CN211869726U

CN211869726U - Universal composite material repairing instrument for aviation and aircraft

Info

Publication number: CN211869726U
Application number: CN201821614982.3U
Authority: CN
Inventors: 阎家奇; 刘旭东; 曹萧华
Original assignee: Zhejiang Sinus Iridum Engineering Technology Co ltd
Current assignee: Zhejiang Sinus Iridum Engineering Technology Co ltd
Priority date: 2018-09-30
Filing date: 2018-09-30
Publication date: 2020-11-06
Anticipated expiration: 2028-09-30

Abstract

The utility model discloses a general aviation aircraft combined material repairs appearance, including the computer, the outside of computer is equipped with display and computer input module, the inside of computer is equipped with central control module, display module, print module, pressure control module and temperature control module, computer input module display module print module pressure control module, temperature control module respectively with central control module electric connection, display module with display electric connection. The utility model forms negative pressure in the composite material repairing area to meet the laminating requirement in the composite material repairing and can carry out accurate pressure inspection and adjustment; the utility model applies the heating function with adjustable temperature to the composite material repair area, and can realize the control of the heating rate, the heating process, the temperature maintaining time and the cooling rate for the heating; so as to ensure the repairing effect and quality of the composite material.

Description

Universal composite material repairing instrument for aviation and aircraft

Technical Field

The patent of the utility model relates to an aircraft maintenance technical field specifically is general aviation aircraft combined material repair appearance.

Background

With the continuous maturity of composite material technology, the excellent performance of the composite material promotes the part proportion of the composite material in the general aviation aircraft to be higher and higher, so that a huge composite material repair requirement is generated in the domestic general aviation aircraft repair market, but the aircraft composite material repair process comprises the following steps:

1. poor adhesion of the composite material (e.g., bubbles, delamination of the material) can result in insufficient strength of the composite material, resulting in breakage of the composite material at the site under certain conditions, resulting in an aircraft accident;

2. the outer surface of the composite material does not meet the aerodynamic requirements (for example, potholes and even bulges), which affects the aesthetic appearance of the airplane, and affects the aerodynamics of the airplane, and therefore the flight of the airplane.

The reasons for the above 2 problems are:

1. in the bonding process of the composite material repairing process, air at the bonding position is not exhausted, and air is left to form bubbles;

2. in the repairing process, pressure with controllable balanced pressure value is not applied to the bonding part, so that partial area pressure is caused, partial pressure is small, and bonding is not uniform;

3. inaccurate and uneven control causes too fast or too slow heating, which affects the bonding effect.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a general aviation aircraft combined material repairs appearance, has solved the problem that proposes among the background art.

In order to achieve the above object, the patent of the utility model provides a following technical scheme: general aviation aircraft combined material repairs appearance, including the computer, the outside of computer is equipped with display and computer input module, the inside of computer is equipped with central control module, display module, printing module, pressure control module and temperature control module, computer input module display module print the module pressure control module, temperature control module respectively with central control module electric connection, display module with display electric connection.

As a preferred embodiment of the patent of the utility model, the outside of computer is equipped with vacuum pump and pressure sensor, pressure sensor with pressure control module electric connection, and the vacuum pump with pressure control module electric connection.

As a preferred embodiment of the patent of the utility model, the outside of computer is equipped with heating element and temperature sensor, temperature sensor with temperature control module electric connection, and heating element with temperature control module electric connection.

As a preferred embodiment of the present invention, the outside of the computer is provided with a printer, the printer with the print module electric connection, the printer with the computer electric connection.

Compared with the prior art, the utility model discloses a beneficial effect as follows:

1. the computer of the utility model is provided with a common maintenance scheme, which simplifies the maintenance process and improves the maintenance speed; meanwhile, self-editing can be carried out, and a more accurate maintenance scheme can be designed according to the requirement; and manual real-time control of the maintenance process can also be carried out.

2. The equipment of the utility model forms negative pressure in the composite material repairing area through the pressure control module, the vacuum pump and the pressure sensor so as to meet the laminating requirement in the composite material repairing and can carry out accurate pressure inspection and adjustment;

3. the utility model can apply the heating function with adjustable temperature to the composite material repairing area by arranging the temperature control module, the heating component and the temperature sensor, and can realize the control of the heating rate, the heating process, the temperature maintaining time and the cooling rate for heating; so as to ensure the repairing effect and quality of the composite material.

4. The utility model monitors the working process through the display by arranging the printing module and the printer, records the measured temperature and pressure per second according to the content, and prints the parameters after the work is finished;

5. the utility model discloses equipment is friendly through setting up display and display module, can implement the demonstration to time, pressure and temperature, and can accomplish the settlement of repair procedure (including temperature and pressure) through the interface;

6. the operating parameters can be recorded every second for analysis with respect to maintenance results.

7. The whole body adopts a box type structural design, and is convenient to carry.

Drawings

Fig. 1 is a functional structure schematic diagram of the composite material repairing instrument for the general aviation aircraft.

In the figure, a computer 1, a display 2, a computer input module 3, a central control module 4, a display module 5, a printing module 6, a pressure control module 7, a temperature control module 8, a vacuum pump 9, a pressure sensor 10, a heating component 11, a temperature sensor 12 and a printer 13 are arranged.

