CA2046788A1 - Launcher control system - Google Patents
Launcher control systemInfo
- Publication number
- CA2046788A1 CA2046788A1 CA002046788A CA2046788A CA2046788A1 CA 2046788 A1 CA2046788 A1 CA 2046788A1 CA 002046788 A CA002046788 A CA 002046788A CA 2046788 A CA2046788 A CA 2046788A CA 2046788 A1 CA2046788 A1 CA 2046788A1
- Authority
- CA
- Canada
- Prior art keywords
- airborne vehicle
- interface means
- launcher
- power
- guidance
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41G—WEAPON SIGHTS; AIMING
- F41G7/00—Direction control systems for self-propelled missiles
- F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
- F41G7/30—Command link guidance systems
- F41G7/301—Details
- F41G7/306—Details for transmitting guidance signals
Abstract
LAUNCHER CONTROL SYSTEM
ABSTRACT OF THE DISCLOSURE
In a weapon system 10 incorporating a target position sensor (14), an information system (16), a power source (22), a launcher (20), and an airborne vehicle (18), a launcher control system (12) which incorporates a communications interface (26) for coupling the information system (16) and the target position sensor (14) to a launcher (20) and an airborne vehicle (18). The communications interface (26) receives target position information and launch and control orders and provides launcher and airborne vehicle status. A airborne vehicle interface (28) couples the launcher (20) and the airborne vehicle (18) to the information system (16) and a power source (22). A transmitter (30) communicates updated target position information to the airborne vehicle after launch. A power control unit (32) converts and regulates power from different power sources (22) to be used by the launcher control system (12). The launcher (20) with launcher control system (12) is preferably modular in construction and is separate from the information system (16) and target position sensor (14).
ABSTRACT OF THE DISCLOSURE
In a weapon system 10 incorporating a target position sensor (14), an information system (16), a power source (22), a launcher (20), and an airborne vehicle (18), a launcher control system (12) which incorporates a communications interface (26) for coupling the information system (16) and the target position sensor (14) to a launcher (20) and an airborne vehicle (18). The communications interface (26) receives target position information and launch and control orders and provides launcher and airborne vehicle status. A airborne vehicle interface (28) couples the launcher (20) and the airborne vehicle (18) to the information system (16) and a power source (22). A transmitter (30) communicates updated target position information to the airborne vehicle after launch. A power control unit (32) converts and regulates power from different power sources (22) to be used by the launcher control system (12). The launcher (20) with launcher control system (12) is preferably modular in construction and is separate from the information system (16) and target position sensor (14).
Description
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LA~NCHER CONTROL SYSTEM
CROSS REFERENCE TO REL~TED APPLICATIONS
This application i5 a continuation-in-part of U.
S. Serial No. 07/447,320 ~iled Decembar 7, 1989 which is hereby incorporated by referenceO
BACKGROUND OF THE INVENTION
1. Technical Field The present invention relates to missile launchers and, more specifically, ~o a launcher control system for controlling the launch and flight of an airborne vehicle.
LA~NCHER CONTROL SYSTEM
CROSS REFERENCE TO REL~TED APPLICATIONS
This application i5 a continuation-in-part of U.
S. Serial No. 07/447,320 ~iled Decembar 7, 1989 which is hereby incorporated by referenceO
BACKGROUND OF THE INVENTION
1. Technical Field The present invention relates to missile launchers and, more specifically, ~o a launcher control system for controlling the launch and flight of an airborne vehicle.
2 Discus ' slon The purpose o~ a launchiny system is to place a weapon into a ~light path as rapidly as required.
~aunching systems must perform with speed and reliability while displaying wPapon system compakibilityO However, system flexibility and performanc~ is o~ten limited by the de~ign lim.itation of the launcher system to a speci~ic environment, such as ground-to-air, ship-to-air, etc.
:
SUMMARY OF_THE INVENTION
It is an object of the present invention to provide a standard launcher control system that can be employed in a mulkitude of environments, thereby expanding the use~ul environment of the weapon being deployed. In the pre~erred embodiment, the ~ystem i~ designed to . .
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control the launch and flight of what was ori~inally d~signed exclusively to be an air-to air missile, the ~dvanced Medium Range Radar ~ir-to-~ir Missile (AMRAAM), although other embodiments envision this same concept being applied to any type of active rad2lr guided airborne vehicle.
In accordance with the teachinqs of the present in~ention, a ~ystem for controlling the launch and flight of an airborne vehicle, is provided. The lalmcher control system is modular in construction, employing standard equipment, and is easily deployable in a variety of environments. It employs a communications inter~ace for receiving target position information and launch control ord~rs, and ~or providing launcher and airborne vehicle status information to an information system. An airborne vehicle interface couples the launcher control system to the launcher and airborne vehicleO The airborne vehicle interfac~ pro~ides power to the airborne vehicle for launch and data and control signal~ to test and launch the airborne vehicle, and d~te~minss the status of the airborne vehicle prior to launch. A transmitter for communicating updated target information to the airborne vehicle while in flight is also provided. Finally, the system employs a power converter ~or converting various forms of input power to power ~orms required by the launcher control system componentsO Regulation of system input power and overload protection for all ~ystem components is also provided.
