Universal spring type adapter and load adjusting method

Abstract

The universal spring type adapter comprises a body, the front face of the body is provided with an abutting assembly used for being matched with the body to abut against an aircraft, and the back face of the body is provided with an antifriction piece; the aircraft can be quickly separated after being taken out of the cylinder, the friction resistance on the contact surface of the adapter and the inner wall of the cylinder is reduced, and the clamping stagnation phenomenon during filling and working of the aircraft is avoided.

Description

Technical Field

[0001] The invention relates to the technical field of mechanical design and manufacturing, in particular to a universal spring type adapter and a load adjustment method. Background Art

[0002] In the barrel launch system, the radial vibration reduction support system is used between the aircraft and the inner wall of the barrel to achieve the functions of shock absorption, support, centering during the storage and transportation of the aircraft, as well as the guidance during the launch. When the aircraft moves in the barrel, the adapter should effectively match the gap between the aircraft and the inner wall of the barrel to reliably ensure the stability of the aircraft's motion posture. After the aircraft leaves the barrel, the adapter should leave the barrel with the aircraft and separate from the aircraft, and a certain initial separation speed must be met.

[0003] The traditional adapter has a complex structure and cannot adjust the gap between the adapter and the inner wall of the tube in real time during the movement of the aircraft. The adapter has no buffering function and is prone to permanent deformation under long-term load, making the original interference fit design invalid. When the adapter is separated from the aircraft, the separation force is not large enough and the horizontal separation distance is short. It cannot be separated quickly and effectively to avoid the flight space of the aircraft. After separation, it falls onto the vehicle-mounted equipment, causing damage to the launch system device. Summary of the invention

[0004] In order to solve the above technical problems, the present invention provides a universal spring type adapter and a load adjustment method.

[0005] The present invention is achieved through the following technical solutions.

[0006] The present invention provides a universal spring-type adapter, which comprises a body. A tightening assembly is arranged on the front of the body for tightening an aircraft in cooperation with the body, and a friction-reducing plate is arranged on the back of the body.

[0007] Preferably, the adjustment assembly includes a guide support rod, a support seat and a spring. A receiving groove is opened on the front side of the main body, and the support seat is installed in the receiving groove. One end of the guide support rod is slidably set in the support seat, and the other end passes through the support seat. Both ends of the spring abut between the bottom of the support seat and the guide support rod.

[0008] Preferably, a sleeve is provided at one end of the guide support rod close to the support seat, and one end of the spring abuts against the sleeve.

[0009] Preferably, a pressing plate is provided at the open end of the support seat, and the pressing plate and the support seat are fixed to the body by connecting screws.

[0010] Preferably, the body surface is configured as an arc-shaped surface.

[0011] Preferably, a side surface of the main body is provided with a windward surface, and the windward surface is inclined.

[0012] Preferably, the friction reducing plate is fixed to the back side of the main body by means of a clamping screw.

[0013] Preferably, the body is made of hard polyurethane foam material.

[0014] Preferably, the friction reducing plate is made of polytetrafluoroethylene rubber material.

[0015] In another aspect, the present invention further provides a method for adjusting the load of a universal spring-type adapter, comprising the following steps:

[0016] S1: Before installing the adapter, multiple guide support rods with different sleeve sizes are provided, and multiple springs with different elastic forces are adapted in sequence;

[0017] S2: Install the spring in the support seat, limit the spring and the guide support rod on the support seat through the pressure plate, and the spring adjusts the moving distance of the guide support rod;

[0018] S3: Install the adapter between the inner side of the launch tube and the aircraft. The spring pushes the head of the guide support rod into the preset slot of the aircraft, so that the adapter is pressed tightly between the launch tube and the aircraft. The elastic force of the spring determines the tightness of the adapter.

