US3680749A

US3680749A - Remote-controlled launch system for missiles

Info

Publication number: US3680749A
Application number: US844017A
Authority: US
Inventors: John S Davis
Original assignee: US Department of Navy
Current assignee: US Department of Navy
Priority date: 1969-07-23
Filing date: 1969-07-23
Publication date: 1972-08-01
Anticipated expiration: 1989-08-01

Abstract

The apparatus of the present invention is employed at an unmanned location to launch a missile by commands received over an R. F. link. The invention apparatus processes these commands and applies them to conduct power to the missile, start its engine, arm the electronics, and ignite a JATO bottle which effects the launch. Each received command is interrelated with signals obtained by monitoring the instantaneous missile tail pipe temperature, engine RPM, generator voltage, and radio control system status. Means are provided for aborting a launch if all prescribed missile operating conditions are not met.

Description

Uited States atom Davis [15] 3,680,749 Aug. 1, 1972 Primary Examiner-Stephen C. Bentley Attorney-Edgar J. Brower, Q. Baxter Warner and [72] Inventor: John S. Davis, Port Hueneme, Calif.

Howard J. Murray, Jr. {73] Assignee: The United States of America as Represented by the Secretary of the [57] ABSTRACT av y The apparatus of the present invention is employed at Flled! J y 1969 an unmanned location to launch a missile by com- [21] Appl. No.: 844,017 mands received over an R. F. link. The invention apparatus processes these commands and applies them to conduct power to the missile, start its engine, arm

. t v a fi c n n a t l n [5 8] held of Search g with signals obtained by monitoring the instantaneous missile tail pipe temperature, engine RPM, generator voltage, and radio control system status. Means are [56] References cued provided for aborting a launch if all prescribed missile UNITED STATES PATENTS operating conditions are not met.

2,866,385 12/1958 Miller ..60/243 3 Claims, 11 Drawing Figures RPM- SENSING UNIT I I4 T IR6E i UNIT l6 TAILPIPE FUEL TARGET RECE'VER 883%,;25 CONTROL MISSILE UNIT UNIT IO I2 '8 PRE- STARTER LAUNCH CONTROL X MONITOR UNIT TELEMETRY JB I MONITOR UNIT COMILAND Z'AEE CONTROL UNIT mm 1 l EXTERNAL POWER LAUNCH ,38

POWER CONTROL 2 CONTROL SOURCE UNIT UNIT PATENTEUAUI; 1 m2 SHEET 2 BF 9 NOmm; 6mm;

FIT

THROTTLE INCREASE DECREASE PATENTEDAUB 11972 3580749 saw u 0F 9 1 L THROTTLE E I 'LO K1067 4 SEC DELAY KIOI 70 SEC DELAY M U LT VIBRATOR 60 SEC DELAY TKIOOZ ril KIOOI 30 SEC DELAY 1 y POWER KIOO3 PATENTED AUG 1 I972 30 SEC DELAY SHEET 8 BF 9 4 SEC DELAY T KI706 OJ KIIOI T K330i FUEL CONTROL UNIT Fig.7

PATENTEDAUB 1 I912 SHEET 9 (IF 9 POWER I K1807 70 SEC.

DELAY (LOW THRUST) 5 SEC DELAY DC POWER POWER COMMAND C 4 D llll ll 0 \l m K m F E M E m K 9 R O E I: m m K R A C 8 0 Q1. m. K NW.- R C E0 D 0 WP P 9 POWER K80! INTERLOCK UNIT REMOTE-CONTROLLED LAUNCH SYSTEM FOR MISSHJES 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 At the present time many missiles are being launched by personnel located in the immediate vicinity of the launching operation. This constitutes a hazard to such personnel in the event of a malfunction of such nature as to cause the missile to blow up or otherwise destruct before it has traveled any appreciable distance. Although remote-controlled systems have been tried previously, they have frequently failed to take into consideration the instantaneous operating status of each missile component or sub-assembly at the time it is to be sequenced into the launch program. Furthermore, provisions for aborting or terminating the launch after it has been initiated have often been omitted resulting in unnecessary firings with consequent waste of money and equipment.

