Performance tester for automatic control device of force arm of airplane

Abstract

The utility model relates to a performance tester for an automatic control device of an airplane force arm, which comprises the components of a rectifying circuit which has an input end connected with an alternating-current power supply and an output end connected with a force arm regulator through a first switch and is used for converting alternating-current voltage into direct-current voltage and supplying power to the force arm regulator; the first push type switch is connected in series between the first switch and the first port of the force arm regulator; the second push type switch is connected in series between the first switch and the second port of the force arm regulator; the signal output end of the force arm position indicator is connected to the force arm adjuster, and the force arm position indicator is used for collecting the stretching length of the force arm, displaying the stretching length and sending the collected length data to the force arm adjuster; a force arm adjuster controlling a force arm connected to the aircraft; the control is connected to the large arm signal lamp. The performance tester for the automatic control device of the force arm of the airplane has the advantages of simple structure, small volume and good portability.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft lever arm regulator performance testing, and more specifically, to an aircraft lever arm automatic control device performance tester. Background Art

[0002] The aircraft's control system is a crucial, core component of the entire aircraft. Its proper functioning directly impacts aircraft safety, enabling the aircraft to ascend or descend during flight. The lever arm automatic adjuster is a crucial component of the aircraft's control system. It automatically adjusts the length of the aircraft's lever arm, thereby improving the longitudinal control quality of supersonic aircraft. Based on changes in the aircraft's apparent airspeed and altitude, the lever arm length is adjusted according to a specific pattern, thereby adjusting the transmission ratios from the control stick to the horizontal stabilizer and from the control stick to the load sensor. This ensures excellent longitudinal control performance while satisfying the pilot's control preferences. Therefore, its proper functioning directly impacts flight safety.

[0003] The automatic adjustment device of the lever arm usually includes a lever arm adjustment machine and a lever arm control box connected to the lever arm adjustment machine; the lever arm adjuster is used to increase or decrease the length of the lever arm according to a preset step size based on the instructions issued by the lever arm control box; the lever arm adjuster is provided with a first port and a second port, both of which are connected to the lever arm control box, and when the first port receives a voltage signal, the length of the lever arm is shortened according to the preset step size; when the first port receives a voltage signal, the length of the lever arm is extended according to the preset step size. The lever arm control box is used to automatically send control signals to the lever arm regulator according to the aircraft's flight altitude and flight speed, thereby controlling the aircraft's lever arm extension length, making the aircraft's flight state more stable and safe; the lever arm control box is usually provided with a dynamic pressure interface and a static pressure interface, wherein the dynamic pressure interface is used to collect the dynamic pressure of the aircraft during flight; the static pressure interface is used to collect the static pressure of the aircraft during flight; the lever arm control box detects the dynamic pressure data of the dynamic pressure interface and the static pressure data of the static pressure interface, and calculates the aircraft's flight speed and flight altitude, and sends instructions to the lever arm regulator based on the flight speed and flight altitude to control the aircraft's lever arm length.

[0004] In the prior art, the performance of automatic lever adjustment devices is typically tested using lever arm device testing equipment. Currently, there are two main types of lever arm device testing equipment on the market: manual and electric. Manual types are largely obsolete, while electric types vary widely. Electric types primarily utilize electric logic control combined with standard metering equipment. However, due to their large size, they are less portable and generally have higher procurement costs. Utility Model Content

[0005] In order to solve the technical problem of poor portability of the force arm device detection equipment in the prior art, the present utility model provides solutions in the following aspects.

[0006] The utility model provides a performance tester for an automatic control device of an aircraft arm, comprising: a rectifier circuit, an input end of which is connected to an AC power supply, and an output end of which is connected to an arm regulator via a first switch, for converting an AC voltage into a DC voltage and supplying power to the arm regulator; a first push-type switch, connected in series between the first switch and a first port of the arm regulator, for transmitting the DC voltage to the first port of the arm regulator; a second push-type switch, connected in series between the first switch and a second port of the arm regulator, for transmitting the DC voltage to the second port of the arm regulator; a arm position indicator, a signal output end of which is connected to the arm regulator, for collecting and displaying the extended length of the arm, and sending the collected length data to the arm regulator; the arm regulator, controlling the arm connected to the aircraft, for shortening the arm length according to a preset step length when the first port receives the DC voltage, and for extending the arm length according to a preset step length when the second port receives the DC voltage; and a control circuit connected to a boom signal light, for controlling the boom signal light to illuminate when the extended length of the arm reaches a maximum.