BRIEF DESCRIPTION~OY TH~3 DRAWINGS
Other objects and advantages of the invention will become appar~nt upon r~ading the following detailed description and upon reference to the drawings, in which.
FIG~ 1 is a schematic diagram o~ a weapon syskem incorporating the launcher control system;
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FIG. 2 is a block diagram of the launcher control system; and FIG. 3 is a block diagram of a sp~cific embodiment of the launcher ~ontrol sy~tem.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT
Turning fir~t to the weapon system 10 of FIG. 1, target position in~ormation is ~ontinuollsly obtained by a sensor 14, such as a radar system. This position information is processed by the information syst2m 16, commonly referred to as the Communication, Command, and Control (C3) System, which generates position control signals for prelaunch testing and flight control of the airborne vehicle 18, such as a missile. Briefly, the C3 Sy~tem is a combination of computer and communications technology and people. The communications technology collects and disseminates information, the computer technology processes the information, and people make decisions based on the in~ormation. The information system 16 is coupled to the launcher control system 12, which processes the position information and sends it to the airborn~ vehicle 18. Before launch, the airborne vehicle 18 recei~es position information and control signals through the launcher 20. In flight, the launcher control system transmits updated target position information to the airborne vehicle 18. The launcher control ~ystem 12 also monitors the prelaunch status of both the launchex 20 and the airborne ~ehicls 18 and relays the status information ~ack to the information system 16. Power ~or operating the launcher control system 12 and ~or activating the airborne vehicle 18 during prelaunch checkout comes from pow~r source 22~
FIG. 2 illust~ates the ~asic components of the launcher control system 12. The launcher control system 12 provides a standard communicakions interface 26 which allows for communication, launch, and guidance of the : . .
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missile from any information system 16 which has this ~tandard interface. The communications interface 26 performs the interface function for target position information from the target sensor 14, and for launch and contxol orders from khe information system 16. The communications inter~ace 26 also prov:ides launcher and airborne vehicle status back to the information system 16 prior to airborne vehicle launch.
The launcher control system 12 communicates with the airborne vehicle 18 in two ways. Prior to launch, the airborne vahicle inter~ace 28 is used. In one embodiment, in which the airborne vehicle 18 is a missile, the commercially available MI~-STD 1760 interface advantageously allows the use o~ standaxd unmodified production misæiles. The airborne vehicle interface 28 provides target position information and control signals for test and launch of the airborne vehicle 18 and provides power ~or airborne vehicle activation during the prelaunch checkout. It also determines the status of the airborne vehicle lB.
During flight, the launcher control system 12 communicates with the airborne vehicle 18 through a radio frequency (RF) data link transmitter 30. Target position information ~rom the communications interface 26 is transmitted to the airborne vehicl2. The launcher control system 12 provides 360~ of data link coverage so that multiple simultaneous missile engageme~t~ can be managed over this full range.
The power control 32 supplies power to the communications interface 26, thP transmitter 30, the airborne vehicle interface 28, the launcher 20, and the airborne vehicle 18. It converts available system power from the power source 22 to power forms xequired by these launch control system components. In addition, the power control 32 regulates launcher control system power and , $
, provides overload protection for all launcher control system components.
Turning now to FIG. 3, there is shown a more detailed embodimenk of the launcher control system 12.
Data link equipment 34 contains a frequency refer2nce unit 36, a transmitter 30, and a load control switch ~0. The frequency referencP. unit 36 is a variable frequency generator which produces a band of freguencies within the X-band of the electromagnetic spectrum. Frequency changes are made in fixed steps or intervalsO Since it is capable of generating dif~erent frequencies, the frequency reference unit is less susceptible to jamming.
Transmitter 30 transmits the output signal from the ~requency reference unit 36. It contains a travelling wave tube amplifier for amplifying the X-band electromagnetic signal.
The load control switch 40 directs the output of the transmitter 30 to the antenna 44 or a dummy load 46.
The dummy load 46 is provided to allow for field tests of the data link equipment 3~ without danger of spurious microwave radiation. ~`
The antenna 44 employs four antenna subsystems each covering a 90 degree swath about the center of the antenna 44. Advantageously, thP data link equipment 34 illuminates only the 90 swath in which the airborne vehicle 18 ts be updated is located, thereby reducing spurious emissions. The antenna 44 is less susceptibl~ to detection by un~riendly forces and the radiation from the antenna is less lik~ly to interfere with other friendly radiation sources in the area. Additionally, only one-fourth the transmitter power is required~
~ he airborn~ vehicle interface 28 provides a variety of control functions throughout the launcher control system 12. It ~mploys a primary inter~ace unit 29 within the housing 24 which implements frequency ~hange orders to the frequency reference unit 36, monitors the , .
