Abstract
A crowd control projectile includes a payload carrier, an incapacitating agent inside the payload carrier, and an activating mechanism for activating the incapacitating agent. The activating mechanism includes a sensor and a timer. The timer delays the activation until a predetermined delay after the sensor senses that the projectile has been launched. Alternatively, the activating mechanism includes a receiver for receiving an activation signal after the projectile has been launched. Preferably, the projectile has the shape of a clay pigeon. A launcher of such a projectile includes a communication mechanism for transmitting a timing signal or an activation signal to the projectile and an arm for launching the projectile by direct contact. To control a crowd, the projectile is launched over the crowd by direct contact with a solid arm and the activating mechanism is used to activate the incapacitating agent when the projectile is above the crowd.
Claims
1. A system comprising a disk-shaped projectile for dispersing non-lethal incapacitating agents for crowd control, for projection by a mechanical launcher, and a mechanical launcher, wherein the projectile comprises: a sensor for sensing a launch of the disk-shaped projectile from the mechanical launcher; a disk-shaped housing having: a shell including a recess at a top portion thereof, a planar bottom cover, and a payload carrier compartment defined between the shell and the bottom cover that contains a powder irritant agent, a pyrotechnic fuse at least partially seated in a hollow central aperture of the shell; an ignition unit seated within the recess, the ignition unit electrically connected to said pyrotechnic fuse and configured for igniting said pyrotechnic fuse for creating an explosion for at least one of tearing through the bottom cover and disconnecting the bottom cover from the shell to allow dispersing said powder irritant agent in the air as said powder irritant agent falls out of said shell; a timing setting switch for delaying said igniting by a predetermined delay after said launch is detected by said sensor for performing said igniting when said disk-shaped projectile is above a crowd; an antenna located in and electrically connected to said ignition unit and configured to receive a signal from the mechanical launcher encoding said predetermined delay and to transmit a return signal to the mechanical launcher indicating readiness to launch, and processing circuitry configured to transmit the predetermined delay received by the antenna to the timing setting switch; and the mechanical launcher comprises: a second antenna configured to transmit the signal to the disk-shaped projectile encoding said predetermined delay and to receive the return signal from the disk-shaped projectile indicating readiness to launch; and a launching arm having a launching surface directly contacting and moving the disk-shaped projectile prior to and during a launch, and wherein the ignition unit does not contact the launching surface prior to and during a launch; and a fire control unit with an electronic system, wherein the electronic system includes (1) at least one sensor for sensing environmental data comprising one or more of an angle of said launcher, a wind direction, a wind speed, and an ambient temperature; and (2) a processor for calculating the predetermined delay according to the environmental data received by the at least one sensor.
2. The disk-shaped projectile of claim 1, further comprising at least one electric contact for electrically coupling with an electric contact of the mechanical launcher for receiving a signal encoding said predetermined delay.
3. The disk-shaped projectile of claim 1, wherein the projectile lacks a propulsion mechanism.
4. The disk-shaped projectile of claim 1, wherein the projectile has a shape of a clay pigeon.
5. The disk-shaped projectile of claim 1, wherein said powder irritant agent is a riot control agent.
6. The disk-shaped projectile of claim 5, wherein said riot control agent includes an active riot control agent.
7. The disk-shaped projectile of claim 2, wherein said electric contact is located on said bottom cover.
8. The disk-shaped projectile of claim 1, wherein said predetermined delay is set manually by an interface for manual setting.
9. The disk-shaped projectile of claim 1, wherein said sensor senses said launch by sensing an acceleration of the projectile.
10. The disk-shaped projectile of claim 1, wherein said payload carrier compartment comprises a heat generating material.
11. The disk-shaped projectile of claim 1, wherein said ignition unit is placed above said payload carrier compartment in a niche of said shell.
12. The disk-shaped projectile of claim 11, wherein said pyrotechnic fuse is located in said niche.
13. The disk-shaped projectile of claim 1, further comprising contact strips that connect said ignition unit to at least one data contact of said mechanical launcher, the contact strips configured to transfer data between the ignition unit and the mechanical launcher.
14. The disk-shaped projectile of claim 1, wherein said sensor senses said launch by sensing centrifugal force created by the spinning of the disk-shaped projectile.
15. The disk-shaped projectile of claim 14, wherein said sensor comprises springs compressed by said centrifugal force.
16. The disk-shaped projectile of claim 1, wherein said predetermined delay is calculated according environmental data selected from a group consisting of an angle of said launcher, a wind direction, a wind speed, and an ambient temperature.
