Portable digital measurement equipment, lifting and thrust line test method and system

Abstract

The invention provides portable digital measurement equipment and a lifting and thrust line test method and system. The equipment comprises a lifting rope, a booster connecting mechanism, a front simulation part and a digital gradienter, the booster connecting mechanism is fixedly connected with the side wall of the aircraft body; the front simulation piece is fixedly connected to the booster connecting mechanism, and the front simulation piece is used for simulating a test part of an actual working condition; the lifting rope is lifted on the front simulation piece; the digital gradienter is mounted on the upper surface of the front simulation piece; the reading of the digital gradienter is used for obtaining the included angle between the test part and the aircraft fuselage, and quantitatively determining whether the yaw moment of the aircraft is within the control margin. According to the invention, the measurement precision of the thrust line of the booster is improved, and the use convenience of the portable digital measurement equipment is improved.

Description

Technical Field

[0001] The present application relates to the technical field of booster thrust line testing, and in particular to a method and system for testing a suspension thrust line. Background Art

[0002] With the emergence of aircraft (large drones, target drones), a large number of unconventional launch platforms have been used, and the use of conventional tandem boosters has been limited. Therefore, boosters located in the belly of the aircraft have been widely used. The thrust line of this type of booster is at a certain angle to the fuselage. In order to ensure that drones and target drones can successfully complete boosted takeoff, how to measure the thrust line of the booster is crucial.

[0003] The conventional method of hanging thrust line adopts the method of mechanically measuring the gap between the cylinder and the disc. The error decreases with the increase of the axial length of the cylinder, resulting in that the accuracy, convenience and economy cannot be met at the same time, and the error cannot be controlled.

[0004] Therefore, the technical problem that urgently needs to be solved is: how to provide a portable digital measuring equipment, a lifting thrust line testing method and system to improve the measurement accuracy of the booster thrust line and improve the convenience of using the portable digital measuring equipment. Summary of the invention

[0005] The purpose of the present application is to provide a portable digital measuring equipment, a method and a system for testing the thrust line of a suspension, so as to improve the measurement accuracy of the thrust line of a booster and improve the convenience of using the portable digital measuring equipment.

[0006] To achieve the above-mentioned purpose, as the first aspect of the present application, the present application provides a portable digital measuring equipment, which includes: a lifting rope, a booster connecting mechanism, a front simulation component and a digital level; the booster connecting mechanism is fixedly connected to the side wall of the aircraft fuselage; the front simulation component is fixedly connected to the booster connecting mechanism, and the front simulation component is used to simulate a test component of actual working conditions; the lifting rope is suspended on the front simulation component; the digital level is installed on the upper surface of the front simulation component; the reading of the digital level is used to obtain the angle between the test component and the aircraft fuselage, and quantitatively determine whether the yaw moment of the aircraft is within the control margin.

[0007] The portable digital measuring equipment as described above, wherein the digital level comprises at least one digital level.

[0008] The portable digital measuring equipment as described above, wherein the digital level comprises a first digital level and a second digital level;

[0009] The first digital level and the second digital level are both disposed on an upper surface of the front analog member.

[0010] The portable digital measuring equipment as described above, wherein the first digital level and the second digital level are respectively located on both sides of the suspension rope.

[0011] As described above, in the portable digital measuring equipment, the suspension rope hangs down in a vertical direction, and the natural hanging direction of the suspension rope represents the direction of gravity.

[0012] The portable digital measuring equipment as described above, wherein the front simulation component and the real booster have the same interface size and appearance profile, simulates the connection state between the real booster and the fuselage in a test environment.

[0013] The portable digital measuring equipment as described above, wherein the booster connection mechanism is an adjustable angle mechanism; the adjustable angle mechanism realizes the adjustment of the angle between the booster thrust line and the center axis of the aircraft.

[0014] As a second aspect of the present application, the present application provides a method for testing a thrust line, which is applied to the portable digital measuring equipment, and the method includes: installing the portable digital measuring equipment on the side wall of the aircraft fuselage to be tested; starting the test; reading the reading of the digital level; and determining the angular relationship between the thrust line of the booster and the aircraft fuselage based on the reading of the digital level.

