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Патент USA US3081062

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March 12, 1963
3,081,051
R. o. ROBINSON, JR
RADOME STRUCTURE
Filed March 5, 1959
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RALPH 0. RUB/IVSO/V JR.
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ATTORNEYS
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Patented, Mar. 12, 1963
2
and 6 in the radome walls. A Well .12 of the insert houses
a pressure responsive device or pressure transducer 113,
hereinafter described in more detail.
$381,651
RADGME STRUCTURE
Ralph 0. Robinson, 51%, Silver Sepring, Md, assigned‘ to the
The hydraulic circulating system for supplying hy
United States of America as represented by the Secre
draulic ?uid to the pressure transducer is indicated in
FIG. 1 as having a hydraulic source ‘16, and a hydraulic
regulator 17 for maintaining a predetermined rate of
tar-y of the Navy
Filed Mar. 5, 1959, Ser. No. 797,553
7 Claims. (63. 244-14)
liquid ?ow through theinpu't line 19 to the insert 9 in the
nose of the radome. The hydraulic liquid is conveyed
from the hydraulic regulator 17 in the input line through
the quick disconnect 18 to the ?tting and then through
The present invention relates to a radorne for a mis
sile, vehicle or craft and more particularly to the com
bination of a rradome with a pressure sensing system.
channel 5 in the radorne Wall to the insert 9.
In the ?ight of missiles, it is necessary to know the force
The pressure transducer 13 is activated by pressure
exerted at the forward end of the missile or on the nose
of the radome, such as ram pressure or stagnation pres
exerted on the nose of the nadome during the course,
or ?ight of the vehicle and causes variations in the rate
sure due to changing speed, altitude or depth of the mis
sile. Prior apparatus for sensing the force and indicat
ing a representation thereof usually requires electrical con
ductors or air ducts in the walls of the radome for trans
ferring this force representation to missile controlling
of liquid flow through the insert. The hydraulic liquid
is returned from the insert 9 through channel 6 in the
radome wall to the ?tting 8 through the return line 29
and quick disconnect 211 to a flow measurement trans
functions, such as fuel, guidance, safety or aerodynamic 20 ducer 22. After the variations in the hydraulic liquid
operate the ?ow transducer, the hydraulic liquid is re
ones. However, this requirement of having conductors
or ducts in the Walls of the radome aifects the radar trans
turned to source 16.
mission properties of the radome by causing discontinui
may be dumped externally of the missile. The flow trans
ducer establishes lfl'OlTl the variations in the rate of liquid
ties therein, creating apparent target maneuvers or move
ments to the intelligence system of the missile.
One of the objects of the present invention is to pro
However, if necessary, the liquid
25 flow an electrical ‘Output signal across contacts 24 and
25 representative of pressure exerted on the nose of the
radome. This electrical signal is required for the opera
tion of the fuel, ‘guidance, safety or aerodynamic control
ling functions of the missile.
The hydraulic lines are provided with the hydraulic
vide a radome having a pressure sensing system which
does not affect the radar transmission qualities of the
radome.
An additional object of the present invention resides in
the provision of a hydraulic liquid in the structure of a
quick disconnects '18 and 21 so that the radome 1 may
radorne ‘for transferring pressure representation during
be removed readily without the loss of hydraulic ?uid
during testing and assembling of the missile.
the ?ight of a guided missile.
Another object of the present invention is to provide a
hydraulic circulation system for ‘measuring pressure exert
The insert and pressure transducer are made from a
dielectric material having the same qualities as the ra
dorne material so that the transmission of radiant energy
through the nose of the radome would not vary from
ed on the forward end of a radome.
Still another object of the present invention contem
plates incorporating a pressure measuring system in a
radome wherein the system exhibits electrical properties
equivalent to that of the ‘dielectric material of the radome
that through the radome walls.
With the development of the present pressure sensing
system, a representation of pressure exerted on the nose
without affecting the radar transmission properties of the
radome.
A further object is to provide hydraulic lines in the
of the radome is very easily ascertainable. The hydraulic
liquid in the circulating system has the same electrical
the hydraulic ?uid used in the hydraulic lines have ap
proximately the same radiant-energy transmission proper
‘14 is not a?ected by the liquid in the radome walls 3.
