Ejection separation mechanism of flight recorder

Abstract

The invention relates to an ejection separation mechanism of a flight recorder, which comprises an ejection spring (3) made of nickel-titanium memory alloy; a hook body (31) is arranged at the top end of the ejection spring (3); a clamping piece (41) is arranged on the bottom surface of the ejection base (4), and the clamping piece (41) is clamped with the hook body (31); a mounting stand column (2) is arranged on the mounting base (1), and the ejection spring (3) is arranged on the mounting stand column (2) in a sleeving mode; the installation stand column (2) is provided with a hollow inner cavity, and the electric heating piece (5) is arranged in the inner cavity. The lower end of the electric heating piece (5) is connected with a power supply wire (6) which penetrates out of the installation base (1) and then is connected with a power module. According to the flight recorder, the nickel-titanium memory alloy is adopted as the actuating mechanism, ejection separation of the flight recorder when the ejection condition is met can be achieved, and the actuating reliability of the ejection separation mechanism is improved.

Description

Technical Field

[0001] The invention relates to the field of civil aircraft avionics technology, in particular to an ejection separation mechanism of a flight recorder. Background Art

[0002] The current air navigation system is unable to identify and locate the position of the aircraft in distress in a timely manner, resulting in delays or failure to recover the flight recorder data of the aircraft involved. ICAO member states and the global industry have begun to systematically promote aircraft tracking and monitoring, and have promoted ejectable flight recorder technology.

[0003] Ejectable flight recorders are used to eject the flight recorder from the aircraft when an aircraft encounters a flight accident, which is beneficial for flight data preservation and accident investigation. However, the flight recorder needs to be ejected within a very short time when a flight accident is detected, so there are high requirements for the response time of the flight recorder's ejection separation mechanism.

[0004] The technologies currently used mostly use pyrotechnics or spring structures. For civil aircraft, pyrotechnics pose a safety risk, and spring structures may have their elasticity weakened after being under pressure for a long time. Therefore, the existing technology has shortcomings and needs to be improved.

[0005] The information disclosed in this background technology section is only intended to deepen the understanding of the overall background technology of the present invention, and should not be regarded as acknowledging or suggesting in any form that the information constitutes the prior art already known to those skilled in the art. Summary of the invention

[0006] In view of the defects existing in the prior art, the purpose of the present invention is to provide an ejection separation mechanism for a flight recorder, which adopts nickel-titanium memory alloy as an actuating mechanism, can realize the ejection separation of the flight recorder when the ejection conditions are met, and improve the actuation reliability of the ejection separation mechanism.

[0007] In order to achieve the above purpose, the technical solution adopted by the present invention is:

[0008] An ejection separation mechanism for a flight recorder, characterized by comprising:

[0009] The ejection spring 3 is made of nickel-titanium memory alloy; a hook 31 is provided at the top of the ejection spring 3;

[0010] The ejectable base 4 has a clamping member 41 on its bottom surface, and the clamping member 41 is clamped with the hook body 31;

[0011] A mounting base 1 is provided with a mounting column 2, and a ejection spring 3 is sleeved on the mounting column 2;

[0012] The mounting column 2 has a hollow inner cavity, and the electric heater 5 is arranged in the inner cavity;

[0013] The lower end of the electric heater 5 is connected to a power supply wire 6 , and the power supply wire 6 passes through the mounting base 1 and is connected to a power module.

[0014] On the basis of the above technical solution, an annular flange 21 is provided at the lower part of the mounting column 2 , and the lower end of the ejection spring 3 abuts against the annular flange 21 .

[0015] On the basis of the above technical solution, the electric heater 5 generates heat when powered on, so that the hook 31 at the top of the ejection spring 3 changes shape into a straight line due to the heat, thereby releasing the clamping member 41 .

[0016] On the basis of the above technical solution, a slot adapted to the clamping member 41 is provided at the upper end of the mounting column 2 .

[0017] On the basis of the above technical solution, anti-slip grooves or limit slots are provided in the slot.

[0018] The ejection separation mechanism of a flight recorder described in the present invention has the following beneficial effects:

[0019] The use of nickel-titanium memory alloy as the actuating mechanism can realize the ejection separation of the flight recorder when the ejection conditions are met, thereby improving the actuation reliability of the ejection separation mechanism. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The present invention has the following accompanying drawings:

[0021] The accompanying drawings are used to better understand the present invention and do not constitute an improper limitation of the present invention.

[0022] Figure 1 A schematic structural diagram of a first embodiment of an ejection separation mechanism for a flight recorder according to the present invention.

[0023] Figure 2 Schematic diagram of the card connection status. DETAILED DESCRIPTION

[0024] The present invention is further described in detail below in conjunction with the accompanying drawings. The detailed description is an explanation made in conjunction with the exemplary embodiments of the present invention, including various details of the embodiments of the present invention to facilitate understanding, which should be considered as merely exemplary. Therefore, it should be recognized by those skilled in the art that various changes and modifications can be made to the embodiments described herein without departing from the scope and spirit of the present invention. Similarly, for the sake of clarity and conciseness, the description of well-known functions and structures is omitted in the following description.

