1. An arrangement, comprising:
p-doped semiconductor layers;
n-doped semiconductor layers; and
a plurality of transitions arranged between the p-doped semiconductor layers and the n-doped semiconductor layers, the transitions displaying a Zener breakdown upon application of a characteristic voltage for each of the transitions, wherein:
the characteristic voltages of the transitions additively correspond to a breakdown voltage of the arrangement,
the p-doped semiconductor layers and the n-doped semiconductor layers are highly doped,
the p-doped semiconductor layers form at least two groups doped at different concentrations, a highly doped layer of the p-doped semiconductor layers being doped at about 2\xd71018 atomscm3,
the n-doped semiconductor layers form at least two groups that are doped at different concentrations, a highly doped layer of the n-doped semiconductor layers being doped at about 2\xd71018 atomscm3,
the p-doped semiconductor layers and the n-doped semiconductor layers exhibit a constant doping, and
the p-doped semiconductor layers and the n-doped semiconductor layers are doped at a same concentration, wherein the p-doped semiconductor layers and the n-doped semiconductor layers have a thickness of approximately 4 \u03bcm.
2. The arrangement according to claim 1, further comprising:
an n-doped substrate on which are arranged the p-doped semiconductor layers and the n-doped semiconductor layers.
3. The arrangement according to claim 2, wherein a doping type of a semiconductor layer farthest away from the n-doped substrate corresponds to a doping type of the n-doped substrate.
4. The arrangement according to claim 2, wherein a doping type of a semiconductor layer farthest away from the n-doped substrate is different than a doping type of the n-doped substrate.
5. The arrangement according to claim 2, wherein the n-doped substrate has a thickness of approximately 500 \u03bcm.
6. The arrangement according to claim 1, further comprising:
a p-doped substrate on which are arranged the p-doped semiconductor layers and the n-doped semiconductor layers.
7. The arrangement according to claim 6, wherein a doping type of a semiconductor layer farthest away from the p-doped substrate corresponds to a doping type of the p-doped substrate.
8. The arrangement according to claim 6, wherein a doping type of a semiconductor layer farthest away from the p-doped substrate is different than a doping type of the p-doped substrate.
9. The arrangement according to claim 7, wherein the p-doped substrate has a thickness of approximately 500 \u03bcm.
10. The arrangement according to claim 1, wherein a concentration of doping for the p-doped semiconductor layers and the n-doped semiconductor layers is approximately 2\xd71019 atomscm3.
11. The arrangement according to claim 1, wherein ten transitions are provided between the p-doped semiconductor layers and the n-doped semiconductor layers.
12. The arrangement according to claim 1, further comprising:
metal contacts arranged over an entire respective surface of an upper side and a lower side of the arrangement.
13. The arrangement according to claim 1, wherein the n-doped semiconductor layers and the p-doped semiconductor layers are silicon layers.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
1. A method comprising estimating weight of an aircraft, wherein said aircraft has an undercarriage fitted with an electrical rotating machine comprising a motor that propels the aircraft on the ground, said method further comprising:
(a) supplying power to the electrical rotating machine and measuring power supplied directly using sensor means or indirectly using current and voltage supplied to the electrical rotating machine to obtain a power measurement;
(b) when said aircraft is propelled on the ground, measuring a change in one or more of speed, acceleration, and torque in response to power supplied to said electrical rotating machine, wherein speed is measured by measuring speed of said aircraft or an aircraft component rotating with a speed proportional to a speed of said aircraft to obtain a speed measurement; acceleration is measured by measuring acceleration of said electrical rotating machine or a component of said electrical rotating machine with an acceleration proportional to acceleration of the aircraft to obtain an acceleration measurement; and torque is measured within the electrical rotating machine or at a structure that displays torque proportional to torque of said electrical rotating machine to obtain a torque measurement;
(c) building a database of speedpower, accelerationpower, and torquepower relationships for many models of aircraft moving on many ground surfaces with various cargo loads comprising a range of weights and comparing the power measurement and one or more of the speed measurement, acceleration measurement, and torque measurement with database relationships for a same or a most similar model aircraft as said aircraft on a same or most similar ground surface as said ground surface;
(d) obtaining an estimate of weight of said aircraft from a comparison of said power measurement and one or more of said speed measurement, said acceleration measurement, and said torque measurement with said database relationships for a same or similar aircraft as said aircraft on a same or similar ground surface as said ground surface;
(e) verifying the estimate of weight obtained for said aircraft and entering said estimate of weight into said database, thereby expanding the speedpower, accelerationpower, and torquepower relationship data for aircraft on ground surfaces in said database and increasing precision of weight estimates as said data is expanded; and
(f) entering a verified obtained estimated weight each time an estimate of aircraft weight is obtained.
