Aeronautics and astronautics – Missile stabilization or trajectory control
Reexamination Certificate
2001-06-12
2002-09-24
Eldred, J. Woodrow (Department: 3644)
Aeronautics and astronautics
Missile stabilization or trajectory control
C244S003150, C244S003170, C244S003190, C244S003110, C244S003140
Reexamination Certificate
active
06455828
ABSTRACT:
SPECIFICATION
The invention relates to a method of combating near-surface and/or surface-bound targets, such as tanks and the like by means of a missile comprising a homing head, an effective charge, and at least one propulsive unit, the missile, after having passed an essentially vertical launching phase, being deflected into an essentially horizontal cruising and homing phase during which the missile scans the terrain ahead by means of the homing head, whereupon finally an essentially vertically downwardly directed approaching phase follows, once the homing head has locked on to a recognized target, an external reconnaissance system in an appropriate aircraft and/or space vehicle, such as a helicopter, a drone, or a satellite picking up information for guidance of the missile.
DE 196 26 975 C1 describes a missile which hardly can be improved further, at reasonable expenditure, as regards its structure to increase the probability of hitting. However, new tank protection systems in particular, such as so-called active protection systems require further improvement.
It was suggested in DE 42 17 185 C1, for example, that a missile be divisible so that, instead of a body member containing the warhead, sensors of a tank will detect and combat a decoy body which is detachable from the body member that includes the warhead.
Furthermore, an autonomous missile is disclosed in DE 42 23 531 C2, namely a missile comprising an inertia reference system to reduce initializing errors.
Likewise known are missiles which are guided towards a target entirely by an external means, instead of autonomous missiles, especially with homing heads and/or inertia reference systems. DE 44 16 885 A1, for instance, discloses a method of guiding a missile by at least one radiation source which can be located by two sensors disposed offset from each other in a launch pad. Guide commands are derived from the locating signals and transmitted to a guide means of the missile so as to keep the missile in the line of sight of at least one sensor detecting a target. This kind of missile control is complicated with LOS operations, i.e. in case of a direct shot method, if a disturbance occurs between the launch pad and the target. The Known method, however, fails completely if the target is not in any line of sight connection with the launch pad, such as is the case with NLOS operations.
A method of the generic kind defined is known from GB-A-2 148 465 according to which the missile trajectory is adjustable by adjustment of a launch means in response to target information received from the reconnaissance system, and photographs taken by the reconnaissance system are input into the missile memory before the missile is launched.
Methods of guiding missiles which are started from airplanes are known from EP 0 797 068 A2, U.S. Pat. No. 5,458,041, and DE 37 15 909 C1.
DE 31 45 374 A1 and DE 33 03 763 A1 describe methods of combating surface targets by means of missiles. These missiles, however, cannot be guided on the basis of information which may be obtained through an external reconnaissance system.
It is, therefore, the object of the invention to improve the method of the generic kind in question such that the short-comings of the prior art are overcome., i.e. in particular that more accurate target lock-on and a higher hit rate are achieved.
That object is met, in accordance with the invention, in that the missile guidance information picked up by the reconnaissance system are transmitted to the missile and, during the homing phase, the homing angle of the missile homing head is optimized continuously in response to target data transmitted to the missile by the reconnaissance system with a view to recognizing the target.
It may be provided, according to the invention, that the reconnaissance system scans the possible target area either statically or in flight during a mission an external reconnaissance system picking up and transmitting information for guidance of the missile.
It is likewise proposed, according to the invention, that, once a combat target has been recognized by the reconnaissance system, in particular as regards the type of target, location of target, and/or target movement, the missile is launched, under control of signals transmitted by the reconnaissance system to a missile launcher, such that the quasi-ballistic course of the missile will lead essentially to the target caught by the reconnaissance system.
According to the invention it is further preferred that, during the target approaching phase, once the target has been recognized and the missile homing head has locked on to it, the homing angle of the missile homing head is reduced and minimized largely together with a corresponding increase in resolution to recognize details of the combat target transmitted to the missile by the reconnaissance system, such as the engine area of a tank and the like.
Moreover, it may be provided according to the invention that the reconnaissance system passes on information picked up to a transmitter station and that the missile is guided to the target via the transmitter station.
Finally, it is also proposed, according to the invention that the missile supplies information to the transmitter station and this information is processed in the transmitter station, together with the data transmitted by the reconnaissance system for guidance of the missile.
The invention thus is based on the surprising finding that missiles conventionally operating autonomously by means of a homing head can be remote controlled, in addition, by a reconnaissance system and data can be transmitted permanently to the missile by the external reconnaissance system in order to continuously optimize the aiming direction of the missile during the homing phase so that, in principle, the result is a combination of two conventional homing methods, whereby the elimination of errors is greatly enhanced and the resulting hit rate far superior over the state of the art. The data link according to the invention between the missile and the reconnaissance system thus makes it possible to transmit timely target data to the missile, while in flight already, either directly or indirectly through a transmitter station, so as to increase the combat effectiveness.
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patent: 5857644 (1999-01-01), Kusters
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patent: 6318667 (2001-11-01), Morton
patent: 31 45 374 (1983-06-01), None
patent: 33 03 763 (1984-08-01), None
patent: 2 148 465 (1985-05-01), None
Arnold Michael
Gauggel Roland
Krüger Reinhard
Tränapp Norbert
Burns Doane , Swecker, Mathis LLP
Eldred J. Woodrow
LFK-Lenkflugkorpersysteme GmbH
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