CN215865719U - Bird strike test device for aircraft engine - Google Patents

Abstract

The utility model relates to an aircraft engine bird strike testing device. The bird strike testing device of the aircraft engine comprises an electromagnetic launching device, wherein the electromagnetic launching device comprises a launching track and an armature mechanism arranged in the launching track, bird projectiles are placed in the launching track, and the electromagnetic launching device pushes the bird projectiles to accelerate to fly away from the launching track through the armature mechanism; the speed measuring device is used for measuring the flying speed of the bird bomb; and the control unit is connected with the speed measuring device and the electromagnetic emission device, receives the flight speed of the bird bomb obtained by the speed measuring device, controls the current of the electromagnetic emission device and executes the emission of the bird bomb. The utility model provides an aircraft engine bird strike test device which can control the speed of a bird bomb and improve the test efficiency.

Description

Bird strike test device for aircraft engine

Technical Field

The utility model relates to the technical field of aero-engine strength tests, in particular to an aero-engine bird strike test device.

Background

Aircraft are susceptible to bird strikes during takeoff and landing, thereby compromising aircraft and passenger safety. Every year, aviation accidents caused by bird strikes, in which the safe operation of the aircraft engine is seriously threatened by bird strikes, which may lead to engine shutdowns and even more serious uncontained accidents. According to airworthiness regulations, an aircraft engine must have sufficient bird strike resistance. Therefore, it is necessary to test the bird impact resistance of the aircraft engine to verify that the aircraft engine meets the airworthiness requirement.

In the process of developing the aero-engine, a bird impact test is carried out on a test piece by generally adopting a mode that an air cannon accelerates a bird bullet by compressed air. The air cannon test device needs a high-pressure air storage tank, and needs long time for pressurization before test, so that quick launching cannot be realized, the required time for the test is long, the efficiency is low, meanwhile, the speed of the air cannon is difficult to accurately control, the precision and the accuracy of a bird collision test are influenced, high-pressure gas has high danger, and the safety of the test device and operators is threatened.

SUMMERY OF THE UTILITY MODEL

Aiming at the problems in the prior art, the utility model provides an aircraft engine bird strike test device which can control the speed of bird bullets and improve the test efficiency.

Specifically, the utility model provides an aircraft engine bird strike test device, which comprises:

the electromagnetic launching device comprises a launching track and an armature mechanism arranged in the launching track, wherein a bird bomb is placed in the launching track, and the electromagnetic launching device pushes the bird bomb to accelerate to fly away from the launching track through the armature mechanism;

the speed measuring device is used for measuring the flying speed of the bird bomb;

and the control unit is connected with the speed measuring device and the electromagnetic emission device, receives the flight speed of the bird bomb obtained by the speed measuring device, controls the current of the electromagnetic emission device and executes the emission of the bird bomb.

According to one embodiment of the utility model, the aircraft engine bird strike testing device further comprises a power supply, and the power supply supplies power to the control unit and the electromagnetic transmitting device.

According to one embodiment of the utility model, the electromagnetic launching device utilizes the electromagnetic principle to make the armature mechanism do accelerated motion in the launching track, and the armature mechanism pushes the bird bomb to accelerate and fly away from the launching track.

According to one embodiment of the utility model, the speed measuring device is a laser speed measuring device, the laser speed measuring device comprises an optical fiber sensor, and the laser speed measuring device calculates the flying speed of the bird bomb by using a signal obtained by the optical fiber sensor.

According to one embodiment of the utility model, the speed measuring device comprises a plurality of speed measuring sensors.

According to one embodiment of the utility model, a plurality of said tacho sensors are arranged on and/or outside said launch track.

According to one embodiment of the utility model, the control unit controls the thrust force exerted on the bird bomb by the armature mechanism according to the acquired flying speed of the bird bomb, wherein the thrust force F is ILB according to the principle of electromagnetic force;

wherein, I is the passing current of the armature mechanism, L is the length of a linear lead of the armature mechanism, and B is the magnetic induction intensity generated by the current in the electromagnetic emission device.

The bird strike test device for the aircraft engine provided by the utility model accelerates the bird bomb by adopting an electromagnetic emission mode, can control the speed of the bird bomb and can improve the test efficiency.

