fuel cell system.
In some possible embodiments, the hooking and releasing mechanism comprises a connecting flange installed at the bottom of the second equipment compartment, a hanging rope with one end connected with the connecting flange and the other end connected with the aircraft body, and a cutting mechanism installed on the connecting flange and used for cutting the hanging rope; the cutting mechanism is connected with the second fuel control module.
In some possible embodiments, the first equipment compartment pressure regulation and control system comprises a flight hydrogen charging tank, a first pressure sensor arranged outside the first equipment compartment, a second pressure sensor arranged in the first equipment compartment, a third hydrogen discharging electromagnetic valve and a fourth hydrogen charging electromagnetic valve which are respectively communicated with the flight hydrogen charging tank, and a regulation and control module respectively connected with the first pressure sensor, the second pressure sensor, the third hydrogen discharging electromagnetic valve and the fourth hydrogen charging electromagnetic valve; the air release port of the third hydrogen release electromagnetic valve is communicated with the outside of the first equipment cabin; the fourth hydrogen charging electromagnetic valve is positioned in the first equipment cabin and communicated with the interior of the first equipment cabin.
The flying method based on the aircraft specifically comprises the following steps:
step S1, delivering through a delivery system, and separating an aircraft body from the system when flying to near space:
step S11: injecting hydrogen into the hydrogen storage container;
step S12: the hydrogen storage container drives the aircraft body to ascend in the atmosphere;
step S13: when flying to the near space, the hooking and releasing mechanism separates the aircraft body from the delivery system;
s2, the aircraft body flies by itself, and the delivery system returns to the ground;
the self-flying of the aircraft body specifically means that: the hydrogen in the flight cabin and the oxygen prepared by the first oxygen generating system are conveyed to the first hydrogen fuel cell system for fuel supply, and kinetic energy is provided for the aircraft body through the first hydrogen fuel cell system;
when the difference between the hydrogen pressure in the first equipment cabin and the atmospheric pressure at the height of the first equipment cabin is higher than the design pressure in the flight process of the aircraft body, releasing part of hydrogen in the first equipment cabin into the atmosphere through a first equipment cabin pressure regulating and controlling system so as to maintain the pressure at the design pressure;
when the difference between the hydrogen pressure in the first equipment cabin and the atmospheric pressure at the height of the first equipment cabin is monitored to be lower than the design pressure, the hydrogen is conveyed into the first equipment cabin through the first equipment cabin pressure regulating and controlling system so as to maintain the pressure at the design pressure.
Compared with the prior art, the invention has the beneficial effects that:
according to the invention, the aircraft is delivered to the nearby space through the delivery system to fly automatically, before flying to the nearby space, the fuel in the aircraft body is not consumed, and the fuel in the aircraft body can be consumed only when the aircraft flies automatically, so that the energy consumption of the aircraft in a take-off stage is greatly reduced, limited energy can be directly used for the cruising flight of the aircraft, the endurance of the aircraft is effectively improved, and the long-endurance cruising flight is realized;
according to the invention, the aircraft is rapidly delivered to the adjacent space through the reusable hydrogen energy-driven delivery system, and released after reaching the specified height, so that the energy consumption of the aircraft in the process of ascending to the adjacent space is reduced; limited energy can be directly used for cruising flight of the aircraft, so that the cruising time of the aircraft is effectively improved, and long-cruising flight is realized; the delivery system is driven by the hydrogen energy system to automatically drop to a designated drop point, and is repeatedly used, so that the economy is good;
the second oxygen generation system can be used for preparing oxygen in a low-temperature and low-pressure environment, and provides the needed oxygen for the second hydrogen fuel cell system; compared with the prior art, the hydrogen and the oxygen are carried on the aircraft at the same time, so that the effective load of the aircraft is greatly reduced;
According to the invention, through the use of the hydrogen storage container, part of lifting force is additionally provided, so that the energy consumption of an aircraft in a take-off stage is greatly reduced, and the weight of the high-pressure hydrogen storage tank is reduced; the hydrogen in the hydrogen storage container is used as fuel of the second hydrogen fuel cell system and additionally provides lift force;
compared with a fuel oil power system, the hydrogen fuel cell system is high in specific energy density and strong in power, and can be used for rapidly delivering the aircraft body to an adjacent space, and the aircraft body can effectively fly after separation;
the invention takes the flight cabin of the unmanned aerial vehicle as one flight cabin, and other systems of the unmanned aerial vehicle are all distributed around the flight cabin; compared with a 70MPa high-pressure hydrogen storage tank mode in the prior art, the hydrogen storage quantity is larger, and the specific hydrogen storage capacity is larger; meanwhile, when high-pressure hydrogen in the flight cabin is consumed and returns to the ground, the hydrogen storage container body can provide extra buoyancy in the air, so that the unmanned aerial vehicle can stably land;
the invention can produce oxygen under the environment conditions of low temperature and low pressure in the near space, and solves the problem that the energy output of the hydrogen fuel cell is unstable due to low temperature and low atmospheric pressure in the near space;
