RU171693U1 - CONTROL SYSTEM FOR BASIC AIRCRAFT FUNCTIONS - Google Patents

Abstract

The utility model relates to the field of aviation, namely to control systems for the basic flight functions of aircraft using electromechanical drives (EMF). The system contains: steering surfaces (RP), used to control the course functions, and located to the left and right of the RP fuselage, used to control the pitch and roll functions, as well as the aerodynamic braking surface (AT); two tracking EMFs connected to each RP and each surface AT, the output links of each of which rotate or linearly move; the electric motor (ED) of each servo EMF RP is a brushless, direct current, permanent magnet with permanent magnets with a shaft rotation speed of 6000 ... 60000 min, and the EMF has a wave reducer connected to the rotor shaft with rotation bodies with a gear ratio of 500 ... 4000. The system also includes control units (BUs) of the tracking EMF RP, which control flight functions of the course, pitch and roll and AT surfaces and are connected to the EMFs with interface buses of the BU ED tracking EMFs of the RP and AT surfaces; the central control unit of each RP for each of the course, pitch and roll functions and the AT surfaces, connected by interface buses to the control units monitoring EMFs, and at least one on-board computer; sensors of the angular position of each output shaft of the tracking EMF, connected by interface buses to the control unit of the tracking EMF; sensors of the angular position and speed of each RP of each of the course, pitch and roll functions and of each AT surface connected by interface buses to the control units of the RP EMF. The system allows you to reduce the size and weight of the electromechanical drives of the steering surfaces. 4 s.p. f-ly, 9 ill.

Description

The utility model relates to the field of aviation, namely to control systems for the basic flight functions of aircraft using electromechanical drives.

A known electric drive system for steering surfaces of flight control (US patent No. 7007897 from 01/27/2004), consisting of: connected to the steering surfaces, at least two electric drives: an electromechanical drive and an electro-pneumatic drive designed to create a force additionally acting on the steering surfaces when the specified value of the force created in the process of controlling electromechanical drives and acting on the steering surface is exceeded. The steering surface to which electromechanical and electro-pneumatic drives are connected can be any steering surface used to control the flight of an airplane: aileron, rudder, elevators, spoilers - brake flaps and spoilers; as well as aerodynamic surfaces used during take-off and landing - slats and flaps. The steering surface control system has a controller for controlling the electromechanical drives of the steering surfaces, receiving control signals and transmitting them to control the electromechanical drive. The steering surface control system has a position sensor at each of the steering surfaces, connected to the controller and transmitting signals about the position of the steering surface; a position sensor acting on the steering surface of the element of the electromechanical drive, transmitting signals to the controller; an on-board computer generating flight control signals or a remote aircraft flight control system.

The disadvantage of this system is that it contains a pneumatic system with air motors, electrically controlled valves and one or many compressors, which complicates and complicates the flight control system of the aircraft and, accordingly, increases the mass of the aircraft.

A known electric drive system for steering surfaces of flight control (US patent No. 8033509 from 02.27.2007), consisting of at least two electric drives connected to the steering surfaces: electromechanical and electro-hydraulic, of which the main drive that creates a force acting on the steering surface in the process control, is an electro-hydraulic drive, and the force created by an electromechanical drive can be additional and acting after determining the level of force acting on the steering surface from electro-hydraulic drive. The mode of joint action of forces from an electromechanical drive and an electro-hydraulic drive can also be used.

The disadvantage of this system is that it uses heterogeneous drives, of which the subsystem with electro-hydraulic drives is more massive than the subsystem with electromechanical drives.

A known electric drive system for steering surfaces of flight control (US patent No. 7549605 from 07.29.2005), in which the forces acting on each steering surface create at least two electromechanical drives of rotational motion (US patent No. 6739550 from 08.10.2002).

The electromechanical drive of the steering surfaces uses an electromechanical drive with a translationally moving element of the ball screw, which converts the rotational movement of the rotor of the electric motor into translational (US patent No. 7764035 from 02.14.2008).

A known control system for the moving surfaces of an aircraft, containing at least two electromechanical drives (patent RU No. 2531998 from 10/18/2011), which can be either electromechanical drives of rotational motion, or electromechanical drives with a screw or other converter of rotational motion of the motor shaft into the translational movement of the element that creates the force acting on the steering surfaces of the aircraft. The control system of electromechanical drives includes a control unit for each electromechanical drive and a central control unit for the system of electromechanical drives of steering surfaces, position sensors of elements of electromechanical drives acting on steering surfaces, and position sensors of steering surfaces connected to both control units of electromechanical drives and the central unit management.

