Interstage free separation structure and two-body free separation wind tunnel test device

Abstract

The present application relates to the technical field of aerodynamic test device, and provides a stage free separation structure and a two-body free separation wind tunnel test device, the stage free separation structure comprises a target aircraft model, the target aircraft model comprises a front stage model and a rear stage model, the rear end surface of the front stage model and the front end surface of the rear stage model are abutted, and the two are fixed by a first electromagnet and a first electromagnetic armature, a power supply and a controller are arranged in the target aircraft model, the power supply is electrically connected with the electromagnet, and the controller is electrically connected with the power supply; a force generating component is arranged between the rear end surface of the front stage model and the front end surface of the rear stage model, so as to generate thrust to overcome the magnetic force generated by the residual magnetism of the first electromagnet. The present application can not only make the front stage model and the rear stage model freely separated, but also make the front stage model and the rear stage model separated at a certain relative speed.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aerodynamic test devices, in particular to an interstage free separation structure and a two-body free separation wind tunnel test device. BACKGROUND

[0002] The free release test of the aircraft can be generally divided into two kinds, one is pressure release and free release, and the free release can be further divided into single-body release (one fixed and one separated) and two-body release (after the two aircrafts as a whole are separated from the carrier aircraft, the two aircrafts are separated from each other).

[0003] During the separation between the two aircrafts in the two-body release (i.e. interstage separation), the flight flow and the rear aircraft form a complex unsteady interference in the tail flow field of the front aircraft, which has a great influence on the aerodynamic force borne by the front aircraft and the rear aircraft, i.e. the separation process, and therefore, how to safely and effectively separate the two aircrafts in the two-body release is particularly important.

[0004] In the prior art, for example, the patent with the publication number "CN104458201A" discloses an interstage separation wind tunnel free flight test device, which provides a separation mode to separate the two aircrafts from each other, so as to perform relevant tests, however, the separation mode provided in the technical solution of the patent can only separate the two aircrafts at a certain relative speed, and cannot realize the free separation between the two aircrafts (i.e. the separation between the two aircrafts in the state of only aerodynamic force and gravity without other external forces), and is difficult to be applied to the test in which the two aircrafts need to be freely separated. SUMMARY

[0005] The present application aims to provide an interstage free separation structure and a two-body free separation wind tunnel test device, which solves the technical problem that the prior art cannot realize the free separation between the two aircrafts.

[0006] The embodiments of the present application are implemented by the following technical solutions:

[0007] The present application provides an interstage free separation structure, which comprises a target aircraft model, the target aircraft model comprises a front stage model and a rear stage model, the rear end surface of the front stage model and the front end surface of the rear stage model are abutted, and the two are fixed by the first electromagnet and the first electromagnetic armature, the inside of the target aircraft model is provided with a power supply and a controller, the power supply is electrically connected with the electromagnet, and the controller is electrically connected with the power supply; a force generating component is arranged between the rear end surface of the front stage model and the front end surface of the rear stage model, so as to generate a thrust to overcome the magnetic force generated by the residual magnetism of the first electromagnet.

[0008] Optionally, the force generating component is a spring, and the rear end face of the front stage model or the front end face of the rear stage model is provided with a blind hole for pressing the force generating component.

[0009] Optionally, the force generating component comprises a compression cylinder, a compression piston and a piston rod, the compression piston is arranged in the compression cylinder, the piston rod is connected with the compression piston and extends out of the compression cylinder, and the rear end face of the front stage model or the front end face of the rear stage model is provided with a blind hole for pressing the force generating component.

[0010] Optionally, the force generating component comprises first and second magnets that repel each other, one of the first and second magnets is arranged on the rear end face of the front stage model, and the other is arranged on the front end face of the rear stage model.

[0011] Optionally, at least two first positioning pins are arranged between the rear end face of the front stage model and the front end face of the rear stage model.

[0012] Optionally, one end of the first positioning pin is in a tapered structure.

