Automatic measuring device and measuring method for dynamic balance point of aircraft
By designing an automatic measurement device, the dynamic balance point of the aircraft is monitored and adjusted using the sliding platform and screw assembly, the problem of inconsistency between the dynamic balance point and the static balance point is solved, efficient and accurate measurement is achieved, and R&D costs and time periods are reduced.
Patent Information
- Application Number
- CN202411728668.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-28
- Publication Date
- 2025-04-11
AI Technical Summary
During the drone design process, the dynamic balance point is inconsistent with the static balance point, resulting in unstable aircraft performance and may not be able to take off normally during the test, resulting in problems such as increasing R&D costs and time cycles.
An automatic measurement device for the dynamic balance point of an aircraft is designed, including a sliding platform, a screw assembly, a screw bracket, a counterweight block, a bracket and a control module. By monitoring the pitch action of the screw bracket, the screw assembly drives the sliding platform to move until the screw bracket reaches a horizontal equilibrium state, thereby measuring the distance between the dynamic balance point and the static balance point.
The device is simple in structure and flexible in scenarios. It can accurately measure the dynamic balance point of the aircraft, reduce R&D costs and time periods, improve measurement efficiency, and reduce aircraft losses.
Smart Images
Figure CN119796517A_ABST
Abstract
Description
Technical Field
[0001] The invention belongs to the technical field of aircraft design, and in particular relates to an automatic measuring device and a measuring method for the dynamic balance point of an aircraft. Background Art
[0002] At present, in the process of UAV design, key performance indicators are mostly verified by theory or analyzed by software. However, there will be uncertainty errors when it comes to physical testing. For example, the actual dynamic balance point (i.e., the balance point formed by the airflow and air resistance generated by the wings and tail during flight) does not coincide with the calculated static balance point (i.e., the theoretical center of gravity) or the distance is too large. Therefore, it is necessary to test each key performance indicator through an engineering prototype, including the measurement of the dynamic balance point of the aircraft.
[0003] The determination of the dynamic balance point of an aircraft may have a minor impact on the performance of the aircraft, or even lead to a failure to take off normally or a crash during the aircraft test, resulting in increased R&D costs and a longer R&D period.
[0004] Traditional methods of measuring dynamic balance points include wind tunnel measurement and centrifugal traction measurement. However, wind tunnel construction is expensive and not suitable for small enterprises and R&D institutions; centrifugal traction requires a large fixed site, and the equipment and facilities are bulky, expensive, and inflexible. Summary of the invention
[0005] In view of this, the present invention provides an automatic measuring device and method for the dynamic balance point of an aircraft. The measuring device is small in size and flexible in structure, will not cause damage to the aircraft, and can reduce R&D costs and R&D time cycles.
[0006] The present invention is achieved through the following technical solutions:
[0007] An automatic measuring device for the dynamic balance point of an aircraft, comprising a sliding platform, a lead screw assembly, a lead screw bracket, a counterweight, a bracket and a control module;
[0008] The bottom of the base bracket is arranged on the mobile platform; the middle position of the top is hinged with the middle position of the lead screw bracket through a hinge axis; the lead screw bracket can perform pitching motion around the hinge axis;
[0009] The screw rod assembly is arranged on the top of the screw rod bracket, and the length direction of the screw rod assembly is perpendicular to the hinge axis;
[0010] The sliding platform is arranged on the screw assembly, and the sliding platform can move along the length direction of the screw assembly under the drive of the screw assembly; the aircraft is arranged on the top of the sliding platform; in the initial position, the static balance point of the aircraft is located directly above the hinge axis;
[0011] The control module is arranged on the screw bracket. When the mobile platform moves, the control module can monitor the pitch of the screw bracket and drive the screw assembly according to the pitch action of the screw bracket, so as to move the sliding platform and finally make the screw bracket reach a horizontal balance state. At this time, the dynamic balance point of the aircraft is located directly above the hinge axis; the horizontal distance between the dynamic balance point and the static balance point of the aircraft can be obtained by the distance moved by the sliding platform relative to the initial position.
[0012] Furthermore, a scale-marked arrow is provided on the sliding platform; a scale is provided on the lead screw bracket along the length direction, and the distance between the dynamic balance point and the static balance point of the aircraft can be obtained by reading the scale on the scale.