In the invention, the flight cabin and the first equipment cabin are manufactured by high-strength carbon fibers; because the strength of the carbon fiber, the elastic die is high, the weight is light, and the flight cabin or the first equipment cabin manufactured by the material is high in strength, good in rigidity of the shell and light in weight; the limited load of the aircraft is improved through the lightweight design;
according to the invention, the first equipment cabin pressure automatic regulation and control system is arranged in the first equipment cabin loaded with the flight airborne system, so that the regulation and control of the first equipment cabin gas pressure is realized, the first equipment cabin gas pressure is ensured to be higher than the external environment atmospheric pressure, and the pressure difference is within an allowable design range, so that the rigidity of the first equipment cabin is maintained; by adopting the arrangement, the heat exchange of the air in the first equipment cabin and the air outside the first equipment cabin is reduced through the sealing structure, so that the heat preservation effect of the flying airborne system is facilitated, and the low-temperature environment adaptability of the flying airborne system in the near space is improved;
compared with the scheme of adopting a high-pressure oxygen storage tank in the prior art, the oxygen generation system has smaller occupied space and lighter weight, and can meet the requirements of the unmanned aircraft in the near space on reliability, environmental adaptability and light weight;
Because the atmospheric pressure in the near space is low, nitrogen adsorbed in the molecular sieve to be regenerated is released into the atmosphere through the air release valve; the regeneration of the molecular sieve adsorbed with nitrogen is very simple and does not require a special vacuumizing regeneration system.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic illustration of the connection of a second nacelle, rotor, hitch and release mechanism of the present invention;
fig. 3 is a schematic view showing the structure of a hydrogen storage container body in embodiment 1 of the present invention;
FIG. 4 is a schematic view of a hitching and releasing mechanism according to the present invention;
FIG. 5 is a schematic view of the position of the cutting mechanism and the lanyard of the present invention;
FIG. 6 is a schematic diagram showing the connection relationship among a hydrogen storage container, a second hydrogen supply system, and a second hydrogen fuel cell system according to the present invention;
FIG. 7 is a schematic view of a heating element of the second oxygen generating system or the first oxygen generating system according to the present invention in a countercurrent heat exchanger;
FIG. 8 is a schematic view of a separation column according to the present invention;
FIG. 9 is a schematic view of the structure of the hydrogen container body of the present invention when it is a balloon;
FIG. 10 is a schematic view of the structure of an aircraft body according to the present invention;
FIG. 11 is a top view of an aircraft body according to the invention;
FIG. 12 is a schematic view of the flight deck structure of the present invention;
FIG. 13 is a cross-sectional view of a first equipment bay of the present invention with an aircraft on-board system installed;
FIG. 14 is a schematic diagram showing the connection relationship between a first hydrogen supply system, a hydrogen storage pressure vessel, and a first hydrogen fuel cell system according to the present invention;
FIG. 15 is a schematic diagram of a first equipment bay pressure regulation system according to the present invention;
FIG. 16 is a cross-sectional view of another set of first equipment pods according to the present invention;
wherein: 1. a delivery system; 11. a second equipment bay; 111. a second control and communication system; 112. a second hydrogen fuel cell system; 113. a second hydrogen supply system; 1131. an automatic control valve; 1132. a gas transfer pump; 1133. a self-control valve; 1134. a hydrogen pressure sensor; 1135. a pressure reducing valve; 114. a second oxygen generation system; 1141. an oxygen separation assembly; 11411. an intake valve; 11412. molecular sieve oxygen separation; 114121, an air inlet end; 114122 molecular sieve beds; 114123 zeolite molecular sieve; 114124, an air outlet end; 11413. a bleed valve; 11414. an exhaust valve; 1142. a heating assembly; 1143. a gas pump; 1144. an oxygen concentration detection sensor; 1145. an axial flow fan; 115. a lithium battery energy storage system; 116. a second fuel control module; 12. a rotor; 13. a hydrogen storage container; 131. a hydrogen storage container body; 1311. a balloon body; 1312. tensioning a motor; 1313. a ring wheel; 1314. tensioning the switch; 1315. tensioning the wire; 132. a delivery cabin connecting plate; 133. a gas conduit; 1331. a second electromagnetic valve; 14. a hitching and releasing mechanism; 140. a cutting motor; 141. a connecting flange; 142. hanging rope; 143. a cutting blade; 2. an aircraft body; 21. a flight deck; 211. a gas conduit; 212. a wing connection plate; 213. rotor propeller connection plates; 214. a hoisting ring; 215. a first equipment bay connection board; 216. a sliding wheel connecting plate; 22. a first equipment bay; 221. a mounting frame; 222. a first equipment bay mounting plate; 223. a thin-walled shell; 224. a sealing gasket; 225. a cover plate; 23. a wing; 24. a rotor propeller; 25. a skid wheel; 26. a first equipment compartment pressure regulation system; 261. a flying hydrogen charging tank; 262. a first pressure sensor; 263. a second pressure sensor; 264. a third hydrogen release solenoid valve; 265. a fourth hydrogen charging solenoid valve; 266. a regulation control module; 27. a first oxygen generation system; 28. a first hydrogen supply system; 29. a first fuel control module; 210. a first hydrogen fuel cell system; 220. a communication and flight control system; 230. a lithium battery energy storage system; 240. an on-board power management system.
Detailed Description
The present invention will be described in detail below.