2 ~ 8 8 frequency refer~nce unit 36 for fre~uency drift, and performs a built-in test of frequency referenc~ unit functions. It signals ths transmitter 30 to transmit a pulse code to the airborne vehicle 18, monitors the output power of the transmitted pulse wave~orm, monitors the transmitter 30 for failure, and performs a built-in t~st function. It selects the antenna subsys~em to be illumina~ed by the data link equipment 34. Finally, it implPments a built in test function for the horizontal reference unit 50.
A horizontal reference unit 50 is a subsystem of the airborne vehicle interface 28 located outside the housing 24 in this embodimen~ which measures the inclination of the launcher rotating platform. P:itch and roll information is sent via the primary inkerface unit 29 to the information system 16 where it is combined with the known global position of the launcher 20. I'his information about the orientation and position o~ the launcher rotating platform is important for missile targeting when using a remotely located targeting sensor 14.
Instrumentation system 54 is a subsystem of the airborne vehicl2 interface 28. It too is located outside the housing 24 in this embodiment. It is a data collection system used to monitor operation of the airborne vehicle interface 28.
The airborne vehicle interface 28 is coupled to the information system 16 through tha communications interface 26 t which employs o~e or more standard serial.
communi~ations i~terface units and one or more discrete signal communications interface units. In this embodiment the standard communications interface is the RS-422. A
multiplicity of communications interfaces provid~s safety and reliability, as control ~unctions are separated from communications function~O
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The airborne vehicle interface 2~ communicates with the launcher 20 through a series of interfaces. A
standard di~ferential serial interface 1533 is used as well as several discrete interfaces. This multiplicity of intarfaces also insures safety and reliability~
The power distribution unit 32 provide~ 28 volt DC power to the data link equipment 34 and the airborne vehicle interface 28. It receives three-phase 400 Hertz power from power ~ource 22, Three-phase 400 Hert2 power is also sent to the airborne vehicle interface 28. Three-phase power and 2~ volt DC power are sent to the launcher 20 via the airborne vehicle interface 28.
Within the information system 16 there is a launcher control unit 52. The launcher control unit 5~
implements the firing orders oE the operator and implements self-test ~unctions for the airborne v~hicle interface 28. It also relays targeting information to the airborne vehicle interface 28~
The launcher 20 with the launcher control system 12 is normally located apart from the information system 16 a~d target sensor 14, t~ereby making the launcher ~0 and the airborne vehicle 18 less vulnerable to destruction by enemy ~orces. It has a housing 24 and is modular in design, thereby facilitating repair and replacement of components. Because .it is a standard interface box, the launcher control system 12 is capable of bei~g used to control an airborne vehicle 18, such as the ~MRAAM, in many other environments besidas air-to-air. Finally, many such launcher control systems are capable of being linked to a common information system 16 to allow the simultaneous launch of multiple airborne vehicles, such as active radar missiles of the A~RAAM type. These advantages over the prior art are readily apparent to one skillQd in the art.
Although the inYention has been described with particular reference to certain preferred embodiments .
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thereof, variations and modi~Eications can be effected within the ~pirit and scope of the following claims.
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~aunching systems must perform with speed and reliability while displaying wPapon system compakibilityO However, system flexibility and performanc~ is o~ten limited by the de~ign lim.itation of the launcher system to a speci~ic environment, such as ground-to-air, ship-to-air, etc.
:
SUMMARY OF_THE INVENTION
It is an object of the present invention to provide a standard launcher control system that can be employed in a mulkitude of environments, thereby expanding the use~ul environment of the weapon being deployed. In the pre~erred embodiment, the ~ystem i~ designed to . .
- . . .,: . : .: : -~.. : - .
- . : : .. . : . . , , , , :
. .
:, : - .
8 ~
control the launch and flight of what was ori~inally d~signed exclusively to be an air-to air missile, the ~dvanced Medium Range Radar ~ir-to-~ir Missile (AMRAAM), although other embodiments envision this same concept being applied to any type of active rad2lr guided airborne vehicle.
In accordance with the teachinqs of the present in~ention, a ~ystem for controlling the launch and flight of an airborne vehicle, is provided. The lalmcher control system is modular in construction, employing standard equipment, and is easily deployable in a variety of environments. It employs a communications inter~ace for receiving target position information and launch control ord~rs, and ~or providing launcher and airborne vehicle status information to an information system. An airborne vehicle interface couples the launcher control system to the launcher and airborne vehicleO The airborne vehicle interfac~ pro~ides power to the airborne vehicle for launch and data and control signal~ to test and launch the airborne vehicle, and d~te~minss the status of the airborne vehicle prior to launch. A transmitter for communicating updated target information to the airborne vehicle while in flight is also provided. Finally, the system employs a power converter ~or converting various forms of input power to power ~orms required by the launcher control system componentsO Regulation of system input power and overload protection for all ~ystem components is also provided.
BRIEF DESCRIPTION~OY TH~3 DRAWINGS
Other objects and advantages of the invention will become appar~nt upon r~ading the following detailed description and upon reference to the drawings, in which.