[0013] Furthermore, the control module includes a control circuit and an electronic gyroscope; the electronic gyroscope can obtain the pitch data of the screw bracket and transmit it to the control circuit. After the control circuit obtains and solves the pitch motion data, it controls the movement of the screw assembly, thereby moving the sliding platform until the screw bracket reaches a horizontal balance position.
[0014] Furthermore, limiting bosses are provided at the tops of both ends of the base bracket to limit the extreme pitch angles of the lead screw bracket.
[0015] Furthermore, the limit angle of pitch is ±6.
[0016] Furthermore, the screw assembly includes two screws arranged in parallel, a stepper motor I and a stepper motor II;
[0017] The stepper motor I and the stepper motor II are respectively fixedly arranged at two ends of the lead screw bracket;
[0018] One end of a lead screw is rotatably connected to the lead screw bracket, and the other end is connected to the output shaft of the stepper motor I; one end of the other lead screw is rotatably connected to the lead screw bracket, and the other end is connected to the output shaft of the stepper motor II; the sliding platform is simultaneously matched with the threads of the two lead screws;
[0019] The control module controls the rotation of stepper motor I and stepper motor II, thereby driving the two lead screws to rotate, thereby realizing the movement of the sliding platform on the lead screw assembly.
[0020] A method for automatically measuring the dynamic center of gravity of an aircraft, based on the claims, is an automatic measuring device for the dynamic center of gravity of an aircraft, comprising the following steps:
[0021] Step 1: Install the automatic measuring device on a mobile platform (such as a vehicle), and install the aircraft on the sliding platform of the automatic measuring device, so that the static balance point of the aircraft and the axis of the hinge shaft are in the same vertical plane;
[0022] Step 2: The mobile platform drives the aircraft to move, and the moving speed of the mobile platform is the take-off speed of the aircraft. At this time, the control module monitors the pitch of the aircraft and controls the screw assembly to control the sliding platform to move in the direction of the elevation angle of the aircraft.
[0023] Step 3: Read the scale on the ruler in conjunction with the scale mark arrow to obtain the deviation between the dynamic balance point and the static balance point, thereby measuring the dynamic balance point of the aircraft.
[0024] Beneficial effects:
[0025] (1) The present invention provides an automatic measurement device for the dynamic balance point of an aircraft, which can measure the dynamic balance point of an aircraft according to the position of a static balance point. The device has a simple structure and is flexible in application scenarios, and can reduce R&D costs and time cycles.
[0026] (2) The present invention provides an automatic measurement device for the dynamic balance point of an aircraft, wherein a scale-marked arrow is provided on a sliding platform; a scale is provided on a lead screw bracket, and the distance between the dynamic balance point and the static balance point of the aircraft can be directly obtained by reading the scale on the scale, which is intuitive and efficient.
[0027] (3) The automatic measurement device for the dynamic balance point of an aircraft provided by the present invention ensures the stability of the sliding platform by setting two parallel screws, thereby improving the accuracy of the measurement of the dynamic balance point of the aircraft.
[0028] (4) The present invention provides an automatic measurement method for the dynamic balance point of an aircraft. By measuring the dynamic balance point of an aircraft, the position of the dynamic balance point of the aircraft relative to the static balance point can be accurately obtained, and the pitch stability, maneuverability and stability of the aircraft can be ensured, thereby obtaining a longer flight time and satisfying the longer airborne time of the aircraft. Moreover, the measurement efficiency can be improved, the loss of the aircraft during the measurement process can be reduced, and the R&D cycle and R&D cost can be greatly shortened. BRIEF DESCRIPTION OF THE DRAWINGS
[0029] Figure 1 It is an automatic measuring device for the dynamic balance point of an aircraft. Figure I ;
[0030] Figure 2 It is an automatic measuring device for the dynamic balance point of an aircraft. Figure II ;
[0031] Among them, 1-stepping motor I, 2-screw bracket, 3-stepping motor II, 4-sliding platform, 5-scale marking arrow, 6-scale ruler, 9-base bracket, 10-articulated shaft. DETAILED DESCRIPTION
[0032] Embodiment 1:
[0033] This embodiment provides an automatic measurement device for the dynamic balance point of an aircraft. Figure 1 and 2 , including a sliding platform 4, a lead screw assembly, a lead screw support 2, a base support 9 and a control module;
[0034] The bottom of the base bracket 9 is arranged on the mobile platform; the middle position of the top is hinged to the middle position of the screw bracket 2 through the hinge shaft 10; the screw bracket 2 can perform pitching movement around the hinge shaft 10;
[0035] The screw assembly is arranged on the top of the screw support 2, and the length direction of the screw assembly is perpendicular to the hinge shaft 10; the sliding platform 4 is arranged on the screw assembly, and the sliding platform 4 can move along the length direction of the screw assembly under the drive of the screw assembly; the aircraft is arranged on the top of the sliding platform 4; in the initial position, the static balance point of the aircraft is located directly above the hinge shaft 10;
[0036] The control module is arranged on the screw bracket 2. When the mobile platform moves, the control module can monitor the pitch of the screw bracket 2 and drive the screw assembly according to the pitch action of the screw bracket 2, so as to move the sliding platform 4, and finally make the screw bracket 2 reach a horizontal balance state. At this time, the dynamic balance point of the aircraft is located directly above the hinge axis 10; the horizontal distance between the dynamic balance point and the static balance point of the aircraft can be obtained by the distance moved by the sliding platform 4 relative to the initial position.
