US3224710A

US3224710A - Timed program apparatus for missile guidance

Info

Publication number: US3224710A
Application number: US7947A
Authority: US
Inventors: Hermann Joachim; Juergensen Ralph
Original assignee: Boelkow Entwicklungen KG
Current assignee: Boelkow Entwicklungen KG
Priority date: 1959-02-20
Filing date: 1960-02-10
Publication date: 1965-12-21
Anticipated expiration: 1982-12-21
Also published as: DE1150286B

Description

D 1965 J. HERMANN ETAL TIMED PROGRAM APPARATUS FOR MISSILE GUIDANCE Filed Feb. 10, 1960 2 Sheets-Sheet 1 l --2 PE 5 PP flIUUl MW 9 Mm. lufor i i [afar 7- Time Device Jnvento rs:

I: 20%. all Will-bull! dram Dec. 21, 1965 J. HERMANN ETAL TIMED PROGRAM APPARATUS FOR MISSILE GUIDANCE Filed Feb. 10, 1960 2 Sheets-Sheet 2 Fig. 2

Jnvenfors: 33mm. Hzznavfl Rmmu UTJeRGENSCU ulna m, mm Mam Tron-021 United States Patent 3,224,710 TIMED PROGRAM APPARATUS FOR MISSILE GUIDANCE Joachim Hermann and Ralph Juergensen, Munich, Germany, assignors to Bolkow-Entwicklungen KG., Munich, Germany, a corporation of Germany Filed Feb. 10, 1 960, Ser. No. 7,947 Clalms priority, application, Germany, Feb. 20, 1959, B 52,180 6 Claims. (Cl. 244-14) The present invention relates to a control device for guiding a missile into a target, said control device having a manually actuated control stick and remaining at the launching point. It produces independent control signals which are transmitted from the control device itself to the missile in a conventional Way.

This invention normally consists of a signal source, the signals of which are transformed according to the setting position of an arbitrarily variable control stick or other control member and are suitably transmitted to the missile to be guided. The control stick may be mounted on gimbals and is actuated by the person observing the moving missile, the actuation of said control stick corresponding to an extent required for correcting the observed deviation of the missile from its desired flight path.

Considerable skill and training are necessary for operating the control stick of such a control device, since the missile usually moves at a high speed and is seen by the operator as a relatively small point, circle or the like. On the other hand, the operator has simultaneously to observe the target to be hit and the missile. The fact that some time passes before the launched missile responds to the transmitted control signals is another complication.

It is the object of the invention to facilitate the guidance of a missile by means of a control device which remains at the launching place, the transmission of signals being rendered independent of arbitrary operations of the person actuating the control stick during a launching period.

It is another object of the invention to facilitate the guidance of a missile by means of a control device which,

Firstly, independent of the duration of pushing a Y push-button, an ignition pulse having a definitive time period is produced by the control device. This pulse is transmitted to one of the missiles being prepared for launching, and starts the booster of this missile;

Secondly, during the following launching phase signals are transmitted to the missile which favor the launching motions of the missile to be guided, without any possibility remaining for the operator to influence this action. Hence the. launching direction of the missile, which is to be launched, cannot be altered for instance by inadvertently moving the control member; and

Thirdly, after the missile is launched and has reached its full speed and thus its full controllability, there follows the actual guiding phase during which said missile can be guided into its target.

During this guiding phase signals are transmitted to the missile which depend on the adjustment of the manually actuated control member of the control device.

Another object of the invention is that the timing device also limits each working cycle of the control device. It is thus possible, for instance, to restrict the power consumption to a minimum. A small and light-weight power source can therefore be used, though suflicient operating capacity is not dispensed with. Therefrom results an apparatus construction which saves space and weight.

Still another object of the invention is that a working cycle comprising an ignition, a launching, and a guiding period can be released at any moment by pushing a spring-loaded push-button of the timing device, which is ice independent of the fact, whether the preceding'working cycle was finished or not.

According to a preferred form of the invention the signals are taken from a common carrier frequency source and are supplied through rectifying conductors to two modulation stages, where they are modulated bycontrol voltages which can. be varied arbitrarily only during a guiding period of the flight of the missile to be guided.

The arbitrarily variable control voltages together with a constant saw-tooth voltage taken from a common generator are supplied to pulse former stages at the exit of which circuit pulses of different widths can be accepted, said pulses serving the modulation of the carrier frequency.

In the following the invention will be described by means of a guided missile. Refer-ring to the drawing illustrating the invention,

FIG. 1 is a block diagram of the control device according to the invention;

FIG. 2 is a block diagram of the timing device of the control device according to FIG. 1; and

FIG. 3 is a diagrammatic perspective view of the control device according to FIG. 1.

