|Title of Invention||
FIELD LEVEL TEST EQUIPMENT FOR MISSILE LAUNCHER
|Abstract||The test equipment is used for checking the functioning of launcher for thrust vector controlled, wire guided second-generation antitank guided missile. The test equipment is designed with state of the art technology using microprocessor, capable of identifying the faulty subassembly. The test result is given as GO or NOGO on front p.anel. The Hamlonising Sighting Gauge and Harmonising Sighting Board supplied with the test equipment provide for harmonization of optical and missile axes of the launcher. The equipment is field portable and self reliant with inbuilt battery pack and charger. The equipment also has built in self-test facility. The test equipment tests the launcher in seven modes. The test equipment has advanced features, simple to operate and testing is automatic.|
The present invention relates to a field level test equipment used for checking overall functioning of the launcher, which in turn is used for firing a second generation anti tank guided missile. More specially, this equipment is adapted for checking the electronic and optical performances of the launcher meant for thrust vector controlled wire guided missile here in after referred to as 'FLAME'.
This test equipment according to invention is also capable of accurately locating the defective sub-assembly involved. By means of this equipment all sub-systems of the launcher are checked and finally a 'GO' or 'NOGO' visual indication is displayed on the front panel of the test equipment.
The present invention consists of a field level test equipment for missile launcher comprising an Electronic Control Unit with a microprocessor based functional module with control and display means, having a CPU PCB, an Interface PCB, Power Supply PCB and Charger PCB, Harmonising Sighting Gauge, Harmonising Sighting Board, Collimator simulating IR source along with a fixture adapted to clamp the collimator on the ramp adapter of the launcher, a battery pack and a plurality of connecting cables.
Accordingly the invention provides for a field level test equipment for missile launcher comprising of an electronic control unit having a microprocessor with self equipped rechargeable battery pack and charger, a Collimator for simulating Infra Red (IR) source mounted on launcher by means of a Collimator fixture in optical alignment between them, where in the IR signal of the Collimator being sensed by launcher generating correction commands to be tested by the Electronic Control Unit, performance of the launcher being displayed GO/NOGO automatically.
Now the invention will be described in detail with reference to the accompanying drawings.
The test setup of the launcher is shown in Fig. 1 whose details are given below:
The test setup consists of launcher under test, test equipment and accessories.
The launcher under test comprises of the following subassemblies: Tripod:
Tripod (1) shown in Fig. 1 is a mechanical structure having three legs and serves as the base for the launcher.
Trigger Mechanism (2) as shown in Fig. 1 is an electro-mechanical assembly, which is used for initiating the launching of the missile.
Guidance Electronic Unit:
It is an electronic unit (3) as shown in Fig. 1, which generates firing sequence for launching the missile and correction commands w.r.t. the error signals generated by Optical device proportional to missile deviation from target. The correction commands generated by Guidance electronic unit are fed to the missile for steering the missile on to the target.
Optical device (4) as shown in Fig. 1 tracks the missile flare and generates error signal in proportion to the missile deviation from the target.
Ramp Adapter (5) as shown in Fig. 1 is an interface between missile and launcher. It provides both electrical and mechanical interface.
The following items shown in Fig. 1 belong to the field level test equipment whose details are explained in subsequent paragraphs.
- Field level test equipment (6)
- Collimator (7)
- Collimator fixture (8) -Ni.Cd. Battery pack (9).
The configuration of Field level test equipment and Accessories is given in Fig. 2. The details of the test equipment and accessories in logic container (1) as shown in Fig. 2 are as given below:
Logistic Container (2) as shown in Fig. 2 is made of FRP material and it has got two parts. Top shell and Bottom shell. It houses the Electronic Control Unit (3) as shown in Fig.2, Tactical Container with Accessories (4) as shown in Fig, 2, Harmonising Sighting Board (5) as shown in Fig. 2, Power Supply Cable Pack (6) as shown in Fig. 2.
Electronic Control Unit;
Electronic Control Unit (3) as shown in Fig. 2 is microprocessor controlled test equipment used for carrying out functional checks of the complete FLAME launcher and its submodules separately.
The functional module (8) as shown in Fig. 2 and Ni. Cd. Battery pack (9) as shown in Fig. 2 of the test equipment are housed within the tactical container for functional module (7) as shown in Fig. 2. The container is provided with 2 hinged carrying handless, allowing it to be carried by two persons. It comprises
(a) A detachable lid ( Top shell) with battery pack at the top and
(b) A casing (Bottom shell) containing the functional module.
