CN105000183B - Self-propelled dropsonde system - Google Patents
Self-propelled dropsonde system Download PDFInfo
- Publication number
- CN105000183B CN105000183B CN201510365833.2A CN201510365833A CN105000183B CN 105000183 B CN105000183 B CN 105000183B CN 201510365833 A CN201510365833 A CN 201510365833A CN 105000183 B CN105000183 B CN 105000183B
- Authority
- CN
- China
- Prior art keywords
- dropsonde
- gas
- self
- cabin
- sonde
- 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.)
- Active
Links
Classifications
-
- 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
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
-
- 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
Landscapes
- Fuel Cell (AREA)
Abstract
A self-propelled dropsonde system comprises an unmanned aerial vehicle on which a propeller motor, an airborne flight control system and a sonde. A hydrogen storage system is arranged at the interior front part of an unmanned aerial vehicle body; an environment control cabin with a fuel cell is mounted at the middle part of the unmanned aerial vehicle body; and the airborne flight control system is arranged at the rear part of the unmanned aerial vehicle body. The self-propelled dropsonde system provided by the invention is advantaged in that an optimal weight ratio of about 1/10 between a dropsonde and an aircraft and the ceiling is high. As the fuel cell is used as unmanned aerial vehicle energy, the flight time is long. Through an air collecting chamber and a supercharger, the air is heated and pressurized by the unmanned aerial vehicle; and the air inlet temperature and the air density of the environment control cabin are adjusted; therefore, the working performance of the fuel cell at high altitude is improved and enough power for guaranteeing cruising duration is provided to the unmanned aerial vehicle. As a plurality of sondes are mounted on the self-propelled dropsonde system, meteorological data of the atmosphere vertical section can be accurately detected from the plurality of dropsondes at altitudes of 12-20 km in once launching. The self-propelled dropsonde system provided by the invention is advantaged in that the system is economic and environment-friendly and the cost performance of the system is higher.
Description
Technical field
The present invention relates to a kind of weather monitoring system, more particularly to a kind of self-propulsion type Dropsonde system adopting.
Background technology
Weather monitoring field constantly has new technology to occur, such as: what Chinese Patent Application No. 99103819.3 was given " has
Self-navigation and Function for Automatic Pilot, can press planned orbit detection data to floor treatment, certainty of measurement is high, and flexibility is strong "
Miniature robot aircraft by " miniature robot aircraft, digitlization sonde and ground receiver control process system form "
Sounding system；" including fuselage, wing, power drive and control system " that China Patent No. zl 200410070186.4 is given
And the flying height that " wing outer end built-in by airborne sonde " forms reaches more than 4km, for " solving manned aircraft rent
With costliness, so that weather modification operating cost is remained high problem " weather modification miniature robot aircraft；China
" Dropsonde instrument is hung over unmanned plane body or wing bottom by hook " that the patent No. 201110058938.5 is given in order to
The unmanned plane Dropsonde instrument of " solve existing sonde and throw in place and highly inaccurate " problem and its releasing control method.On
State in existing patented technology, it is all less to be mounted in its quantity of sonde that is in body or being articulated in external fuselage,
It is unfavorable in many ways gathering meteorological data in more multizone comprehensively；Two is big as the unmanned plane own wt of sonde carrier, visits
Empty instrument and aircraft weight ratio about 1/300, plug-in sonde, increase flight resistance, have a strong impact on UAV Maneuver performance, fly
It is short to there is the flight time in row device, and continuation of the journey region is little, and ceiling is less than the defect of 4km.Above-mentioned Dropsonde system adopting is to accomplish comprehensively
Multi-faceted collection atmosphere data, unmanned plane needs repeatedly to go up to the air, and sonde needs to repeat lower throwing.Traditional Dropsonde system adopting: property
Valency than low, cost of use is high, uneconomical；Temperature in 4km level above SEQUENCING VERTICAL section, wet can not accurately be obtained in real time
Degree, barometric information data, cause the accurate of the defect of upper atmosphere record vacancy, impact weather forecast and data to use and clothes
Business；Its cost of use is big, waste financial resources.
