CN108928481A - A kind of unmanned plane stealthy system automatically - Google Patents
A kind of unmanned plane stealthy system automatically Download PDFInfo
- Publication number
- CN108928481A CN108928481A CN201810726957.2A CN201810726957A CN108928481A CN 108928481 A CN108928481 A CN 108928481A CN 201810726957 A CN201810726957 A CN 201810726957A CN 108928481 A CN108928481 A CN 108928481A
- Authority
- CN
- China
- Prior art keywords
- unmanned plane
- intake duct
- air intake
- stealthy
- system automatically
- 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.)
- Pending
Links
- 238000000576 coating method Methods 0.000 claims abstract description 24
- 239000011248 coating agent Substances 0.000 claims abstract description 19
- 238000005183 dynamical system Methods 0.000 claims abstract description 8
- 238000010521 absorption reaction Methods 0.000 claims abstract description 7
- 239000004020 conductor Substances 0.000 claims abstract description 5
- 239000000835 fiber Substances 0.000 claims abstract description 5
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 3
- 239000006260 foam Substances 0.000 claims description 3
- 238000006471 dimerization reaction Methods 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 6
- 229920000642 polymer Polymers 0.000 abstract description 4
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 238000005457 optimization Methods 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 description 11
- 238000001514 detection method Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000017525 heat dissipation Effects 0.000 description 2
- 230000004083 survival effect Effects 0.000 description 2
- 238000005253 cladding Methods 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000005622 photoelectricity Effects 0.000 description 1
- 238000004886 process control Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
- B64D2033/0273—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for jet engines
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Wind Motors (AREA)
Abstract
The invention discloses a kind of unmanned plane stealthy systems automatically, the sound absorption coating for reducing propeller noise are coated in windmill wings system, to reduce the noise of unmanned plane propeller；The radar gauze screen being made of an electrically conducting material is arranged in the air inlet of dynamical system, and drone body outer surface is coated with the microwave absorbing coating by X fiber as antiradar coatings, and the two collective effect realizes the stealthy of unmanned plane；Heat dissipating layer is set on air intake duct and jet pipe；Heat dissipating layer and air intake duct and jet pipe form cavity, the high polymeric compound big filled with cold capacity in cavity, absorb the heat distributed when turbine jet engine work with this；Unmanned plane of the invention stealthy system automatically, structure is simple, and manufacturing cost is low, in the case where not changing the structure of original unmanned plane, the stealthy and performance optimization for realizing unmanned plane, for the large quantities of unmanned planes used that dispatched from the factory at present, has great dissemination.
Description
Technical field
The invention belongs to unmanned plane stealth technology fields, and in particular to a kind of unmanned plane stealthy system automatically.
Background technique
Unmanned plane is the abbreviation of UAV, be it is a kind of with wireless remotecontrol or by based on itself process control not
Manned aircraft.Compared with manned aircraft, unmanned plane has small in size, low cost, easy to use, low to operational environment requirement, war
The advantages that field survival ability is stronger, by the favor of all armies in the world.Succeeding in developing for unmanned plane is used with battlefield, is opened
With remote attack smart weapon, the new page that intelligent weapon is leading untouchable war.
In modern local war, with the rapid development of military photoelectric technology, aerial military target is faced with increasingly tight
The photoelectricity of weight threatens.And modern military technology had reached " as long as target is found, can be hit, as long as being hit,
Can be destroyed " level.According to statistics, it is to be observed that aircraft loss, which has 80%~90% the reason of, in air battle.Therefore, with regard to nobody
This field of reconnaissance plane, stealth technology are an important factor for influencing its battlefield survival.The low-altitude reconnaissance that the present invention is directed to without
It is man-machine, it refers mainly to flying height in the range of away from ground level at 600 meters to 1000 meters, executes low latitude reconnaissance mission over the ground
Unmanned plane.
