Data Processor Resume
Contact information
Hary S. Simpson
17 Street
Denver
CO
Career objective
Looking for a challenging position of the Data Processor Resume the reputed University with a view to use my wide experience for the benefit of the organization.
On the 20th October 1991 registered a part-time self-employed business in Bruchkoebel, Germany with the original aim of developing and marketing industrial electronic equipment for process analysis in the chemical industry. The business (BEC Navigation Systems) was operated on a very small basis in parallel with full-time employment at Honeywell Regelsysteme GmbH in Maintal, Germany, where Mr. was employed as Project Manager and Senior Systems Analyst. The initial area of viscosity measurement was chosen because this did not conflict with the interests of employer Honeywell. Mr. left Honeywell at the end of June 1994 to operate full-time with his own private business. In November 1994, the business moved to Friesenheim in South West Germany concentrating fulltime on hardware and software development of complex sensor and control systems; the main areas of specialization being inertial sensors, inertial navigation, attitude-reference systems and similarly related subjects. Also offered were services on a contract basis which include development work, consultancy and seminars related to: Mathematical modelling, error model analysis and Kalman filter design Sensor signal and data processing Calibration of systems and sensors Complex system integration Real-time software Microprocessor / DSP hardware and software development Assembly language programming
Other areas of specialization included: Parallel and serial data communications Operator control, interfacing and display software Analogue and digital electronics Motor control applications In-line viscosity measurement Projects completed have included: A solid-state gyrocompass for ship applications A micro-machined silicon accelerometer An electronic flight information system (EFIS) for small aircraft A dynamic positioning system for ships A feasibility study in accelerometer-based car navigation systems A miniature 6-degrees-of-freedom inertial measurement unit Aircraft air-data, attitude and heading reference systems Various gps/ins solutions for air, land and marine applications
In February 2005 BEC Navigation Limited was formed and commenced trading from July 2006 onwards, taking over some of the functions of the original German business. From January 2008 returned from Germany to live and work in the UK and all operations were then taken over by BEC Navigation Limited. The German business was closed and ceased trading.
Career and Education Summary
Between September 1966 and July 1969 Mr studied Physics and Mathematics at the University of Hull, England followed by a further 3 years part-time course in Applied Physics at Polytechnic while working as an electronics technician at University. In September 1973 Mr. started his first engineering job as a Semiconductor Components Reliability Engineer with SGS-Ates in Falkirk, Scotland. Mr. 's involvement in the area of navigation commenced on 3rd January 1976 when he was offered a position as Navigation Engineer with Sperry Gyroscope based at the Rosyth Naval Dockyard in Scotland. Work primarily involved maintenance and refurbishment of navigation and associated equipment on UK Polaris submarines. In 1980, Mr. was promoted to Senior Engineer - Navigation. In 1982, Sperry Gyroscope was bought by British Aerospace. The contract with the Royal Navy continued, however, practically unchanged. At the beginning of September 1985, after nearly ten years with British Aerospace and Sperry Gyroscope, Mr. moved to Freiburg, South West Germany to join Litef GmbH. There, as Systems Engineer, he led a team of specialised engineers in a 20m DM project for the development of a ring-laser-gyroscope inertial navigation system for highly accurate ship and submarine applications. The system was successfully tested by the German Navy in autumn 1988. In July 1989, Mr. joined Honeywell Regelsysteme GmbH as Leader for System Analysis and Projects. The primary function of the work was the development, simulation and testing of new inertial sensor data processing algorithms for application in highly dynamic military aircraft and guided weapons inertial navigation systems and the development of military avionic systems. Mr left Honeywell at the end of June 1994 thereafter concentrating full-time on his own navigation systems business (BEC Navigation Systems).
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Further Education & Training Courses
Over his 33-year career span as an engineer / physicist, Mr. has attended many courses, seminars and symposiums related to his work, of which some of the most important are listed below. ------------------------------------------------------------------------------------------------------------------------1976 - 1982 UK Royal Navy - Computer and data transmission systems - Inertial navigation equipment - Navigation aiding systems (Loran, BRN5) Sperry, N.Y., USA - Inertial navigation & computer systems
Strapdown Associates Inc., - Strapdown inertial navigation Mineapolis, USA - Kalman filters -------------------------------------------------------------------------------------------------------------------------
Information on the Various Development Projects
The following information summarises the work involvement in the projects undertaken by BEC Navigation Systems (Germany) and BEC Navigation Limited (UK).
1. Solid State Gyrocompass for Ship Applications
This project consisted of the development of a low-cost continuously self-calibrating gyrocompass for marine applications, which was partly financed by European funding. There were four participating partners in this development project. The functions undertaken by BEC Navigation Systems were as follows: a) Systems analysis, simulation and sensor modelling b) Development of mathematical algorithms for calibration and gyro compassing c) The basic electronics and processorrequirement definitions d) Total system software development using 3 16-bit micro-controllers e) The development of fast floating point algorithms in assembly language The original design used very low cost gyroscopes, which were found to be too sensitive to acceleration making it impossible to meet the system requirements. A new design, using more precision components was recently started.
