1. Title of the invention
A method for generation of digitally controlled barometric speed and altitude signal
2. Field of Invention
The present invention relates to a method comprising of a novel signal simulator for generation of digitally controlled barometric speed & altitude signal and more specifically to a signal simulator for simulating the barometric speed & altitude signal generated by air data computer system.
3. Background of invention
In typical prior art (Ref Fig 2), barometric speed & barometric altitude generation for bench & aircraft testing on ground, have been extremely complicated, in that signals generation were controlled by an external pressure generator connected to Pitot tube, further connected to digital computer named as air data package (ADP)limited for producing signals useful in testing as per actual range of systems. The use of devices viz Pilot static tubes and air data package are well known for computing the speed and altitude of own aircraft. The mechanical pressure generation based systems were complicated due to the extensive sealing required to generate the static and dynamic corresponding to the range of the simulated speed and altitude. Also the pressure generation systems were bulky in size which brings limitation of easy handling. Additionally, the limited range of the pressure generator which did not use digital computers primarily resulted to the fact that they provided inconvenient means for generating a simulated signal. The limitations in prior method of signal simulation, leads to long lead time in testing and often repetition of test. On ground testing, many times required simulation of input to Pitot static tubes, in particular pressure is to be simulated by ground pressure generator, using such devices involves introducing the device with a pressure that is intended to simulate the pressure transmitted by the Pitot device being received while simulating a movement of an aircraft with unknown speed and checking the speed reading taken by the device. These pressure simulators are bulky in size which adequate chances of leakage, also these simulators are expensive, requires more maintenance, periodic calibration, hence for regular testing activities, it is not recommended. In summary, prior art had following drawbacks:
a) Requirement of external pressure source for simulating speed and altitude.
b) No possibility of simulation of voltage signal failure condition.

c) These pressure simulators are bulky in size, which has adequate chances of leakage, also these simulators are expensive, requires more maintenance and periodic calibration
d) Also, due to high pressure set in pressure generator, it is often unsafe for regular use. As, loose contact in rubber pipe carrying air pressure can cause any loose items to blow, or move freely inside " the aircraft due to air leakage.
e) As no pressure values can be stored in the pressure generator, it is not possible to generate a variable output pressure.
These problems were substantially overcome by the system which is
the subject of this invention. 4. Summary of the Invention
The barometric signal simulator which is the subject of this innovation includes means for generating simulated signal having a real time computed voltage and signal validity substantially equal to the signal generated by air data package and duty replication of the pressure source, interface of pressure source with Pitot, Pitot tube, interface with Air data package utilized by the bench & aircraft system to be tested. The digital signal simulator includes a microcontroller as a voltage output computer which accepts the inputs signals specifying the pressure, speed and signal validity of a simulated level and generates as an output voltage & validity signal. The term simulated signal is used to designate an imaginary speed and altitude level which would be in turn reflected by a simulated signal to generate an equivalent signal having the same characteristics of the actual system generated signal which is generated at the output of the actual system. Each voltage level of the simulated voltage signal is processed and utilized by other system to generate a sequence of output voltage (real time varying level) with each voltage level defining the altitude and speed corresponding to a preset signal, each level being determined by the value of the selected signal at the time the associated values of the signal was simulated. This sequence of voltages comprises four voltage level Pscourse , Psfine, Differential Pressure .Impact Temperaturel, and two validity signal .with no delay from the actual signal corresponding to the range of the simulated level. Additionally, the altitude & speed range computer generates rapid changing signal to simulate actual aircraft movement. The value of the simulated signal viz an amplitude of voltage signal, manually selected to control the amplitude of speed and altitude the simulated target signal in accordance with the range of the simulated target values. The output of the signal of the signal

simulator are coupled as inputs to a signal receiver system to generate at the output thereof the simulated values.
Embodiments of the present invention are intended to address all of major above mentioned problems. According to a general aspect of the present invention there is a device adapted to simulate a voltage signal reflecting the pressure and speed equivalent to values from existing Pitot and air data computer system, the device including majorly a microcontroller for processing the input and dedicated keypad for providing altitude input, dedicated keypad for providing speed input, dedicated keypad for providing validity input, dedicated keypad for providing various functions on altitude and speed, dedicated keypad for providing temperature input .dedicated keypad for providing function pause input, dedicated input for calibration data .dedicated output for providing altitude .speed digital readout, dedicated input line for 28VDC derived from existing connector for providing 28VDC input, dedicated and redundant output line for providing computed voltages output. Microcontroller acts as a device for computing the input signal with a predefined algorithm to produce a processed signal simulating the actual computation carried by air data package. The portable simulator include a housing including an output measurement socket. The housing also includes an integrated interface for output as per user input to further processing unit for systems under test. The housing also has magnetic holder for easy hanging. The simulator for simulating the pressure and speed signal is arranged to simulate the equivalent pressure and speed signal usually generated from a actual device. The simulated moving aircraft is being selected from a plurality of options, each of the options representing a valid envelop of aircraft movement profile. The simulator for simulating the signal is arranged to apply a predefined function or values correlated to the aircraft maneuvering profile, the function relation being based on a function selected by a user that corresponds to a profile of aircraft. The simulator for simulating the signal can be a type of direct digital synthesizer arrangement. The direct digital synthesizer arrangement includes a series of direct digital synthesizer connected. Whilst an invention has been described above, the same extends to any inventive combination of features set out above or in the following description. Although illustrative embodiments of an invention are described in detail herein with reference to the accompanying drawings, it is to be understood that the invention is not limited to these precise embodiments. As such, various modifications and variations will be apparent to practitioners skilled in the art.

5. DESCRIPTION OF THE DRAWINGS
Fig1, is a simplified view of the electrical interconnection of each functional block of novel simulator. It contains an electrical interconnect containing a dedicated altitude selection LCD keypad, speed selection LCD keypad, validity selection LCD keypad, Function selection LCD keypad, microcontroller, temperature selection LCD keypad, Function pause LCD keypad, Power ON/OFF switch, power supply safety box with 1 ampere fuse, distribution box, Real time output display, Measurement socket. Novel signal simulator receives 28VDC from existing 28VDC source connected from ADP adapter A, output is available to ADP adapter B. Here series of numeric values related to speed and altitude also can be fed directly using attitude &speed input LCD.
Fig 2, is a simplified view of example of prior art, which contains external power supply source, pressure generator, interconnection of pressure generator with air data computer and interface with main systems for usage.
Fig 3A, is a simplified view of ADP adapter B, ADP connector B , interconnection of microcontroller with ADP adapter B interface .subsequently with main systems for usage .Fig 3B, is a simplified view of interconnection of ADP connector A, ADP adapter A, which contains 28VDC power supply source & ground signal.
Fig 4, is a simplified view of logical block of microcontroller. Each block has a specific function.
Fig 5, is a simplified view of electrical sockets constructed according to the invention and made for measurement for the 28VDC input line from power supply unit, voltage pertains to PScourse, voltage pertaining to Psfine, voltage pertaining to Def pressure, housing using attachment sockets; This shows way for measurement of real time varying output as per input signal.
Fig 6A, is a simplified view of sample envelop of two different aircraft .
Fig 6B, is a simplified view of computation of difference in amplitude per second applicable for speed and applicable for voltage.
Fig 7, is a simplified view of schematic showing an electrical logic and process flow chart for use with determining "voltages in according with the three types of speed inputs viz speed entered manually or speed selection using dedicated function or speed selection using store data /function;

Fig 7A, is a simplified view of schematic showing an electrical logic and process flow chart for use with determining "voltages in according with the three types of altitude inputs viz altitude entered manually or altitude selection using dedicated function or altitude selection using store data /function;
Fig 8, is a simplified view of schematic showing a state machine used in association with determining speed equivalent voltage in association with an algorithm;
Fig 9, is a simplified view of schematic showing schematically shows a state machine used in association with determining Outliners and Removal;
Fig 10a, is a simplified view that shows a perspective view of the LCD keypad panel with a display and input device for entering required speed value as per profile coupled subsequently coupled with microcontroller, maximum three-digit data can be entered, also it facilities to enter duration of each entered value, keep entering data will save full speed profile ;
Fig 10b, is a simplified view that shows a perspective view of the LCD keypad panel with a display and input device for entering required altitude value as per profile coupled subsequently coupled with microcontroller, maximum three-digit data can be entered, also it facilities to enter duration of each entered value, keep entering data will save full altitude profile ;
Fig 10c, is a simplified view that shows a perspective view of the LCD keypad panel with a display and input device for entering required validity value as per profile coupled subsequently coupled with microcontroller, maximum three 0/1 digit data can be entered;
Fig 10d, is a simplified view that shows a perspective view of the LCD keypad panel with a display and input device for entering required function for speed or altitude or both as per profile coupled subsequently coupled with microcontroller, maximum three types of function data can be entered, also it facilities to enter duration of each entered duty cycle, amplitude values, keep entering data will save full speed, altitude profile;
Fig 10e, is a simplified view of shows a perspective view of the LCD display panel with a display and output device for displaying speed or altitude or both value as per profile coupled subsequently coupled with microcontroller, it displays outliners or real time data;
Fig 10f, is a simplified view of shows a perspective view of the LCD display keypad with a display and input device for displaying selection of pause

/unpause speed or altitude or both value as per profile coupled subsequently coupled with microcontroller;
Fig 10g, is a simplified view of shows a perspective view of the LCD display keypad with a display and input device for displaying selection of save options of function or data for speed or altitude or both value as per profile coupled subsequently coupled with microcontroller;
Fig 10h, is a simplified view of shows a perspective view of the LCD keypad with a display and input device for displaying selection of calibration data as a input options of linear function for speed or altitude or both value as per profile coupled subsequently coupled with microcontroller;
Fig 11, is a simplified view of example of one instance of varying input using speed or altitude selection keypad. This shows that for example dynamic function selection for speed or altitude.
Fig 12, is a simplified view of example of one instance of varying output selectable using speed or altitude selection keypad for speed or altitude. This shows varying output as per input signal.
6. Detailed Description of the Invention
Fig. 1 is a functional block diagram of the novel signal simulator [200]. The interfaces of the novel signal simulator are shown in the block diagram (Fig 1). The novel signal simulator [200] contains, a multi input synchronized panel containing a dedicated altitude selection LCD keypad [116], speed selection LCD keypad [117], validity selection LCD keypad [118], Function selection LCD keypad [120], Microcontroller [111], temperature selection LCD keypad [121], Function pause LCD keypad [124], Power ON/OFF switch [101], power supply safety box with 1 ampere fuse [106], power distribution box [110], Real time output display [123] for display of real time altitude, speed & voltage values, junction box [107], measurement socket[105] .function data /saver LCD keypad [122],calibration input LCD keypad [129],Type of aircraft selection LCD keypad[119].Novel signal simulator [200] receives 28VDC via ADP adapter A [100] from existing 28VDC source of an aircraft and processed output is provided to aircraft via ADP Adapter B [103]. Dedicated altitude selection LCD keypad [116], speed selection LCD keypad [117], validity selection LCD keypad [118], Function selection LCD keypad [120], Function pause LCD keypad [124], calibration input LCD keypad [129], type of aircraft selection LCD keypad [119], temperature selection LCD keypad [121] is coupled as an input to the signal simulator [200] mainly to microcontroller

[111]. The junction box [107] and real time display output [123] acts as an output of microcontroller [111]. The novel signal simulator [200] include an embedded power distribution unit [110] for supply of 28VDC which is a reference power supply used as a voltage input for usage as a voltage input on subsequent electrical interconnect. This simulator does not require any battery or commercial supply of 230 VAC. Therefore, as long as reference voltage is available as input, the simulator can be used and allows further circuitry to host and process signals. As mentioned, the embedded power supply unit contains a power supply safety box with 1 Amp Fuse [106] for supply of 28 VDC, an operable single pole toggle switch named as power ON/OFF switch [101]. Upon power ON condition ,28 VDC is supplied to power supply safety box with 1 Amp Fuse [106]. Fig 3A shows ADP connector B [131] is connected in series with main system [132] and ADP adapter B[103].The interface ADP adapter B [103] receives signals from microcontroller [111]. Fig 3B shows ADP connector A [130] ,is connected in series with ADP adapter A[100].The interface ADP adapter A [100] .receives 28VDC & ground signal from ADP connector A [130].In detail .referring further to FIG. 1 the novel simulator [200] includes components arranged to perform specific function on circuit boards viz, the first component of circuit board is a dedicated altitude selection LCD keypad [116] includes a LCD type input display for providing required altitude or set of altitudes for simulation further input is connected to a microcontroller [111],further circuit board has a dedicated speed selection LCD keypad [117] includes a LCD type input display for providing required speed or set of speed for simulation further input is connected to a microcontroller [111] , further circuit board has a dedicated validity selection LCD keypad [118] includes a LCD type input display for providing required validity for simulation further input is connected to a microcontroller [111], further circuit board has a dedicated function selection LCD keypad [120] includes a LCD type input display for providing required function[120] on speed & altitude for simulation .further input is connected to a microcontroller [111], further circuit board has a dedicated function saver LCD keypad [122] includes a LCD type input display for providing saving function for repetitive function for simulation further input is connected to a microcontroller [111], further circuit board has a dedicated function.pause LCD keypad [124] includes a LCD type input display for providing required pause function for running function for simulation further input is connected to a microcontroller [111], further circuit board has a dedicated temperature selection LCD keypad [121] includes a LCD type input display for providing required temperature for

simulation further input is connected to a microcontroller [111], further circuit board has a dedicated calibration selection LCD keypad [129] includes a LCD type input display for providing required calibration for simulation further input is connected to a microcontroller [111] , further circuit board has a dedicated function pause LCD keypad [124] includes a LCD type input display for providing required for function pause for simulation further input is connected to a microcontroller [111], further circuit board has a dedicated function pause LCD keypad [124] includes a LCD type input display for providing required function pause function for simulation further input is connected to a microcontroller [111], further circuit board has a dedicated type of aircraft selection LCD keypad [119] includes a LCD type input display for providing aircraft type selection function for simulation further input is connected to a microcontroller [111], further circuit board has a dedicated type of Real time Output display LCD display[123] includes a LCD type input display for providing output function after simulation connected to a microcontroller [111], further circuit board has a dedicated type microcontroller [111] includes a microcontroller for processing above signals, measurement socket [105] for measurement of 28VDC input and output signals, junction box [107]for buffering the voltage , ADP connector B [131] is connected in series with junction box[107] for receiving signals from microcontroller [111],ADP ADP adapter A[100] for receiving 28VDC. The multi voltage synchronized signal selection is done by function selection LCD keypad [120] and output is processed and generated by microcontroller [111] .further coupled as an output to a junction box [107] circuit and in turn supply to a measurement socket [105]. Measurement socket [105] has two phase values for measurement one is raw 28VDC input and other is voltages are computed by microcontroller [111]. Microcontroller [111] generate voltages as per input from dedicated altitude selection LCD keypad [116], speed selection LCD keypad [117], validity selection LCD keypad [118], Function selection LCD keypad [120]. Further signal type with the duration determined by the function selection LCD display [120]. Function saver LCD keypad [122] can be selected for save option which is preferably, very specific repetitive function which is used to generate repetitive pulse, which are decoded to generate voltage output or analog output signals. When the analog output counter reaches a specific level, it is reset to initial value and the cycle is repeated for subsequent cycles. For example, the first set of values are processed by the microcontroller [111] circuit to generate a set of voltages which fed voltage to junction box [107]. The junction box [107] distributes signals which is coupled to the ADP Adapter B. A speed selection LCD

keypad [117], as in FIG 10a shows a LCD type input device for speed and simulation duration for use with a microcontroller [111] of the invention. A speed selection LCD keypad [117] couples to microcontroller [111], as shown in figl, and a electrical interconnect completes the circuit between speed selection LCD keypad [117] and a microcontroller [111] to provide speed signal to the microcontroller [111]. In embodiment, speed selection LCD keypad [117] ,as shown in fig 10a ,is a three digit input line for value entry and in case required duration speed value in seconds of to help tester to provide simulation input .FIG. 1 shows speed selection LCD keypad [117] and a microcontroller [111] coupled together. FIG. 10a illustrates a preferred embodiment of the invention, not to scale, where keyboard arrangement associated with a speed selection LCD keypad [117] with an Enter option. In this way, real time data entry is possible, as microcontroller [111] is programmed to read keypad until 28VDC is available. Those skilled in the art should appreciate that value changes can be made in real time within the above description without departing from the Scope of the invention, including a simulating device with a single dedicated keypad that has an extension to couple values the in real time from microcontroller [111] until the 28VDC is removed. Real time data entry is extended for all type of inputs and all parameters.An Altitude selection LCD keypad [116] FIG 13B shows which is a LCD type input device for altitude and simulation duration for use with a microcontroller [111] of the invention. An Altitude selection LCD keypad [116] couples to microcontroller [111], as shown in figl, and a connecting electrical interconnect completes the circuit between Altitude selection LCD keypad [116] and a microcontroller [111] to provide altitude signal to the microcontroller [111]. In embodiment, Altitude selection LCD keypad [116], as shown in fig 10b, is a three digit input line for value entry and in case required duration altitude value in seconds of to help tester to provide simulation input .FIG. 10b shows Altitude selection LCD keypad [116] and a microcontroller [111] coupled together. FIG. 13b illustrates a preferred embodiment of the invention, not to scale, where keyboard arrangement associated with an Altitude selection LCD keypad [116]. Specifically, in FIG. 10b, two input line, with an Enter option, is shown. Once data is fed to a tester, electrical interconnect, connecting to microcontroller [111], thereby processing the inputs. In this way, real time data entry is possible, as microcontroller [111] is programmed to read keypad until 28VDC is available. Validity selection LCD keypad [118] FIG 10c shows which is a LCD type input device for validity for use with a microcontroller [111] of the invention. An validity selection LCD keypad [118] couples to

microcontroller [111], as shown in figl, and a connecting electrical interconnect completes the circuit between validity selection LCD keypad [118] and a microcontroller [111] to provide validity signal to the microcontroller [111]. In embodiment, validity selection LCD keypad [118] ,as shown in fig 13c ,is a three digit separate input line for value entry to help tester to provide simulation input .FIG. 1 shows validity selection LCD keypad [118] and a microcontroller [111] coupled together. FIG. 10c illustrates a preferred embodiment of the invention, not to scale, where keyboard arrangement associated with an validity selection LCD keypad [118]. Specifically, in FIG.10c, two input line, with an Enter option, is shown. Once data is fed by a tester, electrical interconnect, connecting to microcontroller [111], to monitor entered value, thereby processing the inputs. In this way, real time data entry is possible, as microcontroller [111] is programmed to read keypad until 28VDC is available. A function selection LCD keypad [120] FIG 10d shows which is a LCD type input device for function simulation for altitude or speed which includes entry of duty cycle and amplitude for use with a microcontroller [111] of the invention. A function selection LCD keypad [120] couples to microcontroller [111], as shown in figl, and a connecting electrical interconnect completes the circuit between function selection LCD keypad [120] and a microcontroller [111] to provide functional simulated signal to the microcontroller [111]. In embodiment, function selection LCD keypad [120],as shown in fig 10d ,is a split display for value entry to help tester to provide simulation input .FIG. 1 shows function selection LCD keypad [120] and a microcontroller [111] coupled together. FIG. 10d illustrates a preferred embodiment of the invention, not to scale, where keyboard arrangement associated with a function selection LCD keypad [120]. Specifically, in FIG.IOd, two input line, with an Enter option, is shown. Once data is fed by a tester, electrical interconnect, connecting to microcontroller [111], to monitor entered value, thereby processing the inputs.' In this way, real time data entry is possible, as microcontroller [111] is programmed to read keypad until 28VDC is available. A real time output LCD display [123] FIG 10e which is a LCD type output device for display of real time value or outliners for altitude and speed from microcontroller [111] of the invention. A real time output LCD display [123] couples to microcontroller [111], as shown in figl, and a connecting electrical interconnect completes the circuit between real time output LCD display [123] and a microcontroller [111] to provide display output from the microcontroller [111]. In embodiment, real time output LCD display [123],as shown in fig 10e ,is a split display with separate output line for

value and outliners help tester to provide simulation output FIG. 1 shows validity selection LCD keypad [118] and a microcontroller [111] coupled together. FIG. 13e illustrates a preferred embodiment of the invention, not to scale, where keyboard arrangement associated with real time output LCD display [123] Specifically, in FIG.lOe, two input line, with an Enter option, is shown. Once data is fed by a tester, electrical interconnect, connecting to microcontroller [111], to monitor entered value, thereby processing the inputs. In this way, real time data entry is possible, as microcontroller [111] is programmed to read keypad until 28VDC is available.
A function pause LCD keypad [124] FIG 13f. shows which is a LCD type input device for real time pausing of value or functions for altitude and speed from microcontroller [111] of the invention. A real time function pause LCD keypad [124] couples to microcontroller [111], as shown in figl, and a connecting electrical interconnect completes the circuit between real time function pause LCD keypad [124] and a microcontroller [111] to provide function /data pause input to the microcontroller [111]. In embodiment, real time function pause LCD keypad [124] as shown in fig 13f ,is a split display with separate output line for speed and altitude help tester to provide simulation output .FIG. 1 shows function pause LCD display [124] and a microcontroller [111] coupled together. FIG. 10f illustrates a preferred embodiment of the invention, not to scale, where keyboard arrangement associated with real time function pause LCD keypad [124] Specifically, in FIG.IOf, two input line, with an Enter option, is shown. Once data is fed by a tester, electrical interconnect, connecting to microcontroller [111], to monitor entered value, thereby processing the inputs. In this way, real time data entry is possible, as microcontroller [111] is programmed to read keypad until 28VDC is available. A function/data saver LCD keypad [122] FIG 10g shows which is a LCD type input device for real time function/data saving of value or functions for altitude and speed from microcontroller [111] of the invention. A real time function/data saver LCD keypad [122] couples to microcontroller [111], as shown in figl, and a connecting electrical interconnect completes the circuit between real time function/data saver LCD keypad [122] and a microcontroller [111] to provide function /data save input to the microcontroller [111]. In embodiment, real time function/data saver LCD keypad [122] as shown in fig 13f ,is a split display with separate output line for speed and altitude help tester to provide simulation output .FIG. 1 shows function/data saver LCD keypad [122] and a microcontroller [111] coupled together. FIG. 10g illustrates a preferred embodiment of the

invention, not to scale, where keyboard arrangement associated with real time function/data saver LCD keypad [122] Specifically, in FIG.10g, two input line, with an save option, is shown. Once data is fed by a tester, electrical interconnect, connecting to microcontroller [111], to monitor entered value, thereby processing the inputs. In this way, real time data entry is possible, as microcontroller [111] is programmed to read keypad until 28VDC is available. A calibration input LCD keypad [129] FIG 13h shows which is a LCD type input device for real time entry of calibration value for altitude and speed from microcontroller [111] of the invention. A real time calibration input LCD display [129] couples to microcontroller [111], as shown in figl, and a connecting electrical interconnect completes the circuit between calibration input LCD display [129] and a microcontroller [111] to provide entry of calibration value input to the microcontroller [111]. In embodiment, calibration input LCD keypad [129] as shown in fig 13f, is a split display with separate output line for speed and altitude help tester to provide simulation output. FIG. 1 shows calibration input LCD display [129] and a microcontroller [111] coupled together. FIG. 10h illustrates a preferred embodiment of the invention, not to scale, where keyboard arrangement associated with real time calibration input LCD keypad [129]. Specifically, in FIG.10g, two input line, with a save option, is shown. Once data is fed by a tester, electrical interconnect, connecting to microcontroller [111], to monitor entered value, thereby processing the inputs. In this way, real time calibration data entry is possible, as microcontroller [111] is programmed to read keypad until 28VDC is available. A type of aircraft selection input LCD keypad [122] FIG 13i shows which is a LCD type input device for real time entry of aircraft type value for selection of particular aircraft to microcontroller [111] of the invention. A real time aircraft type input LCD keypad [122] couples to microcontroller [111], as shown in figl, and a connecting electrical interconnect completes the circuit between calibration input LCD keypad [129] and a microcontroller [111] to provide entry of aircraft type value input to the microcontroller [111]. In embodiment, aircraft type value input LCD keypad [122] as shown in fig 13i, is a split display with separate output line for type of aircraft entry help tester to provide simulation output. FIG. 1 shows type of aircraft input LCD keypad [122] and a microcontroller [111] coupled together. FIG. 10i illustrates a preferred embodiment of the invention, not to scale, where keyboard arrangement associated with real time type of aircraft input LCD keypad [122]. Specifically, in FIG.IOi, two input line, with a save option, is shown. Once data is fed by a tester, electrical interconnect, connecting to microcontroller [111], to monitor

entered value, thereby processing the inputs. In this way, real time calibration data entry is possible, as microcontroller [111] is programmed to read keypad until 28VDC is available. A temperature input LCD keypad [129] FIG 10j shows which is a LCD type input device for real time entry of outside temperature value for selection of particular aircraft to microcontroller [111] of the invention. A real time aircraft type input LCD keypad [122] couples to microcontroller [111], as shown in figl, and a connecting electrical interconnect completes the circuit between temperature input LCD keypad [129] and a microcontroller [111] to provide entry of outside temperature value input to the microcontroller [111]. In embodiment, outside temperature value input LCD keypad [129] as shown in fig 13i, is a split display with separate output line for outside temperature entry help tester to provide simulation output. FIG. 1 shows a temperature input LCD keypad [129] and a microcontroller [111] coupled together. Microcontroller [111] receives inputs entered by input device and generates signals indicative of speed and altitude. Microcontroller also processes the input signals to simulate desired profile. Preferably, profile such as speed information so that a limited simulation made of environmental conditions. Microcontroller [111] has four logical block, one speed signal synthesizer block [700], Altitude signal synthesizer block [701], speed algorithm computation block [706], altitude algorithm computation block [707], speed data base [708] and altitude database [709]. With reference to FIG. 4, microcontroller logical block speed signal synthesizer block [700] is three types of speed input handler (Ref Fig 7) performs speed verification and outliners removal from inputs. In the preferred embodiment, resulting data items are sent to data speed algorithm computation block [706]. Sent data speed algorithm computation block [706] is ensured in a way that the outliners are removed and can select only desired data for processing. It preferably performs data processing, such as in converting total data. Speed algorithm computation block [706] thus process data for the plurality of inputs. With reference to FIG. 4, microcontroller logical block altitude signal synthesizer block [701] is three types of speed input handler (Ref Fig 7) performs altitude verification and outliners removal from inputs. In the preferred embodiment, resulting data items are sent to data altitude algorithm computation block [707], Sent data altitude algorithm computation block [707] is ensured in a way that the outliners are removed and can select only desired data for processing. It preferably performs data processing, such as in converting total data. Altitude algorithm computation block [707] thus process data for the plurality of inputs. Data stored as a set of

aircraft envelop (Ref fig 6A) in this embodiment are collated and stored in a database so as to characterize a set of possible speed using speed database [708] and altitude in altitude database [709] of possible altitude not varying with time. For example, by looking at magnitude of speed and altitude of database data for a particular event provides detail as to whether the data is falling in envelop. As discussed above, embodiment of the invention includes a barometric speed simulator. FIG. 7 and FIG. 8 collectively illustrate the preferred embodiment for computing and determining speed in accord with the invention. An embodiment configured to measure speed uses a microcontroller as state machine, and FIG. 7 depicts electrical and process steps [700] for processing three types of speed input signals to determine an "voltages" accordingly. FIG.8 illustrates state machine logic used in reporting this voltage. By way of example, FIG. 8 shows that outliners are preferably determined prior to determining voltages, as validation is meaningful in certain applications as aircraft has a defined envelope when the aircraft is moving and non-stationary.
More particularly, FIG. 7 depicts real-time input processing steps of a speed computation algorithm. Speed data received via any of three input lines, first set of speed input manually using Speed selection LCD keyboard [117] or Function selection LCD keyboard [120] or function/data saver LCD display [122]. Respective inputs are stored in store speed profile1[303], store speed profile2[304], store speed profile3[305]. Values stored in speed profile 1[303] goes through verify store profile with data base [306] checks that speed entered is within the aircraft specific envelop. This limit filter serves to limit filtered data at this step. Further data goes to verify store speed profile with real time change [307] which will check maximum possible changes possible is within the limits the difference signal possible is next forwarded (Ref fig 6B). Remaining values are treated as outliners using filtering through respective section and goes to real time output LCD display [123] using remove speed outliners [308]. Valid speed profile values stored in speed profile [310], Set of validity input is fed through validity selection LCD keyboard [118]. Based on valid speed profile [310], voltage is derived from a speed computation block [706] in the form of continuous voltage. Two signal values are produced from speed computation block [706]. More particularly, data from verify speed profile [307] is bifurcated along one signal path through valid speed profile [310] and other through remove speed outliners [308], as shown in fig 8. Two comparators compare speed level to aircraft envelope with thresholds, to generate valid signals used to identify possible valid signals.

In further path, real time filter operation, first filter at step to check maximum possible instantaneous change. These filters generate valid "confidence' data used to assess valid speed values. Finally, a computer [706], evaluates signals to generate voltage values. In plurality the similar method is used for generation of voltage related to altitude signals. FIG. 8 schematically shows flow chart for computation using microcontroller [706] in accord with the invention. Simulation has included several processes, including look for input data, store valid input speed data, voltage computation, display, determining output voltages. Logic.flow between above processes occurs as illustrated and annotated according to the preferred embodiment of the invention as in fig 9. The advantage of simulation as per above process along path in fig 9 is that it checks signal fluctuations that do represent real events, which may occur with an actual profile of aircraft. A speed signal described in FIG. 7 and FIG. 8 is preferably insensitive to the particular axis. In accord with the invention simulation has included several processes, including look for input data, store valid input altitude data, voltage computation, display , determining output voltages . The advantage of simulation as per above process along path in fig 6B is that it checks signal fluctuations that do represent real events, which may occur with an actual profile of aircraft. A signal described in FIG. 6B is preferably insensitive to the particular axis. In illustrative example of operation of computation of outliners ,FIG. 9 shows a flow chart for computation of outliners and valid data in real time method for speed data. The simulated signal is supplied by the novel signal simulator [200], to be used as it is synchronized in altitude and speed and validity, as the normally transmitted by the actual electrical interconnect. Although in one example, the simulated signal using function selection may be illustrated as a square wave pulse, simulating fixed value with duty cycle, this signal can be otherwise simulated as varying wave which has a varying duty cycle using dedication function selector [120]. The varying wave can be chosen in a convenient way to illustrate this signal because changing the duty cycle does change the operation of the signal simulator functions. This is possible because the signal simulator [200] automatically output the duty cycle of the synchronized signal as per selected function. For example, typical cycles of the synchronized signal are illustrated and arbitrarily labeled "1st section" and "2nd section and so on." The voltages of the multi voltage synchronized signal labeled 1st section have been further reflected by varying values of voltages ranging from zero onwards till values being repeated for the 2nd section. After section 1 has expired, pulse repeat algorithm inside microcontroller will generate an output pulse,

which is repetitive, which is coupled to output of junction box [107] generates a signals, which is coupled to the ADP adapter interface B[103]and measurement socket [105]. The next set of the multi voltage synchronizing signal is detected by the microcontroller [111], however function pause LCD keypad [124] can pause the complete set of function instantaneously, till it is selected again. Again selection of function pause LCD keypad [124], reinitializes voltage generation, presets the further circuit to generate same signal. This same sequence of generation, if it is repeated, can be saved using function saver LCD keypad [122]. When function from function saver LCD keypad [122] is selected, first cycle of the multi voltage synchronizing signal is generated, microcontroller [111] select function and generates a set of voltage which is buffered at junction box [107]. Initialization of signal simulator [200], presets the circuits. Further upon selection of function this circuit to generate multi voltages. When the time interval corresponding to pulse width expires, the microcontroller [111] generates a repetitive output pulse which is also coupled to junction box [107],The simulator [200] circuits through an electrical interconnect , preset down voltages with the output of the microcontroller counters decoded to re generate a voltage when a voltage value of zero is reached. Various functions can be implemented using function selection LCD keypad [120]. As previously explained, the synchronized signal is also coupled to the input of microprocessor [111] and junction box [107], ADP adapter B [104], measurement socket [105] receives the output signals of the microcontroller circuit [111]. For example, during the duration of the first pulse of the first cycle of the synchronized voltage signal, a counter which is part of the voltage generation circuit is enabled to count as per generated signal specifying the duration of the first voltage of the 1 st cycle of the synchronized signal. During the time interval between the trailing edge of the first pulse of the 1st cycle of the synchronized signal, and the rising edge of the second pulse of the 1st cycle of this signal, the voltages are generated. This can be stored using function saver LCD keypad [122]. Display voltage level of the rising edge of the second pulse of the 1st cycle of the synchronized signal can be real time displayed in Real time output display [123]. The output as a freewheel counter, causes this counter to be reset and start counting again with the next number in the counter being stored in the memory between the trailing edge of this pulse and the leading edge of the subsequent pulse of the 1st cycle of this signal and so on. This procedure is repeated sequentially till power is available from 28VDC source [100]. This has additional feature that the memory of

microcontroller [111] have separate storage for predefined functional. After the 1st first cycle of the synchronizing signal is completed, the same sequence of pulse width generation and output cycles is repeated for the 2nd and subsequent cycles of the synchronizing signal as per function. Function may of type triangular .square or constant function .It should be noted that the output voltages generated by microcontroller [111] as a synchronized signal is determined by the instantaneous value of the pressure altitude selected by altitude selection LCD keypad [116] and speed selection LCD keypad [117] signal ,at the time the corresponding values of the pressure and speed is detected by the microcontroller [111] circuit and it computes the output as per user defined algorithm and calibration files. The value of the voltage signal from the microprocessor[111] is dependent of input selection viz function selection LCD keypad [120], temperature selection LCD keypad [121] and validity selection LCD keypad [118]. It should also be noted that the output interval associated with any particular voltage is representative of the function selection using function selection LCD keypad [122] for the profile simulation and that this range changes continually based on the profile range. Additionally, the simulator automatically tracks changes of the synchronized output signal using real time output display [123], The operation of the first cycle of the signal simulator, as discussed above, is repeated for the 2nd and subsequent cycles of the synchronized signal. The signal simulator is intended for use with aircraft setup or Rig setup. This being the case, the output controlled by microcontroller [111] produces an voltage signal and validity signal. The voltage and validity signals are coupled output signals and altitude and speed as control signals to a signal generator to generate at the output terminal thereof a voltage signal having an amplitude and a repetition frequency respectively dependent on the range and type of the simulated selection. The output voltage is a indirect function of the input speed and attitude. The voltage signals are functioned in accordance with these mathematical relationships using conventional model. The synchronized voltage signal {FIG. 1) and the validity signal from the microcontroller [111] are coupled as output signals to a distribution box [107]. In response to these signals, the main system generates as an output a simulated signal having the proper value viz amplitude, and speed to be simulated as the expected range. This permits the receivers viz ADP Adapter B[103] for data processing and the complete system to be completely tested using simulated signals. FIG. 11 &12 is a more detailed plots of the signal simulator. In conventional method of testing ,a lot of external equipment

required with no preset values which can be preset to a value specified by
the user. The output signal of the microcontroller [111] is an analog signal
specifying magnitude of the pressure altitude and speed and an
Increase/decrease signal possibilities are coupled as inputs. The
microcontroller [111] generates a pulse train whose frequency is the output
of the function selector [120] as an input signal. The electrical interconnect
as in figl, including microcontroller [111] and LCD interface is well known
conventional circuits. Therefore, no detailed design is illustrated. The
output signal of various signal type and the type input signal are coupled
to a function selector [120], This generates at the output inclusive of
varying speed which specifies the instantaneous speed of the aircraft to be
simulated. The range of the simulated velocity is either constant or
increasing. The output signal of the speed either increments or
decrements speed counter depending on the time as the
increase/decrease signal. The increase/decrease signal is a multiple valued analog signal. The output of the distribution box[107] is coupled with ADP adapter B [104] coupled to the input of further processing unit. The speed may be as per aircraft movement dynamic up/down. An altitude received as input, output the voltage value accordingly and the range of the altitude is simulated. This generates at the output of the microcontroller [111], a signal which specifies the instantaneous value of the altitude to be simulated. The altitude in function selection[120] may remain constant, increase or decrease as determined by the output signal of the function selection[120].This enables the simulator [200] can be model as a real aircrfat profile. The microcontroller [111] is connected to user interface components including a various LCD keypad having LCD display and measurement sockets [105]. The user defined equation is effectively implemented by instructions processed by components of the simulator [200] using speed algorithm computation block[706 ] and using altitude algorithm computation block[707 Jin order to produce a signal simulating the received signal reflecting an analogue of a certain speed and altitude. In addition to allowing the speed and altitude of the simulated profile to be chosen. Embodiment also has interface as a calibration LCD display [116] .which is used to impose calibration values on real time voltage output As using real time display input values viz speed and pressure along with output values viz voltages can be seen real time . Hence in case, there is any discrepancy found in output voltage with respect to input, it can be corrected using calibration values. Simulator [200] is constructed according to the invention. A portable rigid outer housing Surrounds internal elements mentioned in, FIG. 1, which provide

easy functionality for device. A magnetic element couples with device so that device is easily attached to.metal objects. Accordingly, device is easily attached to", or removed from, object.
a. Step of operation for simulator:
Step 1, identify the altitude and speed profile required for testing.
Step2, Identify the function type required for simulation. Example many
times it is required that constant speed and constant altitude is to be
simulated or varying in nature. So it is possible to simulate using this
simulator.
Step 3, Establish infer connection using standard interface for signals
mentioned in step 1 and 2.
Step 4, Connect power port ADP adapter A of connector to simulator at
Rig or aircraft (28VDC).
Step 5, The store the function which is frequently required.
Step 6, Carry out operation on system so that output signal will be
generated and observe result on real time output LCD display.
Step 7, Carry out function pause function, if it is required to see system
behavior at particular time.
b. Details of simulation achieved:
b.1 This simulator has feature of generation of voltage corresponding to
particular pressure altitude. Practically, altitude is a function of pressure ,in
practical condition actual pressure was exposed in aircraft .however here
the voltage is simulated as per altitude directly .
b.2 This simulator has feature of generation of voltage corresponding to
particular speed. Practically, speed is a function of pressure, in practical
condition actual pressure was exposed in aircraft, however here the
voltage is simulated as per speed directly.
b.3 Other feature is setting of validity bit along with altitude and speed. In
practical condition, it was not possible to simulate validity.
b.4.This simulator has additional feature of operation using 28VDC
available on aircraft mating connector ADP adapter A, hence no external
power is required. This simulator does not need any battery or commercial
supply to operate the tester as it can be operated through available
system supply.
b.5 This tester has provision of function selection feature. This simulator
has feature of generation of voltage corresponding to Particular speed and
particular altitude. This altitude and speed can be varying in nature based
on function selection.

b.5 This tester has provision of function storage feature. This simulator
has feature of generation of voltage corresponding to Particular speed
and particular altitude. This altitude and speed can be varying in nature
based on function selection. If is required to use a particular function
multiple time, this function storage feature can be used. This will help to
simulate a particular aircraft profile.
b.6. The simulator has real time voltage monitoring feature. This feature
helps to monitor output of microcontroller in real time.
b.7. The simulator has real time voltage pause feature. This feature
helps to analyses the complete system behavior at a particular
movement.

Title: A method for generation of digitally controlled barometric speed and altitude signal
CLAIMS
We Claim
1. A method and apparatus for generation of digitally controlled barometric speed & altitude signal ; wherein said method uses a novel electrical interconnect (ref Fig1) called as a novel simulator[200] wherein, novel simulator[200] comprises of, a multi input synchronized panel containing a dedicated altitude selection LCD keypad [116], speed selection LCD keypad [117], validity selection LCD keypad [118], Function selection LCD keypad [120], Microcontroller [111], temperature selection LCD keypad [121], Function pause LCD keypad [124], Power ON/OFF switch [101], power supply safety box with 1 ampere fuse [106], power distribution box [110], Real time output display [123] for display of real time altitude, speed & voltage values, junction box [107], measurement socket[105] .function data /saver LCD keypad [122],calibration input LCD keypad [129],Type of aircraft selection LCD keypad[119].
2. The method and apparatus in claim 1, wherein the first component of circuit board is a dedicated altitude selection LCD keypad [116] includes a LCD type input display for providing required altitude or set of altitudes for simulation further input is connected to a microcontroller [111],further circuit board has a dedicated speed selection LCD keypad [117] includes a LCD type input display for providing required speed or set of speed for
. simulation further input is connected to a microcontroller [111] , further circuit board has a dedicated validity selection LCD keypad [118] includes a LCD type input display for providing required validity for simulation further input.is connected to a microcontroller [111], further circuit board has a dedicated function selection LCD keypad [120] includes a LCD type input display for providing required function[120] on speed & altitude for simulation .further input is connected to a. microcontroller [111], further circuit board has a dedicated function saver LCD keypad [122] includes a LCD type input display for providing saving function for repetitive function for simulation further input is connected to a microcontroller [111], further circuit board has a dedicated function pause LCD keypad [124] includes a LCD type input display for providing required pause function for running function for simulation further input is connected to a microcontroller [111], further circuit board has a dedicated temperature selection LCD keypad [121] includes a LCD type input display for providing required temperature for simulation further input is connected to a microcontroller [111], further circuit board has a dedicated calibration selection LCD

keypad [129] includes a LCD type input display for providing required
calibration for simulation further input is connected to a microcontroller
[111] , further circuit board has a dedicated function pause LCD keypad
[124] includes a LCD type input display for providing required for function
pause for simulation further input is connected to a microcontroller
[111], further circuit board has a dedicated function pause LCD keypad
[124] includes a LCD type input display for providing required function
pause function for simulation further input is connected to a microcontroller
[111], further circuit board has a dedicated type of aircraft selection LCD
keypad [119] includes a LCD type input display for providing aircraft type
selection function for simulation further input is connected to a
microcontroller [111], further circuit board has a dedicated type of Real
time Output display LCD display[123] includes a LCD type input display
for providing output function after simulation connected to a
microcontroller [111], further circuit board has a dedicated type microcontroller [111] includes a microcontroller for processing above signals, measurement socket [105] for measurement of 28VDC input and output signals, junction box [107]for buffering the voltage , ADP connector B [131] is connected in series with junction box[107] for receiving signals from microcontroller [111],ADP adapter A[100] for receiving 28VDC; The multi voltage synchronized signal selection is done by function selection LCD keypad [120] and output is processed and generated by microcontroller [111] .further coupled as an output to a junction box [107] circuit and in turn supply to a measurement socket [105]; measurement socket [105] has two phase values for measurement one is raw 28VDC input and other is voltages are computed by microcontroller [111].
3. The method and apparatus in claim 1, wherein it has data base as per type of aircraft; Data stored as a set of aircraft envelop (Ref fig 6A) stored in a database so as to characterize a set of possible speed using speed database [708] and altitude in altitude database [709] of possible altitude not varying with time; by looking at magnitude of speed and altitude of database data for a particular event provides detail as to whether the data is falling in envelop; use the same for filtering the data.
4. The method and apparatus in claim 1, wherein it has real time filter to verify speed and altitude profile with real time change [307] which check maximum possible changes possible is within the limits (Ref fig 6B) for filtering the data.