CN113955144B - Fatigue test loading and unloading protection method for aircraft main control system - Google Patents
Fatigue test loading and unloading protection method for aircraft main control system Download PDFInfo
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- CN113955144B CN113955144B CN202111087363.XA CN202111087363A CN113955144B CN 113955144 B CN113955144 B CN 113955144B CN 202111087363 A CN202111087363 A CN 202111087363A CN 113955144 B CN113955144 B CN 113955144B
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- 238000009661 fatigue test Methods 0.000 title claims abstract description 30
- 238000001228 spectrum Methods 0.000 claims abstract description 123
- 238000006073 displacement reaction Methods 0.000 claims abstract description 85
- 238000012544 monitoring process Methods 0.000 claims abstract description 65
- 230000003068 static effect Effects 0.000 claims abstract description 48
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
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Abstract
The application belongs to the technical field of fatigue tests of aircraft main control systems, and particularly relates to a method for loading and unloading fatigue tests of an aircraft main control system, which comprises the following steps: when the dynamic fatigue spectrum load is applied to the main control system of the aircraft, the control displacement is used as a control quantity, and the control load is used as a monitoring quantity; applying dynamic fatigue spectrum load to the main control system of the airplane, gradually reducing the control displacement control quantity when the load exceeds the limit, and canceling the control displacement control instruction after the control displacement control quantity returns to the zero position; when static fatigue spectrum load is applied to the main control system of the aircraft, the control displacement is used as a monitoring quantity, and the control load is used as a control quantity; and (3) applying static fatigue spectrum load to the main control system of the aircraft, gradually reducing the control load control quantity when the load exceeds the limit, and canceling the control load control instruction after the control displacement monitoring quantity returns to the zero position.
Description
Technical Field
The application belongs to the technical field of fatigue tests of aircraft main control systems, and particularly relates to a method for loading and unloading protection of an aircraft main control system.
Background
The method is characterized in that an aircraft control load and control displacement coordinated loading spectrum is applied to an aircraft main control system, fatigue control loading is carried out on the aircraft main control system, and fatigue test of the aircraft main control system is carried out, so that the method is an important means for checking the fatigue life and performance index of the aircraft main control system.
The airplane control load and control displacement coordination loading spectrum comprises dynamic fatigue spectrum load, left pedal and right pedal double-foot brake spectrum load and static fatigue spectrum load.
The dynamic fatigue spectrum load comprises a one-way control spectrum load and a composite control spectrum load, wherein the one-way control spectrum load comprises an aileron one-way control spectrum load loaded by left deflection/right deflection of an aileron steering rod, a horizontal tail one-way control spectrum load loaded by forward pushing/backward pulling of a horizontal tail steering rod and a rudder one-way control spectrum load loaded by forward pushing/backward pulling of a left pedal and a right pedal; the composite operating spectrum load is the combination of two or three of the aileron unidirectional operating spectrum load, the horizontal tail unidirectional operating spectrum load and the rudder unidirectional operating spectrum load.
The left pedal and the right pedal are used for simultaneously loading the pedal spectrum load forwards through the left pedal and the right pedal.
The static fatigue spectrum load comprises a one-way operation spectrum load and a composite operation spectrum load, wherein the one-way operation spectrum load comprises an aileron one-way operation spectrum load loaded by left deflection/right deflection of an aileron steering rod, a horizontal tail one-way operation spectrum load loaded by forward pushing/backward pulling of a horizontal tail steering rod and a rudder one-way operation spectrum load loaded by forward pushing/backward pulling of a left pedal and a right pedal; the composite operating spectrum load is the combination of two or three of the aileron unidirectional operating spectrum load, the horizontal tail unidirectional operating spectrum load and the rudder unidirectional operating spectrum load.
At present, when the fatigue test of the main control system of the aircraft is carried out, accurate and efficient fatigue control loading of the main control system of the aircraft is difficult to ensure, and when the loading is over-limit, the loading actuator cylinder is subjected to unloading protection in an emergency pressure breaking mode, the unloading protection in the mode can generate impact load with far-exceeding load spectrum variation amplitude, so that the main control system of the aircraft is subjected to excessive fatigue assessment, the reliability of test results is influenced, and even the whole main control system of the aircraft is damaged, even dangerous accidents occur.
The present application has been made in view of the above-described technical drawbacks.
