CN1135439A - Concealed craft - Google Patents
Concealed craft Download PDFInfo
- Publication number
- CN1135439A CN1135439A CN 95104880 CN95104880A CN1135439A CN 1135439 A CN1135439 A CN 1135439A CN 95104880 CN95104880 CN 95104880 CN 95104880 A CN95104880 A CN 95104880A CN 1135439 A CN1135439 A CN 1135439A
- Authority
- CN
- China
- Prior art keywords
- aircraft
- tail gas
- concealed
- protective layer
- electromagnetic wave
- 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
Images
Landscapes
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invisible flight vehicle is characterized by that it makes the outer shell of said vehicle carry positive charge to produce a constant electric field to make radar wave deviate and cann't be reflected back, and at the same time said outer shell is coated with semiconductor layer to absorb electromagnetic wave, and its tail gas exhaust is equipped with a tail gas cover to tower its temp. and block off diffusion of tail gas infrared rays so as to avoid the tracing of radar and infrared detector and attain the goal of stealth flying.
Description
The present invention relates to a kind of flying instrument of weapons, particularly stealth aircraft, stealthy guided missile.
At present, China existing aircraft all can not be accomplished stealth as aircraft, guided missile, promptly can be with aircraft or guided missile location once the electromagnetic wave of the radar emission of taking off, because jet engine tail gas is high-temperature gas, infrared detector can also detect the flight path of aircraft again.It is reported that there is stealth aircraft in the U.S., but do not obtain the data of its principle of play-by-play.
Purpose of the present invention is exactly to solve above-mentioned deficiency, applies steady electric field and provide a kind of at the aircraft outside face, and coating quartz conductor protective layer absorbs electromagnetic wave, and the tailing gas hood reduces exhaust temperature, reaches stealthy.
The solution that realizes the object of the invention is that direct supply 1 is set on aircraft, and is connected on the shell 9 by lead 3, makes aircraft skin 9 positively chargeds; Simultaneously, at shell 9 outside faces coating quartz conductor protective layer, absorb electromagnetic wave; Tail gas cover 6 is set for the aircraft fumarole outward.
The direct supply 1 that is provided with on aircraft is dynamo generator, amplidyne, direct current voltage multiplier.The shape of tail gas cover 6 be one dolioform, tiny in the middle of promptly, two is horn-like amplification.Between tail gas cover 6 and the aircraft fumarole certain interval is arranged, so that enter cold air, cooled exhaust gas.
Advantage of the present invention is to make the enemy radar ripple produce deflection, absorption, reduces the angle of visibility of infrared detector, reaches the purpose of stealthy flight.
The present invention is described in further detail below in conjunction with accompanying drawing:
Fig. 1 is an aircraft skin positively charged scheme drawing;
Fig. 2 is the electromagnetic wave superposition scheme drawing of Fig. 1;
Fig. 3 is a not tailing gas hood scheme drawing of aircraft;
Fig. 4 is an aircraft tailing gas hood scheme drawing.
There is the non-uniform electric field place at indivedual positions, aircraft skin 9 surfaces, still have reflection,a few to produce, and aircraft surface is applied protective layer, and protective layer is made quartz conductor, can absorb electromagnetic wave.Its principle is: when electromagnetic wave was run into metal on working direction, the degree of depth that penetrates metal inside was penetrance, and the metallo-electric conductivity is good more, and penetrance is more little, otherwise penetrated deeply more, and electromagnetic wave can pass insulator; The quartz conductor forward resistance is little, be conductor, back resistance is big, is insulator, the aircraft surface protective layer is made semiconductor layer, when electromagnetic wave directive aircraft,, can penetrate protective layer for oppositely entering, when running into metal case 9 reflex times, protective layer is that forward passes through, and protective layer is electric conductivity and stops electromagnetic wave to penetrate, and protective layer shows as the absorption electromagnetic wave.
Protective layer is made black, absorbs infrared light, prevents infrared acquisition.
Once taking off, infrared detecting set just may detect the angle of visibility 10 that aircraft jet engine discharging high-temperature tail gas 5, infrared detecting set can detect aircraft exhausr port mid point 8 greater than 180 ° of aircraft.After aircraft afterbody air nozzle added tail gas cover 6, the angle of visibility 10 of the angle of visibility 11 that exhaust port mid point 8 is detected by infrared detecting set during than anury gas hood 6 was much smaller.Reduced tested probability, the infrared acquisition of ground station and satellite all can not detect aircraft.
The length 7 that changes tail gas cover 6 can be controlled the size of angle of visibility 11, tail gas cover 6 is done an exit skirt, with the aircraft air nozzle gap is being arranged vertically, the air-flow 2 of aircraft skin 9 is from the exit skirt gap location, pressure enters in the tail gas cover 6, make the drop in temperature of exhaust port mid point 8, reduce ultrared distributing.