SUMMARY OF THE INVENTION The present invention is directed to a missile launchcontrol unit or assembly which responds to commands received over an RF. link to initiate a series of launchcontrol events which may (according to the particular missile with which the invention apparatus is used) include engine starting, power transfer, control system check-out, and ignition of the firing means. When the invention system is employed in conjunction with a missile equipped with a JATO unit, the commands so received may incorporate some or all of the following: (1) external power on: (2) external power off; (3) engine start; (4) JATO arm; (5) .lATO fire; (6) engine shutdown; (7) system reset. The external power-on command applies external power to the missile. The external power-off command removes external power from the missile. The engine-start command activates the throttle system, fuel system, starter and igniter system. When these systems are activated, they will start and run the missile engine, monitoring the engines tail pipe temperature and RPM. The engine RPM will increase to a preset launch RPM and transfer to internal generator power. The JATO-arm command activates the JATO fire-command system so it may receive and process a JATO fire command. The .IATO fire command ignites the JATO bottle which launches the missile. The engine-shut-down command will safely shut down the missile engine and safe the JATO firecommand system. After the engine has completely stopped rotating the starter system is reactivated to windmill the engine to cool the engine tail pipe to a safe temperature. The reset command resets the Launch Control Unit so that a restart may be accomplished after a shut-down command has been received.

OBJECTS OF THE INVENTION One object of the present invention is to provide a remote-controlled launch system for missiles.

Another object of the invention is to provide a system for launching a missile through a predetermined sequence of commands transmitted to the missile over an RF. link.

A further object of the invention is to launch a missile by remote control while at the same time providing means for aborting the launch at any time if all prescribed missile operating conditions are not met.

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 a block diagram of a remote-controlled missile launching system designed in accordance with a preferred embodiment of the present invention;

FIG. 2 is a schematic electrical diagram of the power control unit of FIG. 1;

FIG. 3 is a schematic electrical diagram of the temperature-sensing unit of FIG. 1;

FIG. 4 is a schematic electrical diagram of the RPM- sensing unit of FIG. 1;

FIG. 5 is a schematic electrical diagram of the throttle control unit of FIG. 1;

FIG. 6 is a schematic electrical diagram of the starter control unit of FIG. 1;

FIG. 7 is a schematic electrical diagram of the fuel control unit of FIG. 1;

FIG. 8 is a schematic electrical diagram of the launch control command unit of FIG. 1;

FIG. 9 is a schematic electrical diagram of the monitor tmit of FIG. 1;

FIG. 10 is a schematic electrical diagram of an interlock system to be employed in conjunction with the system of FIG. 1; and

FIG. 11 is a schematic electrical diagram of a manual check-out system which may be employed in conjunction with the arrangement of FIG. 8.

DESCRIPTION OF THE PREFERRED EMBODIMENT The remote-controlled launch system of the present disclosure is, in a preferred embodiment, composed of the sub-assemblies or units illustrated in FIG. 1 of the drawings. The system is designed to launch a missile 10 by commands originating at a remote point and picked up by a receiver 12. One arrangement which has proven to be successful in practice is intended to launch a target missile (such, for example, as that known as the Firebee or BQM-34A) from a surface craft on which the invention apparatus is installed. However, the concept herein set forth is obviously adaptable to many different types of missiles which would otherwise present a hazard to personnel in the immediate vicinity of a launch operation.

The basic units (or sub-assemblies) of the invention embodiment set forth in FIG. 1 of the drawings include a unit 14 for sensing the tail pipe temperature of the missile 10, a cooling unit 16, a pre-launch monitor 18, a shut-down unit 20, a command control unit 22, a power control unit 24, an RPM sensing unit 26, a throttle control unit 28, a fuel control unit 30, a starter control unit 32, a monitor 34, a pre-launch control unit 36, a launch control unit 38, and a telemetering unit 40. The details of certain of these units will be set forth hereinafter in connection with a description of FIGS. 2 through 11 of the drawings.

In designing the system of the present concept, it was found that although it was desirable to break up the various functions of the system along the lines set forth in FIG. 1 of the drawings, nevertheless such a physical separation of parts did not lend itself to convenient check-out or troubleshooting in the event of a malfunction. Consequently, it was decided to assemble the various components of the system into modules in the form of circuit boards which could readily be withdrawn from the system for repair and/or replacement of any or all components wired thereon. However, since the manner in which the individual elements of each unit or sub-system are grouped into modules is not necessarily representative of the function of any particular module, the following description will be based primarily upon the interrelationship of the elements making up each unit of FIG. 1. In so doing, however, it is considered necessary to make reference to the modular status of certain parts, especially when such parts are carried on a single module but are included in more than one of the sub-assemblies of FIG. 1. The following table lists by number of modules (designated M) into which all of the components making up the units of FIG. 1 have been assembled, although such grouping is impracticable (and unnecessary) to illustrate in the drawings:

M1 Fuel, throttle, and starter control module M2 Throttle pulser M3 Main fuel control M4 200 temperature detector M5 650 and 760 temperature detector M6 1,000 temperature detector M7 Temperature amplifier M8 90% RPM detector M9 10% RPM detector M10 Engine stabilization and cooling M1 1 33% RPM detector M12 65% RPM detector M13 85% RPM detector M14 88% RPM detector M15 Interlock M16 Command M17 Miscellaneous M18 Pre-start monitor M19 Pre-launch monitor M20 Remote monitor M22 Carrier monitor M24 Automatic/manual selector M27 Power control relays M28 Regulated power supplies M29 100 detector M30 0% RPM detector M32 Over-voltage detector M33 Power control To aid in an understanding of the interrelationship between the units of FIG. 1 and the modules of the foregoing table, the various components of each unit have been designated by the module on which they are carried. For example, component K3303 of FIG. 2 forms part of module M33, while component K801 of FIG. 10 forms part of module M8. In the following description, both units and modules will be referred to as may be appropriate under the circumstances. The prefix K is employed throughout to designate a relay.

P WER CONTROL UNIT The power control unit of FIG. 2 consists of modules M27, M28, M33, terminal strips TB101, TB102, TB103, TB201, TB202 and the starter power relay K13. Module M27 contains three main power relays which direct power to the automatic system, manual system, and to the missile. Module M33 controls the activation of module M27. Module M28 contains two regulated power supplies which provide a positive 18- VDC and a negative l2-VDC. TB101 is a ZOO-amp shunt which all DC input current is routed through. Terminal strip TB 102 and TB103 distribute DC current throughout the system. Terminal strip TB201 and TB202 are ground buses. Starter power relay K13 controls the heavy DC current required by the starter.

Three supply voltages are supplied J 101, J102, and J 104. Each supply voltage will be discussed separately. A 30-vo1t DC source, capable of supplying a lOO-amp surge for 5 seconds and 50 amps continuous, is applied to connector I101. Power is directed from J 101 to TB101. TB101 is a ZOO-amp shunt which operates an ammeter (not shown). TB101 furnishes DC current to contacts on relays K2701, K2702, K2703, K3303 and the master power switch. When the master power is actuated to the manual position, relay K2701 is energized. Relay K2701 furnishes DC current to a manual control to be described below. When the master power switch is actuated to the automatic position, DC current is routed through contacts of K2204 and energizes relay K3303. K3303 directs DC current to TB103 and the l8-VDC regulated power supply of module M28. K3303 also applies control voltage to relay K3302 which has a 2-second energizing delay. When relay K3302 energizes, control voltage is applied to relay K2703. K2703 supplies DC current to TB102. When commanded, relay K1602 energizes to furnish control voltage through the contacts of relay K2401 to the external power relay K2701. Relay K2701 furnishes DC power to the missile. Two external 1 l5-VAC, -cycle, l-arnp sources are used. One primary and one is secondary. They are routed through Jl04 to relay K2704. Relay K2704 supplies the ll5-VAC source to transformer T-l. Transformer T-l steps the l l5-VAC down to 26 VAC and supplies the 26 VAC to relay contacts of K3303. When K3303 is energized, 26 VAC is supplied to the regulated negative l2-VDC power supply located on M28. Receptacle J102 requires an input source of 30 VDC capable of a 1,000-amp surge for 3 seconds and a sustained 600-amp capability for 30 seconds. J 102 supplies DC current to relay K13. Relay K13, when energized, supplies DC current for the missile starter motor. TB102, TB103 and the positive 18 VDC and negative 12 VDC of module M28, supply the current to all systems.

ENGINE CONTROL SYSTEM The engine control system is divided into five subsystems or units, as follows:

a. the tail pipe temperature sensing unit (FIG. 3)

b. the RPM sensing unit (FIG. 4)

c. the throttle control unit (FIG. 5)

d. the starter control unit (FIG. 6)

e. the fuel control unit (FIG. 7) These will now be described in detail:

a. Tail pipe temperature sensing unit The tail pipe temperature sensing unit of FIG. 3 consists of four temperature detectors and two amplifiers. The temperature detectors are modules M4, M5, M6, and M29. The two temperature amplifiers are located on M7. The two temperature amplifiers are connected to the missile engine tail pipe thermocouples. Engine thermocouples produce a DC voltage which is proportional to the engine tail pipe temperature. The DC voltage level produced by the thermocouple is an extremely low voltage and requires amplification. The two amplifiers located on M7 provide this needed amplification. Of the two amplifiers, one amplifies the voltage level corresponding to to 600 centigrade. The second amplifier, amplifies the voltage level corresponding to 400 to l,000. The 0 to 600 amplifier provides a temperature signal to modules M4 and M29. The 400 to l,000 amplifier provides a temperature signal for modules M5 and M6. Module M4 is adjusted to detect a temperature of 200 and energizes K401. M29 detects a temperature of 100 and energizes K2901. Module M5 is adjusted to detect two temperatures, 650 and 760. When a temperature of 760 is detected, relay K501 will energize. K501 will remain energized until the temperature reduces to 650 at which time K501 will de-energize. Module M6 detects a temperature of 1,000 and energizes relay K601. The engine tail pipe thermocouples are connected to a temperature indicator (not shown). The input to module M7 is also connected to the engine thermocouples. The output of M7 is connected to the four temperature detectors, M4, M5, M6 and M29.

