Aircraft load release mechanism

Abstract

The invention discloses a mechanism for releasing aircraft load, belonging to the field of aircraft technology; the mechanism comprises a push rod barrel, a push rod, a sleeve, a bottom screw, an electric pin puller, a buffer pad, a spring, and a steel sleeve; the electric pin puller is installed on the push rod barrel as an unlocking device, the spring is installed on the push rod as a power source, one end of the push rod is fixedly connected to the sleeve, and the other end passes through the second center hole on the push rod barrel and is connected to the bottom screw; after the sleeve compresses the spring, the sleeve is limited by the pin shaft on the electric pin puller, and when released, the electric pin puller releases the limit of the sleeve by pulling the pin, and the spring drives the load to be released by the push rod. The invention adopts the spring as the power source and releases the load in a limited space by unlocking the electric pin puller, and the release impact is small, the synchronization is high, the consistency is good, and it has the advantages of simple structure, easy assembly, low cost, and reusability.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft, and in particular relates to a mechanism for releasing aircraft load. Background Art

[0002] With the rapid development of aircraft technology, a large number of high-precision detection equipment, micro-weapons and equipment, and small observation satellites have been widely used. The functions of the payloads carried by aircraft have become more diversified, and the structure and composition have become smaller and more complex. Payload release technology has become a research hotspot in the field of aircraft and is directly related to the completion of subsequent tasks.

[0003] Aircraft are limited by space and cost, and the electronic and complex trend of payloads is sensitive to load impact, which puts high demands on the release power source. Most traditional release mechanisms use pyrotechnic mechanisms, which are large in size, high in cost, poor in safety, cause serious pollution after detonation, easily form accompanying flying objects, have large load impact, and cannot be reused, making it increasingly difficult to meet new requirements. Summary of the invention

[0004] In view of the deficiencies in the prior art, the present invention provides a mechanism for releasing aircraft loads, which uses a spring as a power source and an electric pin puller to release the load in a limited space. The release has a small impact, high synchronization, and good consistency. It also has the advantages of simple structure, easy assembly, low cost, and reusability.

[0005] The present invention provides a mechanism for releasing aircraft loads, characterized in that the mechanism mainly comprises a push rod tube, a push rod, a sleeve, a bottom screw, an electric pin puller, a buffer pad, a spring, a steel sleeve, etc.

[0006] The push rod barrel is a stepped cylindrical structure, and a first step hole is provided at its rear end to form a clearance fit with the outer wall of the sleeve; a flange is provided at the root of the rear end of the push rod barrel, and a screw hole is provided on the flange, which is fixedly connected to the aircraft cabin by screws; a boss is provided on the rear end cylinder body of the push rod barrel, and a first center hole and a screw hole are provided on the boss, and the electric pin puller passes through the first center hole and is fixed to the boss by screws; a second step hole is provided at the front end of the push rod barrel for radially limiting the spring; a second center hole is provided on the front end wall of the push rod barrel.

[0007] The sleeve is installed inside the push rod tube, and the outer side of its end is conformal with the effective load and forms the action surface of the effective load through a fixedly connected buffer pad. The inner side of its end is provided with a screw hole for accommodating the push rod, and the outer wall of the sleeve is provided with a step hole for installing the steel sleeve.

[0008] The steel sleeve is stepped, the outer wall of the steel sleeve is nested in the stepped hole of the sleeve through interference fit, and the pin shaft of the electric pin puller is arranged in the inner hole of the steel sleeve to limit the sleeve. The steel sleeve is made of high-strength and high-abrasion-resistant material.

[0009] The push rod passes through the second center hole, one end of which is fixedly connected to the bottom screw, and the other end is provided with a flange disc for constraining the axial movement of the spring. The flange disc is provided with a step through hole for fixing it in the sleeve by screws.

[0010] The spring is mounted on the push rod.

[0011] When the mechanism is locked, the sleeve compresses the spring through the push rod, and the electric pin puller limits the sleeve through the pin shaft; when the mechanism is released, the electric pin puller releases the limit of the sleeve through the pin pulling action, and the spring drives the load to be released through the push rod, and the bottom screw moves with the push rod until it is limited by the end wall of the push rod tube, and the spring stops doing work on the load.

[0012] Furthermore, the distance between the bottom screw and the push rod tube is smaller than the length of the matching surface between the sleeve and the push rod tube, so that the working stroke is smaller than the guide stroke, thereby ensuring the stability and consistency of the thrust during release.

[0013] Furthermore, the push rod is configured as a hollow cylindrical structure, and the sleeve, the push rod, and the bottom screw are all made of low-density alloy materials. A lightening hole may also be provided on the sleeve body. Such a configuration can reduce the weight of the invalid load and increase the work efficiency of the spring on the effective load.