Such systems with electromechanical drives can be massive and have large dimensions if they use electric motors with a reduced rotor speed, for example, less than 6000 min ^-1 .

Electromechanical drives of the aerodynamic surfaces of an airplane are known (patents RU No. 108238 dated 06/09/2010, RU No. 108239 dated June 9, 2010, RU No. 2442721 dated June 9, 2010, RU No. 2515014 dated July 25, 2012, RU No. 2522635 dated July 25, 2012, RU No. 2522638 dated July 25, 2012; RU No. 2522646 dated July 25, 2012), including an electric motor with a nominal rotor speed selected from a range of 3000 min ^-1 to 25000 min ^-1 with a rotor angular position sensor and a wave reducer attached to it with bodies rotation with the number of steps from 1 to 3 with a sensor for the angular position of the output shaft, characterized by a gear ratio m, selected from the range of 500 to 2500. The electromechanical linear actuator (patent RU №2522646) comprises a ball screw drive rotational output shaft motion into linear motion output member connected with a controllable steering surface.

The technical problem solved by the utility model is to reduce the size and weight of the electromechanical drives of the control system of the basic flight functions of the aircraft.

The technical problem is solved in the control system of the basic flight functions of the aircraft, comprising: steering surfaces, which serve to control the flight functions of the course, and steering surfaces located to the left and right of the fuselage, which serve to control the flight functions of pitch and roll, as well as aerodynamic braking surfaces (brake flaps) and interceptors); at least two follow-up electromechanical actuators connected to each steering surface, the output links of each of which rotate or linearly move; control units for tracking electromechanical drives of steering surfaces that control the flight functions of the course, pitch and roll and aerodynamic braking surfaces; control units for electric motors of follow-up electromechanical drives connected by interface buses to control units for follow-up electromechanical drives of steering surfaces and aerodynamic braking surfaces; at least one central control unit (computer, controller) by each steering surface of each of the course, pitch and roll functions and aerodynamic braking surfaces connected by interface buses to control units of tracking electromechanical drives with at least one on-board computer; sensors of the angular position of each output shaft of the follow-up electromechanical drive, connected by interface buses to control units of follow-up electromechanical drives; sensors of the angular position and speed of each steering surface of each of the heading, pitch and roll functions and each aerodynamic braking surface, connected by an interface bus to the control units for tracking electromechanical steering surfaces, while each electric motor of tracking electromechanical steering surfaces of each of the heading, pitch and roll and aerodynamic drag surfaces is a DC brushless DC motor with constant with magnets having a rotor shaft rotational speed selected from the interval 6000 ... 60000 min ^-1 , and a wave reducer connected to the rotor shaft with rotary bodies with a gear ratio selected from the range 500 ... 4000.

To reduce the moment of inertia of the rotating parts of electromechanical drives and to reduce the response time to control actions, a brushless DC direct current electric motor with permanent magnets has a rotation frequency selected from the interval 26000 ... 60000 min ^-1 , and a wave reducer connected to the rotor shaft with rotation bodies with a gear ratio selected from the range of 1000 ... 4000.

To increase the unification of electromechanical drives and simplify the control system, several servo-driven electromechanical steering surfaces that control the flight functions of the course, pitch and roll are identical.

To drive extended steering surfaces, power servo-driven electromechanical steering surface drives that control at least one of the flight functions of the course, pitch and roll are servo-driven electromechanical rotational motion drives.

To drive aerodynamic braking surfaces, servo-mounted electromechanical steering surfaces that control at least one of the flight functions of the course, pitch and roll are power-tracking electromechanical linear actuators.

The technical effect - reducing the size and weight of the electromechanical drives of the control system of the basic flight functions of the aircraft - is achieved due to the combination of distinctive features of the utility model: each electric motor of the tracking electromechanical drives of the steering surfaces of each of the course, pitch and roll functions and aerodynamic braking surfaces is a brushless DC DC motor with permanent magnets having a rotor shaft rotational speed selected from the interval la 6000 ... 60,000 min ^-1 , and a wave reducer connected to the rotor shaft with rotation bodies with a gear ratio selected from the range 500 ... 4000.