b. RPM sensing unit The engine RPM sensing unit of FIG. 4 consists of seven RPM detectors. The seven RPM detectors are modules M8, M9, M11, M12, M13, M14 and M30. The RPM modules are coupled to the output of the missile engine tachometer. The engine tachometer produces an AC voltage and frequency which is proportional to the engine RPM. The RPM module detectors are adjusted to detect specific frequencies. The following is a list of RPM detectors and the adjustment in engine RPM percentages:

a. M8 90% b. M9 10% 0. M11 33% d. M12 65% e. M13 85% f. M14 88% g. M30 0% RPM percentages, and the relays which they operate:

Module Percentages Relay M8 90% K801 M9 10% K901 M11 33% K1101 M12 65% K1201 M13 85% K1301 M14 88% K1401 M30 0% K3002 c. Throttle control unit The throttle control unit of FIG. 5 consists of modules M2, M10, part of M1, and the relay contacts of M4, M5, M8, M9, M12, M13, M14, M16, and M17. When the master power switch is activated to the automatic position, the -second delay timer located on module M1 is activated. The 70-second timer applies a decrease thrust signal to the throttle servo. This function assures that the missile throttle is fully retarded prior .to starting the engine. After a 70-second delay, a signal is sent from the timer to the start interlock circuit. When the start command is applied, DC current is applied to the throttle 4-second timer located on M1 to advance the throttle. When engine RPM reaches 10 percent and the tail pipe temperature reaches 200, DC current is applied to the throttle pulser located on Module M2. The throttle pulser applies DC current to advance the throttle at one second intervals. The throttle continues to advance with pulses until the engine RPM reaches 65 percent RPM. 1n the event the tail pipe temperature exceeds 760, the throttle will cease to increase until the temperature reduces below 650. When the temperature decreases, the throttle will resume pulsing. When the engine RPM reaches 65 percent, the throttle will stop advancing for 30 second. This 30-second period is to allow the engine to stabilize. After the 30-second engine stabilization period, a continuous DC current is applied to advance the throttle until the engine RPM has reaches 85 percent. The continuous throttle action, rather than pulsing the throttle, is to allow the engine to advance as quickly as possible through its critical RPM breathing range of 70 to percent RPM. At percent RPM, the throttle is again pulsed until the engine RPM reaches 89 percent launch RPM. When the shut-down system is activated the throttle is returned to decrease thrust. The throttle shut down system is activated under two conditions: (1) above 65 percent RPM and (2 below 65 percent RPM. If the engine RPM is below 65 percent and a shut down is initiate, a continuous DC current is applied to the decrease thrust. If the engine RPM is above 65 percent a pulsing DC current is applied to the decrease thrust. When the engine RPM reduces to 65 percent the throttle is interrupted for 60 seconds. This 60- second period is to allow the engine tail pipe temperature to cool. After the 60-secor1d delay, the throttle system is reactivated in the same manner as when a shut down is initiated below 65 percent engine RPM. When the master power switch is activated to the automatic position, DC current is applied to K1602, K1605, K1003, K1301 and K1704. DC current is routed through the contacts of K1602 to K101 and the 70- second timer. The contacts of K101 apply current to the coil of K1704. K1704 applies current through its contacts to the missile decrease thrust throttle. When the starter system is activated, K1602 is energized. When K1602 is energized, DC current is removed from K101 and applied to K106 and a 4-second timer. Current is routed through the contacts of K106 to the coil of K1702. When K1702 is energized, current is applied to missile increase thrust throttle. K106 keeps K1702 energized until the 4-second timer energizes K106. After the engine starts and engine RPM reaches 10 percent, K90l is energized. Current is routed from the contacts of K1605 through K1201 and through K901 to K401. When the tail pipe temperature reaches 200, K401 energizes and routes current through K501 to K201 and the multivibrator which activates the coil of K201. The multivibrator switches K201 such that it is I second on and 1.5 seconds off. When K201 is energized, current is applied to K1702 through K202 to increase the throttle position. K501 is controlled by a tail pipe temperature of 650 to 750. When K501 is energized, the current to K201 is interrupted and remains so until K501 de-energizes. At 65 percent RPM, K1201 energizes. When K1201 energizes, current is removed from K901 which removes current from the throttle pulser. At the same time current is removed from K901, current is applied to K1001 and K1003. After a 30-second delay, K1001 energizes and applies current to K201 coil through K1301. Current is also routed to the contacts of K201 through K501. K201 remains energized until K1301 energizes at 85 percent interrupting the current from K1001. When K1301 energizes, current is applied to K1401 and K801-Current from K1401 is applied to K201 and the throttle pulser through K501. At 85 percent RPM, K1401 energizes, removing current from K201. If the engine RPM exceeds 90 percent, K801 will energize and apply current to K201 and the throttle pulser. Current is also applied to K202. When K202 is energized, current is directed to K1704 instead of K1702. K1704 routes current to decrease throttle. K1401 and K801 will position the engine throttle so as to position an engine RPM above 88 percent and below 90 percent. When a shut-down command is activated, K1605 will energize, removing current to the upper sets of contacts and placing it on the lower set of contacts of K1201. If the engine RPM has not yet reached 65 percent, current will be routed through the normally closed contacts of K1003, and the coil of K1704, to decrease thrust. If engine RPM has exceeded 65 percent RPM, K1201 will be energized and current will be routed to K202 coil, the throttle pulser and to the contacts of K201. This will decrease the engine throttle with pulses. When the RPM reduces to 65 percent RPM, K1201 will de-energize, removing current from K202, K201 and the throttle pulser and directing current to K1003. When the engine RPM was above 65 percent, K1003 energized and locked closed the contacts of K1002. When current is applied to K1003, it is directed to a 60-second timer of K1002. After 60 seconds, K1002 energizes and releases the locking current of K1003, de-energizing K1003. When K1003 de-energizes current is directed to K1704 decreasing engine RPM,.

