Description:FIELD OF THE INVENTION
[0001] The present disclosure relates to the field of rocket motor testing, and more particularly relates to a pyro console system and method for controlling a static firing of a Rocket Motor.
BACKGROUND
[0002] Missile propulsion technology has come a long way since the first rockets were developed. In the current era of military technology, missile propulsion systems are a key area of research and development, with advances in this field having significant implications for national security and defense strategies.
[0003] A conventional missile propulsion system includes a dual pulse rocket motor. The dual pulse rocket motor utilizes a safe and arming mechanism for ignition based on a detonator and Through Bulkhead Initiation (TBI) for pulse I and pulse II motors. The conventional missile propulsion system undergoes a destructive static firing test to evaluate its functionality, during which various parameters such as thrust, pressure, temperature, strain, and currents of the dual pulse rocket motor are monitored.
[0004] An existing static firing test setup for the conventional missile propulsion system comprises a console unit and a relay unit. The console unit controls the switching operations required for static firing testing of rocket motors. Further, the console unit incorporates push buttons and toggle switches for controlling the switching operations to the electrical and electronic subsystems that form the firing test setup. The console unit may also issue safe/arm commands for pyro lines and Ignition Safe Arm (ISA) 1. The console unit may further display the status signal such as ISA1 feedback, ISA2 feedback, and relay arm and safe conditions. The console unit may further incorporate switches that may issue commands to a relay box for executing the required operations. Further, the output from the console unit may drive the relays present in the relay unit.
[0005] The main purpose of the relay unit is to meet the power and pyro-switching requirements for conducting the static firing testing of the rocket motors. All the switching requirements are realized using MIL-STD electro-mechanical relays, such as four-pole double-throw 4PDT electro-mechanical relays with a maximum current capacity of 10A. Out of these four poles, two poles are used to provide a break in power supply lines (High and Low lines), the third pole is used to provide the status of relay operation to the console unit, and the fourth pole is used for providing relay status to a recording system. The electro-mechanical relays may include freewheeling diodes for relay coils on two PCB. The freewheeling diodes protect switching circuitry from the high voltage generated by the inductive loads. The electro-mechanical relays may further include resistors for configuring potential dividing networks to derive the on/off status of the relay.
[0006] The existing static firing test setup may suffer from several limitations such as manual operation leading to imprecise timings, absence of data recording, the potential for human errors, dependence on trained operators, and a bulky relay unit that is difficult to troubleshoot and debug. These limitations of the existing setup render it unsuitable for conducting reliable and efficient static tests of the rocket motors.
[0007] Therefore, there lies a need for a new and improved static firing test setup that may overcome the above-mentioned limitations of the existing static firing test setup and may provide a more reliable and efficient means of conducting static tests of the rocket motors.
SUMMARY
[0008] This summary is provided to introduce a selection of concepts in a simplified format that is further described in the detailed description of the invention. This summary is not intended to identify key or essential inventive concepts of the invention, nor is it intended for determining the scope of the invention.
[0009] In an embodiment, the present disclosure discloses a method of controlling a static firing of a rocket motor using a pyro console system. The method includes generating, based on a user input received on a pyro unit of the pyro console system, a first Ignition Safe Arm (ISA) command for arming one or more relays for the static firing of the rocket motor. The method further includes determining whether a first ISA feedback is received from the rocket motor based on the generated first ISA command. Further, the method includes initiating a firing sequence timer upon the determination that the first ISA feedback is received from the rocket motor. Further, the method includes triggering a first bridge of a first pulse motor of the rocket motor after expiry of the firing sequence timer. Further, the method includes triggering a second bridge of the first pulse motor subsequent to the triggering of the first bridge of the first pulse motor after a first predefined time is elapsed.
[0010] In one or more embodiments, the method may further include determining whether a thrust value associated with a thrust feedback from the rocket motor is greater than a predefined value. Further, the method may include triggering, at a first user defined time instance, a Thrust Vector Control (TVC) upon the determination that the thrust value is greater than the predefined value.
[0011] In one or more embodiments, the method may further include determining, after the triggering of the second bridge or the triggering of the TVC, whether a second ISA feedback is received from the rocket motor. Further, the method may include triggering, at a second user defined time instance, a first bridge of a second pulse motor of the rocket motor upon the determination that the second ISA feedback is received from the rocket motor. Further, the method may include triggering a second bridge of the second pulse motor subsequent to the triggering of the first bridge of the second pulse motor after a second predefined time is elapsed.
[0012] In one or more embodiments, the method may further include setting a static firing mode of the rocket motor based on a selection of an operation mode among a plurality of operation modes via a user selection operation.
[0013] In one or more embodiments, the method may further include aborting the static firing of the rocket motor upon non-reception of the thrust feedback or one of the first ISA feedback or the second ISA feedback from the rocket motor.