2. The method described in claim 1, wherein power supplied to the electrical rotating machine to move the aircraft on the ground is measured indirectly by first measuring the current and voltage applied to the electrical rotating machine to move the aircraft and then calculating the power supplied to the electrical rotating machine to obtain said power measurement.
3. The method described in claim 1, further comprising displaying the estimated aircraft weight on the aircraft or transmitting the estimated aircraft weight to a location remote from the aircraft for use by ground airport staff.
4. The method described in claim 1, further comprising using the estimated weight of said aircraft to calculate an amount of fuel needed for a particular journey.
5. The method described in claim 4, further comprising the steps of first transmitting the calculated amount of fuel needed to a fuel loader and then using the fuel loader to load the calculated amount of fuel onto the aircraft.
6. The method described in claim 4, further comprising the steps of comparing the calculated amount of fuel needed to an amount of fuel already on the aircraft and communicating results of the fuel comparison to ground, aircraft, or airport staff so appropriate action can be taken to load the correct amount of fuel.
7. The method described in claim 1 further comprising using the estimate of weight of said aircraft to calculate a centre of gravity of the aircraft and using a calculated centre of gravity to distribute fuel, passengers, luggage, and other cargo to obtain an optimum centre of gravity for said aircraft.
8. The method described in claim 1, further comprising measuring environmental and surface conditions external to said aircraft to obtain environmental and surface data, wherein said database further comprises selected environmental data measurements for said various models of aircraft, and said environmental and surface data is compared to said database selected environmental data measurements for a same or similar model of aircraft as said aircraft.
9. The method described in claim 1, wherein the electrical rotating machine that propels the aircraft undercarriage to move the aircraft on the ground is an electrical rotating machine selected from the group consisting of HPO slotless AC induction machines, HPO short-pitched AC induction machines having more than 18 phases, HPO toroidally-wound AC induction machines, and combination HPO induction and switched reluctance machines.
10. The method described in claim 1, wherein the power supplied to the electrical rotating machine to propel the aircraft on the ground is an amount of power insufficient to change speed, acceleration, or torque of said aircraft or said aircraft component, causing speed, acceleration, or torque to measure zero, so that comparing the power measurement and the zero speed, acceleration, or torque measurement with said database relationships for a same or similar aircraft on a same or similar ground surface produces a minimum value for the estimate of weight of the aircraft.
11. The method described in claim 1, wherein said estimate of weight of said aircraft is logged in the database to increase the precision of data in said database or for use in fault detection.
12. The method described in claim 1, wherein the database is an electronic database, and said method is conducted electronically.
13. The method described in claim 1, wherein the database consists of graphs or tables, and the steps (c) and (d) are conducted manually.
14. The method described in claim 1, wherein said method is performed in combination with existing aircraft weight methods to obtain an estimate of weight of the aircraft.
15. The method described in claim 1, wherein said method is performed to produce a single or average estimated aircraft weight at one or more times or events in ground movement of an aircraft comprising at a start of taxi, immediately before a takeoff roll, and repeatedly over a period of taxiing.
16. An apparatus for performing the method for determining the weight of an aircraft described in claim 1, wherein said apparatus comprises
(a) a self-propelled aircraft undercarriage with an electrical rotating machine comprising an electric motor fitted in a drive wheel of said undercarriage that propels said aircraft on the ground;
(b) power sensing means for sensing and directly measuring power applied to said electric motor;
(c) current and voltage measuring means, for indirectly measuring power applied to said electric motor;
(d) one or more of aircraft speed, acceleration, and torque sensing means for sensing a change in speed, acceleration, and torque behavior of said aircraft in response to power applied to said electric motor; and
(e) a database of power and speed, acceleration, and torque measurements and relationships for a variety of models of aircraft having a variety of weights on the ground under a variety of tarmac and ground conditions.
17. The method of claim 1, wherein said speed measurement is obtained by measuring speed of said aircraft directly using speed sensing means or indirectly by measuring a speed of said aircraft component rotating with a speed proportional to said aircraft speed and calculating speed of said aircraft.
18. The method of claim 1, wherein said speed measurement is obtained by measuring rotational velocity of said electrical rotating machine when said aircraft is moving on the ground and calculating speed of said aircraft.
19. The method of claim 1, wherein said acceleration measurement is obtained by measuring acceleration directly with acceleration sensing means able to determine change in speed per unit of time or indirectly by measuring acceleration of said electrical rotating machine.
20. The method of claim 1, wherein said torque measurement is obtained by measuring torque directly with torque sensing means within said electrical rotating machine, within gears attached to the electrical rotating machine, or on a wheel of said aircraft.