초록 ▼

According to the method of the invention, control parameters V indicating speed, R indicating turn characteristics and γ indicating a path angle are determined such that these parameters are maintained between limits, and such that one of them deviates as little as possible from a correspondin

According to the method of the invention, control parameters V indicating speed, R indicating turn characteristics and γ indicating a path angle are determined such that these parameters are maintained between limits, and such that one of them deviates as little as possible from a corresponding control input parameter Ri. In order to maintain (as much as possible) the value of R unchanged, V can be varied. The method may include the calculation of the maximum and minimum thrust available.

대표청구항 ▼

The invention claimed is: 1. A method for controlling control parameters of an air vehicle having a propulsion system and a plurality of control surfaces configured to allow pitch and roll control of the vehicle, the operation of the propulsion system and the positions of the control surfaces being

The invention claimed is: 1. A method for controlling control parameters of an air vehicle having a propulsion system and a plurality of control surfaces configured to allow pitch and roll control of the vehicle, the operation of the propulsion system and the positions of the control surfaces being controlled by means of control signals which are generated from data relating to the conditions of the vehicle and from control parameters comprising a parameter V indicating speed, a parameter R indicating turn characteristics of the vehicle in a horizontal plane, and a parameter γ indicating a path angle of a path which the vehicle must follow in a vertical plane; the method comprising the step of receiving input control parameters including an input parameter Vi indicating said speed, an input parameter Ri indicating said turn characteristics, and an input parameter γi indicating said path angle; characterized in that the method further comprises the steps of: establishing a lower limit V1 and an upper limit V2 for the value of parameter V, establishing a lower limit γ1 and an upper limit γ2 for the value of parameter γ, and establishing a lower limit R1 and an upper limit R2 for the value of parameter R; setting the value of V at a selected value such that a) V1≦the value of V≦V2 and such that b) it allows setting the value of γ at a certain value which deviates as little as possible from the value of γi while at the same time meets the condition γ1≦the value of γ≦γ2, c) and such that it allows setting the value of R at an optimal value which deviates as little as possible from the value of Ri while at the same time meets the condition R1≦the value of R≦R2; setting the value of γ at said certain value; setting the value of R at said optimal value. 2. A method according to claim 1, characterized in that at least some of the values V1, V2, R1, R2, γ1 and γ2 are calculated in real time from data relating to current flight conditions and from a model of the vehicle. 3. A method according to claim 1, characterized in that if further comprises the steps of: calculating an available minimum thrust T1 and an available maximum thrust T2 for the current flight conditions and from a model of the vehicle; calculating, according to said current flight conditions and from the model of the vehicle, a necessary thrust T for a combination of values of V, R and γ; establishing the values of V, R and γ such that the condition T1≦T≦T2 is met. 4. A method according to claim 1, characterized in that it additionally comprises the steps of: obtaining a real airspeed Va of the vehicle; determining a lower limit V3 and an upper limit V4 for the airspeed Va; if the real airspeed Va<V3 or if the real airspeed Va>V4, establishing the values of V, R and γ such that they lead the vehicle to meeting the condition V3≦Va≦V4. 5. A method according to claim 4, characterized in that when the real airspeed Va<V3, the values of V, R and γ are established such that the condition T=T2 is met. 6. A method according to claim 4, characterized in that when the real airspeed Va>V4, the values of V, R and γ are established such that the condition T=T1 is met. 7. An air vehicle control system having a propulsion system and a plurality of control surfaces configured to allow pitch and roll control of the vehicle, the operation of the propulsion system and the positions of the control surfaces being controllable by means of respective actuators controlled by respective output control signals of the control system, said control system comprising: means for generating from data indicating a path which the vehicle must follow, values for input control parameters including an input parameter Vi indicating speed, an input parameter Ri indicating turn characteristics of the vehicle in a horizontal plane, and an input parameter γi indicating a path angle of a path which the vehicle must follow in a vertical plane; means for generating from the values of a parameter V indicating speed, a parameter R indicating turn characteristics of the vehicle in a horizontal plane, and an input parameter γ indicating a path angle, said signals for actuators, including signals for actuators on the vehicle control surfaces and signals for actuators associated to the propulsion system; characterized in that it further comprises a parameter control module configured to calculate the values of V, R and γ from the values of Vi, Ri and γi, said parameter control module being configured for: establishing a lower limit V1 and an upper limit V2 for the value of parameter V, and a lower limit R1 and an upper limit R2 for the value of parameter R, and a lower limit γ1 and an upper limit γ2 for the value of parameter γ; setting the value of V at a selected value such that a) V1≦the value of V≦V2; b) it allows setting the value of γ at a certain value which deviates as little as possible from the value of γi while at the same time meets the condition γ1≦the value of γ≦γ2, c) and such that it allows setting the value of R at an optimal value which deviates as little as possible from the value of Ri while at the same time meets the condition R1≦the value of R≦R2; setting the value of γ at said certain value; setting the value of R at said optimal value. 8. A system according to claim 7, characterized in that the parameter control module is configured to calculate at least some of the values V1, V2, R1, R2, γ1 and γ2 in real time from data relating to current flight conditions and from a model of the vehicle. 9. A system according to claim 7, characterized in that the parameter control module is further configured for: calculating an available minimum thrust T1 and an available maximum thrust T2 for the current flight conditions and a model of the vehicle; calculating, according to the current flight conditions and the model of the vehicle, a necessary thrust T for a combination of values of V, R and γ; establishing the values of V, R and γ such that the condition T1≦T≦T2 is met. 10. A system according to claim 7, characterized in that the parameter control module is additionally configured for: obtaining a real airspeed Va of the vehicle; determining a lower limit V3 and an upper limit V4 for said airspeed Va; if the real airspeed Va<V3 or if the real airspeed Va >V4, establishing the values of V, R and γ such that they lead the vehicle to meeting the condition V3≦Va≦V4. 11. A system according to claim 10, characterized in that the parameter control module is configured such that when the real airspeed Va<V3, the values of V, R and γ are established such that the condition T=T2 is met. 12. A system according to claim 10, characterized in that the parameter control module is configured such that when the real airspeed Va>V4, the values of V, R and γ are established such that the condition T=T1 is met. 13. An air vehicle comprising: a propulsion system controlled by actuators; a plurality of control surfaces controlled by actuators; a control system according to claim 7, configured to provide control signals to said actuators according to the values of the parameters V, R and γ. 14. A computer with a program stored on a computer readable carrier, the program configured to carry out the method of claim 1 when run on said computer.