[0013] The application also provides a two-body free separation wind tunnel test device, comprising a hanger and the inter-stage free separation structure according to any one of the above, the front stage model and the rear stage model of the inter-stage free separation structure are connected with the hanger through the separation mechanism, the target aircraft model is provided with a positive electrode core and a negative electrode core, one end of the positive electrode core and the negative electrode core abuts against the hanger, and the other end of the positive electrode core and the negative electrode core is connected with a controller through a wire.

[0014] Optionally, one end of the positive electrode core and the negative electrode core close to the hanger is provided with an elastic conductor.

[0015] Optionally, the separation mechanism comprises a second electromagnet and a second electromagnetic armature, the second electromagnetic armature is arranged on the front stage model and the rear stage model, and the second electromagnet is arranged on the hanger.

[0016] Optionally, a second positioning pin is arranged between the front stage model and the hanger, and a third positioning pin is arranged between the rear stage model and the hanger.

[0017] The application has at least the following advantages and beneficial effects: when the target aircraft model in the application is in free flight, the front-stage model and the rear-stage model are fixed by the first electromagnet and the first electromagnetic armature, when separation is needed, the controller controls the power on or off to make the magnetic force of the first electromagnet disappear, the force generating component generates thrust to overcome the magnetic force generated by the residual magnetism of the first electromagnet, when the thrust generated by the force generating component just offsets the magnetic force generated by the residual magnetism of the first electromagnet, the front-stage model and the rear-stage model can be freely separated; when the thrust generated by the force generating component is greater than the magnetic force generated by the residual magnetism of the first electromagnet, the front-stage model and the rear-stage model can be separated at a certain relative speed. BRIEF DESCRIPTION OF DRAWINGS

[0018] In order to more clearly illustrate the technical solutions of the embodiments of the application, the following will briefly introduce the drawings needed to be used in the embodiments. It should be understood that the following drawings only show some of the embodiments of the application, and therefore should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can also be obtained without creative labor.

[0019] Figure 1 A structure schematic diagram of a two-body free separation wind tunnel test device provided by the application;

[0020] Figure 2 A sectional view of a two-body free separation wind tunnel test device provided by the application;

[0021] Figure 3 A partial sectional view of a two-body free separation wind tunnel test device provided by the application;

[0022] Figure 4 A structure schematic diagram of a front-stage model;

[0023] Figure 5 A structure schematic diagram of a rear-stage model;

[0024] Figure: 1-front-stage model, 2-rear-stage model, 201-tail jet, 3-first electromagnet, 4-first electromagnetic armature, 5-power supply, 6-controller, 7-force generating component, 8-front-stage separation mechanism, 801-front-stage electromagnet, 802-front-stage electromagnetic armature, 9-rear-stage separation mechanism, 901-rear-stage electromagnet, 902-rear-stage electromagnetic armature, 10-first positioning pin, 11-hanging rack, 12-positive electrode core, 13-negative electrode core, 14-elastic conductor, 15-second positioning pin, 16-third positioning pin, 17-first screw, 18-second screw, 19-third screw, 20-fourth screw, 21-fifth screw, 22-sixth screw. DETAILED DESCRIPTION

[0025] Embodiment one

[0026] Reference should be made to Figure 2 The embodiment provides a stage free separation structure, which comprises a target aircraft model, the target aircraft model comprises a front stage model 1 and a rear stage model 2, a tail jet 201 is arranged at the rear end of the rear stage model 2, the rear end surface of the front stage model 1 abuts against the front end surface of the rear stage model 2, so that the front stage model 1 and the rear stage model 2 are prevented from being stuck together and affecting the experimental results when being separated, the rear end surface of the front stage model 1 and the front end surface of the rear stage model 2 are fixed by a first electromagnet 3 and a first electromagnetic armature 4, a power supply 5 and a controller 6 are arranged in the target aircraft model, the power supply 5 is electrically connected with the electromagnet, and the controller 6 is electrically connected with the power supply 5.