[0014] Furthermore, the outer diameter of the steel sleeve is smaller than the diameter of the first center hole on the push rod tube, and the steel sleeve is pressed by the sleeve and the push rod tube to ensure the stability of the steel sleeve when the pin is pulled out.

[0015] The present invention can achieve a certain release speed of the effective load in a limited space and effectively reduce the release overload. Specifically, the present invention has the following advantages:

[0016] (1) The design of using an electric pin puller to unlock and a spring as the power source for release reduces the impact during unlocking and releasing, improves the reliability and consistency of the mechanism, and also has the advantages of energy saving, environmental protection, and reusability;

[0017] (2) Simple structure, small space occupation, easy assembly and low cost;

[0018] (3) The working capacity is adjustable by changing the length of the sleeve rod, that is, changing the distance from the bottom screw to the sleeve rod barrel, adjusting the working stroke, and then adjusting the release speed;

[0019] (4) It has strong adaptability and can be used for load release of various types of aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 A schematic structural diagram of an aircraft load release mechanism provided by the present invention.

[0021] Figure 2 The present invention is a structural cross-sectional view of an aircraft load release mechanism provided by the present invention.

[0022] Figure 3 It is a structural cross-sectional view of the push rod tube of the present invention.

[0023] In the figure: 1-push rod tube; 11-flange; 12-first step hole; 13-first center hole; 14-second step hole; 15-second center hole; 16-end wall; 17-boss; 2-push rod; 3-sleeve; 4-bottom screw; 5-electric pin puller; 6-buffer pad; 7-spring; 8-steel sleeve. DETAILED DESCRIPTION

[0024] The specific embodiments of the present invention are further described below in conjunction with the accompanying drawings. It should be noted that the description of these embodiments is used to help understand the present invention, but does not constitute a limitation of the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0025] like Figure 1 , Figure 2 As shown, the embodiment of the present invention includes a push rod barrel 1, a push rod 2, a sleeve 3, a bottom screw 4, an electric pin puller 5, a buffer pad 6, a spring 7, a steel sleeve 8 and the like.

[0026] like Figure 3 As shown, the push rod tube 1 is a stepped cylindrical structure, made of aluminum alloy, and its rear end is provided with a first step hole 12 that forms a clearance fit with the outer wall of the sleeve 3; a square flange 11 is provided at the root of the rear end of the push rod tube 1, and 4 screw holes are provided on the flange 11, which is fixedly connected to the aircraft cabin through 4 screws; a plane boss 17 is provided on the rear end cylinder of the push rod tube 1, and a first center hole 13 and 4 screw holes are provided on the boss 17, and the electric pin puller 5 passes through the first center hole 13 and is fixed on the boss 17 by 4 screws; a second step hole 14 for radially limiting the spring 7 is provided at the front end of the push rod tube 1; a second center hole 15 is provided on the front end wall 16 of the push rod tube 1.

[0027] The sleeve 3 is installed inside the push rod tube 1. The material is aluminum alloy. The outer side of its end is set to an arc surface conformal to the payload. A buffer pad 6 of appropriate thickness is pasted according to the gap between the arc surface and the payload. After installation, the buffer pad 6 should fit the payload exactly or be slightly compressed, which can play a role in shock absorption of the payload during flight and reducing impact during release; 4 screw holes for installing the push rod 2 are set on the inner side of the end of the sleeve 3, and 4 structural lightening holes and 1 step hole for installing the steel sleeve 8 can be set on the outer wall of the sleeve 3. The outer wall diameter of the step hole on the sleeve 3 is large and the inner wall diameter is small; the inner wall diameter of the sleeve 3 is consistent with the second step hole 14.

[0028] The steel sleeve 8 is stepped and made of high-strength, high-abrasion-resistant steel. The outer wall step surface of the steel sleeve 8 is nested in the step hole of the sleeve 3 through interference fit, and does not protrude from the inner and outer walls of the sleeve 3 after installation; the outer diameter of the steel sleeve 8 is smaller than the diameter of the first center hole 13 on the push rod tube 1, and the steel sleeve 8 is pressed by the sleeve 3 and the push rod tube 1 after installation; the inner hole of the steel sleeve 8 is used to fix the pin shaft of the electric pin puller 5, and has a clearance fit with the pin shaft.

[0029] The electric pin puller 5 of the present invention can be a ready-made product, which can be directly installed in the aircraft load release structure of the present invention after purchase. Figure 1 and Figure 2 The diagram only shows the structural relationship of the electric pin puller 5 in the load release structure, and does not show the specific internal structure of the pin puller 5 and its actuation structure principle. For the aircraft load release structure described in the present invention, the clearance fit relationship between the inner hole of the steel sleeve 8 and the pin shaft of the electric pin puller 5 means that when the pin shaft of the electric pin puller 5 is pulled out of the inner hole of the steel sleeve 8 and unlocked, the spring 7 as the power source for release starts to push the push rod 2 to do work, driving the load release.

