U.S. patent number 3,601,055 [Application Number 04/802,075] was granted by the patent office on 1971-08-24 for protective nose cover and in-flight removal means.
This patent grant is currently assigned to The United States of America as represented by the Secretary of the Navy. Invention is credited to Sydney R. Crockett.
United States Patent |
3,601,055 |
Crockett |
August 24, 1971 |
PROTECTIVE NOSE COVER AND IN-FLIGHT REMOVAL MEANS
Abstract
An expendable nose shield for use in a multistage missile
arrangement when a second stage is encapsulated within a first
stage and is launched from such location upon burnout of the first
stage. It comprises an ogive-shaped shell formed of four petallike
quadrants with their bases secured to the leading edge of the first
stage and their tips held together by a common clip. Forward
movement of the second stage releases the clip and the quadrants
separate and break off in the slipstream. The shield may also house
a stabilizing fin assembly including a sleeve through which the
second stage passes and which becomes attached to the slightly
enlarged tail portion of the second stage when the latter
emerges.
Inventors: |
Crockett; Sydney R. (N/A,
CA) |
Assignee: |
Navy; The United States of America
as represented by the Secretary of the (N/A)
|
Family
ID: |
25182772 |
Appl.
No.: |
04/802,075 |
Filed: |
February 25, 1969 |
Current U.S.
Class: |
102/377 |
Current CPC
Class: |
F42B
15/36 (20130101) |
Current International
Class: |
F42B
15/00 (20060101); F42B 15/36 (20060101); F42B
015/08 () |
Field of
Search: |
;102/105,49.4,49.5,34.4,35.4,37.4 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Stahl; Robert F.
Claims
I claim:
1. A removable protective cover for sounding probes mounted at the
nose of a booster motor comprising:
a series of shaped sections in mated relationship surrounding the
probe, said sections connected at their base to the booster and
forming a bore at the nose, and
a nose clip inserted in said bore which locks the sections in their
mated relationship,
said sections and said nose clip having interfitting parts to
retain the sections in place until clip removal, each of the
sections having a forwardly projecting tongue at the leading edge
thereof,
said nose clip including a circumferential groove into which the
tongues on said sections are received, said nose clip also
including an elongate control stem portion receivable in said bore
and extending therethrough with the inner end of said stem lying in
coaxial alignment with the forward end of the probe and directly in
its path of forward movement,
thus upon launch from the booster, the probe strikes and removes
the nose clip freeing the sections and wedging them outwards where
they are torn loose from the booster by the slipstream.
2. The cover as defined in claim 1 wherein the sections are mated
to each other by a tongue-in-slot arrangement.
3. The ogive-shaped cover as defined in claim 2 wherein the
sections are connected to the booster motor by a series of
breakaway fasteners.
4. The cover as defined in claim 1 wherein the sections are at
least four in number.
5. The cover as defined in claim 4 wherein spaced reinforced areas
occur on the interior surface of the joined sections to reinforce
the joint area between adjacent sections.
Description
STATEMENT OF GOVERNMENT INTEREST
THE invention described herein may be manufactured and used by or
for the Government of the United States of America for governmental
purposes without the payment of any royalties thereon or
therefore.
BACKGROUND OF THE INVENTION
1. Field of the Invention
This invention relates to protective nose devices for rocket-type
vehicles and more particularly it relates to improved nose shields
which protect a second stage adapted to be launched from a first or
boost stage at very high altitudes.
2. Description of the Prior Art
Primary means for exploration of the upper atmosphere has been the
use of meteorological probes or sounding rockets. the normal method
of placing such devices at desired altitudes is to use a first
stage booster motor which ejects a second stage probe at first
stage burnout. A suitable construction for this purpose is shown in
the inventor's U.S. Pat. No. 3,377,952 and that patent and the
background material there shown are incorporated herein by
reference. In many instances the probe has sensitive instruments
which must be protected from extreme conditions that may be
encountered during its flight to a high altitude.
While various protective devices have been proposed as coverings
for sounding probes during the early stage of flight serious
difficulties may arise at the moment when the protective covering
is removed. Prior art methods of removing such coverings include
explosive mounting bolts which upon a predetermined signal will
detonate and fragment the segmented protective cover. While this
method is generally successful it does create timing and ignition
problems and the handling of explosive materials may present
hazards. Another method of removing the cover has been the breaking
up or fragmenting of the protective cover by a severe blow from the
inner probe as it is expelled. However under some circumstances
such action may deflect or otherwise adversely affect the flight
characteristics of the probe.
SUMMARY OF THE INVENTION
THE present invention concerns a protective cover for a probe and
comprises a series of shaped sections in mated relationship which
when assembled have an ogive-shaped appearance. Each section is
preferably held in position at the base by rivets engaging the
booster, and at the nose by a cone-shaped clip. A tail fin assembly
for the probe may be positioned within the assembled cover where it
is picked up by the rear end of the probe upon probe launch and
becomes an essential part thereof as it emerges from the booster.
Each tail fin is preferably aligned with a joint between the cover
sections. Upon probe firing, the nose of the probe knocks off the
clip and frees the sections so that they are torn off by the
slipstream.