It is to be understood that both the foregoing general description and the following detailed description of the present invention are exemplary and explanatory and are intended to provide further explanation of the utility model as claimed.

Drawings

The accompanying drawings, which are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the utility model and together with the description serve to explain the principle of the utility model. In the drawings:

fig. 1 shows a schematic structural diagram of an aircraft engine bird strike testing device according to an embodiment of the utility model.

Wherein the figures include the following reference numerals:

bird strike test device 100 for aircraft engine

Electromagnetic emitting device 101

Speed measuring device 102

Control unit 103

Launching track 104

Armature mechanism 105

Bird bomb 106

Power supply 107

Detailed Description

It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict.

The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. It should be apparent that the described embodiments are only some of the embodiments of the present application, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the application, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.

The relative arrangement of the components and steps, the numerical expressions, and numerical values set forth in these embodiments do not limit the scope of the present application unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.

In the description of the present application, it is to be understood that the orientation or positional relationship indicated by the directional terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal" and "top, bottom", etc., are generally based on the orientation or positional relationship shown in the drawings, and are used for convenience of description and simplicity of description only, and in the case of not making a reverse description, these directional terms do not indicate and imply that the device or element being referred to must have a particular orientation or be constructed and operated in a particular orientation, and therefore, should not be considered as limiting the scope of the present application; the terms "inner and outer" refer to the inner and outer relative to the profile of the respective component itself.

Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may also be oriented 90 degrees or at other orientations and the spatially relative descriptors used herein interpreted accordingly.

It should be noted that the terms "first", "second", and the like are used to define the components, and are only used for convenience of distinguishing the corresponding components, and the terms have no special meanings unless otherwise stated, and therefore, the scope of protection of the present application is not to be construed as being limited. Further, although the terms used in the present application are selected from publicly known and used terms, some of the terms mentioned in the specification of the present application may be selected by the applicant at his or her discretion, the detailed meanings of which are described in relevant parts of the description herein. Further, it is required that the present application is understood not only by the actual terms used but also by the meaning of each term lying within.

Fig. 1 shows a schematic structural diagram of an aircraft engine bird strike testing device according to an embodiment of the utility model. As shown in the figure, an aircraft engine bird strike testing device 100 mainly includes an electromagnetic emitting device 101, a speed measuring device 102 and a control unit 103.

The electromagnetic launching device 101 includes a launching track 104 and an armature mechanism 105 disposed in the launching track 104. Within the launching track 104 is a bird bomb 106. The electromagnetic launching device 101 accelerates away from the launching track 104 by the armature mechanism 105 pushing the bird projectiles 106. The dashed tip in the figure illustrates the flight path of the bird shot 106, and the bird shot 106 flies along the left side of the launching track 104 to the right side and finally leaves the launching track 104 to hit the test piece.

The speed measuring device 102 is used for measuring the flying speed of the bird bomb 106.

The control unit 103 is connected with the speed measuring device 102 and the electromagnetic transmitting device 101. The control unit 103 receives the flight speed of the bird bomb 106 acquired by the speed measuring device 102 and controls the electromagnetic emitting device 101 to emit the bird bomb 106.

Preferably, the aircraft engine bird strike testing apparatus 100 further comprises a power source 107. The power supply 107 supplies power to the control unit 103 and the electromagnetic radiation device 101.

Preferably, the electromagnetic launching device 101 utilizes electromagnetic principles to make the armature mechanism 105 perform an accelerating motion in the launching track 104, and the armature mechanism 105 pushes the bird bomb 106 to accelerate away from the launching track 104. It is easy to understand that, according to the electromagnetic principle, the armature mechanism 105 is subjected to the electromagnetic force generated by the current in the magnetic field on the launching track 104 to realize the acceleration motion, and the armature mechanism 105 pushes the bird bomb 106 to move forward to realize the acceleration action of the bird bomb 106 in the aircraft engine bird strike test device 100 provided by the utility model. The electromagnetic emission does not need a longer pressurizing process of a traditional air cannon, so that the electromagnetic emission can be rapidly emitted, and the test efficiency is improved. Compared with the high-pressure gas acceleration mode of the air cannon, the safety is improved, and the safety threat of the high-pressure gas to the testing device and the testing personnel is avoided.

