Aircraft airspeed tube assembly

Abstract

The utility model belongs to the technical field of airspeed tube assemblies, and particularly relates to an aircraft airspeed tube assembly which comprises an airspeed tube sleeve main body, a built-in sealing valve plate is fixedly mounted in the airspeed tube sleeve main body, a blocking hole is formed in the center of the built-in sealing valve plate, a sealing plug is slidably connected in the blocking hole, and the sealing plug is arranged in the sealing hole. The two sides of the sealing plug are fixedly connected with linkage rods, the other end of the linkage rod on the left side is fixedly connected with a first-stage opening plug, and the other end of the linkage rod on the right side is fixedly connected with a second-stage opening plug. According to the utility model, the small stepping motor works to drive the X-axis transposition screw rod to rotate, drive the strip plate to slide along the moving thin groove and drive the first-stage opening plug to move, and the first-stage opening plug, the sealing plug and the second-stage opening plug are connected together, so that the first-stage opening plug, the sealing plug and the second-stage opening plug can move synchronously; and one of the three can be moved into the plugging hole in the sealing valve plate according to requirements, so that the size of the plugging hole is changed, and flexible application is facilitated.

Description

TECHNICAL FIELD

[0001] The utility model relates to a kind of pitot tube assemblies, specifically to a kind of airplane pitot tube assemblies. BACKGROUND

[0002] Pitot tube is important atmospheric data sensor of aircraft, which utilizes pitot tube principle to accurately measure the total pressure and static pressure when flying, and data computer is converted to the flight speed, lift speed and atmospheric pressure data required for flight control by Bernoulli total pressure equation formula etc. To prevent the small hole in front end of pitot tube from icing and blocking in flight, the pitot tube on general aircraft has electric heating device. When aircraft flies forward, airflow rushes into pitot tube, and the inductor at the end of pitot tube will feel the impact force of airflow, i.e. dynamic pressure. The faster aircraft flies, the greater dynamic pressure is. If the pressure when air is static, i.e. static pressure and dynamic pressure are compared, the rushing air can be known how fast, i.e. how fast aircraft flies. The tool for comparing two kinds of pressure is a hollow circular box with corrugated surface made of upper and lower two very thin metal sheets, called diaphragm box.

[0003] When aircraft stays on the ground, foreign matters such as insects and dust can enter pitot tube inside from pitot tube mouth, which increases the risk of pitot tube blocking, and if pitot tube is blocked, atmospheric data measurement result will be deviated, which may cause the value displayed on instrument panel in cockpit to be inconsistent with actual value, thereby affecting the navigation safety of aircraft. SUMMARY

[0004] The main purpose of the present disclosure is to provide an aircraft pitot tube assembly to effectively solve the problems raised by the inventor in the above background.

[0005] To achieve the above purpose, the technical scheme adopted by the utility model is as follows:

[0006] An aircraft pitot tube assembly, comprising a pitot tube sleeve main body, an internal sealing valve plate is fixedly installed inside the pitot tube sleeve main body, a block hole is formed at the center of the internal sealing valve plate, a sealing plug is slidably connected in the block hole, linkage rods are fixedly connected on both sides of the sealing plug, a first opening plug is fixedly connected to the other end of the linkage rod on the left side, a second opening plug is fixedly connected to the other end of the linkage rod on the right side, and the sizes of the first opening plug, the second opening plug and the sealing plug are the same.

[0007] Preferably, a flow port is formed on the first opening plug, and three through holes in annular array are formed on the second opening plug.

[0008] Preferably, the outer side of the air speed tube sleeve body is fixedly provided with a closed slide rail, and the air speed tube sleeve body is provided with a moving fine slot communicated with the closed slide rail, the closed slide rail is slidably connected with a driving strip, and the driving strip slidably penetrates through the moving fine slot.

[0009] Preferably, the driving strip is provided with two, and the two driving strips are fixedly connected with the primary opening plug and the secondary opening plug respectively.

[0010] Preferably, the closed slide rail is rotatably provided with an X-axis transposition screw rod, the two driving strips are threadedly installed on the X-axis transposition screw rod, the outer side of the closed slide rail is fixedly provided with a small stepping motor, and the output end of the small stepping motor is fixedly connected with the X-axis transposition screw rod.

[0011] Preferably, the left end of the air speed tube sleeve body is threadedly provided with a threaded plug.

[0012] Compared with the prior art, the air speed tube sleeve body of the utility model has the advantages that:

[0013] In the application, when the small stepping motor works, it can drive the X-axis transposition screw rod to rotate, the driving strip slides along the moving fine slot, and the primary opening plug is driven to move, and since the primary opening plug, the sealing plug and the secondary opening plug are connected together, the three can move synchronously, according to the requirement, one of the three can be moved to the plug hole on the sealing valve plate, and then the size of the plug hole is changed, thereby facilitating flexible application. BRIEF DESCRIPTION OF DRAWINGS

[0014] Figure 1 Fig. 1 is a structural schematic view of an aircraft air speed tube assembly provided by the utility model;

[0015] Figure 2 Fig. 2 is a schematic view of the sealing plug moving to the right; Figure 1 Fig. 3 is a schematic view of the sealing plug moving to the left;

[0016] Figure 3 Fig. 4 is a side view of the built-in sealing valve plate; Figure 1 Fig. 5 is a side view of the primary opening plug;

[0017] Figure 4 Fig. 6 is a side view of the secondary opening plug.