[0014] Also disclosed herein is a pyro console system to control a static firing of a rocket motor. The pyro console system includes a pyro unit that arms one or more relays of a relay unit for the static firing of the rocket motor, a firing unit connected with the relay unit to control triggering of one or more events associated with the static firing of the rocket motor, and a control unit that includes one or more processors. The one or more processors are configured to determine whether a first Ignition Safe Arm (ISA) feedback is received from the rocket motor when the one or more relays are armed. The one or more processors are further configured to initiate a firing sequence timer upon the determination that the first ISA feedback is received from the rocket motor. Further, the one or more processors are configured to control the firing unit to trigger a first bridge of a first pulse motor of the rocket motor after expiry of the firing sequence timer. Further, the one or more processors are configured to control the firing unit to trigger a second bridge of the first pulse motor subsequent to the triggering of the first bridge of the first pulse motor after a first predefined time is elapsed.
[0015] In one or more embodiments, the one or more processors may be further configured to determine whether a thrust value associated with a thrust feedback from the rocket motor is greater than a predefined value. Further, the one or more processors may be configured to control, at a first user defined time instance, the firing unit to trigger Thrust Vector Control (TVC) upon the determination that the value of the thrust feedback is greater than the predefined value.
[0016] In one or more embodiments, the one or more processors may be further configured to determine, after the triggering of the second bridge or the triggering of the TVC, whether a second Ignition Safe Arm (ISA) feedback is received from the rocket motor. Further, the one or more processors may be configured to control, at a second user defined time instance, the firing unit to trigger a first bridge of a second pulse motor of the rocket motor upon the determination that the second ISA feedback is received from the rocket motor. Further, the one or more processors may be configured to control the firing unit to trigger a second bridge of the second pulse motor subsequent to the triggering of the first bridge of the second pulse motor after a second predefined time is elapsed.
[0017] In one or more embodiments, the one or more processors may be further configured to set a static firing mode of the rocket motor based on a selection of an operation mode among a plurality of operation modes via a user selection operation.
[0018] In one or more embodiments, the one or more processors may be further configured to abort the static firing of the rocket motor upon non-reception of the thrust feedback or one of the first ISA feedback or the second ISA feedback from the rocket motor.
[0019] In one or more embodiments, the pyro console system may further include a data acquisition unit to acquire data corresponding to the one or more events associated with the static firing of the rocket motor. The one or more events include receiving the first ISA feedback or the triggering of one or more of the first pulse motor, the second pulse motor, and the TVC.
[0020] In one or more embodiments, the one or more processors may be further configured to acquire, from the data acquisition unit, the data corresponding to the one or more events in a form of voltage and current. Further, the one or more processors may be configured to store the acquired data in a memory of the control unit. Further, the one or more processors may be configured to control a display screen of the control unit to display the acquired data.
[0021] To further clarify the advantages and features of the method and system, a more particular description of the method and system will be rendered by reference to specific embodiments thereof, which are illustrated in the appended drawing. It is appreciated that these drawings depict only typical embodiments of the invention and are therefore not to be considered limiting its scope. The invention will be described and explained with additional specificity and detail with the accompanying drawings.
BRIEF DESCRIPTION OF THE DRAWINGS
[0022] These and other features, aspects, and advantages will become better understood when the following detailed description is read with reference to the accompanying drawings in which like characters represent like parts throughout the drawings, wherein:
FIG. 1 illustrates an example test setup for static firing of a rocket motor, according to one or more embodiments of the present disclosure;
FIG. 2 illustrates a block diagram of a pyro console system for controlling the static firing of the rocket motor, according to one or more embodiments of the present disclosure;
FIG. 3 illustrates a schematic diagram of a pyro unit of the pyro console system, according to one or more embodiments of the present disclosure;
FIG. 4 illustrates a schematic diagram of a relay unit of the pyro console system, according to one or more embodiments of the present disclosure;
FIG. 5 illustrates a schematic diagram of a firing unit of the pyro console system, according to one or more embodiments of the present disclosure;
FIG. 6 illustrates a connection diagram depicting a connection between the pyro unit, the firing unit, the relay unit, and a data acquisition unit of the pyro console system, according to one or more embodiments of the present disclosure;
FIG. 7 illustrates a block diagram depicting a plurality of operational modes for the static firing of the rocket motor, according to one or more embodiments of the present disclosure;
FIG. 8 illustrates a detailed flowchart of method steps performed by the pyro console system for controlling the static firing of the rocket motor, according to one or more embodiments of the present disclosure;
FIG. 9 illustrates a graph indicating voltage and current corresponding to the one or more events, according to one or more embodiments of the present disclosure; and
FIG. 10 illustrates a user interface for selecting a mode from a plurality of operational modes, according to one or more embodiments of the present disclosure
[0023] Further, skilled artisans will appreciate that elements in the drawings are illustrated for simplicity and may not have necessarily been drawn to scale. For example, the flow charts illustrate the method in terms of the most prominent steps involved to help to improve understanding of aspects of the invention. Furthermore, in terms of the construction of the device, one or more components of the device may have been represented in the drawings by conventional symbols, and the drawings may show only those specific details that are pertinent to understanding the embodiments of the invention so as not to obscure the drawings with details that will be readily apparent to those of ordinary skill in the art having the benefit of the description herein.