It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present application, which is not necessarily prior art to the present patent application, and should not be used for evaluating the novelty and creativity of the present application in the case where no clear evidence indicates that the above content has been disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide a method for protecting the fatigue test loading and unloading of a main operating system of an aircraft, which overcomes or alleviates at least one of the technical drawbacks known in the prior art.
The technical scheme of the application is as follows:
A fatigue test loading and unloading protection method for an aircraft main control system comprises the following steps:
when the dynamic fatigue spectrum load is applied to the main control system of the aircraft, the control displacement is used as a control quantity, and the control load is used as a monitoring quantity;
Applying dynamic fatigue spectrum load to the main control system of the airplane, gradually reducing the control displacement control quantity when the load exceeds the limit, and canceling the control displacement control instruction after the control displacement control quantity returns to the zero position;
when static fatigue spectrum load is applied to the main control system of the aircraft, the control displacement is used as a monitoring quantity, and the control load is used as a control quantity;
And (3) applying static fatigue spectrum load to the main control system of the aircraft, gradually reducing the control load control quantity when the load exceeds the limit, and canceling the control load control instruction after the control displacement monitoring quantity returns to the zero position.
According to at least one embodiment of the present application, in the method for protecting fatigue test loading and unloading of an aircraft main control system, when a dynamic fatigue spectrum load is applied to the aircraft main control system, the method uses a control displacement as a control quantity and a control load as a monitoring quantity, and includes:
When the dynamic fatigue spectrum load of the unidirectional aileron manipulation is applied to the main airplane manipulation system, the loading of the left deviation/right deviation of the aileron steering column is position control and force monitoring;
When the horizontal tail unidirectional operation dynamic fatigue spectrum load is applied to the main control system of the airplane, the loading of forward pushing/backward pulling of the horizontal tail steering column is position control and force monitoring;
when rudder unidirectional operation dynamic fatigue spectrum load is applied to the aircraft main operation system, the left pedal and the right pedal are independently loaded forwards as position control and force monitoring;
The method for applying dynamic fatigue spectrum load to the main control system of the airplane, when the load exceeds the limit, gradually reducing the control displacement control quantity, and after the control displacement control quantity returns to a zero position, canceling the control displacement control instruction comprises the following steps:
Applying an aileron unidirectional operation dynamic fatigue spectrum load to an aircraft main operation system, gradually reducing the position control of an aileron steering column when the loading exceeds the limit, and canceling a position control instruction after the aileron steering column returns to a zero position;
Applying horizontal-tail unidirectional operation dynamic fatigue spectrum load to the main control system of the airplane, gradually reducing the position control of a horizontal-tail steering rod when the loading exceeds the limit, and canceling a position control instruction after the horizontal-tail steering rod returns to a zero position;
the rudder unidirectional operation dynamic fatigue spectrum load is applied to the main control system of the aircraft, the position control of the left pedal/right pedal is lowered step by step when the loading exceeds the limit, and after the left pedal/right pedal returns to the zero position, the position control instruction is cancelled.
According to at least one embodiment of the present application, in the method for protecting fatigue test loading and unloading of an aircraft main control system, when a dynamic fatigue spectrum load is applied to the aircraft main control system, the method uses a control displacement as a control quantity and a control load as a monitoring quantity, and includes:
when an aileron/horizontal tail/rudder compound operation dynamic fatigue spectrum load is applied to an aircraft main control system, the left offset/right offset of an aileron steering column, the forward pushing/backward pulling of the horizontal tail steering column, the forward loading of a left pedal and a right pedal are respectively carried out as position control and force monitoring;
The method for applying dynamic fatigue spectrum load to the main control system of the airplane, when the load exceeds the limit, gradually reducing the control displacement control quantity, and after the control displacement control quantity returns to a zero position, canceling the control displacement control instruction comprises the following steps:
and applying an aileron/horizontal tail/rudder compound operation dynamic fatigue spectrum load to the aircraft main operation system, gradually reducing the position control of an aileron steering column, a horizontal tail steering column and a left pedal/right pedal when the loading exceeds the limit, and canceling a position control instruction after the aileron steering column, the horizontal tail steering column and the left pedal/right pedal return to zero positions.
