The usages of the invention are for example miniature helicopters, miniature multi-copters and airplanes. The before mentioned operation organs of these apparatuses are operated as known by radio operation so that their efficiencies, positions and other functions can be regulated in remote control. It is possible for instance to feed for an electric motor the efficiency by sending from a radio transmitter a signal of a certain wave length through a certain channel into the receiver of the flying apparatus that then relays it to the flight control unit, like for instance a computer, wherefrom it is conveyed using pulse-duration modulation technique, bus technique or some other known technique to the electronically operated speed regulator or to a servo drive operating a manually operated speed regulator and the speed regulator adapts the efficiency going to a motor coming from an electricity source, like a battery or an accumulator, to a certain power corresponding the signal to be sent to a motor.

If a faulty state occurs it is possible that the parachute of the flying apparatus in air must be opened so that the apparatus would not cause danger when falling to the earth and when opening the parachute the motors of the flying apparatus must also be turned off for safety reasons. One of the applications of the invention is in fact linked to this kind of situations. When for example a mulfi-copfer comes in this kind of situation, in the known technique solution the parachute is opened and the motors are stopped by sending a radio signal from the earth and the signal is changed so that the speed regulators stop feeding electricity for the motors. It is known that the parachute can be triggered open either by the remote control or the parachute unit in the apparatus operates automatically. In the latter case the triggering can be based upon the usage of the sensor of for example acceleration, position or pressure.

The drawback of this known technique is that there comes easily a time delay between the parachute triggering and the stop of the motors. Especially, when the parachute is trigged automatically through its operating unit the delay is impossible to avoid. This delay can cause in turn additional problems, e.g. the uncontrolled movements of the apparatus lead to the parachute to be destroyed when the propeller blades hit it.

Earlier mentioned other equipments, like camera stand, the camera itself or the feet of the apparatus are operated in the known technique so that when desired to get their position change, a corresponding radio signal is sent from the remote controller, that signal is led from the receiver through the flight control unit to the servo that operates the operation unit using some known signal technique, e.g. PWM, PPM, or bus technique.

It is known that all the channels of the radio controller are updated all the time during the operation of the flying apparatus and then a signal is given continuously to the operation units. The signal can be the same for a certain time period and then for instance the power of a motor is constant that time. The pulse length of PWM signal can typically vary for instance 1 ,0 - 2,0 ms, and when the motor runs with half power a constant pulse of 1 ,5 ms is fed to the speed regulator. The servos operating the operating unit can correspondingly be set to operate so that the signals of the min and max values have pulse lengths 1 ,0 ms and 2,0 ms when operating in the before mentioned pulse length area.

The greatest drawback of this mentioned known technique is that the position changes of the operation units depend on the reactions of the operator of the flying apparatus, when for instance turning the feet into the landing position can be delayed in some uncommon situation.

The object of this invention is to get such a method to replace the control signal of the operation organ of a remote controlled apparatus with another signal that drawbacks of the known technique are avoided. It is characteristic for the solution according to the invention what has been presented in the characterizing parts of the claims 1 -3.

The biggest advantage of the invention can be seen that the mentioned operating organs when being operated in certain fault situations and during the phases of the flight are not dependent on the reactions of the operator of the flying apparatus and his actions but the system handles them automatically so that the problems coming from the operator's reaction time are avoided.

Advantage is also achieved because the settings of the radio controller can be simplified so that a separate alternative signal is not needed, e.g. turn-off signal for the motor, to be defined in the settings.

The (forced) replacement of the signal according to the invention is very useful also in situations where the flight control equipment is not operational and gives bad or even faulty operation signals. This can happen as a result of a software bug or a sensor failure. Another signal replacement situation can be that the operator becomes incapable†o control the flying apparatus and the operator gives bad commands with his radio control device. The controller can then use for instance the parachute trigger as a so called panic button as he cannot do anything else. The reason for the signal replacement can also be any mechanical failure.