DETAILED DESCRIPTION
[0024] It should be understood at the outset that although illustrative implementations of embodiments are illustrated below, the system and method may be implemented using any number of techniques. The disclosure should in no way be limited to the illustrative implementations, drawings, and techniques illustrated below, including the exemplary design and implementation illustrated and described herein, but may be modified within the scope of the appended claims along with their full scope of equivalents.
[0025] The term “some” and “one or more” as used herein is defined as “one, or more than one, or all.” Accordingly, the terms “one,” “more than one,” but not all” or “all” would all fall under the definition of “some.” The term “some embodiments” or “one or more embodiments” may refer to one embodiment or several embodiments or all embodiments. Accordingly, the term “some embodiments” is defined as meaning “one embodiment, or more than one embodiment, or all embodiments.”
[0026] The terminology and structure employed herein are for describing, teaching, and illuminating some embodiments and their specific features and elements and do not limit, restrict, or reduce the spirit and scope of the claims or their equivalents.
[0027] More specifically, any terms used herein such as but not limited to “includes,” “comprises,” “has,” “have” and other grammatical variants thereof do not specify an exact limitation or restriction and certainly do not exclude the possible addition of one or more features or elements, unless otherwise stated, and must not be taken to exclude the possible removal of one or more of the listed features and elements, unless otherwise stated with the limiting language “must comprise” or “needs to include.”
[0028] The term “unit” used herein may imply a unit including, for example, one of hardware, software, and firmware or a combination of two or more of them. The “unit” may be interchangeably used with a term such as logic, a logical block, a component, a circuit, and the like. The “unit” may be a minimum system component for performing one or more functions or may be a part thereof.
[0029] Unless otherwise defined, all terms, and especially any technical and/or scientific terms, used herein may be taken to have the same meaning as commonly understood by one having ordinary skill in the art.
[0030] Embodiments will be described below in detail with reference to the accompanying drawings.
[0031] One or more embodiments of the present disclosure describe a pyro console system to control a static firing of a rocket motor of a missile system. The static firing of a rocket motor includes the firing of three pyros each for initiating a first pulse motor, a second pulse motor, and Thrust Vector Control (TVC) ejection. The initiation of both the first pulse motor and the second pulse motor is carried out by firing detonators each having two bridges. TVC ejection is achieved by initiating two explosive bolts, each explosive bolt has a single bridge. The successful initiation of anyone explosive bolt ejects the TVC system, while the second bolt provides redundancy.
[0032] One or more embodiments of the present disclosure further describe a mechanism for the automatic firing of different pyros at specific timings once desired conditions are met to ensure a successful static firing of the rocket motor. The pyro console system disclosed herein may generate auto-sequenced launch commands to carry out the rocket motor static firing. The auto-sequenced launch commands are generated as per the launch sequence time base. This present disclosure further provides a reliable and efficient means of the static firing of the rocket motor.
[0033] FIG. 1 illustrates an example test setup 100 for the static firing of a rocket motor, according to one or more embodiments of the present disclosure. The test setup 100 comprises a Main Test Bed (MTB) 102, a Local Instrumentation Center (LIC) 104, a Data Acquisition Center (DAC) 106, and a Master Control Center (MCC) 108.
[0034] The MTB102 is a platform designed to accommodate the rocket motor and all the necessary components for testing of functionality and performance of the rocket motor. The MTB 102 is typically composed of a sturdy structure with a base plate that provides support to the rocket motor during testing. The MTB 102 is equipped with various sensors and instruments to monitor the rocket motor performance during testing. In a non-limiting example, the sensors of the MTB 102 may include a thrust sensor, pressure sensors, temperature sensors, strain gauges, and others. In addition to the sensors, the MTB 102 may also include various mechanisms for positioning and aligning the rocket motor during the testing. The MTB 102 may be formed at a distance, for example around 25 meters, from the LIC 104.
[0035] The LIC 104 typically includes multiple subsystems, such as a data acquisition unit, control and communication systems, and safety and monitoring systems. The data acquisition unit may collect data from various sensors and instruments deployed on the rocket motor and sends the collected data to the DAC 106 for storage and analysis. The control and communication systems within the LIC 104 may control the various test equipment and systems, such as a relay unit and a firing unit. The control and communication systems may also facilitate communication between the LIC 104 and the MCC 108, as well as communication between other subsystems within the LIC 104. The LIC104 may further include various safety and monitoring systems to ensure the safety of personnel and equipment during the testing of the rocket motor. In a non-limiting example, the safety and monitoring systems of the LIC 104 may include fire suppression systems, emergency shutdown systems, and environmental monitoring systems to detect and respond during hazardous conditions. The LIC 104 may be formed at a distance, for example around 70 meters, from the DAC 106.
