Transmission helicopter - a set of structural elements (units) of the kinematic connection propulsion (main) engine with a carrier (or curtain) of screws and other consumers of power, including the aggregates and systems necessary for the maintenance of the transmission and drives other power consumers.
The composition of the transmission:
- - The main and intermediate gearboxes;
- - RV reducer;
- - Connecting and synchronizing shafts with couplings (flexible, universal, slotted and others.) And their support;
- - Oil cooling fans;
- - Freewheel (MA);
- - Brake HB.
Transmission together with its systems and established IA units it must be designed and constructed so that the expected operating conditions for life, the life of its critical failures (resulting in a catastrophic situation) per flight hour were estimated in accordance with the requirements.
When failure of one or more engines (helicopter engines with the number more than one) power from running engines must be transmitted to the screws and other devices to ensure the continuation of the flight and control of the helicopter. Upon cancellation of all motors must be kept at the proper functioning of the screw autorotation and the other device is required to control at lower landing helicopters. The transmission is equipped with devices for the automatic disconnection from her any engine in the event of shutdown or failure (for example, using the Ministry of Agriculture).
The layout of the transmission must be capable of servicing and replacement of parts in accordance with the guidelines for the technical operation and maintenance.
To eliminate the electric potential difference between the main transmission elements and associated elements of the helicopter must be secured, where appropriate, a compound of these elements in the total weight of the webs or direct contact metallization. Auxiliary units must usually have a "weak link" for the transmission protection against excessive torque. "Weakest Link" is constructed so that in the event of the destruction of its fragments do not cause damage to other units or other drive transmission systems of the helicopter. It is allowed to place a "weak link" in the drive from the transmission to the unit. Static and dynamic (fatigue) stress and strain the whole range of basic components and transmission units, as well as vibration components and attachment points of transmission units do not have to (when the data design features, the materials used and accepted technology) exceeds a certain value. These values are set based on the operating experience and the results of bench tests and testing of production and repair of transmission units in order to confirm the adequacy of the static and fatigue strength units (nodes) of the transmission and wear resistance of their components.
The construction of the transmission must be within a certain time of operation (assigned resource) withstand repeated loads in operation without critical failure of the transmission.
Resources components (eg roller bearings) established on the basis of tests on the system of units (units) transmission.
Structural and kinematic scheme TRANSMISSION HELICOPTER
Transmission of single-rotor helicopter Mi-8 with PB (4.2.1) includes: a main gearbox (GR) 2; brake HB 3; tail shaft 4; an intermediate gear (PR) 5; intermediate shaft 6; reducer RV 7; Fan drive shaft oil-air radiator 1. Power to the drive NV and PB units, catering to the helicopter systems (pumps, hydraulic and lubrication systems, electrical generator, compressor and tachometer sensor), coming from the right and left engines through GR.
GR installed by helicopter to the struts podreduktornoy frame at the top of the helicopter. PR is designed to change the direction of power transfer. RV reducer changes the direction of power transmission from PR and lowers the frequency of rotation of the steering shaft.
In light helicopter OH 6A firm Hughes applied KKS transmission. A characteristic feature of this helicopter is the placement of the engine oil radiator and air 2, the use of supercritical shaft with damper 5 4 and no PR. The output of the gas jet in the rear part of the fuselage 7 reduces its aerodynamic drag, and oil cooler fan drive directly from the main shaft and the exclusion OL significantly reduce the overall weight of the transmission.
Feature transmission helicopter CH-47 «Chinook" is determined by its longitudinal scheme. It consists of a front and rear gear screw 1 and 7, unifying gear 3, 5 two angular gear motors 6, synchronizing shafts 4, connects the engine to the gearbox unification.
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