U.S. patent application number 10/522053 was filed with the patent office on 2005-09-29 for programmable artillery fuse.
Invention is credited to Kaden, Rolf, Kautzsch, Karl, Koch, Volker, Pannhorst, Johann.
Application Number | 20050211085 10/522053 |
Document ID | / |
Family ID | 30775065 |
Filed Date | 2005-09-29 |
United States Patent
Application |
20050211085 |
Kind Code |
A1 |
Kautzsch, Karl ; et
al. |
September 29, 2005 |
Programmable artillery fuse
Abstract
In an artillery fuse (12), particularly having a braking fuse
function, in the course of the loading procedure of the howitzer
for firing ammunition equipped with such a fuse (12), a quantity of
data significantly larger than the typical fuse-setting information
may be supplied parallel in time to the typical inductive
fuse-setting procedure, particularly initialization information for
satellite navigation to be performed on board after firing the
ammunition, if the fuse (12) is equipped according to the present
invention in the region of its cap (11), which is shaped like a
hollow truncated cone, with at least one infrared-radiation-sensit-
ive data interface (13), which works together bidirectionally with
a coupling element (16). Preferably, a transceiver is positioned on
the fuse (12) for bidirectional data communication, while a ring
(15), which may be pulled over its tip (14), is equipped with at
least three receivers distributed around the ring circumference as
the coupling elements (16).
Inventors: |
Kautzsch, Karl;
(Schwanstetten, DE) ; Koch, Volker; (Ruckersdorf,
DE) ; Pannhorst, Johann; (Dunnigen, DE) ;
Kaden, Rolf; (Villingen-Schwenningen, DE) |
Correspondence
Address: |
SCULLY SCOTT MURPHY & PRESSER, PC
400 GARDEN CITY PLAZA
SUITE 300
GARDEN CITY
NY
11530
US
|
Family ID: |
30775065 |
Appl. No.: |
10/522053 |
Filed: |
January 20, 2005 |
PCT Filed: |
August 2, 2003 |
PCT NO: |
PCT/EP03/08583 |
Current U.S.
Class: |
89/6 |
Current CPC
Class: |
F42C 17/04 20130101 |
Class at
Publication: |
089/006 |
International
Class: |
F42C 017/00 |
Foreign Application Data
Date |
Code |
Application Number |
Aug 7, 2002 |
DE |
102361576 |
Claims
1. A fuse (12) for artillery ammunition, which is settable during
the course of a loading procedure via a coupling coil positioned
within a cap (11) for the fuse, which cap is shaped in the form of
a hollow truncated cone, characterized in that said fuse has an
infrared data interface (13) in the region of said cap (11) for
receiving, parallel in time to the fuse-setting procedure, a
quantity of of data which is large in comparison with the
fuse-setting information, and which is large in comparison with the
fuse-setting information, and which is in the form of prediction
data as initialization information for satellite navigation for use
on board the ammunition after firing.
2. The fuse according to claim 1, characterized in that a data
interface (13a) is positioned centrally behind a flattened tip (14)
of the fuse (2).
3. The fuse according to claim 1, characterized in that a data
interface (13b) is positioned in a lateral surface of the cap
(11).
4. The fuse according to claim 3, characterized in that a ring (15)
is positionable on the cap (11), said ring having at least one
coupling element (16) for communication with the data interface
(13b).
5. The fuse according to claim 4, characterized in that at least
three coupling elements (16) are positioned distributed around the
circumference of the ring (15).
6. The fuse according to claim 5, characterized in that the
communication between said data interfaces (13) and said coupling
elements (16) is performed bidirectionally via transceivers.
Description
[0001] The present invention relates to a programmable artillery
fuse according to the preamble of claim 1.