To further reduce the size and weight of electromechanical drives, the rotor shaft of a brushless DC direct current motor with permanent magnets has a rotation frequency selected from the range of 26,000 ... 60,000 min ^-1 , and a wave reducer connected to the rotor shaft with rotation bodies with a gear ratio selected from the range of 1000 ... 4000.

This set of distinctive features was not found in the course of patent information research, therefore, the utility model meets the criterion of "novelty."

In FIG. 1 shows a general view of an aircraft with steering surfaces and aerodynamic braking surfaces.

In FIG. 2 is a front view of an aircraft with steering surfaces.

In FIG. 3 - two electromechanical rotational drive for steering surfaces and surfaces of aerodynamic braking.

In FIG. 4 is a view A in FIG. 3.

In FIG. 5 - electromechanical drive of rotational movement with a crank mechanism and a lever for turning the surface of aerodynamic braking.

In FIG. 6 - electromechanical drive for steering surfaces and aerodynamic braking surfaces with a brushless direct current DC electric motor with excitation from permanent magnets and with a three-stage wave gear with bodies of revolution.

In FIG. 7 - linear electromechanical drive steering surface or surface aerodynamic braking.

In FIG. 8 is a design of a linear electromechanical drive with a two-stage wave gear with bodies of revolution and with a ball screw mechanism for converting rotational motion into translational for the steering surface.

In FIG. 9 - control system located to the right of the longitudinal axis of the aircraft electromechanical actuators of steering surfaces and aerodynamic braking surfaces.

The control system of the basic flight functions of the aircraft (Fig. 1-9) contains: the steering surface 1 (rudder 1 direction) (Fig. 1, 2), used to control the flight function of the course, and located to the left and to the right of the longitudinal axis 2 passing through the center of gravity of the aircraft, steering surfaces 3 (rudders 3 heights), used to control the flight function of pitch, and steering surfaces 4 (ailerons 4) located at the ends of the wing 5, used to control the flight function of the roll, as well as the aerodynamic braking surface (brake flaps 6 and inter receptors 7).

Each steering surface 1, 3, 4 has at least two follow-up electromechanical actuators 8 a (Fig. 3-6) of rotational motion or two follow-up electromechanical actuators 8b (Fig. 7, 8) of linear displacement, the rated power of which depends on the area of the steering surface they bring and the maximum speed of its rotation ["Determination of the limit dynamic characteristics of the steering drive based on the limiting flight regimes of the aircraft. TB Bliznova, Yu.G. Obolensky, VA Polkovnikov, Electronic journal" Transactions of Moscow Aviation Institute ", issue No. 61. www.mai.ru/scienc e / trudy / published.php? ID = 35650]:

where N _n - rated power; M is the hinge moment of rotation of the steering surface; ω _max - the maximum angular velocity of rotation of the steering surface; S is the steering surface area; υ is the maximum flight speed.

The aerodynamic braking surfaces - brake flaps 6 (Fig. 1, 7) and interceptors 7 (Fig. 1, 5), mounted on a fixed element 9 (Fig. 3-8) of the plumage power set, are driven by at least two electromechanical actuators 8 and rotational movement via connected to the output shafts 10 and arms 11 and connecting rods 12 (FIG. 5) and fixed to the steering surfaces 1, 3, 4 and the surfaces of the aerodynamic braking 6 and 7, the levers 13, or electromechanical actuators 8b linear displacement via attached to output links 10b, levers 13 (Fig. 7), but to increase reliability by redundancy, they can also be driven by two electromechanical actuators 8 a or 8b through couplings 14 (Fig. 3, 6).

To reduce the size and weight of the electromechanical drives 8 a (Fig. 3-6) or 8b (Fig. 7, 8), as well as to reduce the mass of the stationary elements 9 (Fig. 3-8) of the plumage power set, to which the steering surfaces are attached , each electric motor 15 (Fig. 3-8) of a follow-up electromechanical drive 8 a (8b) of each steering surface 1, 3, 4 is a brushless constant current DC motor with permanent magnets with a rotational speed of the rotor 16 of the electric motor 15, selected from the interval 6000 ... 60000 min ^-1 and electromechanical servo 8 and sky drive (8b) is connected to the rotor shaft 16 of the wave multistage gear 17 with the rotation bodies 18 with the transmission ratio selected from the range of 500 ... 4000.