[0036] The DAC106 and the MCC 108 work together to facilitate the testing and evaluation of the rocket motor. The DAC 106 may be responsible for collecting, storing, and processing sensor data generated during missile testing. In a non-limiting example, the sensor data may include thrust feedback data from the rocket motor, temperature, pressure, strain, and other physical parameters of the rocket motor. The DAC106 may include one or more software tools for analyzing the collected sensor data, generating reports, and sharing information with the testing team.
[0037] The MCC 108 may also be a part of the DAC 106 and may include a control and monitoring system to control the testing of the rocket motor. Each of the MCC 108 and the DAC 106 may include a Junction Box (JB) 110 and 112, respectively. The JB 110 and 112 may be used for connecting multiple sensors and instrumentation cables in a missile instrumentation system. The JB110 and 112 may include one or more terminals or connectors to attach the various cables and wires. The JB 110 and 112 may also include additional circuitry for signal conditioning or amplification.
[0038] FIG. 2 illustrates a block diagram of a pyro console system 200 for controlling the static firing of the rocket motor, according to one or more embodiments of the present disclosure.
[0039] The pyro control system 200 comprises a pyro unit 202, a relay unit 204, a firing unit 206, a rocket motor 208, a firing trigger console 210, and a Data Acquisition Unit (212). The rocket motor 208 is placed on the MTB 102. The firing unit 206, the relay unit 204, and the DAQ 212 are placed in the LIC 104. The pyro unit 202 and the firing trigger console 210 are placed in the DAC 106. The pyro control system may further comprise separate programmable Power supplies Units (PSU1, PSU2, PSU3, PSU4, PSU5) for the pyro unit 202, for each pyro of the relay unit 204, and the firing unit 206. The firing trigger console 210 may further comprise a control unit 210-2. The control unit 210-2 includes one or more processors configured to control functions of the firing trigger console 210.
[0040] The pyro unit 202 may issue safe/arm commands for pyro lines and Ignition Safe Arm (ISA) 1. The pyro unit 202 may further arm one or more relays of the relay unit 204 for the static firing of the rocket motor 208 based on the issuance of the safe/arm commands.
[0041] The relay unit 204 may include electro-mechanical relays to execute power and pyro switching requirements for the static testing of the rocket motor 208. The relay unit 204 may further provide one or more relay feedback to the pyro unit 202, the firing unit 206, and the DAQ 212. In a non-limiting example, the one or more relay feedbacks may include ISA 1 feedback, ISA 2 feedback, and feedback associated with triggering one or more of the first pulse motor, the second pulse motor, and the TVC. The relay unit 204 may also provide the relay on/off status to the pyro unit 202. The relay unit 204 may also receive a trigger signal from the firing unit 206 to trigger the one or more events. In a non-limiting example, the one or more events may include triggering one or more of the first pulse motor, the second pulse motor, and the TVC.
[0042] The firing unit 206 may be a microcontroller-based firing unit. The firing unit 206 may receive the one or more relay feedbacks from the relay unit 204. The firing unit 206 may further send the received one or more relay feedbacks to the firing trigger console 210. The firing unit 206 may also receive a control signal from the control unit 210-2 of the firing trigger console 210. The firing unit 206 may further generate the trigger signal based on the control signal received from the control unit 210-2.
[0043] The one or more processors of the firing trigger console 210 may be configured to manage a LabVIEW based application running on the firing trigger console 210. The one or more processors may be further configured to control a display of a user interface on a display screen of the firing trigger console 210. The user may select a mode from a plurality of operational modes based on a selection operation of the user. The TVC trigger timing and P2B1 trigger timing may be set based on a user input operation on the display screen. The one or more processors may be further configured to receive one or more relay feedbacks from the rocket motor 208 via the firing unit 206. In a non-limiting example, the one or more relay feedbacks may include ISA 1 feedback, ISA 2 feedback, and feedback associated with the triggering of the one or more of the first pulse motor, the second pulse motor, and the TVC.
[0044] In one or more embodiments, the one or more processors may be further configured to determine whether a first Ignition Safe Arm (ISA) feedback is received from the rocket motor 208 when the one or more relays are armed. The one or more processors may be further configured to initiate a firing sequence timer upon the determination that the first ISA feedback is received from the rocket motor 208. Further, the one or more processors may be configured to control the firing unit 206 to trigger a first bridge of a first pulse motor of the rocket motor 208 after expiry of the firing sequence timer. Further, the one or more processors may be configured to control the firing unit 206 to trigger a second bridge of the first pulse motor subsequent to the triggering of the first bridge of the first pulse motor after a first predefined time is elapsed.
[0045] In one or more embodiments, the one or more processors may be configured to determine whether a thrust value associated with a thrust feedback from the rocket motor 208 is greater than a predefined value. The one or more processors may be further configured to control, at a first user defined time instance, the firing unit 206 to trigger Thrust Vector Control (TVC) upon the determination that the value of the thrust feedback is greater than the predefined value.