The lid is secured in position on the casing by means of fasteners and protects the front panel of the test equipment during transport and storage.
The container, made of Fiber Reinforced Plastic (FRP) accommodates the functional module (8) as shown in Fig. 2 and the front panel having the controls, display means, the test and power connectors. The details of the parts of the functional module are given below:
CPU PCB. PCB 1;
This PCB (10) as shown in Fig. 2 consists of 80C186 microprocessor based controlled circuitry, signal level conversion circuits, front panel control circuits and power supply check circuits.
Interface PCB. PCB2:
This PCB (11) as shown in Fig. 2 consists of input battery voltage check circuit, missile signal simulation circuits like wirespool load, decoder and gyro top pulse generation circuhs etc. It is also equipped with co-ordinate conversion and interfacing circuitry.
Power Supply PCB, PCB3:
This PCB (12) as shown in Fig. 2 consists of four DC - DC converter power modules, for which 24 ± 4 V DC is the power input. The DC - DC converters give different supply voltages used by the electronic circuits of the test equipment.
Charger PCB, PCB4:
This PCB (13) as shown in Fig. 2 consists of a constant current switched mode power supply circuit, which is used to charge the discharged Ni, Cd. battery pack. The charger PCB can charge the battery in two modes of operation i.e.. Boost (800 mA) and Normal (400 mA) modes. When the battery is fully charged, it charges the battery in trickle mode of charging i.e. at 40 mA. Whenever the low battery indicator glows on the front panel, the battery pack is to be kept under charge for 16 hrs in "Normal" mode.
The front panel (14) as shown in Fig. 2 is equipped with all controls, indicators, connectors Viz. Launcher test connector. Ramp adapter test connector, Optics test connector, External Power/Charger connector, READY indicator FAULT indicator, GO indicator, NOGO indicator, LOWBAT indicator, TEST under progress indicator, RESET push button, START push button. Fuse holder assembly. Power "ON" indicator, Power Selector rotary switch, Mode Selector rotary switch for different test positions such as Total system, Ramp Adapter (Safe) , Ramp Adapter (Arm), Trigger, Optics, Electronic unit and Day / Night tracer mode, MRD selector rotary switch, Charge indicator and Trickle indicator.
Ni. Cd. Battery Pack with cable:
Ni. Cd. Battery pack (9) as shown in Fig. 2 is a set of 22 Ni. Cd. (Nickel Cadmium) battery cells of each 1.2 V, 4 AH of type 'D', connected in series and packed in a container to supply 22-28 Volts. The same is fixed in the lid with cover. The battery pack terminals are connected to a 12-pin connector and cable.
Tactical Container with Accessories:
Tactical container (15) as shown in Fig. 2 is made of FRP and has two parts viz.; top shell and bottom shell.
It houses the following accessories of the test equipment:
Junction unit test adapter:
Junction unit test adapter (16) as shown in Fig. 2 is a tubular structure with electrical connectors and wiring and provides interface between launcher test cable and the ramp adapter of the launcher.
Test cable pack:
Test cable pack (17) as shown in Fig. 2 consists of the following cables:
(a) Launcher test cable (22) as shown in Fig. 2 used while testing the launcher and it provides interface between launcher and test equipment along with junction unit test adapter.
(b) Ramp adapter test cable (23) as shovra in Fig. 2 used while testing only the Ramp Adapter subassembly.
(c) Optical Device test cable (24) as shown in Fig. 2 used while testing the Optical device as a subassembly.
The Collimator (18) as shown in Fig. 2 consists of optical and mechanical parts. The optical part produces a parallel light beam and the mechanical part provides for changing the angular position of the beam in the horizontal and vertical planes within the specified limits. This equipment generates light source, similar to that of missile flare light and has a provision for shifting the angle of incidence. The flame optical device is aligned against the light source of collimator and its performance is checked. The required power to the collimator is supplied from the test equipment through the launcher test cable. The Collimator is positioned by means of a collimator fixture mounted on the ramp adapter at the front end, fixed with the clamp and lock nut assembly.
It is a mechanical assembly (20) as shown in Fig. 2 used to fix the collimator on the ramp adapter of the launcher.
Harmonising Sighting Gauge:
A Harmonising Sighting Gauge (19 as shown in Fig. 2 is fitted on the ramp adapter, in lieu of the munition for harmonisation of the munition / line of sight, while testing. It is composed of a body equipped with a reticulated sight. It is having two slides and recess for the munhion plug. An additional lens clamp must be fitted to the sight, making the latter suitable for sighting to 50 meters when checking axes harmonisation with the help of the harmonizing sight.
