DE1906152A1 - Method and device for the control of the angle of attack and the sideslip angle of a jet aircraft - Google Patents

Description

DEVELOPMENT RING SÜD GMBH

MUNICH, February 1959

EM 2 270
En / Hb

Method and device for the angle of attack and side slip angle control

of a jet aircraft

The invention relates to a method and a device for angle of attack and steering angle of a jet aircraft, in particular a high-performance fighter, with electrical transmission the control command from the pilot to the control organs with the interposition of a control system.

In the currently known method of the type mentioned above, there is Usually there is a clear connection between the stick or pedal deflection and the corresponding acceleration of the aircraft's center of gravity. This is achieved by direct measurement of the acceleration and a comparison with the electrically tapped stick or pedal signal.

Ser-like methods have the disadvantage that, in addition, for the Slow flight, especially in modern combat aircraft, angle of attack warning devices must be provided. Such devices consist of an angle of attack sensor, a vibrator, a stick release device (pusher) and possibly several angle of attack tolerance lamps different color.

In addition to the considerable weight that such a system entails brings is seen above all as a major disadvantage that everyone The pilot will try to stay as far away as possible from the angle of attack at which the pusher responds, otherwise the machine will is unable to maneuver for a certain period of time. This increases the landing and take-off street beyond what is theoretically achievable.

Another disadvantage of the previously known electrical control and regulation methods results from the fact that it is not the actual control variables ( o ( , ρ) themselves) that are measured, but variables that depend on them or that result from them (Co. ,, Cj ₂ , O _{2, etc.)} and that these indirect variables also serve to control the aerodynamic control organs, which are poor in terms of efficiency

009833/1217 " ^{Sheet 2} "

EM 2 270,

En / Hb February 6, 1969

To program in the control device almost any plug behavior, for this reason cannot be exploited.

It is therefore the object of the invention to provide a method of the initially to create mentioned type, in which additional angle of attack warning devices are superfluous, and the possibilities given by the plug control devices not by the mechanical-aerodynamic acting control devices are limited. ;.; ,

This object is achieved according to the invention by the combined formation of a direct angle of attack or sliding angle control fe ( oc-t ß control), ie use of these angles as control variables, with control torque generation by deflection of the thrust jet.

The invention is explained below using the example of an angle of attack control, the so-called <X control. The same applies analogously to the slip angle or ft control. With the O ^ control there is a direct assignment of the angle of attack to the stick deflection, ie each stick position corresponds to a certain angle of attack. The different control torques required at different plug speeds to achieve a certain angle of attack v. are controlled by the control system, which can be influenced, for example, by the dynamic pressure.

The use of known SiOH nudge trahlablenkung for ER- ψ generation of control moments, in conjunction with the G ^ control special advantages, since the beam deflection almost instantaneously responds to a secondary injection or similar modern methods to control commands such as uses. In this way, the advantages of the fast electrical control, which can be foreseen with almost any characteristic, are not reduced, but on the contrary are supported. In particular, all aerodynamic damping surfaces, such as lateral or horizontal fins, are superfluous when using the so-called stroke beam deflection, so that the plug stuff has practically no self-damping and therefore assumes the ideal damping behavior programmed into the control system much more easily. In addition, sioh results in most of the cases due to the port case

- Sheet 3 009833/1217

EM 2 270 ~, 't

En / Hb 6οFebruary 1969. * |

damping and control systems tailored to the slow flight characteristics

■ * y

surfaces a considerable reduction in the surface or wave resistance, which means a corresponding increase in flight performance.

The invention provides that the angle of attack or sliding angle is determined and entered into the control system for further processing.

According to a further feature of the invention, the measured adjustment and slip angle in the control system compared with the control commands of the pilot or an autopilot and together with them transformed into the control signals for the control organs.

The invention also gives the possibility of direct contact or To be installed alongside a conventional system and via a z “B. Automatic controlled by the airspeed switch on or show low airspeeds.

Furthermore, it is provided according to the invention that the maximum stick deflection in the "pulling" direction corresponds to an angle of attack below the maximum permissible angle of attack. This maximum permissible angle of attack will usually be the angle at which the wing flow breaks off (t ¹ _{a max} ), or, for example, the maximum angle at which the aircraft does not hit the ground during take-off or landing. In this way, the inventive method also acts as a very effective stall protection without additional devices. In addition, it is also possible, for example, to limit the angle of attack downwards in order to avoid unstable flight positions, for example.

