RF-IR Stealth (Techniques/Benefits)

Brief :

The advantage of detecting, identifying and engaging a target while stay invisible is undeniable,  thus for years designers has been attempting to minimize the ability of radar, RWR and Infrared system to detect aircraft. Aircraft with significant low observability characteristics embodied in are called stealth aircraft. This article will discuss some common techniques used by stealth aircraft, their benefits and clear out some common misconceptions.

Low Observability in Electronic Spectrum.

Radar is the main sensor systems for most aircraft and air defense systems so it is not a surprise that most of the detection reduction efforts are concentrated in electronic spectrum.

Recalling the basic radar range equation discussed before:

radar-fundamentals-18-638

It easy to see that the radar detection range is proportional to σ∧¼ where σ is the radar cross-section (the RCS ,the measure of a target’s ability to reflect radar signals in the direction of the radar receiver, often measured in dBsm or m2). Reducing the cross-sectional area, therefore, affects radar range, although only according to the fourth root. However, by carefully designing an aircraft, the value of σ may be reduced by many hundreds of times thus present an effective approach.

Contributors to high RCS: 

RCS contributors

Basic RCS reduction approaches:
1) Shaping

  • Orientation and curvature of surfaces
  • Alignment of edges
  • Shielding of cavities and ducts

2)  Materials selection

  • Composites and RAM
  • Metamaterials and other artificial materials

RCS reduction techniques:

Surface orientation:

Surface orientation

  • Make sure surface normals do not point in high priority threat directions
  • Specular component is frequency independent, but scattering lobe widths decrease with increasing frequency
  •  Principal planes (i.e., cuts with the highest sidelobes) are perpendicular to edges
    Example above: square versus diamond with the same surface area

Retro-directive Reflectors:

conner  reflector

  • Avoid corner reflectors (dihedral and trihedral reflectors)
    No vertical/horizontal tail surfaces on aircraft
  • Surface orientation is the most important feature of a stealth aircraft, even without radar absorbing material, a stealth airframe can achieve much lower RCS compare to conventional aircraft
  • Example  picture: Computer simulation radar scattering characteristics of Mig-21 ( on the top )and F-35 ( on the bottom ),  frontal radar cross section of F-35 fluctuated between -20 and -30 dBsm while Mig-21’s radar cross section fluctuated between 10 and 0 dBsm (both models are without radar absorbing material )

new_bitmap_image

f_35_metal_rcs

Edge Serration and Alignment:

edge diffraction

The maximum intensity of the diffracted lobe from an edge (in the Keller cone direction) increases with edge length.

Edge serration

  • Serrations break up edges to reduce lobe intensities ,serrations are applied to both edges. Example using a rectangular plate is shown.

Edge agliment

  •  Edges are generally aligned so that their lobes occur in low priority region, leading edge scattering is dominated by TE polarization. Trailing edge by TM polarization. Example shown: 5λ plate with wave incident perpendicular to edge, 70 degrees from normal incidence (green arrow is E; red arrow is ki)

Current Discontinuities:

Gaps in conductivity lead to edge diffraction. A seam can look continuous, but there may not be good conduction between the two sides. Ex: wire with a break.

Surface Discontinuities

Passive Cancellation:

  • Approach: add a secondary scatterer and adjust it so its scattered field cancels that of the bare target
  • Only effective over a narrow range of angles and frequency bandwidth
  • Only practical for canceling low RCS levels
  • Examples: parasitic elements and lumped loads

Passive Cancellation

  • Passive cancellation structure ( or  RAS )

Passive Cancellation Structure

Intake RCS reduction:

  • Intake cavity and engine fan blades are a great source of radarreflection.. Stealth aircraft  intake are often  more sophisticated, being a serpentine duct rather than a direct, more conventional intake, they use complex techniques to reduce reflection over a range of frequencies. The intake is designed to counter radar threats at three wavelengths loosely termed long ( 30 cm), medium ( 10–20 cm) and short ( 3 cm),equating to 1 GHz (long-range surveillance radar), 1.5–3 GHz (AWACS radar) and 10 GHz(fighter radar) respectively.
  • At long wavelengths (30 cm ) the stealth fighter inlet ducts behave as follow:

F-35 inlet again L band

  • At medium wavelengths (10-20 cm ) the stealth fighter inlet ducts behave as follow:

F-35 inlet again medium wavelength

  • At medium-short wavelength, stealth fighter inlet ducts behave as follow:

F-35 inlet again X band

Randome RCS reduction: 

  • Antenna mode reflections. The antenna mode reflections mimic the antenna main beam and sidelobes.