FIG~ 1 is a schematic diagram o~ a weapon syskem incorporating the launcher control system;
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FIG. 2 is a block diagram of the launcher control system; and FIG. 3 is a block diagram of a sp~cific embodiment of the launcher ~ontrol sy~tem.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT
Turning fir~t to the weapon system 10 of FIG. 1, target position in~ormation is ~ontinuollsly obtained by a sensor 14, such as a radar system. This position information is processed by the information syst2m 16, commonly referred to as the Communication, Command, and Control (C3) System, which generates position control signals for prelaunch testing and flight control of the airborne vehicle 18, such as a missile. Briefly, the C3 Sy~tem is a combination of computer and communications technology and people. The communications technology collects and disseminates information, the computer technology processes the information, and people make decisions based on the in~ormation. The information system 16 is coupled to the launcher control system 12, which processes the position information and sends it to the airborn~ vehicle 18. Before launch, the airborne vehicle 18 recei~es position information and control signals through the launcher 20. In flight, the launcher control system transmits updated target position information to the airborne vehicle 18. The launcher control ~ystem 12 also monitors the prelaunch status of both the launchex 20 and the airborne ~ehicls 18 and relays the status information ~ack to the information system 16. Power ~or operating the launcher control system 12 and ~or activating the airborne vehicle 18 during prelaunch checkout comes from pow~r source 22~
FIG. 2 illust~ates the ~asic components of the launcher control system 12. The launcher control system 12 provides a standard communicakions interface 26 which allows for communication, launch, and guidance of the : . .
~ r~ ~ ~
missile from any information system 16 which has this ~tandard interface. The communications interface 26 performs the interface function for target position information from the target sensor 14, and for launch and contxol orders from khe information system 16. The communications inter~ace 26 also prov:ides launcher and airborne vehicle status back to the information system 16 prior to airborne vehicle launch.
The launcher control system 12 communicates with the airborne vehicle 18 in two ways. Prior to launch, the airborne vahicle inter~ace 28 is used. In one embodiment, in which the airborne vehicle 18 is a missile, the commercially available MI~-STD 1760 interface advantageously allows the use o~ standaxd unmodified production misæiles. The airborne vehicle interface 28 provides target position information and control signals for test and launch of the airborne vehicle 18 and provides power ~or airborne vehicle activation during the prelaunch checkout. It also determines the status of the airborne vehicle lB.
During flight, the launcher control system 12 communicates with the airborne vehicle 18 through a radio frequency (RF) data link transmitter 30. Target position information ~rom the communications interface 26 is transmitted to the airborne vehicl2. The launcher control system 12 provides 360~ of data link coverage so that multiple simultaneous missile engageme~t~ can be managed over this full range.
The power control 32 supplies power to the communications interface 26, thP transmitter 30, the airborne vehicle interface 28, the launcher 20, and the airborne vehicle 18. It converts available system power from the power source 22 to power forms xequired by these launch control system components. In addition, the power control 32 regulates launcher control system power and , $
, provides overload protection for all launcher control system components.
Turning now to FIG. 3, there is shown a more detailed embodimenk of the launcher control system 12.
Data link equipment 34 contains a frequency refer2nce unit 36, a transmitter 30, and a load control switch ~0. The frequency referencP. unit 36 is a variable frequency generator which produces a band of freguencies within the X-band of the electromagnetic spectrum. Frequency changes are made in fixed steps or intervalsO Since it is capable of generating dif~erent frequencies, the frequency reference unit is less susceptible to jamming.
Transmitter 30 transmits the output signal from the ~requency reference unit 36. It contains a travelling wave tube amplifier for amplifying the X-band electromagnetic signal.
The load control switch 40 directs the output of the transmitter 30 to the antenna 44 or a dummy load 46.
The dummy load 46 is provided to allow for field tests of the data link equipment 3~ without danger of spurious microwave radiation. ~`
The antenna 44 employs four antenna subsystems each covering a 90 degree swath about the center of the antenna 44. Advantageously, thP data link equipment 34 illuminates only the 90 swath in which the airborne vehicle 18 ts be updated is located, thereby reducing spurious emissions. The antenna 44 is less susceptibl~ to detection by un~riendly forces and the radiation from the antenna is less lik~ly to interfere with other friendly radiation sources in the area. Additionally, only one-fourth the transmitter power is required~
~ he airborn~ vehicle interface 28 provides a variety of control functions throughout the launcher control system 12. It ~mploys a primary inter~ace unit 29 within the housing 24 which implements frequency ~hange orders to the frequency reference unit 36, monitors the , .
2 ~ 8 8 frequency refer~nce unit 36 for fre~uency drift, and performs a built-in test of frequency referenc~ unit functions. It signals ths transmitter 30 to transmit a pulse code to the airborne vehicle 18, monitors the output power of the transmitted pulse wave~orm, monitors the transmitter 30 for failure, and performs a built-in t~st function. It selects the antenna subsys~em to be illumina~ed by the data link equipment 34. Finally, it implPments a built in test function for the horizontal reference unit 50.