Modern unmanned plane stealth technology mostly uses greatly radar and infrared technique, and anti-stealth technology in these areas is also opposite
Comparative maturity.In the targeted low-altitude reconnaissance airspace of the present invention, the radar exploration technique almost fails.Target strike to this airspace
Mainly by relying on the detection system and infrared detection system of vision, and the scounting aeroplane being driven by electricity can also teach and be easy to escape
The tracking of infrared detection system.Vision stealth technology existing at present mostly uses coating camouflage either using the illiteracy of changeable colour
Skin.But that there are color changes is slow, variable range is small, is difficult to adapt to the problems such as a variety of weather conditions for these stealth technologies, seriously
Constrain use of these technologies in low-altitude reconnaissance unmanned plane.
In addition, the noise of unmanned plane propeller can make the normal life of nearby residents in the application of civilian unmanned plane
At noise pollution, this is also problem to be solved.
Summary of the invention
The present invention is directed to solve at least some of the technical problems in related technologies.For this purpose, of the invention
Main purpose is to provide a kind of unmanned plane stealthy system automatically, it is intended to solve traditional stealth technology there are color changes it is slow,
Variable range is small, the problem of being difficult to adapt to a variety of weather conditions and the noise pollution of civilian unmanned plane propeller.
The purpose of the present invention is what is be achieved through the following technical solutions:
A kind of unmanned plane stealthy system automatically, including what is be made of windmill wings system, dynamical system and flight control system
Drone body；The sound absorption coating for reducing propeller noise is coated in the windmill wings system；The power
System includes from head to the sequentially connected air intake duct of tail, turbine jet engine and jet pipe；The dynamical system
Air inlet is provided with the radar gauze screen being made of an electrically conducting material；Heat dissipation is provided on the air intake duct and the jet pipe
Layer；The heat dissipating layer and the air intake duct and jet pipe form cavity, and the big high polymeric compound of cold capacity is filled in cavity；Institute
It states drone body outer surface and is also coated with microwave absorbing coating by X fiber as antiradar coatings.
Further, in order to improve stealth effect, in machine back, cross section is side for the air inlet setting of the air intake duct
Shape；The radar shielding net surface and drone body surface keep continual curvature, and logical with drone body surface conductance.
Further, in order to improve the aerodynamic arrangement of unmanned plane, the outlet of the entrance section product/air intake duct of the air intake duct is cut
Area >=1.5, the air intake duct are gradually transitioned into circle by rectangular from air inlet to air intake duct end；The air intake duct end is straight
Diameter/turbine jet engine diameter >=1.05 and be not more than 1.15, inner nozzle internal orifice diameter/turbine jet engine spout
Diameter >=1.2 and be not more than 1.7.
Further, in order to further increase the stealth effect of unmanned plane, the coated area of the microwave absorbing coating is not less than nothing
The 95% of the man-machine body outer surface gross area；The thickness of the microwave absorbing coating is not less than 8mm.
Further, in order to improve noise reduction effect, the sound absorption coating is by the open-celled foam for absorbing medium-high frequency sound wave
Plastic layer and hardboard for absorbing low-frequency sound wave are combined.
Compared with prior art, the present invention has at least the following advantages:
Unmanned plane of the invention stealthy system automatically, cladding is in windmill wings system for reducing propeller noise
Sound absorption coating, to reduce the noise of unmanned plane propeller；The radar being made of an electrically conducting material is arranged in the air inlet of dynamical system
Gauze screen, drone body outer surface are coated with the microwave absorbing coating by X fiber as antiradar coatings, and the two collective effect realizes nothing
Man-machine is stealthy；Heat dissipating layer is set on air intake duct and jet pipe；Heat dissipating layer and air intake duct and jet pipe form cavity, in cavity
Filled with the big high polymeric compound of cold capacity, the heat distributed when turbine jet engine work is absorbed with this；The present invention
Unmanned plane stealthy system automatically, structure is simple, and manufacturing cost is low, in the case where not changing the structure of original unmanned plane,
The stealthy and performance optimization for realizing unmanned plane is to have greatly for the large quantities of unmanned planes used that dispatched from the factory at present
Dissemination.