17. The system of claim 1, wherein the launching arm comprises a planar launching surface for contacting and moving the disk-shaped projectile prior to and during a launch, and wherein the planar bottom cover of the disk-shaped housing contacts the launching surface prior to and during a launch.
18. The system of claim 1, wherein the launching arm comprises an arcuate receptacle for contacting and moving the disk-shaped projectile prior to and during a launch, wherein a lateral surface of the disk-shaped housing contacts the arcuate receptacle prior to and during a launch.
Description
BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWINGS
(1) Various embodiments are herein described, by way of example only, with reference to the accompanying drawings, wherein:
(2) FIG. 1 is a perspective schematic illustration of a prior art manual thrower and a prior art clay target;
(3) FIG. 2 is a side view schematic illustration of a prior art mechanical launcher;
(4) FIG. 3a is a side view schematic illustration of a prior art automatic launcher in its unloaded state;
(5) FIG. 3b is side view schematic illustration of exemplary modified automatic launcher (MAL) of the present invention in its unloaded state;
(6) FIG. 3c is a top view schematic illustration of a contacting surface of an automatic launcher, according to the present invention;
(7) FIG. 4a is a perspective top-side view schematic illustration of a projectile of the present invention;
(8) FIG. 4b is an exploded schematic illustration of a projectile of the present invention;
(9) FIG. 5a is a cross sectional view of the first embodiment of a payload carrier;
(10) FIG. 5b is an exploded schematic illustration of the first embodiment of a payload carrier;
(11) FIG. 6a is a cross sectional view of the second embodiment of a payload carrier;
(12) FIG. 6b is an exploded schematic illustration of the second embodiment of a payload carrier;
(13) FIG. 7a is a cross sectional view of the third embodiment of a payload carrier;
(14) FIG. 7b is an exploded schematic illustration of the third embodiment of a payload carrier;
(15) FIG. 8a is a perspective top-side view schematic illustration of the first embodiment of an ignition unit;
(16) FIG. 8b is a perspective bottom-side view schematic illustration of the first embodiment of an ignition unit;
(17) FIG. 8c is a block diagram of the electronic system of the first exemplary embodiment of an ignition unit;
(18) FIG. 9a is a perspective top-side view schematic illustration of the second embodiment of an ignition unit;
(19) FIG. 9b is a perspective bottom-side view schematic illustration of the second embodiment of an ignition unit;
(20) FIG. 9c is a perspective top-side view schematic illustration of an embodiment of a payload carrier's shell used with the second embodiment of an ignition unit;
(21) FIG. 9d is a block diagram of the electronic system of the second exemplary embodiment of an ignition unit;
(22) FIG. 9e is a cross sectional view of the contact strips that are added to the payload carrier's shell for the second embodiment of an ignition unit;
(23) FIG. 10a is a perspective top-side view schematic illustration of the third embodiment of an ignition unit;
(24) FIG. 10b is a perspective bottom-side view schematic illustration of the third embodiment of an ignition unit;
(25) FIG. 10c is a block diagram of the electronic system of the third exemplary embodiment of an ignition unit;
(26) FIG. 11a is a perspective top-side view schematic illustration of the fourth embodiment of an ignition unit;
(27) FIG. 11b is a perspective bottom-side view schematic illustration of the fourth embodiment of an ignition unit;
(28) FIG. 11c is a block diagram of the electronic system of a fourth exemplary embodiment of an ignition unit;
(29) FIG. 12a is a perspective view of a modified manual thrower (MMT) of the present invention;
(30) FIG. 12b is a block diagram of the electronic system of an exemplary modified manual thrower (MMT) of the present invention;
(31) FIG. 13 is a top-view schematic illustration of the mechanical embodiment of an acceleration sensor;
(32) FIG. 14 is a block diagram of the electronic system of an exemplary modified automatic launcher (MAL) according to the present invention.
DESCRIPTION OF THE PREFERRED EMBODIMENTS
(33) The principles and operation of a crowd control projectile and launcher according to the present invention may be better understood with reference to the drawings and the accompanying description.