Preferably, the speed measuring device 102 is a laser speed measuring device 102, which includes an optical fiber sensor. The laser speed measuring device 102 can obtain the flying speed of the bird bomb 106 by using the signal obtained by the optical fiber sensor and based on the laser interference principle.

Preferably, the tachometer means 102 comprises a plurality of tachometer sensors. More preferably, a plurality of tacho sensors are disposed on the launching track 104 and/or outside the launching track 104. The velocity sensor may obtain a real-time velocity of the bird projectiles 106 within the launch track 104 and may also obtain a real-time velocity of the bird projectiles 106 flying out of the launch track 104. Acceleration information of the bird bomb 106 can be obtained from the change in speed of the bird bomb 106 over the range.

Preferably, the control unit 103 controls the thrust force applied by the armature mechanism 105 to the bird bomb 106 according to the acquired flying speed of the bird bomb 106, and the thrust force F is ILB according to the principle of electromagnetic force. Where I is the current passing through the armature mechanism 105, L is the linear wire length of the armature mechanism 105, and B is the magnetic induction generated by the current. When the flying speed of the bird bomb 106 is not enough, the passing current of the armature mechanism 105 can be increased to obtain a larger thrust, so that the initial acceleration of the bird bomb 106 and the flying speed after flying off the launching track 104 can be increased. It will be readily appreciated that the initial acceleration of the bird projectile 106 and the velocity after flying off the launching track 104 may be reduced by a reverse process. Actually, the control unit 103 realizes the accurate control of the speed of the bird bomb 106 through electromagnetic closed-loop control, so as to improve the test accuracy.

Optionally, the control unit 103 may communicate with the electromagnetic emitting device 101 and the speed measuring device 102 in a wired or wireless manner.

The bird strike test device for the aircraft engine provided by the utility model has the following advantages:

1. the rapid emission is realized, and the test efficiency is improved;

2. the bird bullet speed is accurately controlled, and the test precision is improved;

3. and a high-pressure gas device is not arranged, so that the test safety is improved.

It will be apparent to those skilled in the art that various modifications and variations can be made to the above-described exemplary embodiments of the present invention without departing from the spirit and scope of the utility model. Thus, it is intended that the present invention cover the modifications and variations of this invention provided they come within the scope of the appended claims and their equivalents.

Claims (7)

1. The utility model provides an aeroengine bird strikes test device which characterized in that includes:

the electromagnetic launching device comprises a launching track and an armature mechanism arranged in the launching track, wherein a bird bomb is placed in the launching track, and the electromagnetic launching device pushes the bird bomb to accelerate to fly away from the launching track through the armature mechanism;

the speed measuring device is used for measuring the flying speed of the bird bomb;

and the control unit is connected with the speed measuring device and the electromagnetic emission device, receives the flight speed of the bird bomb obtained by the speed measuring device, controls the current of the electromagnetic emission device and executes the emission of the bird bomb.

2. The aircraft engine bird strike test device of claim 1, further comprising a power source that supplies power to the control unit and the electromagnetic emitting device.

3. The aircraft engine bird strike test device of claim 2, wherein the electromagnetic launching device utilizes electromagnetic principles to cause the armature mechanism to make accelerated motion in the launching track, and the armature mechanism pushes the bird bomb to accelerate away from the launching track.

4. The bird strike testing device of claim 1, wherein the speed measuring device is a laser speed measuring device, the laser speed measuring device comprises an optical fiber sensor, and the laser speed measuring device calculates the flying speed of the bird bomb by using a signal obtained by the optical fiber sensor.

5. The aircraft engine bird strike test device of claim 1, wherein the velocity measurement device comprises a plurality of velocity measurement sensors.

6. The aircraft engine bird strike test device of claim 5, wherein a plurality of said tacho sensors are disposed on and/or off said launch rail.

7. The aircraft engine bird strike test device of claim 1, wherein the control unit controls the thrust force exerted by the armature mechanism on the bird bomb according to the acquired flying speed of the bird bomb, the thrust force F ═ ILB according to the principle of electromagnetic force;

wherein, I is the passing current of the armature mechanism, L is the length of a linear lead of the armature mechanism, and B is the magnetic induction intensity generated by the current in the electromagnetic emission device.

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