RU2303805C1 - Control unit of flight vehicle pitch channel - Google Patents

Abstract

FIELD: instrument engineering, applicable in on-board systems of automatic control of flight vehicles.

SUBSTANCE: the control unit has a control signal selector, pitch-angle pick-off, pitch-rate pick-up, integrator, summing amplifier, reference signal selector, first and second multiplier units, functional signal limiter, flying-velocity transducer, division unit and a ram air-pressure sensor.

EFFECT: expanded functional capabilities.

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Description

The invention relates to airborne systems for the automatic control of aircraft, which realize turns with significant angles of attack during flight.

Aircraft control systems are known that include a control signal adjuster, a pitch angle sensor, a pitch angle sensor and a summing amplifier in the pitch channel, which generate control actions on the steering gears of the aircraft according to the driving actions and signals of the state sensors [1]. These essential features are in the proposed technical solution. In the analog device, modes are possible when the angle of attack is beyond the permissible limits, which reduces the quality of control of the aircraft and there is a likelihood of flight modes exceeding strength limits.

Known solutions include the introduction of additional filters in the control channel to limit the angle of attack [2]. However, these filters solve particular problems, as described in [2], for example, in conditions of wind gusts; at the same time, filters in a direct circuit weaken the passage of control signals.

Closest to the proposed invention, adopted as a prototype, is an aircraft pitch channel control device comprising a control signal adjuster, a pitch angle sensor, a pitch angle sensor and a series integrator and a summing amplifier, the outputs of the pitch angle sensor and the pitch velocity sensor the pitch is connected respectively with the second and third inputs of the summing amplifier, the output of which is the output of the device [3, p.194]. All these essential features are in the proposed technical solution.

In the prototype device [3], as well as in the device [2], modes are possible when the angle of attack is outside the acceptable range, which reduces the quality of control of the aircraft and there is a likelihood that flight modes go beyond strength limits.

The technical problem solved in the proposed device is to expand the maneuverability of the device and limit the angle of attack.

The specified technical result is achieved by the fact that in a known device for controlling the pitch channel of an aircraft, comprising a control signal adjuster, a pitch angle sensor, a pitch angle sensor and a series-connected integrator and a summing amplifier, the pitch pitch sensor and pitch angle sensor being connected respectively, with the second and third inputs of the summing amplifier, the output of which is the output of the device, additionally connected in series reference signal sensor, first and second multiplication blocks and a functional signal limiter, the output of which is connected to the integrator input, a flight speed sensor connected through the division to the second input of the second multiplication block, a pressure head sensor, the output of which is connected to the second input of the division block, this output of the control signal setter is connected to the second input of the functional signal limiter, and a current mass value sensor, the output of which is connected to the second input of the first multiplication unit.

Distinctive features of the proposed technical solution are that a series of connected reference signal adjuster, first and second multiplication units and a functional signal limiter, the output of which is connected to the integrator input, an airspeed sensor connected through the division unit to the second, are introduced into the aircraft’s pitch channel control device the input of the second multiplication unit, a pressure head sensor, the output of which is connected to the second input of the division unit, while the output of the signal generator systematic way connected to the second input of the signal limiter function, and the sensor current weight value, the output of which is connected to a second input of the first multiplier unit.

The proposed control device for the pitch channel of the aircraft allows you to expand the control capabilities of the aircraft and to limit the angle of attack and thereby improve the quality of control of the aircraft and the probability of failure of flight modes for strength limitations.

The drawing shows a structural diagram of a device for controlling the pitch channel of an aircraft.

The device comprises a control signal controller 1, a pitch angle sensor 2, a pitch angle sensor 3 and series-connected integrator 4 and a summing amplifier 5, series-connected reference signal generator 6, a first multiplication unit 7, a second multiplication unit 8 and a functional signal limiter 9, the output of which is connected to the input of the integrator 4, the flight speed sensor 10 connected through the division unit 11 to the second input of the second multiplication unit 8, the pressure sensor 12, the output of which is connected to the second input the division unit 11, and the outputs of the pitch angle sensor 2 and the pitch angle sensor 3 are connected respectively to the second and third inputs of the summing amplifier 5, the output of which is the output of the device, the output of the control signal setter 1 is connected to the input of the signal limiter 9, and the current sensor mass values 13, the output of which is connected to the second input of the first multiplication block.

The control device of the pitch channel of the aircraft operates as follows.

