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Adaptive compensation pwpf modulation method and device for aircraft rcs

A technology of self-adaptive compensation and modulation method, applied in the direction of aerospace vehicle guidance devices, aircraft, aerospace vehicles, etc., can solve the problems of high failure rate of RCS thrusters, increased fuel consumption of RCS thrusters, etc.

Active Publication Date: 2021-04-02
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] In the existing aircraft RCS thruster (reaction control system, Reaction Control System, RCS), the control accuracy is generally improved by PWPF modulation (PWPF, pulse width pulse frequency), but the existing PWPF modulation is based on frequent thrust On the basis of switching on and off the engine, too frequent switching will increase the fuel consumption of the RCS thruster and lead to a higher failure rate of the RCS thruster

Method used

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  • Adaptive compensation pwpf modulation method and device for aircraft rcs
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  • Adaptive compensation pwpf modulation method and device for aircraft rcs

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Embodiment 1

[0052] figure 1 It is a flow chart of an adaptive compensation PWPF modulation method for an aircraft RCS provided in Embodiment 1 of the present invention, and the method includes the following steps:

[0053] Step S11: Receive the control torque signal, use the control torque signal to calculate the adaptive damping coefficient algorithm to obtain the damping coefficient, and use the damping coefficient as the coefficient of the damping link of the negative feedback loop of the pulse width pulse frequency modulation.

[0054] In the embodiment of the present invention, the reaction control system (ReactionControl System, RCS) of the existing hypersonic vehicle often uses a constant value thruster, which needs to rely on PWPF modulation (Pulse-Width Pulse-Frequency, PWPF, pulse width pulse frequency modulation) This means to change the real-time control torque required for attitude control into the "digital" variable thrust of the RCS thruster.

[0055] In the embodiment of...

Embodiment 2

[0077] Figure 5 It is a graph of time and switching times of adaptive compensation PWPF modulation provided by Embodiment 2 of the present invention.

[0078] Figure 5 The four curves in are the added damping coefficients K 11 , K 12 , K 13 as well as K 14 After the PWPF modulation time vs. switching times curve, the damping coefficient K 11 , K 12 as well as K 13 is the ratio of the input control torque signal to the RCS rated torque E Do the calculation to get, K 14 It is a fixed value of 0.7. in, K 11 , K 12 as well as K 13 The calculation formulas are:

[0079] ;

[0080] ;

[0081] ;

[0082] In the formula, K 11 , K 12 as well as K 13 is the damping coefficient, E is the ratio of the control torque signal to the RCS rated torque.

[0083] In the embodiment of the present invention, K 11 It can be used as the optimal adaptive damping coefficient, so that the switching times of the adaptive compensation PWPF modulation are lower i...

Embodiment 3

[0087] Figure 7 It is a schematic structural diagram of an adaptive compensation PWPF modulation device for an aircraft RCS provided in Embodiment 3 of the present invention.

[0088] The adaptive compensation PWPF modulation device 700 of the aircraft RCS includes:

[0089] The damping coefficient calculation module 710 is used to receive the control torque signal, use the control torque signal to calculate the damping coefficient through the adaptive damping coefficient algorithm, and use the damping coefficient as the damping link of the negative feedback loop of the pulse width pulse frequency modulation coefficient;

[0090] The torque signal modulation module 720 is configured to use the control torque signal to perform pulse width pulse frequency modulation to obtain a modulated torque signal, and the negative feedback signal in the pulse width pulse frequency modulation uses the damping coefficient and the modulated torque signal Obtained by multiplication.

[0091...

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Abstract

The present invention provides an adaptive compensation PWPF modulation method and device for aircraft RCS. The adaptive compensation PWPF modulation method for aircraft RCS includes: receiving a control torque signal, using the control torque signal to perform an adaptive damping coefficient algorithm calculation to obtain damping Coefficient, using the damping coefficient as the coefficient of the damping link of the negative feedback loop of pulse width pulse frequency modulation; Utilize the control torque signal to carry out pulse width pulse frequency modulation, obtain the torque signal after modulation, and in the pulse width pulse frequency modulation The negative feedback signal is obtained by multiplying the damping coefficient and the modulated torque signal. The adaptive compensation PWPF modulation method of the aircraft RCS of the present invention can make the modulation period of the PWPF longer, the pulse width larger, and the ability of each modulation to reduce errors becomes stronger, reducing the total number of PWPF modulation cycles, thereby reducing The total number of times the RCS thruster is turned on and off is reduced, and the fuel consumption and failure rate of the RCS thruster are reduced.

Description

technical field [0001] The present invention relates to the field of reaction force control, in particular to an aircraft RCS adaptive compensation PWPF modulation method, device, computer equipment and readable storage medium. Background technique [0002] In the existing aircraft RCS thruster (reaction control system, Reaction Control System, RCS), the control accuracy is generally improved by PWPF modulation (PWPF, pulse width pulse frequency), but the existing PWPF modulation is based on frequent thrust Based on the switch of the engine, too frequent switching will increase the fuel consumption of the RCS thruster and lead to a higher failure rate of the RCS thruster. Contents of the invention [0003] In view of the above problems, the present invention provides an aircraft RCS adaptive compensation PWPF modulation method, device, computer equipment and readable storage medium to reduce fuel consumption and failure rate of RCS thrusters. [0004] In order to achieve ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24B64G1/28
CPCB64G1/24B64G1/28B64G1/245
Inventor 宋佳赵鸣飞张严雪徐小蔚罗雨歇
Owner BEIHANG UNIV
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