In this document the word "motor" means the electric motor that rotates the propeller or rotor of the flying apparatus. Other names are used for other motors.

The invention is described in more detail in the enclosed drawings where

Fig. 1 presents schematically the signal handling system of the invention,

Fig. 2 presents schematically the remote controlling system according to the invention of one remote controlled flying apparatus

Next, a favourable structure and usage of the application of the invention is explained referring to the before mentioned figs.

The figure 1 shows the principal main points of the invention. The radio signals 2a, 2b etc. coming from the transmitter 1 come to the receiver 3 of the flying apparatus, wherefrom the commands 2a\ 2b ^" , etc. of these signals are transmitted to the flight controller 4. The mentioned com- mands are transmitted from the flight controller as control signals a, b etc. to the safety unit 5. The safety unit allows these control signals through itself under normal circumstances to the operation organs, like motors, apparatus feet, camera stand, camera etc. In the method according to the invention, when taking the apparatus into use, the replac- ing signals are stored in the memory of the safety unit 5 and under the fault and danger situations the replacement of the operating signals a, b etc. take place according†o the following example:

The figure 2 describes in more detail schematically and more largely the remote control application according to the invention of a flying multi-copter with four propellers. So, the transmitter is used to send radio signals 2a, 2b, etc. to the receiver 3 that is located in the apparatus with certain frequencies and in certain channels. The orders 2a\ 2b\ etc. according these signals are transmitted from the receiver 3 to the flight controller 4 that is for example a computer or autopilot. The flight controller 4 feeds the pilot signals a, b, etc. that have been treated according to its own algorithms to the safety unit 5. When for instance it is question about the normal operation of the motors 6a- 6d rotating for example the propellers 12, the safety unit 5 lets through the pilot signals a- d to go forwards†o the electronic speed regulators 7a- 7d. of these motors. (Two motors and their speed controllers are not visible in the picture). In this example, the speed regulators use the pulse width modulator (PWM) that is used to define the efficiency of the electric power to be sent to the motors 6 from the power source 1 1 and the multicopter flies as a result of the rotation of the propellers 12 and other measures of the flight control following a certain path or staying in its location in the air. So it has been stored in the memory of the safety unit 5 of the mulfi-copter at hand before flight when the settings were made the replacing signal x that is the abort signal of the motors and when a faulty state occurs where the multi-copter for instance hits an obstacle, the acceleration sensor of the parachute 8 operation unit 9 gives a message of overflow (in this case a negative value) and then the operation unit 9 of the parachute that can be a separate unit, a part of the safety unit 5 or a sensor controlling the parachute trigger sends to the parachute 8 a trigger signal and the parachute is shot out. In this document, the general name of control unit 9 is used about all the equipments that take care of the control of the parachute. In this example, a separate operation unit 9 sends essentially at the moment of the trigger of the parachute a signal s to the safety unit 5 that a trigger has occurred and then the safety unit 5 stops letting control signals a- d to get to the speed regulator 7a- 7d and starts sending the replac- ing signal x, that is the abort signal to the motors by connecting them to the replacing signal a, b, etc. outputs. The signal s telling that the parachute has been triggered can also be replaced by the inner information transfer of the safety unit 5 when the mentioned control unit is a part of the safety unit. In other words, the transmission of the signal de- fining the power transfer of each motor is blocked at that moment and the replacing signal of each motor that stops the motor is started to be transmitted at the same time automatically.

The before mentioned signal replacement of the power of the motors may necessarily be replaced so that the motor or motors 6 get a little of electric power so that after triggering the parachute some current supply remains because then the method according to the invention is realized also in this solution as, however, the propeller rotation slows down essentially.

