Technology Explained

Infrared Radiation

The infra-red is a term used to describe a particular group of electromagnetic waves, those which are longer than visible wavelengths and shorter than microwaves, numerically the band between 0. 8 and 1000 micrometres (um). This means that infrared radiation has very many properties similar to visible light, it can be focussed or diffused, absorbed or reflected.

The reason why the IR is so important is that it may be closely associated with heat and its transfer from bodies. When we heat an object or a volume of material, we are feeding energy into it – at an atomic level, this energy is in the form of crystal lattice vibrations (probably the best way of visualizing the process is to picture an infinite 3-D lattice of tiny balls, each connected to its neighbours by a spring, imagine then what occurs if we tap one of the balls), every atom vibrating about some equilibrium position in the lattice. To make things more complicated, in the physical world, the amount of energy each atom can transfer to its neighbour is limited to an amount of hf (h is Planck’s constant and f is the frequency of vibration) which leads to an interesting result – a heated body emits radiation throughout a continuous band of wavelengths, the relative amplitudes (levels) of each wavelength depending on the body’s temperature. Graph 1 illustrates this relationship. This means that every object radiates energy, the dominant wavelengths depending on the temperature. As it turns out, objects at temperatures around and below 1200°C radiate mainly in the infrared band, the higher the temperature, the shorter the dominant wavelengths. (Note: IR radiation can also be generated by exciting a molecular gas, as the frequencies at which the molecules rotate and vibrate fall into the IR band – this type of radiation forms narrow bands in the spectrum – see TE December 1981, Lasers).

Sources of IR energy

The easiest answer to that question is – any warm or hot object – however, the subject deserves a little more attention. The single greatest source of IR radiation is the sun, however only part of this energy would be available to illuminate the Earth’s surface, as large amounts are absorbed and scattered in the atmosphere, particularly by clouds and moisture. The Earth’s surface becomes a secondary source of IR, as it is being bombarded both with visible and IR energy from the sun and as a result, is being heated. Any processes releasing heat also lead to the emission of IR. All heat engines, i. e. the internal combustion engine or jet turbines radiate IR from various parts of their structures and also release hot exhaust gases. All warm-blooded creatures emit IR.

As far as a guidance system is concerned, all IR radiation from sources other than the target is a nuisance – background clutter that will lower detection ranges or even swamp the emissions of the target. Fortunately, most of the IR energy emitted by the Earth’s surface falls into the vicinity of 10 um, whereas the Sun’s radiation peaks in the visible band and reflected off the Earth’s surface would tend to swamp the region above 3 um, hence leaving a window around 4 um. The sky itself reflects and scatters a certain amount of IR, though its intensity is lower than that of the Earth’s surface.

An Aircraft as a Source of IR

Modern military aircraft are, in spite of the efforts of their designers, abundant sources of IR energy. The principal heat source is the propulsion, as jet engines have an efficiency far below 100%, a considerable amount of energy is thrown away, advertising the aircraft’s position.

The most intense IR source in a jet aircraft is the tailpipe (afterburner off). The exhaust gas temperature (EGT) of a typical turbojet, i. e. the J-79, is around 950°C, newer engines like the F-100 have an EGT of around 1300°C, the highest intensity is for wavelengths around 2 to 3 um (for the physics-oriented, the tailpipe is modelled as a blackbody or rather greybody radiator). The exhaust gases leaving the tailpipe form a plume, as they expand and cool. On dry thrust, the tailpipe is the strongest radiator, the plume being cooler, particularly in the instance of high bypass ratio turbojets (F-404) or turbofans (F-100), where the turbine exhaust gases are mixed with bypass air from the fan. Plume shapes and temperatures vary with engines and operating conditions. Diagram 2 illustrates typical temperature curves for a turbofan. Lighting the afterburner causes further radiation of IR, in fact, the exhaust plume, around 2000°C, then dominates the aircraft’s signature, being hotter and physically larger than the tailpipe. (Note: At speeds above 2. 5M the plume radiance will decrease due to the decreased overall engine pressure ratio).

Aside from tailpipe/plume emissions, the hot parts of the engine, e.g. exterior of the afterburner nozzle, also radiate. High-speed flight will heat the aircraft’s skin and the engine will usually heat up parts of the airframe.