This dielectric characteristic of the hydraulic liquid over
comes the disadvantage of the prior apparatus of using
characteristics as the material of the radome walls where
structure of a radome in which the electrical properties of 45 by the transrnission of radiant energy from the antenna
ties as that of the radome material.
electrical wires or air ducts [for transferring the pressure
ther objects and many of the attendant ‘advantages
of this invention will be readily appreciated as the same 50 representation at the nose of the rad'ome. The wires
and air ducts caused discontinuities in the radar trans~
becomes better understood by reference to the following
mission properties of the radome walls resulting in ap
parent target errors in the intelligence received and/or
detailed description when‘ considered in connection with
the accompanying drawings, wherein:
FIG. 1 is a block ‘diagram of the pressure measuring
system in combination with the radome structure;
FIG. 2 is a cross sectional view of the pressure trans
ducer taken on ‘line 2—2 of FIG. 1; and
55
transmitted vby the steering system of the missile.
v
The pressure transducer 13 as shown in FIGS. 1, 2
and 3 is housed within a well 12 of the insert 9. Dur
ing movement of the craft or vehicle, a force is exerted
on the tip 26 of a movable plunger 27. The plunger
27 acts against a quartz or nonmetallic spring 28 which
Referring to FIG. 1, of the drawings, a radorne ll‘(ir1 60 bears against a ledge 29 in the wall 30 of ‘the well. The
plunger has a ?ange 32 with a keyway 33‘ for ?tting a rib
cross section) is shown for an antenna 14 of a guida‘ble
or key 34 on the wall of the well providing for a longi
or guided missile, vehicle, or craft. The radome is a
FIG. 3 is a cross sectional view of a modi?ed pressure
transducer.
dielectric made, for example, from alumina, glass rein
tudinal displacement of the plunger. The plunger is held
within the Well by a screw threaded retaining ring 35
forced lamina, or a ceramic material.
The walls 3 of the radome 1 are formed with channels 65 in the mouth of the well.
5 and 6 extending from fittings '7 and 8 to an insert 9 in
In the operation of the missile or craft, the vforce act
the nose 4 of the radome. The channels 5 and 6 may be
ing on the tip 26 of the plunger is known as ram pres—
of various cross-section con?gurations, for example,
sure. The displacement of the plunger is representative
of the pres-sure acting on the plunger. The narrow end
of the radorne by adhesive, or by other retaining devices 70 36 of the plunger in FIG. 2 is shown having a triangular
such as screw threaded means. The channels 10‘ and
shape in cross section. This shape of the plunger end 36
11 of the insert register with the ends of the channels 5
varies the rate or" liquid flow through the insert as a
square or circular.
The insert 9 is secured in the nose
3,081,051
3
particular function of the pressure exerted on the plunger.
> The con?guration of the end of the plunger and the cross
sectional shape of the ori?ce of the channel 10 in the
insert determines the manner in which the rate of liquid
flow varies with pressure. The relationship between pres
4
particular function of the pressure on said plunger tip
with the function determined by the cross sectional con
?guration of the reduced end of the plunger.
3. A pressure responsive ‘device as recited in claim 1
wherein the reduced end of said plunger has a transverse
sure and the rate of ?ow could be a linear, exponential,
logarithmic, or any other type of function. Accordingly,
any required function of ram pressure could be supplied
as an electrical output signal ‘from the flow transducer
channel, whereby the movement of said plunger varies
for the operation of the fuel, aerodynamics, guidance, or
safety controls of the vehicle.
verse channel.
channel input and return lines 5 and 6 in different parts
of the radorne, the radome could be made with the hy
draulic lines of various cross-sectional con?gurations and
with the input and return channels in the same part of
the radome. However, the pressure transducer would be
changed accordingly wherein the inlet and outlet ori?ce
of hydraulic channels enter the well of the insert ad
jacent to each other.
Depending upon how many different functions of pres
sure are necessary ‘for the operation of various control
ling means as the missile or craft changes in speed, alti
tude or depth, a multiplicity of hydraulic channels could
be made in the radome wall. Accordingly, the plunger
of the pressure transducer would have a similar multi
plicity of differently shaped ends to establish the various
due to the presence of said hydraulic ?uid in said hy
draulic lines.