A horizontal reference unit 50 is a subsystem of the airborne vehicle interface 28 located outside the housing 24 in this embodimen~ which measures the inclination of the launcher rotating platform. P:itch and roll information is sent via the primary inkerface unit 29 to the information system 16 where it is combined with the known global position of the launcher 20. I'his information about the orientation and position o~ the launcher rotating platform is important for missile targeting when using a remotely located targeting sensor 14.
Instrumentation system 54 is a subsystem of the airborne vehicl2 interface 28. It too is located outside the housing 24 in this embodiment. It is a data collection system used to monitor operation of the airborne vehicle interface 28.
The airborne vehicle interface 28 is coupled to the information system 16 through tha communications interface 26 t which employs o~e or more standard serial.
communi~ations i~terface units and one or more discrete signal communications interface units. In this embodiment the standard communications interface is the RS-422. A
multiplicity of communications interfaces provid~s safety and reliability, as control ~unctions are separated from communications function~O
.
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; 7 ~ ~
The airborne vehicle interface 2~ communicates with the launcher 20 through a series of interfaces. A
standard di~ferential serial interface 1533 is used as well as several discrete interfaces. This multiplicity of intarfaces also insures safety and reliability~
The power distribution unit 32 provide~ 28 volt DC power to the data link equipment 34 and the airborne vehicle interface 28. It receives three-phase 400 Hertz power from power ~ource 22, Three-phase 400 Hert2 power is also sent to the airborne vehicle interface 28. Three-phase power and 2~ volt DC power are sent to the launcher 20 via the airborne vehicle interface 28.
Within the information system 16 there is a launcher control unit 52. The launcher control unit 5~
implements the firing orders oE the operator and implements self-test ~unctions for the airborne v~hicle interface 28. It also relays targeting information to the airborne vehicle interface 28~
The launcher 20 with the launcher control system 12 is normally located apart from the information system 16 a~d target sensor 14, t~ereby making the launcher ~0 and the airborne vehicle 18 less vulnerable to destruction by enemy ~orces. It has a housing 24 and is modular in design, thereby facilitating repair and replacement of components. Because .it is a standard interface box, the launcher control system 12 is capable of bei~g used to control an airborne vehicle 18, such as the ~MRAAM, in many other environments besidas air-to-air. Finally, many such launcher control systems are capable of being linked to a common information system 16 to allow the simultaneous launch of multiple airborne vehicles, such as active radar missiles of the A~RAAM type. These advantages over the prior art are readily apparent to one skillQd in the art.
Although the inYention has been described with particular reference to certain preferred embodiments .
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thereof, variations and modi~Eications can be effected within the ~pirit and scope of the following claims.
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Claims (19)
1. An apparatus for controlling an airborne vehicle, said apparatus being part of a system including a target position sensor, an information system, a power source, and a launcher, said apparatus comprising:
(a) communications interface means for coupling the information system to the launcher and airborne vehicle;
(b) airborne vehicle interface means for coupling said communications interface means and said power source to said launcher and said airborne vehicle; and (c) guidance means for communicating with the airborne vehicle after launch.
(a) communications interface means for coupling the information system to the launcher and airborne vehicle;
(b) airborne vehicle interface means for coupling said communications interface means and said power source to said launcher and said airborne vehicle; and (c) guidance means for communicating with the airborne vehicle after launch.
2. The apparatus of Claim 1 further comprising:
(d) power control means for coupling said power supply to said communications interface means, said airborne vehicle interface means, and said guidance means.
(d) power control means for coupling said power supply to said communications interface means, said airborne vehicle interface means, and said guidance means.
3. The apparatus of Claim 2 further comprising:
(e) housing means for enclosing said communications interface means, said airborne vehicle interface means, said guidance means, and said power control means.
(e) housing means for enclosing said communications interface means, said airborne vehicle interface means, said guidance means, and said power control means.
4. The apparatus of Claim 3 wherein said communications interface means receives target position information from said target position sensor and launch and control orders from said information system and provides launcher and airborne vehicle status information to the information system.
5. The apparatus of Claim 3 wherein said communications interface means comprises a standard RS422 serial interface.
6. The apparatus of Claim 3 wherein said communications interface means comprises a discrete signal interface.
7. The apparatus of Claim 3 wherein said airborne vehicle interface means comprises:
(a) primary interface means for providing target position information and control signals for test and launch of said airborne vehicle, and power from said power control means for activating said airborne vehicle, as well as determining the status of said airborne vehicle;
(b) horizontal reference means, coupled to said primary interface means, for measuring the inclination of the launcher; and (c) instrumentation means coupled to said primary interface means for collecting data used to monitor operation of the primary interface means.
(a) primary interface means for providing target position information and control signals for test and launch of said airborne vehicle, and power from said power control means for activating said airborne vehicle, as well as determining the status of said airborne vehicle;
(b) horizontal reference means, coupled to said primary interface means, for measuring the inclination of the launcher; and (c) instrumentation means coupled to said primary interface means for collecting data used to monitor operation of the primary interface means.
8. The apparatus of Claim 3 wherein said guidance means comprises a transmitter for transmitting target position information to said missile.