2. PFD2525 Airdata, Attitude and Heading Reference System for Small Aircraft
The system, named PFD2525, is generally referred to as an ELECTRONIC FLIGHT INFORMATION SYSTEM (EFIS) or a PRIMARY FLIGHT DISPLAY (PFD). The system is a totally autonomous unit consisting of an inertial and air-data sensing unit, a fluxgate heading sensor and a high-intensity moving colour TFT display for mounting in the aircraft cockpit. The system provides the following dynamic information to the pilot: Altitude, airspeed, magnetic heading, roll, pitch, turn-rate, g-force acceleration and climb rate. This data is displayed in analogue and digital form on the TFT screen, symmetrically positioned around a moving circular artificial horizon. The project, which was mostly funded and developed by BEC Navigation Systems, was a follow-up project using much of the know-how gathered from the previous gyrocompass project using the same original low-cost inertial sensors.
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Significant advances in the development of this system were made, which included: a) The addition of a TMS320C31 floating point DSP processor to handle aircraft dynamics and high-speed Kalman filter data processing. b) Improved continuous self-calibration and alignment techniques c) Extensive built-in test d) Completely new electronics development e) A completely autonomous system - with no user or external inputs e) All system code written in assembler f) A bright TFT colour moving display for providing all primary flight information
3. A Micro-machined Silicon Accelerometer
A micro-machined silicon accelerometer was developed together with the company Microtechnik & Sensorik in Jena, Germany. The work done by BEC was the development and testing of the microelectronic circuits of the sensor.
4. Contractual Development Work on Car Navigation Systems (1999-2003)
Projects under contract with large European companies included: a) b) c) d) e) f) g) A feasibility study into the aiding of car navigation systems with accelerometers. The non-random disturbing effects of GPS aiding on car navigation systems errors. Several system models and Kalman filter mechanisation for car navigation. Wheel dynamic effects on the performance of position and heading determination. Calibration of wheel and gyro characteristics in car navigation. Park house and tunnel navigation phenomena. Mathematical modelling of loosely and tightly coupled GPS / INS solutions
5. A Dynamic Positioning System for Ships (1997-1999)
The contractual functions performed by BEC Navigation Systems were: a) The development of mathematical algorithms for GPS / INS aided positioning. b) Systems analysis and simulation. c) Development of a 22-state Kalman filter for system error estimations. d) Technical support and system test.
7. Viscosity Measurement Equipment (1991-1995)
Some small contracts for the development of in-line viscosity measurement equipment were received.
8. A MEMS based Inertial Navigation System for Unmanned Air Vehicles (2002-4)
This project was joint development between BEC Navigation Systems and the company W. Ludolph of Bremerhaven, Germany. A prototype was available for test by the end of 2004. No further development on this system was conducted thereafter due to the need for extensive hardware design changes, which were considered not financially viable.
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9. A 6-Degrees-of-Freedom Micro Inertial Measurement Unit MICRO-ISU BP3010
This is one of the most important developments undertaken by BEC and is still the main source of income today. A short description of the product is given below. The MICRO-ISU BP3010 is a complete OEM inertial measurement unit offering a wide range of applications for general motion sensing, aided navigation, and low-cost attitude reference systems. A paper was presented on the BP3010 at the Gyro Symposium, Stuttgart in September 2003. The inertial sensor unit consists of three orthogonally arranged +/-300 deg/s angular-rate gyroscopes (Gx, Gy and Gz) and three 6g linear accelerometers (Ax, Ay and Az). The accelerometer measurement axes are aligned parallel to their respective gyroscope sensing axes. The complete unit contains all the necessary sensor and temperature measurement electronics, and includes three miniature flash microcontrollers, two stabilised dc power supplies for separate analogue and digital electronics and a quarz crystal oscillator for maintaining a precision internal clock. The complete unit is enclosed in a copper housing measuring just 35mm (length) x 22mm (width) x 12mm (height) and fits onto the footprint of a 24-pin DIP socket. The sensor measurement electronics of the MICRO-ISU BP3010 contain 6 separate rebalancing integrating circuits, one for each of the inertial sensors, which are shared in pairs with the three flash microcontrollers, whose functions perform the control, measurement and rebalancing of the sensor electronics and the processing of the sensordata. Also contained in the flash memory of the microcontrollers is temperature compensated sensor calibration data for providing accurate angular incremental and velocity incremental output data over the full operating temperature range of -40° to C +85° Data is compensated through the software of the microcontrollers for temperature-dependent C. scale factors, bias errors and misalignments. Data is transmitted serially in frames of 16 bytes at baud and can interface with any standard UART port. With the addition of one RS232 driver/receiver circuit the MICRO-ISU BP3010 can communicate directly with a personal computer without the need for any other additional electronics. The MICRO-ISU BP3010 requires a +5V +/-0.3V dc power input and consumes just 0.5 watt. Two pins provide serial output and serial input and a fifth pin is available for providing an optional external reset.