The harmonisation sighting board is composed of a frame equipped with height adjustable mechanism. A circular target delimiting the optical device harmonisation tolerance, relative to the munition axis is located at the top end of the frame. To the right of the target, a Red Square mark is painted on the frame to line up the sighting gauge.
50 mts Lens Clamp:
50 mts Lens Clamp (21) as shown in Fig. 2 is an Aluminum plate used during axes harmonisation of the launcher.
Harmonising Sighting Board;
Harmonising Sighting Board (5) as shown in Fig. 2 is used for checking the axis harmonisation of Flame launcher with the help of sighting gauge. It is accommodated in the logistic container top coverlid.
The Power supply cable pack (6) as shown in Fig, 2 is kept in the logistic container whose details are given below.
External Power Supply Cable:
This cable (25) as shown in Fig. 2 is used for connecting external DC power supply to the test equipment when the test equipment is operated with external DC power supply.
Vehicle Battery Supply Cable:
This cable (27) as shown in Fig. 2 is used for connecting Vehicle battery to the test equipment, when the test equipment is operated with vehicle battery power supply.
This cable (26) as shown in Fig. 2 is used for charging the battery pack of the test equipment.
Testing of Launcher with Test equipment:
The testing of launcher with test equipment consists of the following steps
(a) Performance check of launcher with test equipment.
(b) Verification of harmonization of missile and optical axes of launcher with axes harmonization setup.
Best Mode of Operation:
Performance Check of launcher:
Launcher, the unit under test is used for loading the missile on ramp adapter (5) as shown in Fig. 1, launching of missile by pressing the trigger of the trigger mechanism (2) as shown in Fig. 1. Optical Device (4) as shown in Fig. 1 is used for selection of the target and for receiving of IR flare signal from the flying missile and generating Frequency Modulated error voltage proportional to missile deviation from line of sight. Line of Sight is the line joining the Optical axis of the launcher and the target. The Frequency Modulated signal generated by optical device is processed by the Guidance Electronic Unit (3) as shown in Fig. 1, which generates deviation error signals correction commands signal proportional to the missile deviation to be transmitted to the missile for guiding it on to hit the target.
In testing the launcher using field level test equipment. Collimator is used for generating IR signal equivalent to the missile deviation from line of sight. The electronic control unit is used for switching on the launcher by giving required power supply and switching signals at appropriate timings, measures different signals generated by the launcher, error voltages generated w.r.t. IR signal provided by collimator and the corresponding correction commands generated by the Guidance Electronic Unit. These signals are compared with the standard reference data stored in the EPROM (Electrically Programmable Read Only Memory) by the Microprocessor circuitry in the CPU PCB of Electronic Control Unit and the performance of the launcher is displayed GO or NOGO on front panel automatically.
Now coming to the overall operation of the field level test equipment, there are two test programs viz.
Verification of the test equipment (self test)
Verification of the launcher (testing).
The purpose of this 'Self Test' of the test equipment is to ensure complete serviceability of the test equipment prior to checking the launcher, in each mode of operation. After connecting test cables to the test equipment, the system is to be switched-on by putting the Power ON / OFF switch to "ON" position and reset the system by pressing the "RESET" push button. The equipment will be first self-tested and after passing the self-test, it proceeds automatically to test mode.
During this 'Self-test', following parts of the circuit are checked pertaining to test equipment control electronics operation viz., RAM Test, INPUT / OUTPUT PORTS TEST, Timers test, ADC Test, DAC test, simulated gyro frequency test and power supplies test.
If all the above checks are satisfactory, the visual indicator "READY" glows on the front panel and proceeds to test the launcher, depending upon the position of mode selector switch. If the indicator 'READY' does not glow, the test equipment is faulty and it does not proceed further. The equipment is capable of carrying out the tests in the following seven modes viz.,
- Total System mode: The test equipment carries out tests on complete launcher with Ramp Adapter (which includes trigger mechanism. Guidance electronic unit and optical device) and gives result finally as 'GO' or 'NOGO'.
- Ramp Adapter (SAFE) mode: In this mode, the test equipment carries out tests on Ramp adapter (5) as shown in Fig. 2 in 'SAFE' mode and gives result finally as 'GO' or 'NOGO'.
- Ramp Adapter (ARM) mode: In this mode of testing, the test equipment
tests the functional performance of the Ramp adapter (5) as shown in Fig. 2 in
'ARM' mode and gives the result in the form of 'GO' or 'NOGO' on the front
" Trigger mode: In this mode, the test equipment tests only the performance of the Trigger mechanism (2) as shown in Fig. 2.