(34) Referring again to the drawings, FIG. 3b is side-view schematic illustration of a modified automatic launcher (MAL) 40 in its unloaded state, according to the present invention. MAL 40 is automatic launcher P6 modified according to the principles of the present invention. MAL 40 includes a fire-control unit 41 and is equipped, on launching surface P5, with a contacting surface 40a used by fire-control unit 41 to communicate with the second embodiment of ignition unit 1a (not shown in the present illustration) that is described below, through contact strips 21a (shown in FIG. 9c below) and contacts 21 (shown in FIG. 9b below). Also, MAL 40 is equipped with an antenna 40b which is used by fire-control unit 41 to communicate with the first embodiment of ignition unit 1a (not shown in the present illustration) that is described below and that is equipped with an antenna 20a (shown in FIG. 8a below).
(35) FIG. 3c is a top-view schematic illustration of contacting surface 40a of MAL 40, according to the present invention. Contact surface 40a is equipped with several electrical contacts 42b (see FIG. 14 below) that are used to communicate data with the second embodiment of ignition unit 1a (not shown in the present illustration). Each electrical contact 42b is connected to fire-control unit 41 via a data contact wire 42c. All of the electrical contacts 42b are surrounded by an insulating surface 42a that electrically insulates electrical contacts 42b from each other and from launching surface P8.
(36) FIG. 4a is a perspective top-view schematic illustration of a projectile 1 of the present invention.
(37) The overall shape and size of projectile 1 is that of the kind of generally disk-shaped or inverted-saucer-shaped clay target that is commonly used in sports such as skeet shooting and trap shooting and that commonly is referred to generically as a clay pigeon. The standard size of such targets is 110 mm overall diameter and 25-26 mm thickness for international competition and 108 mm overall diameter and 28-29 mm thickness for American competition. There also are specialized targets such as battue targets that are thinner than the standard targets and rabbit targets that are thicker than the standard targets. So-called midi targets have a diameter of about 90 mm. So-called mini targets have a diameter of about 60 mm and a thickness of about 20 mm.
(38) FIG. 4b is an exploded schematic illustration of projectile 1 showing that projectile 1 includes a payload carrier 1b and an ignition unit 1a. Four different preferred embodiments of ignition unit 1a are described below. Three different embodiments of payload carrier 1b are described below.
(39) FIG. 5a is cross sectional view of the first embodiment of payload carrier 1b. This embodiment of payload carrier 1b includes as its payload a passive payload such as powder or liquid.
(40) FIG. 5b is an exploded schematic illustration of the first embodiment of payload carrier 1b. This embodiment of payload carrier 1b includes a payload shell 5, a pyrotechnic fuse 6, a passive payload 7 and a passive payload bottom cover 8.
(41) According to the present invention all types of ignition unit 1a described below can be installed in the recess 9 on the top surface of a first embodiment 1b of a payload carrier. Pyrotechnic fuse 6 is located between the pyrotechnic fuse nest 20m in the bottom of an ignition unit 1a (not shown in the present figure) and passive payload 7, through a hole 5a in shell 5. Pyrotechnic fuse 6 is ignited by the ignition unit 1a. After its ignition, pyrotechnic fuse 6 creates an explosion that tears through the bottom cover 8 and/or disconnects bottom cover 8 from shell 5. Then, passive payload 7 is dispersed in the air as passive payload 7 falls out of shell 5.
(42) FIG. 6a is cross sectional view of the second embodiment of a payload carrier 1b. This embodiment of the payload carrier 1b includes as its payload an active payload that produces an irritant material such as smoke or tear gas.
(43) FIG. 6b is an exploded schematic illustration of the second embodiment of payload carrier 1b. This embodiment of payload carrier 1b includes a payload shell 5, a pyrotechnic fuse 6, a secondary payload canister 10, an igniter washer 13, an active payload 11 and an active payload bottom cover 14.
(44) According to the present invention all types of ignition unit 1a described below can be installed in the recess 9 on the top surface of second embodiment 1b of a payload carrier. Pyrotechnic fuse 6 is located between the pyrotechnic fuse nest 20m in the bottom of an ignition unit 1a (not shown in the present figure) and igniter washer 13, through hole 5a in shell 5 and hole 10c in secondary payload canister 10. Ignition unit 1a ignites pyrotechnic fuse 6, which in turn ignites igniter washer 13. The burning of igniter washer 13 along the surface of active payload 11 produces an irritant agent. One example of active payload 11 is a mixture of a lachrymator such as CS or CN and a heat generating material such as smokeless powder. Combustion of the heat generating material vaporizes the lachrymator. The irritant agent thus produced is concentrated within an open space 12. The irritant agent, being hot and pressurized, tears membranes 10b and is dispersed in the air through holes 10a in secondary payload canister 10 and holes 5b in shell 5.