When the rotation speed is less than 6000 min ^-1 , the electromechanical drive 8 a (8b) has a low level of specific power of the electric motor 15, less than 0.45 kW / kg; the increase in specific power with an increase in the rotational speed of the rotor 16 of the electric motor 15 decreases, and at a speed of more than 60,000 min ^{-1, the} increase in specific power becomes small, so an increase in the frequency of more than 60,000 min ^-1 gives an insignificant increase in specific power and becomes impractical.

Wave gears 17 (Fig. 6, 8) with bodies of revolution 18 also have minimal dimensions, especially in comparison with the most used gear multistage gears, and also, in comparison with other types of gears, allow a high gear ratio, which reduces the angular velocity of rotation the steering surface of 1, 3, 4 is 500 ... 4000 times in comparison with the angular speed of rotation of the rotor 16 of the electric motor 15. This range of gear ratios of the gearbox is necessary due to the small angular speed of rotation of each from steering surfaces and aerodynamic braking surfaces.

When used in electromechanical drives 8 a and 8b of electric motors 15 with a rotor speed of 16 more than 26,000 min ^-1 and a two-stage wave gear 17 (Fig. 8) or a three-stage wave gear 17 (Fig. 6) with bodies of revolution 18 with a gear ratio of 1000 ... 4000 for two-stage and three-stage gear 17, respectively, it is possible to drive the control surfaces to increase reliability by increasing the number of electromechanical actuators 8 a and 8b with a smaller increase in their total weight as compared with electromechanical etc. water having a smaller motor rotor speed.

In the frame of the power set of the plumage, for example, wing 5, it is possible to place several electromechanical drives 8 a and 8b to drive each steering surface, and, accordingly, increase the reliability of controlling the main functions of the course, pitch, roll and aerodynamic braking without resorting, along with electromechanical drives 8a and 8b, to electrohydraulic actuators (not shown) and electropneumatic actuators (not shown), as is proposed in the known inventions Airbus firms, Honeywell, Boeing and used in airplanes.

Tracking electromechanical drives 8 a and 8b, which control steering surfaces 1, 3, 4 and aerodynamic braking surfaces 6, 7, having equal areas, can be identical both in rated power and in design, which allows to increase the level of unification of electromechanical drives 8 a and 8b and reduce their cost.

Depending on the predetermined rotation angle of the steering surface 10 and the output shaft of the electromechanical actuator 8 performs a rotary motion (Figs. 3-6), and the output member 10b electromechanical actuator 8b performs linear movement (Figs. 7, 8) obtained by converting the rotational motion the shaft of the rotor 16 of the electric motor 15 into the translational through the crank mechanism 19 (Fig. 5) or through a ball screw transmission 20 (Fig. 8).

Each surface 6 (6.1, 6.2, 6.3) (Fig. 1) of aerodynamic drag can also have at least one servo-driven electromechanical drive 8 a (Fig. 3-6), the output shaft 10 a of which rotates, or electromechanical drive 8b (Fig. 7, 8), the output link 10b of which performs linear movement.

The control of the electromechanical actuators 8 a and 8b of the steering surfaces for the course, pitch or roll functions is carried out through a control system (Fig. 9), having:

- control units 21 tracking electromechanical drives 8 a and 8b of the steering surfaces 1, 3 or 4, performing control of the flight functions of the course (1), pitch (3) and roll (4) and aerodynamic braking surfaces 6, 7;

- control units 22 of electric motors 15 of the tracking electromechanical drives 8 a and 8b, connected by interface buses 23 to control units of 21 tracking electromechanical drives 8 a and 8b of steering surfaces 1, 3, 4 and surfaces 6, 7 of aerodynamic braking;

at least one central control unit 24 of the steering surfaces 1, 3 or 4 of each of the functions of course, pitch and roll, respectively, and aerodynamic braking surfaces 6, 7, connected by an interface bus 23 to the control units 21 and 22 of the tracking electromechanical drives 8 a and 8b and an interface bus 25 with an on-board computer 26;

- sensors 27 of the angular position of the output shaft 10 a and the output link 10 b, respectively, of each servo-driven electromechanical actuator 8 a or 8b, connected by interface buses 28 to control units 21, 22 of the servo-controlled electromechanical actuators 8 a and 8b;

- position sensors 29 of each steering surface 1, 3, 4 and aerodynamic braking surfaces 6, 7, connected by interface tires 30 to control units 21, 22, tracking electromechanical actuators 8 a and 8b of the steering surfaces.