[0027] Specifically, the power supply 5 and the controller 6 are arranged in the rear stage model 2, the rear end surface of the front stage model 1 is provided with a first mounting hole, the first electromagnetic armature 4 is arranged in the first mounting hole, the front end surface of the rear stage model 2 is provided with a second mounting hole, and the first electromagnet 3 is arranged in the second mounting hole, the first electromagnetic armature is connected with the front stage model 1 through a first screw 17, and the first electromagnet 3 is connected with the rear stage model 2 through a second screw 18, so that the first electromagnetic armature and the first electromagnet are convenient to disassemble and assemble, and it is easy to understand that, in other embodiments of the application, the first electromagnet 3 and the front stage model 1 and the first electromagnetic armature 4 and the rear stage model 2 can also be fixed through other ways, for example, bonding.

[0028] The first electromagnet 3 is a de-energized electromagnet, that is, the electromagnetic force disappears when energized, and it is worth mentioning that, because a certain period of time is needed between assembly and debugging of the target aircraft model and the test, the de-energized electromagnet can make the first electromagnet 3 maintain the magnetic force for a long time before separation without power supply, thereby saving energy; on the other hand, because the longer the conventional electromagnet (that is, the electromagnet that obtains the electromagnetic force when energized and disappears when de-energized) is energized, the more serious the heat is, and in addition, the working condition of the separation wind tunnel test is in a closed vacuum environment, which is not conducive to heat dissipation, and the magnetic force of the conventional electromagnet basically disappears at 80 degrees Celsius, so that the separation is advanced, and the de-energized electromagnet can avoid this problem.

[0029] The first electromagnetic armature 4 is made of a material with good magnetic conductivity, and is generally electromagnetic pure iron, such as DT4C and DT4E.

[0030] The force generating component 7 is arranged between the rear end surface of the front-stage model 1 and the front end surface of the rear-stage model 2, and in the embodiment, the force generating component 7 is a spring. The rear end surface of the front-stage model 1 is provided with a blind hole for pressing the force generating component 7. It is worth mentioning that when the front-stage model 1 and the rear-stage model 2 are assembled together and not separated, the spring is compressed in the blind hole. When the front-stage model 1 and the rear-stage model 2 need to be separated, the first electromagnet 3 is selected as a de-energized electromagnet. The controller 6 controls the power supply 5 to supply power to the first electromagnet 3, so that the magnetic force of the first electromagnet 3 disappears. At this time, the spring restores to the original length, and the elastic force generated by the spring is just counteracted by the magnetic force generated by the residual magnetism of the first electromagnet 3, so that the front-stage model 1 and the rear-stage model 2 are freely separated.

[0031] It is worth mentioning that in other embodiments of the present application, the front-stage model 1 and the rear-stage model 2 can also be separated at a certain relative speed. It is only necessary to select a suitable spring, so that the elastic force generated by the spring when it restores to the original length is greater than the magnetic force generated by the residual magnetism of the first electromagnet 3. The greater the elastic force generated by the spring, the greater the relative speed at which the front-stage model 1 and the rear-stage model 2 are separated.

[0032] In practical application, the inter-stage free separation structure provided in the embodiment can be applied to existing launch-type launching and can also be applied to carrier-type launching.

[0033] Please refer to Figure 4 In the embodiment, two first positioning pins 10 are arranged between the rear end surface of the front-stage model 1 and the front end surface of the rear-stage model 2. It is easy to understand that the rear end surface of the front-stage model 1 and the front end surface of the rear-stage model 2 are provided with positioning holes matched with the first positioning pins 10. The first positioning pins 10 can ensure that the front-stage model 1 and the rear-stage model 2 have high repeatability after each assembly. Further, one end of the first positioning pin 10 in the embodiment is in a conical structure. Taking the end of the first positioning pin 10 close to the rear-stage model 2 as an example, the positioning hole on the rear-stage model 2 is also in a conical structure matched with it. It is worth mentioning that the conical structure can not only play a positioning effect, but also avoid the front-stage model 1 and the rear-stage model 2 from being stuck when they are separated. It is easy to understand that in other embodiments of the present application, the number of first positioning pins 10 can also be three or four, and the conical structure of the first positioning pin 10 can also be arranged at the end close to the front-stage model 1.