d. Starter control unit The starter control unit of FIG. 6 consists of module M30, parts of M1, and the relay contacts of M6, M11, M15, M16, and M29. Also contained in the starter unit is relay K13. Relay K13 controls the heavy current required by the missile starter. When a start command is initiated, current is directed through the start interlock system and energizes the start command relay. When the start command relay is energized, the missile throttle is advanced for 4 seconds. After the 4-second throttle, the missile fuel pump is activated for 4 seconds. When the fuel pump turns off after 4 seconds, the starter power relay is energized and power is applied to the missile starter. The starter continues to rotate until the engine RPM reaches 33 percent. At 33 percent RPM, the starter power relay is de-energized. In the event the engine fails to start and engine RPM fails to reach 33 percent, a timer limits the maximum time that the starter will be energized. The timer is adjusted for a maximum time of 30 seconds. If, during the starting of the engine, the tailpipe temperature reaches 1,000, the starter power relay will de-energize allowing the engine to be shut down. The starter control system also contains a windmill circuit for cooling the engine tail pipe. This system is activated at any time the tail pipe temperature is in excess of and the engine RPM is at 0 percent. When this condition exists, the starter power relay K13 will energize and remain so for 10 seconds. At the end of 10 seconds K13 will de-energize and allow the engine to stop. When 0 percent RPM is reached again, and the temperature is still in excess of 100, the cooling cycle'will repeat itself. These 10 second cooling cycles continue until thetail pipe temperature reduces below 100. When the master power switch is placed in the automatic position, DC power is applied to the contacts of K1502, K1605, K2901 and K3002. When a start command is initiated, DC power is routed through the contacts of the starter interlock relay K1502 to the start command relay K1602. When K1602 energizes, it locks closed with DC power from K1605 through K1101 and K601. DC power is also routed from K1602 to K102. After a 4-second delay K102 energizes and applies DC power to K103 through the contacts of K106. After another 4-second delay K103 energizes and applies DC power to K13 through the contacts of K105 and K104. K13 applies DC power to the BQM-34A starter. When the engine RPM increases to 33 percent, K1101 releases K1602 locking power. When K1602 releases, K13 de-energizes releasing the power from the missile starter. In the event the tail pipe temperature increases to 1,000, K601 energizes and will also release K1602. If the engine fails to start or the engine RPM does not reach 33 percent within 30 seconds after K13 energizes, K104 will energize interrupting the power to K13 coil. If a shut-down command is initiated while the starter is energized, the power will be interrupted to K1602. During the windmill cycle K2901 is activated whenever the tail pipe temperature is in excess of 100. Power is routed through K2901 to K3001. When the engine RPM reduces to 0 percent, K3001 energizes, applying DC power to energize K3002. When K3002 energizes, it locks closed through K3003 and also applies power to K13 through K104. As the engine begins to rotate K3001 de-energizes breaking the energizing power source to K3002 coil, leaving only the locking power through the contacts of K3003. After the timer (10 seconds) runs out, K3003 energizes, releasing the locking power to K3002. When K3002 de-energizes, power is removed from K13 releasing power from the missile starter. This complete cycle continues until the tail pipe temperature reduces below 100 and releases K2901.

