Aircraft lift force testing device

Abstract

The utility model provides an aircraft lift force testing device, and belongs to the technical field of lift force testing. Comprising a base, an assembling plate is arranged above the base, a binding belt used for binding an aircraft is arranged at the top of the assembling plate, a tension sensor is assembled on the upper surface of the base, a rope is arranged between the tension sensor and the bottom of the assembling plate in a traction mode, and a supporting column is vertically fixed to the upper surface of the base; the assembly plate is movably placed at the top end of the supporting column, the number of the tension sensors is at least four, the four tension sensors are evenly arranged around the supporting column, and a rope is arranged between each tension sensor and the bottom of the assembly plate in a traction mode. According to the utility model, through the cooperation of the tension sensor and the rope, the lift test of the aircraft is simpler and more convenient, and the practicability is higher.

Description

Technical Field

[0001] The utility model relates to the technical field of lift testing, in particular to an aircraft lift testing device. Background Art

[0002] With the development of electronic technology, the performance of aircraft has been gradually improved and is widely used in military, civilian, scientific research and other fields.

[0003] Lift is one of the main driving forces generated by an aircraft when flying in the air. It enables the aircraft to overcome gravity and stay in the air. The generation of lift is mainly based on the principles of aerodynamics, especially Bernoulli's principle and Newton's third law. When air flows through the wings of an aircraft, due to the difference in shape between the upper and lower surfaces of the wing, the airflow speed increases on the upper surface and slows down on the lower surface, thereby generating a pressure difference and forming lift.

[0004] In order to ensure the performance of the aircraft, the lift of the aircraft needs to be tested during the production and development of the aircraft. Traditional lift testing methods mainly include wind tunnel tests and flight tests. The wind tunnel test simulates the flight environment in a wind tunnel and performs lift tests on the aircraft model at different angles of attack and wind speeds. The lift coefficient and lift characteristics of the aircraft under different flight conditions can be obtained. The flight test collects and analyzes data during the actual flight process to evaluate whether the lift performance of the aircraft meets the design requirements. However, the above two traditional aircraft lift test methods have cumbersome testing processes, and it is difficult to intuitively obtain the evaluation data of the aircraft load. The test of the aircraft lift and load performance is not simple enough. Therefore, the present application provides an aircraft lift test device to meet the needs. Utility Model Content

[0005] The technical problem to be solved by the present invention is to provide an aircraft lift test device to solve the problem that the existing traditional aircraft lift test method has a cumbersome test process and is difficult to intuitively obtain aircraft load evaluation data.

[0006] In order to solve the above technical problems, the present invention provides the following technical solutions:

[0007] An aircraft lift test device includes a base, an assembly plate is arranged above the base, a restraining belt for restraining the aircraft is arranged on the top of the assembly plate, a tension sensor is installed on the upper surface of the base, and a rope is pulled between the tension sensor and the bottom of the assembly plate.

[0008] Optionally, a support column is vertically fixed to the upper surface of the base, and the assembly plate is movably placed on the top of the support column.

[0009] Optionally, at least four tension sensors are provided, and the four tension sensors are evenly arranged around the support column, and a rope is pulled between each tension sensor and the bottom of the assembly plate.

[0010] Optionally, a support plate for carrying an assembly plate is provided at the top end of the support column, and a flange plate connected and fixed to the base is provided at the bottom end of the support column.

[0011] Optionally, a protrusion is provided at the center of the lower surface of the assembly plate, and a groove capable of accommodating the protrusion is provided on the upper surface of the supporting plate.

[0012] Optionally, the protrusion is configured as a spherical structure, and the groove is adapted to fit in the protrusion.

[0013] Optionally, a plurality of lifting rings for tying ropes are evenly arranged around the lower surface of the assembly plate.

[0014] Optionally, a first U-shaped connecting block and a second U-shaped connecting block are fixed to the upper surface of the assembly plate, one end of the restraint belt is hinged to the first U-shaped connecting block, and the other end of the restraint belt is connected to a connecting sleeve that is engaged with the second U-shaped connecting block, and the second U-shaped connecting block is provided with a positioning piece for engaging and positioning the second U-shaped connecting block and the connecting sleeve.

