CN-121973950-A - Fly-through testing device and method for control surface blocking of fly-through transport aircraft

CN121973950ACN 121973950 ACN121973950 ACN 121973950ACN-121973950-A

Abstract

The invention belongs to the field of flight test, and particularly relates to a fly test device and a fly test method for a fly-by-wire transport type aircraft control surface card, which are suitable for fly test of fly-by-wire transport type aircraft control surface card. The control surface blocking setting method is designed, test content is determined according to criticality analysis, the control surface blocking test flight risk of the electric transport aircraft is comprehensively identified, reasonable risk degradation measures are formulated to reduce the test flight risk, and powerful support can be provided for the control surface blocking test flight of the electric transport aircraft on the basis of the principle of progressive and successive approximation in developing the control surface blocking test flight task.

Inventors

SHI JIAWEI
Hui Shaohui
CHEN LI
SHAO BO
WU XING

Assignees

中国飞行试验研究院

Dates

Publication Date: 20260505
Application Date: 20251227

Claims (10)

1. A control surface blocking test flying device of an electric transport type aircraft is characterized by comprising a main flying control module, an actuator controller and a cockpit control panel, wherein the main flying control module stores a control surface blocking program, the control surface blocking program is input through the cockpit control panel, when the main flying control module receives a control surface blocking instruction from the cockpit control panel, a control instruction loop of a steering column, the main flying control module and the actuator controller is interrupted, a control instruction at the interruption moment is frozen, the control surface is blocked at the interruption moment of the control instruction loop, and the control instruction loop of the blocked control surface is changed into a control instruction loop of the cockpit control panel, the main flying control module and the actuator controller.
2. The device for testing the blocking and flying of the control surface of the fly-by-wire transport aircraft according to claim 1, wherein a control surface deflection value is input through a numeric keyboard on a control panel of the cockpit, and the control surface deflection value is superimposed on the blocked control surface to realize the adjustment of the blocking and flying degree of the control surface.
3. A fly-by-wire transport aircraft control surface blocking test method, characterized in that the fly-by-wire transport aircraft control surface blocking test device according to any one of claims 1-2 is adopted, and the method comprises the following steps: Step 1, determining a test flight state point according to control surface jamming criticality analysis; Step 2, determining the maximum control surface blocking angle of each control surface of the aircraft according to the airworthiness regulation requirement of the corresponding model; Step 3, determining control surface blocking test flight evaluation indexes according to the airworthiness regulation requirements of corresponding models; step 4, determining a test flight test item according to the evaluation index determined in the step 3; and 5, carrying out a flight test according to the flight test state point determined in the step 1, the maximum control surface blocking angle of each control surface determined in the step 2 and the flight test experimental project determined in the step 4 by adopting the flight test device for the control surface blocking of the electric transport aircraft, and obtaining a flight test result according to the evaluation index in the step 3.
4. The method for controlling surface blocking test flight of a fly-by-wire aircraft according to claim 3, wherein in the step 1, the specific process of determining the test flight status point comprises: the control surface blocking flying test method comprises the steps of firstly determining the information of the control surface blocking flying test configuration, weight and gravity center elements according to the criticality analysis, ensuring the flying test working condition to be in a relatively harshest state, and taking the front gravity center, the maximum landing weight and the cruising and landing configuration as control surface blocking flying test state points.
5. A method of fly-by-wire aircraft control surface drag test according to claim 3, wherein in step 2 the aircraft control surface comprises an elevator, an aileron, and a rudder.
6. The method for fly-by-wire aircraft control surface drag test according to claim 5, wherein in the step 2, the determining of the maximum control surface drag angle of the elevator comprises: The maximum control surface blocking angle is larger in the first aspect that the aircraft achieves stable normal overload in the speed range from 1.23V SR1 or 1.3V S to V MO /M MO or V FE , the overload range is 0.8 g-1.3 g, the elevator deflection corresponding to the required longitudinal operation position is achieved, and in the second aspect, the stability enhancement system or other automatic systems of the aircraft is elevator deflection corresponding to the longitudinal operation position peak required for resisting 15fps (feet per second) of atmospheric discrete vertical gusts in the height range from sea level to 20000 ft.
7. The method of claim 5, wherein in step 2, the maximum control surface locking angle of the aileron is determined by the position of the aileron required to maintain a steady roll rate of 12 °/s in the speed range of 1.23V SR1 or 1.3V S to V MO /M MO or V FE , but not more than 50% of the maximum lateral steering input.
8. The method according to claim 5, wherein in the step 2, the maximum drag angle of the rudder is larger than that of the rudder corresponding to a maximum rudder deflection required to maintain a yaw trim in a speed range from 1.23V SR1 or 1.3V S to a maximum full operational speed achieved by flying at a climb power level, but not exceeding V MO /M MO or V FE , and that of the rudder corresponding to a peak heading manipulation position required by an augmentation system or other automatic system of the aircraft to resist 15fps of atmospheric discrete vertical gusts.
9. The method for fly-by-wire aircraft control surface drag test according to claim 5, wherein in the step 4, the fly-by-wire evaluation index comprises: 1) Stabilizing 30-degree slope turning to the left or right; 2) From a steady 30 degree grade turn, rolling 60 degrees in no more than 11 seconds to reverse the direction of the turn; 3) The push rod is moved to 0.8g and the pull rod is moved to 1.3g; 4) The wing in the 90 degree crosswind up to 10kn lands horizontally flat.
10. The method for fly-by-wire transport aircraft control surface blocking according to claim 5, wherein in step 4, the specific contents of the fly-by-wire test items include: Aiming at the blocking of the longitudinal control surface, after the blocking state is set, the balancing plane keeps stable and flat flying, and 1.3g overload and 0.8 overload are intercepted and captured by a longitudinal push-pull rod in a maneuvering way, and the balancing plane is stable on an overload step for 1-3 s; aiming at the longitudinal control surface blocking, after a blocking state is set, the balancing plane keeps stable flat flight, and the plane is controlled to simulate the downslide landing; Aiming at the transverse control surface blocking, after a blocking state is set, the balancing plane keeps stable flat flight, the plane is controlled to establish a 30-degree gradient stable spiral 10s at one side, rolling maneuver is carried out to the 30-degree gradient at the other side through transverse step, and after the target gradient is reached, the stable spiral 10s is kept under the gradient; Aiming at the transverse control surface blocking, after a blocking state is set, the balancing plane keeps stable flat flight, and the plane is controlled to simulate downslide landing; Aiming at the jamming of the heading control surface, after the jamming state is set, the balancing plane keeps stable and flat flying, the plane is controlled to establish a 30-degree gradient stable spiral 10s at one side, rolling maneuver is carried out to the 30-degree gradient at the other side through transverse step, and after the target gradient is reached, the stable spiral 10s is kept under the gradient; aiming at the jamming of the heading control surface, after the jamming state is set, the balancing plane keeps stable and flat flight, and the plane is controlled to simulate the downslide landing.