[0046] In one or more embodiments, the one or more processors may be configured to determine, after the triggering of the second bridge or the triggering of the TVC, whether a second Ignition Safe Arm (ISA) feedback is received from the rocket motor 208. The one or more processors may be further configured to control, at a second user defined time instance, the firing unit 206 to trigger a first bridge of a second pulse motor of the rocket motor 208 upon the determination that the second ISA feedback is received from the rocket motor 208. Further, the one or more processors may be configured to control the firing unit 206 to trigger a second bridge of the second pulse motor subsequent to the triggering of the first bridge of the second pulse motor after a second predefined time is elapsed.
[0047] In one or more embodiments, the one or more processors may be configured to set a static firing mode of the rocket motor 208 based on a selection of an operation mode among a plurality of operation modes via a user selection operation.
[0048] In one or more embodiments, the one or more processors may be configured to control the firing unit to abort the static firing of the rocket motor 208 upon non-reception of the thrust feedback or one of the first ISA feedback or the second ISA feedback from the rocket motor 208.
[0049] In one or more embodiments, the one or more processors may be configured to acquire, from the data acquisition unit, the data corresponding to the one or more events in a form of voltage and current. Further, the one or more processors may be configured to store the acquired data in a memory of the control unit 210-2. Further, the one or more processors may be configured to control a display screen of the control unit 210-2 to display the acquired data.
[0050] The DAQ 212 may correspond to a 16-channel data acquisition system. The DAQ 212 may acquire data corresponding to the one or more events associated with the static firing of the rocket motor 208. The one or more events associated with the static firing of the rocket motor 208 may include receiving the first ISA feedback or the triggering of one or more of the first pulse motor, the second pulse motor, and the TVC. The DAQ 212 may also be connected with the firing trigger console 210 to provide information associated with different pyro events in form of voltage and current.
[0051] FIG. 3 illustrates a schematic diagram of the pyro unit 202 of the pyro console system 200, according to one or more embodiments of the present disclosure.
[0052] The pyro unit 202 may control the switching operations for static testing of the rocket motor 208. The pyro unit 202 may also issue safe/arm commands for pyro lines and the ISA 1. The pyro unit 202 may include various switches and indicators at the front panel of the pyro unit 202. The indicator may indicate the status of the current activity. In a non-limiting example, the ISA 1 status, ISA 2 status, and relay arm &safe conditions of P1, P2, and TVC may be displayed. The switches may correspond to pushing buttons or key switches for controlling the switching operations of the electrical/electronic subsystems of the relay unit 204 for the static testing of the rocket motor 208. The pyro unit 202 may further include safety keys at the front panel of the pyro unit 202. The safety keys may be employed to provide 28Vdc to the arm/safe switches to arm/safe the relays in the relay unit 204. The pyro unit 202 may further include various connection pins at the back panel of the pyro unit 204. The connection pins connect the pyro unit 202 with the relay unit 204. The output from the pyro unit 202 may drive the relays in the relay unit 204.
[0053] FIG. 4 illustrates a schematic diagram of the relay unit 204 of the pyro console system 200, according to one or more embodiments of the present disclosure.
[0054] The relay unit 204 includes four-pole double-throw 4PDT electro-mechanical relays to execute power and pyro switching requirements for the static testing of the rocket motor 208. The electro-mechanical relays are ARL MIL standard electro-mechanical relays. Each relay of the electro-mechanical relays may include four poles. The two poles of each relay of the electro-mechanical relays may be used to provide a break in power supply lines (high &low lines) and the other two poles may be used to provide the status of relay operation to the pyro unit 202, the firing unit 206, and the data acquisition unit 212. The status of the relay operation may be provided via connection pins on the relay unit. The relay unit 204 may also provide the relay on/off status to the pyro unit 202 via the connection pins on the relay unit 204. The relay unit 204 may implement a pyro scheme for initiating three numbers of pyro events and may cater to various switching requirements to control power supplies to the electronic subsystems of the relay unit 204.
[0055] FIG. 5 illustrates a schematic diagram of the firing unit 206 of the pyro console system 200, according to one or more embodiments of the present disclosure.
[0056] The firing unit 206 may correspond to a Modern ARM-CORTEX M4 microcontroller-based firing unit. The firing unit 206 may receive one or more commands via TCP/IP from the control unit 210-2 of the firing trigger console 210. The command may be generated via the LabVIEW based application running on the firing trigger console 210. The firing unit 206 may provide a trigger signal to the relay unit 204 to trigger the various relays and the ISA. The firing unit 206 may also indicate feedback status received from various trigger relays on a front panel of the firing unit 206. Further, an emergency stop switch may be provided on the front panel of the firing unit 206 to abort all processes by disabling the trigger relays. The firing unit 206 may also send the received feedback to the firing trigger console 210 via the LabVIEW based application. The firing unit 206 may also receive a control signal from the control unit 210-2 of the firing trigger console 210. The firing unit 206 may also provide trigger signals to the relay unit 204 based on the control signal received from the control unit 210-2. The firing unit 206 may communicate with the control unit 210-2 of the firing trigger console 210 using an Ethernet cable via the TCP/IP protocol.