As shown in fig. 1-16:
an aircraft with a hydrogen energy delivery system 1 comprises an aircraft body 2, a delivery system 1 connected with the aircraft body 2;
the delivery system 1 comprises a second equipment compartment 11 installed on the aircraft body 2 and provided with a rotor 12 at the outer side, a hydrogen storage container 13 connected with the second equipment compartment 11 and positioned above the second equipment compartment 11, a hooking and releasing mechanism 14 for connecting the aircraft body 2 with the second equipment compartment 11, a second hydrogen supply system 113 communicated with the inside of the hydrogen storage container 13 and installed in the second equipment compartment 11, a second hydrogen fuel cell system 112 positioned in the second equipment compartment 11 and connected with the second hydrogen supply system 113, a second oxygen generation system 114 installed in the second equipment compartment 11 and connected with the second hydrogen fuel cell system 112 for supplying oxygen, and a second fuel control module 116 respectively connected with the hooking and releasing mechanism 14, the second hydrogen supply system 113, the second hydrogen fuel cell system 112 and the second oxygen generation system 114;
the aircraft body 2 comprises a wing 23, two groups of first equipment cabins 22 which are arranged at the bottom of the wing 23 and symmetrically arranged along the course, a flight cabin 21 which is positioned between the two groups of first equipment cabins 22 and is used as a hydrogen storage pressure container, a hydrogen energy supply system connected with the flight cabin 21, a first oxygen generation system 27 connected with the hydrogen energy supply system, a first fuel control module 29 respectively connected with the hydrogen energy supply system and the first oxygen generation system 27, a flight onboard system and a first equipment cabin pressure regulating system 26;
The hydrogen energy supply system, the first oxygen generation system 27 and the first fuel control module 29 are positioned in the same first equipment compartment 22;
the aircraft on-board system, first equipment bay pressure regulation system 26 is located within another set of first equipment bays 22;
to effectively realize the transportation of the hydrogen in the flight chamber 21 to the hydrogen energy supply system and the supply of the energy by the reaction with the oxygen prepared by the first oxygen generating system 27; the hydrogen energy supply system includes a first hydrogen fuel cell system 210, a first hydrogen supply system 28 connected to the first hydrogen fuel cell system 210 and supplying hydrogen to the first hydrogen fuel cell system 210, the first hydrogen supply system 28 being connected to the flight deck 21.
Working principle: before delivery, the second equipment compartment 11 is first connected with the aircraft body 2, and hydrogen is injected into the hydrogen storage container 13; the hydrogen is stored in the hydrogen storage container 13, so that the hydrogen can provide partial lifting force for the whole system in the lifting process, the energy consumption of the aircraft body 2 in the take-off stage is greatly reduced, and meanwhile, the weight of the high-pressure hydrogen storage tank is effectively reduced due to the adoption of the hydrogen storage container 13 for storing the hydrogen; the hydrogen gas in the hydrogen storage container 13 is also supplied to the second hydrogen supply system 113 as fuel of the second hydrogen fuel cell system 112 during flight; after the aircraft flies to the near space, the delivery system 1 is separated from the aircraft, and the delivery system 1 falls to a designated falling point automatically under the pushing of a hydrogen energy system of the delivery system 1, so that the aircraft is repeatedly used and has good economy;
After the hydrogen is injected into the specified quantity, the hydrogen storage container 13 is lifted off and drives the aircraft body 2 to fly towards the nearby space, and the hydrogen in the hydrogen storage container 13 is conveyed to the second hydrogen fuel cell system 112 through the second hydrogen supply system 113 to serve as hydrogen fuel in the flying process;
when flying to the near space, the second equipment compartment 11 is separated from the aircraft by the hooking and releasing mechanism 14, and the aircraft body 2 flies by itself after entering the near space; the delivery system 1 returns to the ground;
when the pressure difference between the hydrogen pressure in the first equipment compartment 22 and the atmospheric pressure at the height of the first equipment compartment is higher than the design pressure in the process of flying near space, the aircraft body 2 releases part of hydrogen in the first equipment compartment into the atmosphere through the first equipment compartment pressure regulating and controlling system 26 so as to maintain the pressure near the design pressure;
when the difference between the hydrogen pressure in the first equipment compartment 22 and the atmospheric pressure at the height of the first equipment compartment is lower than the design pressure, the hydrogen is conveyed into the first equipment compartment 22 through the first equipment compartment pressure regulating and controlling system 26 so as to maintain the pressure around the design pressure;
the arrangement of the first equipment cabin pressure regulating system 26 can effectively maintain the gas pressure in the first equipment cabin 22 to be higher than the external environment atmospheric pressure all the time in the ascending and descending processes of the unmanned aerial vehicle, and the pressure difference is always maintained within the design requirement range; the rigidity of the first equipment compartment 22 is effectively maintained.