The control device shown in FIG. 3 has a manually actuated control stick I mounted on gimbals which acts on two otentiometers. In the block diagram of FIG. 1 the manually actuated control stick is shown as control voltage stage 1' mainly consistingof two potentiometers. Two control voltages are generated there andsupplied to two pulse fonmer stages 2 .and 2a. Moreover, a constant saw-tooth voltage taken from a common generator 4 is supplied to the pulse

former stages

2 and 2a in such a way that a square pulse arises at each stage, one flank of which can be shifted to and fro by moving thecontrol stick. Hence squarepulses of arbitrarily variable widths appear at the exits of the pulse former stages 2 and 2

I Modulation stages

3 and 3a are connected to pulse

former stages

2 and 2a at their outlet sides. Said

modulation stages

3 and 3a are connected by rectifying

conductors

12 and 13, with a carrierfrequency generator 5 in sucha way that one modulation stage receives positive pulses only, while the other stage receive negative ones. Relay contact r of FIG. 2 serves to switch on or actuate the

modulation stages

3 and 3 by coupling operating power to these stages. The outputs of the

modulation stages

3 and 3a are connected together with a selector switch 8, which receives in such a way positive and negative pulses of carrier frequency signals having the rhythm of the pulses of the pulse former stages 2- and 2a. The widths of these pulses may be controlled by manipulating the control stick 1. Several missiles, for instance, eight may be connected with the selector switch 8 by two-wire cables. By turning the handle of the selector switch 8 the missiles may be connected one after another with the

modulator stages

3 and 3a and via a line 14'with a timing device 7.

Timing device 7 is connected by a charging line 30,to a common power source 9 which can be charged by a charging set 10. A rechargeable. battery, for instance, can be used as a power source 9; The charging set 10 may be directly connected tothe batter-y sothat it charges irrespective of the operating conditionof the device and without any supervision. A rectifier may be installed so that any current passage through the charging set 10 is prevented in the case of false polarity of the charging line 30. As a result, the charging set 10 can alternatively be connected to a. D.C.- or to an A.C.-source, without any necessity resulting for the actuation of change-over switches or the like.

The timing device may be actuated by'a spring-loaded push-button 15 which is usually covered by a safety device 16 shown in its ineffective position in FIG. 3. Hence, the

spring loaded push-button can be actuated only when safety device 16 has been turned counterclockwise into its position shown in FIG. 3 against the action of a spring which is not shown.

Timing device 7 is shown in detail in FIG. 2. The spring-loaded push-button 15 acts on two switches S and 5 connected in parallel and connected to power source 9 through line 39. Moreover, line 30 leads to a relay contact r In its closed position relay contact r connects the power supply to line 51 to actuate the switching units, including

modulation stages

3 and 3a shown in FIG. 1. Switch S is connected to a decoupling stage 20, a time stage 21, and an amplifier 19, in the output circuit of which there is fitted a relay R Moreover, a line 32 leads from switch S to a relay contact r In its rest position shown in FIG. 2 said relay contact r connects two

time stages

23 and 24, which are connected in parallel, to line 32 through line 33. Time stage 24, consisting for instance of an RC-combination, fixes the duration of the ignition phase, and time stage 23, consisting of an RC- combination, too, fixes the duration of the launching phase of the missile to be guided. Decoupling stage 20 mentioned above uncouples time stage 21 which fixes the operating time comprising the ignition, launching, and guiding phases of the control device from

time stages

23 and 24.

Switch S is connected to a relay contact r through line 34. In its rest position shown in FIG. 2 said relay contact r connects line 34 to the two-wire cable 14 which can be seen in FIG. 1. In the operating position of contact r the two-wire cable 14 is connected to line 17 coming from the carrier frequency generator 5 shown in FIG. 1.

Time stage 24 is connected to control amplifier 22 through amplifier 25. Said control amplifier 22 contains a relay R in its working circuit. However, the time stage 23 which fixes the launching phase is directly connected to control amplifier 22.

When actuating the spring-loaded push-button 15, switches S and S are closed, whereby time stage 21 is charged, while time stages 23 and 24 are charged through line 32, relay contact r and line 33. Thus amplifier 25 becomes effective, too. This amplifier is coupled to control amplifier 22 to block its operation when amplifier 25 is in its operating condition.

Now an ignition pulse can arrive at two-wire cable 14 through line 34 and relay contact r Thus, power at lead is coupled through relay contact r to two wire cable 14 through line 3 until the termination of the period in which the amplifier 25 blocks amplifier 22 to provide an ignition pulse. However, as soon as the charge in time stage 24 decays in the time constant circuit, amplifier 25 switches off and terminates the ignition phase. Control amplifier 22 is thus released, and hence relay R can pull up and bring its relay contacts r and r into the operating position. Independent of push-button 15 remaining pushed down, two-wire cable 14 is connected through contact r now in operating position to line 17 coming from carrier frequency generator 5. The ignition phase is therefore finished and the launching phase is started.

During the launching phase initiated by actuation of relay contact r connecting line 14 to line 17 so that the missile receives the output signals of the carrier frequency generator 5 by which said missile is given a positive incidence or upwardly inclined attitude with respect to its path of travel, said operation of relay contact r being a result of closure of switch 15 and the longer relative time constant of time stage 23 over time stage 2 resulting in operation of relay R and switching of contacts r for a time period which is independent of the operators manually influencing control stick 1. This launching period continues until the charge of time stage 23 has faded out and control amplifier 22 has thus become inatlective. Relay R is released, and its relay contacts 1' and r return to their rest positions shown in FIG. 2. Since push-button 15 has meanwhile also returned to its rest position shown in FIG. 2, time stages 23 and 24 are not charged again.

