U.S. patent number 3,578,877 [Application Number 04/735,956] was granted by the patent office on 1971-05-18 for rotor construction with elastic interconnection of opposite blades.
This patent grant is currently assigned to Bolkow Gesellschaft mit beschrankter Haftung. Invention is credited to Karlheinz Mautz.
United States Patent |
3,578,877 |
Mautz |
May 18, 1971 |
ROTOR CONSTRUCTION WITH ELASTIC INTERCONNECTION OF OPPOSITE
BLADES
Abstract
A four blade rotor construction for helicopters includes means
for rotatably mounting each blade at equally spaced angular
locations around the rotor hub. Diametrically opposed rotor blades
are connected with each other by torsion elastic bands or endless
members which are stretched across the center of the rotor head
with one of the bands being arranged to pass through and intersect
the other. The endless bands are formed of laminations of torsion
elastic bands and the laminations of one of the bands which
connects one pair of blades are arranged in a substantially
vertical orientation and the laminations of the other band which
interconnects the two adjacent blades are arranged in a
substantially horizontal plane. The clearance between the two band
loops at the center of the rotor head is such that collective and
cyclic pitch controls are possible.
Inventors: |
Mautz; Karlheinz (Munich,
DT) |
Assignee: |
Bolkow Gesellschaft mit
beschrankter Haftung (Ottobrunn bei Munich, DT)
|
Family
ID: |
6986954 |
Appl.
No.: |
04/735,956 |
Filed: |
June 4, 1968 |
Foreign Application Priority Data
Current U.S.
Class: |
416/134R;
416/114; 416/205; 416/136; 416/140; 416/134A |
Current CPC
Class: |
B64C
27/327 (20130101) |
Current International
Class: |
B64C
27/32 (20060101); B64c 027/48 () |
Field of
Search: |
;170/160.53,160.58,160.5,160.51
;416/131,134,135,136,138,140,141 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
|
|
|
|
|
|
|
1,334,446 |
|
Jul 1963 |
|
FR |
|
642,206 |
|
Jul 1962 |
|
IT |
|
Primary Examiner: Powell, Jr.; Everette A.
Claims
I claim:
1. A four blade rotor for helicopters comprising, a rotatable rotor
head, four rotor blades symmetrically carried by said rotor head
for rotation therewith about a central head axis and having root
portions rotatably supported in said head for blade angle
variation, and first and second endless laminated torsion-elastic
loop members connecting the root portions of respective
diametrically opposed rotor blades, said first endless laminated
loop member passing entirely through said second endless laminated
loop member, means rotatable mounting each of said blades to said
rotor head, and spring means between said mounting means and said
rotor head for centering each of said blades relative to said rotor
head free of play.
2. A four blade rotor for helicopters comprising a rotatable head
having four angularly symmetrically arranged and radially opening
receiving sleeves for the respective rotor blades, means rotatably
mounting said head for rotation about a substantially central axis,
a rotor blade having a blade root sleeve rotatable mounted in each
of said receiving sleeves, a clamping ring carried in said
receiving sleeve and having a bolt member extending across the axis
of said blade, means securing said clamping ring to said receiving
sleeve for rotation with said receiving sleeve and said blade for
varying the pitch angle of said blade, first and second endless
loop members engaged around said bolt members of respective
diametrically opposed rotor blades, said first and second endless
loop members intersecting centrally within said rotor head and one
of said first and second endless loop members passing through the
other, a retaining nut threaded over said retaining ring and
bearing against said root sleeve, said nut being threaded to shift
the position of said retaining ring axially along said root sleeve
for varying the tension on said first and second loop members.
3. A four blade rotor construction, according to claim 2, wherein
said rotor head has a ledge abutment at the interior of each of
said receiving sleeves, the root sleeves of each of said blades
being spaced from said ledge abutment, and spring means disposed
between said root sleeve and said ledge abutment and centering each
of said root sleeves around said head free of play.
4. A four blade rotor construction, according to claim 2, wherein
said means mounting said root sleeve within said rotor head
receiving sleeve comprises two axially spaced roller bearing
sets.
5. A four blade rotor for helicopters comprising a rotatable rotor
head, four rotor blades symmetrically carried by said rotor head
for rotation therewith about a central head axis and having root
portions rotatably supported in said head for blade angle variation
for rotation about axes lying in substantially a common plane, and
first and second endless laminated torsion-elastic loop members
connecting the root portions of respective diametrically opposed
rotor blades, said first endless laminated loop member passing
entirely through said second endless laminated loop member, said
first endless laminated loop member having laminations which are
arranged substantially in a vertical plane, said second endless
laminated loop member having laminations which are arranged in a
substantially horizontal plane.