[0057] The firing unit 206 may further receive feedback from various sources including ISA1, Thrust, and ISA2 of the rocket motor 208. If the feedback is not received from any of the sources among the ISA1, Thrust, and ISA2, the firing unit 206 may abort the firing of relays. The firing unit 206 may be designed to receive status feedback from the auxiliary contacts of the relays driving the pyros. If such feedback is not received, the firing unit 206 may abort firing and communicate the status to the LabVIEW based application running on the firing trigger console 210. Additionally, the firing unit 206 may also receive crucial thrust feedback after the P1 motor fires and may abort the firing of relays in the event of thrust failure. The firing unit 206 may also be designed to operate on a 230VAC main supply.
[0058] FIG. 6 illustrates a connection diagram of the pyro unit 202, the relay unit 204, the firing unit 206, and the DAQ 212 the pyro console system, according to one or more embodiments of the present disclosure.
[0059] As illustrated in Fig. 6, the pyro unit 202 is connected with the relay unit 204 via a plurality of connection ports. The pyro unit 202 may send arm/safe input to the relay unit 204. The relay unit 204 may arm the relays for triggering the pyros based on the received arm/safe input. The relay unit 204 may send the status input indicating the arm/safe status of relays to the pyro unit 202. The relay unit 204 may further send a control input to the pyro unit 202 for controlling ISA 1.
[0060] The relay unit 204 may also be connected to the firing unit 206, the DAQ 212, and the rocket motor 208. The relay unit 204 may send a signal to the rocket motor 208 to trigger the relays connected with the rocket motor 208. The relay unit 204 may also send information associated with the relay events and sensor data to the DAQ 212. Further, the relay unit 204 may receive the trigger input from the firing unit 206 to trigger the various relays. The relay unit 204 may also send status feedback of various triggering events to the firing unit 206.
[0061] Although not shown in the figure, the firing unit 206 may also be connected with the firing trigger console 210. The firing unit 206 may transfer the received feedback status to the firing trigger console 210 and may receive the control signal from the firing trigger console 210. The firing unit 206 may also send the trigger signal to the relay unit 204 based on the received control signal from the firing trigger console 210.
[0062] FIG. 7 illustrates a plurality of operational modes for the static firing of the rocket motor 208, according to one or more embodiments of the present disclosure. The pyro control system 200 may be operated in one of the plurality of modes. The firing trigger console 210 of the pyro control system 200 may enable a user to set an operational mode of the pyro control system 200. The control unit 210-2 of the firing trigger console 210 may manage the LabVIEW based application running on the firing trigger console 210. The control unit 210-2 may control the display of the user interface on the display screen of the firing trigger console 210. The user may select a mode from the plurality of operational modes based on a user selection operation on the display screen. The user may also set TVC trigger timing and P2B1 trigger timing based on a set operation on the display screen. The TVC timing may be set between 4 to 8 seconds. Further, the P2B1 trigger timing may be set between 8 to 200 seconds. The plurality of operational modes includes, but not limited to, mode 1 (P1, TVC, P2), mode 2(P1, TVC), mode 3(P1), mode 4(P2), and mode 5(P1, P2).
[0063] FIG. 8 illustrates a detailed flowchart of method steps performed by the pyro console system 200 of FIG. 2 for controlling the static firing of the rocket motor 208, according to one or more embodiments of the present disclosure.
[0064] In one or more embodiments, the present disclosure further relates to a method of controlling a static firing of rocket motor 208 using the pyro console system 200. The rocket motor 208 comprises three pyros each for initiating the pulse1 motor, pulse 2 motor, and Thrust Vector Control (TVC) ejection. The initiation of both the pulse 1 and pulse 2 motors may be carried out by firing detonators. Each detonator may include two bridges with all fire currents per bridge. TVC ejection may be achieved by initiating two explosive bolts, each explosive bolt may include a single bridge with all fire currents. The successful initiation of any of one explosive bolt may eject the TVC system, while the second bolt provides redundancy.
[0065] In a non-limiting example, for mode 1 operation, all three pyros may fire in the sequence of pulse1 pyro fire, TVC ejection, and pulse2 pyro fire. The pulse2 pyro fire and TVC ejection events may not be initiated until the pulse1 pyro fire command is issued. Thus, the pyro supply to the TVC ejection and pulse 2 pyro relays may be enabled only after the P1 fire command is issued. In order to ensure safety during pyro operations, a break is used in both the high and low lines using pyro unit 202. Unless the safe/arm break is closed, all further relay operations may become ineffective. All pyro operations may be of a momentary type and may be implemented by non-latch relays of the relay unit 204.
[0066] In one or more embodiments, the method includes generating, based on a user input received on the pyro unit 202 of the pyro console system 200, the first ISA command for arming one or more relays for the static firing of the rocket motor 208. The method further includes determining whether the first ISA feedback is received from the rocket motor 208 based on the generated first ISA command. Further, the method includes initiating the firing sequence timer upon the determination that the first ISA feedback is received from the rocket motor 208. Further, the method includes triggering the first bridge of the first pulse motor of the rocket motor 208 after expiry of the firing sequence timer. Further, the method includes triggering the second bridge of the first pulse motor subsequent to the triggering of the first bridge of the first pulse motor after the first predefined time is elapsed.