[0034] Embodiment two

[0035] The difference between the embodiment and the embodiment one is that the structure of the force generating component 7 is different. The force generating component 7 of the embodiment includes a compression cylinder, a compression piston and a piston rod. The compression piston is arranged in the compression cylinder. The piston rod is connected with the compression piston and extends out of the compression cylinder. The rear end surface of the front-stage model 1 or the front end surface of the rear-stage model 2 is provided with a blind hole for press-fitting the force generating component 7. The compression piston and the compression cylinder are in a closed cavity and filled with air. After the front-stage model 1 and the rear-stage model 2 are assembled, the air between the compression piston and the compression cylinder is compressed, that is, the piston rod is in a compressed state. Only the force generated when the piston rod is restored needs to be designed to counteract the magnetic force generated by the residual magnetism of the first electromagnet 3, and the purpose of freely separating the front-stage model 1 and the rear-stage model 2 can be achieved. On this basis, it is easy to understand that in other embodiments of the application, the force generated when the piston rod is restored is designed to be greater than the magnetic force generated by the residual magnetism of the first electromagnet 3, that is, the front-stage model 1 and the rear-stage model 2 can be separated at a certain relative speed.

[0036] It is easy to understand that the end of the piston rod away from the compression cylinder can abut against the front-stage model 1 or the rear-stage model 2 during installation. For example, the end of the piston rod away from the compression cylinder abuts against the rear-stage model 2. In this case, the end of the compression cylinder away from the piston rod abuts against the end surface of the rear-stage model 2. Conversely, the same applies.

[0037] Embodiment three

[0038] The difference between the embodiment and the embodiment one is that the structure of the force generating component 7 is different. The force generating component 7 of the embodiment includes a compression cylinder, a compression piston and a piston rod. The compression piston is arranged in the compression cylinder. The piston rod is connected with the compression piston and extends out of the compression cylinder. The rear end surface of the front-stage model 1 or the front end surface of the rear-stage model 2 is provided with a blind hole for press-fitting the force generating component 7. The compression piston and the compression cylinder are in a closed cavity and filled with air. After the front-stage model 1 and the rear-stage model 2 are assembled, the air between the compression piston and the compression cylinder is compressed, that is, the piston rod is in a compressed state. Only the force generated when the piston rod is restored needs to be designed to counteract the magnetic force generated by the residual magnetism of the first electromagnet 3, and the purpose of freely separating the front-stage model 1 and the rear-stage model 2 can be achieved. On this basis, it is easy to understand that in other embodiments of the application, the force generated when the piston rod is restored is designed to be greater than the magnetic force generated by the residual magnetism of the first electromagnet 3, that is, the front-stage model 1 and the rear-stage model 2 can be separated at a certain relative speed.

[0039] Embodiment four

[0040] Please refer to Figures 1-3The embodiment provides a two-body free separation wind tunnel test device, which comprises a hanger 11 and the interstage free separation structure provided in the first embodiment, the hanger 11 is used for connecting external angle of attack adjusting equipment to perform tests under different angles of attack. The front stage model 1 and the rear stage model 2 of the interstage free separation structure are connected with the hanger 11 through separation mechanisms respectively, the separation mechanism in the embodiment comprises a second electromagnet and a second electromagnetic armature, the second electromagnetic armature is arranged on the front stage model 1 and the rear stage model 2, and the second electromagnet is arranged on the hanger 11. For the convenience of description, the separation mechanism connecting the front stage model 1 and the hanger 11 is named as a front stage separation mechanism 8, and correspondingly, the front stage separation mechanism 8 comprises a front stage electromagnet 801 and a front stage electromagnetic armature 802; the separation mechanism connecting the rear stage model 2 and the hanger 11 is named as a rear stage separation mechanism 9, and correspondingly, the rear stage separation mechanism 9 comprises a rear stage electromagnet 901 and a rear stage electromagnetic armature 902.