Radar RCS reduction

  • Random scattering. This is caused if the antenna characteristics are not uniform across the antenna.

Radar RCS reduction 2

  • Radar antenna edge diffraction. Mismatches of impedances at the perimeter of the antenna can cause reflections called edge diffraction. In effect the outer perimeter of the antenna acts as a loop and reflections tend to be abeam of the antenna rather than fore and aft.

Radar RCS reduction 3

Canopy RCS reduction :

  • Radar wave can go through canopy and reflected off object inside the cockpit , thus increase RCS significantly. Solution : coat the inner of canopy with a thin layer of gold to prevent radar wave from entering the cockpit , the outter cockpit is coated with transparent radar absorbing material.
  • Example :

Canapy RCS reduction

Weapons RCS reduction :

Missiles , bombs are all great contributors to radar reflection due to the perpendicular angle of their wings, fins , Pylons is another great contributors because of the corner they make with aircraft wing. As a result,  stealth aircraft often carry weapons internally, the added benefits is the reduction in drag .However due to limitation in size when using internal configuration , a stealth fighter cannot carry as much weapons as a normal fighter.

Example: F-35 weapons bay

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20140110_FTU13_10_weaps_14_J00011_1267828237_2218

Skin RCS reduction :

No matter what shape they have, airframe will always reflect radar waves.The only different that shaping will make is the directions that the airframe will reflect radar.While this may be enough in most situation.The adversary may consist of very complex radar network that can illuminate stealth platform from different angles, so along with unique shaping to redirect radar wave from the original source, stealth aircraft often have radar absorbing paint or use radar absorbing material (RAM ).One might be very tempted to construct stealth aircraft skin from such “radio transparent” materials, but radar would then reflect off objects beneath the surface such as sensors, fuel, metallic airframe and engine parts and the pilot.The result may be a RCS value even higher than if the skin was radar reflective. As a result, in practice, the bottom layer of a stealth skin is a highly conductive material, such as metal, which strongly reflects radar waves before they reach the complex reflecting environment below.

The ability of a substance to absorb electromagnetic (EM) waves depends on two material properties called permittivity and permeability, which are the capacity to store electrical or magnetic energy, respectively. The source of both is the existence of electric or magnetic dipoles at the atomic, molecular or crystal lattice level. When an EM wave passes through the material, these dipoles orient opposite to the field’s direction. In some materials, the dipoles effortlessly return to neutral after the EM field returns to zero. In other materials, the dipoles are “sticky” and require energy to orient them or return them to neutral. That additional energy is lost and the material’s permittivity or permeability is said to have a loss component.

In general, RAMs are composites made up of a matrix material and a filler. The matrix is a low-loss dielectric material with appreciable permittivity and negligible permeability. They are effectively “transparent” to EM waves and are usually chosen for their physical properties. Typically, they are insulating polymers like plastic, glass, resin, polyurethane and rubber. Ceramics have higher permeabilities and heat tolerance. Foams and honeycombs have especially low permittivity—electrical energy storage—because they contain a lot of air.The RAM filler, on the other hand, is typically particles composed of or coated with a lossy material. Carbon is the material of choice for dielectric absorption because electrical lossiness is proportional to conductivity and carbon’s conductivity is below metals but above insulators. Magnetic absorbers, which have some permittivity but far greater permeability—magnetic energy storage—are typically carbonyl iron (a pure powdered form of the metal) or iron oxides, also called ferrites. These materials can be impregnated into rubber or dissolved into a paint and ferrites are often sintered into tiles.

As its permittivity, permeability, and loss components increase, a material can absorb more EM energy because EM wavelengths shrink as these values rise. But when waves reach a boundary between two mediums, energy can be reflected rather than admitted. The amount reflected depends on their impedances—the square root of the ratio between each material’s permeability and permittivity. The greater the impedance change, the more energy is reflected before it can be absorbed. So RAM design must balance absorptivity with surface reflectivity to maximize absorption.