Specific embodiment
Based on the embodiments of the present invention, those of ordinary skill in the art are obtained without creative efforts
The every other embodiment obtained, shall fall within the protection scope of the present invention.
In the present invention unless specifically defined or limited otherwise, term " connection ", " fixation " etc. shall be understood in a broad sense,
For example, " fixation " may be a fixed connection, it may be a detachable connection, or integral；It can be mechanical connection, be also possible to
Electrical connection；It can be directly connected, the connection inside two elements or two can also be can be indirectly connected through an intermediary
The interaction relationship of a element, unless otherwise restricted clearly.It for the ordinary skill in the art, can basis
Concrete condition understands the concrete meaning of above-mentioned term in the present invention.
It in addition, the technical solution between each embodiment of the present invention can be combined with each other, but must be general with this field
Based on logical technical staff can be realized, it will be understood that when the combination of technical solution appearance is conflicting or cannot achieve this
The combination of technical solution is not present, also not the present invention claims protection scope within.
A kind of unmanned plane stealthy system automatically, including what is be made of windmill wings system, dynamical system and flight control system
Drone body；It is coated in the windmill wings system for reducing propeller noise by for absorbing medium-high frequency sound
The sound absorption coating that the open cell foam layer of wave and the hardboard for absorbing low-frequency sound wave are combined；The power
System includes from head to the sequentially connected air intake duct of tail, turbine jet engine and jet pipe；The dynamical system
Air inlet is provided with the radar gauze screen being made of an electrically conducting material；Heat dissipation is provided on the air intake duct and the jet pipe
Layer；The heat dissipating layer and the air intake duct and jet pipe form cavity, and the big high polymeric compound of cold capacity is filled in cavity；Institute
It states drone body outer surface and is also coated with microwave absorbing coating by X fiber as antiradar coatings；The coated area of the microwave absorbing coating
Not less than the 95% of drone body total outer surface area；The thickness of the microwave absorbing coating is not less than 8mm.
Preferably, in order to improve stealth effect, in machine back, cross section is side for the air inlet setting of the air intake duct
Shape；The radar shielding net surface and drone body surface keep continual curvature, and logical with drone body surface conductance.
Preferably, in order to improve the aerodynamic arrangement of unmanned plane, the outlet of the entrance section product/air intake duct of the air intake duct is cut
Area >=1.5, the air intake duct are gradually transitioned into circle by rectangular from air inlet to air intake duct end；The air intake duct end is straight
Diameter/turbine jet engine diameter >=1.05 and be not more than 1.15, inner nozzle internal orifice diameter/turbine jet engine spout
Diameter >=1.2 and be not more than 1.7.
More than, it is merely preferred embodiments of the present invention, but the protection scope invented is not limited thereto, it is any ripe
Know those skilled in the art in the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of, should all contain
Lid is within protection scope of the present invention.Therefore, the scope of protection of the invention shall be subject to the scope of protection specified in the patent claim.
Claims (5)
1. a kind of unmanned plane stealthy system automatically, including the nothing being made of windmill wings system, dynamical system and flight control system
Man-machine ontology, which is characterized in that the sound absorption coating for reducing propeller noise is coated in the windmill wings system；
The dynamical system includes from head to the sequentially connected air intake duct of tail, turbine jet engine and jet pipe；It is described dynamic
The air inlet of Force system is provided with the radar gauze screen being made of an electrically conducting material；It is respectively provided on the air intake duct and the jet pipe
There is heat dissipating layer；The heat dissipating layer and the air intake duct and jet pipe form cavity, and the big high dimerization of cold capacity is filled in cavity
Close object；The drone body outer surface is also coated with the microwave absorbing coating by X fiber as antiradar coatings.
2. unmanned plane according to claim 1 stealthy system automatically, which is characterized in that the air inlet of the air intake duct is arranged
In machine back, cross section is rectangular；Radar shielding net surface and drone body surface keep continual curvature, and with nothing
Man-machine body surface conducts.
