US3502285A - Missile system with pure fluid guidance and control - Google Patents

Description

MISSILE SYSTEM WITH PURE FLUID GUIDANCE AND CONTROL March 24. 1970 T. GAMBILL Original Filed June 24, 1965 FIG. 2

Russell T. Gqmbill,

INVENTOR.

United States Patent 3,502,285 MISSILE SYSTEM WITH PURE FLUID GUIDANCE AND CONTROL Russell T. Gambill, Huntsville, Ala., assignor to the United States of America as represented by the Secretary of the Army Continuation of application Ser. No. 466,869, June 24, 1965. This application Apr. 19, 1968, Ser. No. 723,650 Int. Cl. F41g 7/12; F421) 15/02; G06f 15/50 U.S. Cl. 2443.22 2 Claims ABSTRACT OF THE DISCLOSURE A missile system in which dilferential pressures from opposite sides of a missile are picked off and used to control fluid amplifiers. The fluid amplifiers in turn have output ports thereof that are controlled by said differential pressures to provide fluid control to exhaust gases from the rocket motor of the missile. By utilizing four fluid amplifiers and their control on the exhaust gases from the rocket nozzle, the missile is guided in two degrees of freedom.

This application is a continuation of application Ser. No. 466,869, filed June 24, 1965, and now abandoned The invention described herein may be used by or for the Government for govermental purposes without the payment of any royalty thereon.

This invention relates to a missile system in which pure fluid mechanism is used to guide and control the flight of a missile.

In the missile industry, there is a constant need for guidance and control mechanisms that are small, simple, accurate, reliable and relatively cheap to build.

Therefore, it is an object of this invention to provide a missile system with pure fluid mechanism that is used to guide and control a missile.

Another object of this invention is to provide a missile system with guidance and control mechanism for guiding a missile in two degrees of freedom.

A further object of this invention is to provide a guidance and control mechanism that has no moving parts.

A still further and primary object of this invention is to sense angle of attack of a missile and constrain the missile to straight line flight.

Still another object of the invention is to provide a guidance and control mechanism that can utilize the atmosphere and pressure from the motor of a missile to actuate and control the guidance and control mechanism.

Yet another object of this invention is to provide a pure fluid guidance system that jets into the atmosphere and/or exhaust gases from the motor of a missile to correct the course of the missile.

A still further object of this invention is to provide opposed sensor ports on the nose or side of a missile to sense deviations of the missile from the intended course.

In accordance with this invention, a missile system is provided and includes a missile that has a motor therein for propelling the missile to its intended destination and pure fluid guidance and control mechanism for guiding the missile while in flight. The missile is kept as near on course as possible by the guidance and control mechanism irrespective of disturbances from wind, gravity, aerodynamic dissymmetry of the missile, misalignment of the rocket thrust relative to the nominal axis of aerodynamic symmetry and relative to the center of mass, and aerodynamic disturbances accompanying the rapid change in flight speed.

In the accompanying drawing forming a part of this specification, and in which like numerals are employed to designate corresponding parts throughout the same:

FIGURE 1 is a perspective view, partially cut-away and in section, of a missile with guidance and control mechanism in accordance with an embodiment of this invention,

FIGURE 2 is a sectional view of a portion of another missile with guidance and control mechanism in accordance with another embodiment of this invention,

FIGURE 3 is a sectional view taken on line 33 of FIG. 2, and

FIGURE 4 is a sectional view taken on line 44 of FIG. 2.

The invention may be better understood by referring to the drawing in which numeral 1 to FIGURE 1 designates a missile according to this invention. The missile has anose portion 3 and a body portion 5 withfins 7 near the rear thereof. Body 5 has conventional solid propellant rocket motor 9 therein, but this motor could be of the liquid or hybrid types.

Guidance and control means for the missile include twoconventional fluid amplifiers 11 and 13. Each of the fluid amplifiers are supplied with power fluid from the rocket motor by a T-shaped interconnecting line 15 which connectsinputs 17 and 19 respectively ofamplifiers 11 and 13 to the rocket motor. It should also be noted that the amplifiers may be supplied with power fluid from some other conventional source than the rocket motor, if desired.