e. Fuel control unit The fuel control unit of FIG. 7 consists of module M3, part of M1, M17, M33, and the relay contacts of M6, M10, M11, and M16. The fuel system is activated by the start command system. When a start command has been initiated, the throttle is advanced for 4 seconds. At the end of the 4-second throttle advance, the fuel pump, located in the missile is activated for 4 seconds. This 4 seconds of fuel time is to pressurize the fuel system to assure an engine light-off. At the end of the 4 seconds of fuel, the engine starter is energized. At the same time that the starter is activated, DC power is applied to the missile ignitor and start fuel valve. 2.2 seconds after the starter has been activated, the fuel pump is again activated and locks on. When a shut down command is initiated, the fuel pump is de-activated shutting the engine fuel off. If the engine tail pipe temperature reaches l,000, the fuel pump will also be shut off. During a normal engine shut down when the missile has been on internal power, the fuel pump will remain on until the engine RPM reduces to a point where the missile low voltage relay cuts off the internal power. When the master power switch is placed in the automatic position, DC power is applied to the contacts of K1602 through K1605, K1101 and K601. Power is also applied to the contacts of K1701, K301 and K3301. When the start command is initiated, K1602 energizes applying DC power to K102. Four seconds after power is applied to K102, K102 energizes, applying power to the coil of K105 through K106 and K103. When K105 energizes, power is applied to the coil of K1701, energizing K1701. When K1701 energizes, power is applied to the fuel pump. Relay K105 remains energized until the 4-second timer of K103 activates. When K103 energizes, K105 de-energizes removing power from K1701, turning the fuel pump off. When K103 energizes and K105 de-energizes, power is applied to the coil of K1706 through K104 and K1101. When K1706 energizes, power is applied to K301 timer. 2.2 seconds after power has been applied to K301 timer K301 energizes and locks on. K301 applies power to K1701 which activates the fuel pump. When K1706 energizes, power is also applied to K3301. K3301 applies power to the missile igniter and the start-fuel valve. When the engine reaches 33 percent RPM, K1101 energizes removing power from K1706. When K1706 de-energizes, K3301 will de-energize removing power from the missile igniter and startfuel valve. A shut-down command (K1605) or over temperature of l,0() (K601) will remove power from K1602. When power is removed from K1602, all power is removed from the fuel control circuit except K301 which may be locked in. This circuit is interrupted by K1004 when K1605 energizes (note FIG. 5).

COMMAND CONTROL SYSTEM The command control system is divided into three sub-systems or units, as follows:

a. launch control command unit (FIG. 8)

b. monitor (FIG. 9)

c. interlock unit (FIG. 10) These will now be described in detail:

a. Launch control command unit The launch control command unit of FIG. 8 consists of modules M16, M22 and M34. These modules receive and process all command signals transmitted to the receiver 12 of FIG. 1. There are a total of seven (7) commands which may be received by the command system: (1) external power on; (2) external power off; (3) engine start; (4) arm; (5) launch; (6) shut down; (7) reset. Also included in this system is a launch control command carrier monitor circuit. The carrier monitor circuit provides a fail-safe condition in the event there is a failure in the command control R.F. carrier link. The external power-on command places external power on the missile. The external power-off command removes external power. The engine-start command activates the missile engine starter, fuel, throttle, and igniter system. These systems, when activated, will start and run the missile engine. The arm command arms the firing circuit to the JATO igniter. The launch command ignites the JATO igniter. The shut-down command shuts the engine off and safes the system to prevent an engine start. The reset command resets the shut-down system so an engine-start command may be processed. The launch control command carrier monitor circuit monitors the command control R.F. carrier. In the event there is a loss of an R.F. carrier for seconds or more, the carrier monitor circuit will activate the shut-down system.