[0015] As a third aspect of the present application, the present application provides a suspension thrust line testing system, the suspension thrust line testing method, the system comprising: a portable digital measuring equipment and a drone; the portable digital measuring equipment is installed on the side wall of the drone; the portable digital measuring equipment is used to test the booster thrust line installed on the side wall of the drone.

[0016] As the fourth aspect of the present application, the present application provides a suspended thrust line test system for executing the suspended thrust line test method, the system comprising: a portable digital measuring equipment and a target aircraft; the portable digital measuring equipment is installed on the side wall of the target aircraft; the portable digital measuring equipment is used to test the booster thrust line installed on the side wall of the target aircraft.

[0017] The beneficial effects achieved by this application are as follows:

[0018] (1) The present application provides a method for testing the lifting thrust line applied to an unmanned aerial vehicle or a target drone, which reduces the difficulty of leveling production during measurement and auxiliary measurement, improves the accuracy and convenience of measurement, and enhances the accuracy of flight result analysis.

[0019] (2) This application uses a portable digital measuring device to improve test convenience, measurement precision and test accuracy.

[0020] (3) The present application uses two digital levels, which can not only measure the thrust line and fuselage angle, but also quantitatively determine whether the yaw moment is within the control margin. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present application. For those skilled in the art, other drawings can also be obtained based on these drawings.

[0022] Figure 1 This is a schematic structural diagram of a portable digital measuring device according to an embodiment of the present application.

[0023] Figure 2 This is a flow chart of a method for testing a lifting thrust line according to an embodiment of the present application.

[0024] Figure numerals: 1 - aircraft fuselage; 2 - booster connection mechanism; 3 - front analog part; 4 - digital level; 5 - suspension rope. DETAILED DESCRIPTION

[0025] The following is a clear and complete description of the technical solutions in the embodiments of the present application in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present application.

[0026] Embodiment 1

[0027] like Figure 1 As shown, the present application provides a portable digital measuring equipment, which includes: a lifting rope 5, a booster connecting mechanism 2, a front simulation component 3 and a digital level 4; the booster connecting mechanism is fixedly connected to the aircraft fuselage 1; the front simulation component 3 is fixedly connected to the booster connecting mechanism 2, and the front simulation component 3 is used to simulate the test component of the actual working condition; the lifting rope 5 is hoisted on the front simulation component 3; the digital level 4 is installed on the front simulation component 3; the reading of the digital level 4 is used to obtain the angle between the test component and the aircraft fuselage 1, and quantitatively determine whether the yaw moment of the aircraft is within the control margin.

[0028] As a specific embodiment of the present invention, the front simulation part 3 is a model with a similar shape and connection structure to the booster. For example, the front simulation part 3 is a simulation part made of metal or composite materials with the same proportion as the booster. It has the same interface size and appearance as the real booster, and can simulate the connection state between the real booster and the fuselage in the test environment, so as to determine parameters such as the angle between the booster thrust line and the fuselage. Its function is to facilitate test personnel to repeatedly measure, adjust and calibrate without using the real thruster, thereby reducing the loss and risk of the real booster.

[0029] As a specific embodiment of the present invention, the suspension rope 5 is arranged in the vertical direction, and the suspension rope 5 is used to simulate the direction of gravity and provide a vertical reference. When the suspension rope 5 is suspended at a certain point on the front simulation component 3, its natural drooping direction represents the direction of gravity. In the measurement process, the drooping direction of the suspension rope 5 can be used as a vertical reference benchmark to help determine the posture of the thruster. For example, by observing the angle between the marking line on the surface of the front simulation component 3 and the direction of the suspension rope 5, it is assisted to judge whether the thrust line of the thruster is perpendicular to the ground and other related angle information. In combination with the suspension rope 5 and the digital level 4, the position of the thrust line of the booster can be calculated. For example, the position and length of the suspension rope 5, as well as the relative relationship between certain fixed points on the front simulation component 3 and the suspension rope 5 are known, and the position relationship or angle relationship of the thrust line of the booster relative to the direction of gravity or the fuselage is determined using geometric principles.

[0030] As a specific embodiment of the present invention, the thrust line of the booster is distributed along the central axis of the booster, that is, the thrust line of the booster is perpendicular to the upper surface of the booster. The reading of the digital level 4 can accurately show the angle between the plane on which it is placed (i.e., the upper surface of the booster) and the absolute horizontal position. Since the thrust line of the booster is perpendicular to the upper surface of the booster, the angle between the thrust line of the booster and the vertical direction or the angle between the thrust line of the booster and the aircraft fuselage 1 can be calculated through the reading of the digital level 4.

