CN-122009519-A - Unmanned tiltrotor aircraft test system based on model simulation

CN122009519ACN 122009519 ACN122009519 ACN 122009519ACN-122009519-A

Abstract

The invention discloses an unmanned tilt rotorcraft testing system based on model simulation, which belongs to the technical field of aerospace and comprises a flight state and environment parameter acquisition module, a control margin dynamic evaluation module and a control margin dynamic evaluation module, wherein the flight state and environment parameter acquisition module is used for acquiring current airspeed and task load quality representing the flight state of an unmanned tilt rotorcraft, environment wind speed representing the external environment and invoking inherent aircraft air quality and maximum design roll angle of an aircraft, and the control margin dynamic evaluation module is used for calculating wind speed interference compensation factors based on the current airspeed and the environment wind speed and calculating load influence factors based on the task load quality and the aircraft air quality so as to quantify coupling consumption of strong wind and heavy load on control margin.

Inventors

JIANG HAITAO
ZHANG ZHENGUO
ZHENG FENG

Assignees

山东风向标智航装备有限公司

Dates

Publication Date: 20260512
Application Date: 20260204

Claims (9)

1. An unmanned tiltrotor aircraft test system based on model simulation, comprising: The flight state and environment parameter acquisition module is used for acquiring the current airspeed representing the flight state of the unmanned tilt rotorcraft And task load mass And ambient wind speed characterizing the external environment And invoking aircraft-inherent aircraft air-to-air quality With maximum design roll angle ; A control margin dynamic evaluation module for based on current airspeed And the ambient wind speed Calculating wind speed disturbance compensation factors And based on task load quality And the air-to-air mass of the aircraft Calculating load influencing factors To quantify the coupling consumption of strong wind and heavy load to the control margin; The flight risk index calculation module is used for applying a multiplicative attenuation model and combining the maximum design rolling angle Wind speed disturbance compensation factor Load influencing factor Determining a dynamic effective maximum roll angle And thereby generating a quantified risk of flight index Thereby converting the flight safety margin into a precisely calculated value; risk early warning and flight control intervention module for indexing flight risk With a preset warning threshold Threshold of risk And performing real-time comparison, and executing a closed-loop control strategy of safety, warning or automatic intervention according to the comparison result so as to realize active safety guarantee on the flight risk.
2. The model simulation-based unmanned tiltrotor aircraft test system according to claim 1, wherein the risk of flight index calculation module is further configured to, prior to risk assessment, calculate a current airspeed based on the current airspeed And maximum design roll angle The ideal minimum turning radius is calculated according to the following formula As a performance benchmark: Wherein A gravitational acceleration constant.
3. The model simulation-based unmanned tiltrotor aircraft test system according to claim 1, wherein the control margin dynamic assessment module calculates the wind speed disturbance compensation factor by the following formula To accurately reflect aerodynamic characteristics: ; for maximum design of the wind resistance limit, The airspeed is designed for a reference, The sensitivity index is influenced for wind speed.
4. A model simulation based unmanned tiltrotor aircraft test system according to claim 3, wherein the risk index calculation module incorporates the maximum design roll angle by a multiplicative attenuation model as follows Wind speed disturbance compensation factor Load influencing factor Generating an effective maximum roll angle : 。
5. The model simulation based unmanned tiltrotor aircraft test system according to claim 4, wherein the risk of flight index calculation module further utilizes the generated effective maximum roll angle Calculating dynamic minimum turning radius considering real-time interference The calculation formula is as follows: 。
6. The model simulation-based unmanned tiltrotor aircraft test system according to claim 5, wherein the risk of flight index calculation module incorporates an ideal minimum turning radius And dynamic minimum turning radius Generating a flight risk index by the following formula To obtain a standardized risk indicator: 。
7. The unmanned tiltrotor aircraft test system based on model simulation according to claim 1, wherein the risk pre-warning and flight control intervention module executes a closed-loop control strategy for the flight risk index All possible logical intervals are explicitly defined and assigned explicit actions, including in particular when the risk of flight is indexed Less than the warning threshold When the flight risk index is determined to be safe, no intervention measures are taken Greater than or equal to the warning threshold And is less than the hazard threshold When the flight risk index is determined to be a warning zone, a prompt message that the maneuvering margin is limited is sent to the ground station Greater than or equal to the hazard threshold And when the dangerous area is judged, the highest-level alarm is sent out, and the intervention measures are automatically executed.
8. The model simulation based unmanned tiltrotor aircraft test system according to claim 7, wherein the automatically performed intervention includes limiting the maximum airspeed command sent to the flight control system or forcing an increase in the turning radius of the preset route, thereby fundamentally improving flight safety.
9. The model simulation based unmanned tiltrotor aircraft test system according to claim 7, wherein the warning threshold value And a risk threshold The method for setting has definite engineering criteria, and comprises calibrating by multiple pilots through a flight simulator, and reporting the flight risk index when the majority of pilots report the aircraft response start delay Is set as a warning threshold Through Monte Carlo off-line simulation, the flight risk index causing the aircraft to run away is counted Distribution of values, taking the safety boundary value as the dangerous threshold 。