Content of the invention
The purpose of the present invention is that to provide a kind of airborne sonde quantity many, throws that measurement point is many under sonde, and sonde is thrown in
Precisely, the Dropsonde system adopting under unmanned aerial vehicle onboard relates to long between space-time, liter limit for height, highly high to air Layer Detection, can be real in place
When accurately obtain 12~Temperature in the highly following atmosphere vertical section of 20km, humidity and air pressure data information, are conducive to
The extensive region multi-faceted self-propulsion type Dropsonde system adopting gathering meteorological data comprehensively.
The purpose of the present invention is that by.The self-propulsion type Dropsonde system adopting of the present invention includes being provided with screw
Motor, the unmanned plane of ground control system, airborne flight control system and sonde, the self-propulsion type Dropsonde system adopting feature of the present invention
It is: the front portion in described unmanned aerial vehicle body is provided with hydrogen storage system, middle part is provided with environmental Kuznets Curves cabin, described airborne flight control system sets
Put in fuselage afterbody, in described environmental Kuznets Curves cabin, be provided with a fuel cell, be transversely provided with a cage ring, cage ring is by environment
Control cabinet is separated into forward air supply portion and backside gas discharge unit, and fuel cell separator is become forward part and rear portion
Point, connect a gas booster at the right front in described environmental Kuznets Curves cabin, gas booster passes through air inlet pipe and band spiral
The collection chamber of oar motor connects, and the gas of described collection chamber is the gas flowing through motor and being heated by motor, in described air inlet pipe
One point of gas baffle plate is installed, unmanned plane right flank leading edge is provided with an inflation inlet, inflation inlet is connected at point gas baffle plate with air inlet pipe
Logical, the hydrogen of described hydrogen storage system is connected with the hydrogen inlet of fuel cell, and described unmanned plane body is in gas discharging part
Left side is provided with a gas outlet, and the rear part of described fuel cell is passed through gas outlet and linked up with air, and described fuel cell is constituted
General supply is simultaneously connected with each electricity consumption part of unmanned plane by electric lead.
Self-propulsion type Dropsonde system adopting of the present invention, the fuselage lower abdomen of wherein said unmanned plane is provided with several sondes
Cabin, the lower aerofoil of left and right wing is respectively provided with several sonde cabins respectively, and each sonde cabin is built-in to be placed with a sonde, visits
The hatch door in empty instrument cabin is connected with the hatch door controlling organization circuit of airborne flight control system by electronic mechanism for opening/closing.
Self-propulsion type Dropsonde system adopting of the present invention, wherein said point of gas baffle plate passes through electronic guiding mechanism and airborne winged control system
Point gas control mechanism circuit of system connects.
Self-propulsion type Dropsonde system adopting of the present invention, wherein said point of gas baffle plate has one at 0 °~Random angle in the range of 45 °
Rotary motion trace under degree.
Self-propulsion type Dropsonde system adopting of the present invention, described point of gas flapper, flow through air inlet pipe and enter environmental Kuznets Curves cabin
Air's ratio is in inverse ratio variable condition.
Self-propulsion type Dropsonde system adopting of the present invention, described gas booster changes working condition, the gas in environmental Kuznets Curves cabin
It is the variate-value servo-actuated with gas booster working condition that pressure is worth.
Self-propulsion type Dropsonde system adopting difference from prior art of the present invention is self-propulsion type Dropsonde system of the present invention
System has mission payload weight (Dropsonde instrument) optimum weight percent than about 1/10 with aircraft weight, rises limit for height.Using combustion
, as the energy of High Altitude UAV, hours underway is long for material battery.The present invention utilizes the screw motor of unmanned plane to pass through collection chamber
The air themperature of supply fuel cell is heated, connects collection chamber and the air inlet pipe in environmental Kuznets Curves cabin is provided with air even
Logical point gas baffle plate, changes the angle of point gas baffle plate, and adjustable cold and heat air enters the ratio in environmental Kuznets Curves cabin it is ensured that sending into combustion
The intake air temperature of material battery is optimum value.Booster increases entrance environmental Kuznets Curves cabin atmospheric density.By adjusting ambient control cabinet
Intake air temperature and increase send into fuel cell atmospheric density, improve the efficiency of fuel cell, improve fuel cell and exist
The service behaviour in high-altitude.Fuel cell, as general supply, is connected with each electricity consumption part of unmanned plane by electric lead and is no
The man-machine enough power providing guarantee continuation of the journey duration.The self-propulsion type Dropsonde system adopting of the present invention, airborne 37 sondes, one
A sonde is thrown, lift-off once can be adopted in real time accurately in extensive region multi-faceted Dropsonde instrument comprehensively under individual collection point
Collection atmosphere is 12~20km highly descends temperature in SEQUENCING VERTICAL section, humidity gentle pressure meteorological data.Using the present invention from
Boat formula Dropsonde system adopting economy, environmental protection, cost performance is higher.