A material’s EM properties also varied significantly with frequency. At higher radar bands, no magnetic materials have permittivity and permeability in a ratio close to that of air, so high surface reflection is inevitable. However, if the material is a quarter-wavelength deep, reflection from the metal backing partially cancels the surface reflection.Radar absorbing materials operate via phase cancellation like this is often called magnetic absorber. Because of the high permeability of magnetic RAM, the depth required is small. Absorption performance of 20 dB (99%) is achieved by commercially available “resonant absorbers” with resonant frequencies of 1-18 GHz and thicknesses of 0.04-0.2 in. The main disadvantages of such absorber is very narrow absorbing bandwidth, however, with significant absorption extending perhaps 15% from the resonance frequency.

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RAM2

Given that magnetic absorbing material has limited bandwidth, as well as high weight and cost, dielectric absorbers are often preferred for wideband absorption at high frequencies. Since dielectrics have no magnetic properties, their impedances never match air, but by using layers of materials—each with an increasing concentration of carbon particles—permittivity, conductivity and dielectric losses all gradually increase while impedance gradually decreases. Layers can also be adjusted to maximize cancellations. These graded dielectric absorbers can reduce reflection by 20 dB, and their bandwidth easily covers higher frequencies. High levels of reflection loss, in many cases better than 20dB, can be achieved in materials which are <1/3 wavelength thick. One of the most common type of graded dielectric absorber is the reticulated foam absorbing material.

ram-dielectric

Another approach is to use a physical gradient. These “geometric transition” absorbers use pointed objects of homogeneous material oriented perpendicular to waves. At high frequencies, waves bounce among these structures, losing energy with each strike. If the wavelength is large relative to the structure, the waves act as though encountering a gradual change in material properties rather than a geometric shape. Absorbers of this type can reduce reflection by up to 60 dB, but require structures very big structures and high weight so their only application is the pyramidal absorbers that line anechoic chambers used for RCS testing.

pyramid-ram

It is a common misconception that radar absorbing material is only effective around X band (8-12 Ghz) or that RAM work at low frequencies will always need to be thick or heavy. In fact, some magnetic materials actually become more effective at lower frequencies because their energy storage (permeability) increases. At frequencies of 30-1,000 MHz, certain ferrites exhibit extreme wave compression and impedance close to air. Commercial ferrite tiles can achieve over 20 dB reduction in VHF band and 10 dB reduction through UHF, with a thickness of only 0.25 in. and a weight of 7 lb./ft.2.

So far, what has been discussed is reducing specular reflections—those that bounce off an object like light off a mirror—but RAM is also particularly effective at reducing surface waves. These are the waves emitted by currents induced in a conductive surface when struck by radar. As they move along the surface they emit traveling waves, usually at angles close to grazing, and when they encounter discontinuities—an airframe edge, a gap or step in the surface or a change in material—they emit edge waves, concentrated closer to the specular reflection. Surface currents travel along a material’s length rather than through its thickness, and the RAM acts as a waveguide, trapping the currents and absorbing them. Magnetic RAM can suppress surface currents well in a thickness of only 0.03 in. There are ways to combine techniques. Layered magnetic materials can reduce RCS by 10 dB from 2-20 GHz with 0.3 in. of depth. Hybrid RAMs can be created with a front layer of graded dielectric and a back layer of magnetic material to attenuate radar reflections from VHF to Ku-band (30 MHz-18 Ghz).