A further source of emissions is reflected sunlight/IA, conventional paints apparently reflecting around 60%, though the newer low IR greys (USN F-14, F-4, F-18 etc. ) reflect around 5% to 15%. A well-polished canopy may also reflect enough energy for a lock-on.

From the practical point of view, the IR signature of an aircraft is impossible to eliminate, the best one could ask for is a reduction. The use of turbofans reduces the overall EGT and where possible, parts of the airframe may be used to shield the exhaust, as in the A-10, where the tail surfaces screen off the relatively cool exhausts of the TF-34s. (Note: The positioning of the engine makes it impossible to gain a lock-on with a shoulder-launched SAM, e. g. SA-7, until the aircraft has covered a relatively large distance, assuming the aircraft passes over the launch site. ) The use of low-reflectance paints and flat canopies (halos) can be of some use.

Atmospheric Propagation of IR Radiation

The atmosphere basically affects IR energy in three different ways – absorption, scattering and scintillation (for a more detailed treatment see TE December 1981, Lasers). Photons of IR wavelengths are absorbed mainly by atmospheric carbon dioxide and water molecules, fortunately for the militarist, this is a quantum physical effect and is confined to particular bands in the IR, leaving transmission “windows”. The most important windows in the near IR are centred on 1. 6 um, 2. 2 um and 3. 75 um, the last being the widest at about 1 um; at an altitude cca 5000 m and low water vapour concentrations these allow for up to 95% transmittance at ranges cca 30 km (16. 5 nm). If the water vapour concentration increases, scattering becomes noticeable. Scattering occurs when the wavelength of the IR is comparable in size with the scattering particles. Clouds and fog contain droplets around 1 um in size – this results in extremely low transmission throughout most of the IR band. On the other hand, rain droplets are much larger, with the seemingly surprising result that IR transmission through rain is substantially better. Rain is liable to degrade the system’s performance, but still allows it to function (at 1. 8 km/1 nm transmittance for light rain is cca 90% and for heavy rain cca 65%).

Scintillation is caused by the same effect responsible for the blooming of laser beams, local variations in the atmosphere’s refractive index caused by variations in temperature (observable flickering of distant images on a well-heated bitumen road). This effect isn’t particularly important for guidance systems, as the apparent changes in the target’s position get smaller and smaller as the weapon approaches the target; once the angular size of the target becomes larger than the size of the apparent changes in position, it can be neglected. The effects of the atmosphere can be summarized as a lowering of the target’s intensity over a distance, and the introduction of small position errors at large distances. These two effects basically serve to limit the maximum range at which a guidance system may detect, track and lock on to the target.

The Heat-seeking Missile

The aircraft as an intrinsic source of IR energy and the reasonably good propagation of IR clearly indicate the potential for relatively simple, accurate short-range missile guidance. As the target itself emits all the energy needed for detection and guidance, the weapon may be fire-and-forget, without the need for complex and cumbersome fire control and illuminating radar. As a relatively simple system, the weapon may be smaller and lighter, its fire-and-forget ability makes it then ideal as a dogfight weapon, complementing cannon. This is reflected in the widespread use of such weapons, e. g. the AIM-9J/L with the F-16, the R. 550 Magic/Mirage III/F1 or the Israeli Rafael Shafrir used with virtually all IAF fighter aircraft, not to speak of the K-13A Atoll or the AA-8 Aphid used by Warpac air forces.

A guided missile can be broken down into three systems, guidance and control, warhead and propulsion, all fitted to an airframe. Propulsion is usually provided by a solid propellant rocket with a burn time of the order of seconds, this is adequate for acceleration to speeds cca 3. 5 M. The warhead is usually small in weapons of this class, as it is assumed the missile will detonate either on the target or within it; warheads are commonly high explosive/fragmentation types. Most weapons employ a combination of proximity and impact fusing.

The guidance and control systems of the missile occupy its nose section, the guidance senses the position of the target and issues commands to the servos in the control section which then actuate the control surfaces to achieve the desired flightpath correction. The vast majority of operational IR guided missiles employ a canard control surface/tail stabiliser configuration, the type of canard employed usually betraying the particular emphasis placed during design, e. g. the stabilising fins fore of the canards on the R. 550 serve to prevent stalling at high angles of attack.

