U.S. patent number 3,747,533 [Application Number 05/201,521] was granted by the patent office on 1973-07-24 for short trajectory missile.
This patent grant is currently assigned to Werkzeugmaschinenfabrik Oerlikon-Buhrle AG. Invention is credited to Rudolf Rossmann.
United States Patent |
3,747,533 |
Rossmann |
July 24, 1973 |
SHORT TRAJECTORY MISSILE
Abstract
Short trajectory missile comprising a missile body and a missile
head separating during flight. A part of the missile head such as
the front end thereof is formed of a material capable of melting
due to the friction of air resistance.
Inventors: |
Rossmann; Rudolf (Zurich,
CH) |
Assignee: |
Werkzeugmaschinenfabrik
Oerlikon-Buhrle AG (Zurich, CH)
|
Family
ID: |
4432163 |
Appl.
No.: |
05/201,521 |
Filed: |
November 23, 1971 |
Foreign Application Priority Data
|
|
|
|
|
Dec 8, 1970 [CH] |
|
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18326/70 |
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Current U.S.
Class: |
102/529;
244/3.1 |
Current CPC
Class: |
F42B
10/52 (20130101) |
Current International
Class: |
F42B
10/00 (20060101); F42B 10/52 (20060101); F42b
013/20 () |
Field of
Search: |
;102/49.4,93,92.6,92.7,105 ;244/3.1 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Pendegrass; Verlin R.
Claims
I claim:
1. A short trajectory training missile comprising:
a missile body;
a missile head separably attached to the forward end of said
missile body;
said attached missile body and missile head having an exterior
shape to produce external ballistic characteristics within the
range of desired utilization identical to those of a corresponding
actual missile;
said missile having means for causing said missile head to separate
from said missile body upon passage of said missile from said range
of utilization, thereby substantially altering the ballistic
characteristics of said missile, and for imparting a rapid braking
of the trajectory of said missile;
said means comprising a hollow space on the interior of said
missile head, and a forward end of said missile head closing said
hollow space, said forward end being formed of a material capable
of being melted through by the friction of air resistance upon the
passage of said missile from said range of utilization, whereby
said hollow space is subjected to an instantaneous air pressure
increase, and said missile head being formed of a material capable
of bursting under the force of such interior air pressure
increase.
2. A missile is claimed in claim 1, further comprising an axial
channel extending into said missile body from the forward end
thereof, said missile head extending into said axial channel, said
hollow space communicating with said axial channel and at least one
radial hole extending outwardly through said missile body from said
axial channel to the exterior of said missile, whereby when said
forward end of said missile head melts, air passes through said
hollow space, inJo said axial channel, and outwardly through said
at least one radial hole, thereby creating increased rapid braking
of the trajectory of said missile.
3. A missile as claimed in claim 2, wherein said at least one
radial hole comprises a plurality of radial holes symmetrically
spaced around said missile body.
4. A missile as claimed in claim 2, wherein said at least one
radial hole comprises a pluralIty of radial holes asymmetrically
spaced around said missile body.
5. A missile as claimed in claim 2, wherein said at least one
radial hole comprises four radial holes spaced around said missile
body.
Description
BACKGROUND OF THE INVENTION
The present invention relates to a short trajectory missile with a
missile body and a missile head which separates from the body
during the flight of the missile. A missile of this kind should
have the same external ballistic characteristics for practice
purposes in the range or area of utilization as the or actual type
corresponding thereto. In the braking zone of the flight of the
missile, means or agents should become effective to alter the
ballistic characteristics of the missile in such a way that the
flight trajectory will be considerably reduced in comparison with
that of the effective or actual missile.
With a known missile of this type, the missile head is held by
balls which are introduced into the missile head, into which a
groove of the missile body projects and is held by a pin. At the
time of firing a safety bolt is sheared off and the pin is thrown
backwards, so that the balls become free. However, in the area of
utilization these balls are pressed outwardly into the
aforementioned groove by centrifugal force. Following a reduction
in the centrifugal force, the balls fall out of the groove in the
braking area, and the missile head is thrown forward by a spring,
as a result of which the missile head and missile body rapidly
loose speed and fall to the ground.
A disadvantage with this missile is that a large number of
components are required for the separation of the missile head, as
a result of which the manufacture of the missile requires
considerable expenditure in time and money.
SUMMARY OF THE INVENTION
It is an object of this invention to create a short trajectory
missile with a very simple and cost-saving design, such missile
having the same external ballistic charcteristics in the range or
area of utilization as the effective or actual missile
corresponding thereto.