[0007] Preferably, it also includes a lever arm control box, a second switch and a switching switch, the second switch is connected in series between the output end of the rectifier circuit and the power supply end of the lever arm control box, and the switching switch is used to select to connect the connection between the first switch and the lever arm control box, or to connect the connection between the second switch and the lever arm regulator; the lever arm control box is provided with a dynamic pressure interface and a static pressure interface, the dynamic pressure interface is used to connect to the first air pressure generating device, and the static pressure interface is used to connect to the second air pressure generating device; the lever arm control box is connected to the lever arm regulator, and is used to control the action of the lever arm regulator according to the air pressure of the dynamic pressure interface and the air pressure of the static pressure interface.

[0008] Preferably, the dynamic pressure interface and the static pressure interface are also connected to an airspeed indicator.

[0009] Preferably, the static pressure interface is also connected to an altimeter.

[0010] Preferably, the static pressure interface is also connected to a vertical speed indicator.

[0011] Preferably, the output end of the rectifier circuit is also connected to a voltage measuring device.

[0012] Preferably, the output end of the rectifier circuit is also connected to a heat dissipation fan.

[0013] Preferably, it further comprises an AC / DC switching switch, one end of which is connected to the first switch and the second switch; and the other end is respectively connected to a DC power supply and the output end of the rectifier circuit.

[0014] Preferably, the voltage measuring device is an LED DC voltmeter.

[0015] Preferably, the rectifier circuit adopts a switching type voltage-stabilized power supply.

[0016] The technical effects of the utility model are as follows: the aircraft arm automatic control device performance tester of the present embodiment has a simple structure, a small size, and good portability; the aircraft arm automatic control device performance tester of the present embodiment can effectively detect the performance of the aircraft arm automatic control device.

[0017] Furthermore, by setting a second switch and a switching switch, it is possible to choose to test the performance of the arm control box and the performance of the arm regulator at the same time; or to choose to test the performance of the arm regulator alone; thereby improving the applicability of the aircraft arm automatic control device performance tester of the present invention.

[0018] Furthermore, by connecting the dynamic pressure interface and the static pressure interface to an airspeed indicator, the experimenter can intuitively observe the aircraft flight speed simulated by the air pressure of the dynamic pressure interface and the air pressure of the static pressure interface.

[0019] Furthermore, by connecting the static pressure interface to an altimeter, the experimenter can visually observe the aircraft flight altitude simulated by the air pressure of the static pressure interface.

[0020] Furthermore, by connecting the static pressure interface to the vertical speed meter, the experimenter can intuitively observe the aircraft vertical speed meter simulated by the pressure change process of the static pressure interface.

[0021] Furthermore, by connecting a voltage measuring device to the output end of the rectifier circuit, it is possible to observe whether the voltage output by the rectifier circuit is the rated operating voltage of the arm control box and the arm regulator. When the voltage output by the rectifier circuit is too large or too small, the power supply of the rectifier circuit can be disconnected, thereby helping to avoid damage to the arm control box and the arm regulator.

[0022] Furthermore, by connecting a cooling fan to the output end of the rectifier circuit, the aircraft arm automatic control device performance tester of the present invention can be prevented from being burned due to excessive temperature.

[0023] Furthermore, by providing an AC / DC switch, power can be supplied by a DC power supply in the event of a rectifier circuit failure, thereby improving the reliability of the aircraft arm automatic control device performance tester. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The above and other objects, features and advantages of the exemplary embodiments of the present invention will become readily understood by reading the detailed description below with reference to the accompanying drawings. In the accompanying drawings, several embodiments of the present invention are shown in an exemplary and non-limiting manner, and the same or corresponding reference numerals represent the same or corresponding parts, wherein:

[0025] Figure 1 This is a schematic diagram of the circuit structure of an aircraft lever arm automatic control device performance tester according to an embodiment of the present utility model;

[0026] Figure 2 The utility model is a schematic diagram of the air circuit structure of an aircraft lever arm automatic control device performance tester according to an embodiment of the present invention. DETAILED DESCRIPTION

[0027] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without making creative efforts shall fall within the scope of protection of the present invention.