According to the invention, there is a device for carrying out the method provided, which is characterized by aerodynamic pitch and sliding angle sensors, position and angle sensors for education electrical signals corresponding to the measured values and the pilot's commands, a controller for processing these signals, as well as electrical or electro-hydraulic actuated control elements controlled by the regulator to deflect the thrust jet. These control organs can in at In a known manner, flaps protruding into the thrust jet, pivotable nozzles or openings for secondary jet injection arranged within the nozzle be..

009833/1217 - sheet 4 -

EM 2 27O V

En / Hb February 6, 1969

An embodiment of the invention is shown in the drawing and described in more detail below. Show it:

Fig. 1 is provided with O ^, jb sensors and thrust jet deflectors

Plane in a side view,
2 shows a block diagram for a CC control or regulation.

The jet aircraft 1 shown in Fig. 1 has a conventional Have a fuselage and a pair of wings 2, but the stern is formed without control and damping surfaces, as the required Control moments around the center of gravity 3 by horizontal or ver ~ ™ vertical deflection of the thrust jet emerging from the aircraft tail is effected «To deflect the gas jet are several, by one Steering machine actuated flaps 4 are provided. ■ -. "■■■

In Fig. 2 the block diagram for an angle control (οέ control) is shown. Via the control stick 10, the pilot gives his control commands, which are converted into electrical signals by the position transmitter 11. These signals are input to the controller 12. At the same time, the oC sensors 13) enjoy the angle of attack and also convert it into electrical signals by means of the angle of attack transmitter 14. The Signale.des Ansteilwinkelgebers, are also inputted into the controller 12 ,, as compared with the signals of the throttle position sensor 11 and · to a signal for controlling the rudder ψ organs. 15 processed.,. -.- -. . ■

The function of the pilot can, of course, also take place in a conventional manner be perceived by an autopilot 16 "

A cross-fade of the c (control with a conventional control the! Toraalbenchelerationirunj- (n "control) or" a switch to on Such a system int in a manner known per se by corresponding Flühaltunken in the controller 12 possible and. therefore not shown in more detail, ■

One of those "-OC-Steuorun;" cnt. '-. splendid establishment is also possible for the "chicbevankelste-u · rwnß_, as. -in Fig. 2 ( ß ) was indicated"

ÜU98 3 3/121 7 ....

BADORlQiNAL

Claims (1)

ENTWICKLIJNGSRING GÜD GMBH ζ MUNICH , _. February 6th EM 2 270
En / Hb Claims / 1.ι method for setting and sliding angle control of a jet flight ^^ stuff, especially a high-performance fighter plane, with a electrical transmission of the S-control command from the pilot to the Control organs with the interposition of a regulator system, characterized by the combined use of a direct one Angle of attack or sliding angle control ((X, & -control), i.e. Use of these angles as controlled variables, with a control torque generation by deflection of the thrust jet. 2β method according to claim 1, characterized in that the angle of attack or sliding (<X, ß) determined and for further processing can be entered into the control system (12). 3 «Method according to claims 1 and 2, characterized in that the measured angles of attack and throwing ( <X , ρ) in the Heglersystea (12) compared with the control commands of the pilot and together with this to the control signals for the control organs (15 ) are reshaped. 4. The method according to claims 1 to 3, characterized net that the direct part or sliding angle control next to is built into a conventional system and switched on or displayed via an automatic system controlled, for example, by the plug speed will. 5 «Method according to claims 1 to 4» daduroh characterized in that the maximum deflection of the control stick (1O) in the "pull" direction corresponds to an angle of attack (oL) below the highest to-Iäi3igen angle of attack. 6 »Device for carrying out the process according to claims 1 to 5 »characterized by aerodynamic pitch and Cutting angle sensors (13), position sensors (11) and angle sensors (14) for the formation of electrical, the Keßwert as well as the pilot command corresponding Signals, a controller (12) for processing these signals »Nale, as well as electrically or electrohydraulically operated by the controller activated control elements (15) for deflecting the thrust jet. . ,. _: - 0.09833 / 12 17 Lee rse i te