10. AHRS and GPS/INS Inertial Navigations Systems for Airborne, Land and Marine Applications
All these systems have been developed around the new MICRO-ISU BP3010 inertial measurement unit. They include: BP-S200 BP-INA-200 BP-INL-300 BP-INM-300 Aircraft air-data, attitude and heading reference system Aircraft gps/ins inertial navigation system Land-based gps/ins inertial navigation system Marine gps/ins inertial navigation system
11. Contractual Work on Borehole Surveying Systems for Oil and Gas Exploration
Spanning a 4 year period from Jan 2005 to December 2008, work was conducted on the development of new navigation algorithms, error model analysis, calibration, fast alignment techniques and new Kalman Filter solutions, including gyro-compassing, for multi-mode operations of an inertial navigation system designed for precision surveying of deep boreholes in oil and gas exploration.
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MICRO-ISU BP3010 The world's smallest IMU with integral processor
FREQUENCY 64 Hz 32 Hz 16 Hz 8 Hz
BYTE 1 7B Hex 7B Hex 7B Hex 7B Hex
BYTE 2 88 Hex 89 Hex 8A Hex 8B Hex
The serial receiver of the MICRO-ISU BP3010 does not contain a FIFO for storing input data. Instead the serial input port is periodically polled to test for serial input data. The frequency at which it polls the receiver port is 3072 Hz (every 325.5µs). The period between polling is therefore slightly longer than the interval between continuous bytes at the baud rate. If bytes are transmitted with no interval between bytes, there is a possibility that the incoming message is not properly received. To ensure that the message is always received, it is recommended that the two bytes have a break of minimum 75µs and maximum 1000µs between the two-byte transmissions. Serial Output data is transmitted as a frame of 16 bytes. The data is transmitted as signed, scaled 16-bit integers. The frame is defined as follows: BYTE 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 DESCRIPTION 78 Hex 1st identification byte 87 Hex 2nd identification byte Status byte dTHx LS byte dTHx MS byte dTHy LS byte dTHy MS byte dTHz LS byte dTHz MS Byte dVx LS byte dVx MS byte dVy LS byte dVy MS byte dVz LS byte dVz MS byte XOR checksum of bytes 1 to 15 UNITS LS-BIT
Actual Size
Description
The MICRO-ISU BP3010 is a complete 6-degrees-of-freedom inertial measurement unit, with 2 built-in internally regulated power supplies for powering separate analogue and digital electronics and is calibrated for operation over its temperature range of -40° to +85° It performs accurately wit h angular C C. rates up to +/-300° and accelerations up to +/-6g . /s The unit transmits output data as angular incremental and velocity incremental data in serial frames of 16 bytes at one of the user-selectable frequencies of 64 Hz, 32 Hz, 16 Hz or 8 Hz. Serial data is transmitted and received in standard UART format as asynchronous bytes at 38,400 baud with 1 start bit, 8 data bits, 1 stop bit and no parity. The MICRO-ISU fits onto the footprint of a 24 DIP socket (0.6" socket width, pin spacings 0.1") and has 5 pins defined as follows: Pin 1. Pin 12. Pin 18. Pin 19. Pin 24. +5V +/- 0.3V Power Power and signal ground (0V) Serial Input (may be left unconnected) Serial Output Reset (low for reset, may be left unconnected) 1 24
1/65536 rad 1/65536 rad 1/65536 rad 0.001 m/s 0.001 m/s 0.001 m/s
The Status byte defines the validity of the output data: BIT 7 MSB 6 5 4 3 2 1 0 LSB WHEN 0 Not used, always = 0 Not applicable dVz within range dVy within range dVx within range dTHz within range dTHy within range dTHx within range WHEN 1 Not applicable Send flag, always = 1 dVz out of range dVy out of range dVx out of range dTHz out of range dTHy out of range dTHx out of range
X - axis
Top View
19 18
Y - axis Z - axis into paper
12 At power-on the MICRO-ISU automatically performs an internal reset and the Reset pin, which has an internal pull-up resistor may be left unconnected or connected to +5V if not required. A minimum of 10ms (high-low-high pulse) is recommended when applying a reset. Serial input and output signals use standard CMOS +5V / 0V voltage transitions. The no-data transmission voltage is +5V. The Serial Input pin may be left unconnected if frequency selection is not required. After power-on, output data is automatically transmitted at the default frame transmission frequency of 64 Hz. To select one of the transmission frequencies a 2-byte frame must be sent to the serial input pin. The 2 bytes are defined as follows:
For an angular increment, the "range" is defined as the maximum allowed angular increment for an angular rate with the maximum value of +/-300° The range is reduced at low frame /s. frequencies to avoid overflows. For a velocity increment the "range" is defined as the maximum allowed velocity increment at the maximum acceleration of 6g. The range is also reduced at low frame frequencies to avoid overflows. Physical dimensions Weight Power Consumption Scale Factor Accuracy Residual Bias Error Misalignment Error Output Noise (rms) 35 mm x 22 mm x 12 mm 30 g approximately 0.5 Watt 0.3 % 0.5 ° (gyro) 10mg (accel) /s 0.5 degree 0.03° (dTh) 0.010 m/s (dV) BEC Navigation Limited http://www.becnav.co.uk
References
Hary S. Simpson
Manager
Wap Company.
Hary_Simpson@gmail.com