3. unmanned plane according to claim 1 or 2 stealthy system automatically, which is characterized in that the entrance of the air intake duct is cut
Area/air intake duct discharge area >=1.5, the air intake duct are gradually transitioned into circle by rectangular from air inlet to air intake duct end
Shape；Air intake duct end diameter/turbine jet engine diameter >=1.05 and be not more than 1.15.
4. unmanned plane according to claim 1 stealthy system automatically, which is characterized in that the coated area of the microwave absorbing coating
Not less than the 95% of drone body total outer surface area；The thickness of the microwave absorbing coating is not less than 8mm.
5. unmanned plane according to claim 1 stealthy system automatically, which is characterized in that the sound absorption coating is by for absorbing
The open cell foam layer of medium-high frequency sound wave and the hardboard for absorbing low-frequency sound wave are combined.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810726957.2A CN108928481A (en) | 2018-07-05 | 2018-07-05 | A kind of unmanned plane stealthy system automatically |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810726957.2A CN108928481A (en) | 2018-07-05 | 2018-07-05 | A kind of unmanned plane stealthy system automatically |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108928481A true CN108928481A (en) | 2018-12-04 |
Family
ID=64446746
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810726957.2A Pending CN108928481A (en) | 2018-07-05 | 2018-07-05 | A kind of unmanned plane stealthy system automatically |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108928481A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111005807A (en) * | 2019-11-22 | 2020-04-14 | 北京机电工程研究所 | Cavity structure applying wave-absorbing material |
| CN115384774A (en) * | 2022-08-24 | 2022-11-25 | 湖南省蓝鹰科技有限公司 | Investigation unmanned aerial vehicle is used in actual combat countermeasure |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070028589A1 (en) * | 2005-08-03 | 2007-02-08 | Hamilton Sundstrand Corporation | Thermal management system for a gas turbine engine |
| US20080053101A1 (en) * | 2006-09-01 | 2008-03-06 | United Technologies Corporation | Aircraft thermal management system with reduced exhaust re-ingestion |
| CN104110326A (en) * | 2014-07-02 | 2014-10-22 | 北京航空航天大学 | New concept high-speed aerocraft propulsion system layout method |
| CN104557095A (en) * | 2014-11-28 | 2015-04-29 | 中国建筑材料科学研究总院 | Glass fiber based composite absorbing material and preparation method thereof |
| CN106833215A (en) * | 2017-03-16 | 2017-06-13 | 上海琛岫自控科技有限公司 | A kind of unmanned plane that can reduce electromagnetic interference |
| CN107380457A (en) * | 2017-07-31 | 2017-11-24 | 西安天拓航空科技有限公司 | A kind of stealthy unmanned plane dynamical system of Flying-wing |
| CN107472509A (en) * | 2017-07-31 | 2017-12-15 | 西安天拓航空科技有限公司 | A kind of stealthy unmanned plane of Flying-wing |
| CN107554802A (en) * | 2017-08-23 | 2018-01-09 | 北京航空航天大学 | A kind of air intake duct suitable for Flying-wing's miniature jet formula unmanned plane |
| CN107614379A (en) * | 2015-05-25 | 2018-01-19 | 多特瑞尔技术有限公司 | Shield for aircraft |
| CN108910059A (en) * | 2018-07-18 | 2018-11-30 | 中国人民解放军国防科技大学 | Precooling type air inlet and hypersonic aircraft |
-
2018
- 2018-07-05 CN CN201810726957.2A patent/CN108928481A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070028589A1 (en) * | 2005-08-03 | 2007-02-08 | Hamilton Sundstrand Corporation | Thermal management system for a gas turbine engine |
| US20080053101A1 (en) * | 2006-09-01 | 2008-03-06 | United Technologies Corporation | Aircraft thermal management system with reduced exhaust re-ingestion |