ram

new-bitmap-image-2

One disadvantage that all radar absorbing materials mentioned above share is that they add weight and volume without adding structural integrity.The radar absorbing materials developed for F-117, B-2 F-22 can kept their RCS small, but their maintenance burdens proved too heavy. Their durability disappointed, necessitating frequent replacements that ballooned support costs and time while restricting aircraft availability. RAM fillers tend to be spherical, a few to tens of micrometers in size and densely packed, which is good for absorptive qualities but bad for durability. Bonding them to aircraft surfaces also proved troublesome. As a result, from the beginning of the F-35 program, Lockheed’s goal was to achieve acceptable stealth while reducing maintenance needs.In May of 2010, Tom Burbage, then executive vice president for the F-35 program, disclosed the incorporation of “fiber mat” technology, describing it as the biggest technical breakthrough they’ve had on F-35 program.The fiber mat would replace many RAM appliques by being cured into the composite skin, making it durable. Burbage further specified the mat featured a “non-directional weave” which would ensure EM properties do not vary with angle. Baked into the skin, this layer could vary in thickness as necessary. Lockheed declined to provide further details, citing classification. Without further evidence, fiber mat would imply the use of fibers, rather than particles, which would make for stronger surfaces and the word “conductive” points to carbon-based RAM. That wasn’t the first time it is hinted that F-35 has a unique kind of RAM. One month before Burbage’s disclosure, Lockheed filed a patent claiming the first method of producing a durable RAM panel. The patent details a method for growing carbon nanotubes (CNT) on any kind of fiber—glass, carbon, ceramic or metal with unprecedented precision in control of length, density, a number of walls, connectivity, and even orientation. The CNT-infused fibers can absorb or reflect radar, and connectivity among the CNTs provides pathways for induced currents. Moreover, the CNTs can be impregnated with iron or ferrite nanoparticles. Fibers can have differing CNT densities along their lengths and homogenous fibers can be layered or mixed. The embodiments described include front layers with impedance matching air, use of quarter-wavelength depths for cancellation, stepped or continuous CNT-density gradients and continuously varying densities at specific depths for broadband absorption. The fibers can be disposed with “random orientation” in materials including “a woven fabric, a non-woven fiber mat and a fiber ply.”.The patent claims composites with CNT-infused fibers are capable of absorbing EM waves from 0.1 MHz to 60 GHz with particular effectiveness in L- through K-band.That is a bandwidth unheard of commercial radar absorbing material before. The patent does not quantify the absorptivity, but does say the panels would be “nearly a black body across . . . various radar bands.” Also, interestingly, a layer can be composed so an attached computer can read the induced currents in the fibers, making the layer a radar receiver.While the patent mentions stealth aircraft, it does not mention the F-35 specifically, and the manufacturing readiness level of the material at the time it was granted is not known. But the proximity in timing and technology of the filing to the “fiber mat” disclosure is hard to ignore.

sos-ram_chart4

Results:

With careful design stealth aircraft can have RCS equal a fraction of conventional aircraft.

rcs-of-aircraft

f-35-production-12-728

Benefit of low RCS

  • Reduce radar detection range: 

One easy to see benefit of RCS reduction is the deduce in enemy detection range ,thus giving pilots  more times to react to the threat or getting into weapon engagement zone

Example : radar detection range between conventional and stealth aircraft.

Radar detection range

  • Improve jamming effectiveness:

It is a common misconception that stealth technology is short live and as radar get more   powerful   , soon , they will be able to out range weapon engagement envelop , thus renders all money spend on RCS reduction a waste. This impression is inaccurate because any technology that can increase a radar peak power or gain   will also benefit a jammers in the same ways. And stealth have a synergy relationship with jamming .

Another common opinion is that the gap in RCS can easily be close by using a more powerful jammer .This is also inaccurate because RCS directly proportional to the power required to jam a radar at a certain distance.Which mean  when RCS is reduced to 1/100th the original value, the required jamming power is also reduced to 1/100th the original value to achieve the same effect.In others words, if a stealth aircraft need a 10 kW jammer , a conventional asset will need  jammer with power of 10Mw or more

If the jamming power is keeping the same then burn-through range is reduced by 10 times, which mean stealth assets( RCS =0.001m2 ) can get 10 times closer the threat compared to conventional aircraft ( RCS=0.1m2).In other words ,even if adversary radar can see through jamming of conventional assets from 400 km aways, a stealth asset can still get within 40 km of such radar using exactly same jamming system

  • Example : burn-through distance of F-35 , F-18E with same jamming assets, same threat radar ( image not to scale )

 jamming-burn-throgh31

  • Burn-through Range is the radar to target range where the target return signal can  first be distinguished from the Jamming signal ( rendering jamming ineffective).

Burn through effect

Low Observability In Infrared Spectrum.