(45) FIG. 7a is cross sectional view of the third embodiment of payload carrier 1b. This embodiment of payload carrier 1b includes as its payload an explosive charge that creates a loud noise accompanied by a blinding flash of light, in the manner of a stun grenade.
(46) FIG. 7b is an exploded schematic illustration of the third embodiment of payload carrier 1b. This embodiment of payload carrier 1b includes a payload shell 5, a pyrotechnic fuse 6, a secondary payload canister 10, an explosive charge 16 and an explosive charge bottom cover 17.
(47) According to the present invention all types of ignition unit 1a described below can be installed in the recess 9 on the top surface of the third embodiment of payload carrier 1b. Pyrotechnic fuse 6 is located between the pyrotechnic fuse nest 20m in the bottom of ignition unit 1a (not shown in the present figure) and explosive charge 16, through a hole 5a in shell 5 and hole 10c in secondary payload canister 10. Ignition unit 1a ignites pyrotechnic fuse 6, which in turn ignites explosive charge 16. The explosion of explosive charge 16 produces a loud noise accompanied by a temporarily blinding flash.
(48) FIG. 8a is a perspective top-view schematic illustration of a first embodiment of ignition unit 1a.
(49) FIG. 8b is a perspective bottom-view schematic illustration of the first embodiment of ignition unit 1a.
(50) FIG. 8c is a block diagram of the electronic system of the first exemplary embodiment of ignition unit 1a. The launching of a projectile 1 that includes this embodiment of ignition unit 1a preferably is done using a modified manual thrower (MMT) (described below with reference to FIGS. 12A and 12B), a modified mechanical launcher (MML) (described below with reference to FIG. 14) or a modified automatic launcher (MAL) (described above with reference to FIG. 3b and below with reference to FIG. 14). The electronic system of the first exemplary embodiment of ignition unit 1a includes a power source 20d, which supplies power through an activation button 20c that is operatively connected to an antenna 20a, a data transmitter 20e, a data receiver 20f, a power source tester 20g, an acceleration sensor 20h and a micro-switch 20j. A data processor 20i receives data from data receiver 20f, from the power source tester 20g and from the acceleration sensor 20h, and outputs data to a LED light 20b, to micro-switch 20j and to data transmitter 20e. Data transmitter 20e outputs data it gets from activation button 20c and from data processor 20i to antenna 20a for transmission to a fire control unit such as fire control unit 24b of FIG. 12a below or fire control unit 41 of FIG. 3b above and FIG. 14 below. Micro-switch 20j receives data from data processor 20i and from activation button 20c and outputs a direct current (DC) voltage to a DC/DC converter 20k which converts the received DC voltage to a level suitable for ignition of pyrotechnic fuse 6 of payload carrier 1b (not shown in this figure) in contact with a pyrotechnic fuse nest 20m.
(51) Upon system startup using activation button 20c, power source tester 20g informs data processor 20i when the power source 20d voltage level is suitable for operation of ignition unit 1a and data processor 20i then lights up LED light 20b. Data processor 20i then receives required data (such as detonation command, delay time, identification number, etc.) via wireless transmission from fire-control unit 24b or 41 (not shown in the present figure) via antenna 20a and data receiver 20f, and then signals a ready signal back through data transmitter 20e and antenna 20a, or by signaling with LED light 20b. When projectile 1 is launched, acceleration sensor 20h senses the launch and signals to the data processor 20i that projectile 1 has been launched. Upon receiving the launch indication from acceleration sensor 20h, data processor 20i starts to count down the delay time received before launch or waits for a detonation command, after which, data processor 20i signals micro-switch 20j to pass the required DC voltage to pyrotechnic fuse nest 20m via DC/DC converter 20k, thereby detonating pyrotechnic fuse 6 (not shown in present figure).
(52) FIG. 9a is a perspective top view schematic illustration of a second embodiment of ignition unit 1a.
(53) FIG. 9b is a perspective bottom view schematic illustration of the second embodiment of an ignition unit 1a.
(54) FIG. 9c is a perspective top view schematic illustration of the payload's shell 5 required for use with the second embodiment of an ignition unit 1a.