With the closing of switch S time stage 21 had been charged, too. Amplifier 19 was thereby switched in, which made its relay R in the working circuit pull up, and hence relay contact F was closed. Therefore, the different units of the control device namely the pulse

former stages

2 and 2a, the modulation stages 3 and 3a, the saw-tooth voltage generator 4 and the carrier frequency generator 5 as shown in FIG. 1 are supplied with current through line 31 until the charge of time stage 21 has faded out, after a time interval which is longer than the flying time of the missile. Amplifier 19 and with it relay R too, thus become deenergized, whereby relay contact r is returned to the position shown in FIG. 2. The current supply to said different units of the control device is interrupted. The working cycle of the control device is then finished, and the guiding phase is thus finished.

The operating process just described can be started again upon failure of a missile without awaiting the completion of the control cycle time by actuating push-button 15. This starting of a new control process is independent of the discharged state of time stages 21, 23, and 24 which determine the operating processes. Consequently, a working cycle comprising the ignition, launching, and guiding phases can be started at any time by actuating the spring-loaded pushbutton 15, this actuation being independent of the state of progress of the preceding working cycle. When reswitching selector switch 3, a new missile can therefore be launched by actuating push-button 15 immediately after the possible occurrence of a so-called launching failure. Since ignition of a missile is controlled by switch 15 through line 14, the selection of another missile into ready position with selector switch 8 will not launch the missile, but only serves to prepare it for launching when button 15 is closed.

In a general manner, while we have, in the above description, disclosed what we deem to be practical and efficient embodiment of the invention, it should be well understood that we do not wish to be limited thereto as there might be changes made in the arrangement, disposition and form of the parts without departing from the principle of the present invention as comprehended within the scope of the accompanying claims.

What we claim is:

1. A control device for guided missiles comprising in combination, means for generating an operating potentional, means for generating control pulses, means including a single control stick for manually deriving control signals of two different characteristics from said control pulses, means including a manually actuated switch to couple said operating potential both to ignite the missile and to generate said control pulses for a time period covering the missile flight, and a timing device for cou pling said control signals to said missile after the launching period of the missile to thereby place the missile under manual control of said means for manually deriving the signals until the time period covering the missile flight expires.

2. A control device as claimed in claim 1 in which the means for generating the control signals comprises a carrier frequency generator.

3. A control device as claimed in claim 2 in which the means for generating the control signals comprises two modulator stages, the inputs of which are connected with the carrier frequency generator.

4. A control device for guided missiles comprising an electric power supply, means for generating control signals, means for transmitting the control signals to the guided missile, manually actuated control means including a single control stick for varying the control signals, a manually actuated switch which connects said power supply to an ignition circuit of the missile and resettable timing means operated by said switch comprising three time stages which establish independent periods of operation for the ignition, launching and guiding phases of the missile, and which disconnects said manually actuated control means from the missile during the ignition and launching phases, wherein the three time stages are connected in parallel with the power supply through the manually actuated switch so that a new working cycle will immediately be started whenever said switch is actuated.

5. A control device as defined in claim 4 wherein the manually actuated switch comprises a spring loaded push-button, a spring-loaded cover normally over the pushbutton and wherein one of said time stages operates to switch on and off said means for generating control signals.

6. A control device as defined in claim 4 wherein the time stages each comprise R-C combinations which are connected to said power supply by said manually actuated switch.

References Cited by the Examiner UNITED STATES PATENTS 1,249,274 12/ 1917 Chandler 24414 2,397,088 3/1946 Clay 244--14 2,950,474 8/1960 Page 24414 2,958,282 11/1960 Czajkowski et al 10250 BENJAMIN A. BORCHELT, Primary Examiner.

SAMUEL FEINBERG, CHESTER L. JUSTUS,

Examiners.

Claims

1. A CONTROL DEVICE FOR GUIDED MISSILES COMPRISING IN COMBINATION, MEANS FOR GENERATING AN OPERATIVE POTENTIONAL, MEANS FOR GENERATING CONTROL PULSES, MEANS INCLUDING A SINGLE CONTROL STICK FOR MANUALLY DERIVING CONTROL SIGNALS OF TWO DIFFERENT CHARACTERISTICS FROM SAID CONTROL PULSES, MEANS INCLUDING A MANUALLY ACTUATED SWITCH TO COUPLE SAID OPERATING POTENTIAL BOTH TO IGNITE THE MISSILE AND TO GENERATE SAID CONTROL PULSES FOR A TIME PERIOD COVERING THE MISSILE FLIGHT, AND A TIMING DEVICE FOR COUPLING SAID CONTROL SIGNALS TO SAID MISSILE AFTER THE LAUNCHING PERIOD OF THE MISSILE TO THEREBY PLACE THE MISSILE UNDER MANUAL CONTROL OF SAID MEANS FOR MANUALLY DERIVING THE SIGNALS UNTIL THE TIME PERIOD COVERING THE MISSILE FLIGHT EXPIRES.