All The Claims

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.

1. A dispenser for dispensing a composition in response to level changes in a liquid in a tank, the dispenser comprising:
a container for holding the composition;
a discharge conduit in fluid communication with the container;
an air inlet in fluid communication with the container; and
a level sensing member mounted to the dispenser such that a lower end of the level sensing member contacts the liquid in the tank and senses its level;
whereby a rise of the liquid in the tank between a lower liquid level and a higher liquid level can cause the level sensing member to alter air pressure in a headspace of the container above the composition and thereby cause a controlled discharge of the composition from the discharge conduit; and
whereby a fall of the liquid in the tank between the higher liquid level and the lower liquid level causes the level sensing member to alter pressure in the headspace and thereby causing air to be vented into the headspace from the air inlet.
2. The dispenser of claim 1, wherein:
the dispenser further comprises a holder structured to mount the container on a top end of an outer wall of the tank.
3. The dispenser of claim 2, wherein:
the holder has at least one hook for mounting the container on a top end of an outer wall of the tank.
4. The dispenser of claim 1, further comprising:
a vent tube having an upper end opening and a lower end opening, the upper end opening of the vent tube being in fluid communication with the air inlet, and the lower end opening of the vent tube being in fluid communication with a section of an interior space of the container.
5. The dispenser of claim 1, further comprising:
a compartment in fluid communication with the container and in fluid communication with the discharge conduit, the compartment accumulating an amount of the composition before a portion of the amount of the composition is discharged from the discharge conduit.
6. The dispenser of claim 5, wherein:
the compartment is in fluid communication with the container by way of a composition supply conduit having a lower orifice,
the compartment includes an exit passageway having an upper inlet and a lower outlet, and
the lower orifice of the composition supply conduit is positioned in the compartment below the upper inlet of the exit passageway of the compartment.
7. The dispenser of claim 6, wherein:
the upper inlet of the exit passageway is located on a top surface of an interior shoulder of the compartment, and
the lower orifice of the composition supply conduit is positioned in a well below the top surface of the interior shoulder of the compartment.
8. The dispenser of claim 1, wherein:
an air gap hole is located in a discharge passageway between the container and a discharge opening of the discharge conduit.
9. The dispenser of claim 1, further comprising:
a vent tube having an upper end opening and a lower end opening, the upper end opening of the vent tube being in fluid communication with the air inlet, and the lower end opening of the vent tube being in fluid communication with a lower section of an interior space of the container; and
a supply tube having an upper end opening and a lower end opening, the upper end opening of the supply tube being in fluid communication with the discharge conduit, and the lower end opening of the supply tube being in fluid communication with the lower section of the interior space of the container.
10. The dispenser of claim 1, further comprising:
a closure for sealing a mouth of the container.
11. The dispenser of claim 10, further comprising:
a vent tube attached to the closure, the vent tube having an upper end opening and a lower end opening, the upper end opening of the vent tube being in fluid communication with the air inlet, and the lower end opening of the vent tube being in fluid communication with a lower section of an interior space of the container; and
a supply tube attached to the closure, the supply tube having an upper end opening and a lower end opening, the upper end opening of the supply tube being in fluid communication with the discharge conduit, and the lower end opening of the supply tube being in fluid communication with the lower section of the interior space of the container.
12. The dispenser of claim 10, wherein the air inlet passes through the closure.
13. The dispenser of claim 10, further comprising a latch for holding the closure against the mouth of the container.
14. The dispenser of claim 1, wherein the tank is a toilet tank and the liquid is water.
15. The dispenser of claim 1 wherein:
the dispenser further comprises a housing and a diaphragm, the housing having an open end that is sealed by the diaphragm thereby defining an interior space of the housing, the interior space being in fluid communication with the headspace of the container above the composition; and
the level sensing member is a float; and
the float is attached to the diaphragm;
whereby the fall of liquid in the tank from a higher liquid level to a lower liquid level, the diaphragm may flex in a first direction and displace air in the headspace to be vented into the headspace from the air inlet; and
whereby the rise of liquid in the tank between the lower liquid level and the higher liquid level causes the diaphragm to flex in a second direction to alter air pressure in the headspace of the container above the composition and thereby cause the controlled discharge of the composition from the discharge conduit.
16. The dispenser of claim 1, wherein:
the level sensing member is a float;
the float is attached to a rod; and
a longitudinal position of the float on the rod can be adjusted.
17. A method for delivering a composition to a toilet bowl of a toilet having a toilet tank, the method comprising:
(a) providing a dispenser having
(i) a container holding the composition,
(ii) a level sensor in fluid communication with headspace above the composition in the container,
(iii) a discharge conduit in fluid communication with the container, and
(iv) an air inlet in fluid communication with the container;

