Double-screen supporting device capable of being flexibly adjusted in aircraft cockpit

Abstract

The invention discloses a flexibly adjustable double-screen support device in an aircraft cockpit, which comprises a cylindrical base and a flat tray, the outer side of the cylindrical base is sleeved with a damping ring and an outer cylinder, the cylindrical base is of a hollow structure internally provided with a strut, the strut is internally provided with a first torque hinge, and the first torque hinge is provided with a second torque hinge. The upper end of the first torque hinge is connected with a limiting block capable of rotating, the upper end of the limiting block is fixedly connected with a supporting frame, the two ends of the supporting frame are connected with two sets of movable assemblies, and each set of movable assembly comprises a second torque hinge, a lower supporting arm, a third torque hinge, an upper supporting arm, a fourth torque hinge and a quick-release connector. The end of the supporting frame is connected with the lower supporting arm through the second torque hinge, the lower supporting arm is connected with the upper supporting arm through the third torque hinge, and the upper supporting arm is connected with the quick-release connector through the fourth torque hinge. The multi-screen information classification display requirement in the cockpit can be met.

Description

Technical Field

[0001] The invention relates to a flexibly adjustable double-screen supporting device in an aircraft cockpit. Background Art

[0002] With the continuous advancement of aviation technology, the level of informatization and intelligence in aircraft cockpits is increasing. During the flight of an aircraft, pilots need to process a large amount of flight information at the same time to ensure flight safety. Therefore, multi-screen information classification display has become a key technology to be equipped in the aircraft cockpit. The existing traditional tablet computer holder can often only install one tablet computer, which cannot meet the needs of multi-screen information classification display. Moreover, the existing tablet computer support frame is mostly a single support structure, which is difficult to meet the complex and changeable use environment and space requirements in the aircraft cockpit, and cannot meet the needs of pilots to use tablet computers at different flight stages and angles, which to a certain extent affects the convenience and efficiency of flight operations. The equipment in the cockpit needs to have high stability and shock resistance to ensure that pilots can use tablet computers safely and conveniently during flight. Therefore, it is necessary to design a new support device to meet the needs of multi-screen information display and have higher stability and flexibility. Summary of the invention

[0003] The purpose of the present invention is to provide a flexibly adjustable dual-screen support device in an aircraft cockpit, which can simultaneously install two tablet computers, meet the multi-screen information classification display needs in the cockpit, and has better stability and flexibility.

[0004] The purpose of the present invention can be achieved through the following technical solutions.

[0005] A dual-screen support device that can be flexibly adjusted in an aircraft cockpit comprises a columnar base connected to a bottom plate and a tablet tray for mounting a tablet computer, wherein a shock absorbing ring and an outer cylinder are sleeved on the outer side of the columnar base from bottom to top, the columnar base is a hollow structure with a pillar installed inside, the columnar base, the outer cylinder and the pillar are fixedly connected to form an integral bottom support by a locking pin, a first torque hinge is installed inside the pillar, a rotatable limit block is connected to the upper end of the first torque hinge, the upper end of the limit block is fixedly connected to a support frame, two sets of movable components are connected to both ends of the support frame, each set of movable components comprises a second torque hinge, a lower support arm, a third torque hinge, an upper support arm, a fourth torque hinge and a quick-release joint, the end of the support frame is connected to the lower support arm through the second torque hinge, the lower support arm is connected to the upper support arm through the third torque hinge, the upper support arm is connected to the quick-release joint through the fourth torque hinge, and the quick-release joint is detachably clamped and fixed to the tablet tray through a concave-convex fitting structure.

[0006] The usage method of the present invention is as follows. One tablet computer is installed on each flat tray, and each torque hinge can be freely adjusted in angle. By combining multiple torque hinges, the positions and angles of the two flat trays can be adjusted. The pilot can place the tablet computer on the flat tray and achieve stable support of the tablet computer at different angles by adjusting the angles of the torque hinges. The outer cylinder provided on the outer side of the cylindrical base of the present invention can provide additional support. At the same time, the shock-absorbing ring provided below the outer cylinder can absorb the vibration from the base during the flight of the aircraft, and the torque hinge also has strong earthquake resistance, thereby ensuring the stability of the flat tray.

[0007] The present invention also has the following preferred designs:

[0008] A cover is provided at the upper end of the outer cylinder of the present invention. A first hollow hole is provided in the middle of the cover. The limiting block passes through the first hollow hole of the cover and then connects to the support frame. The cover is used to prevent dust and sundries from entering the outer cylinder and protect the internal structure.

[0009] Further, a snap ring is installed on the upper part of the limiting block. The snap ring is installed above the cover and is used to fix the cover to ensure the stable installation of the cover.

