A rigid device for measuring the initial speed and the swing distance of an aircraft
Patent Information
- Application Number
- CN202521978646.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-09-15
- Publication Date
- 2026-10-20
- Estimated Expiration
- 2035-09-15
AI Technical Summary
[0002]以往的测量飞行器初速和摆动距离的刚性装置是悬挂式的，利用悬挂的绳索进行测量，由于不具有足够的刚度，发射时会发生弯曲变形，产生弧度
[0017]上述技术方案所提供的测量飞行器初速和摆动距离的刚性装置，操作简单方便，便于固定、拆卸，摆杆具有刚性，摆动时不会产生弧度，基本不受风力的影响，能够准确测量数据。
Smart Images
Figure CN224873276U_ABST
Abstract
Description
Technical Field
[0001] This utility model belongs to the field of testing tooling technology, and relates to a rigid device for measuring the initial velocity and swing distance of an aircraft. It is used to measure the dynamic imbalance impulse during the launch of an aircraft, and to test the influence of the aircraft's folding wings and rudder blades on the dynamic imbalance impulse during the launch. Background Technology
[0002] Traditional rigid devices for measuring the initial velocity and swing distance of aircraft are suspension-type, using suspended ropes for measurement. Due to insufficient rigidity, they bend and deform during launch, producing curvature. This is detrimental to observation, measurement, and data calculation during use. Summary of the Invention
[0003] (I) Purpose of the Invention
[0004] The purpose of this invention is to provide a rigid device for measuring the initial velocity and swing distance of an aircraft, used to measure the dynamic imbalance impulse during aircraft launch; and to test the influence of the aircraft's folding wings and rudder blades on the dynamic imbalance impulse during launch.
[0005] (II) Technical Solution
[0006] To solve the above-mentioned technical problems, this utility model provides a rigid device for measuring the initial velocity and swing distance of an aircraft, which includes an upper mounting plate 1, a bracket 3, a swing rod 15, a bracket 12, and a pointer 7; the bracket 3 is a three-dimensional frame structure; the upper mounting plate 1 is installed on the top of the bracket 3; the pointer 7 is fixed at the bottom center of the bracket 3; there are two swing rods 15, the upper end of which is swayably installed on the upper mounting plate 1, and the lower end is connected to the bracket 12, which is located above the pointer 7 and is used to place the aircraft to be tested; when the rigid device is in a static state, the top of the pointer 7 points to the center of the bracket 12 and the center of mass of the aircraft.
[0007] Furthermore, the support 3 is a four-sided pyramidal frame structure, including an upper frame and a lower frame arranged in parallel, and four connecting beams that connect the four corners of the upper frame and the four corners of the lower frame respectively.
[0008] Furthermore, the upper hanging plate 1 is fixed to the upper frame of the bracket 3 by four hexagonal nuts; two upper bearings 2 are provided on the upper hanging plate 1, and the upper ends of the two swing rods 15 are respectively connected to the two upper bearings 2.
[0009] Furthermore, the lower ends of the two swing arms 15 are fixedly connected to the bracket 12 via right-angle supports 14.
[0010] Furthermore, the right-angle support 14 and the swing rod 15 are connected by an M24 fine-threaded hexagonal bolt 4, a flat washer 5, and a spring washer 6.
[0011] Furthermore, a tray 13 is arranged on the bracket 12, and the aircraft is arranged on the tray 13.
[0012] Furthermore, the bottom of the bracket 12 is suspended and connected to the counterweight 10 by connecting screws 11.
[0013] Furthermore, the four corners of the bottom of the lower frame of the bracket 3 are respectively fixed with ground stakes 8, which facilitates fixing the rigid device on uneven ground.
[0014] Furthermore, a pointer base plate 9 is fixedly installed on the lower frame of the bracket 3, and a pointer 7 is fixedly installed on the pointer base plate 9.
[0015] Furthermore, the upper bearing 2 is a ball bearing; the two suspended swing arms 15 are arranged in parallel and of equal length.
[0016] (III) Beneficial Effects
[0017] The rigid device for measuring the initial velocity and swing distance of an aircraft provided by the above technical solution is simple and convenient to operate, easy to fix and disassemble, the swing arm is rigid and will not produce arc when swinging, and is basically unaffected by wind force, and can accurately measure data. Attached Figure Description
[0018] Figure 1 This is a schematic diagram of the rigid device for measuring the initial velocity and swing distance of an aircraft according to an embodiment of the present invention. Detailed Implementation
[0019] To make the objectives, contents, and advantages of this utility model clearer, the specific embodiments of this utility model will be described in further detail below with reference to the accompanying drawings and examples.
[0020] Reference Figure 1 As shown, the rigid device for measuring the initial velocity and swing distance of an aircraft in this embodiment includes an upper mounting plate 1, a bracket 3, a swing rod 15, a bracket 12, and a pointer 7. The bracket 3 is a three-dimensional frame structure. The upper mounting plate 1 is installed on the top of the bracket 3. The pointer 7 is fixed at the bottom center of the bracket 3. There are two swing rods 15, the upper end of which is swingably installed on the upper mounting plate 1, and the lower end is connected to the bracket 12. The bracket 12 is located above the pointer 7 and is used to place the aircraft under test. When the rigid device is in a static state, the top of the pointer 7 points to the center of the bracket 12 and the center of mass of the aircraft.