(55) FIG. 9d is a block diagram of the electronic system of the second exemplary embodiment of an ignition unit 1a. The launching of a projectile 1 that includes this embodiment of ignition unit 1a should be done by modified manual thrower (MMT) (FIG. 12a), modified mechanical launcher (MML) or modified automatic launcher (MAL) (FIG. 3b). The electronic system of the second exemplary embodiment of an ignition unit 1a includes a power source 20d, which supplies power through an activation button 20c that is operatively connected to a data transmitter 20e, a data receiver 20f, a power source tester 20g, an acceleration sensor 20h and a micro-switch 20j. A data processor 20i receives data from data receiver 20f, power source tester 20g and acceleration sensor 20h and outputs data to a LED light 20b, to micro-switch 20j and to data transmitter 20e. Data transmitter 20e outputs data it gets from activation button 20c and from data processor 20i to the ignition unit's contacts to fire-control unit 21. Micro-switch 20j receives data from data processor 20i and from activation button 20c and outputs a direct current (DC) voltage to a DC/DC converter 20k which converts this DC voltage to a level suitable for ignition of pyrotechnic fuse 6 (not shown in this figure) connected to pyrotechnic fuse nest 20m.
(56) Upon system startup using activation button 20c, power source tester 20g informs data processor 20i when the power source 20d voltage level is suitable and data processor 20i lights up LED light 20b. Data processor 20i then receives required data (such as a delay time, an identification number, etc.) via wire transmission from the electrically contacting surface 40a of an automatic launcher's fire-control unit 41 (not shown in the present figure), from the similar fire-control unit of a mechanical launcher, or from the data contacts 21a of an MMT's fire-control unit 24b (not shown in the present figure) via data receiver 20f, the ignition unit's contacts to fire-control unit 21, and contact strips 21a that connect between the ignition unit and data contacts 24a of MMT 24 or contacting surface 40a of FIG. 3C. Then, data processor 20i signals a ready signal back through data transmitter 20e or by signaling with LED light 20b. When projectile 1 is launched, acceleration sensor 20h senses the launch and signals to data processor 20i that projectile 1 has been launched. Upon receiving the launch indication from acceleration sensor 20h, data processor 20i starts to count down the delay time received before launch. At the end of the countdown, data processor 20i signals micro-switch 20j to pass the DC voltage to pyrotechnic fuse nest 20m via DC/DC converter 20k, thereby detonating pyrotechnic fuse 6 (not shown in present figure).
(57) FIG. 9e is a cross sectional view of the contact strips 21a that are added to the payload carrier's shell 5 for use with the second embodiment of an ignition unit 1b. Contact strips 21a, mounted on the payload carrier's shell 5 as is shown in FIG. 9c, connect between the second embodiment of an ignition unit 1b (not shown in present figure) and data contacts 24a of an MMT (shown in FIG. 12a) or contacting surface 40a of an MAL or MML (shown in FIG. 3c). The ignition unit's contacts to fire-control unit 21 (shown in FIG. 9b) are connected, during the manufacturing process, to the surfaces 21b of the contact strips 21a. Surfaces 21c of contact strips 21a are in contact with data contacts 24a of an MMT (shown in FIG. 12a) or contacting surface 40a of a MAL or MML (shown in FIG. 3c) when projectile 1 is loaded into the MMT or onto the MAL or MML for launch.
(58) FIG. 10a is a perspective top view schematic illustration of a third embodiment of ignition unit 1a.
(59) FIG. 10b is a perspective bottom view schematic illustration of the third embodiment of ignition unit 1a.
(60) FIG. 10c is a block diagram of the electronic system of the third exemplary embodiment of ignition unit 1a. The launching of a projectile 1 that includes this embodiment of ignition unit 1a can be done by a modified manual thrower (MMT), by a modified mechanical launcher (MML), by a modified automatic launcher (MAL) or by any prior art thrower/launcher. The electronic system of the third exemplary embodiment of ignition unit 1a includes a power source 20d, which supplies power through an activation button 20c that is operatively connected to a timing setting switch 22, to a power source tester 20g, to an acceleration sensor 20h and to a micro-switch 20j. A data processor 20i receives data from timing setting switch 22, from power source tester 20g and from the acceleration sensor 20h and outputs data to a LED light 20b and to a micro-switch 20j. Micro-switch 20j receives data from data processor 20i and from activation button 20c and outputs a direct current (DC) voltage to a DC/DC converter 20k that converts this DC voltage to a level suitable for ignition of pyrotechnic fuse 6 (not shown in this figure) connected to pyrotechnic fuse nest 20m.