STATEMENT OF THE OBJECTS OF INVENTION
IT is an object of the present invention to provide an improved
sounding rocket protective cover which is simple in design, rugged
in structure and reliable in operation.
Another object of the invention is to provide a protective cover
for a sounding rocket which is nonhazardous to ground
personnel.
Another object of the invention is to provide a protective cover
for a sounding rocket which does not interfere with the functioning
of said rocket.
A further object is to provide a protective cover for a sounding
probe which obviates any timing and ignition problems at the moment
of probe release from the booster.
Other objects, advantages, and novel features of the invention will
become apparent from the following detailed description of the
invention when considered in conjunction with the accompanying
drawings.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is an overall perspective view of the forward end of a
rocket incorporating the present invention.
FIG. 2 is an enlarged longitudinal sectional view taken along line
2--2 of FIG. 1.
FIG. 3 is a perspective view of the cone-shaped nose clip.
FIG. 4 is an enlarged cross-sectional view taken along a line
substantially corresponding to line 4--4 of FIG. 2.
FIG. 5 is an enlarged cross-sectional view taken along line 5--5 of
FIG. 2.
FIG. 6 is a diagrammatic view of two ogive quadrants illustrating
the tongue-in-slot arrangement of joining abutting edges.
FIG. 7 is a perspective view showing the interior surface of one
ogive quadrant.
FIG. 8 is an enlarged cross-sectional view taken along line 8--8 of
FIG. 4.
FIG. 9 is a diagrammatic representation of the relative positions
of the parts as they appear just after probe expulsion.
DESCRIPTION OF THE PREFERRED EMBODIMENT
REFERRING now to the drawings and particularly to FIGS. 1 and 2
wherein is illustrated a protective probe cover assembly 10 and an
enclosed probe 12. The nose portion 14 of probe 12 is nestled
within the cover 10 while a central payload section 16 is
positioned within an elongate canister 18 which extends within the
bore of a booster motor 20. An elongated slightly tapered booster
extension 24 is located between the end of the booster motor 20 and
the cover assembly 10. Canister 18 has a flange 25 at its forward
end which is clamped to the rear of the booster extension 24 by
bolts 29 thus holding the canister in fixed axial alignment within
the elongated bore of the propellant.
After a predetermined period of time, usually at burnout of the
booster motor 20, it is necessary to free the probe 12 from the
confines of the protective cover assembly 10. The removal of the
cover assembly should be accomplished with as little probe
interference as is possible so that no damage or deflection is
caused to the probe or to any of the sensitive instruments carried
thereon.
As shown in FIGS. 4 and 5, the protective cover assembly 10
includes four or more elongated and shaped sections 26 joined at
abutting edges in mated relationship by a tongue-in-slot
arrangement, each section being so shaped as to give an ogive
appearance to the overall assembly. The rear portion of each
section 26 may be riveted to a sleeve 27 which telescopes within
booster extension 24. It will be noted in FIG. 7 that each section
26 has a grooved internally built up forward area 23 that
cooperates with like areas of adjacent sections to provide a nose
opening 30 having a tapered bore 32 therein. This bore receives a
correspondingly tapered axial stem 36 of a cone-shaped clip 34
designed to lock together the forward ends of sections 26. At
spaced peripheral intervals, reinforced ridges 27 (FIG. 4) are
provided along the interior edges of each section 26.
The cone-cone shaped clip 34 (FIG. 3) has a bottom recess or groove
50 extending around the stem 36. This groove receives an arcuate
protrusion 52 (FIG. 2) formed at the forward tip of each section 26
in such a manner as to lock the assembled sections together and
prevent separation. It is apparent that forward axial movement
directed against the inner end of stem 36 will eject the
cone-shaped clip 34 and free the ends 52 from their locked
positions. If desired an impact actuated explosive device can be
incorporated in the stem which will assist separation by
explosively removing the clip while simultaneously separating the
sections until they are removed by the slipstream.
As shown in FIG. 2 a fin engaging and retaining ring 38 may be
located within the booster extension 24 and may be an integral part
thereof if so desired. A probe fin assembly including a tubular
sleeve 42 and fins 44 may be engaged by ring 38 which serves to
support and align the assembly as shown. Each fin 44 is
accommodated within radially disposed slots 46 preferably
positioned in registry with the joints of the assembled sections
26. The support sleeve 42 is slightly larger than the exterior
dimension of the probe 12 so that when the probe leaves the booster
motor 20 it will pass freely through the sleeve until the flared
tail portion of the probe reaches the sleeve at which time the
sleeve is picked up and carried along on the probe tail portion and
the fins then serve to provide stability to the probe. O-ring 40
and a suitable snap ring 48 may be located within the stabilizer
fin mounting unit 38 and serve to steady the fins 44 in place until
they are picked up by the probe 12 as it leaves the booster.
Thus in operation it is clear that as the probe 10 leaves the
booster motor 12 at burnout, the nose 14 thereof strikes clip 34
removing it and freeing the sections 26. As the probe emerges from
the booster motor 12 the exterior surface of the probe nose pushes
against the interior of the sections 26 moving them out to where
the slip stream of the probe rips them away from their riveted base
connection.
* * * * *