The guidance system itself commonly consists of a window/ filter assembly in the nose of the weapon, this serves to select only particular wavelengths of IR, these then enter an optical modulation system, a reticle or chopper, which enables a detector element to receive IR emissions from the target, while rejecting clutter. The output from the detector is processed by signal detection electronics which separate target positions carrying information from the clutter present, a computer then employs proportional navigation to generate guidance commands.

IR Optical Filters

An optical filter is a device, which, by a particular mechanism, allows the transmission of certain wavelengths, while suppressing others. The principal reason behind the use of filters in guidance systems is the necessity to suppress background IR radiation, such as reflected solar energy, or thermal radiation from the earth’s surface and to enable the guidance to discriminate between various parts of the target’s signature, as it wouldn’t be very helpful to have a $20,000 missile guide into a ten-metre long afterburner plume and detonate without damaging the target.

Optical filters used in these applications fall into two broad groupings, absorption filters and interference filters. Absorption filters are characterised by wide bandwidths (width of transmitted band) and are usually employed to suppress large regions, typically sunlight. Interference filters can be designed with extremely narrow bandwidths (less than 0. 1 of the wavelength at the band centre) and good transmittance, they have the further advantage of reflecting unwanted energy instead of absorbing it. The physical phenomenon exploited in this instance is interference, an effect that occurs when we add a wave to its own reflection. Consider a series of layers of transparent material, the layers with alternating refractive indices. If we pass a light wave through these layers it will be partly reflected at each interface between layers, with alternate interfaces reflecting in and out of phase. Now if the wavelength of the wave is four times longer than the thickness of the layers, an interesting thing occurs, namely the reflections from successive interfaces are all in phase, leading to a very high reflectance for that wavelength. Filters employ layers of varying thicknesses to achieve certain degrees of reflectance for particular wavelengths. Precise filters employ up to a hundred layers, and each must have a very accurately defined thickness (for IR less than one micrometre), in order to meet the bandpassing specifications.

Optical Modulators

Probably the most complex individual mechanism assembly in a missile guidance system is its optical modulator or reticle. It performs two extremely important tasks, providing the system with directional target information and suppressing background IR radiation. In principle, a reticle is an IR transparent substrate with a particular pattern of opaque and transparent fields on its surface. In operation the reticle is placed between the filter/ optics and detectors, its motion relative to the optics results in the chopping of the IR incident on the detector in such a fashion as to enable the electronics processing the detector’s output to separate information on the target’s direction from background images, typically sunlit clouds.

The subject of reticle design is quite complex; to make things more difficult, the military has had the most information on the subject classified, however, the basic principles may be understood from the following.

Diagram 3A illustrates a simple rotating reticle for background suppression. Consider the reticle to be rotating at a constant rate, then visualise it passing over the image in its field of view. The chopping action will result in different detector outputs for the point target and for the cloud. The pulses corresponding to the target (we assume the target is distant enough to be regarded as a point source) may then be easily separated from the rippled pulse corresponding to the cloud by electronic filtering (a narrow bandpass filter at the pulse frequency), thus enabling the required discrimination between the target and cloud.

Diagram 38 illustrates a reticle configured for the finding of the target’s direction. Once again consider a constant rate of rotation and pass it over the target. A pulse is generated during each rotation of the reticle, however, the instant in time when the pulse commences depends on the angular position of the target. The time lag or lead of the pulses or phase carries the information as to the target’s angular position, this information can be extracted via simple electronic means if we know the position of the reticle as it rotates, which is quite easily accomplished in practice.

The third reticle in Diagram 3 combines the functions of reticles A and B, providing directional information and background rejection. The upper half is comprised of opaque transparent fan-shaped segments, and the lower half is semitransparent with a transmittance equal to the average transmittance of the upper half. When the segmented half passes over the target, the output will contain a series of pulses and some varying output given by the background; when the semitransparent part passes over the target the output corresponds to the average brightness of the target and background. The output would resemble B, but with bursts of pulses instead of individual pulses. By electronically filtering out these bursts, we can separate target information from clutter, the phase of the bursts yields the angular direction. The radial distance of the target can be found by examining the amplitudes of the pulses, as the actual image of the target on the reticle is a circle rather than a point. The width of the segments on the reticle is smaller than the circle’s diameter, if the circle is near the edge of the reticle a lot of light is passed through, if it is near the centre, very little is passed, causing the observed variation in amplitude. Knowing the angular and radial components of the target’s direction, we can easily find the X and Y components with respect to the missile’s control axes, a computer can then find the required control deflection for target interception. It may be apparent to many a reader that this system cannot provide target direction information if the reticle axis (missile axis) is pointing directly at the target; actual operational systems employ complicated mechanical systems for the rotation and nutation of the optics and reticle to avoid this. The reticle patterns employed are also quite complex and must be extremely accurate.