[0015] Optionally, the positioning member includes a sleeve fixed on the end wall of the second U-shaped connecting block, a slider movably arranged in the sleeve, a pin fixed on the side of the slider facing the second U-shaped connecting block, and a spring arranged between the side of the slider away from the second U-shaped connecting block and the inner end wall of the sleeve, the pin passes through the end of the second U-shaped connecting block and is movably connected to the connecting sleeve, and the end of the slider away from the second U-shaped connecting block is also connected to a pull rod, and the pull rod passes through the end surface of the sleeve and is connected to a push handle.

[0016] Optionally, a latex pad is provided on the side of the restraint belt facing the assembly plate.

[0017] Compared with the prior art, the present invention has at least the following beneficial effects:

[0018] In the above scheme, a tension sensor is set up to cooperate with the rope to pull the assembly plate, the aircraft to be tested is placed on the assembly plate, the restraint belt is passed through the aircraft's tripod to restrain it, the aircraft suspension assembly plate is started to rise, the rope pulls the assembly plate, and the tension sensor is pulled by the rope. By collecting the tension detected by the tension sensor, it can be used to evaluate the aircraft's lift, thereby achieving the purpose of testing the aircraft's lift. The overall structure is simple and easy to operate, making the aircraft's lift test easier.

[0019] By arranging at least four tension sensors around the support column, a rope is pulled between each tension sensor and the assembly plate, so that the rope can evenly pull the force on the aircraft, reducing test errors and having higher practical performance.

[0020] By plugging and matching the latch pin with the connecting sleeve, the restraint belt can quickly restrain the aircraft to the assembly plate or detach the aircraft, making the operation more convenient and having higher practicality. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The accompanying drawings, which are incorporated herein and constitute part of the specification, illustrate embodiments of the invention and, together with the description, further serve to explain the principles of the invention and enable those skilled in the relevant art to make and use the invention.

[0022] Figure 1 This is a schematic diagram of the three-dimensional structure of the aircraft lift test device;

[0023] Figure 2 It is a structural diagram of the assembly plate;

[0024] Figure 3 is a structural schematic diagram of the second U-shaped connecting block and the positioning member;

[0025] Figure 4 Schematic diagram of the structure of the bottom of the assembly plate and the support column.

[0026] [reference numerals]

[0027] 1. Base; 2. Assembly plate; 3. Restraint belt; 4. Tension sensor; 5. Rope; 6. Support block; 7. Rubber pad; 8. Support column; 9. First U-shaped connecting block; 10. Second U-shaped connecting block; 11. Connecting sleeve; 12. Positioning piece; 13. Latex pad; 14. Sleeve; 15. Slider; 16. Latch; 17. Pull rod; 18. Spring; 19. Push handle; 20. Bump; 21. Support plate; 22. Groove; 23. Lifting ring; 24. Flange.

[0028] As shown in the figure, in order to clearly implement the structure of the embodiment of the present invention, specific structures and devices are marked in the figure, but this is only for illustrative purposes and is not intended to limit the present invention to the specific structure, devices and environment. According to specific needs, ordinary technicians in this field can adjust or modify these devices and environments. DETAILED DESCRIPTION

[0029] The following describes in detail an aircraft lift test device provided by the present invention, with reference to the accompanying drawings and specific embodiments. It is also noted that, for the sake of completeness, the following embodiments are best and preferred embodiments, and those skilled in the art may employ alternative implementations for known technologies. Furthermore, the accompanying drawings are intended only to provide a more detailed description of the embodiments and are not intended to limit the present invention.

[0030] It should be noted that references in the specification to "one embodiment," "an embodiment," "an exemplary embodiment," "some embodiments," etc. indicate that the described embodiments may include specific features, structures, or characteristics, but not every embodiment necessarily includes such specific features, structures, or characteristics. In addition, when specific features, structures, or characteristics are described in conjunction with an embodiment, it is within the knowledge of persons skilled in the relevant art to implement such features, structures, or characteristics in conjunction with other embodiments (whether or not explicitly described).

[0031] In general, terms can be understood, at least in part, from their use in context. For example, depending at least in part on the context, the term "one or more" as used herein can be used to describe any feature, structure, or characteristic in the singular sense, or can be used to describe a combination of features, structures, or characteristics in the plural sense. Additionally, the term "based on" can be understood as not necessarily intended to convey an exclusive set of factors, but can instead, depending at least in part on the context, allow for the presence of other factors that are not necessarily explicitly described.