The hydrogen in the flight cabin 21 and the oxygen prepared by the first oxygen generating system 27 are respectively transmitted to a hydrogen energy supply system, and are converted into electric energy after reaction to realize the electric energy supply of the unmanned aerial vehicle, so that the unmanned aerial vehicle realizes navigation; the aircraft body 2 takes the whole flight cabin 21 as the flight cabin 21, realizes the energy supply of the unmanned aircraft by arranging a hydrogen energy supply system in one group of first equipment cabins 22, and realizes the flight control by arranging a flight airborne system in the other group of first equipment cabins 22; compared with the prior art, a high-pressure hydrogen storage tank is omitted, the flight cabin 21 is adopted as a hydrogen storage space, the hydrogen storage amount is larger, and the specific hydrogen storage capacity is larger;
the delivery system 1 is combined with the whole flight cabin 21 as the flight cabin 21, so that the aircraft can effectively realize long-endurance flight, and is beneficial to exploration in a nearby space;
in some possible embodiments, to effectively achieve the delivery of hydrogen gas within the flight deck 21 or the hydrogen storage container 13 to the corresponding hydrogen fuel cell system (first hydrogen fuel cell system 210, second hydrogen fuel cell system 112);
as shown in fig. 6 and 13, the first hydrogen supply system 28 and the second hydrogen supply system 113 have the same structure;
Comprising an automatic control valve 1131, a gas transfer pump 1132 connected with the automatic control valve 1131, an automatic control valve 1133 connected with the gas transfer pump 1132, a hydrogen pressure sensor 1134 arranged on a connecting pipeline of the automatic control valve 1131 and the gas transfer pump 1132, and a pressure reducing valve 1135 connected with the gas transfer pump 1132 in parallel. The gas transfer pump 1132 is an oil-free hydrogen transfer pump;
specific: when the hydrogen pressure sensor 1134 detects that the hydrogen pressure in the flight chamber 21 or the second equipment chamber 11 is higher than 0.2MPa, the first fuel control module 29 or the second fuel control module 116 closes the gas transfer pump 1132 by opening the automatic control valve 1131, the pressure reducing valve 1135 and the self-control valve 1133, and supplies hydrogen to the first hydrogen fuel cell system 210 or the second hydrogen fuel cell system 112;
when the hydrogen pressure sensor 1134 detects that the hydrogen pressure is less than 0.2MPa, the first fuel control module 29 or the second fuel control module 116 supplies hydrogen to the first hydrogen fuel cell system 210 or the second hydrogen fuel cell system 112 by opening the automatic control valve 1131, the gas transfer pump 1132, the self-control valve 1133, and simultaneously closing the pressure reducing valve 1135;
in order to effectively ensure the transfer of hydrogen, the lowest inlet pressure of the gas transfer pump 1132 is less than 10kPa, the outlet pressure is more than 0.5MPa, and the gas leakage rate is high <1×10 -7 Pa.m 3 .s -1 。
In some possible embodiments, the hydrogen storage container 13 includes a hydrogen storage container body 131 mounted on the second equipment compartment 11, and a gas pipe 133 having both ends communicating with the hydrogen storage container body 131 and the second hydrogen supply system 113.
In order to effectively perform the injection of hydrogen gas into the hydrogen storage container body 131 at the time of the ground, as shown in fig. 6, a second solenoid valve 1331 connected to the second fuel control module 116 is provided on the gas pipe 133; a second electromagnetic valve 1331 is provided on the gas pipe 133 as a valve for supplying hydrogen gas into the hydrogen storage container 13 when it is at the ground level;
in some possible embodiments, in order to avoid damage to the hydrogen storage container body 131 during delivery, the hydrogen storage container body 131 and the flight chamber 21 are made of carbon fibers, and the hydrogen storage container body 131 made of the material has high strength, good rigidity of a shell and light weight, and has high strength and high elastic modulus; the limited load is improved through the lightweight design;
in order to meet the hydrogen fuel consumption requirement of the delivery system, the working pressure of the hydrogen storage container body 131 is 5MPa-30MPa, and the volume of the hydrogen storage container body 131 is 20m 3 -50m 3 Gas leakage rate<1×10 -7 P.am 3 .s -1 ；
In order to avoid damage to the hydrogen storage container body 131 caused by vacuum inside the hydrogen storage container body 131 during delivery of the aircraft, the hydrogen storage container body 131 has an external pressure bearing capacity of Δp, Δp=p External pressure -P Internal pressure of >0.15MPa; wherein P is External pressure Is the pressure of the outside of the hydrogen storage container body 131, P Internal pressure of Is the pressure on the outside of the hydrogen storage container body 131.
In order to avoid that the flight deck 21 is damaged by the external atmospheric pressure when the hydrogen is evacuated; the working pressure of the flight chamber 21 is 5MPa to 20MPa, and the gas leakage rate is high<1×10 -7 Pa.m 3 .s -1 With a volume of 5m 3 -30m 3 ；
The external pressure bearing capacity of the flight chamber 21 is Δp, Δp=p External pressure -P Internal pressure of >0.15MPa; wherein P is External pressure For pressure outside the flight chamber 21, P Internal pressure of Is the pressure inside the flight deck 21.
Further, as shown in fig. 1, 9, 10, 11, and 12, the flight chamber 21 is cylindrical, the long axis direction thereof is set along the heading direction, and the hydrogen storage container body 131 has a spherical structure; the flight deck 21 is connected with the second equipment deck 11 through a second equipment deck connecting plate 132 arranged at the bottom of the flight deck, and a gas pipeline 133 is connected with the second hydrogen supply system 113; the second hydrogen supply system 113 is directly connected to the gas pipe 133;
in some possible embodiments, as shown in fig. 9, the hydrogen storage container body 131 is a balloon having a volume of 20m in communication with the gas pipe 133 3 -50m 3 Gas leakage rate<1×10 -6 MPa.m 3 .s -1 The method comprises the steps of carrying out a first treatment on the surface of the Comprises a balloon body 1311 arranged on a second equipment cabin connecting plate 132, a tensioning motor 1312 arranged in the balloon body 1311, a ring wheel 1313 in transmission connection with the tensioning motor 1312, and a tensioning assembly with one end connected with the ring wheel 1313 and the other end connected with the top of the balloon body 1311;
The tightening assembly includes a tightening switch 1314, a tightening wire 1315 for the tightening switch 1314 and the reel 1313, and the tightening switch 1314 and the balloon body 1311.
The balloon comprises a balloon body 1311 arranged on the second equipment cabin connecting plate 132, a tensioning motor 1312 arranged in the balloon body 1311, a ring wheel 1313 in transmission connection with the tensioning motor 1312, and a tensioning component with one end connected with the ring wheel 1313 and the other end connected with the top of the balloon body 1311, wherein the tensioning motor 1312, the ring wheel 1313 and the tensioning component are all positioned in the balloon body 1311;
the tightening assembly includes a tightening switch 1314, a tightening wire 1315 for the tightening switch 1314 and the reel 1313, and the tightening switch 1314 and the balloon body 1311.