The operation of the electromechanical drive of the system of steering surfaces 1, 3, 4 and surfaces 6 and 7 of aerodynamic braking with tracking electromechanical drives 8 a or 8b of the described structures (Fig. 1-8) to control the basic functions of the course, pitch and roll during flight includes the following actions :

- start-up of electromechanical drives 8 a and 8b, providing the start of rotation of one or more steering surfaces 1, 3, 4 and, if necessary, aerodynamic braking surfaces 6, 7 by signals supplied by the central control unit 24 (Fig. 9) to control units 21, 22 servo drives 8 a and 8b in accordance with the laws of control and algorithms laid down in the control program;

- acceleration of the steering surfaces with the necessary acceleration to a steady speed according to the program specified by the central control unit 24 and the signals issued by the sensors 27, 29 that are converted in the control units 21, 22 of the tracking electric drives 8 a , 8b; change in the speed of rotation of the steering surfaces while monitoring the angular position of the output shaft 10 a and the output link 10 b of the electromechanical drives 8 a and 8 b, respectively, and the angular position of the steering surfaces according to the signals received from the central control unit 24 and converted in the control units 21, 22 of the follow-up electric drives 8 a 8b;

- a change in the direction of rotation of the rotors 16 of the electric motors 15, the output shaft 10 a and the output link 10b, the steering surfaces 1, 3, 4 and the aerodynamic braking surfaces 6, 7 according to the signals received from the central control unit 24 and converted in the monitoring control units 21, 22 electromechanical drives 8 a , 8b; acceleration of an electromechanical drive 8 a or 8b with a given acceleration to a steady speed of one or more steering surfaces 1, 3, 4 when performing functions of course, pitch and roll, and aerodynamic braking surfaces 6, 7, respectively, by adjusting the frequency of synchronous rotation of the shaft 10 a and link 10b of the electric drives, respectively 8 a and 8b.

In case of failure or failure of at least one of the electromechanical actuators 8 a or 8b, it is disengaged, for example, by a squib 31 (Fig. 3, 4, 6) [patent RU No. 2522638], by command from the central control unit 24 to the control unit 21 or 22, after which all the servo-driven electromechanical drives 8 a , 8b can continue to work when the total power of the electromechanical drives decreases.

Claims (5)

1. The control system of the basic flight functions of the aircraft, comprising: steering surfaces used to control the flight functions of the course, and steering surfaces located to the left and right of the fuselage, used to control the flight functions of pitch and roll, as well as aerodynamic braking surfaces; at least two servo-driven electromechanical drives connected to each steering surface and each aerodynamic drag surface; control units for tracking electromechanical drives of steering surfaces and aerodynamic braking surfaces; electric motor control units for tracking electromechanical drives; a central control unit for each steering surface and each aerodynamic braking surface connected to the on-board computer; sensors of the angular position and speed of each steering surface and each surface of aerodynamic braking, characterized in that the electric motor of each servo-driven electromechanical drive of the steering surfaces of each of the course functions, pitch and roll, and surfaces of aerodynamic braking, is a brushless constant current DC motor with permanent magnets having rotor rotational frequency selected from the range of 6000 ... 60,000 min ^-1 and the electromechanical drive has Cpd enny with the rotor shaft of the wave gear with rotation bodies with the transmission ratio selected from the range of 500 ... 4000. 2. The control system according to claim 1, characterized in that the rotor shaft of a brushless direct current DC motor with permanent magnets has a rotation frequency selected from the interval 26000 ... 60000 min ^-1 , and the electromechanical drive has a wave gearbox connected to the rotor shaft of the electric motor with bodies rotation with a gear ratio selected from the range of 1000 ... 4000. 3. The control system according to claim 1, characterized in that several servo-controlled electromechanical steering surfaces that control the flight functions of the course, pitch and roll are identical. 4. The control system for PP. 1-3, characterized in that the power follow-up electromechanical actuators of the steering surfaces used to control at least one of the flight functions of the course, pitch and roll, are follow-up electromechanical drives of rotational motion. 5. The control system for PP. 1-3, characterized in that the tracking electromechanical actuators of the steering surfaces, used to control at least one of the flight functions of the course, pitch and roll, are power tracking electromechanical linear actuators.

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