[0032] It will be understood that the meanings of “on,” “over,” and “above” in the present invention should be interpreted in the broadest manner, so that “on” means not only “directly on” something but also includes the meaning of being “on” something with intervening features or layers, and “on” or “above” means not only “on” or “above” something but also includes the meaning of being “on” or “above” something with no intervening features or layers.

[0033] Additionally, spatially relative terms such as "below," "beneath," "lower," "above," and "upper" may be used herein for descriptive convenience to describe the relationship of one element or feature to another element or features, as illustrated in the accompanying drawings. Spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the accompanying drawings. The device may be oriented in other ways, and the spatially relative descriptors used herein should be similarly interpreted accordingly.

[0034] like Figure 1 and Figure 2As shown, an embodiment of the present invention provides an aircraft lift test device, including a base 1, an assembly plate 2 is provided above the base 1, and a restraining belt 3 for restraining the aircraft is provided on the top of the assembly plate 2, and a tension sensor 4 is provided on the upper surface of the base 1, and a rope 5 is pulled between the tension sensor 4 and the bottom of the assembly plate 2. The aircraft to be tested is placed on the assembly plate 2, and the restraining belt 3 is passed through the aircraft's tripod for restraint. The aircraft suspension assembly plate 2 is started to fly up, and the rope 5 pulls the assembly plate 2, and the tension sensor 4 is pulled by the rope 5. By collecting the tension detected by the tension sensor 4, it can be used to evaluate the aircraft lift, thereby achieving the purpose of testing the aircraft lift. The overall structure is simple and easy to operate, making the aircraft lift test simpler; support blocks 6 are provided at the four corners of the bottom of the base 1, and rubber pads 7 are provided at the bottom of the support blocks 6 for stably supporting the base 1.

[0035] like Figure 1 and Figure 4 As shown, a support column 8 is vertically fixed on the upper surface of the base 1, and the assembly plate 2 is movably placed on the top of the support column 8. A support plate 21 for carrying the assembly plate 2 is provided on the top of the support column 8, and a flange 24 connected and fixed to the base 1 is provided at the bottom of the support column 8. A protrusion 20 is provided in the center of the lower surface of the assembly plate 2, and a groove 22 for accommodating the protrusion 20 is provided on the upper surface of the support plate 21. The protrusion 20 is set to a spherical structure, and the groove 22 is adapted to fit with the protrusion 20 to provide a support platform for the assembly plate 2, which is beneficial to the take-off and landing during the aircraft test.

[0036] like Figure 1 and Figure 4 As shown, there are at least four tension sensors 4, which are evenly arranged around the support column 8. A rope 5 is pulled between each tension sensor 4 and the bottom of the assembly plate 2. A plurality of rings 23 for tying the rope 5 are evenly arranged around the lower surface of the assembly plate 2. This structural method enables the rope 5 to evenly pull the force on the aircraft, reducing the test error.

[0037] like Figure 1 and Figure 2As shown, a first U-shaped connecting block 9 and a second U-shaped connecting block 10 are fixed to the upper surface of the assembly plate 2, one end of the restraining belt 3 is hinged to the first U-shaped connecting block 9, and the other end of the restraining belt 3 is connected to a connecting sleeve 11 that is engaged with the second U-shaped connecting block 10, and a positioning member 12 is provided on the second U-shaped connecting block 10 for engaging and positioning the second U-shaped connecting block 10 and the connecting sleeve 11, and the positioning member 12 includes a sleeve 14 fixed on the end wall of the second U-shaped connecting block 10, a slider 15 movably arranged in the sleeve 14, a pin 16 fixed on the side of the slider 15 facing the second U-shaped connecting block 10, and a spring 18 provided between the side of the slider 15 away from the second U-shaped connecting block 10 and the inner end wall of the sleeve 14, and the pin 16 passes through the second The end of the U-shaped connecting block 10 is movably connected to the connecting sleeve 11, and the end of the slider 15 away from the second U-shaped connecting block 10 is also connected to a pull rod 17. The pull rod 17 passes through the end face of the sleeve 14 and is connected to a push handle 19. A latex pad 13 is provided on the side of the restraint belt 3 facing the assembly plate 2. The restraint belt 3 passes through the aircraft's tripod so that the connecting sleeve 11 is embedded in the second U-shaped connecting block 10. The spring 18 is used to push the slider 15 so that the pin 16 is connected to the connecting sleeve 11, so that the aircraft can be restrained to the assembly plate 2. The setting of the latex pad 13 can reduce the wear on the aircraft's tripod. By pulling the push handle 19 to drive the pull rod 17 to disengage the pin 16 from the connecting sleeve 11, the restraint belt 3 can be pulled out of the aircraft's tripod and the aircraft can be removed from the assembly plate 2.