The invention can also be applied so that when the motors 6 are being stopped or their power supply is reduced essentially the propeller 12 position is locked immobile or very slow so that their wild rotation is prevented when they are falling or they are got to a position where the falling is slowed down. The invention is also realized when differently than in the before mentioned example the speed controller 7 takes care of more than one motor 6. By feeding a certain signal into this kind of speed regulator more than one motors are got to function in a desired way. The invention can also be applied so that the before mentioned parachute trigger signal is given directly from a radio control device to a mentioned separate control unit 9 or safety unit 5, either at the same time or separately with the flight control unit 4. This signal can be sent by any radio device that is in contact with the system or by an author- ized user. As an example of this kind of sender a police officer can be mentioned.

Every propeller 12 can have a motor of its own in which case the power of these motors can be regulated with more than one signal. It is also possible to use a one motor construction in which case power transmission organs are used between the motor and the propellers to transfer different power to the propellers. It is also possible†o use power transfer organs in one motor one propeller systems. It is possible to stop more than one motor by sharing the signal x with all the motors.

Another application of the invention is to replace the signal y that keeps the feet of the flying apparatus in flight position with such a replacing signal y ^" that has been stored in the memory of the safety unit 5 that gets the servo 10.1 controlling the feet 10†o turn in a certain way so that the mechanism that has been connected to the servo turns the feet into the landing position. If desired, this application can be connected to the trigger of the parachute 8, when the signal s from the control unit 9 to the safety unit 5 activates the safety unit 5 to stop also sending†o the servo the signal y of the feet and to begin to send the replacing signal y\ The invention can be applied to get the feet position changed in such a way that the closing and opening of the feet is connected to certain altimeter value so that the feet close at a certain altimeter value and open at a certain value automatically. In this case, the signal coming from the altimeter to the safety unit 5 causes the safety unit to replace the signal y to be sent to the feet 10 with a replacing signal y\

In the same way, the control of the camera in the flying apparatus can be done by sending a replacing signal that the camera stand or camera trigger has sent to the servo at a certain moment with another signal that causes a certain movement.

The speed regulator that is used can also be mechanical and then its operation is controlled with a servo and the operation of this servo by signals coming from the safety unit 5. Instead of the before mentioned PWM technique some bus technique can be used in the method according to the invention, PPM technique or any other signal transmission technique. It is essential for the invention that any signal that the flying apparatus transmits to any control organ can be replaced at a certain moment with another signal that has been stored in the memory of the safety unit 5 of the flying apparatus or that is sent past the safety unit.

The control organ can be any radio operated control organ of the flying apparatus. The operational control organ can be for instance the feet of the flying apparatus, camera stand, camera, stabilizing system or electric motor. The need of the position change of the control organ can be expressed for instance by sending a signal to the safety unit 5 automatically from the parachute control unit 9, from the altimeter, position sensor, from some other unit that is following or controlling the flight or from some other radio transmitted that is connected to the system in question at a certain moment.

The method according to the invention can also be adopted so that the signal to open the parachute and turning the motors off is sent by a separate radio transmitter, one or more, in channels that have been reserved for that having certain frequencies.

One application of the invention can be seen a method where the replacing signal is a signal that is sent from the earth that cuts the current from the motors.

The method according to the invention can also be applied so that the replacing signal is sent from the receiver (3) past the flight control (4) to the safety unit or also past the safety unit directly to the speed regulator or servo controlling the control organ. According to the figure 2, when the replacing signal x, y\ τ etc. is sent through the safety unit (5), and from the receiver (3) a signal v is sent telling rotation speed of the control organ or the need for the position change to the safety unit and the safety unit replaces this signal to be replaced with a replacing sig- nal. In case the replacing signal is sent by the before described way directly past the safety unit (5), it is another replacing signal x\ ^¾ \ z ^" , etc. In this case the other replacing signal ~ is another replacing signal to be sent to the speed controller or servo and y ^* \ z ^" etc. are other replacing signals to be sent to other controlling organs (servos) .

The power source 1 1 to be used in the method can be for instance accumulator, battery or fuel cell. I† should be noted that even though this description keeps to one type of favourable realization of fhe invention, this does not intend†o limit fhe use of fhe invention only in this kind of examples, but many varia- tions are possible within the scope of the inventive idea that is defined in the claims.