All objects with a temperature above absolute zero emit heat energy in the form of radiation. Usually this radiation is invisible to the human eye because it radiates at infrared wavelengths, but it can be detected by electronic devices designed for such a purpose , these devices are called infrared (IR )sensor. With the improvement in optics and processing power of CPU , nowadays infrared sensors can see much further than human eyes .As a result, all stealth aircraft use one way or another to suppress their infrared signature.

Infrared signature suppression has two objectives:

  • Reduce the range at which an IR missile or sensor can detect and track the
    aircraft.
  •  Increase the effectiveness of countermeasure systems and devices.

It is important to note that infrared sensor detecting assets by comparing the contrast of such assets infrared signature  with background radiation , thus the effectiveness of infrared suppression is affected significantly by the temperature of background. In general clear sky is the worst background  due to their low temperature while   cloud and/or hot land surface make the best backgrounds for stealth aircraft to hide from adversary infrared sensor.( for the same reason, aircraft fly higher are much easier to detect by IRST )

Example: infrared photo of C-130 in 2  different background

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Like all electromagnetic radiation, IR interacts with matter in a variety of ways:

  • Reflects—A wave is reflected from a surface. The angle of reflection equals the
    angle of incidence.
  • Refracts—The direction of a wave bends when passing between two transparent
    media with different propagation speeds (Snell’s law).
  •  Scatters—Scattering occurs upon interaction with particles whose size
    approaches the length of the wave (why the sky is blue).
  • Diffracts—This interaction occurs around the edges of an obstruction.
  •  Interferes–This interaction occurs in both a constructive and destructive manner.
  •  Absorbs—When absorbed by matter, radiation is converted into another form of
    energy. The most common conversion is to heat.
  • Emits—Radiation is emitted from matter by conversion from another form of
    energy.
  • Transmits—IR propagates through a transparent medium (or vacuum).
  •  Polarizes—An electric field is partially polarized by reflection from dielectric

Infrared wavelength range from 0.7-14 µm ,  divided to short ( 0.7-1.5 µm ) medium (1.5-6 µm ) and long infrared wave (7-14 µm ),  with different characteristics they all have different military application.

Infrared band

Infrared signature of aircraft:

An aircraft’s infrared  signature is a complex mixture of emissions and reflections from different materials with different emissivity and different areas. Signature is complex in its spectral distribution, in its contrast against background, and in its dependence on conditions. Aspect angle, altitude, airspeed, ambient air temperature, power setting, and
sun angle are only a partial list of conditions affecting signature values.

F-4 IR signature

F-14A IR image

High infrared signature component of fighter aircraft:

  •  Engine “hot parts,” which usually consist of the aft turbine face, engine center
    body, and interior nozzle sidewalls.
  • Engine exhaust plumes, which are emissions from the combustion constituents
    of CO2 and water vapor.
  • Airframe, which includes all of the external surfaces of the wings, fuselage,
    canopy, etc. Airframe signature includes solar and terrestrial reflections, mach shock wave in addition to direct emissions.

Similar to radar cross section, IR signature of an aircraft is very aspect angle dependence thus lead to very different detection range, For example : OLS-35 ( IRST system on Su-35 ) can easily detect an aircraft from 90 km aways from tail aspect, however in head on aspect the detection range reduce significantly down to 30 km

Infrared band

infrared percentages

Airframe Aerodynamic Heating:

The temperature of the airframe is warmer than ambient by the amount of aerodynamic heating. A good estimate of airframe temperature is given by the formula for the recovery temperature given below. Note that the temperature units are Kelvin.The temperature of the skin of an aircraft stabilizes at the ambient air temperature plus aerodynamic heating. Aero heating increases as the square of Mach number. The formula below gives a good approximation:

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Aircraft moving at supersonic speed also produces compressed air ( Mach cone ) which not only increase the airframe temperature significantly but also increase frontal area present to the infrared sensor.