In accordance with the invention there is provided a short
trajectory missile comprising a missile body and a missile head
capable of separating during the flight of the missile, wherein a
part of the missile head comprises material capable of melting due
to the friction of air resistance. In a particularly advantageous
embodiment, a front end of the missile head consists of a material
capable of melting as a result of the friction of air resistance,
and the missile head has a hollow space, so that after the melting
of the aforementioned front end, the missile head bursts as a
result of a momentary increase in air pressure into the hollow
space and is separated from the missile body.
The advantages achieved with the invention lie in the fact that the
missile has a very simple construction, whereby the flight range
can be determined by a corresponding dimensioning of the missile
head. The external ballistic characteristics of the missile can be
matched to those of the effective or actual missle by weight and
shaping of the missile body and missile head.
BRIEF DESCRIPTION OF THE DRAWINGS
The invention will now be described by way of example with
reference to the accompanying drawings in which:
FIG. 1 shows a longitudinal section through the short trajectory
missile;
FIG. 2 shows the short trajectory missile of FIG. 1 but without
protective hood and plastics sheath during flight in the area of
use; and
FIG. 3 shows the short trajectory missile of FIG. 2, without the
separated missile head during flight in the braking zone.
DETAILED DESCRIPTION OF THE INVENTION
Referring to the drawings FIG. 1 shows a missile body 1 provided at
its front end with an axially drilled channel 2 into which extend
four radially drilled holes 3, which are mutually perpendicular to
each other. The missile body 1 has an annular front surface 4,
which is engaged by annular ridge 6 of a missle head 5, the missile
head 5 projecting into the channel 2. The missile head 5 tapers to
a front end 8 and has an interior hollow space 7 opening rearwardly
into channel 2. The missile head 5 is thus hollow and is made from
a material capable of melting as a result of the friction of air
resistance, in this case plastic material. The missile body 1 is
surrounded by a plastic sheath 9, which at its rear end has a
guiding and sealing band 10. A protective hood 11 surrounds the
missile head 5 and the front end of missile body 1 and is secured
in an annular groove 12 of the plastic sheath 9.
The missile is shown while in flight in the area of utilization in
FIG. 2, whereby the air L striking the missile head 5 creates a ram
or pressure point P and flow lines S.sub.1 and S.sub.2. FIG. 3
shows the missile while in the braking zone whereby the
unfavourable flow ratios are represented by flow lines S.sub.3 and
S.sub.4.
After firing, when the short trajectory missile has left the
barrel, the protective hood 11 and plastic sheath 9 are separated
from the missile body by centrifugal force. The missile, including
the missile head 5, now posses a favourable, low resistance
external shape, creating flow lines S.sub.1 and S.sub.2 (see FIG.
2). At ram point P the front end 8 of the missile head undergoes,
as a result of the friction of air resistance, an increase in
temperature, which, for example, at a missile velocity of 1,300/m/s
is about 850.degree. C and causes the missile head to melt. The
wall thickness of the hollow missile head 5 is dimensioned so that
the possibility of melting through in the area of utilization is
avoided, that is to say, that the optimum missile shape is
maintained in the area of utilization.
On entry of the missile into the braking zone, the melting process
has progressed sufficiently that the front end 8 of missile head 5
is melted completely through. The opening occuring as a result of
this brings out a displacement of ram point P rearwardly into
hollow space 7. The momentarily effective pressure increase
therefore brought about in hollow space 7 causes the missile head 5
to burst and separate from missile body 1. The air L flowing into
channel 2 is directed radially outwardly through radial holes 3, as
a result of which a turbulent flow develops on the external surface
of the missile body. As a result the flow characteristics of the
missile become very unfavourable, as shown in FIG. 3 by flow lines
S.sub.3 and S.sub.4, and air resistance is increased very
considerably. The missile body is thus braked very quickly so that
the flight trajectory is tremedously reduced.
In this embodiment, the four radial drillings 3 are arranged
mutually perpendicular to each other, or in other words, they are
arranged symmetrically in relation to a plane running through the
longitudinal centre line A of the missile. With an asymmetrical
arrangement in relation to the aforementioned plane of at least two
radial drillings, the stability of the missile body is additionally
disturbed in the braking zone. A resultant movement similar to a
pendulum movement occurs, so that the flight trajectory is even
further reduced.
* * * * *