When the tension wire 1315 is in a tensioned state, the pullswitch is in an off state; as the hydrogen in the balloon body 1311 is delivered to the fuel of the second hydrogen fuel cell system 112 and is delivered to the second hydrogen supply system 113, the tension wire 1315 will be changed from a tension state to a relaxation state, at this time, the tension switch is closed, the tension motor 1312 will receive the tension wire 1315 on the reel 1313, and finally, the balloon body 1311 will be received in a receiving compartment provided on the second equipment bay connection board 132.
In some possible embodiments, as shown in fig. 7-8, the first oxygen generation system 27 and the second oxygen generation system 114 are identical in structure; comprises an oxygen separation assembly 1141 for supplying oxygen, a heating assembly 1142 connected with the oxygen separation assembly 1141, a gas pump 1143 connected with the heating assembly 1142, and an oxygen concentration detection sensor 1144 arranged at the output end of the oxygen separation assembly 1141; a gas pump 1143 is disposed between the oxygen separation assembly 1141 and the heating assembly 1142.
Air in the low-temperature low-atmospheric-pressure environment enters the heating component 1142 after being pressurized by the gas pump 1143, the air in the heating component 1142 is heated to be normal-temperature gas, then the normal-temperature gas is conveyed to the oxygen separation component 1141 through the gas pump 1143 to separate oxygen from nitrogen, the oxygen after being separated by the oxygen concentration detection sensor 1144 is detected, and the oxygen after reaching the concentration requirement is conveyed to the first hydrogen fuel cell system 210, and the nitrogen is discharged, so that oxygen production in the low-temperature low-atmospheric-pressure environment is effectively realized.
The oxygen concentration detection sensor 1144 is configured to detect the concentration of oxygen that is to enter the first hydrogen fuel cell system 210 after separation; when the oxygen concentration is lower than 50%, as shown in fig. 7, the first fuel control module 29 or the second fuel control module 116 controls the air inlet valve 11411 and the air outlet valve 11414 corresponding to one group of separation columns to close, and opens the air release valve 11413, so that nitrogen adsorbed by zeolite molecular sieves in the separation columns is released to the atmosphere; at the same time, the first fuel control module 29 or the second fuel control module 116 will control the intake valve 11411 and the exhaust valve 11414 corresponding to the other group of separation columns to open and close the purge valve 11413; in this way, the first fuel control module 29 or the second fuel control module 116 controls the corresponding valves to alternately operate the separation column in the two operation modes of oxygen-nitrogen separation and molecular sieve regeneration, so as to achieve the purpose of continuously producing oxygen and regenerating the molecular sieve.
Further, the heating component 1142 may be an electric heater with a gas pipe, where the second hydrogen fuel cell system 112 and the first hydrogen fuel cell system 210 do not supply heat energy to the corresponding first oxygen generating system 27 or the second oxygen generating system 114;
as shown in fig. 7, the heating assembly 1142 may also be a counter flow heat exchanger with a gas line; when it is a counter-flow heat exchanger, a thermal circulation line is provided between the counter-flow heat exchanger and the second hydrogen fuel cell system 112 or the first hydrogen fuel cell system 210; the heat circulation pipeline is used for effectively heating the low-temperature air in the countercurrent heat exchanger by extracting the heat generated during the operation of the first hydrogen fuel cell system 210, and the heated air enters the oxygen separation assembly 1141, so that the working environment is good.
In some possible embodiments, the oxygen separation assembly 1141 is a molecular sieve oxygen separation device; the molecular sieve oxygen separation device comprises at least two groups of molecular sieve oxygen separation pieces 11412 which are connected in parallel and are respectively connected with a gas pump 1143; the other end of the molecular sieve oxygen separator 11412 communicates with the oxygen inlet of the first hydrogen fuel cell system 210.
The separation column comprises a molecular sieve bed 114122 provided with an air inlet end 114121 and an air outlet end 114124 and provided with a cavity inside, and a zeolite molecular sieve 114123 filled in the cavity; the inlet 114121 and outlet 114124 are in communication with the cavity, respectively.
A pipe for connecting the heating assembly 1142 and the air inlet port 114121 is provided at the air inlet port 114121, and an air inlet valve 11411 is provided on the pipe;
at the outlet end 114124, a pipe for connecting the first hydrogen fuel cell system 210 and the outlet end 114124 is provided, and a purge valve 11413 and an exhaust valve 11414 are provided on the pipe. Molecular sieve bed 114122 is made of light material and has gas leakage rate<1×10 -7 Pa.m 3 .s-1；
Further, the molecular sieve bed 114122 is made of a lightweight material, such as plastic, so that it is lightweight;
in order to effectively realize pressurization of low-atmospheric-pressure air, the problem of oxygen production performance reduction caused by the fact that the zeolite molecular sieve 114123 material loses activity due to pressurized oil vapor is avoided; the air pump 1143 may be a chinese patent with application number 2022211845482, named high purity air booster and air flow intelligent control pump;
specifically, the gas pump 1143 includes a base, a variable frequency gear motor, a crankshaft connecting rod assembly for connecting the base and the variable frequency gear motor into a whole, a piston and cylinder assembly installed in the base, and a diaphragm assembly arranged between a lower cylinder cover and an upper cylinder cover assembly above the base;
the diaphragm assembly is configured to include upper and lower spacers disposed in spaced opposition, and a plurality of layers of first diaphragms disposed between the upper and lower spacers; the first diaphragms of each layer are provided with curved surface structures which are matched with the molded surfaces in the upper cylinder cover assembly and the lower cylinder cover in space, and under the action of oil pressure deformation, the curved surface radius and the height of the first diaphragms are configured to be the same as the curved surface radius and the height of the molded surfaces; the first membranes of each layer are configured to be made of a plastically deformable material, and have a thickness of between 0.05 and 0.1mm, and the number of first membranes is 8 to 10.