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Aircraft moving at Mach 1 can be detected  by IR sensor at twice the distance compare to aircraft moving at Mach 0.8

shockwave

supersonic and IR detection

  • As shown in table above flying supersonic can increase aircraft infrared signature significantly, so the most simple solution is to stay subsonic, the trade off of such decision is smaller  weapon engagement envelope, longer reaction time for adversary , this solution works well in design that high speed is not a requirement such as F-117 , B-2 .
  • Another solution is to use fuel as heat sink , most modern stealth aircraft have internal fuel tanks distributed evenly through out the airframe, the fuel being use all the time thus they can transfer the built up heat aways from the aircraft.Fuel can also be used to reduce heat generated by electronic equipments,avionics systems like radar and  jammer can generate very high amount of heat.Example :  fuel tank contribution of conventional aircraft ( on the left)  vs stealth aircraft ( on the right)

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  • Modern stealth assets also use  carbon composite material in the leading edge of the wing, such material has good IR dissipation ability, some RAM paints also have modest infrared reduction ability, For example the Top coat on F-22 , F-35 reported to reduce their skin infrared signature in long infrared wavelength (8–12 microns) by more than half.

F-22 , topcoat

Internal Equipment Heating:

Electronics equipment such as radars and jammers generate significant amount of heat, the more sophisticated and powerful the equipment is the more heat they will create , cooling are required not only to reduce enemy’s infrared sensor detection range but also to prevent the equipment from being overheat and shutdown

aircraft that lack significant  cooling features for electronics  often have higher body temperature , thus easier to  detect.

For example:

picture of F-16 in mid-infrared wavelength.

vidéo_pod_sniper_LM

  • Solution : As mentioned earlier , avionics can be cooled using fuels , furthermore aircraft can  use open vents, thus  atmosphere air can act  as heat exchanger with the fuel which got heated by avionics

For example : F-35  has a scoop located on the top of the right wing-glove to provide air to the fuel/air heat exchanger. A deployable scoop is located on the left-aft fuselage to provide air to the IPP and to the avionics

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The aircraft also use engines bypass air as heat exchanger

F-135 heat exchanger

Airframe heating due to engines:

With the core temperature of several hundreds degrees of modern jet engines , without appropriate measuares, they can increase aircraft body temperature dramatically

For example : picture of Typhoon in mid-infrared wavelength

typhoon-ir-1

Solution :

  • Airframe  heating due to jet engines can be reduced by extensive use of cooling vents, the cold air at high altitude  provides an isolation layer between the engine and the airframe

For example: the F-35 has two scoops located in the wing/fuselage to provide nacelle bay ventilation

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F-35 nozzle

Temperature from the exhaust fumes:

The biggest contributors of signature in mid-infrared wavelength on a jet aircraft is their exhaust fumes, reduction of exhaust temperature as little as 100 degrees can reduce aircraft infrared emission by more than haft

F-22 , topcoat

One very common misconception about jet engine and infrared signature is : an engine with higher thrust will always have a higher infrared signature, however that is an inaccurate assumption. It is entirely possible to have higher IR signature with lower thrust value.

Jet engine

To understand why lets have a look at the design of jet engines: below is a diagram of a normal turbofan engine commonly used in all aircraft flying nowadays:

The 2 main components that responsible for thrust are the Fan and engine core.

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The compressor , turbine and combustor ( also know as the engine core ) move air at very high speed hence, they are less dependence on air density and aircraft velocity. On the other hand, the fan stage moves air at much slower rate ,which is much more fuel efficient and also mix the exhaust plume with cold air, thus reduce the temperature of the plume. Not all air suck in by the first stage fan will go through the engine’s core (compressor , turbine and combustor ) some will pass through the outer duct. The air that passed through the outer duct is called bypass air. To get to a certain  thrust level, an engine can either have very big fan and small core ( good for combat radius and thermal signature ) or very big core and relatively small fan (good for speed and high altitude performance )

  • Due to reasons stated above one of the solution for exhaust temperature reduction is to use engines with higher bypass ratio , the trade off of such design choice is the aircraft will not be able to fly very high or very fast. ( For example F-135 have much higher bypass ratio compared to F-119 , EJ200 , Snecma M88 , R-15 ,F404 )

Engine Bypass ratio

 