[0038] The working principle of the technical solution provided by the utility model is as follows:

[0039] During use, the aircraft to be tested is placed on the assembly plate 2, the restraint belt 3 is passed through the aircraft's tripod, the connecting sleeve 11 is embedded in the second U-shaped connecting block 10, and the elastic force of the spring 18 is used to push the slider 15 to connect the pin 16 with the connecting sleeve 11. The restraint belt 3 cooperates with the latex pad 13 to restrain the aircraft to the assembly plate 2. Thus, the aircraft suspension assembly plate 2 is started to rise, and the four ropes 5 pull the assembly plate 2. The four tension sensors 4 are then pulled by the four ropes 5. By collecting the tension detected by the four tension sensors 4, it can be used to evaluate the aircraft lift, thereby achieving the purpose of testing the aircraft lift. The overall structure is simple and easy to operate, and the four tension sensors 4 are arranged around the support column 8, so that the four ropes 5 can evenly pull the aircraft, reducing the test error and having high practical performance.

[0040] This invention encompasses any alternatives, modifications, equivalents, and solutions that do not depart from the spirit and scope of this invention. To provide a thorough understanding of this invention, specific details are described in detail in the following preferred embodiments of this invention, but those skilled in the art will be able to fully understand this invention without these detailed descriptions. Furthermore, to avoid unnecessary confusion regarding the essence of this invention, well-known methods, processes, procedures, components, and circuits are not described in detail.

[0041] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications should also be regarded as within the scope of protection of the present invention.

Claims

1. An aircraft lift test device, comprising a base, characterized in that: An assembly plate is provided above the base, a restraining belt for restraining the aircraft is provided on the top of the assembly plate, a tension sensor is provided on the upper surface of the base, and a rope is pulled between the tension sensor and the bottom of the assembly plate.

2. The aircraft lift test device according to claim 1, characterized in that: A support column is vertically fixed on the upper surface of the base, and the assembly plate is movably placed on the top of the support column.

3. The aircraft lift test device according to claim 2, characterized in that: At least four tension sensors are provided, and the four tension sensors are evenly arranged around the support column. A rope is pulled between each tension sensor and the bottom of the assembly plate.

4. The aircraft lift test device according to claim 2, characterized in that: The top end of the support column is provided with a supporting plate for carrying the assembly plate, and the bottom end of the support column is provided with a flange connected and fixed to the base.

5. The aircraft lift test device according to claim 4, characterized in that: A protrusion is provided at the center of the lower surface of the assembly plate, and a groove capable of accommodating the protrusion to be embedded is provided on the upper surface of the supporting plate.

6. The aircraft lift test device according to claim 5, characterized in that: The protrusion is configured as a spherical structure, and the groove is adapted to fit in the protrusion.

7. The aircraft lift test device according to claim 3, characterized in that: A plurality of lifting rings for rope binding are evenly arranged on the circumference of the lower surface of the assembly plate.

8. The aircraft lift test device according to claim 1, characterized in that: A first U-shaped connecting block and a second U-shaped connecting block are fixed to the upper surface of the assembly plate, one end of the restraint belt is hinged to the first U-shaped connecting block, and the other end of the restraint belt is connected to a connecting sleeve that is engaged with the second U-shaped connecting block, and a positioning piece is provided on the second U-shaped connecting block for engaging and positioning the second U-shaped connecting block and the connecting sleeve.

9. The aircraft lift test device according to claim 8, characterized in that: The positioning member includes a sleeve fixed on the end wall of the second U-shaped connecting block, a slider movably arranged in the sleeve, a pin fixed on the side of the slider facing the second U-shaped connecting block, and a spring arranged between the side of the slider away from the second U-shaped connecting block and the inner end wall of the sleeve. The pin passes through the end of the second U-shaped connecting block and is movably plugged into the connecting sleeve. The end of the slider away from the second U-shaped connecting block is also connected to a pull rod, and the pull rod passes through the end surface of the sleeve and is connected to a push handle.

10. The aircraft lift test device according to claim 1, characterized in that: A latex pad is provided on one side of the restraint belt facing the assembly plate.

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