[0019] S4: During the launch of the aircraft, the separation trajectory of the aircraft is verified and the flight trajectory of the aircraft is recorded;

[0020] S5: Replace the guide support rods of other sizes and the corresponding springs into the adapter, install the corresponding adapter between the launch tube and the aircraft, and record the flight trajectory of the aircraft when the aircraft is launched;

[0021] S6: Test multiple groups of springs with different elastic forces, analyze the flight trajectories of the aircraft in different groups of adapters, test the most suitable guide support rods and matching springs, and realize the load adjustment of the adapter between the launch tube and the aircraft.

[0022] The beneficial effects of the present invention are:

[0023] 1. Install the guide support rod and spring on the support seat, limit them through the pressure plate, match the appropriate spring size and the corresponding guide support rod, effectively adapt to the structural size tolerances of various cylinders and aircraft, and efficiently achieve the matching of the gap between the aircraft and the inner wall of the cylinder, the transportation support and the transmission of the working load. Due to the rebound effect of the spring, the aircraft can be quickly separated after leaving the cylinder, and the spring makes the aircraft have a certain buffering effect during the launch process.

[0024] 2. The friction reducing plate is made of polytetrafluoroethylene rubber sheet. The friction coefficient of the polytetrafluoroethylene rubber sheet on the side in contact with the inner arm of the tube is 0.1-0.3, which reduces the friction resistance on the contact surface between the adapter and the inner wall of the tube, and avoids the jamming phenomenon during the loading and operation of the aircraft.

[0025] 3. The pressure plate is installed on the support seat by connecting screws, which is convenient for installing springs of different specifications, including spring middle diameter, spring material diameter, spring stiffness, free height and other parameters. According to the axial movable displacement of the guide support rod between the support seat and the pressure plate, the installation length and working length of the spring are designed, the installation load and working load are determined, and the spring load can be flexibly adjusted.

[0026] 4. By setting the windward surface, at the moment when the adapter comes out of the tube with the aircraft, the windward surface is used to capture and guide the wind force, thereby improving the separation efficiency between the adapter and the aircraft. In addition, with the appropriate spring return load, the design of the windward surface reduces the overall weight of the adapter, speeds up the rapid separation of the adapter after it comes out of the tube with the aircraft, and quickly avoids the flight space of the aircraft, effectively improving the safety and reliability of the aircraft launch.

[0027] 5. The main body is made of hard polyurethane foam material with a density of about 400kg / m3 and a stiffness of about 1×108N / m. It has the functions of lightness, compression resistance and shock absorption. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a schematic diagram of the structure of the present invention;

[0029] Figure 2 It is a structural schematic diagram mainly used for displaying the internal structure of the present invention;

[0030] Figure 3 is a side view of the present invention;

[0031] Figure 4 The present invention Figure 3 Schematic diagram of the cross-sectional structure of AA;

[0032] Figure 5 It is a structural schematic diagram mainly used to show the connecting screws in the present invention;

[0033] In the figure: 1-main body; 2-friction reducing plate; 3-tensioning screw; 4-spring mechanism; 5-support seat; 6-spring; 7-guide support rod; 8-pressure plate; 9-connecting screw; 10-windward surface. DETAILED DESCRIPTION

[0034] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0035] It should be noted that all directional indications in the embodiments of the present invention (such as up, down, left, right, front, back, etc.) are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0036] In this embodiment, refer to Figure 1 and Figure 3 , including a body 1, which is made of a hard polyurethane foam material with a density of about 400kg / m3 and a stiffness of about 1×108N / m, and has the functions of lightness, pressure resistance and shock absorption; the surface of the body 1 is set as an arc surface, so that the outer side and the inner side of the body 1 are respectively attached to the inner wall of the tube and the outer wall of the aircraft, so that the adapter can be better pressed between the inner wall of the tube and the aircraft; at the same time, a windward surface 10 is set on the side of the body 1, and the windward surface 10 is set at an angle. At the moment when the adapter comes out of the tube with the aircraft, the windward surface 10 is used to capture and guide the wind force. At the same time, the design of the windward surface 10 reduces the overall weight of the adapter, and the adapter can be quickly separated after coming out of the tube with the aircraft.