[0041] The front stage electromagnetic armature 802 is arranged on the front stage model 1 and can be connected and fixed with the front stage model 1 through a third screw 19, and it is easy to understand that the front stage electromagnetic armature 802 is arranged directly above the center of mass of the front stage model 1, so that the front stage model 1 is not subjected to force in the direction of gravity after assembly, and the test process is more stable and reliable. The front stage electromagnet 801 is arranged on the hanger 11 and can be connected and fixed with the hanger 11 through a fourth screw 20.

[0042] The rear stage electromagnetic armature 902 is arranged on the rear stage model 2 and can be connected and fixed with the rear stage model 2 through a fifth screw 21, and in the same way, the rear stage electromagnetic armature 902 is arranged directly above the center of mass of the rear stage model 2, so that the rear stage model 2 is not subjected to force in the direction of gravity after assembly, and the test process is more stable and reliable. The rear stage electromagnet 901 is arranged on the hanger 11 at a position corresponding to the rear stage electromagnetic armature 902 and can be connected and fixed with the hanger 11 through a sixth screw 22.

[0043] It is easy to understand that the front stage electromagnet 801 and the rear stage electromagnet 901 are powered by an external power supply. In the same way, the front stage electromagnet and the rear stage electromagnet 901 can also be selected as de-energized electromagnets, that is, when separation is needed, the electromagnets are energized to make the magnetic force disappear. In the same way, the selection of the de-energized electromagnets can solve the problem that the conventional electromagnets are prone to failure due to high temperature and can also save energy. In addition, the front stage electromagnet and the front stage electromagnetic armature should be completely attached, and the rear stage electromagnet 901 and the rear stage electromagnetic armature 902 should be completely attached, so as to exert the maximum suction force. Furthermore, the front stage electromagnet 801 and the rear stage electromagnetic armature 802 are also made of materials with good magnetic conductivity, generally electromagnetic pure iron, such as DT4C and DT4E.

[0044] In this embodiment, a second positioning pin 15 is provided between the front-stage model 1 and the pylon 11, and a third positioning pin 16 is provided between the rear-stage model 2 and the pylon 11. The end structure of the third positioning pin 16 is not limited; it can be either a cylindrical structure or a conical structure. The second positioning pin 15 and the third positioning pin 16 can ensure that the target aircraft has a high degree of repeatability each time it is loaded into the pylon 11.

[0045] Please refer to Figure 3 , Figure 5 The target aircraft model is equipped with a positive electrode core 12 and a negative electrode core 13. One end of the positive electrode core 12 and the negative electrode core 13 abuts against the pylon 11. Furthermore, the positive electrode core 12 and the negative electrode core 13 are provided with an elastic conductor 14 (such as a spring, an elastic iron sheet, etc.) near the pylon 11 to facilitate good contact between the positive electrode core 12 and the negative electrode core 13 and the pylon 11 (it is understood that the pylon 11 is made of metal material and can conduct electricity). The other end of the positive electrode core 12 and the negative electrode core 13 is connected to the controller 6 through a wire.