Optics mode: In this mode, the test equipment tests only the optical device (4) as shown in Fig. 2 performance, isolating the Guidance Electronics unit and Trigger mechanism.
- Electronic Unit mode: In this mode of testing, the test equipment tests the
complete Guidance Electronics unit (5) as shown in Fig. 2 and gives the result
in the form of 'GO' or 'NOGO' on the Front panel.
DAY/NIGHT Tracer mode: In this mode, the test equipment tests the function of DAY/NIGHT tracer selection switch of the Guidance Electronic Unit (5) as shown in Fig. 2, to ensure that the ignition circuit of the day tracer is isolated, when the selector switch is in "NIGHT" mode and gives the result in the form of 'GO' or 'NOGO' on the front panel and vice versa.
Approximately 16 seconds are required for the test equipment to say GO or 'NOGO' after pressing the trigger mechanism, in total system mode.
At the beginning of testing the launcher, the battery voltage is to be verified, by observing the LOWBAT indication on the front panel. There is a provision for connecting an external supply of DC 26 V ± 4.0 @ 4.0 amps.
Verification of Harmonization of missile and optical axes:
Axes harmonization set up consisting of Harmonising Sighting Gauge (6) as shown in Fig. 3, 50 mts lens clamp (5) as shown in Fig. 3, Harmonising Sighting Board (7) as shown in Fig. 3. Functional description of the above parts was already described in previous paragraphs.
The Harmonising sighting board (7) with stand (8) as shown in Fig, 3 is kept at a distance of 50 mts from launcher (1) as shown in Fig. 3 and the Harmonising Sighting Gauge is mounted on ramp adapter of launcher (2) as shown in Fig. 3 in place of missile. The sighting gauge is focused on to the Red Cross marking (10) as shown in Fig. 3 on the sighting board. Viewing through the eye piece (4) as shown in Fig. 3 of optical device (3) as shown in Fig. 3, the optical device small circle should match with the circular target (9) as shown in Fig. 3 marked on the sighting board.
If the circle of the optical device matches with the tolerance circle marked on the sighting board, the axes harmonization is correct otherwise the harmonisation shall be achieved by adjusting the screws provided on the launcher.
The 50 mts lens clamp shall be used for correct focusing of the optical device for viewing at 50 mts distance.
It will be appreciated that the arrangement according to the invention has been described at length with reference to certain preferred embodiments thereof. Variation and modification can be effected within the spirit and scope of the invention as described herein above and as defined in the appended claims.
1) A field level test equipment for missile launcher comprising of an Electronic Control Unit having a microprocessor with self equipped rechargeable battery pack and charger; a Collimator for simulating Infra Red (IR) source mounted on launcher by means of a Collimator fixture in optical alignment between them, where in the IR signal of the Collimator being sensed by launcher generating correction commands to be tested by the Electronic Control Unit, performance of the launcher being displayed GO / NOGO automatically.
2) The test equipment as claimed in claim 1, where in the harmonisation of missile and optical axes is done with Harmonising sighting gauge equipped with a reticulated sight having 2 slides and a recess for munition plug is adapted to be fitted on the ramp adapter for harmonisation of axis while testing.
3) The test equipment as claimed in claim 1, wherein the Harmonising sighting board comprised of a frame equipped with a circular target and a red Square mark on the top end with height adjustment mechanism for harmonisation of optical and missile axes of launcher.
4) The test equipment as claimed in claim 1 wherein the collimator has a means for generating light source similar to missile flare consisting of an optical part capable of producing parallel light beam and a mechanical part capable of changing the angular position of the beam in the horizontal and vertical planes.
5) The test equipment as claimed in claim 1 wherein the said battery pack is capable of supplying 22-28 Volts.
6) The test equipment as claimed in claim 1 to 5 where in it is packed in a
7) The test equipment substantially as herein described with reference to and as
shown in fig. 1 to 3 of the accompanying drawings.
Dated 9th day of November 1999.
|Indian Patent Application Number||1089/MAS/1999|
|PG Journal Number||26/2007|
|Date of Filing||11-Nov-1999|
|Name of Patentee||BHARAT DYNAMICS LIMITED|
|Applicant Address||KANCHANBAGH, HYDERABAD-500 058|
|PCT International Classification Number||F41G7/00|
|PCT International Application Number||N/A|
|PCT International Filing date|