1. A Wolfrom-type, webless planetary gear set, comprising:
two coaxial housing parts which can be rotated relative to each other each with inner toothing on a respective inner side, a toothed sun gear and a plurality of toothed planetary gears which roll between the sun gear and the inner sets of teeth and are flying in a floating manner, without a planetary gear carrier but instead their front sides slide along between two level, parallel, ring-shaped gliding surfaces which are located on inner sides of front faces of the two housing parts comprising an bearing arrangement between the two housing parts having bearing bodies that circulate along paths which:
a) are located radially outside at least one of the inner sets of teeth as well as
b) at an axial height between the two gliding surfaces of the housing for guidance of the planetary gears,
wherein the sun gear
c) exhibits an axial extension, which is shorter than a distance between both casing endplates, and
d) is supported by a bearing system at another bearing body, which is located at a face opposite to a connection for a drive motor and which is connected to an opposite casing endplate.
2. The planetary gear set as defined in claim 1, wherein at least one of the housing parts has a pot or bowl-shaped design.
3. The planetary gear set as defined in claim 1, wherein at least one of the housing parts has a cover-like design with a flashing running around a circumference, and the flashing is displaced radially to an inside relative to an edge of the housing parts.
4. The planetary gear set as defined in claim 1, wherein one or both of the two housing parts which can be rotated relative to each other have one level front face for a connection to a foundation, chassis or another machine or system part.
5. The planetary gear set as defined in claim 4, wherein one or both connection surfaces have bored holes or blind bored holes provided with an internal threading, arranged distributed in a ring around a rotation axis for positioning on a fundament, chassis or on any other machine or system part.
6. The planetary gear set as defined in claim 1, wherein the bearing arrangement has two rings which can be rotated against each other, between which the bearing arrangement rolls along.
7. The planetary gear set as defined in claim 6, wherein the rings which can be rotated against each other, each create a part of a housing shell.
8. The planetary gear set as defined in claim 6, wherein the rings of the bearing arrangement, which can be rotated against each other, are integrated with or connected to or screwed to one front plate each.
9. The planetary gear set as defined in claim 1, wherein the bearing arrangement between two rings which can be rotated against each other or the housing parts is are designed as a radial bearing.
10. The planetary gear set as defined in claim 1, wherein the bearing arrangement between two rings which can be rotated against each other or the housing parts have one or more ball andor roll bearing rows.
11. The planetary gear set as defined in claim 1, wherein at least one of the housing parts has a closed front face, without through passing or exit of a drive or power-down shaft.
12. The planetary gear set (1) as defined in claim 1, wherein one or both of rings or the housing parts which can be rotated against each other, have the inner toothing.
13. The planetary gear set as defined in claim 1, wherein an additional ring is located on an inner side of at least one of the two rings which can be rotated against each other or the housing parts, and the additional ring has the inner toothing.
14. The planetary gear set as defined in claim 12, wherein the inner sets of teeth on the rings which can be rotated against each other or the housing parts have identical or nearly identical pitch circle diameters.
15. The planetary gear set as defined in claim 12, wherein a difference in the number of teeth zH1, zH2 exists between the numbers of teeth zH1, zH2 of the inner sets of teeth of the two housing parts:
\u0394z=|zH1\u2212zH2|\u22671.
16. The planetary gear set as defined in claim 15, wherein the difference in the number of teeth \u0394z=|zH1\u2212zH2| between the numbers of teeth zH1, zH2 of the inner sets of teeth of the two housing parts is equal to or less than the number p of the planetary gears, the number of planetary gears that are meshing:
\u0394z=|zH1\u2212zH2|\u2266p.
17. The planetary gear set as defined in claim 12, wherein the toothing on the inner sides of both of the housing parts have different quotients from pitch circle diameter d and scaling p:
\u0394(d\u03c1)=|dH1\u03c1H1\u2212dH2\u03c1H2|>0.
18. The planetary gear set as defined in claim 12, wherein the toothing on the inner sides of the two housing parts are different from each other regarding their pitch circle diameter dH1, dH2 andor regarding their scaling PH1, PH2 so that the following inequality is fulfilled:
1\u03c0\u2266\u0394(d\u03c1)=|dH1\u03c1H1\u2212dH2\u03c1H2|\u2266p\u03c0.
19. The planetary gear set as defined in claim 12, wherein the sets of teeth on the inner sides of the two housing parts have the same pitch circle diameter d while their scalings PH1 PH2 differ from each other:
\u0394d=dH1\u2212dH2=0;
\u03c1H1(p*|zH1\u2212p|)\u2266\u0394\u03c1=|\u03c1H1\u2212\u03c1H2|\u2266\u03c1H1|zH1\u22121|.
20. The planetary gear set as defined in claim 1, wherein the number n of the planetary gears is two or more, or is three or more, or is four or more.
21. The planetary gear set as defined in claim 1, wherein two adjacent of a total of n planetary gears are displaced by 360\xb0n against each other.
22. The planetary gear set as defined in claim 1, wherein axes of all planetary gears run parallel to each other.
23. The planetary gear set as defined in claim 1, wherein all planetary gears are limited by cylindrical coating surfaces in which a toothing is integrated or molded.