(61) Upon system startup using activation button 20c, power source tester 20g informs data processor 20i when the power source 20d voltage level is suitable and data processor 20i lights up LED light 20b. Data processor 20i then receives a delay time from timing setting switch 22. Then, data processor 20i signals a ready signal back by signaling with LED light 20b. When projectile 1 is launched, acceleration sensor 20h senses the launch and signals to data processor 20i that projectile 1 has been launched. Upon receiving the launch indication from acceleration sensor 20h, data processor 20i starts to count down the delay time received before launch. At the end of the count down, data processor 20i signals micro-switch 20j to pass the DC voltage to pyrotechnic fuse nest 20m via DC/DC converter 20k, thereby detonating pyrotechnic fuse 6 (not shown in present figure).
(62) FIG. 11a is a perspective top view schematic illustration of a fourth embodiment of ignition unit 1a.
(63) FIG. 11b is a perspective bottom view schematic illustration of the forth embodiment of ignition unit 1a.
(64) FIG. 11c is a block diagram of the electronic system of the fourth exemplary embodiment of ignition unit 1a. The launching of a projectile 1 that includes this embodiment of ignition unit 1a can be done by a modified manual thrower (MMT), by a modified mechanical launcher (MML), by a modified automatic launcher (MAL) or by any prior art thrower/launcher. The electronic system of the fourth exemplary embodiment of ignition unit 1a includes a power source 20d, which supplies power through an activation button 20c that is operatively connected to a power source tester 20g, to an acceleration sensor 20h and to a micro-switch 20j. A data processor 20i has a default delay time programmed therein by the manufacturer of ignition unit 1a and receives data from power source tester 20g and from acceleration sensor 20h, and outputs data to a LED light 20b and to micro-switch 20j. Micro-switch 20j receives data from data processor 20i and from activation button 20c and outputs a direct current (DC) voltage to a DC/DC converter 20k that converts this DC voltage to a level suitable for ignition of pyrotechnic fuse 6 (not shown in this figure) connected to pyrotechnic fuse nest 20m.
(65) Upon system startup using activation button 20c, power source tester 20g informs data processor 20i when the power source 20d voltage level is suitable, and data processor 20i lights up LED light 20b. Then, data processor 20i signals a ready signal back by signaling with LED light 20b. When projectile 1 is launched, acceleration sensor 20h senses the launch and signals to data processor 20i that projectile 1 has been launched. Upon receiving the launch indication from acceleration sensor 20h, data processor 20i starts to count down the default delay time that has been programmed by the manufacturer. At the end of the countdown, data processor 20i signals micro-switch 20j to pass the DC voltage to pyrotechnic fuse nest 20m via DC/DC converter 20k, thereby detonating pyrotechnic fuse 6 (not shown in present figure).
(66) FIG. 12a is a perspective view of a modified manual thrower (MMT) 24. MMT 24 includes a fire-control unit 24b, data contacts 24a of a fire-control unit 24b, an antenna 24c of fire-control unit 24b, a screen 24d of fire-control unit 24b, a fire button/timing setting switch 24e of fire-control unit 24b, an on/off switch 24f of fire-control unit 24b, a mode switch 24h of fire control unit 24b, and a body 24g that terminates in a launch receptacle 24i in which data contacts 24a are embedded. Payloads 1 are loaded into receptacle 24i for launching. A payload 1, whose ignition unit 1a is the second embodiment of ignition unit 1a, is loaded into receptacle 24i for launching so that contact strips 21a make electrical contact with data contacts 24a.
(67) FIG. 12b is a block diagram of the electronic system of the fire control unit 24b of MMT 24. The electronic system of fire control unit 24b includes a power source 24i, which supplies power through an on/off switch of fire-control unit 24f, that is operatively connected to an antenna 24c, to a data receiver 24j, to a data transmitter 24k, to a fire button/timing setting switch 24e of fire-control unit 24b, a screen 24d, and a data processor 24m. Mode switch 24h is connected to data transmitter 24k and to data receiver 24j and directs data to/from antenna 24c or data contacts 24a according to the embodiment (first or second) of the ignition unit 1a that is installed in a launched projectile 1. If the embodiment of ignition unit 1a is the first embodiment of ignition unit 1a, then mode switch 24h directs data to/from antenna 24c. If the embodiment of ignition unit 1a is the second embodiment of ignition unit 1a, then mode switch 24h directs data to/from data contacts 24a. Fire button/timing setting switch 24e has two optional functions: to set the delay time for the first and second embodiments of ignition units 1a and to issue the detonation command for the first embodiment of ignition unit 1a. Data processor 24m receives data from on/off switch 24f, from fire button/timing setting switch 24e and from data receiver 24j and outputs data to screen 24d and to data transmitter 24k.