  • A common misconception is that engine turbine inlet temperature is also proportional to exhaust temperature, that is wrong, however, in reality, turbine inlet temperature does not reflect the engine case temperature or even the exhaust plume temperature. It simply means that the gasses entering the turbine is at a higher energy state and the engine will yield more gross energy per drop of fuel or air entering the combustor(s). That energy however, is extracted to do work  first by the high-pressure turbine, then by the low-pressure turbine before going out the tail pipe at a given velocity. The final temperature depends on how much energy is extracted to drive the compressors and the fan, and how much bypass air is mixed into the exhaust. The F-35 has twice as many low pressure turbine stages which in theory will extract more energy. It also has a bigger and higher pressure ratio fan which adds energy to the exhaust as well as introduce relatively cold air into the mix. The exhaust plume temperature and engine case temperature can never be derived from the turbine inlet temperature alone.
  • It is also important to remember that unlike a rocket, jet engines are air-breathing engine, which means their performance depending a lot on air density, the thinner the air the less thrust they will be able to generate, so aircraft thrust will reduce as they go higher. For example: a jet engine that can generate more than 190kN at sea level can be  struggled to push out 10kN at 40-50K feet. On the other hand, a rocket engine can generate the same amount of thrust regardless of altitude

 

 

Using high bypass engine is not the only method of reducing exhaust temperature, however. Modern stealth aircraft also use exotic engines nozzles that either long and flat or with the serrated pattern so that exhaust fumes become unstable and mixed quicker with cool ambient air .As a result, the heat will be dissipated rapidly. In some aircraft, there are  spacing between nozzle plates linked to cooling vents to help reduce the temperature of outer nozzle surface

Example :

  1. F-117 and B-2 have flat  exhaust nozzles

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2.F-35 with serrated nozzle and cooling vents on nozzles

LOAN nozzles

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F-35B nozzle

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3. Thermal image of exhaust fumes.First nozzle uses conventional circular design. Second nozzle use serrated design. It is estimated that fumes length is reduced by around 40%

f_35_metal_rcs

4. Test data comparison between conventional exhaust nozzle and serrated nozzle:

nozzles

  • Stealth aircraft are also designed so that from front, the view of their engines nozzles will be  blocked by their vertical and horizontal stabilizer

Example:  conventional aircraft ( on the left ) have exposed engine nozzles  while stealth aircraft ( on the right ) have masked nozzles

visual

References :