[0067] In one or more embodiments, the method may include determining whether the thrust value associated with the thrust feedback from the rocket motor 208 is greater than the predefined value. The method may further include triggering, at the first user defined time instance, the TVC upon the determination that the thrust value is greater than the predefined value.
[0068] In one or more embodiments, the method may include determining, after the triggering of the second bridge or the triggering of the TVC, whether the second ISA feedback is received from the rocket motor 208. The method may further include triggering, at the second user defined time instance, the first bridge of the second pulse motor of the rocket motor 208 upon the determination that the second ISA feedback is received from the rocket motor 208. Further, the method may include triggering the second bridge of the second pulse motor subsequent to the triggering of the first bridge of the second pulse motor after the second predefined time is elapsed.
[0069] FIG. 9 illustrates a graph indicating voltage and current corresponding to the one or more events, according to one or more embodiments of the present disclosure. In one or more embodiments, the firing trigger console 210 may be connected to the DAQ 212 through the ethernet cable. The firing trigger console 210 may obtain data corresponding to the one or more events for the selected operation mode in the form of voltage and current. The one or more processors may generate a system report including the graph of the voltage and the current corresponding to the one or more events for the selected operation mode. In one or more embodiments, the one or more processors may be further configured to apply X and Y cursors on the voltage and the current graph to enable the user to measure the amplitude of the one or more events at any time. The one or more processors may also be configured to apply the X and Y cursors on the voltage and the current graph to enable the user to measure a time of occurrence of the one or more events.
[0070] FIG. 10 illustrates a user interface for selecting a mode from a plurality of operational modes, according to one or more embodiments of the present disclosure. In one or more embodiments, the one or more processors of the firing trigger console 210 may control the display screen of the firing trigger console 210 to display the user interface.
[0071] An example of the user interface is illustrated in FIG. 10. As shown in FIG. 10, the user interface enables the user to control, set, and view the one or more events during the static firing of the rocket motor 208. The user interface includes first selection fields for enabling the user to select an operation mode from the plurality of operational modes. Further, the user interface also includes input fields for enabling the user to set the TVC trigger timing and P2B1 trigger timing. The user interface further includes a display of the voltage and current waveform corresponding to the one or more events. Further, the user interface includes control fields for controlling the start and stop of the one or more events. The user interface may also include various LED indicators for providing connection status feedback. In particular, a TCP/IP communication LED may be used to indicate a connection between the firing unit 206 and the firing trigger console 210. Further, an HBM LED may also be used to indicate when a connection between the firing trigger console 210 and the DAQ 212 is established. The LEDs turn red when there is a loss of communication. The user interface also includes an elapsed time feature that displays the start time of the ISA1 trigger. The various status feedback received from the firing unit 206 are displayed below the elapsed time feature to enable the user to decide whether to abort or continue with the firing sequence.
[0072] The system and method disclosed herein above provides various technical benefits and advantage including providing a user-friendly interface with multiple features for online and offline data analysis, that may help in time saving and reduce cost in the missile test setup. The system disclosed herein is a fully automated system including a programmed microcontroller having the ability to easily compile and execute programs. Overall, the fully automated system offers an efficient and effective solution for the missile test setup. The system disclosed herein provides the mechanism for the automatic firing of different pyros at specific timings once desired conditions are met to ensure a successful static firing of the rocket motor. The system disclosed herein is ideal for a variety of applications, including data acquisition and missile control systems.
[0073] The units, amongst other things, include routines, programs, objects, components, data structures, etc., which perform particular tasks or implement data types. The units may also be implemented as, signal processor(s), state machine(s), logic circuitries, and/or any other device or component that manipulates signals based on operational instructions.
[0074] Aspects of the present invention are described herein with reference to flow chart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the invention. It will be understood that each block of the flowchart illustrations and/or block diagrams, and combinations of blocks in the flowchart illustrations and/or block diagrams, can be implemented by computer-readable program instructions.
[0075] The descriptions of the various embodiments of the present invention have been presented for purposes of illustration but are not intended to be exhaustive or limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments. The terminology used herein was chosen to best explain the principles of the embodiments, the practical application or technical improvement over technologies found in the marketplace, or to enable others of ordinary skill in the art to understand the embodiments disclosed herein.
[0076] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting to the invention. As used herein, the singular forms “a”, “an” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprises” and/or “comprising,” when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one more other features, integers, steps, operations, element components, and/or groups thereof.
[0077] The flow diagrams depicted herein are just one example. There may be many variations to this diagram, or the steps (or operations) described therein without departing from the spirit of the invention. For instance, the steps may be performed in a differing order, or steps may be added, deleted, or modified. All of these variations are considered a part of the claimed invention.