According to at least one embodiment of the present application, in the method for protecting fatigue test loading and unloading of an aircraft main control system, when a static fatigue spectrum load is applied to the aircraft main control system, the method uses a control displacement as a monitoring quantity and a control load as a control quantity, and includes:
When the static fatigue spectrum load of the unidirectional aileron manipulation is applied to the main manipulation system of the aircraft, the left deflection/right deflection of the aileron steering column is loaded for force control and displacement monitoring;
when the horizontal tail unidirectional control static fatigue spectrum load is applied to the main control system of the airplane, the forward pushing/backward pulling load of the horizontal tail steering column is force control and displacement monitoring;
When a rudder unidirectional operation static fatigue spectrum load is applied to an aircraft main control system, the left pedal and the right pedal are independently loaded forwards, and the force control and displacement monitoring are carried out;
applying static fatigue spectrum load to the main control system of the airplane, gradually reducing control load control quantity when the load exceeds the limit, and canceling control load control instructions after the control displacement monitoring quantity returns to a zero position, wherein the method comprises the following steps:
applying an aileron unidirectional operation static fatigue spectrum load to an aircraft main control system, gradually reducing the force control of an aileron steering column when the load exceeds the limit, and canceling a force control instruction after the aileron steering column returns to a zero position;
applying a horizontal tail unidirectional operation static fatigue spectrum load to the main control system of the airplane, gradually reducing the force control of a horizontal tail driving rod when the loading exceeds the limit, and canceling a force control instruction after the auxiliary horizontal tail driving rod returns to a zero position;
and applying rudder unidirectional operation static fatigue spectrum load to the aircraft main control system, gradually reducing force control of the left pedal/right pedal when the load exceeds the limit, and canceling a force control instruction after the left pedal/right pedal returns to the zero position.
According to at least one embodiment of the present application, in the method for protecting fatigue test loading and unloading of an aircraft main control system, when a static fatigue spectrum load is applied to the aircraft main control system, the method uses a control displacement as a monitoring quantity and a control load as a control quantity, and includes:
When an aileron/horizontal tail/rudder compound control static fatigue spectrum load is applied to an aircraft main control system, the left offset/right offset of an aileron steering column, the forward pushing/backward pulling of the horizontal tail steering column, the forward loading of a left pedal and a right pedal are respectively controlled by force and displacement monitoring;
The method for applying static fatigue spectrum load to the aircraft main control system, when the load exceeds the limit, gradually reducing the control load control quantity, and after the control displacement monitoring quantity returns to the zero position, canceling the control load control instruction comprises the following steps:
And applying an aileron/horizontal tail/rudder composite control static fatigue spectrum load to the aircraft main control system, gradually reducing the force control of an aileron steering column, a horizontal tail steering column and a left pedal/right pedal when the loading exceeds the limit, and canceling a force control instruction after the aileron steering column, the horizontal tail steering column and the left pedal/right pedal return to zero positions.
According to at least one embodiment of the present application, in the method for protecting fatigue test loading and unloading of the main control system of an aircraft, the method further comprises:
when the left pedal and the right pedal are applied to the main control system of the airplane, the loading of the left pedal is position control and force monitoring, and the loading of the right pedal is force control and displacement monitoring;
and when the load exceeds the limit, the force control of the right pedal is gradually reduced, the position control of the left pedal is maintained, the operating force of the left pedal is reduced, the left pedal and the right pedal return to zero positions, and the position control and force control instructions are cancelled.
Drawings
FIG. 1 is a schematic diagram of a method for protecting fatigue test loading and unloading of an aircraft main control system according to an embodiment of the present application.
For the purpose of better illustrating the embodiments, certain elements of the drawings may be omitted, enlarged or reduced and do not represent the actual product dimensions; further, the drawings are for illustrative purposes, wherein the terms describing the positional relationship are limited to the illustrative description only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solution of the present application and its advantages more clear, the technical solution of the present application will be further and completely described in detail with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application and not for limitation of the present application. It should be noted that, for convenience of description, only the part related to the present application is shown in the drawings, and other related parts may refer to the general design, and the embodiments of the present application and the technical features of the embodiments may be combined with each other to obtain new embodiments without conflict.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of the application should be given the ordinary meaning as understood by one of ordinary skill in the art to which the application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in the description of the present application are merely used for indicating relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and that the relative positional relationships may be changed when the absolute position of the object to be described is changed, thus not being construed as limiting the application. The terms "first," "second," "third," and the like, as used in the description of the present application, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the application are not to be construed as limiting the amount absolutely, but rather as existence of at least one. As used in this description of the application, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term as such, but does not exclude other elements or articles from the list of elements or articles that appear after the term.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description of the present application are used in a broad sense, and for example, the connection may be a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
The application is described in further detail below with reference to fig. 1.
