Title of the invention A method for validation of launch circuit safety and performance, on Rig
2. Field of Invention 5 The present invention relates to a novel method for real time launch circuit safety and performance, test on Rig using a novel tester. This tester provides a user programmable real time validation of release signal sequence which has critical completion timing requirement on Rig. This also validates stray voltages checks with variable &programmable limits. 10 Further, an instantaneous visual indication of successful competition launches signals and presence of valid stray voltage.
3. Background of invention
Each Launcher uses a specific launch sequence or Sequence of Events, 15 for activation of final electric launch signal to successfully complete fire ordnance. These electric launch circuits with sequence of events must be tested to ensure that the launcher circuit is working in designed way and Launcher output the correct voltage after a proper sequence to the ordnance. In order to test the launch circuits of launcher, it is not 20 necessary to load the weapon instead a simulated tester and then validate the launch of the weapon. The indication indicates, with an valid visual display, the components of launch circuit in totality is serviceable. Some test must be repeated prior to each launch and on the all stations from which the weapon is fired. This method of testing does provide feedback 25 indicating whether the launch circuit is operating in the normal mode.
Additionally, for each test of the launch circuit the actual weapon must not be loaded. Smart weapons uses a complete hand shaking (Cyclogram) or a defined signal sequencing, between weapon, launcher and aircraft system prior to release. These hand shaking circuits must be tested to 30 ensure that the circuit meets the correct timing requirement and voltage requirement. This hand shaking test has to be done prior to loading of smart weapon .This requirement is performed using a tester .In order to test the hand shaking circuits for smart weapons it shall not be necessary to load the weapon .hence it is validated using tester and allowed to load 5 the weapon. Testing with actual weapon has safety hazard as weapon may explode during checks. The growing costs of weapon simulator for individual weapon testing .leads to an optimization of number of tester required for pre loading checks of newly integrated & launcher . Until now it has been practised of dedicated exhaustive tester for detailed testing 10 instead of minimal testing and evaluate electrical behavioural load on launcher for preventing "current over loading or over timing requirement” at the launcher mating connector beyond technically specified limit by incremental real time testing analysis. Also needs gradual validation of stray voltages level at each critical mating point on launcher. The 15 problem in hand involves firstly ascertain characteristic of signals of respective pins of aircraft launcher which becomes increasingly used in dynamic condition and secondly unacceptable timing behaviour lead by an electrical component deterioration or failure of launcher. These electrical malfunctioning characteristic arise on launcher during steady or 20 intermittent usages. Normally, such phenomenon leads to failure of the respective weapon launching. Therefore, so-called stray voltage and timing calculations which are employed already during the initial validation, needs periodic validation prior to each launching .The mathematically computed launch sequence system used in high performance aircraft 25 needs to validate along with the stray voltage and launch characteristics.
To validate these mathematical characteristics in optimal manner, a method for validation of armament launches circuit on Test Rig is designed. This novel tester which comprises LCD input panels, microcontroller, data handling block, indicators, algorithms to controls the 30 characteristic behaviour of the signals. In other words, such tester achieves a real time validation based on computed signal values. The novel tester contains two databases; first the stray voltage database containing maximum permissible values allowed as adjusting elements, which are periodically validated at the characteristic voltage of the attachment or pins, in order to achieve maximum safety on the unwanted 5 release, second the timing database containing maximum permissible values allowed as maximum time delay or permissible time limits. Ground crew has real time control in test based on database. . And sequence of modelling of timing in milli second is not possible in manual way. In response to signals generated by; launcher means providing a 10 representing value. Such tester are integrated with launcher system which provide a timing signal as a means for generation of the means in response to a voltage and time which does not exceeds a certain selectable threshold value. The variable are stray voltage or signal timing which provide the respective pass /fail for the means in response to an 15 current voltage and timing level which exceeds in its amplitude ,a selectable threshold value. These threshold values signal or anticipate a contour of timing or amplitude. The testing variables are then maintained in the current values until the next desired has been visualized. The mentioned, the tester has means for adjusting the valid profile of aircraft 20 .In typical prior art, in case of integration of new launcher ,a component on aircraft ,it is required that launcher integrity to be tested with aircraft , manually operated test points were selected by Ground crew to call off the weapon loading decision based on voltage data. When values is . moved to close threshold limit and anomaly is detected, under such 25 circumstances, the effort of reducing the aircraft threshold can be extremely reduced by the usage of automatic performance tester. Ground crew can has On/Off toggle on-off switch mounted on tester to select start and end of automatic testing. This tester provides an excellent safety handling feature during development phase, with the benefit of not 30 needing or using any manual intervention making a vital safety-critical requirement. In summary, prior art had following drawbacks:
a) For Ground crew, there is no auto testing system where test to be operated using cyclogram with reduced testing time reduction. b) No possibility to check the safe stray voltage limit to decide safety in real time threshold. 5 c) No possibility to know the repeat test as per data base to decide cyclogram reduction in real time. d) For Ground crew, there is no possibility where cyclogram to be defined in real time. e) For Ground crew, there is no possibility where stray voltage values 10 to be defined in real time.
These problems were substantially overcome by the system which is the subject of this invention.
4. Summary of the Invention 15 The present invention overcomes deficiencies of bulky and dedicated tester by replacing the portable and programmable, integrated tester. The portable safety and performance launch circuit tester is a microcontroller based tester. The tester requires no power supply but works on batteries and it does not draw the power directly from the test lab. The tester is 20 able to indicate whether the launch circuit is good or bad. The tester incorporates a microcontroller, running embedded software with a unique method of calculating measuring stray voltage, input and output ports as per user defined requirement. The software design allowed substantial processing in real time. It is capable of input \being loaded by LCD display 25 that provides inputs to tester. The invention relates to a method for the launch safety & performance tester of a high speed aircraft, for optimizing the aircraft pre weapon loading test requirement in much optimized manner. For this, the stray voltage and cyclogram are placed with suitable values in accordance to mathematically model used in indicating probable 30 failure of high timing requirement. The levels which may cause a catastrophic failure by the stay voltage or electrical signal area of an launcher during weapon loading .As the stray voltage point reaches to maximum possible limit or closer to the threshold point prior to loading thereby tester provides a suitable indication regarding in pass/fail values.
The tester system activates display which includes display of failed 5 cyclogram in the aircraft when needed and stay in an activated for visual effective signal display for a length of time sufficient for visual analysis. The signal activation takes place rapidly in about 2 to 4 milliseconds from the time the test .During routine phase, it is essential to monitor the safety of aircraft, specially stray voltage and launcher condition 10 of aircraft .In case of any exigency condition on aircraft, certain set of manual operation also has to be performed, which is more safe, or change the launcher of aircraft. Especially for replacement related decision, in case of failure in meeting cyclogram requirement, it has to be determined very precisely based on current cyclogram requirement of launcher. Prior 15 to this, safety decision depends upon ground crew skill. There was no automatic method to compute in real time the safe levels using set of auto sensing and auto pass/fail indication .There is high chance of judgmental error which may be catastrophic .Also, in case based on error in manual judgment ground crew may opt for loading weapon even in 20 presence of stray voltages .Hence as an additional safety measure, ground crew is provided with additional feature of auto validate the signal using novel performance tester. This novel performance tester does real time computation of safe voltages based on various input ports inputs and does auto computation. Auto computation of voltage and cyclogram helps 25 the aircraft to reduce test time .Also ground crew has feature of real time display of test outputs automatically. Also Ground crew has indication for additional manual operation to control stray voltage .This lead to maximum possible validation using .This ultimately helps Ground crew to bring aircraft at safe level and eventually ensure the safe release . The interface 30 between a Ground crew and the tester of an aircraft, especially in case of voltage nearing threshold, needed much attention. The Ground crew control interfaces are simple but needed a great deal of ground crew skill to control aircraft signal in case of stray voltage. The novel tester helps, Aircraft, with uses of microcontroller based electronics and interfaces to assist the ground crew for semi-automated operation and make condition 5 of flight safer. In no "automatic” interface, the ground crew interacts with a manual user interface using dedicated selection indicators in the legacy tester. This controller also enables Ground crew to select auto test mode wherein tester will check stray voltage, cyclogram, continuity and show result. This feature is helpful for trainee Ground crew with less test 10 experience. Algorithm in novel tester is constantly working to make and control the interface safer, easier to understand and automatically operate, and more effective, efficient and reliable way. Launcher cyclogram in conjunction with an electrical incoming and outgoing signal is considered as a reference command. In smart weapon, the Ground crew ensures and 15 operates to provide a safety during release phases. In this case, a manual validation operation provides increase in aircraft testing and inaccuracy.
This type of automatic testing provides good handling qualities while in normal integrity condition. More specifically, any sudden aircraft test requirement condition often do not provide suitable action time, and in 20 particular to reduce testing time. Generally speaking, auto testing can be useful by reducing the aircraft's test time. However in case of aircraft testing in short span of time, based on required scenario, manual testing has to be stopped .For this, the database of tester is used to validate the safety. Under Such circumstances, the effort of test aircraft based on 25 human judgment needs time .In an automated testing system the aircraft testing can be extremely reduced by the usage of a microcontroller processing which in turn momentary change the test requirement , making easier the task of aircraft testing without the ground crew intervention. This controller provides good handling qualities during rapid testing and, with 30 the benefit of not needing or reading manually validation information in safety-critical aircraft. In an . exemplary illustrative non-limiting implementation, a microcontroller based on testing information, is presented. For example, the controller computes the possibility of stray overshoot operation based on a set of aircraft voltage parameters and without the ground crew interruption .The ground crew interruption maybe 5 any of a plurality of devices used in aeronautics industry to serve as an interface with a human ground crew, e.g. LCD input, or any adequate operation. The aircraft parameters include, but are not limited to, in this example, stray voltage, and signal sequence. The technology herein aims to propose an aircraft testing system and a method of adding accuracy io with speedy testing characteristics, where the aircraft is set to the a particular configuration, i.e. when the voltage threshold is set to the increasing as per launcher location. The effort of reducing the aircraft test time during time critical requirement can be extremely reduced by the usage of a output of controller .The exemplary illustrative non-limiting 15 technology described herein is an aircraft control system that is configured for rapid testing. Since the illustrative reconfigured control system for testing, in addition to manual visual capability, an auto testing process is performed similarly to a conventional aircraft: the ground crew not will be required to keep the eye on aircraft voltage in order to reduce the aircraft 20 test time which reduces significantly the ground crew workload. When the tester is selected, the current test configuration is latched as a new tester configuration. A non-limiting advantage of the illustrative solution is a testing that provides adequate handling qualities during aircraft test condition. This eliminates the failure case of using erroneous information 25 during training phase of ground crew and allows the testing of the aircraft without reduction of safety margins. In one example non-limiting implementation,additional hardware or physical parts are needed to implement the proposed solution when compared to the aircraft in the basic configuration.
5. DESCRIPTION OF THE DRAWINGS
FIG. 1 is a simplified view of the electrical interconnection of each functional block of novel launch circuit safety & performance tester. All features and advantages using tester will be better and more completely 5 understood by referring to the following detail description of exemplary non-limiting illustrative embodiments in conjunction with the drawings of which: FIG. 1 is a non-limiting example of a launch circuit tester;
FIG. 2 is a schematic diagram of logical block inside microcontroller io exemplary illustrative non-limiting implementation of an example non­limiting structure integrity controller system, showing a basic non-limiting internal logical architecture;
FIG. 3 is a schematic front views of tester with voltage overshoot 15 protection circuit, Output voltage protection circuit, impedance matching - circuit as shown in a somewhat exaggerated way; where each rheostat position along with the protection circuit is mapped with dynamic required values. The each point of numeric values is mapped using mathematical
data.
20
FIG. 4 presents a schematic of an detail description of electrical interconnect of real time data entry block consisting of LCD display for dynamic pass/fail limit for stray voltage for each port .This example no limiting architecture of the number of input lines and value computation 25 algorithm based on current platform required values of an aircraft.
FIG. 5 presents a schematic of an detail description of electrical interconnect of real time data entry block for generation of signal sequencing (cyclogram ) .This example no limiting architecture of the 30 number of signal used in sequencing based on current requirement , .The computed profile of electrical signal sequencing .
circuit which prohibits excessive voltage to be transmitted to launcher .It has a voltage direction protection circuit which has a diode and ensures that voltage flow in only one direction .It has impedance matching circuit when there is requirement to transmit signals with certain impedance.
6. Detailed Description of the Invention
23-Qpt-2023/113866/202341072336/Form 2(Title Page)
The following specification particularly describes the invention and the manner in which electronic launch circuit safety and performance test is 10 carried out using a novel tester called launch circuit safety and performance [200], Referring to the drawings, FIG. 1 shows a block diagram of the electronic launch circuit safety and performance tester [200] which is used to ensure safety of launch system , includes a microcontroller [111] that has input and output port and LCD panels . 15 Launch circuit safety and performance tester [200] has feature of dynamic stray voltage and momentary continuity, signal sequencing feature as per received signal(cyclogram), essential each time the when launch circuit is required to be triggered. This launch circuit safety and performance tester [200] has microcontroller [111] and the LCD displays 20 and battery operated DC Power Supply through battery source [100], Referring to Fig. 1, the main interconnect of launch safety & performance tester [200] for launch circuit validation of launcher [201] as per requirement is illustrated in a schematic manner. The launch safety & performance tester [200] has several components that include a plurality of 25 electronic input device includes an indicators as LCD type connected each other via an electrical interconnect with microcontroller [111]: Microcontroller [111] having well known hardware devices such as a CPU and memory devices. In detail, Fig. 1 shows a functional block diagram of the of launch safety & performance tester [200]. The input section of 30 launch safety & performance tester [200] contains, input section named as a multi input synchronized data acquisition section containing a dedicated interface as LCD panel 1 [108] an input interface for providing real time threshold setting for stray voltages .LCD panel 2 [109] an input interface for providing real time port configuration or generation of sequence of timing signals(cyclogram) between various ports ,LCD panel3[110] an 5 input interface for providing real time continuity test requirement which may be momentary , LCD panel 4 [112] an input interface for selection of database using database manager [112].The database manager [112] stores values of previous test profiles and threshold settings .The launch safety & performance tester [200] also contains output section namely io programmable output ports[106] for interconnecting to launcher unit[201] , Pass /Fail Indication using LCD panel 5[107] to ground crew for showing real time results for stray voltage, along with pass/fail indication for launch circuit using LCD panel 6[114] for display of pass /fail indication for launch circuit or failure of cyclogram .input lines [113] for acquisition of is input signal form launcher[201] .signal handling block [119] which act as mainly protection against high input voltages, battery source [100],0n/0ff/reset switch [116] for On/Off and reset function, continuity pass fail indication sing LCD panel 7 [115] for status of continuity checks .
All stray voltage values, where it has reached to boundary condition to 20 avoid accidental launch will be displayed in pass /Fail Indication LCDS panel [107] (Ref Fig 8B). The sequence signal will be given to launcher [201] using output ports [106], to validate launch circuit within launcher [201], for the visual feedback to ground crew to do certain manual operation for reduction of tray voltage as possible or change the faulty 25 launcher. The Signal handling block [119] (ref Fig 10) converts the signals into compatible volt DC for the microcontroller [111] in a manner well known in the art. FIG. 8 is a detailed schematic of the tester .The tester [200] employs a commercially available microcontroller[111] with an EPROM, that gets inputs from which it calculates the voltage and 30 current of the ports[202] and generates output signals depending on the programming requirement .The microcontroller [111] is a conventional electronic control unit and provided with defined software for control functions for a controlling the signal sequence with predetermined time interval to validate the launch sequence based on requirement. Such modified software provides a visual pass/fail indication [114] launch 5 sequence validation. The launch sequence is user configurable .An algorithm realized by software elements for the sequence signal (Ref Fig 8A). The launcher is equipped with a signal interface ports [202].Existing ports and their sequencing system can be used for the present purpose with no or only minor modifications. The signal handling block [119] ,has io voltage overshoot protection circuit[301] prohibits excessive voltage to be transmitted to microcontroller[111] . protection circuit[301] has one comparator (C1) which compares with threshold set by microcontroller [111].The signal handling block [119] has a voltage direction protection circuit [303] which has a diode (D1)and ensures that voltage flow in only 15 one direction(REF FIG 10). protection circuit[306] has one comparator (C2) which compares with threshold set by microcontroller [111], voltage overshoot protection circuit[306] which prohibits excessive voltage to be transmitted to launcher [201] .The signal handling block [119] has a voltage direction protection circuit [304] which has a diode(D2) and 20 ensures that voltage flow in only one direction .The signal handling block [119] has impedance matching circuit [305] when there is requirement to transmit signals with certain impedance. Processing arrangement can in principle comprise any conventional known processing system based e.g., on microcontroller [111] and associated memory, peripherals and 25 hardware interfaces. Then, processing arrangement is able to compute a time based command based on the input data received from input lines [113], After processing, results are sent to an indicators Pass /Fail Indication [107] as a mean of indication for stray voltage values, in case crossing limit, enable a manual control on stray voltage. The 30 microcontroller[111] has a software program set into the EPROM of the chip that calculates the values of the voltage of the launch circuit and causes output signals to be developed that provide feedback to the launcher and user through the LCD display 1[108]. The tester senses stray voltage from the launch circuit through the voltage detector sequence. Consequently, the pass fail for launch sequence is generated 5 according to the signals computed by launcher [201] is displayed in pass/fail indication [114], The continuity pass fail indication [115] is also indicated by indication to ground crew such that the ground crew is aware of critical loom or circuit failure. Novel launch sequence and performance controller [200] receives 28VDC from 28VDC source battery [100] by using 10 a dedicated electrical interconnect. With reference to FIG. 2, Microcontroller [111] has seven logical blocks, first logical block is database manager interface [701] which is a LCD interfaced with memory unit which stores previous stray voltage range .release sequence , continuity test requirement data indicative of characteristics of the 15 behavior at various requirements, second logical block is input handling section [702] which is a I/O handling unit which reads user input data , Third logical block is a indication module [705] .fourth logical block is data processing block [704] enables to validates user entered data, fifth logical block is algorithm 1 block [706] .sixth logical block is algorithm 2 20 block [703].In summary ,the sequence and performance controller [200] has a microcontroller [111] as a main computing unit, which further has a LCD panel 1 [108] , a LCD panel 2[109], a LCD panel 3[110], a LCD panel 4[112].Input lines [113] which has multiple input line and output ports [106] which gives output signal and pass/fail indication for stray 25 volts using LCD panell [108], pass/fail indication for launch circuit using LCD panel 6 [114]. The microcontroller^ 11] send visual feedback user by display pass /fail , a light on the LCD panel to constantly blink if a no stray voltage is established and to blink if the stray voltage limit is bad.
The LCD display4 [107] is used as input signals for the microcontroller 30 [111] to determine peak values for voltage received from the input ports[106]. The logical block database manager interface [701] is having previous operated history. It has a set of various points on threshold values and sequencing requirement as per aircraft, mathematically maximum permissible stray voltage values, and cyclogram .Each port of input connector from start to end is mapped with array of voltage and 5 cyclogram database .This set of possible data base not varying with time.
In the preferred embodiment, resulting data items after processing and appropriate unit conversion are sent to algorithm 1 block [706] and algorithm 2 block [703]. Algorithm 2 blocks [703] thus generates signal data for the plurality of outputs. The Algorithm 1 detects and provides the io ability to detect the presence of stray AC or DC voltage at the launch pin through the use of voltage measurement .The algorithm 2 block [703] generates signal for output port signal .The mathematical model reiterated by database [701] shows its permissible values , as per the aircraft and weapon profile for which the; launcher[201] has been 15 designed. The sequence of the generation of the cyclogram at various ports[106], as per the design may largely be explained by the altered response as per fig 8. The invention employs this effect, and alters or acknowledges the possible increases and/or the limit voltage and timing values as per database manager interface[701] or by data entered using 20 LCD panel 2[109] at the onset of or in response to a signal2[402] .The signal2[402] at various ports[202] at launcher [201] is as input signals .The response is generated by tester [200] as per cyclogram define din microcontroller [111] .which includes appropriate delay in response or signal 1 [403] at various defined levels .This response is achieved in a 25 gradual or steady manner, whereby a desired signal sequence as per the input values. The prompt recognition of the signal instability and the correction must become effective sufficiently quickly established using this method. A action is sufficiently fast if the desired control as per database [701] used more than and, within a time interval of approximately 2 to 4 30 msec after generation of a first signal. Alternatively, the extension or operation of appropriate timing requirement performed more precisely by means of a cyclogram signal at level above previously achieved timing level. In the existing stringent timing requirement for aircraft it is required that aircraft must remain stray voltage free up to certain of design level.
The operation of the tester will be further clarified through a hypothetical 5 launch circuit test. The tester is placed in the near launch circuit and the tester is then cycled through the interconnect. At the LCD panels the various command are given and the trigger is initiated causing a voltage to be developed across the launch ports[106]. The microcontroller [111] monitors input lines and calculates the voltage and current that was at the 10 launch ports [106]. If the voltage or duration is less than specified volts or of less duration, bad circuit is indicated. To indicate a bad circuit, the microcontroller [111] will causing the LCD light on the control panel to blink or not at all if the voltage received was too low. If the voltage measured is greater than or equal to specified volts a good circuit will be 15 indicated. To indicate a good circuit, the microcontroller reduces constant display .Because of the need for almost real-time feedback the microcontroller!1 11] must process the values for voltage almost instantaneously and send the required output signals. This was accomplished by a software algorithm that works in the "real time 20 domain" to calculate voltage values for voltage. This program runs much faster and takes up much less memory space than traditional calculating routines provided by commercial software compilers .The microcontroller also sends outputs to the LCD display which will display the results.
The LCDs represent different conditions of the test fire: Go or no GO. 25 The Go is represented by the constant LCDs and a lit LCD will indicate that the proper voltage is being applied. If either the voltage or current is not or time is not within parameters then a blinking LCD will illuminate.
Each row of the LCD display represents the conditions for one test cycle.
The tester [200] can record data base of the launch circuit [202]. The LCD 30 display will remain illuminated forever till power off. The suggested features of the invention are thus intended primarily for such release concepts in which the validation of stray voltage or signal sequencing may arises , hence to be ground tested gradually with required automation Such a ground testing have further advantages of extreme conformity of safety'and successful launch . As a part .of invention, the 5 limitation of accidental release, unsuccessful release is optimized by ground testing with dedicated interface to sense voltage which causes accidental release. To control accidental release of the weapon , in turn safety of aircraft is achieved through automatic validation by launch safety & performance tester [200] mainly by the ground crew, by io validation of the voltages with respect to a prescribed value. In detail the logical block named data processing block [704] is dedicated for processing all input data .either by data base manager [112] or by input from LCD panel 2[109]. Data processing block [704] performs combination of information from data base manager interface [701] or LCD 15 Panel 2[109]. This module, data base manager interface [701] ensures that all voltage and timing is handed as per voltage level and timing requirement or by history of data entered. Respective inputs are stored in input handling [702] section. Further output of data processing block [704] to feed to algorithm 2 blocks [703] and algorithm 1 block [706].AIgorithm 1 20 block [706] thus process data for the plurality of inputs. The algorithm 1 block [706] monitors stray voltage levels using the database is selected by data processing block [704] or by user defined values by LCD panel 2[109].The database processing block[704] is having profiling data as shown in fig 8. It has a set of various voltage points as per aircraft, 25 mathematically maximum permissible voltage values, and timing requirement .Each voltage level on various ports on aircraft is mapped with array of port [202] and voltage information .This set of possible data base not varying with time. In the preferred embodiment, resulting voltage items after processing and appropriate unit conversion are sent to algorithm 1 30 block [706]. It preferably performs data processing, such as in converting voltage data. With reference to FIG.2, microcontroller [111]logical block holding circuit [707] is also act as output to perform visual indication for pass fail indication for no volts LCD 5 [107] an pass fail indication for launch circuit [201], In the preferred embodiment, based on resulting voltage and timing signal is generated .The output of algorithm block 1 5 [706] generate various levels as an indication from ground crew to do monitor visually and will indicate stray voltage levels .The ports[202] are arranged in those inputs of the launch circuit in which the overshot of the stray voltage are expected to occur. The signal of these voltage is then processed so that only levels not having amplitude io within the band of the expected voltages may passthrough effective way causing the generation of pass fail indication signal LCD panel 5[107].
Since the voltage with respect to ports [106] is known or measurable, constructing the respective algorithm is then processed. When a given threshold voltage or a given limit is exceeded, visual indication is 15 generated. In particular, the voltage and ports [106] are arranged in the form of array means between in both extreme voltages, the resulting failure signals causing failure signal generation. The voltage signal input at LCD panel 1 [108] is as a function of a prescribed limit or threshold and real time acquired values. The LCD panel 1 [108] is shown in fig 4 20 .wherein there is a split display 108(2) for selection of ports and pass /fail limit individually and data entry filed 108(1) for data entry .The LCD panel 2 [109] is shown in fig 5 .wherein there is a split display 109(2) for selection of sequence .logic and pass /fail criteria individually and data entry filed 109(1) for data entry .The LCD panel 3 [110] is shown in fig 6 25 .wherein there is a split display 110(2) for selection of continuity test logic and pass /fail criteria individually and data entry filed 110(1) for data entry .The LCD panel 7 [112] is shown in fig 7 .wherein there is a split display 112(2) for selection of test requirement and pass /fail criteria individually and data entry filed 112(1) for data entry .Signal as per cyclogram(Fig8) 30 can be generated after a delay time of approximately 2-4 msec . The duration of the generated voltage signals as per LCD panel 2[109] are ascertained by microcontroller [111]. The voltage signals[109] generated are based on algorithm 2 block [703] which are fixed in their values as per mathematical model for each ports[106] in the tester[200] and as per requirement The described steps and features provide an optimal 5 decrease of the voltage level of ports by means of the simple function of a one-time extension or operation of a control which is then held open for a sufficient period of time. Contrary thereto, in the prior art the voltage limits are decreased by means of periodically validation mainly offline validation of critical levels of a ports by offline analysis. The ports, 10 which are under development, the external attachment on launcher possesses a well-defined voltage related issues. The input module [113] acquires Real time voltage values from ports[202] provides , likewise it handles voltage up to Nth ports .The algorithm 2 block [703] carry out signal sequencing for first signals likewise in plurality for Nth ports. The 15 data is fed to block compute signal values for output port[106] and likewise for Nth ports .The output is fed to output ports [106] which compares from database manager interface [701] and further gives output to holding circuit for display pass or fail indication likewise for Nth ports .The algorithm 1 block [706] carry out comparison conversion using 20 module for first ports likewise in plurality for Nth ports. The output is fed to logical comparator which compares from database processing block[704] and further gives output to control signal pass fail holding circuit for [707] likewise for Nth ports. The voltage is fed to logical OR gate in case any signal is high .logical OR gate will be triggered. The signal is be 25 high in variable length till voltage levels reaches to safe values .The output is passed to indication module [705] which has threshold indication for boundary value indication. The same is also given to LCD panel 4(107] for permanent indication to ground crew for unsafe values for no repetition of same voltages. After the engagement of this tester, indication for pass fail 30 LCD panel 5[107] along with pass fail for launch circuit [114] operates. In this way with safety and release assurance , is accomplished in a manner similar to a conventional aircraft selectable by ground crew .This reduces error in unwanted release by ground crew and suitability of loading of weapon system . The indication module LCD 4[107] &LCD 5[114] further includes an indication for previous overshoot of voltage and failure in 5 cyclogram. The output of output ports [106] generates various signal as a cyclogram to do monitor visually and will indicate ground crew for proper functioning of launcher .The same data is shown in LCD panel [114] for display of all values where it has reached to boundary condition .Further, based on algorithm 1 block [706] gives signal to indication module [107] to 10 generate assist indication which needs ground crew. The cyclogram signal which is variable 0-28VDC type of signal .generated by output ports [106] that indicates possibility of signal action .The signal at output ports [106] further converted by momentary signal holding circuit by holding circuit LCD panel 4 [107] in case of failure . The signal is based on method 15 and rules are defined by taking a threshold safe voltages and maximum possible control , a requirement for preventing stray voltage overshoot and a stability of signals is into consideration. A method and rules for determining safe stray voltage in the aircraft determining unit is obtained by database processing block [704] or a set of data stored in 20 the memory devices. The method and rules for determining safe voltage is also stores by data maps stored in the memory devices. For instance, the microcontroller [111] stores data maps shows a map for determining prohibited range and available range in accordance with the present weapon. FIG. 9 shows the tester in its preferred package that 25 approximates the length as a portable tester. This front view with partial cut out reveals the general construction of the tester. The front end is a removable socket assembly /pin [202] and handle [203], made preferably out of high density material. This detachable method was chosen to allow handling and packing a requirement .The tester is subjected to enormous 30 hazardous working condition .The voids of outside atmosphere if went inside socket assembly /pin[202] or oil attached to handle[203], can cause difficulty is testing hence, due to suitable detachment of the tester can progress the testing in smoother way .The detachable socket assembly /pin[202] assembly is attached in standard attachment to ensure that the appropriate sizes are available during the testing process. The LCD 5 display was chosen because of the low power consumption and easy visibility is less light condition.
CLAIMS
We Claim
1. A method and apparatus for real time validation of launch circuit safety and performance of an aircraft during development phase; wherein said method uses a novel electrical interconnect (Ref Figi) called launch safety & performance tester [200] wherein, the novel launch safety & performance tester [200] consist of, a microcontroller [111] and the LCD display and battery operated DC Power Supply through battery[100] , an LCD type indicators connected each other via an electrical interconnect with microcontroller [111], input section named as a multi input synchronized data acquisition section containing a dedicated interface as an input interface LCD panel 1 [108] for providing real time threshold setting for stray voltages , an input interface LCD panel 2 [109] for providing real time port configuration for generation of sequence of timing signals between various ports (cyclogram), an input interface LCD panel3[110] for providing real time continuity test requirement which may be momentary , LCD panel 4 [112] an input interface for selection of database using database manager which stores values of previous test profiles and threshold settings ,an output section namely programmable output ports[106] to for interconnecting to launcher unit[201], pass /Fail Indication LCD 5[107] for showing real time results for stray voltage, with LCD 6[114] for pass/fail indication for launch circuit for failure of cyclogram .input lines [113] for acquisition of input signal from launch circuit .signal handling block [119] which act as protection against high input voltages, On/Off/reset switch [116] for On/Off &reset function, LCD 7[115] for continuity pass fail indication .