The control output signal σb _is generated by the signals of the 4-ϑ _y integrator, 2-ϑ pitch angle sensor and angular velocity sensor

3-ω _z in the form:

where σ _B is the control signal generated by the summing amplifier 5;

- передаточные числа, выставляемые в суммирующем усилителе 5;K _ϑ , K

- gear ratios set in the summing amplifier 5;

ϑ - pitch angle signal from sensor 2;

поступающий от датчика 3;ω _z is the pitch angular velocity signal,

coming from sensor 3;

функционального ограничителя сигнала 9:ϑ _у - control signal generated by the integrator 4 by the signal

signal limiter 9:

Moreover, in the basic mode - under the conditions of acceptable values of the angle of attack:

- сигнал с выхода задатчика сигнала управления 1.Where

- the signal from the output of the control signal setter 1.

. А именно, для решения поставленной технической задачи сигнал

формируется от задатчика сигнала управления 1 по сигналу

при функциональном ограничении его величиной

.в блоке 9, т.е.Under the conditions of the device’s functioning as part of the aircraft’s control system, the value of the angle of attack of the aircraft α (direct measurement of which is a known difficulty) is indirectly analyzed and, when the value of α approaches the permissible α, an _additional restriction is introduced in the control law (1) regarding the formation

. Namely, to solve the technical problem, the signal

formed from the setpoint control signal 1 by a signal

with functional limitation by its value

. in block 9, i.e.

формируется блоками 6, 7, 8, 10, 11 и 12 для блока 9 следующим образом.Value

is formed by blocks 6, 7, 8, 10, 11 and 12 for block 9 as follows.

The main relation in transient processes for the development of control actions is, as shown, for example, in [2], the relation for the angle of attack α:

- коэффициент подъемной силы летательного аппарата.Where:

is the lift coefficient of the aircraft.

From equation (5):

Where

Thus, up to the dynamic component

, то, зная α_доп., можно оценить

:Since the pitch channel of the aircraft fulfills a predetermined value

, then, knowing α _add. can be estimated

:

As

(see, for example, [3, p.30]),

- коэффициент подъемной силы;Where:

- lift coefficient;

ρ is the air density;

S is the wing area;

m is the mass of the aircraft,

V is the flight speed of the aircraft, then from (8), taking into account (9), the relation can be obtained:

Where

The pressure sensor 11 generates a speed signal

From (11) it follows:

and then (10) will rewrite:

(коэффициент в числителе K_α α_доп. выставлен в блоке 6 как заданная величина и поступает на первый вход первого блока умножения 7).According to relation (13), a signal is formed

(the coefficient in the numerator K _α α _{add. is} set in block 6 as a given value and is supplied to the first input of the first multiplication block 7).

в соответствии с (10).The signals of the flight speed V and the pressure head q from the corresponding sensors 10 and 12 are divided in the division block 11. The division signal is fed to the second input of the second multiplication block 8, at the output of which we have a signal

in accordance with (10).

Thus, the proposed device for controlling the pitch channel of the aircraft allows you to expand the control capabilities of the aircraft and to limit the angle of attack.

All blocks of the control device are standard and can be implemented on the elements of automation and computer technology, for example, according to [4, 5].

Information sources

1. RF patent No. 1751716, cl. G05B 13/02, 07/30/92.

2. “Aerodynamics, stability and controllability of supersonic aircraft” Ed. G.S. Byushgens. M.: Science, Fizmatlit, 1998, pp. 616-618.

3. I. A. Mikhalev and others. "Automatic control systems for an aircraft" M.: Mechanical Engineering, 1987, p.30, 194.

4. A.U. Yalyshev, O. I. Razorenov. "Multifunctional analog control devices for automation." M .: Mechanical Engineering, 1981, p. 103.

5. V. B. Smolov. "Functional information converters" L .: Energoizdat, Leningrad branch, 1981, p.55.

Claims (1)

An aircraft pitch channel control device comprising a control signal adjuster, a pitch angle sensor, a pitch angle sensor and an integrator and a summing amplifier connected in series, the pitch angle sensor and pitch angle sensor outputs being connected respectively to the second and third inputs of the summing amplifier, the output of which is the output of the device, characterized in that it contains serially connected reference signal setter, first and second multiplication units, and a functional limiter of the signal, the output of which is connected to the input of the integrator, a flight speed sensor connected through the division unit to the second input of the second multiplication unit, a pressure head sensor, the output of which is connected to the second input of the division unit, while the output of the control signal generator is connected to the second input of the functional signal limiter, and a sensor of the current mass value, the output of which is connected to the second input of the first multiplication block.