[0028] The specific implementation of the present utility model will be described in detail below with reference to the accompanying drawings.

[0029] Aircraft lever arm automatic control device performance tester embodiment:

[0030] like Figure 1 As shown, the aircraft arm automatic control device performance tester of the present invention includes: a rectifier circuit, whose input end is connected to an AC power supply, and whose output end is connected to a lever arm regulator through a first switch K1, for converting AC voltage into DC voltage and supplying power to the lever arm regulator; a first push-type switch K2, connected in series between the first switch and the first port a of the lever arm regulator, for transmitting the DC voltage to the first port of the lever arm regulator; a second push-type switch K3, connected in series between the first switch and the second port b of the lever arm regulator, for transmitting the DC voltage to the second port of the lever arm regulator. The DC voltage is transmitted; a lever position indicator P, whose signal output end is connected to the lever adjuster, is used to collect and display the extended length of the lever, and send the collected length data to the lever adjuster; the lever adjuster controls the lever connected to the aircraft, and is used to shorten the length of the lever according to a preset step length when the DC voltage is received at the first port thereof; and to extend the length of the lever according to a preset step length when the DC voltage is received at the second port thereof; and is controlled to be connected to the boom signal light L, and is used to control the boom signal light to light up when the extended length of the lever reaches the maximum.

[0031] In this embodiment, the rectifier circuit adopts a switching type voltage-stabilized power supply; in other embodiments, the rectifier circuit may also adopt other devices for rectification.

[0032] The operating principle of the aircraft arm automatic control device performance tester of this embodiment is as follows: the first switch K1 is controlled to be closed, the first push-type switch K2 is continuously pressed, and the arm position data displayed on the arm position indicator P is observed to see whether it continuously decreases; the second push-type switch K3 is continuously pressed, and the arm position data displayed on the arm position indicator P is observed to see whether it continuously increases. When the arm position data reaches the maximum, the boom signal light L is observed to light up; thereby determining whether the performance of the arm adjuster is good.

[0033] It should be noted that the innovation of the aircraft arm automatic control device performance tester of this embodiment lies in the circuit structure of the aircraft arm automatic control device performance tester, rather than the performance testing method of the aircraft arm automatic control device.

[0034] The aircraft arm automatic control device performance tester of this embodiment has a simple structure, a small size, and good portability; the aircraft arm automatic control device performance tester of this embodiment can effectively test the performance of the aircraft arm automatic control device.

[0035] In one embodiment, it further includes a force arm control box, a second switch K4 and a switching switch K5, wherein the second switch is connected in series between the output end of the rectifier circuit and the power supply end of the force arm control box, and the switching switch is used to select whether to connect the first switch to the force arm control box or to connect the second switch to the force arm regulator; Figure 2 As shown, the lever arm control box is provided with a dynamic pressure interface and a static pressure interface, the dynamic pressure interface is used to connect to the first air pressure generating device through a rubber hose, and the static pressure interface is used to connect to the second air pressure generating device through a rubber hose; the lever arm control box is connected to the lever arm regulator, and is used to control the action of the lever arm regulator according to the air pressure of the dynamic pressure interface and the air pressure of the static pressure interface.

[0036] The working principle of the aircraft arm automatic control device performance tester in this embodiment is as follows: first, the first switch K4 is controlled to be closed, the first switch K1 is disconnected, the working state of the switching switch K5 is controlled, the connection between the first switch and the arm control box is connected, the arm control box is powered on, the dynamic pressure interface of the arm control box is connected to the first air pressure generating device, and the air pressure generated by the first air pressure generating device is used to simulate the dynamic pressure of the aircraft during flight, and the static pressure interface of the arm control box is connected to the second air pressure generating device, and the air pressure generated by the second air pressure generating device is used to simulate the aircraft during flight. The static pressure during flight, the lever arm control box detects the dynamic pressure data and static pressure data and converts them into the aircraft flight speed and altitude, and according to the flight speed and altitude, and in accordance with the preset correspondence between the flight speed, altitude and lever arm length, sends a control instruction to the lever arm regulator to adjust the extended length of the lever arm; by adjusting the air pressure generated by the first air pressure generating device and / or the air pressure generated by the second air pressure generating device, observing whether the lever arm position data displayed by the lever arm position indicator corresponds to the static pressure data and dynamic pressure data, so as to evaluate the performance of the lever arm control box and the lever arm regulator.