Below in conjunction with the accompanying drawings the self-propulsion type Dropsonde system adopting of the present invention is described further.
Brief description
Fig. 1 is the structural representation of self-propulsion type Dropsonde system adopting of the present invention.
Fig. 2 is the distribution schematic diagram in unmanned aerial vehicle body belly and wing bottom for the sonde cabin.
Fig. 3 throws in front storing schematic diagram in sonde cabin for sonde.
Specific embodiment
As shown in figure 1, the present invention improves on the basis of prior art obtaining.Throw under the self-propulsion type of the present invention and visit
What empty set system included prior art is provided with screw motor 1, ground control system, airborne flight control system 2 and sonde 3
Unmanned plane 4.In the self-propulsion type Dropsonde system adopting of the present invention, the front portion in unmanned plane 4 fuselage is provided with hydrogen storage system 5, and middle part sets
There is environmental Kuznets Curves cabin 6, airborne flight control system 2 is arranged on fuselage afterbody.It is provided with a fuel cell 7, laterally in environmental Kuznets Curves cabin 6
It is provided with a cage ring 8.Environmental Kuznets Curves cabin 6 is separated into forward air supply portion and backside gas discharge unit by cage ring 8,
Fuel cell 7 is separated forward part and rear part.The right front in environmental Kuznets Curves cabin 6 connects a gas booster 9.Gas increases
Depressor 9 is connected with the collection chamber 1-1 with screw motor 1 by air inlet pipe 10.The gas of collection chamber 1-1 is to flow through motor quilt
Gas after motor heating.One point of gas baffle plate 11 is provided with air inlet pipe 10.Point gas baffle plate 11 pass through electronic guiding mechanism with
Point gas control mechanism circuit of airborne flight control system 2 connects.Gas baffle plate 11 is divided to have one at 0 °~Arbitrarily angled in the range of 90 °
Under rotary motion trace.Unmanned plane 4 right flank leading edge is provided with an inflation inlet 4-1, and inflation inlet 4-1 and air inlet pipe 10 are in a point gas baffle plate 11
Place's connection.Gas baffle plate 11 is divided to be connected with a point gas control mechanism circuit for airborne flight control system 2 by electronic guiding mechanism.Rotate and divide
Gas baffle plate, the air's ratio flowing through air inlet pipe 10 is in inverse ratio variable condition.In high-altitude, ambient air temperature is gentle to be forced down, and opens
Dynamic booster, increases the air capacity entering environmental Kuznets Curves cabin 6, and adjusts point gas baffle plate 11 change air's flow proportional, protects
Barrier operation of fuel cells performance.
Hydrogen in hydrogen storage system 5 is connected with the forward part of fuel cell 7.Unmanned plane 4 body is in gas discharging part
Left side is provided with a gas outlet 4-2, and the rear part of fuel cell 7 is passed through gas outlet 4-2 and linked up with air, for discharging fuel
The residual air that battery 7 is discharged.Fuel cell 7, as general supply, is connected and supplies with each electricity consumption part of unmanned plane 4 by electric lead
To its electricity consumption.
As shown in Figure 2 and Figure 3, in self-propulsion type Dropsonde system adopting of the present invention, the fuselage lower abdomen of unmanned plane 4 is provided with eight
Sonde cabin 12, the lower aerofoil of left and right wing is respectively provided with seven sonde cabins 12 respectively.Sonde cabin 12 is built-in is placed with one for each
Individual sonde.The hatch door in sonde cabin 12 is connected by the hatch door controlling organization circuit of electronic mechanism for opening/closing and airborne flight control system 2
Connect.Airborne flight control system, according to pre-flight setting program or guidance command, controls sounding respectively in different when and wheres
The hatch door in instrument cabin 12 is opened, sonde in release.Sonde, under Gravitative Loads, falls to leaving unmanned plane.Air is carried out
Monitoring.