[0037] In this embodiment, refer to Figure 2 , Figure 3 , Figure 4 and Figure 5 , an adjusting assembly 4 is provided on the front of the body 1, which is used to cooperate with the body 1 to press tightly between the aircraft and the inner wall of the launch tube. The adjusting assembly 4 includes a guide support rod 7, a support seat 5 and a spring 6. A receiving groove is provided on the front of the body 1, and the support seat 5 is installed in the receiving groove. One end of the guide support rod 7 is slidably arranged in the support seat 5, and the other end passes through the support seat 5. A sleeve is provided at one end of the guide support rod 7 close to the support seat 5, one end of the spring 6 abuts in the sleeve, and the other end of the spring 6 abuts on the bottom of the support seat 5, which has a certain guiding and protective effect on the spring 6 during the telescopic process; a pressing plate 8 is provided at the open end of the support seat 5, and the pressing plate 8 and the support seat 5 are fixed to the body 1 by connecting screws 9, and one end of the guide support rod 7 is limited in the support seat 5 by the pressing plate 8, which is convenient for limiting and stabilizing the spring 6 and the guide support rod 7, and also convenient for assembling and disassembling the spring 6 and the guide support rod 7.

[0038] In this embodiment, refer to Figure 1A friction reducing plate 2 is arranged on the back of the body 1. The friction reducing plate 2 is made of polytetrafluoroethylene rubber material with a friction coefficient of 0.1 to 0.3. Two friction reducing plates 2 are arranged. Two mounting grooves are provided on the back of the body 1. The two friction reducing plates 2 are respectively placed in the two mounting grooves, and then the friction reducing plates 2 are fixed in the mounting grooves by multiple clamping screws 3, which reduces the friction resistance of the contact surface between the adapter and the inner wall of the cylinder, and avoids the jamming phenomenon during the loading and operation of the aircraft.

[0039] The working principle of this embodiment is as follows: the support seat 5 is installed in the accommodating groove, and the spring 6 and the guide support rod 7 adapted to the corresponding gap between the launch tube and the aircraft are placed in the support seat 5, one end of the spring 6 is pressed against the sleeve of the guide support rod 7, and the pressure plate 8 is pressed against the opening of the support seat 5, and the pressure plate 8 and the support seat 5 are fixed to the main body 1 together by connecting screws 9, so that the spring 6 and the guide support rod 7 are limited in the support seat 5, and the adapter is installed between the launch tube and the aircraft. The guide support rod 7 is pushed into the specific groove of the aircraft under the action of the spring 6, so that the adapter is pressed against the inner wall of the launch tube and the aircraft. When the aircraft is launched, the spring 6 pushes the adapter to quickly separate from the aircraft through its own elastic load, which effectively improves the safety and reliability of the aircraft launch process.

[0040] A preferred embodiment of the present invention further provides a load adjustment method for a universal spring-type adapter, comprising the following steps:

[0041] S1: Before installing the adapter, a plurality of guide support rods 7 with different sleeve sizes are provided, and a plurality of springs 6 with different elastic forces are sequentially adapted;

[0042] S2: Install the spring 6 in the support seat 5, and limit the spring 6 and the guide support rod 7 on the support seat 5 through the pressure plate 8, and the spring 6 adjusts the moving distance of the guide support rod 7 on the support seat 5;

[0043] S3: Install the adapter between the inner side of the launch tube and the aircraft. The spring 6 pushes the head of the guide support rod 7 into the preset slot of the aircraft, so that the adapter is pressed tightly between the launch tube and the aircraft. The elastic force of the spring 6 determines the tightness of the adapter.