A fatigue test loading and unloading protection method for an aircraft main control system comprises the following steps:
when the dynamic fatigue spectrum load is applied to the main control system of the aircraft, the control displacement is used as a control quantity, and the control load is used as a monitoring quantity;
Applying dynamic fatigue spectrum load to the main control system of the airplane, gradually reducing the control displacement control quantity when the load exceeds the limit, and canceling the control displacement control instruction after the control displacement control quantity returns to the zero position;
when static fatigue spectrum load is applied to the main control system of the aircraft, the control displacement is used as a monitoring quantity, and the control load is used as a control quantity;
And (3) applying static fatigue spectrum load to the main control system of the aircraft, gradually reducing the control load control quantity when the load exceeds the limit, and canceling the control load control instruction after the control displacement monitoring quantity returns to the zero position.
For the fatigue test loading and unloading protection method of the main control system of the aircraft disclosed in the above embodiment, it can be understood by those skilled in the art that when the dynamic fatigue spectrum load is applied to the main control system of the aircraft, the control displacement is used as a control amount, the control load is used as a monitoring amount, and when the static fatigue spectrum load is applied to the main control system of the aircraft, the control displacement is used as a monitoring amount, the control load is used as a control amount, so as to ensure the accurate and efficient fatigue control loading to the main control system of the aircraft.
As for the fatigue test loading and unloading protection method of the aircraft main control system disclosed in the above embodiment, it can be further understood by those skilled in the art that the design is that when the dynamic fatigue spectrum load is applied to the aircraft main control system and the loading is over-limited, the control displacement control amount is gradually reduced, that is, the control displacement control amount is gradually reduced, after the control displacement control amount returns to the zero position, the control displacement control instruction is cancelled, and when the static fatigue spectrum load is applied to the aircraft main control system and the loading is over-limited, the control load control amount is gradually reduced, that is, the control load control instruction is cancelled after the control displacement monitoring amount returns to the zero position, so as to avoid generating larger impact control load.
In some optional embodiments, in the method for protecting fatigue test loading and unloading of an aircraft main control system, when the dynamic fatigue spectrum load is applied to the aircraft main control system, the controlling displacement is used as a control quantity, and the controlling load is used as a monitoring quantity, including:
When the dynamic fatigue spectrum load of the unidirectional aileron manipulation is applied to the main airplane manipulation system, the loading of the left deviation/right deviation of the aileron steering column is position control and force monitoring;
When the horizontal tail unidirectional operation dynamic fatigue spectrum load is applied to the main control system of the airplane, the loading of forward pushing/backward pulling of the horizontal tail steering column is position control and force monitoring;
when rudder unidirectional operation dynamic fatigue spectrum load is applied to the aircraft main operation system, the left pedal and the right pedal are independently loaded forwards as position control and force monitoring;
The method for applying dynamic fatigue spectrum load to the main control system of the airplane, when the load exceeds the limit, gradually reducing the control displacement control quantity, and after the control displacement control quantity returns to a zero position, canceling the control displacement control instruction comprises the following steps:
Applying an aileron unidirectional operation dynamic fatigue spectrum load to an aircraft main operation system, gradually reducing the position control of an aileron steering column when the loading exceeds the limit, and canceling a position control instruction after the aileron steering column returns to a zero position;
Applying horizontal-tail unidirectional operation dynamic fatigue spectrum load to the main control system of the airplane, gradually reducing the position control of a horizontal-tail steering rod when the loading exceeds the limit, and canceling a position control instruction after the horizontal-tail steering rod returns to a zero position;
the rudder unidirectional operation dynamic fatigue spectrum load is applied to the main control system of the aircraft, the position control of the left pedal/right pedal is lowered step by step when the loading exceeds the limit, and after the left pedal/right pedal returns to the zero position, the position control instruction is cancelled.