[0046] It is worth noting that when the positive electrode core 12 and the negative electrode core 13 are in contact with the hanger 11, the controller 6 controls the first electromagnet 3 to be de-energized, maintaining the magnetic force to keep the front-stage model 1 and the rear-stage model 2 together. When the target aircraft is detached from the hanger 11, the positive electrode core 12 and the negative electrode core 13 detach from the hanger 11, triggering the timer in the controller to work. After a certain delay (e.g., a delay of 2 seconds), the controller 6 controls the first electromagnet 3 to be energized, and the magnetic force of the first electromagnet 3 is reduced to a minimum. At the same time, under the action of the force generating component 7, the residual magnetism of the first electromagnet 3 is overcome. Under the action of aerodynamic force, the front-stage model 1 and the rear-stage model 2 achieve free separation.

[0047] Of course, the force generated by the force generating component 7 can also be greater than the residual magnetism of the first electromagnet 3, thereby causing the front-stage model 1 and the rear-stage model 2 to separate at a certain relative speed. That is, this embodiment can solve the problem of how to achieve free separation or separation at a certain relative speed between stages during the flight process after the target aircraft detaches from the pylon 11.

[0048] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. An interstage free separation structure, comprising a target aircraft model, the target aircraft model comprising a front-stage model (1) and a rear-stage model (2), characterized in that: The rear end face of the front stage model (1) and the front end face of the rear stage model (2) abut against each other, and the two are attracted and fixed by the first electromagnet (3) and the first electromagnetic armature (4). The target aircraft model is equipped with a power supply (5) and a controller (6). The power supply (5) is electrically connected to the electromagnet, and the controller (6) is electrically connected to the power supply (5). A force generating component (7) is provided between the rear end face of the front stage model (1) and the front end face of the rear stage model (2) to generate thrust to overcome the magnetic force generated by the residual magnetism of the first electromagnet (3). The force generating component (7) adopts Scheme 1, Scheme 2 or Scheme 3, wherein: In Scheme 1, the force generating component (7) is a spring, and the rear end face of the front model (1) or the front end face of the rear model (2) is provided with blind holes for press-fitting the force generating component (7); The force generating component (7) described in Scheme 2 includes a compression cylinder, a compression piston and a piston rod. The compression piston is located inside the compression cylinder, and the piston rod is connected to the compression piston and extends out of the compression cylinder. The rear end face of the front model (1) or the front end face of the rear model (2) is provided with blind holes for pressing the force generating component (7). The force generating component (7) in Scheme 3 includes a first magnet and a second magnet that repel each other. One of the first magnet and the second magnet is located on the rear end face of the front model (1), and the other is located on the front end face of the rear model (2).

2. The interstage free separation structure according to claim 1, characterized in that: At least two first positioning pins (10) are provided between the rear end face of the front-end model (1) and the front end face of the rear-end model (2).

3. The interstage free separation structure according to claim 2, characterized in that: One end of the first positioning pin (10) has a tapered structure.

4. A two-body free separation wind tunnel test device, characterized in that: The system includes a pylon (11) and an interstage free separation structure as described in any one of claims 1-3. The pre-stage model (1) and the post-stage model (2) of the interstage free separation structure are respectively connected to the pylon (11) through a separation mechanism. The target aircraft model is provided with a positive electrode core (12) and a negative electrode core (13). One end of the positive electrode core (12) and the negative electrode core (13) abuts against the pylon (11), and the other end of the positive electrode core (12) and the negative electrode core (13) is connected to the controller (6) through a wire.

5. The two-body free separation wind tunnel test device according to claim 4, characterized in that: The positive electrode core (12) and the negative electrode core (13) are provided with an elastic conductor (14) at one end near the bracket (11).

6. The two-body free separation wind tunnel test device according to claim 4, characterized in that: The separation mechanism includes a second electromagnet and a second electromagnetic armature. The second electromagnetic armature is mounted on the front-stage model (1) and the rear-stage model (2), and the second electromagnet is mounted on the hanger (11).

7. The two-body free separation wind tunnel test device according to claim 4, characterized in that: A second positioning pin (15) is provided between the front-end model (1) and the hanger (11), and a third positioning pin (16) is provided between the rear-end model (2) and the hanger (11).

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