Missile guidance | golis systems

GOLIS systems

Israel's Arrow 3 missiles use a gimbaled seeker for hemispheric coverage. By measuring the seeker's line-of-sight propagation relative to the vehicle's motion, they use proportional navigation to divert their course and line up exactly with the target's flight path.[7]

Whatever the mechanism used in a Go-Onto-Location-in-Space guidance system is, it must contain preset information about the target. These systems' main characteristic is the lack of a target tracker. The guidance computer and the missile tracker are located in the missile. The lack of target tracking in GOLIS necessarily implies Navigational Guidance.[2]

Navigational guidance is any type of guidance executed by a system without a target tracker. The other two units are on board the missile. These systems are also known as self-contained guidance systems; however, they are not always entirely autonomous due to the missile trackers used. They are subdivided by their missile tracker's function as follows:

  • Entirely autonomous - Systems where the missile tracker does not depend on any external navigation source, and can be divided into:
  • Inertial Guidance
  • Preset Guidance
  • Dependent on natural sources - Navigational guidance systems where the missile tracker depends on a natural external source:
  • Celestial Guidance
  • Astro-inertial guidance
  • Terrestrial Guidance
  • Topographic Reconnaissance (Ex: TERCOM)
  • Photographic Reconnaissance (Ex: DSMAC)
  • Dependent on artificial sources - Navigational guidance systems where the missile tracker depends on an artificial external source:
  • Satellite Navigation
  • Global Positioning System (GPS)
  • GLObal NAvigation Satellite System (GLONASS)
  • Hyperbolic Navigation

Preset guidance

Preset guidance is the simplest type of missile guidance. From the distance and direction of the target, the trajectory of the flight path is determined. Before firing, this information is programmed into the missile's guidance system, which, during flight, maneuvers the missile to follow that path. All of the guidance components (including sensors such as accelerometers or gyroscopes) are contained within the missile, and no outside information (such as radio instructions) is used. An example of a missile using Preset Guidance is the V-2 rocket.[8]

Inertial guidance

Inspection of MM III missile guidance system

Inertial Guidance uses sensitive measurement devices to calculate the location of the missile due to the acceleration put on it after leaving a known position. Early mechanical systems were not very accurate, and required some sort of external adjustment to allow them to hit targets even the size of a city. Modern systems use solid state ring laser gyros that are accurate to within metres over ranges of 10,000 km, and no longer require additional inputs. Gyroscope development has culminated in the AIRS found on the MX missile, allowing for an accuracy of less than 100m at intercontinental ranges. Many civilian aircraft use inertial guidance using the ring laser gyroscope, which is less accurate than the mechanical systems found in ICBMs, but which provide an inexpensive means of attaining a fairly accurate fix on location (when most airliners such as Boeing's 707 and 747 were designed, GPS was not the widely commercially available means of tracking that it is today). Today guided weapons can use a combination of INS, GPS and radar terrain mapping to achieve extremely high levels of accuracy such as that found in modern cruise missiles.[4]

Inertial guidance is most favored for the initial guidance and reentry vehicles of strategic missiles, because it has no external signal and cannot be jammed.[3] Additionally, the relatively low precision of this guidance method is less of an issue for large nuclear warheads.

Astro-inertial guidance

The astro-inertial guidance is a sensor fusion/information fusion of the inertial guidance and celestial navigation. It is usually employed on submarine-launched ballistic missiles. Unlike silo-based intercontinental ballistic missiles, whose launch point does not move and thus can serve as a reference, SLBMs are launched from moving submarines, which complicates the necessary navigational calculations and increases Circular error probable. This stellar-inertial guidance is used to correct small position and velocity errors that result from launch condition uncertainties due to errors in the submarine navigation system and errors that may have accumulated in the guidance system during the flight due to imperfect instrument calibration.

The USAF sought a precision navigation system for maintaining route accuracy and target tracking at very high speeds.[citation needed] Nortronics, Northrop's electronics development division, had developed an astro-inertial navigation system (ANS), which could correct inertial navigation errors with celestial observations, for the SM-62 Snark missile, and a separate system for the ill-fated AGM-48 Skybolt missile, the latter of which was adapted for the SR-71.[9][verification needed]

It uses star positioning to fine-tune the accuracy of the inertial guidance system after launch. As the accuracy of a missile is dependent upon the guidance system knowing the exact position of the missile at any given moment during its flight, the fact that stars are a fixed reference point from which to calculate that position makes this a potentially very effective means of improving accuracy.

In the Trident missile system this was achieved by a single camera that was trained to spot just one star in its expected position (it is believed[who?] that the missiles from Soviet submarines would track two separate stars to achieve this), if it was not quite aligned to where it should be then this would indicate that the inertial system was not precisely on target and a correction would be made.[10]

Terrestrial guidance

TERCOM, for "terrain contour matching", uses altitude maps of the strip of land from the launch site to the target, and compares them with information from a radar altimeter on board. More sophisticated TERCOM systems allow the missile to fly a complex route over a full 3D map, instead of flying directly to the target. TERCOM is the typical system for cruise missile guidance, but is being supplanted by GPS systems and by DSMAC, Digital Scene-Matching Area Correlator, which employs a camera to view an area of land, digitizes the view, and compares it to stored scenes in an onboard computer to guide the missile to its target.

DSMAC is reputed to be so lacking in robustness that destruction of prominent buildings marked in the system's internal map (such as by a preceding cruise missile) upsets its navigation.[4]

Other Languages