Description

Unmanned tiltrotor aircraft test system based on model simulation Technical Field The invention relates to the field of aerospace, in particular to an unmanned tilt rotorcraft testing system based on model simulation. Background The unmanned tilt rotorcraft is widely applied to high-demand scenes such as offshore operation, rescue and relief work and the like, but the scenes are often accompanied by complex weather such as strong wind and the like, and in engineering practice, the unmanned tilt rotorcraft faces the inherent contradiction between high-speed flight performance and high maneuverability, and is particularly embodied as the balance of two core indexes of maximum flight speed and minimum turning radius. When the aircraft encounters strong wind under the condition of approaching the upper limit of the mission load and heavy load, the contradiction is greatly amplified, the flight control system consumes a large amount of control resources for compensating the strong wind interference, meanwhile, the high inertia caused by the heavy load also makes maneuvering turning more difficult, and the coupling effect of the strong wind interference and the heavy load inertia can seriously compress maneuvering margin in high-speed flight and has the technical risk of out-of-control gesture. The prior art lacks a model and a method capable of effectively quantifying the influence of the coupling effect on the flight safety margin, and cannot provide dynamic and real-time risk assessment for the flight. The above information disclosed in the above background section is only for enhancement of understanding of the background of the disclosure and therefore it may include information that does not form the prior art that is already known to those of ordinary skill in the art. Disclosure of Invention The invention aims to provide an unmanned tiltrotor aircraft testing system based on model simulation, which aims to solve the problems in the background technology. The technical scheme of the invention is that the method comprises the following steps: the flight state and environment parameter acquisition module is used for acquiring current airspeed and task load quality representing the flight state of the unmanned tilt rotorcraft, and environment wind speed representing the external environment, and calling inherent aircraft air-to-air quality and maximum design roll angle of the aircraft; the control margin dynamic evaluation module is used for calculating a wind speed interference compensation factor based on the current airspeed and the ambient wind speed, and calculating a load influence factor based on the task load quality and the aircraft air-plane quality so as to quantify the coupling consumption of strong wind and heavy load to the control margin; The flight risk index calculation module is used for applying a multiplicative attenuation model, combining a maximum design rolling angle, a wind speed interference compensation factor and a load influence factor, determining a dynamic effective maximum rolling angle, and generating a quantized flight risk index according to the dynamic effective maximum rolling angle, so that the flight safety margin is converted into a numerical value capable of being calculated accurately; And the risk early warning and flight control intervention module is used for comparing the flight risk index with a preset warning threshold value and a preset danger threshold value in real time, and executing a closed-loop control strategy of safety, warning or automatic intervention according to the comparison result so as to realize active safety guarantee of the flight risk. Preferably, the flight risk index calculation module is further configured to, prior to risk assessment, calculate a risk of the aircraft based on the current airspeed And maximum design roll angle, calculating ideal minimum turning radius as performance reference according to the following formula: Wherein the gravitational acceleration constant. Preferably, the control margin dynamic assessment module calculates the wind speed disturbance compensation factor to accurately reflect the aerodynamic characteristics by the following formula: The wind resistance limit is designed for maximum, the airspeed is designed for reference, The sensitivity index is influenced for wind speed. The flight risk index calculation module combines the maximum design rolling angle through the following multiplicative attenuation modelWind speed disturbance compensation factorAnd a load influencing factor, generating an effective maximum roll angle : Preferably, the flight risk index calculation module further calculates a dynamic minimum turning radius considering real-time interference by using the generated effective maximum roll angle, and the calculation formula is as follows: Preferably, the flight risk index calculation module combines the ideal minimum turning radius and the dynamic minimum turning radius to generate the fli