[0044] S4: During the launch of the aircraft, the separation trajectory of the aircraft is verified and the flight trajectory of the aircraft is recorded;

[0045] S5: Replace the guide support rod 7 and the corresponding spring 6 of other sizes in the adapter, install the corresponding adapter between the launch tube and the aircraft, and record the flight trajectory of the aircraft when the aircraft is launched;

[0046] S6: Test multiple groups of springs 6 with different elastic forces, analyze the flight trajectories of the aircraft in different groups of adapters, test the most suitable guide support rod 7 and matching spring 6, and realize load adjustment of the adapter between the launch tube and the aircraft.

[0047] The above are only preferred embodiments of the present invention, and are not intended to limit the patent scope of the present invention. All equivalent structural changes made using the contents of the present invention's specification and drawings, or directly / indirectly applied in other related technical fields, are included in the patent protection scope of the present invention.

Claims

1. A universal spring-type adapter, characterized in that: It comprises a main body (1), the front of which is provided with an adjustment assembly (4) for cooperating with the main body (1) to press tightly between the aircraft and the inner wall of the tube, and the back of the main body (1) is provided with a friction reducing plate (2).

2. A universal spring-type adapter as claimed in claim 1, characterized in that: The adjustment assembly (4) comprises a guide support rod (7), a support seat (5) and a spring (6); a receiving groove is provided on the front of the body (1); the support seat (5) is installed in the receiving groove; one end of the guide support rod (7) is slidably arranged in the support seat (5); the other end passes through the support seat (5); and both ends of the spring (6) are abutted between the bottom of the support seat (5) and the guide support rod (7).

3. A universal spring-type adapter as claimed in claim 2, characterized in that: A sleeve is provided at one end of the guide support rod (7) close to the support seat (5), and one end of the spring (6) abuts against the inside of the sleeve.

4. A universal spring-type adapter as claimed in claim 2, characterized in that: A pressing plate (8) is provided at the open end of the support seat (5), and the pressing plate (8) and the support seat (5) are fixed to the body (1) by connecting screws (9).

5. A universal spring-type adapter as claimed in claim 1, characterized in that: The surface of the body (1) is arranged as an arc-shaped surface.

6. A universal spring-type adapter as claimed in claim 1, characterized in that: The side surface of the body (1) is provided with a windward surface (10), and the windward surface (10) is arranged in an inclined manner.

7. A universal spring adapter and load adjustment method as claimed in claim 1, characterized in that: The friction reducing plate (2) is fixed to the back side of the main body (1) by means of a clamping screw (3).

8. A universal spring-type adapter as claimed in claim 1, characterized in that: The body (1) is made of hard polyurethane foam material.

9. A universal spring-type adapter as claimed in claim 1, characterized in that: The friction reducing plate (2) is made of polytetrafluoroethylene rubber material.

10. A load adjustment method for a universal spring-type adapter according to any one of claims 1 to 9, characterized in that: The following steps are involved: S1: Before installing the adapter, a plurality of guide support rods (7) with different sleeve sizes are provided, and a plurality of springs (6) with different elastic forces are sequentially adapted; S2: Install the spring (6) in the support seat (5), and limit the spring (6) and the guide support rod (7) on the support seat (5) through the pressure plate (8), and the spring (6) adjusts the moving distance of the guide support rod (7); S3: The adapter is installed between the inner side of the launch tube and the aircraft, and the spring (6) pushes the head of the guide support rod (7) into the preset slot of the aircraft, so that the adapter is pressed tightly between the launch tube and the aircraft. The elastic force of the spring (6) determines the degree of pressing of the adapter; S4: During the launch of the aircraft, the separation trajectory of the aircraft is verified and the flight trajectory of the aircraft is recorded; S5: Replace the guide support rod (7) and the corresponding spring (6) of other sizes into the adapter, install the corresponding adapter between the launch tube and the aircraft, and record the flight trajectory of the aircraft when the aircraft is launched; S6: Test multiple groups of springs (6) with different elastic forces, analyze the flight trajectories of the aircraft in different groups of adapters, test the most suitable guide support rod (7) and matching spring (6), and realize load adjustment of the adapter between the launch tube and the aircraft.

Images