[0031] As a specific embodiment of the present invention, the present invention can adopt various forms of thrust line tests of the booster adapter structure to ensure that the booster adapter structure and the fuselage can be stably connected when the fuselage achieves an inverted posture (thrust line posture).

[0032] As a specific embodiment of the present invention, the digital level 4 includes at least one digital level. Preferably, the digital level of the present invention adopts a dual-level digital level, and the digital level 4 includes a first digital level and a second digital level, and the first digital level and the second digital level are both arranged on the upper surface of the front analog component 3, and the first digital level and the second digital level are respectively located on both sides of the suspension rope 5. The accuracy of the first digital level and the second digital level is 0.001°, which meets the accuracy requirement (less than 0.1°). The angle between the thrust line and the fuselage can be obtained by the readings of the dual-level digital level, and at the same time, it can be quantitatively determined whether the yaw moment is within the control margin. Yaw moment refers to the torque acting on the aircraft to rotate the aircraft around its vertical axis; control margin refers to the ability range of the aircraft control system to effectively correct the yaw within the design allowable range. For example, the control margin of the aircraft is + 1°; then it means that within the range of -1° to +1°, the aircraft is capable of correcting the yaw. If the yaw angle measured by the digital level 4 continues to increase and exceeds the angle corresponding to the control margin, and the control surface has deflected to the maximum angle but cannot prevent the yaw angle from further increasing, it can be determined that the yaw moment exceeds the control margin. For example, the data analysis software shows that the rudder has deflected to the extreme position, but the yaw angle continues to increase, exceeding the allowable control range.

[0033] The present invention adopts two digital level gauges 4 to read the reading together, thereby improving the measurement accuracy of the angle between the thrust line of the booster and the fuselage.

[0034] As other embodiments of the present invention, the booster connection mechanism 2 adopts an adjustable structure, such as an adjustable angle mechanism, and can also realize the suspension thrust line adjustment. Suspension thrust line adjustment is the process of calibrating the thrust line of the aircraft booster. The front simulation member 3 is suspended by the suspension rope 5. Due to the effect of gravity, when suspended, the front simulation member 3 naturally droops, which serves as a reference state. Thrust line adjustment refers to adjusting the installation angle or position of the front simulation member 3 or the booster so that the thrust line of the booster reaches the position or angle required by the design. For example, the thrust line of the booster is maintained at a specific angle with the central axis of the aircraft, or the thrust line of the booster is intersected near the center of gravity of the aircraft, etc., to ensure the balance of forces and the correct flight attitude during the flight of the aircraft.

[0035] Embodiment 2

[0036] like Figure 2 As shown, the present application provides a method for testing a lifting thrust line, the method comprising:

[0037] Step S1, installing a portable digital measuring device on the side wall of the aircraft fuselage to be measured;

[0038] Step S2, starting the thrust line test;

[0039] Step S3, reading the reading of the digital level;

[0040] Step S4, determining the angle relationship between the thrust line of the booster and the fuselage of the aircraft according to the reading of the digital level.

[0041] Embodiment 3

[0042] The present application provides a suspension thrust line test system for executing the suspension thrust line test method, the system comprising: a portable digital measuring device and a drone; the portable digital measuring device is installed on the side wall of the drone; the portable digital measuring device is used to test the booster thrust line installed on the side wall of the drone.

[0043] Embodiment 4

[0044] The present application provides a suspension thrust line test system for executing the suspension thrust line test method, the system comprising: a portable digital measuring device and a target drone; the portable digital measuring device is installed on the side wall of the target drone; the portable digital measuring device is used to test the booster thrust line installed on the side wall of the target drone.

[0045] The present application also provides a computer storage medium, wherein the computer storage medium stores computer instructions, and when the computer instructions are called, they are used to execute the address mapping method of the large-capacity solid-state hard disk. The computer storage medium contains one or more program instructions, and the one or more program instructions are used by the processor to execute a method for testing a lifting thrust line.