In some optional embodiments, in the method for protecting fatigue test loading and unloading of an aircraft main control system, when the dynamic fatigue spectrum load is applied to the aircraft main control system, the controlling displacement is used as a control quantity, and the controlling load is used as a monitoring quantity, including:
when an aileron/horizontal tail/rudder compound operation dynamic fatigue spectrum load is applied to an aircraft main control system, the left offset/right offset of an aileron steering column, the forward pushing/backward pulling of the horizontal tail steering column, the forward loading of a left pedal and a right pedal are respectively carried out as position control and force monitoring;
The method for applying dynamic fatigue spectrum load to the main control system of the airplane, when the load exceeds the limit, gradually reducing the control displacement control quantity, and after the control displacement control quantity returns to a zero position, canceling the control displacement control instruction comprises the following steps:
and applying an aileron/horizontal tail/rudder compound operation dynamic fatigue spectrum load to the aircraft main operation system, gradually reducing the position control of an aileron steering column, a horizontal tail steering column and a left pedal/right pedal when the loading exceeds the limit, and canceling a position control instruction after the aileron steering column, the horizontal tail steering column and the left pedal/right pedal return to zero positions.
In some optional embodiments, in the method for protecting fatigue test loading and unloading of an aircraft main control system, when the static fatigue spectrum load is applied to the aircraft main control system, the method uses the control displacement as a monitoring quantity and the control load as a control quantity, and includes:
When the static fatigue spectrum load of the unidirectional aileron manipulation is applied to the main manipulation system of the aircraft, the left deflection/right deflection of the aileron steering column is loaded for force control and displacement monitoring;
when the horizontal tail unidirectional control static fatigue spectrum load is applied to the main control system of the airplane, the forward pushing/backward pulling load of the horizontal tail steering column is force control and displacement monitoring;
When a rudder unidirectional operation static fatigue spectrum load is applied to an aircraft main control system, the left pedal and the right pedal are independently loaded forwards, and the force control and displacement monitoring are carried out;
applying static fatigue spectrum load to the main control system of the airplane, gradually reducing control load control quantity when the load exceeds the limit, and canceling control load control instructions after the control displacement monitoring quantity returns to a zero position, wherein the method comprises the following steps:
applying an aileron unidirectional operation static fatigue spectrum load to an aircraft main control system, gradually reducing the force control of an aileron steering column when the load exceeds the limit, and canceling a force control instruction after the aileron steering column returns to a zero position;
applying a horizontal tail unidirectional operation static fatigue spectrum load to the aircraft main control system, gradually reducing the force control of a horizontal tail steering rod when the loading exceeds the limit, and canceling a force control instruction after the horizontal tail steering rod returns to a zero position;
and applying rudder unidirectional operation static fatigue spectrum load to the aircraft main control system, gradually reducing force control of the left pedal/right pedal when the load exceeds the limit, and canceling a force control instruction after the left pedal/right pedal returns to the zero position.
In some optional embodiments, in the method for protecting fatigue test loading and unloading of an aircraft main control system, when the static fatigue spectrum load is applied to the aircraft main control system, the method uses the control displacement as a monitoring quantity and the control load as a control quantity, and includes:
When an aileron/horizontal tail/rudder compound control static fatigue spectrum load is applied to an aircraft main control system, the left offset/right offset of an aileron steering column, the forward pushing/backward pulling of the horizontal tail steering column, the forward loading of a left pedal and a right pedal are respectively controlled by force and displacement monitoring;
The method for applying static fatigue spectrum load to the aircraft main control system, when the load exceeds the limit, gradually reducing the control load control quantity, and after the control displacement monitoring quantity returns to the zero position, canceling the control load control instruction comprises the following steps:
And applying an aileron/horizontal tail/rudder composite control static fatigue spectrum load to the aircraft main control system, gradually reducing the force control of an aileron steering column, a horizontal tail steering column and a left pedal/right pedal when the loading exceeds the limit, and canceling a force control instruction after the aileron steering column, the horizontal tail steering column and the left pedal/right pedal return to zero positions.
In some optional embodiments, the method for protecting fatigue test loading and unloading of the main control system of the aircraft further comprises:
when the left pedal and the right pedal are applied to the main control system of the airplane, the loading of the left pedal is position control and force monitoring, and the loading of the right pedal is force control and displacement monitoring;
And when the load exceeds the limit, the force control of the right pedal is gradually reduced, the operating force of the left pedal is reduced, the left pedal and the right pedal return to zero positions, and the position control and force control instructions are canceled.