Further, the exhaust valve 11414 is an automatic control exhaust valve, the air release valve 11413 is an automatic control air release valve, the air intake valve 11411 is an automatic control air intake valve, and the above three components, the oxygen concentration detection sensor 1144 and the heating component 1142 are respectively connected with the first fuel control module 29 or the second fuel control module 116; the first fuel control module 29 or the second fuel control module 116 achieves a temperature of the air entering the molecular sieve near room temperature (25 ℃) by controlling the heating assembly 1142.
In some possible embodiments, the second equipment bay 11 is connected and disconnected from the aircraft body 2 for efficient implementation; as shown in fig. 4 and 5, the hooking and releasing mechanism 14 includes a connection flange 141 installed at the bottom of the second equipment compartment 11, a hanging rope 142 having one end connected to the connection flange 141 and the other end connected to the aircraft body 2, and a cutting mechanism installed on the connection flange 141 for cutting the hanging rope 142; the cutting mechanism is coupled to a second fuel control module 116.
The connecting flange 141 is used for connecting the aircraft body 2 and the second equipment compartment 11 through a hanging rope 142, and the cutting mechanism is arranged on the connecting flange 141 and comprises a cutting motor 140 and a cutting blade 143, wherein the cutting motor 140 is arranged on the connecting flange 141, and the output shaft is arranged vertically; when cutting, the cutting motor 140 is started under the control of the second fuel control module 116 and drives the cutting blade 143 to rotate so as to cut the hanging rope 142; the separation of the second equipment compartment 11 and the aircraft body 2 can be effectively realized by adopting the mode, and the structure is simple and the weight is light;
Further, as shown in fig. 2, a second control and communication system 111 is further disposed in the second equipment compartment 11 and used in cooperation with the rotor 12; the second hydrogen fuel cell system 112 is used to power the hitch and release mechanism 14, the second oxygen generation system 114, and the rotor 12, second oxygen generation system 114 connections.
In some possible embodiments, as shown in fig. 6, the first equipment bay pressure regulation system 26 includes a flight hydrogen charging tank 261, a first pressure sensor 262 disposed outside of the first equipment bay 22, a second pressure sensor 263 disposed within the first equipment bay 22, a third hydrogen discharge solenoid valve 264 and a fourth hydrogen charging solenoid valve 265 in communication with the flight hydrogen charging tank 261, respectively, and a regulation control module 266 connected with the first pressure sensor 262, the second pressure sensor 263, the third hydrogen discharge solenoid valve 264 and the fourth hydrogen charging solenoid valve 265, respectively;
the air release port of the third hydrogen release electromagnetic valve 264 is communicated with the outer side of the first equipment compartment 22; the fourth hydrogen solenoid 265 is located within the first equipment compartment 22 and communicates with the interior of the first equipment compartment 22.
When the regulation control module 266 detects that the pressure difference between the inside of the first equipment compartment 22 and the outside of the first equipment compartment 22 is higher than the designed internal-external pressure difference, the designed internal-external pressure difference is 15kPa-10kPa; the regulation control module 266 controls the third hydrogen release solenoid valve 264 to open and release hydrogen to the atmosphere;
When the regulation control module 266 detects that the pressure difference between the inside of the first equipment compartment 22 and the outside of the first equipment compartment 22 is lower than the design pressure difference, the design internal-external pressure difference is 15kPa-10kPa; the regulation control module 266 controls the fourth hydrogen charging solenoid valve 65 to open and charge hydrogen into the first equipment compartment 22 so that the internal and external pressure difference of the first equipment compartment 22 is within a design range to maintain the rigidity of the first equipment compartment 22;
further, the third hydrogen discharging solenoid valve 264 and the fourth hydrogen charging solenoid valve 265 are normally closed solenoid valves;
further, as shown in fig. 15 and 16, the first equipment compartment 22 is also made of carbon fiber material; the limited load of the aircraft body 2 is improved through the lightweight design of the flight deck 21, the first equipment deck 22 and the hydrogen storage container body 131; this technology has been widely used in the manufacture of small volume high pressure hydrogen storage tanks, and is mature and not described in detail herein.
The first equipment compartment 22 comprises a thin-wall shell 223, a first equipment compartment mounting plate 222 mounted outside the thin-wall shell 223 and connected with the wing 23, a mounting bracket arranged in the thin-wall shell 223 and connected with the thin-wall shell 223 to form a mounting cavity, and a cover plate 225 connected with one side of the thin-wall shell 223 far away from the mounting cavity and matched with the shell to form a sealing cavity;
The first equipment bay mounting plate 222 is connected to the first equipment bay connector plate 215 located on the flight bay 21;
the mounting bracket is positioned in the sealed cavity and is in sealing connection with the shell;
further, the mounting bracket, the first equipment bay mounting plate 222 is fabricated from a high strength aluminum alloy;
the mounting frame 221 is integrally formed with the thin-wall shell 223, and a sealing gasket 224 is arranged between the thin-wall shell 223 and the cover plate 225, so that the sealing performance of the sealing chamber is ensured; the formed sealing structure reduces the heat exchange of the air in and out of the first equipment compartment 22, is beneficial to the heat preservation effect of the airborne system, and improves the low-temperature environment adaptability of the airborne system in the adjacent space.
