Simulated flight condition test bench
By designing a simulated flight condition test bench suitable for small drones, the problem of lack of small test benches in the prior art is solved, and effective simulation and parameter determination of pitch and rolling motion of small aircraft are realized.
Patent Information
- Application Number
- CN202421867871.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-08-02
- Publication Date
- 2025-05-02
- Estimated Expiration
- 2034-08-02
AI Technical Summary
There is a lack of equipment suitable for small drones to conduct simulated flight conditions tests in the prior art. Traditional large flight simulation test benches are not suitable for small drones, and there is a lack of general small flight conditions test benches on the market.
A test bench simulated flight conditions is designed, including a base, pitch unit, support plate rotary member and rolling unit. The overall size is small and suitable for small drones to conduct simulation experiments. The pitch and rolling movement of the aircraft are simulated through the pitch unit and rolling unit.
The simulated flight conditions test of small drones is realized. The overall size is small and easy to use. It can effectively simulate the pitch and rolling motion state of small aircraft and measure relevant parameters.
Smart Images
Figure CN222820271U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of flight simulation, in particular to a simulated flight condition test bench. Background Art
[0002] With the advancement of technology, small UAVs are becoming more and more useful on the battlefield and are being used more and more widely. Before UAVs leave the factory, their performance often needs to be tested. The simulated flight attitude test bench is a specially designed device used to simulate the state of an aircraft under various flight attitude conditions. However, the traditional large-scale flight simulation test bench is too large and inconvenient to use, and is not suitable for testing small UAVs. There is currently no mature and universal small flight condition test bench on the market. Therefore, there is an urgent need for a simulated flight condition test bench that is small in size, easy to use, and suitable for simulation experiments on small UAVs. Utility Model Content
[0003] The utility model aims to provide a simulated flight condition test bench to solve the problems existing in the above-mentioned prior art. The utility model has small size, is easy to use, and is suitable for conducting simulation experiments on small unmanned aerial vehicles.
[0004] To achieve the above purpose, the utility model provides the following solutions:
[0005] The utility model provides a simulated flight condition test bench, comprising: a base, a pitch unit, a support plate rotating member and a roll unit, the base comprising a bottom frame and a bracket, the bracket is fixedly connected to the upper side of the bottom frame, the pitch unit is fixedly arranged on the bracket, the support plate is rotatably connected to the pitch unit around a first straight line, the roll unit is fixedly connected to the upper side of the support plate, the rotating member is rotatably connected to the roll unit around a second straight line, the rotating member is used to fix a test piece, the first straight line and the second straight line are perpendicular to each other, the bottom frame is a square frame with a side length not greater than 1000mm, the support plate is a rectangular plate with a long side not greater than 1600mm, and the vertical distance from the highest point of the roll unit to a plane parallel to the bottom surface of the base is not greater than 2200mm. Preferably, the pitch unit includes a first base, a first rotating shaft and a pitch drive assembly, the first rotating shaft is rotatably connected to the base, the axis of the first rotating shaft coincides with the first straight line, the support plate is fixedly connected to the first rotating shaft, the pitch drive assembly is fixedly disposed on the first base, and the output end of the pitch drive assembly is connected to the first rotating shaft.
[0006] Preferably, the first rotating shaft is rotatably connected to the first base via two sleeves, the two sleeves are rotatably sleeved on both ends of the first rotating shaft respectively, the first base has two oppositely arranged mounting holes, the two sleeves are fixedly arranged in the mounting holes respectively.
[0007] Preferably, the support plate is fixedly connected to the first rotating shaft via a fixing member, the fixing member is fixedly sleeved on the first rotating shaft, and the lower side of the support plate is fixedly connected to the fixing member.
[0008] Preferably, the rolling unit includes a second base, a second rotating shaft and a rolling drive assembly, the second base is fixedly connected to the upper side of the support plate, the second rotating shaft is rotatably connected to the second base, the axis of the second rotating shaft coincides with the second straight line, the rolling drive assembly is fixedly set on the support plate, the output end of the rolling drive assembly is connected to the second rotating shaft, and the second rotating shaft is used to fix the specimen.