[0046] The embodiment disclosed in the present invention provides a computer-readable storage medium, in which computer program instructions are stored. When the computer program instructions are executed on a computer, the computer executes the above-mentioned method for testing a lifting thrust line.

[0047] The beneficial effects achieved by this application are as follows:

[0048] (1) The present application provides a method for testing the lifting thrust line applied to an unmanned aerial vehicle or a target drone, which reduces the difficulty of leveling production during measurement and auxiliary measurement, improves the accuracy and convenience of measurement, and enhances the accuracy of flight result analysis.

[0049] (2) This application uses a portable digital measuring device to improve test convenience, measurement precision and test accuracy.

[0050] (3) The present application uses two digital levels, which can not only measure the thrust line and fuselage angle, but also quantitatively determine whether the yaw moment is within the control margin.

[0051] In the description of this application, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, "plurality" means two or more, unless otherwise clearly and specifically defined.

[0052] In the description of the present application, the word "for example" is used to mean "used as an example, illustration or explanation". Any embodiment described as "for example" in the present application is not necessarily to be construed as being more preferred or advantageous than other embodiments. The following description is given to enable any technician in the field to implement and use the present invention. In the following description, details are listed for the purpose of explanation. It should be understood that a person of ordinary skill in the art can recognize that the present invention can be implemented without using these specific details. In other examples, well-known structures and processes will not be elaborated in detail to avoid obscuring the description of the present invention with unnecessary details. Therefore, the present invention is not intended to be limited to the embodiments shown, but is consistent with the widest scope consistent with the principles and features disclosed in the present application.

[0053] The above description is only an embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent substitution, improvement, etc. made within the spirit and principle of the present invention should be included in the scope of the claims of the present invention.

Claims

1. A portable digital measuring device, characterized in that: The equipment includes: sling, booster attachment mechanism, front analog and digital level; The booster connection mechanism is fixedly connected to the side wall of the aircraft fuselage; The front simulation part is fixedly connected to the booster connection mechanism, and the front simulation part is used to simulate the test component of the actual working condition; The sling is suspended on the front simulation member; The digital level is installed on the upper surface of the front simulation component; the reading of the digital level is used to obtain the angle between the test component and the aircraft fuselage, and quantitatively determine whether the yaw moment of the aircraft is within the control margin.

2. The portable digital measuring equipment according to claim 1, characterized in that: The digital level includes at least one digital level.

3. The portable digital measuring equipment according to claim 2, characterized in that: The digital level comprises a first digital level and a second digital level; The first digital level and the second digital level are both disposed on an upper surface of the front analog member.

4. The portable digital measuring equipment according to claim 3, characterized in that: The first digital level and the second digital level are respectively located on both sides of the suspension rope.

5. The portable digital measuring equipment according to claim 1, characterized in that: The suspension rope hangs down in a vertical direction, and the natural hanging direction of the suspension rope represents the direction of gravity.

6. The portable digital measuring equipment according to claim 1, characterized in that: The front simulation component and the real booster have the same interface size and appearance profile, simulating the connection state between the real booster and the fuselage in a test environment.

7. The portable digital measuring equipment according to claim 1, characterized in that: The booster connection mechanism is an angle-adjustable mechanism; The adjustable angle mechanism realizes the adjustment of the angle between the thrust line of the booster and the central axis of the aircraft.

8. A method for testing a lifting thrust line, characterized in that: The method is applied to the portable digital measuring equipment according to any one of claims 1 to 7, and the method comprises: Installing the portable digital measuring equipment on the fuselage side wall of the aircraft being measured; Start the test; Take readings from a digital level; Based on the reading of the digital level, determine the angular relationship between the thrust line of the booster and the aircraft fuselage.

9. A suspension thrust line test system, characterized in that: The method for testing the lifting force line according to claim 8 is performed, wherein the system comprises: a portable digital measuring device and a drone; The portable digital measuring equipment is installed on the side wall of the drone; The portable digital measuring equipment is used to test the thrust lines of the boosters installed on the side walls of the UAV.

10. A suspension thrust line test system, characterized in that: The method for testing the lifting thrust line according to claim 8 is implemented, wherein the system comprises: a portable digital measuring device and a target drone; The portable digital measuring equipment is installed on the side wall of the target drone; The portable digital measuring equipment is used to test the thrust line of the booster installed on the side wall of the target drone.

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