Further, a wing connection plate 212 for connecting the wings 23, a runner connection plate 216 for mounting the runner 25, a rotor propeller connection plate 213 for mounting the rotor 12 propeller, and a gas conduit 211 connected to the first hydrogen supply system 28 are provided outside the flight chamber 21.
The flight chamber 21 is in a columnar structure, the axial direction of the flight chamber is along the course direction of the flight chamber, and the sliding wheel connecting plate 216 is arranged at the bottom of the flight chamber 21;
wings 23, planing wheels 25, rotor 12 propellers, and flying on-board systems are prior art and are not described in detail herein; further, the flight onboard system comprises a communication and flight control system 220, a lithium battery energy storage system 230 and an onboard power management system 240;
The flying method based on the aircraft specifically comprises the following steps:
step S1, delivering by the delivery system 1, and separating the aircraft body 2 from the system when flying to the near space:
step S11: injecting hydrogen gas into the hydrogen storage container 13;
step S12: the hydrogen storage container 13 drives the aircraft body 2 to ascend in the atmosphere;
in the take-off stage, oxygen prepared by the second oxygen generating system 114 and hydrogen in the hydrogen storage container 13 are conveyed to the second hydrogen fuel cell system 112, and the second hydrogen fuel cell system 112 is used as an energy supply system in the take-off stage to drive the aircraft body 2 to fly to the adjacent space;
step S13: the hooking and releasing mechanism 14 separates the aircraft body 2 from the delivery system 1 when flying to the near space;
s2, the aircraft body 2 flies by itself, and the delivery system 1 returns to the ground;
the self-flying of the aircraft body 2 specifically means: the hydrogen in the flight chamber 21 and the oxygen prepared by the first oxygen generating system 27 are conveyed to the first hydrogen fuel cell system 210 for fuel supply, and the first hydrogen fuel cell system 210 provides kinetic energy for the aircraft body 2;
when the difference between the hydrogen pressure in the first equipment compartment 22 and the atmospheric pressure at the height of the first equipment compartment is higher than the design pressure in the flight process of the aircraft body 2, the first equipment compartment pressure regulating and controlling system 26 releases part of hydrogen in the first equipment compartment to the atmosphere so as to maintain the pressure at the design pressure;
When it is detected that the difference between the hydrogen pressure in the first equipment compartment 22 and the atmospheric pressure at the level thereof is lower than the design pressure, hydrogen is fed into the first equipment compartment 22 through the first equipment compartment pressure regulating system 26 to maintain the pressure at the design pressure.
The invention is not limited to the specific embodiments described above. The invention extends to any novel one, or any novel combination, of the features disclosed in this specification, as well as to any novel one, or any novel combination, of the steps of the method or process disclosed.
Claims (10)
1. An unmanned near space vehicle with a delivery system is characterized by comprising a vehicle body and the delivery system connected with the vehicle body;
the delivery system comprises a second equipment cabin which is arranged on the aircraft body and is provided with a rotor wing at the outer side, a hydrogen storage container which is connected with the second equipment cabin and is positioned above the second equipment cabin, a hooking and releasing mechanism which is used for connecting the aircraft body and the second equipment cabin, a second hydrogen supply system which is communicated with the inside of the hydrogen storage container and is arranged in the second equipment cabin, a second hydrogen fuel cell system which is positioned in the second equipment cabin and is connected with the second hydrogen supply system, a second oxygen generation system which is arranged in the second equipment cabin and is used for supplying oxygen to the second hydrogen fuel cell system, and a second fuel control module which is respectively connected with the hooking and releasing mechanism, the second hydrogen supply system, the second hydrogen fuel cell system and the second oxygen generation system;
The aircraft body comprises a wing, two groups of first equipment cabins which are arranged at the bottom of the wing and are symmetrically arranged along the course, a flight cabin which is positioned between the two groups of first equipment cabins and is used as a hydrogen storage pressure container, a hydrogen energy supply system connected with the flight cabin, a first oxygen generation system connected with the hydrogen energy supply system, a first fuel control module respectively connected with the hydrogen energy supply system and the first oxygen generation system, a flight airborne system, a first equipment cabin pressure regulation system and a pressure control module connected with the first equipment cabin pressure regulation system;
the hydrogen energy supply system, the first oxygen generation system and the first fuel control module are positioned in the same first equipment cabin;
the flight airborne system and the first equipment cabin pressure regulation and control system are positioned in another group of first equipment cabins;
the hydrogen energy supply system comprises a first hydrogen fuel cell system and a first hydrogen supply system which is connected with the first hydrogen fuel cell system and supplies hydrogen for the first hydrogen fuel cell system, and the first hydrogen supply system is connected with the flight cabin.
2. The unmanned near space vehicle having a delivery system of claim 1, wherein the first hydrogen supply system and the second hydrogen supply system are identical in structure;
The device comprises an automatic control valve, a gas transfer pump connected with the automatic control valve, an automatic control valve connected with the gas transfer pump, a hydrogen pressure sensor arranged on a connecting pipeline of the automatic control valve and the gas transfer pump, and a pressure reducing valve connected with the gas transfer pump in parallel.