5. A radome for use in a guidable craft, said radome
the hydraulic ?uid ?ow through said well as a particular
function of the pressure on said plunger tip with the func
tion determined by the cross sectional shape of the trans
4. In a guidable craft having a radome at its forward
“In FIG. 3 a modi?cation of the plunger of the pres
end and an electromagnetic wave antenna in said ra
sure transducer is shown. The modi?ed plunger 37 has
dome, a pressure transducer in the nose of said radome,
a transverse channel 33 for registering with the ori?ce of
and a plurality of hydraulic lines communicating with
the hydraulic line 5 or insert channel 10. The particular 15 said pressure transducer and formed as integral channels
function of the rate or" liquid flow as it varies wit-h ex
in the walls of said radome and of the same material as
ternal ram pressure could be determined by various con
said radon-re, the new use in said hydraulic lines of a
hydraulic fluid having the same dielectric properties as
?guration-s of the cross sectional shape of the transverse
the walls of said radome whereby radiant energy passing
channel 38 and the hydraulic channels 5 and ‘6.
Although the invention is indicated as having hydraulic 20 through said radome will not encounter discontinuities
functions or" the variation of the rate of liquid flow with a
pressure for the ?ow transducer to transfer as electrical
signals to the different controlling means such as fuel,
comprising an ogive-shaped body having walls formed
of a dielectric material, a plurality of hydraulic lines in
tegrally formed as channels in the walls of said radome
and of the same material as said radome, and a hydraulic
fluid in said hydraulic lines, said ?uid having dielectric
properties duplicating those of the dielectric material con
stituting the walls or" said radorne.
6. A radorne for use in a guidable craft, said radome
comprising an ogive-shaped body having walls formed
of a dielectric material, a plurality of hydraulic lines
integrally formed as channels in the walls of said radome,
and a hydraulic ?uid in said hydraulic lines, said hy
draulic lines and hydraulic ?uid having dielectric prop
erties duplicating those of the dielectric material consti
tuting the walls of said radome, whereby radiant energy
guidance, saLr’ety or aerodynamic.
passing through said radorne will not encounter discon
with a well, a plunger with a tip and a reduced end, said
fluid having dielectric properties duplicating those of the
Obviously many modi?cations and variations of the 40 tinuities due to the presence of said hydraulic lines or of
hydraulic ?uid in said hydraulic lines.
present invention are possible in ‘the light of the above
7. in a guidable aircraft, a radome comprising an
teachings. It is therefore to be understood that within
ogive-vshaped body having walls ‘formed of a dielectric
the scope Off the appended claims the invention may be
material, a pressure transducer in the nose of said ra
practiced otherwise than as speci?cally described.
dome, a plurality of hydraulic lines integrally formed as
What is claimed is:
channels in the walls of said radome and communicating
l. A pressure responsive device in the nose of a radorne
with said pressure transducer, and a hydraulic ?uid in
of a missile for measuring the external i?uid pressure
said hydraulic lines, said hydraulic lines and hydraulic
exerted on the nose of the radome, comprising a housing
‘plunger having a ?ange between said tip and end, said
plunger ?ange and end being placed within said well,
said well having a ledge portion, a spring between’ said
?ange and said ledge portion, said plunger .moving ‘against
said spring whereby the displacement of said plunger be 55
‘ing representative of the pressure exerted on the tip of
said plunger and said reduced end of said plunger being
capable of varying hydraulic iluid ?ow through said well.
2. A pressure responsive device as recited in claim 1
wherein the reduced end of said plunger has a cross sec
tional con?guration, whereby movement or" said plunger
varies the hydraulic ?uid ?ow through said well as a
dielectric material constituting the walls of said radome,
whereby radiant energy passing through said radcme will
not encounter discontinuities due to the presence of said
hydraulic lines or of hydraulic fluid in said hydraulic
lines.
References Cited in the ?le of this patent
The United States Air Force Dictionary, D, Van Nos
trand ‘Co., Princeton, N.J., 1957.
American Machinist, Dec. 2, 1957, pp. 106408.
Available in the USPQ Scienti?c Library.
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