Патент USA US3081062код для вставки
March 12, 1963 3,081,051 R. o. ROBINSON, JR RADOME STRUCTURE Filed March 5, 1959 9. mmoine \ zmDhu monw wnul h J_ RALPH 0. RUB/IVSO/V JR. INvENTdR. V W ATTORNEYS 3,®8l ,51 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.