[0002] Such a fuse having a coupling coil, positioned coaxially in
the region of its tip, for accepting fuse-setting data during the
loading procedure at the howitzer is NATO standard and described in
greater detail, for example, in DE-Z SOLDAT & TECHNIK [SOLDIER
& TECHNOLOGY], Issue 3, 1997, for the fuse series ANNZ DM74 and
ZDZ DM52. This standardized conductive interface operates at a
frequency of 100 kHz and programming cycles of 775 ms, a maximum of
30 bits able to be transmitted and acknowledged within a cycle.
Such a data rate is completely sufficient for the input of typical
fuse-setting information, particularly target distance and
triggering proximity, which are dependent on the flight time, or
impact delay and/or detonation height and possibly overflight
safety and self-destruct criteria.
[0003] According to EP 0 451 522 A1, a transmitting coil system is
housed in the howitzer, for the inductive transmission of
fuse-setting information into a fuse-setting coil of an artillery
shell positioned coaxially in the fuse tip, which extends
essentially over a third of a circle, along which the projectile is
supplied to the breech of the weapon and its fuse is inductively
set at the same time, i.e., equipped with the trigger
information.
[0004] According to U.S. Pat. No. 4,788,899 A, in contrast,
fuse-setting information of lesser informational extent, as may be
represented using 8 bit digital information, for example, is stored
in a capacitor bit by bit in that the capacitor is charged in the
fuse tip via a photocell, which has light applied to it from the
fuse front face via an optical fiber parallel to the fuse axis. To
input the fuse-setting information, i.e., to charge individual
capacitors, a hood is temporarily placed on the fuse front face
which contains a light source that irradiates these locally
assigned optical fibers to their photocells via individually
releasable channels. The informational extent thus transmittable is
therefore significantly less than in the case of inductive fuse
setting via a programming coil contained in the fuse, and nay not
be integrated into the howitzer as free of complications as
inductive information transmission in the course of the loading
procedure.
[0005] It is provided in U.S. Pat. No. 4,091,734 A, and comparably
thereto in EP 0 806 625 A2, not for setting artillery fuses, but
rather for cable-free information transmission to air-launched
rockets from their carrier aircraft, that the rockets are each
equipped with at least one optical-electronic receiver for
optical-electronic information transmission in order to avoid
departure malfunctions as may occur when, upon delivery of the
rockets from this flying launcher, plugs must first still be pulled
out of the rocket hull from cable connections transverse to the
start direction.
[0006] For future generations of artillery ammunition, to reduce
the ammunition required as a result of increased hit precision, the
use of target-dependent satellite-supported path influencing is
provided in particular. The artillery ammunition may be equipped,
according to U.S. Pat. No. 5,467,940 A, with Canard rudders to
increase the range by entering a flat glide flight after the apogee
of the ballistic starting curve, or may be equipped, according to
DE 197 40 888 A1, with a braking parachute to steepen the descent
rate out of the ballistic start curve, for example. In the latter
case, it is suggested therein that the target position for a final
phase control of the projectile be transmitted to the shell using
an inductive data transmission system before the shell is fired,
for example, and then this predetermined target data be compared
after firing on board the artillery projectile with satellite
navigation data obtained there, in order to obtain correction data
for the projectile steering. Such target coordinates, which are
merely to be preset, only have a data extent in the magnitude of
the typical fuse-setting information, however, possible current
projection data for accelerating the use of satellite navigation
may not be reliably introduced into the ammunition via an inductive
system of this type in the course of the loading procedure with the
speed necessary in regard to the cadence of the howitzer and then
possibly queried again to verify correct data transmission.
[0007] This also applies correspondingly for the use of correction
fuses to increase the hit precision by reducing the lengthwise
scattering or artillery ammunition. With these fuses, upon reaching
a predetermined path point, the artillery projectile is deflected
into a steeper descent path by an aerodynamic braking device
integrated into its fuse, as described in greater detail in regard
to the apparatus in DE 100 23 345 A and functionally in DE 199 57
363 A. DE 198 24 288 A1 represents a further example of a
correction fuse of this type, in which a GPS antenna is located in
front on the fuse tip, behind which electronics for performing the
satellite navigation functions are positioned inside. Foldable
mantel segments for the braking function of the correction unit are
positioned in the largest lower diameter region of the projectile
fuse between the electronics and the fuse safety device.