[0021] The support 3 is a four-sided pyramidal frame structure, including an upper frame and a lower frame arranged in parallel, as well as four connecting beams that connect the four corners of the upper frame and the four corners of the lower frame respectively.
[0022] The upper hanging plate 1 is fixed to the upper frame of the bracket 3 by four hexagonal nuts 16, 17, 18, and 19.
[0023] Two upper bearings 2 are installed on the upper hanging plate 1, and the upper ends of the two swing rods 15 are respectively connected to the two upper bearings 2.
[0024] The lower ends of the two swing arms 15 are fixedly connected to the bracket 12 via right-angle supports 14.
[0025] The right-angle support 14 and the swing arm 15 are connected by an M24 fine-threaded hex bolt 4, a flat washer 5, and a spring washer 6.
[0026] A tray 13 is arranged on the bracket 12, and the aircraft is arranged on the tray 13.
[0027] The counterweight 10 is suspended at the bottom of the bracket 12 by connecting screws 11.
[0028] The four corners of the bottom of the lower frame of bracket 3 are fixed with ground stakes 8, which makes it easy to fix the rigid device on uneven ground.
[0029] The pointer base plate 9 is fixedly installed on the lower frame of the bracket 3, and the pointer 7 is fixedly installed on the pointer base plate 9.
[0030] In this embodiment, the upper bearing 2 is a well-lubricated ball bearing; the two suspended swing arms 15 are arranged in parallel and of equal length, and the suspension has sufficient rigidity to ensure that the suspension does not produce curvature after launch and will not affect the deformation and torsion of the maximum horizontal displacement test. The center of gravity of the counterweight and the center of gravity of the aircraft are located in the same plane, and the center of gravity of the counterweight and the center of gravity of the aircraft are located between the brackets.
[0031] The pendulum 15 is 2000mm long and can test a maximum distance of 100mm.
[0032] In this embodiment, when the measurement work is carried out, the rigid device is assembled and connected according to the test conditions. Before launch, the device should be stationary in the equilibrium position. During each launch, the swing arm swings to simulate the displacement change of the aircraft. The high-speed video recording device records the changes over time, and then the maximum horizontal displacement after launch is measured.
[0033] The above description is only a preferred embodiment of the present utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of the present utility model, and these improvements and modifications should also be considered within the protection scope of the present utility model.
Claims
1. A rigid device for measuring the initial velocity and oscillation distance of an aircraft, characterized in that, It includes an upper mounting plate (1), a bracket (3), a swing rod (15), a bracket (12), and a pointer (7); the bracket (3) is a three-dimensional frame structure; the upper mounting plate (1) is installed on the top of the bracket (3); the pointer (7) is fixed at the bottom center of the bracket (3); there are two swing rods (15), the upper end of which is swingable and installed on the upper mounting plate (1), and the lower end is connected to the bracket (12). The bracket (12) is located above the pointer (7), and the aircraft to be tested is placed on the bracket (12); when the rigid device is in a static state, the top of the pointer (7) points to the center of the bracket (12) and the center of mass of the aircraft.
2. The rigid device for measuring the initial velocity and oscillation distance of an aircraft as described in claim 1, characterized in that, The support (3) is a four-sided pyramidal frame structure, including an upper frame and a lower frame arranged in parallel, and four connecting beams that connect the four corners of the upper frame and the four corners of the lower frame respectively.
3. The rigid device for measuring the initial velocity and oscillation distance of an aircraft as described in claim 2, characterized in that, The upper hanging plate (1) is fixed to the upper frame of the bracket (3) by four hexagonal nuts; two upper bearings (2) are provided on the upper hanging plate (1), and the upper ends of the two swing rods (15) are respectively connected to the two upper bearings (2).
4. The rigid device for measuring the initial velocity and oscillation distance of an aircraft as described in claim 3, characterized in that, The lower ends of the two swing rods (15) are fixedly connected to the bracket (12) by right-angle supports (14).
5. The rigid device for measuring the initial velocity and oscillation distance of an aircraft as described in claim 4, characterized in that, The right-angle support (14) and the swing rod (15) are connected by an M24 fine-thread hexagonal bolt (4), a flat washer (5), and a spring washer (6).
6. The rigid device for measuring the initial velocity and oscillation distance of an aircraft as described in claim 5, characterized in that, The bracket (12) is equipped with a tray (13), and the aircraft is placed on the tray (13).
7. The rigid device for measuring the initial velocity and oscillation distance of an aircraft as described in claim 6, characterized in that, The bracket (12) is suspended from the bottom by a connecting screw (11) to connect the counterweight (10).
8. The rigid device for measuring the initial velocity and oscillation distance of an aircraft as described in claim 7, characterized in that, The four corners of the bottom of the lower frame of the bracket (3) are fixed with ground stakes (8) to facilitate the fixing of the rigid device on uneven ground.
9. The rigid device for measuring the initial velocity and oscillation distance of an aircraft as described in claim 8, characterized in that, The pointer base plate (9) is fixedly installed on the lower frame of the bracket (3), and the pointer (7) is fixedly installed on the pointer base plate (9).
10. The rigid device for measuring the initial velocity and oscillation distance of an aircraft as described in claim 9, characterized in that, The upper bearing (2) is a ball bearing; the two suspended swing arms (15) are arranged in parallel and of equal length.