Detailed Description

The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments, not all embodiments, of the present invention. Based on the embodiments in the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative work belong to the scope of the present invention.

Referring to fig. 1, the present invention provides a technical solution: general aviation aircraft combined material repairs appearance, including computer 1, computer 1's outside is equipped with display 2 and computer input module 3, computer 1's inside is equipped with central control module 4, display module 5, print module 6, pressure control module 7 and temperature control module 8, computer input module 3 display module 5 print module 6 pressure control module 7 and temperature control module 8 respectively with central control module 4 electric connection, display module 5 with display 2 electric connection.

Referring to fig. 1, the apparatus of the present invention forms a negative pressure in the composite material repair area through the pressure control module 7, the vacuum pump 9 and the pressure sensor 10, so as to meet the bonding requirement in the composite material repair, and can perform accurate pressure check and adjustment;

referring to fig. 1, a heating assembly 11 and a temperature sensor 12 are disposed outside the computer 1, the heating assembly 11 and the temperature sensor 12 are electrically connected to the temperature control module 8, and can apply a temperature-adjustable heating function to the composite material repair area and control the heating rate, the heating process, the temperature maintaining time and the cooling rate of the composite material repair area; so as to ensure the repairing effect and quality of the composite material.

Referring to fig. 1, a printer 13 is disposed outside the computer 1, and the printer 13 is electrically connected to the printing module 6, so as to print out a more accurate maintenance scheme as required, thereby facilitating analysis by a worker.

The utility model discloses a general aviation aircraft combined material repair appearance utilizes vacuum pump 9 to form the negative pressure in combined material repair area in the in-process of using, so as to meet the jointing requirement in the repair of the composite material, the pressure sensor 10 is utilized to carry out accurate pressure check and adjustment, meanwhile, the composite material repair area is utilized to exert the heating function with adjustable temperature, the heating rate, the heating process, the temperature maintaining time and the cooling rate can be controlled for heating, the central control module 4 is utilized to record the measured temperature and pressure per second, after the work is finished, the parameters are printed, the display module 5 is utilized to display the time, the pressure and the temperature, the repairing procedure can be completed through the interface, the process procedure stored in advance is directly called to carry out the repairing operation, and the repairing operation can also be carried out by utilizing the procedure and the field programming process.

The computer 1, the display 2, the computer input module 3, the central control module 4, the display module 5, the printing module 6, the pressure control module 7, the temperature control module 8, the vacuum pump 9, the pressure sensor 10, the heating assembly 11, the temperature sensor 12 and the printer 13 of the utility model are all universal standard parts or parts known by technicians in the field, and the structure and the principle of the parts are all known by technicians through technical manuals or conventional experimental methods, the problem solved by the utility model is that along with the continuous maturity of the technology of the composite material, the excellent performance of the parts can promote the proportion of the composite material in the universal aviation aircraft to be higher and higher, so huge composite material repair requirements are generated in the maintenance market of the domestic universal aviation aircraft, but the repair equipment of the composite material needs to be imported and the cost is very high, the devices are not available in China, and some alternative methods are generally adopted for repair, so that the problems of serious potential safety hazards and serious influence on flight safety exist. The utility model discloses a through set up the maintenance scheme commonly used in the system, simplify the maintenance flow, improve maintenance speed; meanwhile, self-editing can be carried out, and a more accurate maintenance scheme can be designed according to the requirement; the maintenance process can also be controlled manually in real time; through vacuum, negative pressure which can be continuously regulated, controlled and monitored is formed in a composite material repairing area so as to meet different bonding requirements in composite material repairing; the composite material repair area can be heated in a precisely controllable manner, so that the repair effect and quality of the composite material can be guaranteed; the working process can be monitored through the display; the operating parameters per second can be recorded so as to be analyzed for maintenance results; the box body type structural design is needed, and the carrying is convenient.

Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described above, or equivalents may be substituted for elements thereof. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. General aviation aircraft combined material repair appearance, including computer (1), its characterized in that: the outside of computer (1) is equipped with display (2) and computer input module (3), the inside of computer (1) is equipped with central control module (4), display module (5), print module (6), pressure control module (7) and temperature control module (8), computer input module (3) display module (5) print module (6) pressure control module (7), temperature control module (8) respectively with central control module (4) electric connection, display module (5) with display (2) electric connection.

2. The universal aircraft composite repair instrument according to claim 1, wherein: a vacuum pump (9) and a pressure sensor (10) are arranged outside the computer (1), the pressure sensor (10) is electrically connected with the pressure control module (7), and the vacuum pump (9) is electrically connected with the pressure control module (7).

3. The universal aircraft composite repair instrument according to claim 1, wherein: the outside of computer (1) is equipped with heating element (11) and temperature sensor (12), temperature sensor (12) with temperature control module (8) electric connection to and heating element (11) with temperature control module (8) electric connection.

4. The universal aircraft composite repair instrument according to claim 1, wherein: the outside of computer (1) is equipped with printer (13), printer (13) with print module (6) electric connection, printer (13) with computer (1) electric connection.