[0018] Figure 5 Fig. 7 is a side view of the sealing plug;

[0019] Figure 6 Fig. 8 is a side view of the primary opening plug;

[0020] Figure 7 Fig. 9 is a side view of the secondary opening plug.

[0021] Fig. 10 is a structural schematic view of an aircraft air speed tube assembly provided by the utility model;

[0022] 1-annular velocity tube body; 2-internal sealing valve plate; 3-sealing plug; 4-primary opening plug; 401-flow port; 5-secondary opening plug; 501-through hole; 6-threaded cap; 7-closed slide rail; 8-moving fine groove; 9-driving strip; 10-X-axis displacement screw; 11-small stepping motor. DETAILED DESCRIPTION

[0023] The technical solutions in the embodiments of the utility model will be clearly and completely described below with reference to the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the protection scope of the utility model.

[0024] Please refer to Figures 1-7 The utility model provides the following embodiments:

[0025] An aircraft pitot tube assembly, comprising a pitot tube body 1, an internal sealing valve plate 2 is fixedly installed in the pitot tube body 1, and a plug hole is formed in the center of the internal sealing valve plate 2, a sealing plug 3 is slidably connected in the plug hole, and linkage rods are fixedly connected to the two sides of the sealing plug 3, a primary opening plug 4 is fixedly connected to the other end of the left linkage rod, and a secondary opening plug 5 is fixedly connected to the other end of the right linkage rod, the sizes of the primary opening plug 4, the secondary opening plug 5 and the sealing plug 3 are the same, a flow port 401 is formed in the primary opening plug 4, and three through holes 501 arranged in a ring array are formed in the secondary opening plug 5.

[0026] Specifically, a closed slide rail 7 is fixedly installed on the outside of the pitot tube body 1, a moving fine groove 8 is formed in the pitot tube body 1 and communicates with the closed slide rail 7, a driving strip 9 is slidably connected in the closed slide rail 7, and the driving strip 9 slidably penetrates the moving fine groove 8, the driving strip 9 is provided with two, and the two driving strips 9 are fixedly connected with the primary opening plug 4 and the secondary opening plug 5 respectively.

[0027] Specifically, an X-axis displacement screw 10 is rotatably installed in the closed slide rail 7, the two driving strips 9 are threadedly installed on the X-axis displacement screw 10, a small stepping motor 11 is fixedly installed on the outside of the closed slide rail 7, and the output end of the small stepping motor 11 is fixedly connected with the X-axis displacement screw 10.

[0028] Specifically, a threaded cap 6 is threadedly installed on the left end of the pitot tube body 1 to seal the other end of the pitot tube body 1.

[0029] The specific implementation of the embodiment is that the small stepping motor 11 works, drives the X-axis displacement wire rod 10 to rotate, drives the strip plate 9 to slide along the moving groove 8, and drives the first open plug 4 to move.

[0030] In the description of the present specification, the description referring to the terms "one embodiment", "an example", "a specific example" and the like means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In the present specification, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0031] The preferred embodiments of the present application disclosed above are only used to help explain the present application. The preferred embodiments do not describe all the details and limit the present application to the specific embodiments described. Obviously, according to the content of the present specification, many modifications and changes can be made. The present specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present application, so that the persons skilled in the art can well understand and utilize the present application. The present application is limited by the claims and the entire scope and equivalents thereof.

Claims

1. An aircraft pitot tube assembly, characterized in that: The invention comprises a pitot tube sleeve body (1), wherein a built-in sealing valve plate (2) is fixedly installed inside the pitot tube sleeve body (1), and a blocking hole is opened at the center of the built-in sealing valve plate (2), a sealing plug (3) is slidably connected in the blocking hole, and both sides of the sealing plug (3) are fixedly connected with linkage rods, the other end of the linkage rod on the left side is fixedly connected with a first-level opening plug (4), and the other end of the linkage rod on the right side is fixedly connected with a second-level opening plug (5), and the first-level opening plug (4), the second-level opening plug (5) and the sealing plug (3) have the same size.

2. The aircraft pitot tube assembly according to claim 1, characterized in that: The first-stage opening plug (4) is provided with a flow port (401), and the second-stage opening plug (5) is provided with three through holes (501) distributed in a ring array.

3. The aircraft pitot tube assembly according to claim 1, characterized in that: A closed slide rail (7) is fixedly mounted on the outer side of the pitot tube housing body (1), and a movable slot (8) communicating with the closed slide rail (7) is provided on the pitot tube housing body (1). A driving strip plate (9) is slidably connected in the closed slide rail (7), and the driving strip plate (9) slides through the movable slot (8).

4. The aircraft pitot tube assembly according to claim 3, characterized in that: Two driving strips (9) are provided, and the two driving strips (9) are fixedly connected to the primary opening plug (4) and the secondary opening plug (5) respectively.

5. The aircraft pitot tube assembly according to claim 4, characterized in that: An X-axis transposition screw (10) is rotatably mounted in the closed slide rail (7), and the two driving strips (9) are both threadedly mounted on the X-axis transposition screw (10). A small stepping motor (11) is fixedly mounted on the outer side of the closed slide rail (7), and the output end of the small stepping motor (11) is fixedly connected to the X-axis transposition screw (10).

6. The aircraft pitot tube assembly according to claim 1, characterized in that: The left end of the pitot tube sleeve body (1) is threadedly mounted with a threaded plug cap (6).

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