Embodiment described above, the description only preferred embodiment for the present invention being carried out, the not model to the present invention
Enclose and be defined, on the premise of without departing from design spirit of the present invention, the technical side to the present invention for the those of ordinary skill in the art
Various modifications and improvement that case is made, all should fall in the protection domain of claims of the present invention determination.
Claims (6)
1. a kind of self-propulsion type Dropsonde system adopting, including being provided with screw motor (1), ground control system, airborne winged control
The unmanned plane (4) of system (2) and sonde (3) it is characterised in that: the front portion in described unmanned plane (4) fuselage is provided with hydrogen storage system
System (5), middle part is provided with environmental Kuznets Curves cabin (6), and described airborne flight control system (2) is arranged on fuselage afterbody, described environmental Kuznets Curves cabin
(6) longitudinally it is provided with a fuel cell (7) in, is transversely provided with a cage ring (8), environmental Kuznets Curves cabin (6) are divided by cage ring (8)
It is divided into forward air supply portion and backside gas discharge unit, fuel cell (7) is separated into forward part and rear part, described
At the right front in environmental Kuznets Curves cabin (6) connect a gas booster (9), gas booster (9) pass through air inlet pipe (10) with
Collection chamber with screw motor (1) (1-1) connects, and the gas of described collection chamber (1-1) is to flow through motor and heated by motor
Gas, described air inlet pipe (10) is provided with a point of gas baffle plate (11), unmanned plane (4) right flank leading edge is provided with an inflation inlet
(4-1), inflation inlet (4-1) and air inlet pipe (10) connect at point gas baffle plate (11) place, the hydrogen of described hydrogen storage system (5) and fuel
The hydrogen inlet connection of battery (7), described unmanned plane (4) body is provided with a gas outlet (4- in the left side of gas discharging part
2), the rear part of described fuel cell (7) passes through gas outlet (4-2) with air communication, and described fuel cell (7) constitutes general supply
And be connected with each electricity consumption part of unmanned plane (4) by electric lead.
2. self-propulsion type Dropsonde system adopting according to claim 1 it is characterised in that: under the fuselage of described unmanned plane (4)
Belly is provided with several sonde cabins (12), and the lower aerofoil of left and right wing is respectively provided with several sonde cabins (12) respectively, each
Sonde cabin (12) is built-in to be placed with a sonde, and the hatch door of sonde cabin (12) passes through electronic mechanism for opening/closing and airborne winged control system
The hatch door controlling organization circuit of system (2) connects.
3. self-propulsion type Dropsonde system adopting according to claim 1 and 2 it is characterised in that: described point of gas baffle plate (11) is led to
Cross electronic guiding mechanism to be connected with a point gas control mechanism circuit for airborne flight control system (2).
4. self-propulsion type Dropsonde system adopting according to claim 3 it is characterised in that: described point of gas baffle plate (11) has one
Individual at 0 °~In the range of 90 ° arbitrarily angled under rotary motion trace.
5. self-propulsion type Dropsonde system adopting according to claim 4 it is characterised in that: described point of gas baffle plate (11) rotates,
The air's ratio flowing through air inlet pipe (10) entrance environmental Kuznets Curves cabin (6) is in inverse ratio variable condition.
