CN-121543454-B - Helicopter vortex ring state prediction method and device, helicopter and storage medium

CN121543454BCN 121543454 BCN121543454 BCN 121543454BCN-121543454-B

Abstract

The application provides a method, a device, a helicopter and a storage medium for predicting the state of a vortex ring of the helicopter, which relate to the technical field of helicopter data processing, and the method respectively determines the characteristic parameters of a downwash field and the derivative characteristic parameters based on the current flight parameters, and determining input parameters based on the characteristic parameters of the downwash field, the current flight parameters and the derivative characteristic parameters, and obtaining output vortex ring state prediction information based on the input parameters and a pre-trained risk prediction model. By introducing the characteristic parameters of the downwash field and the derivative characteristic parameters to predict the vortex ring state in advance, early warning time and operating margin can be provided for pilots, early warning accuracy can be improved, and flight safety can be further improved.

Inventors

YANG NINGMENG
ZHANG WEIGUO
WANG CHANG
WANG LIANGQUAN
CHE BINGHUI
SONG XIN
Duan Zhangcheng

Assignees

中国空气动力研究与发展中心低速空气动力研究所

Dates

Publication Date: 20260512
Application Date: 20260119

Claims (7)

1. A method for predicting the state of a vortex ring of a helicopter is characterized by comprising the following steps: The method comprises the steps of obtaining current flight parameters, wherein the current flight parameters comprise torque, rotor angular speed, rotor radius, air pressure, air temperature, rotor rotating speed, vertical drop rate, current flight state and rotor pitch area; determining an intermediate characteristic parameter based on the current flight parameter, and determining a downwash field characteristic parameter based on the intermediate characteristic parameter and the current flight parameter; determining derived feature parameters based on the current flight parameters and the downwash field feature parameters; determining input parameters based on the downwash field characteristic parameters, the current flight parameters, and the derivative characteristic parameters; obtaining output vortex ring state prediction information based on the input parameters and a pre-trained risk prediction model; The intermediate characteristic parameters include a current rotor tension and a current air density, the determining the intermediate characteristic parameters based on the current flight parameters includes: determining a current rotor pull based on torque, rotor angular speed, and rotor radius; determining a current air density based on the air pressure and the air temperature; The downwash field characteristic parameters include an average downwash flow rate, and the determining the downwash field characteristic parameters based on the intermediate characteristic parameters and the current flight parameters includes: determining an average downwash flow rate based on the current flight status, the current rotor drag, the air density, and the rotor disk area; the derived feature parameters include an inflow ratio, and the determining the derived feature parameters based on the current flight parameters and the downwash field feature parameters includes: The inflow ratio is determined based on rotor speed, rotor radius, vertical descent rate, and average downwash flow rate.
2. The helicopter vortex ring state prediction method of claim 1 wherein determining an average wash down flow rate based on a current flight state, a current rotor pull, an air density, and a rotor disk area comprises: determining an average downwash flow rate based on the current rotor drag, air density, and rotor disk area when the current flight condition is a hover condition; When the current flight condition is a forward flight condition, an average downwash flow rate is determined based on the current rotor drag, air density, rotor disk area, and vertical descent rate.
3. The method of claim 1, wherein said determining input parameters based on said downwash field characteristic parameters, said current flight parameters, and said derivative characteristic parameters comprises: And splicing the characteristic parameters of the downwash field, the current flight parameters and the derivative characteristic parameters to obtain the input parameters.
4. The method of predicting state of a helicopter vortex ring according to claim 1, said method further comprising: And determining early warning information based on the vortex ring state prediction information, and displaying the early warning information.
5. A helicopter vortex ring state prediction apparatus for performing a helicopter vortex ring state prediction method as claimed in any one of claims 1 to 4, comprising: the data acquisition module is used for acquiring current flight parameters, wherein the current flight parameters comprise torque, rotor angular speed, rotor radius, air pressure, air temperature, rotor rotating speed, vertical drop rate, current flight state and rotor disk area; The first processing module is used for determining an intermediate characteristic parameter based on the current flight parameter, and determining a downwash characteristic parameter based on the intermediate characteristic parameter and the current flight parameter; the second processing module is used for determining derivative characteristic parameters based on the current flight parameters and the downwash characteristic parameters; a third processing module for determining input parameters based on the downwash field characteristic parameters, the current flight parameters, and the derivative characteristic parameters; and the risk prediction module is used for obtaining output vortex ring state prediction information based on the input parameters and a pre-trained risk prediction model.
6. A helicopter comprising a memory and a processor for executing program instructions stored in the memory to implement the helicopter vortex ring state prediction method of any of claims 1 to 4.
7. A computer readable storage medium, having stored thereon a computer program which, when executed by a processor of a computer, causes the computer to perform the helicopter vortex ring state prediction method of any of claims 1 to 4.