[0009] Preferably, the rotating member is a frame-shaped structure, and the rotating member is fixedly connected to the second rotating shaft.
[0010] Preferably, the pitch drive assembly and the roll drive assembly both include a motor and a reducer, the respective output shafts of the two motors are connected to the input ends of the two reducers, and the output shafts of the two reducers respectively form the output ends of the pitch drive assembly and the roll drive assembly.
[0011] Preferably, it also includes a controller, which is signal-connected to the pitch drive component and the roll drive component, and the controller can control the pitch drive component and the roll drive component to work simultaneously or individually to simulate the aircraft performing rolling movement and pitching movement simultaneously or individually.
[0012] Compared with the prior art, the utility model has achieved the following technical effects:
[0013] The simulated flight condition test bench provided by the utility model has a bottom frame which is a square frame with a side length of no more than 1000mm, a support plate which is a rectangular plate with a long side of no more than 1600mm, and a vertical distance from the highest point of the rolling unit to the bottom surface of the base which is no more than 2200mm. The overall size is small and the use is more convenient. It is suitable for testing small specimens and can simulate the motion state of a small aircraft during pitch and roll and measure relevant parameters. BRIEF DESCRIPTION OF THE DRAWINGS
[0014] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.
[0015] Figure 1 A three-dimensional structural diagram of the simulated flight condition test bench provided by the utility model;
[0016] In the figure: 1-base, 11-bottom frame, 12-bracket, 2-pitch unit, 21-first base, 22-first rotation axis, 221-sleeve, 23-pitch drive assembly, 3-support plate, 4-fixing member, 5-roll unit, 51-second base, 52-second rotation axis, 53-roll drive assembly, 54-rotating member. DETAILED DESCRIPTION
[0017] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.
[0018] The utility model aims to provide a simulated flight condition test bench to solve the problems existing in the above-mentioned prior art. The utility model has small size, is easy to use, and is suitable for conducting simulation experiments on small unmanned aerial vehicles.
[0019] In order to make the above-mentioned purposes, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below in conjunction with the accompanying drawings and specific implementation methods.
[0020] The utility model provides a flight condition simulation test bench, such as Figure 1 As shown, it includes: a base 1, a pitch unit 2, a support plate 3 and a roll unit 5, the base 1 includes a bottom frame 11 and a bracket 12, the bracket 12 is fixedly connected to the upper side of the bottom frame 11, the pitch unit 2 is fixedly arranged on the bracket 12, the support plate 3 is connected to the pitch unit 2 and rotates around a first straight line, the roll unit 5 is fixedly connected to the upper side of the support plate 3, the test piece is connected to the roll unit 5 and is used to rotate around a second straight line, the first straight line and the second straight line are perpendicular to each other, the bottom frame 11 is a square frame with a side length not greater than 1000mm, the support plate 3 is a rectangular plate with a long side not greater than 1600mm, and the vertical distance from the highest point of the roll unit 5 to the plane parallel to the bottom surface of the base 1 is not greater than 2200mm.
[0021] The simulated flight condition test bench provided by the utility model has a bottom frame 11 which is a square frame with a side length of no more than 1000 mm, a support plate 3 which is a rectangular plate with a long side of no more than 1600 mm, and a vertical distance from the highest point of the roll unit 5 to the bottom surface of the base 1 which is no more than 2200 mm. The overall size is small and the use is more convenient. It is suitable for testing small specimens and can simulate the motion state of a small aircraft during pitch and roll through the pitch unit and the roll unit to measure relevant parameters.