6. self-propulsion type Dropsonde system adopting according to claim 1 it is characterised in that: described gas booster (9) changes
Working condition, the atmospheric pressure value in described environmental Kuznets Curves cabin (6) is the variate-value servo-actuated with gas booster (9) working condition.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510365833.2A CN105000183B (en) | 2015-06-29 | 2015-06-29 | Self-propelled dropsonde system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510365833.2A CN105000183B (en) | 2015-06-29 | 2015-06-29 | Self-propelled dropsonde system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105000183A CN105000183A (en) | 2015-10-28 |
| CN105000183B true CN105000183B (en) | 2017-01-18 |
Family
ID=54373118
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510365833.2A Active CN105000183B (en) | 2015-06-29 | 2015-06-29 | Self-propelled dropsonde system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105000183B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107200119A (en) * | 2016-03-16 | 2017-09-26 | 上海重塑能源科技有限公司 | Fuel cell unmanned plane |
| CN106058283A (en) * | 2016-08-11 | 2016-10-26 | 深圳市科比特航空科技有限公司 | Heat radiation structure and method for fuel cell of unmanned aerial vehicle |
| CN110576972B (en) * | 2019-08-30 | 2024-05-07 | 中国气象局气象探测中心 | Multi-cylinder type downward projecting sonde ejection device, projecting device and projecting method |
| CN110673228B (en) * | 2019-08-30 | 2020-09-01 | 北京航空航天大学 | Formula of throwing sonde under imitative dandelion structure |
| CN111661342A (en) * | 2020-06-06 | 2020-09-15 | 河北柒壹壹玖工业自动化技术有限公司 | Energy-saving hybrid unmanned aerial vehicle |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1267006A (en) * | 1999-03-11 | 2000-09-20 | 江西省气象科学研究所 | Sounding system using miniature robot aircraft |
| BR0110056A (en) * | 2000-04-03 | 2003-12-30 | Aerovironment Inc | Liquid hydrogen-powered stratospheric aircraft, its wing, power system and method for delivering a gaseous reagent to a fuel cell at a desired operating flow rate |
| CN102183962B (en) * | 2011-03-11 | 2013-09-11 | 中国气象局气象探测中心 | Unmanned aerial vehicle (UAV) dropsonde and method for releasing and controlling same |
| DE102012002067A1 (en) * | 2012-02-03 | 2013-08-08 | Eads Deutschland Gmbh | Air-to-ground monitoring and / or control system and method for airborne inspection and / or control of offshore or offshore objects |
| CA2867479A1 (en) * | 2012-04-05 | 2013-10-10 | Avox Systems, Inc. | Oxygen/air supply for fuel cell applications |
| DE102012104783B4 (en) * | 2012-06-01 | 2019-12-24 | Quantum-Systems Gmbh | Aircraft, preferably UAV, drone and / or UAS |
-
2015
- 2015-06-29 CN CN201510365833.2A patent/CN105000183B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN105000183A (en) | 2015-10-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105000183B (en) | Self-propelled dropsonde system | |
| CN113165732A (en) | Aircraft with enhanced pitch control and interchangeable components | |
| CN102520727B (en) | Reconnaissance system with unmanned plane | |
| CN106347694B (en) | A kind of Information Acquisition System based near space floating platform | |
| CN108058802A (en) | A kind of variable density unmanned airship based on solar energy | |
| CN108688803A (en) | It is a kind of can VTOL aircraft | |
| CN108750101A (en) | A kind of super maneuver high speed compound unmanned rotary wing aircraft, assembly, assembly and disassembly methods | |
| CN204776011U (en) | Many rotor unmanned aerial vehicle that can entry | |
| CN106379552B (en) | Small drone folding and unfolding method based on captive balloon | |
| CN105857630A (en) | Parking apron device, aircraft and aircraft parking system | |
| CN109319126A (en) | It manages to the response threatened that freezes | |
| CN103268121A (en) | Application system for direct letter delivery between high-rise buildings by unmanned plane for letter express delivery | |
| CN203410624U (en) | Small-sized hand-thrown unmanned aerial vehicle | |
| CN202923888U (en) | Photovoltaic hawk-type unmanned scout for sea area governance | |
| CN103558653A (en) | Weather detection airplane based on platform with multiple rotor wings | |
| CN108284954A (en) | A kind of unmanned increasing rain aircraft | |
| CN208715485U (en) | A kind of agricultural remote sensing data acquisition equipment equipped with three smooth cameras | |
| CN206141833U (en) | Unmanned aerial vehicle system | |
| CN107554351A (en) | To the aerogenerator device people of high electric air commercial aircraft wireless power | |
| CN204916155U (en) | Multipurpose unmanned aerial vehicle | |
| CN209617517U (en) | A kind of dynamic quadrotor of double hair oil | |
| EP4045403A1 (en) | Aircraft fluid release system | |
| Siddique et al. | Development of an Experimental Unmanned-Aerial System (UAS) to Study the Effects of Adverse Weathers on its Flight Performance | |
| CN208119432U (en) | A kind of electric assembly power unmanned vehicle of distributed oil | |
| CN108750126A (en) | A kind of dynamic quadrotor of double hair oil |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |