1. Title of the invention
A method for take-off control of an aircraft in case of engine fire emergency.
2. Field of Invention
The present invention relates to a method comprising of a novel take off controller for automatic abandonment of aircraft take off in case of engine fire using real time computed safe distance based on Global positioning system (GPS) data .runway mapping data .aircraft speed .aircraft acceleration , weight on wheels and radio altimeter height data .
3. Background of invention
In typical prior art, in case of detection of engine fire during takeoff phase, manually operatable aircraft controls were selected by Pilot to call off the flying decision. When aircraft is set to take off and it is in takeoff roll phase, i.e. when the throttle lever is set to the takeoff roll position and landing gears are still, in locked down position and any engine fire is detected, under such circumstances, the effort of reducing the aircraft speed and subsequently parachute release operation can be extremely reduced by the usage of automatic takeoff controller. This controller is highly recommended during practice sorties of trainee Pilots. Pilot can select auto mode using a toggle on-off switch mounted on cockpit to select whether automatic or manual control is required in case of fire. Along with this switch, one novel system controller using various inputs like throttle . input, aircraft current speed input, forward acceleration input and weight on wheels inputs, height computed by radio altimeter are processed, making the task of aircraft speed control automatic in place of any selection by the Pilot. This controller provides an excellent safety handling qualities during takeoff roll, with the benefit of not needing or using any manual intervention making a vital safety-critical requirement. A novel control system for controlling an engine control provided to an engine includes cut off of throttle position and operating a parachute when aircraft

is in safe distance on runway. The controller calculates, based.on engine fire sensor input and present aircraft speed according to an operational state of the aircraft. In novel controller, to control the aircraft, when a predetermined fire condition is satisfied, action is divided between semi manual and automatic operation. Semi manual operation like, removal of removable parachute system mounted on an aircraft, which helps to reduce aircraft speed .For automatic operation, The system comprises a generation of signal to open fire bottle container .throttle cut off and operating air brake system. In summary, prior art had following drawbacks:
a) For trainee pilot, there is no auto control system to operate when engine fire is detected and automatically operate other system for speed reduction.
b) No possibility to compute mathematically the safe distance to decide safe abort operation.
c) No possibility of extraction indication of parachute based on engine fire.
d) No possibility of automatic throttle cut off based on engine fire.
e) No possibility of automatic fire bottle operation based on engine fire.
f) No possibility of automatic air brake operation based on engine fire. These problems were substantially overcome by the system which is the subject of this invention.
4. Summary of the Invention
During takeoff ,it is essential to monitor the safety of aircraft .specially fire condition of engine .In case of any fire condition on aircraft .certain set of manual operation has be performed .which is time consuming ,to stop the movement of aircraft. Especially abort decision, in case of fire has to be determined very precisely based on current aircraft speed and acceleration and position of aircraft on runway .This abort decision depends upon Pilot's skill. There is no automatic method to compute in real time the safe braking distance and using a set of auto operation and manual operation There is high chance of judgmental error which may be

catastrophic Also, in case based on error in manual judgment Pilot may unnecessarily select for ejection Hence as an additional safety measure, Pilot is provided with additional feature of auto braking using novel auto braking system. This auto braking system does real time computation of safe distance based on various aircraft inputs and upon engine fire condition, does fire bottle operation ,air brake operation along with auto throttle cutoff .Fire bottle helps the engine to stop fire and throttle helps to stop acceleration . Feature of opening of air brake opening system automatically helps to reduce aircraft speed. Also Pilot have indication for additional manual operation to stop aircraft further This lead to maximum possible braking using parachute operation .flap position reduction ,angle of attack reduction .brake pedal operation. This ultimately helps Pilot to bring aircraft at safe speed and eventually stops the aircraft Different phases are shown in fig 11 .The interface between a Pilot and the control Surfaces of an aircraft, especially in case of engine fire during takeoff roll, needed much attention. The Pilot control interfaces are simple but needed a great deal of pilot skill to control aircraft in case of engine fire. The novel controller helps .Aircraft with no " flyby wire' interfaces, with uses of a microcontroller based electronics and interfaces to assist the pilot for semi-automated operation and make take off condition of flight safer. In no "flyby wire' interface , the pilot interacts with an manual user interface using a dedicated selection indicators in the cockpit This controller also enables Pilot to select auto operation mode during aircraft take off in case of fire. This feature is helpful for trainee Pilot with less flying experience. This novel controller uses to controls the actuators at each aircraft control Surface. Algorithm in novel controller is constantly working to make the control user interface safer, easier to understand and automatically operate, and more effective, efficient and reliable way. In terms of up gradation on old aircraft, limited digital control laws are used to implement control laws that use a reference command based on fire sensor at engine area, GPS data, aircraft speed .throttle position ,fuel flow .acceleration and

combination of thereof. Aircraft speed in conjunction with a normal acceleration is considered as a reference command. No "fly-by-wire' aircraft the Pilot manually moves (deflects) a throttle stick and operate brake to provide a control command during takeoff flight phases. In this case, a manual operation provides reduction in aircraft speed with stability. This type of control provides average handling qualities while in normal take off condition but not necessarily engine fire condition. More specifically, any sudden engine fire condition often do not provide adequate action time, and in particular to reduce speed during takeoff. Generally speaking, take off is initiated by increasing the aircraft's throttle position as high as possible to increase the acceleration to a desired amount above the runway surface. The thrust ,in ideal case , is smoothly increased from idle to maximum as the flare progresses. However in case of engine fire in short span of time, based on current aircraft speed take off has to be aborted .For this , the information of height above ground level is also used to change the control law to control aircraft speed stability near to the ground. Particularly, a control law in case of fire with positive speed stability and auto parachute indication operation that provides a control law with positive speed stability. Change in the speed can only be accomplished while parameter like speed and acceleration is within abort limit. Under Such circumstances, the effort of braking aircraft based on human judgment needs little time .In automated system the aircraft speed can be extremely reduced by the usage of a microcontroller processing which in turn momentary change the throttle position, making easier the task of aircraft speed reduction without the pilot intervention. This controller provides good handling qualities during takeoff roll, with the benefit of not needing or reading manually sensor information in safety-critical engine fire condition .In an exemplary illustrative non-limiting implementation, a controller based on sensor information, the control is presented. For example, the controller computes the possibility of brake operation in runway based on a set of aircraft parameters and without of

the pilot interruption .The pilot interruption maybe any of a plurality of devices used in aeronautics industry to serve as an interface with a human pilot, e.g. throttles, control surface, or fire bottle operation. The aircraft parameters include, but are not limited to, in this example, acceleration, and speed.
The technology herein aims to propose a aircraft control system and a
method of adding negative speed with Stability characteristics .where the
aircraft is set to the takeoff configuration , i.e. when the flap lever is set to
the takeoff position and landing gears are down, ,with fire detected in
engine, with requiring use of radio altimeter ,GPS information. The effort of
reducing the aircraft speed during takeoff can be extremely educed by the
usage of a output of controller The exemplary illustrative non-limiting
technology described herein is an aircraft control system that is configured
for takeoff, i.e. flap levers in the takeoff position and landing gears down.
Since the illustrative reconfigured control system for takeoff, in addition to
manual airbrake capability, an auto braking process is performed similarly
to a conventional aircraft: the pilot not will be required to keep the control
of aircraft control surface position in order to reduce the aircraft speed
which reduces significantly the pilot workload. Once the target speed is
reached, auto fail indication will grow, the pilot can decide based on this
current speed reference value by selecting appropriate selection. As Jong
as the Switch is selected, the reference control is continuously
resynchronized to the current airspeed. When the switch is selected, the
current airspeed is latched as a new control. The disengagement of the
takeoff mode is indicated as a flag also in the primary display. A non-
limiting advantage of the illustrative solution is a control law that provides
Suitable handling qualities during engine fire condition. This eliminates
the failure case of using erroneous information during training phase of
pilot and allows the control 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. An example non-limiting illustrative system provides a flight control safety mode and method that provides aircraft speed control through the usage of a switch and controller . Configured for takeoff, the engagement of the proposed mode adds positive reduction in speed. A way to the flight control system detects that the aircraft is configured for safe takeoff. The flap ; landing gear position and weight on wheels sensors can for example be used to characterize the takeoff phase. However, any other sensor used in aeronautical industry could be used to detect the flight phase, for instance, but not limited to, airspeed, inertial data,.radio altimeter. A way to the pilot to change the aircraft speed when positive speed Stability is engaged. The pilot inceptor may be any of a plurality of devices used in aeronautics industry to serve aircraft interface with a human pilot, e.g. throttle, or parachute operation . Till the max allowed speed is reached a on-off switch with controller operates to select the brake operation . This Switch may comprise any of a plurality of devices used in aeronautic industry Such as Switch button. A mean of processing data and computing outputs, based on a determined logic, and commanding the control Surfaces and brake operation, A mean of commanding the braking surface according to the command given by this mean of processing data and computing outputs. A set of sensors which senses the flying parameters of the aircraft and the position of aircraft on runway, to be used in a logic module that decides if the auto braking mode is to be engaged. Once braking engaged, a set of operations which controls the braking of the flight vehicle, is used in a logic module The various phases of seeped reduction is shown in fig 11.
5. Detail Description of the Drawings
FIG. 1 is a simplified view of the electrical interconnection of each functional block of novel take off controller. All features and advantages using controller will be better and more completely understood by referring to the following detailed description of exemplary non-limiting illustrative

embodiments in conjunction with the drawings of which: FIG. 1 is a non-limiting example of a takeoff safety feature during aircraft takeoff;
FIG. 2 is a schematic diagram of logical block inside microcontroller exemplary illustrative non-limiting implementation of an example non-limiting takeoff control system, showing a basic non-limiting internal logical architecture;
FIG. 3 presents a schematic of an detail description of logical unit of real time data processing block viz GPS data, speed data This example no limiting architecture of the safe distance computation algorithm based on current speed .runway position during takeoff and acceleration of an aircraft The computed profile with the speed path provides possibility of auto brake application with aircraft dynamic stability
FIG. 4 is a diagram that details the exemplary illustrative input and output module handling various signals.
FIG. 5 pictorially describes algorithm computational block [701] and interfaces details, how the vital fire sensing information is used into processing and algorithm block of microcontroller This show various output of microcontroller to achieve auto braking operation using dedicated computational algorithm
FIG. 6 presents runway where aircraft is taking off along with the runway mapping data. The. each point of runway is mapped using latitude, longitude of data. The current position of aircraft is also shown with respect to start to end of runway
FIG. 7 presents control for throttle position using relay R1. This shows that till the fire signal in turn break signal is not arrive throttle position is passed through B1 and B2 .Upon arrival of break signal with fire sensor data throttle position will cut off.

FIG.8 presents control for fire bottle operation position using relay R1. This shows that till the fire signal in turn break signal is not arrive fire bottle switch position is passed through d and c2 Upon arrival of break signal with fire sensor data fire bottle position will cut off and supply will be given from local 28VDC source .
FIG. 9 presents control for air brake switch position using relay R1. This shows that till the fire signal in turn break signal is not arrive air brake switch position is passed through D1 and D2 .Upon arrival of break signal with fire sensor data air brake position will cut off and supply will be given from local 28VDC source .
FIG. 10 presents flow of data processing. It is a simplified view of schematic showing an electrical logic and process flow chart for use with determining "brake signal in according with the various types of speed inputs viz speed ,GPS position ,wow, radio altimeter data ;
Fig 11 presents various phases of braking operation. It is a simplified view of combination of automatic braking along with manual braking and how it helps to reduce the speed in the runway.
6. Detailed Description of the Invention
Referring to FIG. 1, a first embodiment of an automatic takeoff control system [200] for an aircraft takeoff control, in case of engine fire, is illustrated in a schematic manner. The aircraft takeoff control system [200] has several components that includes a plurality of electronic sensors an indicators connected each other via a electrical interconnect with microcontroller [119]. The automatic Control system [200] has a microcontroller [119] having well known hardware devices such as a CPU and memory devices. Further, Fig. 1 also shows a functional block diagram of the novel take off controller [200]. The novel take off controller [200] contains, input section named as a multi input synchronized data acquisition section containing a dedicated interface as GPS input

interface [102] for providing real time GPS data , aircraft speed input [103] for providing real time aircraft speed data, normal acceleration input[104] for providing real time aircraft acceleration data, throttle position [105] for current throttle position , Radio altimeter [106] for providing real time radio altimeter altitude data, Engine fire sensor [108] for providing real time engine fire data, weight on wheel [109] for providing current aircraft position in air or in ground, Angle of attack input [118] for providing Angle of attack data, flap position [113] for providing flap position The controller also contains output section namely Real time angle of attack indication[110] to pilot for making appropriate angle of attack for lift reduction ,auto pass /fail indication[111] to indicate that in case auto mode cannot be engaged due to safe distance ,air brake operation [112] for speed reduction .parachute operation indication [116] for operation of parachute for speed reduction ,flap retraction indication[117] for flap retraction ,fire bottle Switch[114] for fire bottle operation. Novel take off controller [200] receives 28VDC from 28VDC source [100] from existing 28VDC source of an aircraft and power supply to the controller is by using a dedicated switch named as auto/man selection switch [101].The indication of auto,man selection is presented by auto man selection indication [120] to confirm that auto mode is selected during takeoff. With reference to FIG. 2, Microcontroller [119] has six logical blocks, first logical block is real time aircraft data processing block [700], second logical block is algorithm for safe distance block [701];third logical block is indication module [702], fourth logical block is brake signal holding circuit [703],fifth logical block is input /output module [704] and sixth logical block is runway database [705] .In summary ,the novel controller[200] has a microcontroller [119] as a main computing unit, which further has a real time data processing block[700] , algorithm for safe distance computation [701],indication module [702],brake signal holding circuit[703],Runway database[705] which is a memory unit which stores runway latitude .longitude and altitude profile data indicative of characteristics of the

runway, input/output module[704] (ref fig 4) which has multiple input line and single output line brake signal control circuit [703]. The indication module [702] further includes a indication for takeoff control for operation to be done by pilot that controls the speed reduction of and aircraft. In detail, Microcontroller's logical block named real time aircraft data processing block [700] is dedicated for processing GPS data [102], aircraft speed input [103], normal acceleration input[104] , throttle position [105], Radio altimeter [106], weight on wheel [109], Angle of attack input [118] and flap position [113] . Aircraft data processing block [700] performs speed verification and outliner's removal from inputs. This all inputs are handled by input/output module [704].This module ensures that all data is handled as per data type and range requirement. Respective inputs are stored in store speed [303], store acceleration Data [304], store current GPS data [307]. GPS values stored in GPS data [307] goes through validate GPS profile [310] checks that GPS data is valid and within in the specific runway envelop. This limit filter serves to limit filtered data at this step. Further speed data [303] goes to compute distance travelled block[306] along with store acceleration data [304] will compute distance travelled [306].Further validated GPS profile[310] and compute current runway position [305] will generate a signal which will be fed to Algorithm for safe distance block[701] (ref fig 3).The logical block runway database[705] is having runway profiling data [401] as shown in fig 7. It has latitude .longitude of runway[400].Each point of runway from runway start . to runway end is mapped with array of a latitude and longitude .This set of possible latitude and longitude not varying with time. In the preferred embodiment, resulting data items after processing and appropriate unit conversion are sent to algorithm for safe distance block [701], It preferably performs data processing, such as in converting total data. Algorithm for safe distance block [701] thus process data for the plurality of inputs. The Algorithm computation block[701] will generate signal for safe braking distance .As, brake signal is very vital for further circuitry it will be

processed by brake signal control circuit [703] which will ensure that appropriate level is maintained. The output of Algorithm computation block[701] will generate various signal as an indication from pilot to do certain action like angle of attack position indication [110] will indicate Pilot to bring angle of attack to neutral position to avoid any high lift ,Auto pass fail indication [123] to indicate the auto braking could not be done due to safe distance .parachute operation indication [116] to operate parachute to speed reduction .Brake pedal operation [115] op operate brake pedal. With reference to FIG.2, microcontroller logical block runway database [705] is also act as input to perform computation of current position of aircraft after interpolating real time GPS data [102], In the preferred embodiment, based on resulting data items brake signal is generated This brake signal is conditioned at brake signal holding circuit [703] and made available to further system via input/output module [704]. The sensors data received via input/output [704] block. The brake signal [118] is further used by relay circuitry RLThe relay R1, switching circuit works on availability of pulse generated from AND gate D1, which is in turn based on brake signal [118], couples in parallel with momentary signai holding circuit [120] for holding signal from fire sensor [108].In more detail, FIG. 3 depicts real¬time input processing steps of real time aircraft data processing block [700]. The controller is also connected with a plurality of relay (R1) contact. For example, throttle position and fire bottle [114] respectively controller ON/OFF way on each engine, a fire bottle for generating auto voltage for fire bottle operation. Fig. 10 shows a processing of the signals in auto control system [200] executed. Auto control system [200] computes potential braking level on the basis of the sensed values. The relay R1, switching circuit works on availability of pulse generated from AND gate D1, which is in turn based on brake signal [118], couples in parallel with momentary signal holding circuit [120] . As shown in FIG. 9, the ground potential side of relay is fed to terminal X2, which act as ground signal and the potential side of fixed input is fed to terminal XL The switching relay

R1 accordingly conduct the load current from R1 to fire bottle switch [114] as Bland B2 of R1 makes momentary contact and the potential side of variable output B2 fed supply to throttle position onward circuitry As shown in FIG. 8, the ground potential side of relay is fed to terminal X2, which act as ground signal and the potential side of fixed input is fed to terminal X1. The switching relay R1 accordingly conduct the load current from R1 to throttle position [105] as Bland B2 of R1 makes momentary contact and the potential side of variable output B2 fed supply to throttle position onward circuitry . FIG. 8 also shows as an example: take off control through automatic manipulation of a throttle lever irrespective of any position selected by pilot (Fig8) .Here throttle position is passed through relay R1 and once algorithm in microcontroller detects that auto mode is selected and possible to apply brake; throttle position passed through relay is cut off automatically. The Relay R1 controls components of the throttle control and two more controls namely fire bottle control(Ref fig 8) and air brake control(Ref fig 9) in accordance with fire brake signal[118] for fire bottle command signals connected with a Pilot Throttle handle for controlling a speed of an engine. The amount of injected fuel is controlled by throttle cutoff by relay (R1) amount of injected fuel is restricted as small as possible to keep the engine running or to avoid immediate shut down. The relay R1, it is connected with a fire bottle ON/OFF position switch[114] for operation without Pilot intervention(Ref fig 8) and a put the fire switch in ON condition. Similarly, the relay R1 ,it is connected with a airbrake ON/OFF position switch [112]for operation without Pilot intervention and a put the fire switch in ON condition. Further, based on algorithm computation block [701] gives signal(ref fig 5) to indication module [702] to generate assist indication which needs Pilot intervention which in turn connected with a plurality of actuators. For example, the brake pedals operation, parachute operation actuator. Brake signal control circuit [703] sends information including possible brake signal in case of engine fire .Brake signal which is 28VDC type of

signal that indicates possibility of brake action in case of fire , based on a current acceleration/deceleration for executing the speed control The brake signal [118] along with fire sensor [108] which further converted by momentary signal holding circuit [120] controls throttle position[105] of the engine. The brake signal[703] is based on method and rules are defined by taking a safe distance and maximum possible braking estimated from the present position of the aircraft , a requirement for preventing speed and a stability of aircraft is into consideration. A control method and rules for determining safe distance in the aircraft determining unit is obtained by runway profile [401] or data stored in the memory devices. The control method and rules for determining safe braking is also obtained by maps or functional expressions stored in the memory devices. Specific values in the maps or expressions in the control methods and rules are previously stored in the microcontroller [119]. For instance, the microcontroller [119] stores maps as shown in FIG. 7 shows a map for determining prohibited range and available range in accordance with the present speed and acceleration. Mainly, algorithm block [701] output used for automatic braking by signal brake holding circuit [703], Auto braking laws typically implemented by a microcontroller [119] based processing system to auto control braking system and acceleration system that in turn control the further movement of an aircraft. During takeoff, landing gear on the aircraft shall not be above ground and same shall be confirmed by radio altimeter height [106] above ground to ensure that weight on wheel [109] are still in contact of the runway [400] during takeoff and permit algorithm to further verify the possibility of application of auto braking algorithm by algorithm for safe distance [701] (Ref fig 6). Algorithm for safe distance [701] performs as a non-limiting electronic takeoff control system mainly for aborting take off in case of fire sensed by engine fire sensor [108]. The aircraft is equipped with a pilot throttle lever [105] at maximum position that the pilot can manually control the thrust of an aircraft in turn speed of aircraft [103]. The present

automatic control system is manually selectable prior to take off by auto/man selection switch [101] This controller [200]in case of fire and auto selection switch [101] case ,the throttle lever position signal[105] is ceased and reduces the fuel flow to engine in the takeoff configuration, the aircraft shall be identified as being on ground by means of sensing weight on wheel signal[109] and Radio altimeter height[106] above the ground (ref fig 6). After the engagement of this auto mode, parachute operation indication [116] along with fire bottle [114] operates (Ref fig 8). In this configuration with speed reduction, is accomplished in a manner similar to a conventional aircraft selectable by pilot. This reduces error in judgment by Pilot for suitability of applying brake system .The system receives the GPS position[102] inputs from exiting aircraft system and does runway [400]position analysis for safe clearance . The Pilot will not be required to keep the throttle [105] pulled back position in order to reduce the aircraft speed. In the correct sense, the pilot gets time to communicate with Air traffic controller for other activities till the speed is reduced. Reference auto reduction in speed be set in this manner for example when the automatic on-off Switch is depressed. The switch [101] selection is also indicated by auto man indication [120] to pilot such that that the pilot wishes to OFF the automatic selection cut off .Also, the pilot receive visual feedback to do certain manual operation such as flap position [117] and angle of attack indication [110] for reduction to bring aircraft speed reduction as fast as possible. In the example illustration, when the pilot selected Switch [101], the current controller [200] is latched and used as a reference in the aircraft take off control automatically. The illustrative control system [200] receives signals from a set of sensors, namely: speed sensor, Angle of attack sensor, that provides angle of attack [107] and airspeed [103], GPS [102] provides normal acceleration, other sensor and the flap position [113]. In the example non-limiting implementation, the information flows via dedicated electrical interconnect of transmitting data .All these data, i.e., from pilot

commands, and aircraft sensors, are sent to a mean of processing data and computing outputs .based on a programmable code stored in a storage medium along with runway profile . Processing arrangement can comprise any conventional known processing system based e.g., on digital microprocessors and associated memory, peripherals and hardware interfaces. Then, processing arrangement is able to compute a command based on the input data received. This command is sent pilot as a indicator to a mean of indication for actuating a takeoff control Surface which comprises a control unit or actuator able to command the Surfaces of the elevator to the commanded position desired position. Consequently, the elevator Surfaces to be positioned according to the command computed by pilot. FIG. 3 details blocks and command calculated based on the summation of two terms. The first term is the normal acceleration multiplied, current speed and current position. In order to calculate the second term, the runway profiling data [101] along with the normal speed is filtered through a customized algorithm [701]. In this filtering process, the derivative of the safe braking position signal [118] is estimated and in case of fire [108] further algorithm gives the actionable output viz brake signal [118]. The resulting forward command is the applied to respective areas. The filtered command also used to calculate the required manual action by pilot for more efficiently braking viz the angle of attack [110] and flap position [117] bringing to neutral position. These references are subtracted from the real sensed value of angle of attack passed through a complementary filter and the estimated value of the derivative of angle of attack respectively. The integral path of is generated by the integral of the difference between the filtered input values and the sensed vales converted to the stability axis . In order to provide positive speed stability when the aircraft is configured during takeoff. The first modification is the calculation of safe distance with the reference speed [103] and the sensed forward acceleration [104]. This error is converted to a safe distance computation [701]. This term is the

summation of sensed values of speed [103], and true acceleration [104]
multiplied by individual with runway [400] distance. The summary of
complete steps is shown in fig 10.
Step of operation for simulator:
Step 1, Receive speed input from aircraft speed source
Step 2, Receive GPS input from aircraft GPS source
Step 3, Receive GPS input from aircraft normal acceleration from aircraft
source
Step 4, Receive Radio Altimeter input from aircraft source.
Step 5, Store runway profiling data containing latitude and longitude.
Step 6, Select auto/man switch to auto position.
Step 7, when engine fire is detected during takeoff, using microcontroller
the safe distance is computed.
Step 8, when engine fire is detected during the safe distance auto braking
operation is performed.
Step 9, as a part of automatic braking throttle position will cut off
automatically.
Step10, as a part of automatic braking fire bottle will operate automatically.
Step11, as a part of automatic braking few indicators will glow to instruct
Pilot to apply actions automatically.
a. Details of simulation achieved:
B.1 This controller has feature of generation of auto brakeing feature in
case of engine fire.
B.2 This controller has feature of generation of indications to assist Pilot to
carry out some manual action in case of engine fire to do braking action.

CLAIMS
We Claim
1. A method and apparatus for take-off control of an aircraft in case of engine fire emergency ; wherein said method uses a novel electrical interconnect (ref Figl) called as a aircraft takeoff control system [200] wherein, aircraft takeoff control system [200] comprises of, a multi input synchronized system containing a dedicated input section named as a multi input synchronized data acquisition section containing a dedicated interface as GPS input interface [102] for providing real time GPS data , aircraft speed input [103] for providing real time aircraft speed data, normal acceleration input[104] for providing real time aircraft acceleration data, throttle position [105] for current throttle position , Radio altimeter [106] for providing real time radio altimeter altitude data, Engine fire sensor [108] for providing real time engine fire data, weight on wheel [109] for providing current aircraft position in air or in ground, Angle of attack input [118] for providing Angle of attack data, flap position [113] for providing flap position ,along with output section namely Real time angle of attack indication[110] to pilot for making appropriate angle of attack for lift reduction ,auto pass /fail indication^ 11] to indicate that in case auto mode cannot be engaged due to safe distance ,air brake operation [112] for speed reduction .parachute operation indication [116] for operation of parachute for speed reduction .flap retraction indication^ 17] for flap retraction .fire bottle Switch[114] for fire bottle operation .connected each other via an electrical interconnect with microcontroller [119].
2. The method and apparatus in claim 1, wherein the first component of circuit board is a dedicated microcontroller [119], which has a real time data processing block[700] is dedicated for processing unit for processing GPS data [102], aircraft speed input [103], normal acceleration input[104] .throttle position [105], Radio altimeter [106], weight on wheel [109], Angle of attack input [118] and flap position [113] with speed verification and outliner's removal from inputs, algorithm for safe distance computation [701],indication module [702] includes an indication for takeoff control for operation to be done by pilot that controls the speed reduction of and aircraft brake signal holding circuit[703],Runway database[705] .which is in a memory unit which stores runway latitude .longitude and altitude

