Embodiments of the present invention relate to a rocket or ballistic launch rotary wing air vehicle.

Rocket or ballistic launch rotary wing vehicle

Improved stability is provided in a hingeless helicopter rotor by inclining the principal elastic flexural axes and coupling pitching of the rotor blade with the lead-lag bending of the blade. The primary elastic flex axes can be inclined by constructing the blade of materials that display non-uniform stiffness and the specification describes various cross section distributions and the inclined flex axes resulting therefrom. Also described are arrangements for varying the pitch of the rotor blade in a predetermined relationship with lead-lag bending of the blade, i.e., bending of the blade in a plane parallel to its plane of rotation.

Hingeless helicopter rotor with improved stability

A blade retention member which is compressible and torsionable in installation and operation of a rotor control system, the torsional stiffness of the member decreasing with increasing rotor blade speed, the compressible stress not exceeding the strength of the material out of which the member is fabricated. Its inboard end is fixedly connected to either the rotor blade or a movable hub enveloping it at its inboard end, while its outboard end is fixedly connected to the fixed hub or extension thereof in the rotor system. Means are also provided in the system for isolating bearing means supporting the blade from the blade retention member. The member itself comprises a plurality of circumferentially spaced parallel rails spacedly disposed radially equidistant and arcuately about from a common centerline coincident with the feathering axis for the blade.

A retention member

Each rotor blade is rigidly affixed to a pair of strap members which are also rigidly connected to a rotor hub. Each strap member is defined as an elongated open box beam of rectangular cross section. Each strap member has its open web located on the side of the rectangle opposite that of its associated strap member of a pair. A pitch shaft which is located intermediate the two strap members associated with the given rotor blade, is rigidly attached to that rotor blade, and is rotatably connected with respect to the rotor hub. In alternative configurations, the strap members are configured as various alternative solid or open web designs, but all are configured as pairs having a pitch shaft therebetween.

Composite hingeless rotor hub for rotary wing aircraft

Bei einem Rotor, insbesondere fur ein Drehflugelflugzeug, bei dem die Einstellwinkelbeweglichkeit des einzelnen Rotorblattes gegenuber einer Rotornabe entweder durch einen torsionselastischen Blatthals zwischen einer Blattwurzel und einem Blattflugel oder durch einen Blattanschlus an einem torsionselastischen Rotornabenarm sichergestellt ist und die Blatteinstellwinkelsteuerung mittels einer Steuerstange uber eine in koaxialer Anordnung dem Blatthals bzw. Rotornabenarm entlang bis zum Blattflugel bzw. zur Blattwurzel sich beruhrungsfrei erstreckende, torsionssteife Blattsteuerhulle (5) erfolgt, ist diese blattwurzel- bzw. rotornabenseitig mittels wenigstens eine Strebe (6) abgestutzt , welche in Blattlangsrichtung ein T-Profil aufweist, dessen Profilsteg (6.2) der Blattsteuerhulle (5) zugeordnet und dessen Profilfus (6.1) torsions­elastisch und der Blattwurzel 2.1) bzw. Rotornabe (11) zugeordnet ist, wobei deren Verbindung mit dem Profilfus (6.1) auf seine beiden Enden beschrankt ist. Damit vermag die Strebe (6) nicht nur eine Stutzfunktion fur die Blattsteuerhulle (5) zu erfullen, sondern ist zugleich als ein Torsionslager wirksam, d.h. ermoglicht Drehwinkelbewegungen der Blatt­steuerhulle (5).

Rotor, insbesondere eines Drehflügelflugzeuges

THIS INVENTION RELATES TO AN IMPROVED ATTACHMENT FOR A ROTOR BLADE IN A ROTATING WING AIRCRAFT HAVING A SEMIRIGID ROTOR SYSTEM. MORE PARTICULARLY, THE INVENTION PROVIDES A LOW COST, LIGHTWEIGHT, LOW MAINTENANCE ROTOR SYSTEM EMBODYING ALL OF THE DESIRED CHARACTERISTICS OF THE SEMI-RIGID HUB BUT WITH A MINIMUM CHANCE OF FATIGUE OR FAILURE.

Rotor hub and blade attachments

This invention relates to an improved attachment for a rotary wing aircraft having opposed pairs of rotor blades about a central rotor hub in which diametrically extending pairs of cables are supported on the hub and have their ends interconnect the rotor blades and act as hinges therefore and balance the radial load on the cables between associated blades. A rigid member, rotatable in a hub fixture, connects the hub to each rotor blade and acts as a pitch change tube and droop stop. A transverse pivot in this member at the blade connector also allows for lead-lag movement.

Attachment for rotor hub and pairs of blades

This invention relates to an improved design for autogyros. It involves a more desirable layout of cockpit/engine placement than heretofore thought of. It provides for improved efficiency, visibility and balance and solves some of the problems of recent autogyros. Further, it provides for an improved and simplified rotor spin up mechanism.

Autogyro having blade tip jets

This invention relates to an improved attachment for rotary wing aircraft where a pair of cables are connected between a central rotor hub and a bearing fixture adjacent the inner end of a blade. A rotatable spar is journaled in the bearing fixture and supports the blade such that the blade may be feathered or changed in pitch by rotating the spar independently of the position of the cables or fixture. The cables allow the blade to change in lead-lag and in flap movements but do not interfere with the pitch control of the blade. A pitch control tube is journaled in a fixture on the hub and is pivotally connected to the rotatable spar to change the pitch of the blade and also provide the droop stop therefor.

Rotor blade and hub attachment and control

A drag operated collective pitch control system is provided for gyroplane rotary wing aircraft. The system employs drag surfaces which are selectively engaged while the hub is rotating to actuate the system. Each blade mount is provided with a feathering pivot. Pinion gears control the pitch of each blade, and the pinions, mounted on the hub, are engaged by a pair of ring gears, also carried on the hub. To operate the system, either one or the other of the ring gears, to which the drag surfaces are coupled, is engaged by suitable drag means. The pitch of all the blades is thereby adjusted simultaneously.

Gerald L Breuner

Papers

Rotor hub and blade attachments

Attachment for rotor hub and pairs of blades

Autogyro having blade tip jets

Rotor blade and hub attachment and control

Drag operated rotor pitch adjustment system for gyroplanes