RU2031814C1 - Device for manual control of engine forward and reverse thrust mechanisms - Google Patents

Abstract

FIELD: aeronautical engineering. SUBSTANCE: device has forward thrust control lever 1, reverse thrust control lever 2 and bell crank 4 connected with control roller 6 by means of rod 5; roller 6 is kinematically linked with lever 9 of engine 10. Quadrant 26 fixed on control roller 6 has end surface with hollow 27 which is engageable with roller 28 at the IDLE REVERSE mode. Control of forward thrust and reverse at landing is effected as follows. At landing, the pilot places forward thrust control lever 1 in the IDLING position. At touchdown, the pilot places reverse thrust control lever 2 in the MAXIMUM REVERSE position. After braking the aircraft to a speed which slightly exceeds that at which engines start sucking foreign matter from the runway, reverse lever 2 is shifted to IDLE REVERSE position. Device ensures reliable setting of reverse lever 2 in this mode. EFFECT: improved service characteristics through improved operating conditions of engine. 4 dwg

Description

 The invention relates to aviation, in particular to mechanisms for manual control of the operating modes of aircraft engines.

 A device is known for manual control of direct and reverse engine thrust mechanisms, comprising a direct thrust control lever, a reverse lever pivotally mounted on a direct thrust control lever, on the axis of which a rocker is pivotally fixed, connected by a thrust to the reverse lever and an additional thrust, the other end of which is pivotally connected to a control roller that is mounted on the axis of the bracket and kinematically connected with the engine (Technical Maintenance Manual TU-154 M, 1983, section 071, 076.00.00, s.3-4, fig. 1, 076.11.00, s.5- 6, fig. 2).

 The disadvantage of this device is that it does not allow the exact inclusion of the "Small reverse" mode. The installation of a small reverse on the device distracts the attention of the pilot and takes time. Braking performed in the "Maximum reverse" mode, with a decrease in speed, leads to the throwing of foreign objects from the strip into the engine at low braking speeds. Turning on the reverse to the casting speed leads to an increase in the time and range of the aircraft, wear of the wheels and brakes.

 The purpose of the invention is to increase the operational properties of the device by providing the possibility of improving the operating conditions of the engine.

 Figure 1 shows a device for manual control of direct and reverse engine thrust mechanisms,; figure 2 is the same in isometry; figure 3 - node I in figure 2; figure 4 - node II in figure 2.

 The manual control device for direct and reverse engine thrust mechanisms comprises a direct thrust control lever 1, a reverse lever 2 pivotally mounted on a direct thrust control lever 1, an axis 3, on which a rocker 4 is pivotally mounted, pivotally connected to a rod 5, the other end of which is pivotally connected with a control roller 6 mounted on the axis 7, and an arm 8 kinematically connected to the control lever 9 of the engine 10. The kinematic connection includes cables 11, rollers 12 and 13, rod 14, rocker 15. The direct link control lever 1 has a stop 16 maximum reverse and two grooves 17, in which the pin 18 is fixedly mounted on the earring 19, pivotally connected to the rod 20. The bracket 21 has an emphasis 22 of small gas, a groove 23 and a limiter 24 of the reverse.

 A sector 26 is fixedly mounted on the control roller 6 with bolts 25, the end surface of which is profiled with a hole 27 and is in contact with the roller 28, pivotally mounted on the end of the additional rocking chair 29, movably mounted on the additional axis 30 of the bracket 8.

 The end of the additional rocker 29 with the roller 28 is pivotally connected to the movable rod 31 extending inside the hollow adjustable stop 32. A spring 33 is installed between the protrusion of the rod 31 and the adjustable stop 32. The opposite end of the additional rocker 29 is equipped with an additional adjustable stop 34 in contact with the crimping member of the working body 35 (circuit breaker).

 Sector 26 has through elongated holes 36 through which bolts 25 pass. The engine 10 is provided with a limb 37.

 The manual device control mechanisms of direct and reverse engine thrust is regulated and operates as follows.

 After the engine management system is adjusted, the device is adjusted. For this, the direct thrust control lever 1 is mounted on the stop 22 of small gas. In this case, the pin 18 stops opposite the groove 23 of the bracket 21. The reverse lever 2 is set along the limb 37 on the engine 10 to the "Small reverse" position by a certain angle. In this case, the pin 18 enters the groove 23 of the bracket 21 and blocks the control lever 1 from moving when operating with the reverse lever 2. After that, the mounting bolts 25 of the sector 26 are loosened and it moves until the roller 28 completely engages in the hole 27. In this position, the sector 26 is locked by the bolts 25 on the roller 6.

 At the same time, the emphasis 34 is adjusted until the actuation of the working body 35, i.e. until the moment an electrical signal is issued about the inclusion of the "Small Reverse" in adjacent systems. The rotation of the adjustable stop 32 regulates the preload force of the spring 38, so that when the roller 28 leaves the hole 27, an additional force appears on the reverse lever 2.

 The magnitude of this effort can vary from 1 to 2 kgf depending on the number of levers, i.e. engines, efforts in the wiring itself, efforts to move the executive body and other conditions. In addition, the additional effort should not noticeably interfere with the translation of the reverse lever from the "Reverse off" position to the "Maximum reverse" position and vice versa, bypassing the "Small reverse".

 The proposed device gives the following positive effect. When the lever 2 of the reverse is raised, it itself is set to the "Small reverse" position and fixed in it. This is explained by the fact that the roller 28, preloaded by the spring, having slightly crossed the edge of the hole 27, under the action of the spring 33 helps to deploy the sector 26 with the roller 6 in order to occupy the lowest position in the hole.

 Direct thrust and reverse control during landing is as follows.

 When the aircraft lands, the pilot sets the direct thrust control lever 1 to the "Small gas" position. When the plane touches the runway, the pilot sets the reverse lever 2 to the "Maximum reverse" position and when the aircraft reaches the braking speed a little more than the speed at which the engines begin to suck foreign objects from the runway, puts the reverse lever 2 into the "Small reverse" position. Next, the pilot withstands the "Small Reverse" to taxi speed.

Claims (1)

 MANUAL CONTROL DEVICE FOR DIRECT AND REVERSE ENGINE THRUST, comprising a direct linkage control lever with a reverse lever pivotally mounted thereon, a rocking chair pivotally mounted on an axis of the direct linkage control lever and connected by a linkage to the reverse linkage lever and an additional linkage connected to the linkage, on the axis of the bracket and kinematically connected to the engine, characterized in that, in order to improve the operational properties of the device by providing the possibility of improving conditions engine operation, it is equipped with an additional spring-loaded rocking chair with a roller at one end and an adjustable additional stop at the other end, the control roller is equipped with a sector with a profiled end surface, and the bracket is equipped with an additional axis, while the additional rocking is pivotally mounted on the additional axis of the bracket, and the additional rocking roller contacts the profiled end surface of the sector, and the sector is made adjustable relative to the side surface of the control conductive roller.

Images