| CN104110326A (en) * | 2014-07-02 | 2014-10-22 | 北京航空航天大学 | New concept high-speed aerocraft propulsion system layout method |
| CN104557095A (en) * | 2014-11-28 | 2015-04-29 | 中国建筑材料科学研究总院 | Glass fiber based composite absorbing material and preparation method thereof |
| CN107614379A (en) * | 2015-05-25 | 2018-01-19 | 多特瑞尔技术有限公司 | Shield for aircraft |
| CN106833215A (en) * | 2017-03-16 | 2017-06-13 | 上海琛岫自控科技有限公司 | A kind of unmanned plane that can reduce electromagnetic interference |
| CN107380457A (en) * | 2017-07-31 | 2017-11-24 | 西安天拓航空科技有限公司 | A kind of stealthy unmanned plane dynamical system of Flying-wing |
| CN107472509A (en) * | 2017-07-31 | 2017-12-15 | 西安天拓航空科技有限公司 | A kind of stealthy unmanned plane of Flying-wing |
| CN107554802A (en) * | 2017-08-23 | 2018-01-09 | 北京航空航天大学 | A kind of air intake duct suitable for Flying-wing's miniature jet formula unmanned plane |
| CN108910059A (en) * | 2018-07-18 | 2018-11-30 | 中国人民解放军国防科技大学 | Precooling type air inlet and hypersonic aircraft |
Non-Patent Citations (1)
| Title |
|---|
| 史丽萍、郝晓东: "可重复使用航天器的热防护系统概述", 《航空制造技术》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111005807A (en) * | 2019-11-22 | 2020-04-14 | 北京机电工程研究所 | Cavity structure applying wave-absorbing material |
| CN115384774A (en) * | 2022-08-24 | 2022-11-25 | 湖南省蓝鹰科技有限公司 | Investigation unmanned aerial vehicle is used in actual combat countermeasure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107472509B (en) | A kind of stealthy unmanned plane of Flying-wing | |
| CN102868021B (en) | A kind of High-performance frequency selection radar cover | |
| RU2599198C2 (en) | Camouflaged aircraft | |
| US20140070056A1 (en) | Aricraft with improved aerodynamic performance | |
| CN102026531A (en) | Super-matching wave-absorbing material formed by utilizing sheeted cross-shaped metal unit structure | |
| WO2020107846A1 (en) | Stealth large maneuvering target aircraft and control method for stealth large maneuvering target aircraft | |
| CN112734278B (en) | Time-sensitive target hit-oriented C2 organization resource dynamic scheduling method | |
| CN108928481A (en) | A kind of unmanned plane stealthy system automatically | |
| CN106341206A (en) | Low-altitude unmanned aerial vehicle defense system | |
| CN207602785U (en) | One kind has high wave-penetrating composite material antenna radar cover | |
| RU2502643C2 (en) | Multifunctional aircraft of decreased radar signature | |
| CN111176321A (en) | Heterogeneous swarm unmanned aerial vehicle cooperative attack system and method | |
| CN104008260A (en) | Designing method of conformal fairing optimum face type and parameters | |
| CN108808239A (en) | A kind of high-performance blister towards high-speed cruising carrier satellite communication system | |
| CN104901018A (en) | Panel with anti-radar detection function | |
| CN202429355U (en) | Engine cooling channel | |
| CN202258383U (en) | Polyurethane foam pyramid wave-absorbing material | |
| CN112407237A (en) | Medium-sized unmanned aerial vehicle with high lift-drag ratio | |
| CN117913495A (en) | Double-air-duct heat dissipation method and system for airborne satellite antenna | |
| CN215944888U (en) | Unmanned aerial vehicle synthesizes electronic war system | |
| CN112027050A (en) | Novel invisible fighter | |
| CN207242070U (en) | Subsonic speed target drone | |
| CN205589525U (en) | Be used for wireless broadcast unmanned aerial vehicle | |
| CN206611700U (en) | A kind of radiating proof mechanism of water for electricity tune in plant protection unmanned plane closed shell | |
| CN201419795Y (en) | Unmanned aerial photography aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181204 |
|
| RJ01 | Rejection of invention patent application after publication |