Established artillery ammunition, which is first equipped with its
fuse in case of use, is now fired using such a braking fuse instead
of the typical time fuse if necessary. The function-critical
braking point on the ballistic flight path then actually flown is
expediently established by comparing the current path data with
predetermined path criteria, the information about the current
flight path being obtained on board the projectile using satellite
navigation.
[0008] Such a satellite-supported path determination is, however,
extremely time-consuming in consideration of the short computing
time available during the engagement possibilities in the course of
a flight, such as braking the projectile at the right time, since
multiple navigation satellites must be detected over the horizon
and analyzed in regard to their instantaneous path data. This
computer navigation task for the current determination of
sequential positions on the path flown may, however, be decisively
shortened if as much projection data as possible about the location
determination using the navigation satellites foreseeably to be
detected may also be given to the navigation computer on board the
projectile. In order to be current, this data may not be provided
already in the magazine, but rather it must occur close in time to
the firing of the ammunition in order to be able to actually
noticeably shorten the necessary computing time for the path
determination on board. However, the data rate necessary for
transmitting navigation information for multiple satellites in a
short time is much too high to be executed via the inductive
coupling coil of the loading system.
[0009] Integrating a second coil system into the fuse, which is
optimized for the higher data rate for additional information to be
input inductively in addition to the typical fuse-setting presets,
could be considered. However, the installation space under the fuse
ogive is insufficient for two inductive coupling systems to be
operated separately; this does not even consider the problems of
interference-free separate operation of two systems which are
inductively coupled because of the installation conditions. The
suggestion of implementing the higher data rate of the additional
information via a sensor in the ammunition tail, known from EP 0
992 762 B1, also does not represent an achievable solution, at
least for existing ammunition. This is because a reliable, rapid
information connection to the electronic assembly in the ammunition
tip through the warhead is necessary for this purpose, which may
not be implemented as retrofitting in existing ammunition, but
rather requires a new construction. Such information coupling into
the projectile floor in the course of supplying the ammunition
would also not be compatible with the fuse setting introduced
during the loading procedure. Because of such compatibility
requirements, the typical inductive fuse-setting capability must be
maintained without interference in any case.
[0010] In recognition of these conditions, the present invention is
based on the technical object of being able to implement data rates
which significantly exceed the data extent of current fuse-setting
systems directly before the firing of the ammunition from the
howitzer, particularly to be able to transmit the greatest possible
extent of initialization data for a rapid satellite-supported
flight path determination on board the projectile, without
interfering with the established inductive fuse setting in the
course of the loading procedure in this way.
[0011] This object is achieved according to the present invention
by the combination of essential features cited in the main claim.
According to this claim, an infrared data interface in the form of
at least one IR receiver, which is connected to the navigation
electronics with its satellite navigation receiver and a satellite
antenna, as is described in greater detail in DE 10037886 A, for
example, is positioned under the radome of the fuse tip, e.g., in
front of the programming coil for the inductive fuse-setting
standard also positioned coaxially therein (possibly behind a
protective cap made of infrared-transparent plastic material).
[0012] The present invention and its refinements are described in
greater detail in the following on the basis of the single FIGURE
of the drawing, which has a simplified axial frontal view toward
the fuse tip, shaped like a truncated cone, as its object.
[0013] At least one infrared data interface 13a and/or 13b is
located inside the tip 11 of the fuse 12, which essentially has the
shape of a hollow truncated cone and may be blown open laterally to
release braking means. This interface is essentially a commercially
available infrared receiving diode, known per se, which is
installed coaxially behind the flattened fuse tip 14 and via which
a data stream up to 10,000 bits may be implemented without anything
further, which is completely sufficient to transmit all available
initialization information for satellite navigation into the
ammunition parallel in time to the inductive fuse-setting procedure
in the course of the loading procedure and thus reduce the
computing outlay on board to a minimum.