9. The apparatus of Claim 3 wherein said guidance means comprises:
(a) a radio frequency (RF) data link transmitter;
(b) frequency reference means for generating an X-band electromagnetic signal containing guidance information to be transmitted by said data link transmitter:
(c) antenna means coupled to said data link transmitter for radiating guidance information to the airborne vehicle;
and (d) load control means for coupling said X-band electromagnetic signal to said antenna means or to a dummy load.
(a) a radio frequency (RF) data link transmitter;
(b) frequency reference means for generating an X-band electromagnetic signal containing guidance information to be transmitted by said data link transmitter:
(c) antenna means coupled to said data link transmitter for radiating guidance information to the airborne vehicle;
and (d) load control means for coupling said X-band electromagnetic signal to said antenna means or to a dummy load.
10. The apparatus of Claim 9 wherein said frequency reference means is tunable to a plurality of X-band electromagnetic signals.
11. The apparatus of Claim 9 wherein said antenna means comprises:
(a) a plurality of antennas oriented in a circle, the radiation patterns of said antennas adding to provide an omnidirectional radiation pattern; and (b) antenna selection control means for coupling said data link transmitter to one of said antennas, said airborne vehicle being within the radiation pattern of said one antenna.
(a) a plurality of antennas oriented in a circle, the radiation patterns of said antennas adding to provide an omnidirectional radiation pattern; and (b) antenna selection control means for coupling said data link transmitter to one of said antennas, said airborne vehicle being within the radiation pattern of said one antenna.
12 12. The apparatus of Claim 3 wherein said power control means converts power from different power sources to power required by said communications interface means, said airborne vehicle interface means and said guidance means.
13. The apparatus of Claim 3 wherein said housing means comprises a box-like container, being portable and separate from said target position sensor and said information system.
14. The apparatus of Claim 3, being modular in construction with said communications interface means, said airborne vehicle interface means, said guidance means, and said power control means being easily removable and replaceable.
15. The apparatus of Claim 3 wherein said airborne vehicle is a missile.
16. An apparatus for controlling an airborne vehicle, said apparatus being part of a system comprising a target position sensor, an information system, a power source, and a launcher, said apparatus comprising:
(a) communications interface means for coupling the information system to the launcher and airborne vehicle, said communications interface means receiving target position information from said target position sensor and launch and control orders from said information system, and providing launcher and airborne vehicle status information to the information system, said communications interface means including a plurality of serial interfaces;
(b) airborne vehicle interface means for coupling said communications interface means and said power source to said launcher and said airborne vehicle, said airborne vehicle interface means including a primary interface means for providing target position information and control signals for test and launch of said airborne vehicle and power from said power control means, for activating said airborne vehicle, and for determining the status of said airborne vehicle, said airborne vehicle interface means further including horizontal reference means coupled to said primary interface means for measuring the inclination of the launcher, and instrumentation means coupled to said primary interface means for collecting data used to monitor operation of the primary interface means;
(c) guidance means for communicating with the airborne vehicle after launch, said guidance means including a radio frequency data link transmitter, frequency reference means for generating an X-band electromagnetic signal having guidance information to be transmitted by said data link transmitter, antenna means coupled to said data link transmitter for radiating guidance information to the airborne vehicle;
(d) power control means for coupling said power supply to said communications interface means, said airborne vehicle interface means, and said guidance means, said power control means being capable of converting power from different power sources to power required by said communications interface means, said airborne vehicle interface means, and said guidance means; and (e) housing means for enclosing said communications interface means, said airborne vehicle interface means, said guidance means, and said power control means, said housing means comprising a box-like container being portable and separate from said target position sensor and said information system;
said apparatus being modular in construction with said communications interface means, and airborne vehicle interface means, said guidance means, and said power control means being easily removable and replaceable.
(a) communications interface means for coupling the information system to the launcher and airborne vehicle, said communications interface means receiving target position information from said target position sensor and launch and control orders from said information system, and providing launcher and airborne vehicle status information to the information system, said communications interface means including a plurality of serial interfaces;
(b) airborne vehicle interface means for coupling said communications interface means and said power source to said launcher and said airborne vehicle, said airborne vehicle interface means including a primary interface means for providing target position information and control signals for test and launch of said airborne vehicle and power from said power control means, for activating said airborne vehicle, and for determining the status of said airborne vehicle, said airborne vehicle interface means further including horizontal reference means coupled to said primary interface means for measuring the inclination of the launcher, and instrumentation means coupled to said primary interface means for collecting data used to monitor operation of the primary interface means;
(c) guidance means for communicating with the airborne vehicle after launch, said guidance means including a radio frequency data link transmitter, frequency reference means for generating an X-band electromagnetic signal having guidance information to be transmitted by said data link transmitter, antenna means coupled to said data link transmitter for radiating guidance information to the airborne vehicle;
(d) power control means for coupling said power supply to said communications interface means, said airborne vehicle interface means, and said guidance means, said power control means being capable of converting power from different power sources to power required by said communications interface means, said airborne vehicle interface means, and said guidance means; and (e) housing means for enclosing said communications interface means, said airborne vehicle interface means, said guidance means, and said power control means, said housing means comprising a box-like container being portable and separate from said target position sensor and said information system;
said apparatus being modular in construction with said communications interface means, and airborne vehicle interface means, said guidance means, and said power control means being easily removable and replaceable.