An alternate method of determining the target’s direction would involve an array of detector elements; however, the electronics required to separate the target from clutter would be substantially more complex.

IR Detectors

The detector is a device that converts IR energy into some electrical signal, which is then processed by the missile’s electronics. As a device, the detector is comprised of a piece of semiconductor material (the photosensitive element), with antireflective and/or filter coatings and a reflector, which increases sensitivity by reflecting any IR that may have passed through the detector back into it. The two principal types of detector elements used are photoconductive and photovoltaic, the former change their electrical resistance when illuminated, and the latter generates an output voltage on illumination. An in-depth look at the mechanisms responsible for these effects exceeds the scope of this treatment, but some understanding may be gained from the following look at solid-state physics.

One of the basic conclusions of quantum physics was the fact that electrons orbiting an atom may have only certain discrete energies, energies other than those corresponding to the given orbits being forbidden. If we examine the electronic structure of a multi-electron atom, we find the electrons occupying the outermost orbits are the easiest to remove from the atom, by some external force. If we then take a large number of these atoms and begin to move them together, the orbits begin to interfere with each other, with the result that the previously sharply defined energy levels begin to smear out, leading to the formation of energy bands rather than levels for large numbers of atoms. The uppermost two levels, the so-called valence band and conduction band are of the most interest. The electrical resistance of a material depends on the number of free electrons in the material, the more free electrons, the lower the resistance. In terms of energy bands, an electron must transition from the lower valence band to the upper conduction band before it can be available for conduction as a free electron. The difference in energy between the two bands is called the energy gap (Eg), an electron in the lower band must receive at least this amount of energy to transition up and become free for conduction. One way in which this can happen is when an electron absorbs a photon of radiation with an energy hf larger than Eg.

This is basically the effect used in a detector. The energy gap in the semiconductor materials used is usually less than one electronvolt, which is close to the energy of IR photons with wavelengths shorter than 1 O um. Photons that enter the detector collide with electrons, enabling them to become free and alter the electrical properties of the detector. However, the detector must be cooled down to around – 200°C, as otherwise, the thermal energy of the vibrating atoms would free enough electrons to swamp the effects of the detected IR. Cooling is provided either by a closed-circuit low-temperature refrigerator or by a thermoelectric refrigerator (early AIM-9), the lower the temperature available, the higher the sensitivity of the detector.

The choice of a detector material depends on the required sensitivity at a given wavelength, which is given by the temperature of the target. The majority of materials used fall into the Selenides, Antimonides and Tellurides, typical IR-sensitive materials being Mercury-Cadmium Telluride (HgCdTe) or Indium Antimonide (lnSb). Early guidance systems were constrained by the lack of available detector materials to work in the 2. 5 um band – as a result, the weapons were easily confused by strong sunlight, cloud edges or flares and were not effective if launched at a target head-on, as they would rather guide for the plume than the aircraft. Later systems operate in the more convenient 4-um band, which falls into a reasonable transmission window and a region where background IR is fairly low. New weapons such as the GD Stinger employ combined infra-red and ultraviolet band sensors (POST seeker}, this enables the seeker to discriminate between targets and countermeasures such as flares, though its ability to handle jamming systems such as flashing IR beacons (Cesium lamps) could be questioned. (Further reading: Hudson, R. D. – Infrared System Engineering; Dow, R. B. – Fundamentals of Advanced Missiles.)

Heat-seeking missile guidance is, after more than twenty-five years of use, anything but obsolete. New technology expands launch envelopes and extends ranges with each new generation of weapons, some developments in electronics (consider the recent fabrication of 30 x 30 element arrays of HgCdTe on single mounting chips) may lead to completely different configurations in future weapons, the potential for improvements is very large.