All commands are received through I 103. The external power-on command is received through pin D of J 103 and routed to the coil of K1602. When K1602 is energized it will remain energized with power from the normally-closed contacts of K1601. With K1602 energized, DC power is routed through K1705, K2401 and to the coil of K2701. K2701 applies external power to the ROM-34A. The external power off command is received through pin C of J 103 and routed to the coil of K1601. When K1601 is energized, K1602 will de-energize and remove external power from the missile. The engine-start command is received through pin J of J 103 and is routed through the contacts of K301 and K1502 to the coil of K1603. When K1603 is energized, it activates the engine start system. The arm command is received through pin A of J 103 and power is routed through the contacts of K1503 and K1504 to the coil of K3401. When K3401 is energized it remains energized by power from K1605. The launch command is received through pin B of J 103 and power is routed the contacts of K1505 to the coil of K3402. When K3402 is energized, the short circuit between the two JATO igniter wires are removed and power is applied to one lead and a ground is applied to the other. This completes the circuit for the JATO igniter. The shutdown command is received through pin E of J 103 and power is routed to the coil of K1605. At any time K1605 is energized, a system shut-down will be in effect which safes the console and prevents the missile engine from being started and the JATO igniter from being ignited. The reset command is received through pin G of J 103 and power is routed through two paths. If the engine has not yet been started, power will be routed through the contacts of K2205 and to the coil of K2204. When K2204 is energized, power is interrupted to the coil of K3303 which removes power from the entire system thereby resetting all functions. If the engine has been started, K2205 will be energized and power will then be routed through the contacts of the 10- minute timer relay K2203 and K1605 to the coil of K2204. The reason for the timer is, if the engine has been running and a shut-down is initiated, there will be ample time for the engine to shut down and for the tail pipe temperature to cool off prior to attempting a restart. The carrier monitor signal is received through pin F of J 103 and power is routed to the coil of K2201. Whenever there is a failure of the RF. carrier, the power to K2201 is removed de-energizing K2201. When K2201 is de-energized, power is routed to the timer of K2202. If power remains on the timer for 60 seconds or more K2202 will energize allowing power to be routed to the coil of K1605 initiating a shut-down.

b. Monitor The command control monitor of FIG. 9 consists of module M20 and part of M18. During a remote launch, it is necessary to assure that the missile command control system is functioning properly. This is accomplished by remotely commanding a missile climb, dive, right turn, and left turn. As these commands are received by the missile, module M20 monitors each function as it occurs and locks a relay closed. After all four (4) commands have been detected, a signal is provided to the interlock system to complete that part of the launch interlock circuit. Also included in the missile command control monitor system is a command control carrier monitor. This monitor is located on M18. The carrier monitor will prevent an engine-start command from being received and will initiate the shut-down system if the engine has been started whenever there is a failure in the missile command RF link for 5 seconds or more.

A dive command energizes K2004, a climb command energizes K2003, a left turn energizes K2002, and a right turn energizes K2001. When these relays are energized, they will complete a series circuit and route DC power to the coil of K1504. Relay K1504 is part of the launch interlock system. Whenever there is a loss of command control R.F. carrier, relay K1804 will de-energize, allowing DC power to be routed to K1809. If K1804 remains de-energized for five (5) seconds or more K1809 will energize, interrupting the start command circuit. If the missile engine has been started, DC power will be routed through the contacts of K1101 and to the coil of K1604, initiating a shut down.

c. Interlock unit The command interlock unit of FIG. assures that certain conditions are met prior to allowing commands to be received by the launch control command system. The command interlock system consists of modules M15, M18 and M19. Prior to allowing an engine-start command to be received, there must be external power on the missile, a command carrier must be present, a launch control command carrier must be present, the missile autopilot must be initiated, and the 70-second throttle decrease thrust timer must be timed out. With these conditions being met, a start command may be received and processed. Prior to allowing the arm command to be received, the engine RPM must be between the limits of 88 and 90 percent, the missile must be on internal power, and the missile must have received all four remote checks (climb, dive, left turn and right turn). The arm command may then be received. The launch command may be received at any time after an arm command has been received.

The pre-start monitor completes the circuit for the engine-start command to be received by the command system. When K1801 is energized by the missile external power, DC power is routed through the contacts of K1801 to K1802. The autopilot bus energizes K1802 and DC power is routed to K1809. K1809 is the command control carrier 5-second timer. As long as the command control carrier does not remain off for 5 seconds or more, DC power is routed through K1809 to K1807. K1807 is energized by the throttle second decrease thrust timer. This completes the engine start interlock circuit and DC power is directed to the coil of K1502. When K1502 is energized, the engine start command may be received. The arm interlock consists of relays K1909, K1908, K1504 and K1503. K1908 is energized by the internal power and routes DC power to K1909. K1909 is energized by K801 and K1401. When the engine RPM is above 88 percent and below 90 percent, K801 and K1401 are energized and route DC power to K1909. With K1909 energized DC power is routed to the contacts of K1504. The command control monitor system provides DC power to energize the coil of K1504. When K1504 is energized DC power is routed to the coil of K1503. With K1504 and K1503 energized, the arm command may be received by the command system. When the arm command is received, K1604 is energized and allows DC power to be routed through its contacts and the contacts of K1504 to the coil of K1505. When K1505 is energized, it allows the launch command to be received.