[0037] An automatic measurement device for the dynamic balance point of an aircraft provided in this embodiment can measure the dynamic balance point of the aircraft according to the position of the static balance point. It has a simple structure and is flexible in application scenarios, and can reduce R&D costs and R&D time cycles.
[0038] In a specific embodiment, a scale marking arrow 5 is provided on the sliding platform 4; a scale 6 is provided on the lead screw bracket 2 along the length direction, and the distance between the dynamic balance point and the static balance point of the aircraft can be directly obtained by reading the scale on the scale 6, so as to measure the dynamic balance point;
[0039] In a specific embodiment, the control module includes a control circuit and an electronic gyroscope; the electronic gyroscope can obtain the pitch data of the screw bracket 2 and transmit it to the control circuit. After the control circuit obtains and solves the pitch motion data, it controls the movement of the screw assembly, thereby moving the sliding platform 4 until the screw bracket 2 reaches a horizontal balance position.
[0040] In a specific embodiment, limiting bosses are provided at the tops of both ends of the base support 9 to limit the limit angle of pitch of the lead screw support 2. Preferably, the limit angle of pitch is ±6°.
[0041] In a specific embodiment, the screw assembly includes two screws arranged in parallel, a stepper motor Ⅰ1 and a stepper motor Ⅱ3;
[0042] The stepper motor Ⅰ1 and the stepper motor Ⅱ3 are respectively fixedly arranged at two ends of the lead screw support 2;
[0043] One end of a lead screw is rotatably connected to the lead screw support 2, and the other end is connected to the output shaft of the stepping motor Ⅰ1;
[0044] One end of the other lead screw is rotatably connected to the lead screw bracket 2, and the other end is connected to the output shaft of the stepper motor II 3; the sliding platform 4 is simultaneously engaged with the threads of the two lead screws;
[0045] The control module controls the rotation of the stepper motor Ⅰ1 and the stepper motor Ⅱ3 to drive the two lead screws to rotate, thereby realizing the movement of the sliding platform 4 on the lead screw assembly.
[0046] By providing two parallel lead screws, the stability of the sliding platform 4 is ensured, thereby improving the accuracy of the dynamic balance point measurement of the aircraft.
[0047] Embodiment 2:
[0048] This embodiment provides an automatic measurement method for the dynamic balance point of an aircraft based on the automatic measurement device for the dynamic balance point of an aircraft in Embodiment 1, comprising the following steps:
[0049] Step 1: Install the automatic measuring device on a mobile platform (such as a vehicle), and install the aircraft on the sliding platform 4 of the automatic measuring device, so that the static balance point of the aircraft and the axis of the hinge shaft 10 are in the same vertical plane;
[0050] Step 2: The mobile platform drives the aircraft to move, and the moving speed of the mobile platform is the take-off speed of the aircraft; at this time, the control module monitors the pitch of the aircraft, and controls the screw assembly to control the sliding platform 4 to move in the direction of the aircraft's elevation angle;
[0051] Step 3: Read the scale on the scale ruler 6 in combination with the scale mark arrow 5 to obtain the deviation between the dynamic balance point and the static balance point, thereby measuring the dynamic balance point of the aircraft.