[0022] In a preferred implementation of the present embodiment, the pitch unit 2 includes a first base 21, a first rotating shaft 22 and a pitch driving assembly 23, the first rotating shaft 22 is rotatably connected to the base, the axis of the first rotating shaft 22 coincides with the first straight line, the support plate 3 is fixedly connected to the first rotating shaft 22, the pitch driving assembly 23 is fixedly arranged on the first base 21, and the output end of the pitch driving assembly 23 is fixedly connected to the first rotating shaft 22. During the test, the pitch driving assembly 23 can drive the first rotating shaft 22 to rotate around the first straight line, and the support plate 3 can rotate around the first straight line to drive the specimen on the roll unit 5 to rotate around the first straight line to simulate the pitch motion process of the aircraft. Wherein, when the support plate 3 is kept horizontal, the rotation angle of the support plate 3 in the clockwise and counterclockwise directions is not greater than 70°.
[0023] In a preferred implementation of the present embodiment, the first rotating shaft 22 is rotatably connected to the first base 21 through two shaft sleeves 221. The two shaft sleeves 221 are rotatably sleeved at the two ends of the first rotating shaft 22 respectively. The first base 21 has two mounting holes arranged opposite to each other, and the two shaft sleeves 221 are fixedly arranged in the mounting holes respectively. During the rotation of the first rotating shaft 22, since the first rotating shaft 22 needs to bear the weight of the support plate, the rolling unit 5 and the test piece, the torque at the connection of the first rotating shaft 22 is also relatively large. The use of the shaft sleeves 221 can improve the reliability of the connection between the first rotating shaft 22 and the first base 21.
[0024] In a preferred implementation of this embodiment, the support plate 3 is fixedly connected to the first rotating shaft 22 through the fixing member 4, the fixing member 4 is fixedly sleeved on the first rotating shaft 22, and the lower side of the support plate 3 is fixedly connected to the fixing member 4. The connection mode in which the fixing member 4 is sleeved on the first rotating shaft 22 is more stable.
[0025] In a preferred implementation of this embodiment, the rolling unit 5 includes a second base 51, a second rotating shaft 52 and a rolling drive assembly 53. The second base 51 is fixedly connected to the upper side of the support plate 3, the second rotating shaft 52 is rotatably connected to the second base 51, the axis of the second rotating shaft 52 coincides with the second straight line, the rolling drive assembly 53 is fixedly set on the support plate 3, the output end of the rolling drive assembly 53 is connected to the second rotating shaft 52, and the second rotating shaft 52 is used to fix the test piece. When conducting the test, the rolling drive assembly 53 drives the second rotating shaft 52 to rotate around the second straight line, thereby driving the test piece to rotate around the second rotating shaft 52 to simulate the rolling motion. Among them, the line connecting the position of the test piece corresponding to the head of the aircraft and the position corresponding to the tail of the aircraft is perpendicular to the second straight line.
[0026] In order to facilitate the installation of the test piece, in a preferred implementation of this embodiment, the rotating member 54 is a frame-shaped structure, and the rotating member 54 is fixedly connected to the second rotating shaft 52. The rotating member 54 is preferably a rectangular frame, and two through holes are arranged on the two edges of the rectangular frame, and two second rotating shafts 52 are arranged. One end of each of the two second rotating shafts 52 is fixedly connected in the through hole, and the other end of each is rotatably connected to the second base 51. When the support plate 3 is kept horizontal and the rotating member 54 is in a vertical state, the vertical distance from the top edge of the rotating member 54 to the bottom surface of the bottom frame 11 is not greater than 2200mm. Among them, a screw hole or a plug hole can be opened on the rotating member 54, and a screw or a pin can be set on the test piece, and the test piece is fixed to the rotating member 54 by bolt connection or plugging.
[0027] In a preferred implementation manner of this embodiment, the pitch drive assembly 23 and the roll drive assembly 53 both include motors and reducers, the respective output shafts of the two motors are connected to the input ends of the two reducers, and the output shafts of the two reducers respectively form the output ends of the pitch drive assembly 23 and the roll drive assembly 53.