Description

Helicopter vortex ring state prediction method and device, helicopter and storage medium Technical Field The application relates to the technical field of helicopter data processing, in particular to a method and a device for predicting the state of a helicopter vortex ring, a helicopter and a storage medium. Background The vortex ring state is a dangerous flight state of the helicopter and usually occurs in the descending process of a large descending rate and a small forward flying speed. At this time, the helicopter rotor falls into the vortex formed by self downwash, which causes the rotor efficiency to be rapidly reduced, the operability to be deteriorated, the body to be severely dithered and accompanied with uncontrollable rapid falling, the window-out period to be changed is extremely short, and the flying accident is extremely easy to be caused. In an sandy blind environment, a pilot can not effectively judge the altitude and the ground speed visually, so that the pilot can more unconsciously operate the helicopter into a flight envelope inducing VRS (Vortex RING STATE ). Currently, alarms for VRS in the related art are mostly based on simple threshold judgment, such as monitoring whether the vertical drop rate exceeds a certain empirical threshold. The post-alarm mechanism has the obvious defects that when an alarm is triggered, a helicopter is always in or very close to VRS, the change time and the height left for a pilot are almost all left, the safety is insufficient, and the early warning accuracy and the early warning prospect are insufficient. Disclosure of Invention The application provides a method and a device for predicting the state of a vortex ring of a helicopter, the helicopter and a storage medium, and the vortex ring state is predicted in advance by introducing a characteristic parameter of a downwash field and a derivative characteristic parameter, so that early warning time with longer duration and a manipulation margin can be provided for a pilot, the early warning accuracy can be improved, and the flight safety can be further improved. The application provides a method for predicting the state of a vortex ring of a helicopter, which comprises the following steps: The method comprises the steps of obtaining current flight parameters, wherein the current flight parameters comprise torque, rotor angular speed, rotor radius, air pressure, air temperature, rotor rotating speed, vertical drop rate, current flight state and rotor pitch area; determining an intermediate characteristic parameter based on the current flight parameter, and determining a downwash field characteristic parameter based on the intermediate characteristic parameter and the current flight parameter; determining derived feature parameters based on the current flight parameters and the downwash field feature parameters; determining input parameters based on the downwash field characteristic parameters, the current flight parameters, and the derivative characteristic parameters; And obtaining output vortex ring state prediction information based on the input parameters and a pre-trained risk prediction model. Optionally, the intermediate characteristic parameter includes a current rotor tension and a current air density, and the determining the intermediate characteristic parameter based on the current flight parameter includes: determining a current rotor pull based on torque, rotor angular speed, and rotor radius; The current air density is determined based on the air pressure and the air temperature. Optionally, the downwash field characteristic parameter includes an average downwash flow rate, and the determining the downwash field characteristic parameter based on the intermediate characteristic parameter and the current flight parameter includes: Based on the current flight status, current rotor drag, air density, and rotor disk area, an average downwash flow rate is determined. Optionally, determining the average wash-down flow rate based on the current flight status, the current rotor drag, the air density, and the rotor disk area comprises: determining an average downwash flow rate based on the current rotor drag, air density, and rotor disk area when the current flight condition is a hover condition; When the current flight condition is a forward flight condition, an average downwash flow rate is determined based on the current rotor drag, air density, rotor disk area, and vertical descent rate. Optionally, the derived feature parameter includes an inflow ratio, and the determining the derived feature parameter based on the current flight parameter and the downwash feature parameter includes: The inflow ratio is determined based on rotor speed, rotor radius, vertical descent rate, and average downwash flow rate. Optionally, the determining the input parameter based on the downwash field feature parameter, the current flight parameter, and the derivative feature parameter includes: And splicing the charact