[0078] While the preferred embodiment of the invention had been described, it will be understood that those skilled in the art, both now and in the future, may make various improvements and enhancements which fall within the scope of the claims which follow. These claims should be construed to maintain the proper protection for the invention first described.
[0079] Benefits, other advantages, and solutions to problems have been described above with regard to specific embodiments. However, the benefits, advantages, solutions to problems, and any component(s) that may cause any benefit, advantage, or solution to occur or become more pronounced are not to be construed as a critical, required, or essential feature or component of any or all the claims. , Claims:1. A method of controlling a static firing of a rocket motor using a pyro console system, the method comprising:
generating, based on a user input received on a pyro unit of the pyro console system, a first Ignition Safe Arm (ISA) command for arming one or more relays for the static firing of the rocket motor;
determining whether a first ISA feedback is received from the rocket motor based on the generated first ISA command;
initiating a firing sequence timer upon the determination that the first ISA feedback is received from the rocket motor;
triggering a first bridge of a first pulse motor of the rocket motor after expiry of the firing sequence timer; and
triggering a second bridge of the first pulse motor subsequent to the triggering of the first bridge of the first pulse motor after a first predefined time is elapsed.

2. The method as claimed in claim 1, further comprising:
determining whether a thrust value associated with a thrust feedback from the rocket motor is greater than a predefined value; and
triggering, at a first user defined time instance, a Thrust Vector Control (TVC) upon the determination that the thrust value is greater than the predefined value.

3. The method as claimed in any one of claims 1 or 2, further comprising:
determining, after the triggering of the second bridge or the triggering of the TVC, whether a second ISA feedback is received from the rocket motor;
triggering, at a second user defined time instance, a first bridge of a second pulse motor of the rocket motor upon the determination that the second ISA feedback is received from the rocket motor; and
triggering a second bridge of the second pulse motor subsequent to the triggering of the first bridge of the second pulse motor after a second predefined time is elapsed.

4. The method as claimed in any of the preceding claims, further comprising setting a static firing mode of the rocket motor based on a selection of an operation mode among a plurality of operation modes via a user selection operation.

5. The method as claimed in any of the preceding claims, further comprising aborting the static firing of the rocket motor upon non-reception of the thrust feedback or one of the first ISA feedback or the second ISA feedback from the rocket motor.

6. A pyro console system to control a static firing of a rocket motor, the pyro console system comprising:
a pyro unit that arms one or more relays of a relay unit for the static firing of the rocket motor;
a firing unit connected with the relay unit, wherein the firing unit controls triggering of one or more events associated with the static firing of the rocket motor; and
a control unit that includes one or more processors, wherein the one or more processors are configured to:
determine whether a first Ignition Safe Arm (ISA) feedback is received from the rocket motor when the one or more relays are armed;
initiate a firing sequence timer upon the determination that the first ISA feedback is received from the rocket motor;
control the firing unit to trigger a first bridge of a first pulse motor of the rocket motor after expiry of the firing sequence timer; and
control the firing unit to trigger a second bridge of the first pulse motor subsequent to the triggering of the first bridge of the first pulse motor after a first predefined time is elapsed.

7. The pyro console system as claimed in claim 6, wherein the one or more processors are further configured to:
determine whether a thrust value associated with a thrust feedback from the rocket motor is greater than a predefined value; and
control, at a first user defined time instance, the firing unit to trigger Thrust Vector Control (TVC) upon the determination that the value of the thrust feedback is greater than the predefined value.

8. The pyro console system as claimed in any one of claims 6 or 7, wherein the one or more processors are further configured to:
determine, after the triggering of the second bridge or the triggering of the TVC, whether a second Ignition Safe Arm (ISA) feedback is received from the rocket motor;
control, at a second user defined time instance, the firing unit to trigger a first bridge of a second pulse motor of the rocket motor upon the determination that the second ISA feedback is received from the rocket motor; and
control the firing unit to trigger a second bridge of the second pulse motor subsequent to the triggering of the first bridge of the second pulse motor after a second predefined time is elapsed.

9. The pyro console system as claimed in any of claims 6 to 8, wherein the one or more processors are further configured to set a static firing mode of the rocket motor based on a selection of an operation mode among a plurality of operation modes via a user selection operation.

10. The pyro console system as claimed in any of claims 6 to 9, wherein the one or more processors are further configured to abort the static firing of the rocket motor upon non-reception of the thrust feedback or one of the first ISA feedback or the second ISA feedback from the rocket motor.

11. The pyro console system as claimed in any of claims 6 to 10, further comprising a data acquisition unit to acquire data corresponding to the one or more events associated with the static firing of the rocket motor, wherein the one or more events includes receiving the first ISA feedback or the triggering of one or more of the first pulse motor, the second pulse motor, and the TVC.

12. The pyro console system as claimed in any of claims 6 to 11, wherein the one or more processors are further configured:
acquire, from the data acquisition unit, the data corresponding to the one or more events in a form of voltage and current;
store the acquired data in a memory of the control unit; and
control a display screen of the control unit to display the acquired data.