6. A four blade rotor for helicopters comprising a rotatable rotor
head, four rotor blades symmetrically carried by said rotor head
for rotation therewith about a central head axis and having root
portions rotatably supported in said head for blade angle variation
for rotation about axes lying in substantially a common plane,
first and second endless laminated torsion-elastic loop members
connecting the root portions of respective diametrically opposed
rotor blades, said first endless laminated loop member passing
entirely through said second endless laminated loop member, and
means carried by each of said rotor blades adjacent their root
portions for adjustably connecting and tensioning the associated
first and second endless laminated loop members.
7. A four blade rotor for helicopters comprising a rotatably rotor
head, four rotor blades symmetrically carried by said rotor head
for rotation therewith about a central head axis and having root
portions rotatably supported in said head for blade angle variation
for rotation about axes lying in substantially a common plane,
first and second endless laminated torsion-elastic loop members
connecting the root portions of respective diametrically opposed
rotor blades, said first endless laminated loop member passing
entirely through said second endless laminated loop member, a bolt
member extending across the axis of each of said blades with which
said respective ones of said first and second endless laminated
loop members are engaged, and means adjustably positioning said
bolt member on each of said blades.
8. A four blade rotor for helicopters comprising a rotatable rotor
head, four rotor blades symmetrically carried by said rotor head
for rotation therewith about a central head axis and having root
portions rotatably supported in said head for blade angle variation
for rotation about axes lying in substantially a common plane,
first and second endless laminated torsion-elastic loop members
connecting the root portions of respective diametrically opposed
rotor blades, said first endless laminated loop member passing
entirely through said second endless laminated loop member, a
sleeve having a cross bolt therethrough, means adjustably mounting
said sleeve in respective ones of each of said root portions for
radial inward and outward adjustment, said first and second endless
laminated loop members being looped over corresponding
diametrically opposite cross belt bolts of said blades.
9. A four blade rotor for helicopters comprising a rotatable rotor
head, four rotor blades symmetrically carried by said rotor head
for rotation therewith about a central head axis and having root
portions rotatably supported in said head for blade angle variation
for rotation about axes lying in substantially a common plane, and
first and second endless laminated torsion-elastic loop members
connecting the root portions of respective diametrically opposed
rotor blades, said first endless laminated loop members passing
entirely through said second endless laminated loop member, said
first endless laminated loop member extending substantially
vertically and having horizontal lamina, said second endless
laminated loop member extending horizontally and having
substantially vertical arranged lamina.
Description
SUMMARY OF THE INVENTION
This invention relates, in general, to the construction of rotors
of helicopters and, in particular, to a new and useful four blade
rotor construction for helicopters having blades which are
rotatably mounted in the head and are connected at their connecting
respective opposite blades intersecting centrally in the head.
Rotors for helicopters are known which include traction laminations
of a pack of laminations of an interconnecting band which is
associated with a pair of rotor blades. In such construction, the
laminations are arranged in alternating layers which are separately
centrally connected to a bolt arranged coaxially to the axis of the
rotor head. By such an arrangement, each pack of laminations, which
is secured to the center of the rotor head against displacement and
rotation during angular movement of the rotor blade, may be twisted
only up to the limit of its centric clamping in the head. This
means that the specific torsion for the entire twisting angle range
related to the free torsion length of the pack of laminations is
very great.
If each rotor blade is to have, for a collective incidence in range
of
0.degree. .delta..sub.collective +16.degree. (1)
And cyclic incidence range of
-11.degree. .delta..sub.cyclic +11.degree. (2)
This results in a total incidence range of
-11.degree. to +27.degree.,
Hence 38.degree.. This incidence range is transmitted to the pack
of lamination and twists the latter or half a lamination length so
that the specific torsion is
The maximum specific angle or twist is achieved with full
collective and cyclic incidence in a positive direction and is
For constructional and aerodynamic reasons, it has been attempted
to keep the rotor head diameter and the length of the laminations
as small as possible. But since the specific torsion must not
exceed a maximum admissible value, this value becomes the quantity
determining the dimensions of the rotor head under certain
conditions. A reduction of the specific torsion is only possible in
the rotors of the known or suggested types by lengthening the
laminations.
In accordance with the present invention, an improved helicopter
rotor is provided by connecting opposite pairs of rotor blades with
laminated bands constructed so that specific torsion is
considerably reduced and thus it is possible to use bands with
shorter laminations or the fatigue strength of the laminations of
conventional length can be considerably increased. The problem is
solved in accordance with the invention by using laminations which
are constructed as portions of endless stretched loops or bands.