2. The method and apparatus as said in claim 1, microcontroller [111] having seven logical blocks, first logical block is database manager interface [701] which is a LCD interfaced with memory unit which stores previous stray voltage range .release sequence , continuity test requirement indicative of characteristics of the behavior at various requirements & previous operated history, it has a set of various points on threshold values and sequencing requirement as per aircraft, mathematically maximum permissible stray voltage values and cyclogram .mathematically maximum permissible voltage values, and timing requirement, second logical block is input handling section [702] which is a I/O handling unit which reads user input data , Third logical block is an indication module [705] .fourth logical block is data processing block [704] enables to validates user entered data, fifth logical block is algorithm 1 block [706] detects and provides the ability to detect the presence of 5 stray AC or DC voltage at the launch pin through the use of voltage measurement, sixth logical block is algorithm 2 block [703] generates signal for output port.
3. The method and apparatus as said in claim 1 , wherein Novel io Launch circuit safety and performance tester [200] has dynamic configuration of stray voltage and validation as per received signal, a dedicated interface as LCD panel 1 [108] an input interface for providing real time threshold setting for stray voltages , pass /Fail Indication using LCD panel 5[107] for showing real time results for stray voltage, light on 15 the panel to constantly blink if a no stray voltage is established and to blink if the stray voltage limit is bad , accomplished by a software algorithm that works in .the "real time domain”. 4. The method and apparatus as said in claim 1, wherein Novel 20 Launch circuit safety and performance tester [200] has LCD panel 2 [109] ,an input interface for providing real time port configuration or generation of sequence of timing signals(cyclogram) between various ports , along with pass/fail indication for launch circuit using LCD panel 6[114] for display of pass /fail indication for launch circuit or failure of cyclogram, a 25 light on the external panel to constantly blink if a successful cyclogram is established and to blink if failed cyclogram is established , Each port of input connector from start to end is mapped with array of voltage and cyclogram database, which includes appropriate delay in response or signal [403] at various defined levels by a software algorithm that works in 30 the "real time domain , cyclogram signal which is variable 0-28VDC type of signal .generated by output ports [106] that indicates possibility of signal action
5. The method and apparatus as said in claim 1, wherein Novel 35 Launch circuit safety and performance tester [200] has LCD panel3[110] an input interface for providing real time continuity test requirement which may be momentary .continuity pass fail indication sing LCD panel 7 [115] for status of continuity checks for critical loom or circuit failure and a LCD panel 4 [112] an input interface for selection of database using database 40 manager [112], database manager [112] stores values of previous test profiles and threshold settings .
6. The method and apparatus as said in claim 1, wherein Novel Launch circuit safety and performance tester [200] has voltage overshoot protection circuit[301] prohibits excessive voltage to be transmitted to microcontroller^ 11] , protection circuit[301] has one comparator (C1) which compares with threshold set by microcontroller [111],The signal handling block [119] has a voltage direction protection circuit [303] which has a diode (D1)and ensures that voltage flow in only one direction(REF FIG 10), protection circuit[306] has one comparator (C2) which compares with threshold set by microcontroller [111], voltage overshoot protection circuit[306] which prohibits excessive voltage to be transmitted to launcher [201] ,The signal handling block [119] has a voltage direction protection circuit [304] which has a dlode(D2) and ensures that voltage flow in only one direction ,The signal handling block [119] has impedance matching circuit [305] when there is requirement to transmit signals with certain impedance.
23-Oct-2023/113866/202341072336/Form 2(Title Page)
7. The method and apparatus as said in claim 1, wherein Novel Launch circuit safety and performance tester [200], voltage signal input at LCD panel 1 [108] is as a function of a prescribed limit or threshold and real time acquired values shown in fig 4 ,wherein there is a split display 108(2) for selection of ports and pass /fail limit individually and data entry field 108(1) for data entry, LCD panel 2 [109] is shown in fig 5 .wherein there is a split display 109(2) for selection of sequence .logic and pass /fail criteria individually and data entry filed 109(1) for data entry , LCD panel 3 [110] is shown in fig 6 .wherein there is a split display 110(2) for selection of continuity test logic and pass /fail criteria individually and data entry filed 110(1) for data entry , LCD panel 7 [112] is shown in fig 7 .wherein there is a split display 112(2) for selection of test requirement and pass /fail criteria individually and data entry filed 112(1) for data entry .