Description

Fly-through testing device and method for control surface blocking of fly-through transport aircraft Technical Field The invention belongs to the field of flight test, and particularly relates to a fly test device and a fly test method for a fly-by-wire transport type aircraft control surface card, which are suitable for fly test of fly-by-wire transport type aircraft control surface card. Background The control surface blocking test flight is one of the most important test flight subjects in the model test flight of the transport aircraft, and is an important means for checking whether the aircraft has the capability of continuing to safely aircraft and land in a typical fault state. The method has important significance for safely and stably developing continuous navigable flying, and is closely concerned by all stakeholders. The flight quality and the control capability of the fly-by-wire transport type aircraft in the control surface blocking state determine the tolerance of the aircraft to the control surface blocking fault, and meanwhile, the residual safety margin of the fly-by-wire transport type aircraft in the control surface blocking state can be also embodied. Therefore, by developing the control surface blocking flight test, the control quality characteristics and the residual control capacity of the fly-by-fly transport aircraft in the control surface blocking state are checked, and the fly-by-fly transport aircraft is an important guarantee for safe operation of the fly-by-fly transport aircraft. Disclosure of Invention The invention aims to provide a device and a method for preventing a control surface of an electric transport type aircraft from blocking and testing flight, which are significant for reasonably planning a flight test process, avoiding the flight test risk and improving the flight test efficiency. The technical scheme of the invention is as follows: In order to achieve the above object, according to a first aspect of the present invention, an electric transport type aircraft control surface blocking and flight testing device is provided, which includes a main flight control module, an actuator controller, and a cockpit control panel, wherein the main flight control module stores a control surface blocking program, and realizes the instruction input of the control surface blocking program through the cockpit control panel, and when the main flight control module receives a control surface blocking instruction from the cockpit control panel, the control instruction loop of the control lever-main flight control module-actuator controller is interrupted, and the control instruction at the interruption moment is frozen, and the control instruction loop of the blocked control surface is changed into the control instruction loop of the cockpit control panel-main flight control module-actuator controller. In one possible embodiment, the control surface deviation value is input through a numeric keyboard on the control panel of the cockpit, and the difference value is superimposed on the jammed control surface, so as to realize the adjustment of the control surface jamming deviation. According to a second aspect of the present invention, a fly-by-wire transportation type aircraft control surface blocking test method is provided, and the fly-by-wire transportation type aircraft control surface blocking test device is adopted, and the method comprises: Step 1, determining a test flight state point according to control surface jamming criticality analysis; Step 2, determining the maximum control surface blocking angle of each control surface of the aircraft according to the airworthiness regulation requirement of the corresponding model; Step 3, determining control surface blocking test flight evaluation indexes according to the airworthiness regulation requirements of corresponding models; step 4, determining a test flight test item according to the evaluation index determined in the step 3; and 5, carrying out a flight test according to the flight test state point determined in the step 1, the maximum control surface blocking angle of each control surface determined in the step 2 and the flight test experimental project determined in the step 4 by adopting the flight test device for the control surface blocking of the electric transport aircraft, and obtaining a flight test result according to the evaluation index in the step 3. In one possible embodiment, in the step 1, the specific process of determining the test flight status point includes: The control surface blocking flying test method comprises the steps of firstly determining the information of the control surface blocking flying test configuration, weight and gravity center elements according to the criticality analysis, ensuring the flying test working condition to be in a relatively harshest state, and taking the front gravity center, the maximum landing weight and the cruising and landing configuration as control surface blo