  • Barr, E. S. “Historical Survey of the Early Development of the Infrared Spectral
    Region,” American Journal of Physics, Vol. 28, No. 1 (January 1960), p. 49.
  • Herschel, W. “Experiments on the Refrangibility of the Invisible Rays of the Sun,”Philosophical Transactions of the Royal Society of London, Vol. 90 (1800),
    pp. 284–292.
  • Herschel, W. “Investigation of the Powers of the Prismatic Colours to Heat andIlluminate Objects; With Remarks, That Prove the Different Refrangibility ofRadiant Heat. To Which Is Added, an Inquiry Into the Method of Viewing the SunAdvantageously, With Telescopes of Large Apertures and High Magnifying
    Powers,” Philosophical Transactions of the Royal Society of London, Vol. 90 (1800),pp. 255–283.
  • Hudson, R. Infrared System Engineering. Hoboken, New Jersey, John Wiley & Sons,1969.
  • Huygens, C. Treatise on Light. London, Macmillan and Co., Limited, 1690.
  • Naval Surface Warfare Center. Genesis of Infrared Decoy Flares. The Early Years from 1950 into the 1970s, by B. Douda. Crane, Indiana, NSWC, 26 January 2009.
    (ADA495417, UNCLASSIFIED.)
  • Newton, I. Opticks: or a Treatise of the Reflections, Refractions, Inflections & Colours of Light. The Second Edition, With Additions. Printed for W. and J. Innys, printers to the Royal Society, at the Prince’s- Arms in St. Paul’s Church-Yard, London,
    1718.
  • Planck, M., and Willis, A. P. Eight Lectures on Theoretical Physics. Mineola, NewYork, Dover Publications Inc., 1998. P. 92.
  • Sylvania Electronic Defense Laboratories. Radiometry, by F. Nicodemus. Mountain
    View, California, Sylvania Electronic Defense Laboratories, 15 March 1965.(Report Number EDL-G324, publication UNCLASSIFIED.)
  • Westrum, R. Sidewinder: Creative Missile Development at China Lake. Annapolis, Maryland, Naval Institute Press, 1999.
  • Schleher, C.D. (1978) MTI Radar, Artech House.
  • Schleher, C.D. (1999) Electronic Warfare in the Information Age, Artech House.
  • Skolnik, M.I. (1980) Introduction to Radar Systems, McGraw-Hill.
  • Stimson, G.W. (1998). Introduction to Airborne Radar, 2nd edn, SciTech Publishing Inc.
  • Thornborough, A.M. and Mormillo, F.B. (2002) Iron Hand – Smashing the Enemy’s Air Defences, Patrick Stephens.Joint Advanced Strike Technology Program, Avionics architecture definition – issues/decisions/rationale document, version 1, 8 August 1994. A. Doucet, N. Gordon, and V. Krishnamurthy. Particle lters for state
  • Joint Advanced Strike Technology Program, Avionics architecture definition – issues/decisions/rationale document, version 1, 8 August 1994.
    A. Doucet, N. Gordon, and V. Krishnamurthy.
  • Particle lters for state estimation of jump Markov linear systems. IEEE Transactions on Signal Processing, 49(3):613–-624, 2001.N.J. Gordon, D.J. Salmond, and A.F.M. Smith.
  • A novel approach to nonlinear/non-Gaussian Bayesian state estimation.In IEE Proceedings on Radar and Signal Processing, volume 140, pages 107-–113, 1993.F. Gustafsson.
  • Adaptive Filtering and Change Detection. John Wiley & Sons Ltd, 2000.
  • Military & War Documentaries HD (2017) Building the ultimate fighter jet – Eurofighter typhoon documentary. Available at: https://www.youtube.com/watch?v=iBppYV8X3nQ (Accessed: 17 January 2016).
  • Katz, D. (2016) The ‘magic’ behind radar-absorbing materials for stealthy aircraft. Available at: http://aviationweek.com/aircraft-design/magic-behind-radar-absorbing-materials-stealthy-aircraft (Accessed: 28 October 2016).
  • Lockheed Martin Corporation.(2010) Patent US20100271253 – Cnt-based signature control material. Available at: http://www.google.co.uk/patents/US20100271253 (Accessed: 7 February 2016).
  • RAO, G.A. and MAHULIKAR, S.P. Integrated review of stealth technology and its role in airpower, Aeronaut J, December 2002, 106, (1066), pp 629–641.
  • ROGERS, C.B. and PAREKH, D.E. Mixing enhancement by and noise characteristics of streamwise vortices in an air jet, AIAA J, March 1994, 32, (3) pp 464–471
  • SAMIMY, M., ZAMAN, K.B.M.Q. and REEDER M.F. Effect of tabs on the flow and noise field of an axisymmetric jet, AIAA J, April 1993, 31, (4), pp 609–619.
  • SAMIMY, M. KIM, J.H. and CLANCY, P. Supersonic jet noise reduction and mixing enhancement through nozzle trailing edge modifications, 35th AIAA Aerospace Sciences Meeting and Exhibit, 6-9 January 1997, Reno, NV, Paper No 97-0146
  • SAMIMY, M., KIM, J.H., and CLANCY, P. Mixing enhancement in supersonic jets via trailing edge modifications, 4th AIAA Shear Flow Control Conference, Snowmass, CO, 29 June-2 July 1997, Paper No 97-1877
  • PANNU, S.S. and JOHANNESEN, N.H. The structure of jets from notched nozzles, J Fluid Mechanics, 1976, 74, (3), pp 515–528.
  • SADDINGTON, A.J., KNOWLES, K. and WONG, R.Y.T. Numerical modelling of mixing in jets from castellated nozzles, Aeronaut J, December 2002, 106, (1066), pp 643–652.
  • BANKEN, G.J. CORNETTE, W.M. and GLEASON, K.M. Investigation of infra-red characteristics of three generic nozzle concepts, 16th AIAA/SAE/ASME Joint Propulsion Conference, 30 June-2 July 1980, Hartford, CT, USA, Paper no AIAA-80-1160.
  • DECHER, R. Infra-red emissions from turbofans with high aspect ratio nozzles. AIAA J, December 1981, 18, (12), pp 1025–1031.
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2 thoughts on “RF-IR Stealth (Techniques/Benefits)

  1. There are a handful of intriguing points with time here but I do not know if I see these people center to heart. There is certainly some validity but I’ll take hold opinion until I take a look at it further. Good post , thanks and we want a lot more! Added to FeedBurner also

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