3. The unmanned near space vehicle with delivery system of claim 1, wherein the hydrogen storage vessel comprises a hydrogen storage vessel body mounted on the second equipment compartment, and a gas conduit having two ends in communication with the hydrogen storage vessel body and the second hydrogen supply system.
4. The unmanned near space vehicle with delivery system of claim 3, wherein the hydrogen storage container body and the flight chamber are made of carbon fiber, and have working pressure of 5-30 MPa and gas leakage rate<1×10 -7 Pa.m 3 .s -1 ；
The external pressure bearing capacities of the hydrogen storage container body and the flight cabin are deltaP, deltaP=P External pressure -P Internal pressure of >0.15MPa；
The volume of the hydrogen storage container body is 20m 3 -50m 3 The volume of the flight chamber is 5m 3 -30m 3 ；
Wherein P is External pressure Is the outside pressure, P Internal pressure of Is the pressure of the inner side.
5. A near space unmanned aerial vehicle having a delivery system of claim 3 wherein the hydrogen storage container body is a balloon in communication with a gas conduit; the device comprises a balloon body arranged on a second equipment cabin connecting plate, a tensioning motor arranged in the balloon body, a ring wheel in transmission connection with the tensioning motor, and a tensioning assembly, wherein one end of the tensioning assembly is connected with the ring wheel, and the other end of the tensioning assembly is connected with the top of the balloon body;
The tensioning assembly comprises a tensioning switch and a tensioning wire used for the tensioning switch and the ring wheel and the tensioning switch and the balloon body.
6. The unmanned near space vehicle having a delivery system of claim 1, wherein the first and second oxygen generating systems are identical in structure;
the oxygen concentration detection device comprises an oxygen separation assembly for oxygen supply, a heating assembly connected with the oxygen separation assembly, a gas pump connected with the heating assembly, and an oxygen concentration detection sensor arranged at the output end of the oxygen separation assembly.
7. The unmanned near space vehicle with delivery system of claim 6, wherein the oxygen separation assembly is a molecular sieve oxygen separation device;
the molecular sieve oxygen separation device comprises at least two groups of molecular sieve oxygen separation pieces which are connected in parallel and are respectively connected with the gas pump; the other end of the molecular sieve oxygen separator is in communication with the oxygen inlet of the first hydrogen fuel cell system.
8. The unmanned near space vehicle with delivery system of claim 1, wherein the hitching and releasing mechanism comprises a connecting flange mounted at the bottom of the second equipment compartment, a hitching rope having one end connected to the connecting flange and the other end connected to the vehicle body, and a cutting mechanism mounted on the connecting flange for cutting the hitching rope; the cutting mechanism is connected with the second fuel control module.
9. The unmanned near space vehicle with delivery system of claim 1, wherein the first equipment bay pressure regulation system comprises a flight charging tank, a first pressure sensor disposed outside the first equipment bay, a second pressure sensor disposed within the first equipment bay, a third and a fourth hydrogen-charging solenoid valve in communication with the flight charging tank, respectively, and a regulation control module in communication with the first pressure sensor, the second pressure sensor, the third hydrogen-charging solenoid valve, and the fourth hydrogen-charging solenoid valve, respectively;
the air release port of the third hydrogen release electromagnetic valve is communicated with the outside of the first equipment cabin; the fourth hydrogen charging electromagnetic valve is positioned in the first equipment cabin and communicated with the interior of the first equipment cabin.
10. A method of flying a unmanned near space vehicle according to any one of claims 1 to 9, comprising the steps of:
step S1, carrying out aircraft delivery through a delivery system, wherein when flying to near space, the aircraft body is separated from the system:
step S11: injecting hydrogen into the hydrogen storage container;
step S12: the hydrogen storage container drives the aircraft body to ascend in the atmosphere;
Step S13: when flying to the near space, the hooking and releasing mechanism separates the aircraft body from the delivery system;
s2, the aircraft body flies by itself, and the delivery system returns to the ground;
the self-flying of the aircraft body specifically means that: the hydrogen in the flight cabin and the oxygen prepared by the first oxygen generating system are conveyed to the first hydrogen fuel cell system for fuel supply, and kinetic energy is provided for the aircraft body through the first hydrogen fuel cell system;
when the difference between the hydrogen pressure in the first equipment cabin and the atmospheric pressure at the height of the first equipment cabin is higher than the design pressure in the flight process of the aircraft body, releasing part of hydrogen in the first equipment cabin into the atmosphere through a first equipment cabin pressure regulating and controlling system so as to maintain the pressure at the design pressure;
when the difference between the hydrogen pressure in the first equipment cabin and the atmospheric pressure at the height of the first equipment cabin is monitored to be lower than the design pressure, the hydrogen is conveyed into the first equipment cabin through the first equipment cabin pressure regulating and controlling system so as to maintain the pressure at the design pressure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311470398.0A CN117602134A (en) | 2023-11-06 | 2023-11-06 | Near space unmanned aerial vehicle with delivery system and flight method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311470398.0A CN117602134A (en) | 2023-11-06 | 2023-11-06 | Near space unmanned aerial vehicle with delivery system and flight method |
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| Publication Number | Publication Date |
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| CN117602134A true CN117602134A (en) | 2024-02-27 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202311470398.0A Pending CN117602134A (en) | 2023-11-06 | 2023-11-06 | Near space unmanned aerial vehicle with delivery system and flight method |
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| Country | Link |
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| CN (1) | CN117602134A (en) |
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2023
- 2023-11-06 CN CN202311470398.0A patent/CN117602134A/en active Pending
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