For the fatigue test loading and unloading protection method of the main control system of the aircraft disclosed in the above embodiment, those skilled in the art can understand that when the left pedal and the right pedal are applied with the brake spectrum load of the left pedal and the right pedal, the loading of the left pedal is position control and force monitoring, and the loading of the right pedal is force control and displacement monitoring, so that the situation that the left pedal and the right pedal step back and forth is avoided, and the accurate and efficient fatigue control loading of the main control system of the aircraft is ensured.
As for the fatigue test loading and unloading protection method of the main control system of the aircraft disclosed in the above embodiment, those skilled in the art can also understand that the design is that when the dynamic fatigue spectrum load is applied to the main control system of the aircraft, the force control of the right pedal is gradually reduced, and the control force of the left pedal is reduced, namely, the force control of the right pedal is slowly reduced in a grading manner, and the control force of the left pedal is slowly reduced gradually, so that the left pedal and the right pedal return to zero positions, and the position control and the force control instruction are cancelled, thereby avoiding generating larger impact load.
In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described by the differences from other embodiments, so that the same similar parts among the embodiments are mutually referred.
Having thus described the technical aspects of the present application with reference to the preferred embodiments shown in the drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the related technical features without departing from the principle of the present application, and those changes or substitutions will fall within the scope of the present application.
Claims (5)
1. The method for protecting the fatigue test loading and unloading of the main control system of the aircraft is characterized by comprising the following steps of:
when the dynamic fatigue spectrum load is applied to the main control system of the aircraft, the control displacement is used as a control quantity, and the control load is used as a monitoring quantity;
Applying dynamic fatigue spectrum load to the main control system of the airplane, gradually reducing the control displacement control quantity when the load exceeds the limit, and canceling the control displacement control instruction after the control displacement control quantity returns to the zero position;
when static fatigue spectrum load is applied to the main control system of the aircraft, the control displacement is used as a monitoring quantity, and the control load is used as a control quantity;
applying static fatigue spectrum load to the main control system of the aircraft, gradually reducing the control load control quantity when the load exceeds the limit, and canceling the control load control instruction after the control displacement monitoring quantity returns to the zero position;
when the dynamic fatigue spectrum load is applied to the main control system of the airplane, the control displacement is used as a control quantity, the control load is used as a monitoring quantity, and the method comprises the following steps:
When the dynamic fatigue spectrum load of the unidirectional aileron manipulation is applied to the main airplane manipulation system, the loading of the left deviation/right deviation of the aileron steering column is position control and force monitoring;
When the horizontal tail unidirectional operation dynamic fatigue spectrum load is applied to the main control system of the airplane, the loading of forward pushing/backward pulling of the horizontal tail steering column is position control and force monitoring;
when rudder unidirectional operation dynamic fatigue spectrum load is applied to the aircraft main operation system, the left pedal and the right pedal are independently loaded forwards as position control and force monitoring;
The method for applying dynamic fatigue spectrum load to the main control system of the airplane, when the load exceeds the limit, gradually reducing the control displacement control quantity, and after the control displacement control quantity returns to a zero position, canceling the control displacement control instruction comprises the following steps:
Applying an aileron unidirectional operation dynamic fatigue spectrum load to an aircraft main operation system, gradually reducing the position control of an aileron steering column when the loading exceeds the limit, and canceling a position control instruction after the aileron steering column returns to a zero position;
Applying horizontal-tail unidirectional operation dynamic fatigue spectrum load to the main control system of the airplane, gradually reducing the position control of a horizontal-tail steering rod when the loading exceeds the limit, and canceling a position control instruction after the horizontal-tail steering rod returns to a zero position;
the rudder unidirectional operation dynamic fatigue spectrum load is applied to the main control system of the aircraft, the position control of the left pedal/right pedal is lowered step by step when the loading exceeds the limit, and after the left pedal/right pedal returns to the zero position, the position control instruction is cancelled.