[0037] Specifically: In one embodiment, the test process for speed regulation is as follows: the air pressure generated by the first air pressure generating device is controlled to gradually increase from zero and be less than the first air pressure threshold, which is equivalent to the take-off and landing state. The lever arm regulator should control the aircraft lever arm to remain in the large arm state, and the large arm signal light is on. The lever arm position data displayed by the "lever arm position indicator" is the position corresponding to the maximum length of the lever arm. When the air pressure generated by the first air pressure generating device gradually increases from the first air pressure threshold, the "lever arm regulator" should control the aircraft lever arm to automatically move toward the small arm direction, the large arm signal light is off, and the lever arm position data displayed by the lever arm position indicator begins to decrease. When the air pressure generated by the first air pressure generating device is greater than the second air pressure threshold, the "lever arm regulator" stops working, and the pointer of the "lever arm position indicator" indicates the right limit small arm position.

[0038] The test process for height adjustment is as follows: After the speed adjustment test is completed, the air pressure generated by the first air pressure generating device is kept constant, and the static pressure interface is slowly evacuated. When the air pressure of the static pressure interface is less than the second air pressure threshold, the arm regulator should control the aircraft arm to always remain in the forearm state. When the air pressure of the static pressure interface gradually decreases from the second air pressure threshold, the arm regulator should control the length of the aircraft arm to gradually increase, and at the same time, the position data of the arm position indicator begins to decrease. When the air pressure of the static pressure interface is less than the third air pressure threshold, the arm stops working, the arm signal light lights up, and the position data displayed by the "arm position indicator" is the maximum.

[0039] By setting the second switch K4 and the switching switch K5, the performance of the arm control box and the arm regulator can be tested simultaneously; or the performance of the arm regulator can be tested separately; thereby improving the applicability of the aircraft arm automatic control device performance tester of the present invention.

[0040] In one embodiment, the dynamic pressure interface and the static pressure interface are further connected to an airspeed indicator B.

[0041] By connecting the dynamic pressure interface and the static pressure interface to an airspeed indicator, the experimenter can intuitively observe the aircraft flight speed simulated by the air pressure of the dynamic pressure interface and the air pressure of the static pressure interface.

[0042] In one embodiment, the static pressure interface is further connected to an altimeter C.

[0043] By connecting the static pressure interface to the altimeter, the experimenter can visually observe the aircraft flight altitude simulated by the air pressure of the static pressure interface.

[0044] In one embodiment, the static pressure interface is further connected to a vertical speed table D.

[0045] By connecting the static pressure interface to the vertical speed indicator, the experimenter can visually observe the pressure change process of the static pressure interface to simulate the aircraft vertical speed indicator.

[0046] In one embodiment, the output end of the rectifier circuit is further connected to a voltage measuring device V.

[0047] By connecting a voltage measuring device to the output end of the rectifier circuit, it is possible to observe whether the voltage output by the rectifier circuit is the rated operating voltage of the arm control box and the arm regulator. If the voltage output by the rectifier circuit is too large or too small, the power supply of the rectifier circuit can be disconnected to avoid damage to the arm control box and the arm regulator.

[0048] In this embodiment, the voltage measuring device is an LED DC voltmeter. In other embodiments, the voltage measuring device may also be other devices for measuring voltage.

[0049] In one embodiment, the output end of the rectifier circuit is further connected to a cooling fan M.

[0050] By connecting a cooling fan to the output end of the rectifier circuit, the aircraft arm automatic control device performance tester of the present invention can be prevented from being burned due to excessive temperature.

[0051] In one embodiment, an AC / DC switching switch K6 is further included, one end of which is connected to the first switch and the second switch; and the other end is respectively connected to a DC power supply and the output end of the rectifier circuit.

[0052] The AC / DC switch in this embodiment has a pair of stationary contacts at the first end, one of which is connected to the first and second switches via a fuse FU, and the other contact is grounded. The second end has two pairs of stationary contacts, one of which is connected to the output of the rectifier circuit, and the other is connected to a DC power supply. In this embodiment, the DC power supply voltage is 27V.