24. The planetary gear set as defined in claim 1, wherein at least one of the planetary gears has a concentric recess along its longitudinal axis.
25. The planetary gear set as defined in claim 24, wherein an inner diameter of the recess in the planetary gears that is designed in such a manner that the remaining wall strength from a tooth foot to an inner bored hole is equal to or less than three times a tooth module of the planetary gears, or is equal to or less than twice the tooth module, or is equal to or less than a single tooth module.
26. The planetary gear set as defined in claim 1, wherein the planetary gears are manufactured with slightly larger dimensions so that, on the one hand, the planetary gears mesh in the sun gear and, on the other hand, the inner toothing is forced to deform slightly.
27. The planetary gear set as defined in claim 1, wherein at least one of the planetary gears has continuous toothing between its two front sides.
28. The planetary gear set as defined in claim 1, wherein at least one of the planetary gears is scaled crosswise to its longitudinal axis and has toothing sections which are rotated against each other in azimuthal direction.
29. The planetary gear set as defined in claim 28, wherein the toothing sections of the at least one of the planetary gears which are rotated relative to each other have the same number of teeth zp.
30. The planetary gear set as defined in claim 28, wherein the toothing sections of the at least one of the planetary gears which are rotated relative to each other are arranged on separate gears which are inserted on a common shaft.
31. The planetary gear set as defined in claim 1, wherein a toothing of the sun gear has a shorter axial length than a length of the planetary gears.
32. The planetary gear set as defined in claim 1, wherein a toothing of the sun gear has an axial length which is about half an axial length of at least one of the planetary gears.
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 computer program product for controlling a plurality of control effectors of an aerodynamic vehicle having a plurality of states, the computer program product comprising a computer-readable storage medium having computer-readable program code embodied in said medium, the computer-readable program code comprising:
a first executable portion for determining a current commanded state of the plurality of control effectors including the current commanded states of nozzle vectoring and at least one aerodynamic surface, wherein the current commanded state of the plurality of control effectors is capable of being different than the current state of the plurality of control effectors;
a second executable portion for determining differences between anticipated changes in the plurality of states of the aerodynamic vehicle based upon the current commanded state of the plurality of control effectors and desired changes in the plurality of states of the aerodynamic vehicle, wherein the second executable portion determines the anticipated changes in the plurality of states based upon the current commanded state of each control effector and current flight conditions; and
a third executable portion for controlling the plurality of control effectors at least partially based upon the differences in order to implement at least a portion of the desired changes in the plurality of states of the aerodynamic vehicle.
2. A computer program product according to claim 1 wherein said third executable portion adjusts a control effector that effects a greater portion of the desired change more than a control effector that effects a smaller portion of the desired change.
3. A computer program product according to claim 1 further comprising a fourth executable portion for limiting the permissible change of at least one of the control effectors, wherein said third executable portion controls the plurality of control effectors based upon the weighted differences subject to limitations in the permissible changes of at least one of the control effectors in order to implement at least a portion of the desired change in the plurality of states of the aerodynamic vehicle without exceeding the permissible changes of at least one of the control effectors.
4. A computer program product according to claim 3 wherein said fourth executable portion limits the permissible rate of change of at least one of the control effectors.
5. A computer program product according to claim 3 wherein said fourth executable portion limits at least one of the control effectors to within a predefined range.
6. A computer program product according to claim 1 further comprising a fifth executable portion for weighting the differences between the anticipated and desired changes based upon a predetermined criteria, and wherein said third executable portion controls the plurality of control effectors at least partially based upon the weighted differences.
7. A computer program product according to claim 6 wherein said fifth executable portion weights the differences based upon the relative importance of the respective states of the aerodynamic vehicle.
8. A computer program product according to claim 6 wherein said fifth executable portion weights the differences based upon a predefined penalty having an effect that varies based upon the magnitude of a respective difference.
9. A computer program product according to claim 1 wherein said second executable portion determines a first dot product of a vector representing the current commanded state of each control effectors and a matrix representing changes in the plurality of state rates of the aerodynamic vehicle in response to changes in the plurality of control effector, wherein the matrix is comprised of a plurality of terms, each term representing the anticipated change in a respective state rate of the aerodynamic vehicle in response to the change of a respective control effector, and wherein said second executable portion also obtains a vector difference between the first dot product and a vector representing the desired change in the plurality of states of the aerodynamic vehicle.
10. A computer program product according to claim 9 further comprising a sixth executable portion for constructing the matrix to represent changes in the state rates associated with lift, attitude and a plurality of engine parameters of the aerodynamic vehicle in response to changes in the plurality of control effectors.
11. A computer program product according to claim 9 further comprising a seventh executable portion for determining a second dot product of the weighted vector difference and a transpose of the matrix representing changes in the plurality of state rates of the aerodynamic vehicle in response to changes in the plurality of control effectors, and wherein said third executable portion controls the plurality of control effectors at least partially based upon the second dot product.
12. A computer program product according to claim 11 further comprising an eighth executable portion for weighting the second dot product based upon the relative importance of the respective control effectors such that the plurality of control effectors are controlled based, at least partially, upon the weighted second dot product.