Nose portion 3 has foursensing ports 21, 23, 25, 27 located apart about a circle around the nose portion. Tube 29 communicates sensed pressures fromport 21 to one side of fluid amplifier 11, and tube 31 communicates sensed pressures fromport 25 to another and opposite side of fluid amplifier 11. Tube 33 communicates sensed pressures fromport 23 to one side offluid amplifier 13, and tube 35 communicates sensed pressures fromport 27 to another and opposite side offluid amplifier 13.

Fluid amplifier 11 has outputs 37 and 39 connected by tubes 41, 43 tojet ports 45, 47 respectively; andfluid amplifier 13 has outputs 49 and 51 connected bytubes 53, 55 to jet ports 57, 59 respectively.Jet ports 45, 47, 57, 59 are located 90 apart on a circle about the outside of the missile.

It should also be noted that even though the sensing ports are illustrated in the nose portion of the missile, they may be located in the side of the missile. Also, the jet ports are illustrated as jetting into the atmosphere, but if desired, they could jet into the exhaust nozzle of the rocket motor or jet partially into the atmosphere and partially into the exhaust nozzle of the rocket motor.

As illustrated in FIGURE 1, the jet ports are in front of the center of gravity of the missile, but they may be behind the center of gravity. This would only require that each output feed the opposite jet port to the one that it is illustrated as feeding in FIGURE 1, or the sensor signals could be fed to the opposite sides of the fluid amplifiers from the ones illustrated.

In operation, power fluid is supplied from rocket motor 9 by way of line 15 toinputs 17 and 19 offluid amplifiers 11 and 13 respectively. The power fluid is supplied opposite are sent bysensors 21, 25, or 23, 27 tofluid amplifier 11 or 13, the control fluid supplied from the sensors to the fluid amplifiers will cause different amounts of power fluid to flow out the outputs in proportion to the sensor signals. The different amounts of power fluid flowing out the outputs will also flow out the jet ports to create suflicient forces on the missile to cause it to tilt back to the correct position to maintain the desired trajectory.

For example, assume that the missile has tilted off course from a straight trajectory by tilting toward the top of FIG. 1. This will cause a greater sensed pressure atsensor 25 than atsensor 21. Therefore, more power fluid will be deflected to output 37 rather than output 39. The power fluid from output 37 will jet through jet port 45 to cause the missile to be tilted down to the correct position.

Referring now to the embodiment illustrated in FIGS. 2 and 3,numeral 100 designates a portion of a missile according to this invention. The missile has abody portion 102 with arocket motor 104 mounted therein. The motor has a body forming achamber portion 106 and anozzle portion 108. The rocket motor utilized is of the solid propellant type, but a liquid or hybrid propellant type could be used.

Guidance and control mechanism for the. missile includes fourfluid amplifiers 110, 112, 114 and 116. Each of the fluid amplifiers has apower input port 118, apower output port 120, andexhaust port 122,control ports 124, 126 and aninterconnecting chamber 128. Thepower input port 118 of each fluid amplifier is arranged relative to thepower output port 120 and theexhaust port 122 so that when equal and opposite signals are present atcontrol ports 124, 126, power fluid flowing throughpower input port 118 will flow outexhaust port 122. But when and only when a predetermined differential in pressure exists betweencontrol ports 124, 126, power fluid flowing through the power input port will be deflected intopower output port 120.Supply lines 130, 132, 134, 136 supply power fluid fromrocket motor 104 topower input 118 of each of the fluid amplifiers. Foursensing ports 138, 140, 142, 144 are equally spaced around the side of the missile to supply differential pressures to the control ports of the fluid amplifiers.

Branched line 146 connects sensingport 138 to controlport 126 offluid amplifier 110 and to controlport 124 offluid amplifier 114; and controlport 126 offluid amplifier 114 and controlport 124 offluid amplifier 110 are connected bybranched line 150 to sensingport 142.Branched line 148 connects sensingport 140 to controlport 126 offluid amplifier 112 and to controlport 124 offluid amplifier 116; and control .port 126 offluid amplifier 116 and controlport 124 offluid amplifier 112 are connected bybranched line 152 to sensingport 144.