[0030] The push rod 2 is a hollow cylindrical aluminum alloy structure. When installed, it passes through the second center hole 15, and one end is fixedly connected to the bottom screw 4. After the push rod 2 is installed, the distance between the bottom screw 4 and the push rod tube 1 is 45mm, which is less than the length of the matching surface of the sleeve 3 and the push rod tube 1 of 55mm; the other end of the push rod 2 is provided with a flange disc to constrain the axial movement of the spring 7, and the flange disc is provided with 4 stepped through holes that are fixedly connected to the sleeve 3 by 4 screws. The spring 7 is installed on the push rod 2.

[0031] The screw holes provided on the flange 11, the screw holes provided on the boss 17, the structural lightening holes provided on the outer wall of the sleeve 3, and the step through holes provided on the flange disc in the present invention can each have more than three, and they can each have different numbers according to specific circumstances or differences in structure and volume. For example, in this embodiment, four are used for each.

[0032] The above is only a preferred embodiment of the present invention, but the present invention should not be limited to the contents disclosed in the embodiment and the drawings. Therefore, any equivalent or modification completed without departing from the spirit disclosed in the present invention shall fall within the scope of protection of the present invention.

Claims

1. An aircraft load release mechanism, comprising a push rod tube (1), a push rod (2), a sleeve (3), a bottom screw (4), an electric pin puller (5), a buffer pad (6), a spring 7, and a steel sleeve 8, characterized in that: The push rod tube (1) is a stepped cylindrical structure, and a first stepped hole (12) is provided at its rear end to form a clearance fit with the outer wall of the sleeve (3); a flange (11) is provided at the root of the rear end of the push rod tube (1), and a screw hole is provided on the flange (11) to be fixedly connected to the aircraft cabin; a boss (17) is provided on the rear end cylinder body of the push rod tube (1), and a first center hole (13) and a screw hole are provided on the boss (17), and the electric pin puller (5) passes through the first center hole (13) and is fixed to the boss (17) by screws; a second stepped hole (14) is provided at the front end of the push rod tube (1) to radially limit the spring (7); a second center hole (15) is provided on the end wall (16) of the push rod tube (1); The sleeve (3) is installed inside the push rod tube (1), and the outer side of its end is conformal with the effective load and forms an effective load action surface through a fixedly connected buffer pad (6). The inner side of the end is provided with a screw hole for accommodating the push rod (2); the outer wall of the sleeve (3) is provided with a stepped hole for accommodating the steel sleeve (8); The steel sleeve (8) is in a step shape, the outer wall of which is nested on the sleeve (3) by interference fit, and the inner hole and the pin shaft of the electric pin puller (5) are clearance fit; The push rod (2) passes through the second center hole (15), one end of which is fixedly connected to the bottom screw (4), and the other end of which is provided with a flange disc for constraining the axial movement of the spring (7), and the flange disc is provided with a stepped through hole for fixing it in the sleeve (3) by screws; the spring (7) is installed on the push rod (2).

2. An aircraft load release mechanism according to claim 1, characterized in that: The distance between the bottom screw (4) and the push rod tube (1) is smaller than the length of the matching surface between the sleeve (3) and the push rod tube (1).

3. The aircraft load release mechanism according to claim 1, characterized in that: The sleeve (3) is provided with a lightening hole on its body.

4. An aircraft load release mechanism according to claim 1, 2 or 3, characterized in that: The screw holes provided on the flange (11), the screw holes provided on the boss (17), the lightening holes provided on the sleeve (3), and the stepped through holes provided on the flange disc may each be more than three.

5. The aircraft load release mechanism according to claim 3, characterized in that: There are more than three lightening holes arranged on the sleeve (3).

6. An aircraft load release mechanism according to claim 1, 2 or 3, characterized in that: The push rod (2) is configured as a hollow cylindrical structure, and the sleeve (3), the push rod (2) and the bottom screw (4) are all made of low-density alloy materials.

7. The aircraft load release mechanism according to claim 1, characterized in that: The outer diameter of the steel sleeve (8) is smaller than the diameter of the first center hole (13) on the push rod tube (1). The steel sleeve (8) is pressed tightly by the sleeve (3) and the push rod tube (1) to ensure the stability of the steel sleeve (8) when the pin is pulled out.

8. An aircraft load release mechanism according to claim 1 or 7, characterized in that: The steel sleeve (8) is made of a high-strength, high-abrasion-resistance material.

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