The laminations of one band connect one pair of blades and are
arranged substantially in a vertical orientation whereas the
laminations of the other band connects the adjacent pair of blades
and they are arranged in a horizontal plane and conducted through
the loop of the vertical laminations. The clearance of the two
loops and the lamination width are so tuned to each other that both
collective and cyclic pitch controls are possible without impairing
the respective crossed laminations. Because of such an arrangement,
the cyclic pitch no longer contributes to the torsion of the
laminations. Since a positive cyclic angle of incidence of a rotor
blade always corresponds to an equal negative cyclic angle of
incidence of the opposite rotor blade, the entire pair of rotor
blades including the pack of laminations is tipped in a cyclic
pitch control about the axis of the angular adjustment.
In collective pitch control, the two opposing rotor blades are
turned equally but in opposite directions whereas in cyclic pitch
control, they are turned equally in the same direction. The sum of
the collective blade angles of the two opposing blades is
distributed over the entire length of the lamination so that we
obtain for the above-mentioned example:
Since the torsion from the untwisted form of the pack of
laminations is only possible in a direction corresponding to the
positive incidence of the blades, the value of the torsion is at
the same time the value of the maximum specific angle of twist.
The specific angle of twist can be further reduced in accordance
with another feature of the invention by arranging each rotor blade
so that it has an angle of incidence which is approximately in the
center of the entire collective incidence range. From this fixed
presetting each blade can be turned by the same amount
corresponding to half the collective incidence range in a positive
and in a negative direction. Thus, the specific angle of twist of
the pack of laminations is reduced by half, but it can appear in
both directions of twist. The following relationship is present
In accordance with another feature of the invention, the tension of
the laminations can be adjusted and readjusted during assembly
because of the use of fastening devices which permit a shift of
position of each rotor blade and the securing of the rotor blade in
its suspension sleeve free from play. In order to insure that the
freedom from play will be present during all operating states of
the rotor, spring elements are provided which bear on the rotor
head and on the blade sleeve.
Since the individual laminations of the bands interconnecting
opposite pairs of rotors are displaced toward each other by
twisting, intermediate layers of material with a substantially
lower friction with respect to the laminations are employed. For
example, for steel laminations, intermediate layers of
tetrafluoroethylene are employed. The intermediate layers are
arranged between the individual steel laminations in order to
reduce the wearing of these laminations by friction. The
laminations may be made such that they lie parallel to the axes of
the the bolts about which they are looped to secure them to the
associated rotor blade in the manner of a number of laminations or
a pack. On the other hand, each pack of laminations can also
consist of a number of fitted loops or of a long band wound in
several layers. All elastic materials with sufficient prolonged
alternating strength stress, for example, spring steel or fiber
reinforced plastics may be used for the lamination material.
Accordingly, it is an object of the present invention to provide a
four blade rotor for helicopters in which the roots of opposing
blades are interconnected by stretched loops of laminations and,
wherein adjacent bands intersect centrally in the rotor head and
one advantageously passes through the other and wherein one is
advantageously arranged in a horizontal plane and the other in a
vertical plane.
Another object of the invention is to provide an improved rotor
head construction for helicopters wherein the rotor blades are
mounted in sleeves at their roots for rotation at respective fixed
locations on the rotor head and wherein the rotor head is hollow to
provide passage for endless bands which interconnect the roots of
opposing rotor blades, and wherein the blades may be adjustably
secured in position by interconnecting or locking sleeve
elements.
A further object of the invention is to provide a rotor head for a
helicopter which is simple in design, rugged in construction and
economical to manufacture.
The various features of novelty which characterize the invention
are pointed out with particularity in the claims annexed to and
forming a part of this specification. For a better understanding of
the invention, its operating advantages and specific objects
attained by its use, reference should be had to the accompanying
drawings and descriptive matter in which there are illustrated and
described preferred embodiments of the invention.
BRIEF DESCRIPTION OF THE DRAWINGS
In the Drawings:
FIG. 1 is a partial side elevational and partial sectional view of
a rotor head for a helicopter constructed in accordance with the
invention;
FIG. 2 is a schematic top perspective view of the interconnecting
bands for opposed rotor blades of the rotor head indicated in FIG.
1;
FIG. 3 is a view similar to FIG. 2, but with the loops tipped for
cyclic pitch of the rotor blades;
FIG. 4 is a view similar to FIG. 2, but with the loops twisted for
collective pitch; and
FIG. 5 is a partial sectional view on an enlarged scale of a pack
of laminations forming the connecting bands.