(68) Upon system startup using on/off switch 24f, the user sets mode switch 24h and fire button/timing setting switch 24e according to the type of ignition units 1a in use. Data processor 24m receives data from fire button/timing setting switch 24e and transfers the data via data transmitter 24k and mode switch 24h, which directs the data via antenna 24c or via data contacts 24a to ignition unit 1a. The data received from ignition unit 1a is directed by mode switch 24h to data receiver 24j and then to data processor 24m. Information received by data processor 24m is displayed on screen 24d.
(69) FIG. 13 is a top view schematic illustration of a mechanical embodiment of an acceleration sensor 20h. This embodiment of acceleration sensor 20h includes arm members 25a, springs 25b, first accelerometer contacts 25c, second accelerometer contacts 25d and an external member 25e.
(70) After the launching of a projectile 1, the centrifugal force created by the spinning of projectile 1 compresses springs 25b that are placed between arm members 25a and external member 25e. As a result, first accelerometer contacts 25c touch second accelerometer contacts 25d, and acceleration sensor 20h outputs a signal to data processor 20i (not shown in this figure) to inform data processor 20i that projectile 1 has been launched.
(71) FIG. 14 is a block diagram of the electronic system of fire control unit 41 of a MAL. The electronic system of fire control unit 41 includes a power source 41a, which supplies power through an on/off switch 41b, that is operatively connected to antenna 40b, to a data receiver 41f, to a data transmitter 41c, to sensors 41d, to an input keyboard 41e, to a screen 41m, and to data processor 41k. Mode switch 41j is connected to data transmitter 41c and to data receiver 41f and directs data to/from antenna 40b or electrical contacts 42b according to which embodiment of ignition unit 1a is installed in the launched projectiles 1. If the embodiment of ignition unit 1a that is installed in projectiles 1 is the first embodiment of ignition unit 1a, then mode switch 41j directs data to/from antenna 40b. If the embodiment of ignition unit 1a that is installed in projectiles 1 is the second embodiment of ignition unit 1a, then mode switch 41j directs data to/from electrical contacts 42b. Input keyboard 41e is used to input different required data, such as a delay time for the first and second embodiments of ignition units 1a; the immediate detonation command for the first embodiment of ignition unit 1a; the number of projectiles to launch; the direction of fire, etc. Sensors 41d collect environmental data such as the angle of the launcher, the wind direction and speed, and/or the ambient temperature, and output the environmental data to data processor 41k. Data processor 41k receives data from on/off switch 41b, from input keyboard 41e, from sensors 41d and from data receiver 41f, and outputs data to screen 41m, to data transmitter 41c and to the motors and the launching button of MAL 40, which are placed in the main body of the MAL (not shown in this figure).
(72) Upon system startup using on/off switch 41b, the user sets mode switch 41j and uses input keyboard 41e to input all required data. Data processor 41k receives data from input keyboard 41e and transfers the received data via data transmitter 41c and mode switch 41j, which directs the data to antenna 40b or to electrical contacts 42b. Data received from the ignition unit 1a of a projectile 1 that is to be launched is directed by mode switch 41j to data receiver 41f and then to data processor 41k. Data received from sensors 41d and from input keyboard 41e is transferred by data processor 41k to the MAL's motors and launching button. Information received by processor 41k is displayed on screen 41m.
(73) Prior art mechanical launcher P3 of FIG. 2 is modified to be a MML of the present invention in a manner similar to how prior art automatic launcher P6 of FIG. 3a is transformed into MAL 40 of the present invention. The description above of MAL 40 applies, mutatis mutandis, to a MML of the present invention. In particular, the description above of the structure and use of fire control unit 41 applies, mutatis mutandis, to the fire control unit of a MML of the present invention.
(74) While the invention has been described with respect to a limited number of embodiments, it will be appreciated that many variations, modifications and other applications of the invention may be made. Therefore, the claimed invention as recited in the claims that follow is not limited to the embodiments described herein.