2. The method for protecting fatigue test loading and unloading of main control system of airplane according to claim 1, wherein,
When the dynamic fatigue spectrum load is applied to the main control system of the airplane, the control displacement is used as a control quantity, the control load is used as a monitoring quantity, and the method comprises the following steps:
when an aileron/horizontal tail/rudder compound operation dynamic fatigue spectrum load is applied to an aircraft main control system, the left offset/right offset of an aileron steering column, the forward pushing/backward pulling of the horizontal tail steering column, the forward loading of a left pedal and a right pedal are respectively carried out as position control and force monitoring;
The method for applying dynamic fatigue spectrum load to the main control system of the airplane, when the load exceeds the limit, gradually reducing the control displacement control quantity, and after the control displacement control quantity returns to a zero position, canceling the control displacement control instruction comprises the following steps:
and applying an aileron/horizontal tail/rudder compound operation dynamic fatigue spectrum load to the aircraft main operation system, gradually reducing the position control of an aileron steering column, a horizontal tail steering column and a left pedal/right pedal when the loading exceeds the limit, and canceling a position control instruction after the aileron steering column, the horizontal tail steering column and the left pedal/right pedal return to zero positions.
3. The method for protecting fatigue test loading and unloading of main control system of airplane according to claim 1, wherein,
When the static fatigue spectrum load is applied to the main control system of the airplane, the control displacement is taken as a monitoring quantity, the control load is taken as a control quantity, and the method comprises the following steps:
When the static fatigue spectrum load of the unidirectional aileron manipulation is applied to the main manipulation system of the aircraft, the left deflection/right deflection of the aileron steering column is loaded for force control and displacement monitoring;
when the horizontal tail unidirectional control static fatigue spectrum load is applied to the main control system of the airplane, the forward pushing/backward pulling load of the horizontal tail steering column is force control and displacement monitoring;
When a rudder unidirectional operation static fatigue spectrum load is applied to an aircraft main control system, the left pedal and the right pedal are independently loaded forwards, and the force control and displacement monitoring are carried out;
applying static fatigue spectrum load to the main control system of the airplane, gradually reducing control load control quantity when the load exceeds the limit, and canceling control load control instructions after the control displacement monitoring quantity returns to a zero position, wherein the method comprises the following steps:
applying an aileron unidirectional operation static fatigue spectrum load to an aircraft main control system, gradually reducing the force control of an aileron steering column when the load exceeds the limit, and canceling a force control instruction after the aileron steering column returns to a zero position;
applying a horizontal tail unidirectional operation static fatigue spectrum load to the aircraft main control system, gradually reducing the force control of a horizontal tail steering rod when the loading exceeds the limit, and canceling a force control instruction after the horizontal tail steering rod returns to a zero position;
And applying rudder unidirectional operation static fatigue spectrum load to the aircraft main control system, gradually reducing force control of the left pedal/right pedal when the loading exceeds the limit, and canceling a force control instruction after the left pedal/right pedal steering rod returns to the zero position.
4. The method for protecting fatigue test loading and unloading of main control system of airplane according to claim 1, wherein,
When the static fatigue spectrum load is applied to the main control system of the airplane, the control displacement is taken as a monitoring quantity, the control load is taken as a control quantity, and the method comprises the following steps:
When an aileron/horizontal tail/rudder compound control static fatigue spectrum load is applied to an aircraft main control system, the left offset/right offset of an aileron steering column, the forward pushing/backward pulling of the horizontal tail steering column, the forward loading of a left pedal and a right pedal are respectively controlled by force and displacement monitoring;
The method for applying static fatigue spectrum load to the aircraft main control system, when the load exceeds the limit, gradually reducing the control load control quantity, and after the control displacement monitoring quantity returns to the zero position, canceling the control load control instruction comprises the following steps:
And applying an aileron/horizontal tail/rudder composite control static fatigue spectrum load to the aircraft main control system, gradually reducing the force control of an aileron steering column, a horizontal tail steering column and a left pedal/right pedal when the loading exceeds the limit, and canceling a force control instruction after the aileron steering column, the horizontal tail steering column and the left pedal/right pedal return to zero positions.
5. The method for protecting fatigue test loading and unloading of main control system of airplane according to claim 1, wherein,
Further comprises:
when the left pedal and the right pedal are applied to the main control system of the airplane, the loading of the left pedal is position control and force monitoring, and the loading of the right pedal is force control and displacement monitoring;
and when the load exceeds the limit, the force control of the right pedal is gradually reduced, the position control of the left pedal is maintained, the operating force of the left pedal is reduced, the left pedal and the right pedal return to zero positions, and the position control and force control instructions are cancelled.
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