Eachexhaust port 122 of the fluid amplifiers is communicated by one oftubes 154, 156, 158, 160 to the rear of the missile, and eachpower output port 120 is in communication with the exhaust nozzle by one oftubes 162, 164, 166, 168.Tubes 162, 164, 166, 168 open into the exhaust nozzle at positions 90 apart around the nozzle to jet power fluid into exhaust gases flowing through the nozzle.

In operation, so long as the missile continues in a straight line trajectory, equal pressures will be sensed at sensingports 138, 140, 142, 144 and equal and opposite pressures will be. communicated to controlports 124, 126 of each of the fluid amplifiers. Since equal and opposite pressures are present atcontrol ports 124, 126 of each of the fluid amplifiers, the power fluid supplied to inputports 118 will be exhausted throughexhaust ports 122 andexhaust tubes 154, 156, 158, 160 to the atmosphere. However, when the missile deviates from the straight line trajectory due to some disturbance, the guidance and control mechanism begins guiding the missile back to the straight line trajectory. For example, assume that the missile of FIGURE 2 is caused by some means to tilt to the left as viewed from the bottom. The pressure sensed at sensingport 138 will be greater than the pressure sensed at sensingport 142. Therefore, the sensed pressure communicated to controlport 124 of fluid amplified 114 will be greater than the sensed pressure communicated to controlport 126 offluid amplifier 114, and the flow of fluid throughcontrol port 124 will cause the power fluid frominput 118 to be deflected through power output andpower output tube 166 intoexhaust nozzle 108. This deflected power stream will act on the exhaust gases flowing throughexhaust nozzle 108 and cause the exhaust gases to be deflected to one side. This deflection of the exhaust gases will cause forces to be exerted on the missile to tilt it back toward the straight line trajectory and correct the course of the missile.

Since sensingports 138 and 142 form a pair of ports 180 apart and since sensing ports and 144 form another pair of ports apart, the guidance and control mechanism is adapted for guiding the missile in two degrees of freedom, namely pitch and yaw.

I claim:

1. A missile system including: a missile body; a rocket motor mounted in said body, said rocket motor having a single central exhaust nozzle coaxial with said body; and guidance and control mechanism mounted in said missile body and including four fluid amplifier means spaced about said single exhaust nozzle, each of said fluid amplifier means including a power input port, a power output port, an exhaust port, first and second control ports and a chamber intercommunicating all the ports, said exhaust port being in alignment with said input port for directly receiving power fluid therefrom, means supplying power fluid to the input port of each of the fluid amplifier means, first, second, third and fourth sensing means spaced 90 from each other on the side of said missile body, means communicating sensed pressure from said first of said sensing means to said first control port of a first of said four fluid amplifier means and to said second control port of a third and opposite of said four fluid amplifier means, means communicating sensed pressure from said third sensing means to said first control port of said third of said four fluid amplifier means and to said second control port of said first of said four fluid amplifier means, means communicating sensed pressure from said second sensing means to said first control port of a second of said four fluid amplifier means and to said second control port of a fourth and opposite of said four fluid amplifier means, means communicating sensed pressure from said fourth sensing means to said first control port of said fourth of said four fluid amplifier means and to said second control port of said second of said four fluid amplifier means, whereby the power fluid of at least one of said four fluid amplifier means will be diverted from the exhaust port to the power output port when sensed pressures on opposite sides of the missile exceed a predetermined ditferential, means communicating the exhaust port of each fluid amplifier means to the rear of the missile, and means communicating the power output port of each fluid amplifier means to one of four openings spaced 90 from each other and which open into said single exhaust nozzle of the rocket motor, whereby said missile body is guided in two degrees of freedom by the power output of said fluid amplifier means exhaust ports exhausting into said single exhaust nozzle of said rocket motor in response to trajectory diviations of said missile body.

5 6 2. A missile system as set forth in claim 1, wherein said 3,143,856 8/1964 Hausmann. fluid pressure from the rocket motor is utilized as the 3,255,971 6/1966 Widell. common source of power fluid for each of said four fluid 3,278,140 10/ 1966 Evans.

amphfisr means- FOREIGN PATENTS 5 879,835 12/1942 France.

960,525 3/1957 Germany.

References Cited UNITED STATES PATENTS 3,135,291 6/1964 Kepler et a1. 7,464 6/1964 Horton. VERLIN R. PENDEGRASS, Primary Examiner

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