GENERAL DESCRIPTION OF THE PREFERRED EMBODIMENTS
Referring to the drawings, in particular, the invention embodied
therein comprises a four blade rotor construction for helicopters,
which includes a rotor shaft 1 which is secured by means of bolts 2
to a rotor head 3 for rotation therewith. The rotor head 3 carries
a number of rotor arms having bearing sleeves 4 corresponding to
the number of rotor blades 9. Each blade 9 carries a blade root
sleeve 5, which is secured to the blade by one or more securing
bolts 6. The blade root sleeve 5 extends into the associated
bearing sleeve 4 and is rotatably supported therein at two axially
spaced locations on roller bearings 7 and 8. The bearings 7 and are
arranged as far apart as possible in order to provide an adequate
supporting force for each blade and to accommodate forces
originating from the swinging and striking movements of the
blades.
The rotor head 3 includes four equally spaced bearing sleeves 4 and
each two opposing blade root sleeves which are rotatably supported
therein are connected together by packs of laminations designed as
loops or endless bands 10 and 18.
In accordance with a feature of the invention each blade root
sleeve 5 carries a clamping ring 12, which is secured by a wedge 13
against rotation in respect to its associated root sleeve. The
clamping carries a cross bolt or loop-holding member 11 around
which each loop 10 or 18 is directed. An initial stress can be
imparted to the loop 10 by adjusting a retaining nut 14 which is
threaded on the clamping ring 12 and which bears against a collar
15 of the blade root sleeve 5. The blade root sleeve 5 is pulled by
the tightened loop 10 by the threading of the retaining nut 14 and
stresses one side of a cup spring 17. The spring 17 contacts an
axial bearing 16 arranged at the end of the root sleeve and bears
at its opposite or inner end against the rotor head 3. The cup
spring 17 ensures centering, free from play, of the two opposing
blade angle sleeves 5, 5 with respect to the axis of rotation of
the rotor even at full rotor speed when the laminations of the
bands 10 are expanded by centrifugal forces.
In the arrangement indicated in FIG. 2, two crossed loops or bands
20 and 21 are arranged in the untwisted state with the loop 20
disposed in a generally vertical orientation or plane and the loop
21 in a horizontal orientation. The loop 21 passes through the loop
20 and the breadth and width of the loops are so selected that the
loops do not interfere with each other in their movement in all
collective and cyclic blade angles.
In the representation of the embodiment of FIG. 2, all of the
blades are arranged at a fixed positive setting angle .delta..sub.1
=+8.degree. . At the maximum collective angle of incidence, where
.delta..sub.1 maximum = +16.degree. each rotor blade is therefore
only twisted by an additional 8.degree.. The loop over its entire
length therefore is twisted by two times +8.degree. or +16.degree..
At the minimum collective angle of incidence, the twist
.delta..sub.1 minimum = 0.degree. and, correspondingly, there will
be a twist in the amount of not more than -16.degree..
In the embodiment of FIG. 3, loop members 30 and 31 are shown as
schematically connecting blades 34 and 35 and 32 and 33,
respectively. The blades 32, 33, 34 and 35 are arranged so that
they do not have any fixed setting angle .delta..sub.1. The rotor
blades 32 and 33 connected with the loop 30 assume an angle of
incidence .delta..sub.2 determined by the inclination of the loop
30. Thus, rotor blade 32 is imparted with a positive incidence
angle and rotor blade 33 has a negative incidence angle. The rotor
blades 34 and 35 are indicated as not having any fixed incidence
angle settings.
In the embodiment indicated in FIG. 4, the loops 40 and 41 are
shown as being schematically connected between blade paths 43 and
45 and 42 and 44, respectively. The position of the loops 40 and 41
corresponds to the position where collective pitch control is
effected. All rotor blades 42, 43, 44 and 45 are set by the same
positive angle .delta..sub.3. Both the loop 40 and loop 41 twist by
the same amount.
In the sectional view indicated in FIG. 5, the pack of laminations
for a loop member generally designated 20, advantageously comprises
steel laminations 50 between which are inserted intermediate layers
of tetrafluoroethylene 51. The material 51 is of less friction than
the material of the laminations 50 in order to reduce deterioration
of the laminations by friction.
While specific embodiments of the invention have been shown and
described in detail to illustrate the application of the inventive
principles, it will be understood that the invention may be
embodied otherwise without departing from such principles.
* * * * *