Claims (5)
1, a kind of concealed aircraft is characterized in that: a, direct supply 1 is set on aircraft, and is connected on the shell 9 by lead 3, make aircraft skin 9 positively chargeds; B, shell 9 outside faces coating quartz conductor protective layer; C, tail gas cover 6 is set.
2, according to the said concealed aircraft of claim 1, it is characterized in that said power supply 1, be dynamo generator, amplidyne, direct current voltage multiplier.
3, according to the said concealed aircraft of claim 1, the shape that it is characterized in that said tail gas cover 6 is that a dolioform i.e. centre is tiny, and two is horn-like amplification.
4, according to claim 1,3 said concealed aircrafts, it is characterized in that between tail gas cover 6 and the aircraft fumarole gapped.
5, according to the said concealed aircraft of claim 1, the color that it is characterized in that said quartz conductor protective layer is a black.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN 95104880 CN1135439A (en) | 1995-05-05 | 1995-05-05 | Concealed craft |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN 95104880 CN1135439A (en) | 1995-05-05 | 1995-05-05 | Concealed craft |
Publications (1)
Publication Number | Publication Date |
---|---|
CN1135439A true CN1135439A (en) | 1996-11-13 |
Family
ID=5075278
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN 95104880 Pending CN1135439A (en) | 1995-05-05 | 1995-05-05 | Concealed craft |
Country Status (1)
Country | Link |
---|---|
CN (1) | CN1135439A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1426726A1 (en) | 2002-12-05 | 2004-06-09 | Buck Neue Technologien GmbH | Radar-camouflaged launcher |
CN102328746A (en) * | 2011-07-05 | 2012-01-25 | 罗晓晖 | Bag-release delay-control-type invisible bombing system of aircraft |
CN104986002A (en) * | 2015-06-04 | 2015-10-21 | 重庆大学 | Micro triphibian quadrocopter |
-
1995
- 1995-05-05 CN CN 95104880 patent/CN1135439A/en active Pending
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1426726A1 (en) | 2002-12-05 | 2004-06-09 | Buck Neue Technologien GmbH | Radar-camouflaged launcher |
CN102328746A (en) * | 2011-07-05 | 2012-01-25 | 罗晓晖 | Bag-release delay-control-type invisible bombing system of aircraft |
CN102328746B (en) * | 2011-07-05 | 2015-04-15 | 罗晓晖 | Bag-release delay-control-type invisible bombing system of aircraft |
CN104986002A (en) * | 2015-06-04 | 2015-10-21 | 重庆大学 | Micro triphibian quadrocopter |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CN107472509B (en) | A kind of stealthy unmanned plane of Flying-wing | |
Yue et al. | Numerical simulation of RCS for carrier electronic warfare airplanes | |
US5490644A (en) | Ducted boundary layer diverter | |
CN106894917B (en) | A kind of double outlet S bending nozzles and its control method of low-infrared radiation signal | |
CN214701950U (en) | Air-ground type target bomb | |
US6134879A (en) | Suppression system for a gas turbine engine | |
CN1135439A (en) | Concealed craft | |
US3713157A (en) | Energy absorption by a radioisotope produced plasma | |
US7032830B2 (en) | Method and device for generating a liquid mist | |
EP0227122B1 (en) | Lightning protection apparatus for an exterior surface | |
Ab-Rahman et al. | Lock-on range of infrared heat seeker missile | |
US3480231A (en) | Lightning protection for aircraft components | |
US3482802A (en) | Lightning protection for aircraft components | |
US20160363322A1 (en) | IR-radar image generator to provide a decoy and associated method of operation | |
CN111017267B (en) | High-thrust near space thruster based on corona discharge and Hall effect | |
Polezhaev | Will there or will there not be a hypersonic airplane? | |
CN112286059A (en) | Second-order front angle remodeling guidance method with attack angle and field angle constraints | |
CN112027050A (en) | Novel invisible fighter | |
Whitford | Designing for stealth in fighter aircraft (stealth from the aircraft designer's viewpoint) | |
Hitzel | Aerodynamics and radar signature-A combination of theoretical methods | |
CN220103894U (en) | Camouflage fabric and device for thermal infrared detection prevention | |
Chen et al. | Research and analysis on jamming effectiveness of towed decoy | |
FOC | Indigenous Punch | |
Yang et al. | Design and Implementation of Trajectory Planning Algorithm for UAV Borne Air-to-Surface Missile | |
RU2120396C1 (en) | Propulsor |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
C06 | Publication | ||
PB01 | Publication | ||
C01 | Deemed withdrawal of patent application (patent law 1993) | ||
WD01 | Invention patent application deemed withdrawn after publication |