(b) mounting the level sensor such that a lower end of the level sensor contacts water in the toilet tank;
(c) positioning the discharge conduit such that a discharge opening of the discharge conduit can deliver the composition to the toilet bowl; and
(d) flushing the toilet whereby a fall of liquid in the tank between a higher liquid level and a lower liquid level causes the level sensing member to alter air pressure in a headspace of the container above the composition and thereby causing air to be vented into the headspace from the air inlet, and a subsequent rise of the liquid in the tank between a lower liquid level and a higher liquid level causes the level sensing member to alter pressure in the headspace and thereby causes a controlled discharge of the composition from the discharge conduit.
18. The method of claim 17, wherein the discharge opening of the discharge conduit is positioned in or above an overflow tube of the toilet.
19. The method of claim 17, wherein the container is mounted on a top end of an outer wall of the toilet tank.
20. The method of claim 17, wherein the container is mounted on a top end of an outer wall of the toilet tank such that the container is located outside the toilet tank.
21. The method of claim 17, wherein the dispenser is maintained at constant pressure during the fall and rise of liquid in the tank.
22. The method of claim 18, wherein the constant pressure is atmospheric pressure.

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. Headlight, in particular for motor vehicles, with an elongated incandescent body (2) with an incandescent body longitudinal axis (4), with a reflector (6) associated with the incandescent body for bundling of light emitted from the incandescent body, and with a photoconductor, in which light emitted from the reflector (6) in a direction of an optical axis (10) is coupled-in by means of a coupling-in surface (12) of the photoconductor (8), characterized in that the incandescent body longitudinal axis (4) forms an angle a with the optical axis (10) of >0 degrees.
2. Headlight as defined in claim 1, characterized in that the angle () between the incandescent body longitudinal axis (4) and the optical axis (10) 30 degrees.
3. Headlight as defined in claim 1, characterized in that the angle () between the incandescent body longitudinal axis (4) and the optical axis 45 degrees.
4. Headlight as defined in claim 1, characterized in that the angle () between the incandescent body longitudinal axis (4) and the optical axis (10) 60 degrees.
5. Headlight as defined in claim 1, characterized in that the angle () between the incandescent body longitudinal axis (4) and the optical axis (10)90 degrees.
6. The headlight as defined in claim 1, characterized in that incandescent body images (62, 66) emitted from the incandescent body (2) and bundled from the reflector (6) are produced with large and small projection surfaces.
7. Headlight as defined in claim 1, characterized in that the photoconductor (8) andor the coupling-in surface (12) have a non-circular cross section with an extension in a longitudinal and a transverse direction (56, 72; 58, 74).
8. Headlight as defined in claim 7, characterized in that the photoconductor (8) andor the coupling-in surface (12) have a cross section with a maximum extension in a longitudinal direction.
9. Headlight as defined in claim 7, characterized in that the photoconductor andor the coupling-in surface have a cross section with a maximum extension (60), wherein a direction of the maximum extension deviates from a direction of the longitudinal extension (54) of the cross section.
10. Headlight as defined in claim 9, characterized in that the incandescent body images (62, 66) with large projection surfaces lie parallel to a maximum extension (60) of the coupling-in surface (12) of the photoconductor (8).
11. Headlight as defined in claim 6, characterized in that the incandescent images (62, 66) with small projection surfaces lie in regions of the coupling-in surface that are not covered or only partially covered by incandescent body images with large projection surfaces.
12. Headlight as defined in claim 1, characterized in that the incandescent body (2) is formed as an incandescent coil.
13. Headlight as defined in claim 1, characterized in that the incandescent body (20) is formed as an arc lamp.
14. Headlight as defined in claim 13, characterized n that the arc lamp is produced from a gas discharge lamp.