[0052] This method measures and verifies the dynamic balance point of the aircraft, which can not only accurately obtain the position of the dynamic balance point of the aircraft, but also ensure the pitch stability, controllability and stability of the aircraft, thereby obtaining a longer flight time and satisfying the longer airborne time of the aircraft. Moreover, it can improve the measurement efficiency, reduce the loss of the aircraft during the measurement process, and greatly shorten the R&D cycle and R&D cost.
[0053] In summary, the above are only preferred embodiments of the present invention and are not intended to limit the protection scope of the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.
Claims
1. An automatic measuring device for the dynamic balance point of an aircraft, characterized in that: It includes a sliding platform, a lead screw assembly, a lead screw bracket, a counterweight, a bracket and a control module; The bottom of the base bracket is arranged on the mobile platform; the middle position of the top is hinged with the middle position of the lead screw bracket through a hinge axis; the lead screw bracket can perform pitching motion around the hinge axis; The screw rod assembly is arranged on the top of the screw rod bracket, and the length direction of the screw rod assembly is perpendicular to the hinge axis; The sliding platform is arranged on the screw assembly, and the sliding platform can move along the length direction of the screw assembly under the drive of the screw assembly; the aircraft is arranged on the top of the sliding platform; in the initial position, the static balance point of the aircraft is located directly above the hinge axis; The control module is arranged on the screw bracket. When the mobile platform moves, the control module can monitor the pitch of the screw bracket and drive the screw assembly according to the pitch action of the screw bracket, so as to move the sliding platform and finally make the screw bracket reach a horizontal balance state. At this time, the dynamic balance point of the aircraft is located directly above the hinge axis; the horizontal distance between the dynamic balance point and the static balance point of the aircraft can be obtained by the distance moved by the sliding platform relative to the initial position.
2. The automatic measuring device for the dynamic balance point of an aircraft as claimed in claim 1, characterized in that: The sliding platform is provided with a scale-marked arrow; a scale is provided on the lead screw bracket along the length direction, and the distance between the dynamic balance point and the static balance point of the aircraft can be obtained by reading the scale on the scale.
3. The automatic measuring device for the dynamic balance point of an aircraft as claimed in claim 1, characterized in that: The control module includes a control circuit and an electronic gyroscope; the electronic gyroscope can obtain the pitch data of the screw bracket and transmit it to the control circuit. After the control circuit obtains and solves the pitch motion data, it controls the movement of the screw assembly, so that the sliding platform moves until the screw bracket reaches a horizontal balance position.
4. The automatic measuring device for the dynamic center of gravity of an aircraft as claimed in claim 1, characterized in that: Limiting bosses are arranged at the tops of both ends of the base bracket to limit the extreme pitch angles of the lead screw bracket.
5. The automatic measuring device for the dynamic center of gravity of an aircraft as claimed in claim 4, characterized in that: The maximum pitch angle is ±6.
6. An automatic measuring device for the dynamic center of gravity of an aircraft as claimed in any one of claims 1 to 5, characterized in that: The lead screw assembly includes two lead screws arranged in parallel, a stepper motor I and a stepper motor II; The stepper motor I and the stepper motor II are respectively fixedly arranged at two ends of the lead screw bracket; One end of a lead screw is rotatably connected to the lead screw support, and the other end is connected to the output shaft of the stepper motor I; One end of the other lead screw is rotatably connected to the lead screw bracket, and the other end is connected to the output shaft of the stepper motor II; the sliding platform is simultaneously matched with the threads of the two lead screws; The control module controls the rotation of stepper motor I and stepper motor II, thereby driving the two lead screws to rotate, thereby realizing the movement of the sliding platform on the lead screw assembly.
7. A method for automatically measuring the dynamic center of gravity of an aircraft, based on the automatic measuring device for the dynamic center of gravity of an aircraft as claimed in claim 2, comprising the following steps: Step 1: Install the automatic measuring device on a mobile platform (such as a vehicle), and install the aircraft on the sliding platform of the automatic measuring device, so that the static balance point of the aircraft and the axis of the hinge shaft are in the same vertical plane; Step 2: The mobile platform drives the aircraft to move, and the moving speed of the mobile platform is the take-off speed of the aircraft. At this time, the control module monitors the pitch of the aircraft and controls the screw assembly to control the sliding platform to move in the direction of the elevation angle of the aircraft. Step 3: Read the scale on the ruler in conjunction with the scale mark arrow to obtain the deviation between the dynamic balance point and the static balance point, thereby measuring the dynamic balance point of the aircraft.