AUTOMATIC MANUAL CONTROL The automatic manual control unit of FIG. 11 provides a set of switches to manually command the same functions as the command control carrier system. There is also a launch control command carrier test switch. The switches are provided so that a complete system test may be accomplished without the need for an RF. transmitter and tone generator.

There is a total of 8 switches in this section of M31. They are as follows: l external power on; (2) external power off; (3) engine start; (4) arm; (5) launch; (6) shut down; (7) reset; and (8) carrier test. All of these switches except the carrier test parallel the functions of the command receiver which enters the console at J 103. The carrier test function energizes relay K3101. K3101 is a 12-VDC relay with a 330-ohm 2-watt resistor in series with the ground lead of the relay coil. When K3101 is momentarily energized, it will remain energized by DC power through its own contacts. The other contacts provide a DC signal which parallels the carrier signal at J 103. Once K3101 is energized, it will remain so until the external power-on command is given either remotely or manually. When external power-on is commanded, K3101 will release.

I claim:

1. In a system designed to launch a JATO-assisted missile from an unmanned area through the medium of commands in the form of electrical signals transmitted from a remote point, the combination of:

means in the vicinity of, but external to, said missile for receiving said commands;

means responsive to the reception of a particular command by said first-mentioned means to electrically connect the engine of said missile to a source of external power;

means responsive to the reception of a subsequent particular command by said first-mentioned means to start the engine of said missile, said means including means for applying a decrease thrust to the throttle for a predetermined period of time prior to starting, and means for pulsing the throttle advance at one second intervals between the approximate maximum RPM limits of to 65 percent and 85 to 90 percent;

means responsive to the reception of a still subsequent particular command by said first-mentioned means to arm the said JATO unit;

means responsive to the reception of a still subsequent particular command by said first-mentioned means to ignite the said JATO unit and thus effect a launch of said missile;

means for monitoring the tail pipe temperature of said missile;

means for monitoring the speed of the said missile engine; and

means for aborting a missile launch at any point in the said command sequence if either or both the missile tail pipe temperature and engine speed as ascertained by said monitoring means lies outside predetermined limits.

2. The combination of claim 1 in which the means for monitoring the speed of the missile engine includes a tachometer designed to produce an AC output the frequency of which is proportional to engine speed, and a plurality of detectors connected to receive the output of said tachometer, each of said detectors being responsive only to a predetermined engine speed as represented by the frequency of the AC input thereto, each of said detectors being designed to respond to an engine speed difi'erent from the speeds to which all of the remaining detectors are responsive.

3. The combination of claim 2 in which said missile is equipped with an internal generator, and means for switching from said source of external power to internal generator power when the speed of said engine reaches a predetermined level as sensed by the particular one of said plurality of detectors which is responsive to engine speed at such level.

Claims

1. In a system designed to launch a JATO-assisted missile from an unmanned area through the medium of commands in the form of electrical signals transmitted from a remote point, the combination of: means in the vicinity of, but external to, said missile for receiving said commands; means responsive to the reception of a particular command by said first-mentioned means to electrically connect the engine of said missile to a source of external power; means responsive to the reception of a subsequent particular command by said first-mentioned means to start the engine of said missile, said means including means for applying a decrease thrust to the throttle for a predetermined period of time prior to starting, and means for pulsing the throttle advance at one second intervals between the approximate maximum RPM limits of 10 to 65 percent and 85 to 90 percent; means responsive to the reception of a still subsequent particular command by said first-mentioned means to arm the said JATO unit; means responsive to the reception of a still subsequent particular command by said first-mentioned means to ignite the said JATO unit and thus effect a launch of said missile; means for monitoring the tail pipe temperature of said missile; means for monitoring the speed of the said missile engine; and means for aborting a missile launch at any point in the said command sequence if either or both the missile tail pipe temperature and engine speed as ascertained by said monitoring means lies outside predetermined limits.

2. The combination of claim 1 in which the means for monitoring the speed of the missile engine includes a tachometer designed to produce an AC output the frequency of which is proportional to engine speed, and a plurality of detectors connected to receive the output of said tachometer, each of said detectors being responsive only to a predetermined engine speed as represented by the frequency of the AC input thereto, each of said detectors being designed to respond to an engine speed different from the speeds to which all of the remaining detectors are responsive.