[0028] In a preferred implementation of this embodiment, a controller is also included. The controller is connected to the pitch drive assembly 23 and the roll drive assembly 53 by signals. The controller can control the pitch drive assembly 23 and the roll drive assembly 53 to work simultaneously or separately to simulate the aircraft to perform rolling and pitching movements simultaneously or separately. The controller can improve the automation level of the device. Among them, the controller is built with a PLC intelligent control system, and the controller and the pitch drive assembly 23 and the roll drive assembly 53 are preferably connected by signals through a 485 communication line.
[0029] The present invention uses specific examples to illustrate the principle and implementation of the present invention. The above examples are only used to help understand the method and core idea of the present invention. At the same time, for those skilled in the art, according to the idea of the present invention, there will be changes in the specific implementation and application scope. In summary, the content of this specification should not be understood as limiting the present invention.
Claims
1. A simulated flight condition test bench, characterized in that: include: A base, a pitch unit, a support plate rotating member and a rolling unit, wherein the base includes a bottom frame and a bracket, the bracket is fixedly connected to the upper side of the bottom frame, the pitch unit is fixedly arranged on the bracket, the support plate is connected to the pitch unit by rotation around a first straight line, the rolling unit is fixedly connected to the upper side of the support plate, the rotating member is connected to the rolling unit by rotation around a second straight line, the rotating member is used to fix a test piece, the first straight line and the second straight line are perpendicular to each other, the bottom frame is a square frame with a side length not exceeding 1000mm, the support plate is a rectangular plate with a long side not exceeding 1600mm, and the vertical distance from the highest point of the rolling unit to a plane parallel to the bottom surface of the base is not greater than 2200mm.
2. The simulated flight condition test bench according to claim 1, characterized in that: The pitch unit includes a first base, a first rotating shaft and a pitch driving assembly, the first rotating shaft is rotatably connected to the base, the axis of the first rotating shaft coincides with the first straight line, the support plate is fixedly connected to the first rotating shaft, the pitch driving assembly is fixedly arranged on the first base, and the output end of the pitch driving assembly is connected to the first rotating shaft.
3. The simulated flight condition test bench according to claim 2, characterized in that: The first rotating shaft is rotatably connected to the first base through two sleeves, and the two sleeves are rotatably sleeved on both ends of the first rotating shaft respectively. The first base has two oppositely arranged mounting holes, and the two sleeves are fixedly arranged in the mounting holes respectively.
4. The simulated flight condition test bench according to claim 2, characterized in that: The support plate is fixedly connected to the first rotating shaft via a fixing piece, the fixing piece is fixedly sleeved on the first rotating shaft, and the lower side of the support plate is fixedly connected to the fixing piece.
5. The simulated flight condition test bench according to claim 2, characterized in that: The rolling unit includes a second base, a second rotating shaft and a rolling drive assembly, the second base is fixedly connected to the upper side of the support plate, the second rotating shaft is rotatably connected to the second base, the axis of the second rotating shaft coincides with the second straight line, the rolling drive assembly is fixedly set on the support plate, the output end of the rolling drive assembly is connected to the second rotating shaft, and the second rotating shaft is used to fix the specimen.
6. The simulated flight condition test bench according to claim 5, characterized in that: The rotating member is a frame-shaped structure, and the rotating member is fixedly connected to the second rotating shaft.
7. The simulated flight condition test bench according to claim 5, characterized in that: The pitch drive assembly and the roll drive assembly both include a motor and a reducer, the respective output shafts of the two motors are connected to the input ends of the two reducers, and the output shafts of the two reducers respectively form the output ends of the pitch drive assembly and the roll drive assembly.
8. The simulated flight condition test bench according to claim 5, characterized in that: It also includes a controller, which is connected to the pitch drive assembly and the roll drive assembly by signal. The controller can control the pitch drive assembly and the roll drive assembly to work simultaneously or individually to simulate the aircraft performing rolling movement and pitching movement simultaneously or individually.