[0014] In this way, by maintaining the fuse-setting coil in the
fuse 12, the function of the widely established, standardized
inductive fuse-setting procedure in the course of the loading
procedure in the howitzer is ensured, while a preferably
pulse-frequency-modulated transmission of initialization
information for the satellite navigation is performed
simultaneously via the additional infrared data interface 13a
placed in front, just behind the fuse tip 14. These two data paths
may therefore not mutually impair one another in spite of being
close spatial neighbors because of the different transmission
principles (inductive and optical).
[0015] If the infrared data interface 13a is positioned coaxially
behind the center of the small truncated cone base of the fuse tip
14 in the form of a receiving diode, which is sensitive to infrared
radiation, as shown, for the optronic transmission of the
initialization information in the course of the loading procedure,
this requires a relative approach of the fuse tip 14 to a thrust
bearing in the weapon, equipped with an infrared radiation
transmitter as a coupling element, in order to be able to transmit
the initialization information in the course of the loading
procedure. Because, in the established loading technology, the
ammunition is not axially displaced before reaching the breech,
this thrust bearing having its infrared coupling element must be
axially displaceable in order to be able to approach the data
interface 13a sufficiently closely for the optronic data
transmission in the course of the loading procedure, even if there
is shorter ammunition, which would nonetheless still require
significant interventions in the construction of the weapon.
[0016] This problem is overcome if, according to a refinement of
the present invention, as also shown in the drawing, a ring 15 is
provided as the thrust bearing for receiving the coupling element
of the infrared transmission path, whose internal diameter is
between the smallest and the largest diameters of the fuse 12,
which is shaped like a truncated cone, so that it may be pushed
onto the fuse 12 from the flattened tip 14 in a self-centering way
without problems. The infrared data interface 13b is then
accessible not in the flattened tip 14, but rather in the truncated
cone lateral surface of the cap 11 for supplying modulated IR
radiation, for which the ring 15 is equipped with at least one
emitting coupling element 16 as shown in the drawing. In order to
not have to define the positioning of the ring 15 in relation to
the interface 13b with a narrow tolerance, multiple transmission
paths operated in parallel are made possible distributed around the
circumference of the ring 15. If large aperture angles are provided
for the interface 13b and the coupling element 16, it is
sufficient, because of the small installation space there in the
fuse 12 itself, to provide only one data interface 13b, while at
least three coupling elements 16 are distributed uniformly around
the ring 15.
[0017] The typical inductive fuse setting is not suitable for
acknowledgments to check the total extent of transmission, at least
for acknowledgments of a check sum, because of its data processing
capacity in regard to the transmission speed. In contrast, the
rapid infrared transmission allows a complete acknowledgment of the
data sets supplied for the functionally important initialization
information for satellite navigation, for which both the interface
13b and the coupling element 16 are each laid out as transceiver
units.
[0018] Therefore, in a modern artillery fuse 12, particularly
having a braking fuse function, to be able to supply a
significantly larger data quantity than the fuse-setting
information to be transmitted inductively in the course of the
loading procedure of the howitzer for firing ammunition equipped
with such fuses 12, particularly to supply initialization
information for satellite navigation on board the ammunition during
its ballistic flight, the fuse 12 is equipped according to the
present invention, behind its flattened radome tip 14, for example,
with an infrared data interface 13 in the form of a receiving diode
sensitive to infrared radiation, for example, via which the
initialization information for the satellite navigation receiver
may be supplied optronically parallel in time to the inductive
fuse-setting information, but without impairing it. Preferably,
however, a transceiver interface 13b is installed in the cone
mantel region of the fuse cap 11, which works together with at
least one of multiple transceiver coupling elements 16 on a ring
15, operated bidirectionally in parallel, through which the fuse
tip 14 projects for the data transmission.
* * * * *