[0053] By setting up an AC / DC switch, power can be supplied by a DC power supply when a rectifier circuit fails, thereby improving the reliability of the aircraft arm automatic control device performance tester.

[0054] In the above description of this specification, unless otherwise expressly specified or limited, terms such as "connection" should be understood broadly. For example, the term "connection" can refer to fixed connection, detachable connection, or integration; it can refer to mechanical connection or electrical connection; it can refer to direct connection or indirect connection through an intermediate medium; it can refer to internal communication between two components or interaction between two components. Therefore, unless otherwise expressly defined in this specification, those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0055] In addition, the terms "first" or "second" used in this specification to refer to numbers or ordinal numbers are used for descriptive purposes only and should not be understood as explicitly or implicitly indicating relative importance or implicitly indicating the number of technical features indicated. Therefore, a feature specified as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of this specification, "plurality" means at least two, such as two, three or more, etc., unless otherwise clearly specified.

[0056] Although this specification has shown and described a number of embodiments of the present invention, it will be apparent to those skilled in the art that such embodiments are provided by way of example only. Those skilled in the art will recognize numerous modifications, variations, and alternatives without departing from the concept and spirit of the present invention. It should be understood that in practicing the present invention, various alternatives to the embodiments of the present invention described herein may be employed.

Claims

1. An aircraft lever arm automatic control device performance tester, characterized in that: include: a rectifier circuit, whose input end is connected to an AC power supply and whose output end is connected to the lever arm regulator via a first switch, for converting the AC voltage into a DC voltage and supplying power to the lever arm regulator; a first push-type switch connected in series between the first switch and the first port of the lever arm regulator, for transmitting the DC voltage to the first port of the lever arm regulator; a second push-type switch connected in series between the first switch and the second port of the lever arm regulator, for transmitting the DC voltage to the second port of the lever arm regulator; a lever arm position indicator, whose signal output end is connected to the lever arm regulator, for collecting and displaying the extended length of the lever arm, and sending the collected length data to the lever arm regulator; a lever arm regulator, controlling a lever arm connected to the aircraft, and configured to shorten the lever arm according to a preset step length when the first port thereof receives the DC voltage; When the DC voltage is received at the second port, the length of the lever arm is extended according to a preset step length; and the control is connected to the boom signal light, which is used to control the boom signal light to light up when the extended length of the lever arm reaches the maximum.

2. The aircraft arm automatic control device performance tester according to claim 1, characterized in that: The invention also includes a force arm control box, a second switch and a switching switch, wherein the second switch is connected in series between the output end of the rectifier circuit and the power supply end of the force arm control box, and the switching switch is used to select whether to connect the first switch to the force arm control box or to connect the second switch to the force arm regulator; the force arm control box is provided with a dynamic pressure interface and a static pressure interface, the dynamic pressure interface is used to connect to the first air pressure generating device, and the static pressure interface is used to connect to the second air pressure generating device; The lever arm control box is connected to the lever arm regulator and is used to control the action of the lever arm regulator according to the air pressure of the dynamic pressure interface and the air pressure of the static pressure interface.

3. The aircraft lever arm automatic control device performance tester according to claim 2, characterized in that: The dynamic pressure interface and the static pressure interface are also connected to an airspeed indicator.

4. The aircraft lever arm automatic control device performance tester according to claim 3, characterized in that: The static pressure interface is also connected to an altimeter.

5. The aircraft arm automatic control device performance tester according to claim 3, characterized in that: The static pressure interface is also connected to a vertical speed indicator.

6. The aircraft lever arm automatic control device performance tester according to claim 1, characterized in that: The output end of the rectifier circuit is also connected to a voltage measuring device.

7. The aircraft lever arm automatic control device performance tester according to claim 1, characterized in that: The output end of the rectifier circuit is also connected to a heat dissipation fan.

8. The aircraft lever arm automatic control device performance tester according to claim 2, characterized in that: It also includes an AC / DC switching switch, one end of which is connected to the first switch and the second switch; and the other end is respectively connected to a DC power supply and the output end of the rectifier circuit.

9. The aircraft lever arm automatic control device performance tester according to claim 6, characterized in that: The voltage measuring device adopts an LED DC voltmeter.

10. The aircraft lever arm automatic control device performance tester according to any one of claims 1 to 9, characterized in that: The rectifier circuit adopts a switching type voltage-stabilized power supply.

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