17. The apparatus of Claim 16 wherein said airborne vehicle is a missile.
18. The apparatus of Claim 16 wherein said antenna means comprises:
(a) a plurality of antennas oriented in a circle, the radiation patterns of said antennas adding to provide an omnidirectional radiation pattern; and (b) antenna selection control means for coupling said data link transmitter to one of said antennas, said airborne vehicle being within the radiation pattern of said one antenna.
(a) a plurality of antennas oriented in a circle, the radiation patterns of said antennas adding to provide an omnidirectional radiation pattern; and (b) antenna selection control means for coupling said data link transmitter to one of said antennas, said airborne vehicle being within the radiation pattern of said one antenna.
19. The apparatus of Claim 16 wherein said frequency reference means is tunable to a plurality of X-band electromagnetic signals.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US07/568,298 US5118050A (en) | 1989-12-07 | 1990-08-16 | Launcher control system |
| US568,298 | 1990-08-16 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA2046788A1 true CA2046788A1 (en) | 1992-02-17 |
Family
ID=24270730
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002046788A Abandoned CA2046788A1 (en) | 1990-08-16 | 1991-07-11 | Launcher control system |
Country Status (8)
| Country | Link |
|---|---|
| US (1) | US5118050A (en) |
| EP (1) | EP0471225B1 (en) |
| JP (1) | JP2530777B2 (en) |
| CA (1) | CA2046788A1 (en) |
| DE (1) | DE69127414T2 (en) |
| IL (1) | IL98906A0 (en) |
| NO (1) | NO306313B1 (en) |
| TR (1) | TR26547A (en) |
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|---|---|---|---|---|
| US5221062A (en) * | 1989-12-07 | 1993-06-22 | Hughes Aircraft Company | Frequency synthesizer |
| US5186414A (en) * | 1992-04-20 | 1993-02-16 | The United States Of America As Represented By The Secretary Of The Navy | Hybrid data link |
| US5471213A (en) * | 1994-07-26 | 1995-11-28 | Hughes Aircraft Company | Multiple remoted weapon alerting and cueing system |
| US5657947A (en) * | 1994-08-24 | 1997-08-19 | Loral Corp. | Precision guidance system for aircraft launched bombs |
| US5647558A (en) * | 1995-02-14 | 1997-07-15 | Bofors Ab | Method and apparatus for radial thrust trajectory correction of a ballistic projectile |
| US5671139A (en) * | 1995-07-06 | 1997-09-23 | Bessacini; Anthony F. | Hierarchical fuzzy controller for beam rider guidance |
| US5671138A (en) * | 1995-07-06 | 1997-09-23 | The United States Of America As Represented By The Secretary Of The Navy | Fuzzy controller for acoustic vehicle target intercept guidance |
| US5671140A (en) * | 1995-07-06 | 1997-09-23 | The United States Of America As Represented By The Secretary Of The Navy | Fuzzy controller for target intercept guidance |
| US5828571A (en) * | 1995-08-30 | 1998-10-27 | The United States Of America As Represented By The Secretary Of The Navy | Method and apparatus for directing a pursuing vehicle to a target with evasion capabilities |
| US5691531A (en) * | 1995-11-09 | 1997-11-25 | Leigh Aerosystems Corporation | Data insertion system for modulating the carrier of a radio voice transmitter with missile control signals |
| US5944762A (en) * | 1996-04-01 | 1999-08-31 | The United States Of America As Represented By The Secretary Of The Navy | Hierarchical target intercept fuzzy controller with forbidden zone |
| DE19651888C1 (en) * | 1996-12-13 | 1998-08-13 | Daimler Benz Aerospace Ag | System for the final phase guidance of guided autonomous missiles |
| US5987362A (en) * | 1997-10-06 | 1999-11-16 | The United States Of America As Represented By The Secretary Of The Navy | Final approach trajectory control with fuzzy controller |
| US6161061A (en) * | 1998-06-26 | 2000-12-12 | The United States Of America As Represented By The Secretary Of The Navy | Guidance controller for a minimal discrete command set |
| US6845938B2 (en) * | 2001-09-19 | 2005-01-25 | Lockheed Martin Corporation | System and method for periodically adaptive guidance and control |
| GB0503212D0 (en) * | 2005-02-15 | 2005-11-23 | Ultra Electronics Ltd | Improvements relating to target direction indication and acoustic pulse analysis |
| US7910867B1 (en) * | 2006-03-03 | 2011-03-22 | Lockheed Martin Corporation | Architecture for a launch controller |