[0025] like Figure 1 , Figure 2As shown, the present invention provides an ejection separation mechanism for a flight recorder, comprising:

[0026] The ejection spring 3 is made of nickel-titanium memory alloy; a hook 31 is provided at the top of the ejection spring 3;

[0027] The ejectable base 4 has a clamping member 41 on its bottom surface, and the clamping member 41 is clamped with the hook body 31;

[0028] A mounting base 1 is provided with a mounting column 2, and a ejection spring 3 is sleeved on the mounting column 2;

[0029] The mounting column 2 has a hollow inner cavity, and the electric heater 5 is arranged in the inner cavity;

[0030] The lower end of the electric heater 5 is connected to a power supply wire 6 , and the power supply wire 6 passes through the mounting base 1 and is connected to a power module.

[0031] On the basis of the above technical solution, an annular flange 21 is provided at the lower part of the mounting column 2 , and the lower end of the ejection spring 3 abuts against the annular flange 21 .

[0032] like Figure 2 As shown, in the clamping state, the ejection spring 3 is in a compressed energy storage state, and the annular flange 21 abuts against the lower end of the ejection spring 3 to limit the ejection spring 3; the clamping member 41 hooks the hook body 31 and presses the hook body 31 downward. The clamping member 41 limits the ejection spring 3 on the one hand, and makes the ejection spring 3 in a compressed energy storage state on the other hand.

[0033] On the basis of the above technical solution, the electric heater 5 generates heat when powered on, so that the hook 31 at the top of the ejection spring 3 changes shape into a straight line due to the heat, thereby releasing the clamping member 41 .

[0034] Figure 1 Shows the ejection status, Figure 2 Shows the snap-in status.

[0035] On the basis of the above technical solution, a slot adapted to the clamping member 41 is provided at the upper end of the mounting column 2 .

[0036] On one hand, the clamping member 41 hooks the hook body 31 and presses the hook body 31 downwards, and on the other hand, the clamping member 41 is plugged into the slot, so that the ejectable base 4 is fixed to the upper end of the mounting column 2 .

[0037] On the basis of the above technical solution, anti-slip grooves or limit slots are provided in the slot.

[0038] In order to ensure the firmness of the connection between the hook body 31 and the clamping piece 41, and to ensure that the ejectable base 4 is reliably fixed to the upper end of the mounting column 2, anti-slip grooves or limit slots are provided in the slot so that a certain friction force is formed between the clamping piece 41 and the mounting column 2 to prevent the clamping piece 41 from accidentally falling off.

[0039] When ejection is not required, the hook body 31 is engaged with the clamping member 41, and the clamping member 41 is inserted into the slot to fix the flight recorder on the ejectable base 4;

[0040] In the clamping state, the ejection spring 3 mounted on the mounting column 2 is in a compressed energy storage state;

[0041] In the ejection state (for example, when a flight accident occurs), the power module energizes the electric heater 5 through the power supply wire 6 according to the instruction. The electric heater 5 generates heat in the energized state to raise its temperature to the deformation temperature. The nickel-titanium memory alloy of the hook body 31 is deformed by heat, and the shape of the hook body 31 changes to a straight line. The clamping part 41 is no longer clamped by the hook body 31. Driven by the deformation and release of the elastic force of the ejection spring 3, the clamping part 41 is separated from the slot, and the ejection base 4 is ejected. In this way, the flight recorder is ejected.

[0042] By combining shape memory alloy with electric heater, the rapid formation of shape memory alloy can be utilized to quickly eject the flight recorder ejection body in the event of a flight accident, thereby ensuring the reliability of the ejection.

[0043] The contents not described in detail in this specification belong to the prior art known to professional and technical personnel in this field.

[0044] The above description is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above embodiment. Any equivalent modifications or changes made by those skilled in the art based on the contents disclosed by the present invention should be included in the protection scope recorded in the claims.

Claims

1. An ejection separation mechanism for a flight recorder, characterized in that: include: The ejection spring (3) is made of nickel-titanium memory alloy; a hook body (31) is provided at the top of the ejection spring (3); The ejectable base (4) has a clamping piece (41) on its bottom surface, and the clamping piece (41) is clamped with the hook body (31); A mounting base (1) is provided with a mounting column (2), and a ejection spring (3) is sleeved on the mounting column (2); The mounting column (2) has a hollow inner cavity, and the electric heater (5) is arranged in the inner cavity; The lower end of the electric heater (5) is connected to a power supply wire (6), and the power supply wire (6) passes through the mounting base (1) and is connected to a power module.

2. The ejection separation mechanism of a flight recorder according to claim 1, characterized in that: An annular flange (21) is provided at the lower part of the mounting column (2), and the lower end of the ejection spring (3) abuts against the annular flange (21).

3. The ejection separation mechanism of a flight recorder according to claim 1, characterized in that: The electric heater (5) generates heat when powered on, causing the hook body (31) at the top of the ejection spring (3) to change shape into a straight line due to the heat, thereby releasing the clamping member (41).

4. The ejection separation mechanism of a flight recorder according to claim 1, characterized in that: The upper end of the mounting column (2) is provided with a slot adapted to the clamping piece (41).

5. The ejection separation mechanism of a flight recorder as claimed in claim 4, characterized in that: Anti-slip grooves or limit slots are arranged in the slot.

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