profile data, input/output modu!e[704] ,brake signal control circuit [703], inputs are handled by input/output module [704] to ensures that all data is handled as per data type and range requirement, Respective inputs are stored in store speed [303], store acceleration Data [304], store current GPS data [304], GPS values stored in GPS data [304] goes through validate GPS profile [310] checks that GPS data is valid and within in the specific runway envelop, this limit filter serves to limit filtered data at this step, further speed data [303] goes to compute distance travelled block[306] along with store acceleration data [304] will compute distance travelled [306],further validated GPS profile[310] and compute current runway position [305] will generate a signal which will be fed to Algorithm for safe distance block[701] ,in the preferred embodiment, resulting data items after processing and appropriate unit conversion are sent to algorithm for safe distance block [701] and generate signal for safe braking distance.
3. The method and apparatus in claim 1, wherein, brake signal is processed by further circuitry named brake signal control circuit [703] to ensure that appropriate signal level is maintained, output of Algorithm computation block[701] generate signal as an indication from pilot to do action like angle of attack position indication [110] will indicate Pilot to bring angle of attack to neutral position to avoid any high lift ,Auto pass fail indication [123] to indicate the auto braking could not be done due to safe distance .parachute operation indication [116] to operate parachute to speed reduction .Brake pedal operation [115] op operate brake pedal.
4. The method and apparatus in claim 1, wherein The brake signal [118] is further used by relay circuitry R1, relay R1, switching circuit works on availability of pulse generated from AND gate D1 , which is in turn based on brake signal [118], couples in parallel with momentary signal holding circuit [120] for holding signal from fire sensor [108],first throttle position[105] for controlling a speed of an engine second .fire bottle [114],third air brake[112] , a fire bottle for generating auto voltage for. fire bottle operation , throttle position is passed through relay R1 and once algorithm in microcontroller detects that auto mode is selected and possible to apply brake; throttle position passed through relay is cut off automatically.
5. The method and apparatus in claim 1, Brake signal control circuit [703] which is 28VDC type of signal indicates possibility of brake action in case of fire , based on a current acceleration/deceleration for executing the speed control ,the brake signal [118] along with fire sensor [108]

converted by momentary signal holding circuit [120] controls throttle position[105] of the engine the brake signal[703] is based on method and rules are defined by taking a safe distance and maximum possible braking estimated from the present position of the aircraft, a requirement for preventing speed and a stability of aircraft is into consideration, for determining safe distance in the aircraft determining unit is obtained by runway profile[401] ,a map for determining prohibited range and available range in accordance with the present speed and acceleration, during takeoff, landing gear on the aircraft shall not be above ground and same is confirmed by radio altimeter height[106] above ground to ensure that weight on wheel[109] are still in contact of the runway[400] ;during takeoff and permit algorithm to further verify the possibility of application of auto braking algorithm by algorithm for safe distance [701] .the aircraft is equipped with a pilot throttle lever [105]at maximum position that the pilot can manually control the thrust of an aircraft in turn speed of aircraft [103] , the present automatic control system is manually selectable prior to take off by auto/man selection switch [101] ,this reduces error in judgment by Pilot for suitability of applying brake system, the Pilot will not be required to keep the throttle [105] pulled back position in order to reduce the aircraft speed; In the correct sense, the pilot gets time to communicate with Air traffic controller for other activities till the speed is reduced, the switch [101] selection is also indicated by auto man indication [120] to pilot such that that the pilot wishes to OFF the automatic selection cut off, the pilot receive visual feedback to do certain manual operation such as flap position [117] and angle of attack indication [110] for reduction to bring aircraft speed reduction as fast as possible.