| US7881337B2 (en) * | 2006-08-24 | 2011-02-01 | Raytheon Company | Methods and apparatus for information management systems |
| IL178840A0 (en) * | 2006-10-24 | 2007-09-20 | Rafael Advanced Defense Sys | System |
| US20100217899A1 (en) * | 2007-01-31 | 2010-08-26 | Raytheon Company | Munitions control unit |
| US11313650B2 (en) | 2012-03-02 | 2022-04-26 | Northrop Grumman Systems Corporation | Methods and apparatuses for aerial interception of aerial threats |
| US9551552B2 (en) | 2012-03-02 | 2017-01-24 | Orbital Atk, Inc. | Methods and apparatuses for aerial interception of aerial threats |
| US9501055B2 (en) | 2012-03-02 | 2016-11-22 | Orbital Atk, Inc. | Methods and apparatuses for engagement management of aerial threats |
| US9170070B2 (en) | 2012-03-02 | 2015-10-27 | Orbital Atk, Inc. | Methods and apparatuses for active protection from aerial threats |
| US11947349B2 (en) | 2012-03-02 | 2024-04-02 | Northrop Grumman Systems Corporation | Methods and apparatuses for engagement management of aerial threats |
| US10975718B2 (en) | 2013-02-12 | 2021-04-13 | Garrett Transportation I Inc | Stainless steel alloys, turbocharger turbine housings formed from the stainless steel alloys, and methods for manufacturing the same |
| KR101965580B1 (en) * | 2017-12-21 | 2019-04-04 | 주식회사 한화 | Apparatus and method for controlling miss operation of guided weapon based on pils model |
| CN112050691B (en) * | 2020-07-23 | 2022-10-28 | 北京临近空间飞行器系统工程研究所 | Miniaturized high-reliability missile-borne wireless transmission controller |
| CN114576042B (en) * | 2022-03-11 | 2023-06-20 | 中国工程物理研究院总体工程研究所 | Remote ignition device and ignition method suitable for solid rocket engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3987447A (en) * | 1965-06-21 | 1976-10-19 | The United States Of America As Represented By The Secretary Of The Navy | Missile command link with pulse deletion command coding |
| US4093153A (en) * | 1965-11-18 | 1978-06-06 | The United States Of America As Represented By The Secretary Of The Army | Ground-controlled guided-missile system |
| US4238090A (en) * | 1978-09-22 | 1980-12-09 | The United States Of America As Represented By The Secretary Of The Army | All-weather intercept of tanks from a helicopter |
| FR2459955A1 (en) * | 1979-06-27 | 1981-01-16 | Thomson Csf | NEW MISSILE AND MISSILE PILOT CONTROL SYSTEM |
| FR2597226B3 (en) * | 1986-04-09 | 1988-05-20 | Messerschmitt Boelkow Blohm | GUIDANCE COMPUTER FOR A LAUNCHING INSTALLATION |
| IL78757A0 (en) * | 1986-05-12 | 1986-08-31 | Israel State | Launcher for an optically guided,wire-controlled missile with improved electronic circuitry |
| DE3625649A1 (en) * | 1986-07-29 | 1988-02-18 | Messerschmitt Boelkow Blohm | ANGLE CODING DEVICE |
| FR2603695B1 (en) * | 1986-09-09 | 1990-10-19 | Thomson Csf | METHOD AND DEVICE FOR VIEWING TARGETS AND / OR TARGET POSITIONS USING MEANS OF ACQUISITION OF WEAPONS SYSTEM |
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| US5042742A (en) * | 1989-12-22 | 1991-08-27 | Hughes Aircraft Company | Microcontroller for controlling an airborne vehicle |
-
1990
- 1990-08-16 US US07/568,298 patent/US5118050A/en not_active Expired - Lifetime
-
1991
- 1991-07-11 CA CA002046788A patent/CA2046788A1/en not_active Abandoned
- 1991-07-21 IL IL98906A patent/IL98906A0/en unknown
- 1991-07-25 DE DE69127414T patent/DE69127414T2/en not_active Expired - Lifetime
- 1991-07-25 EP EP91112536A patent/EP0471225B1/en not_active Expired - Lifetime
- 1991-08-13 TR TR91/0798A patent/TR26547A/en unknown
- 1991-08-14 JP JP3204473A patent/JP2530777B2/en not_active Expired - Lifetime
- 1991-08-15 NO NO913195A patent/NO306313B1/en not_active IP Right Cessation
Also Published As
| Publication number | Publication date |
|---|---|
| NO306313B1 (en) | 1999-10-18 |
| TR26547A (en) | 1995-03-15 |
| NO913195L (en) | 1992-02-17 |
| JPH04227493A (en) | 1992-08-17 |
| US5118050A (en) | 1992-06-02 |
| EP0471225A3 (en) | 1992-09-30 |
| JP2530777B2 (en) | 1996-09-04 |
| EP0471225A2 (en) | 1992-02-19 |
| DE69127414T2 (en) | 1998-01-02 |
| DE69127414D1 (en) | 1997-10-02 |
| EP0471225B1 (en) | 1997-08-27 |
| NO913195D0 (en) | 1991-08-15 |
| IL98906A0 (en) | 1992-07-15 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request | ||
| FZDE | Discontinued |