[0010] A support disk is fixedly connected to the bottom of the support frame of the present invention. A second hollow hole is provided in the middle of the support disk. The limiting block passes through the second hollow hole of the support disk and then connects to the support frame. The support disk can provide a larger support area for the support frame, and the support frame and the support disk can be connected into one body through fixing connectors such as bolts.

[0011] A long convex platform is provided at the upper end of the limiting block of the present invention. A long groove matching the long convex platform is opened in the middle of the support frame, and the long convex platform is clamped into the long groove.

[0012] The lower support arm and the upper support arm of the present invention form an L-shaped movable adjustment arm.

[0013] The present invention has the following beneficial effects:

[0014] 1. Multi-screen display. The double support structure of the present invention can install two tablet computers at the same time to achieve classified display of multi-screen information and improve the efficiency of the pilot to obtain information.

[0015] 2. Strong stability. Through the design of the shock-absorbing ring and the torque hinge, the present invention reduces the impact of vibration during flight on the tablet computer and ensures the stability and safety of the tablet computer.

[0016] 3. Wide adaptability. The support frame and the flat tray of the present invention can be adjusted according to the usage requirements in different flight states, which is convenient for the pilot to operate the tablet computer at different flight stages and angles. Brief Description of the Drawings

[0017] Figure 1 is a three-dimensional view of a double-screen support device that can be flexibly adjusted inside an aircraft cockpit according to the present invention;

[0018] Figure 2 is Figure 1 exploded view of;

[0019] Figure 3 is Figure 2 exploded view of the bottom support and the support frame in;

[0020] Figure 4 is the exploded view of the movable component.

[0021] Description of the reference numerals in the drawings: 1-cylindrical base, 2-shock-absorbing ring, 3-locking pin, 4-outer cylinder, 5-strut, 6-first torque hinge, 7-limit block, 8-quick-release joint, 9-flat tray, 10-cap, 11-retaining ring, 12-support frame, 13-support plate, 14-second torque hinge, 15-lower support arm, 16-second torque hinge, 17-upper support arm, 18-third torque hinge. Detailed Description of the Invention

[0022] The following combines the drawings and embodiments to detail the technical solutions of the present invention, so that those of ordinary skill in the art can better understand and implement the technical solutions of the present invention.

[0023] A double-screen support device that can be flexibly adjusted inside an aircraft cockpit, as Figures 1 to 4 shown, includes a cylindrical base 1 with a connecting bottom plate and a flat tray 9 for installing a tablet computer. An outer shock-absorbing ring 2 and an outer cylinder 4 are sleeved on the outside of the cylindrical base 1 from bottom to top. The cylindrical base 1 is a hollow structure with a strut 5 installed inside. The cylindrical base 1, the outer cylinder 4, and the strut 5 are fixedly connected into an integral bottom support through a locking pin 3. A first torque hinge 6 is installed inside the strut 5. The upper end of the first torque hinge 6 is connected to a rotatable limit block 7. The upper end of the limit block 7 is fixedly connected to a support frame 12. Two sets of movable components are connected to both ends of the support frame 12. Each set of movable components includes a second torque hinge 14, a lower support arm 15, a third torque hinge 16, an upper support arm 17, a fourth torque hinge 18, and a quick-release joint 8. The end of the support frame 12 is connected to the lower support arm 15 through the second torque hinge 14. The lower support arm 15 is connected to the upper support arm 17 through the third torque hinge 16. The upper support arm 17 is connected to the quick-release joint 8 through the fourth torque hinge 18. The quick-release joint 8 is detachably clamped and fixed to the flat tray 9 through a concave-convex fitting structure.

[0024] In one embodiment, a cover 10 is provided at the upper end of the outer cylinder 4. A first hollow hole is provided in the middle of the cover 10. After the limiting block 7 passes through the first hollow hole of the cover 10, it is connected to the support frame 12. The cover 10 is used to prevent dust and sundries from entering the outer cylinder 4 and protect the internal structure.

[0025] In one embodiment, a retaining ring 11 is installed on the upper part of the limiting block 7. The retaining ring 11 is installed above the cover 10 and is used to fix the cover 10 to ensure the stable installation of the cover 10.

[0026] In one embodiment, a support disk 13 is fixedly connected to the bottom of the support frame 12. A second hollow hole is provided in the middle of the support disk 13. After the limiting block 7 passes through the second hollow hole of the support disk 13, it is connected to the support frame 12. The support disk 13 can provide a larger support area for the support frame 12. The support frame 12 and the support disk 13 can be connected into one body through fixing connectors such as bolts.

[0027] In one embodiment, a long convex platform is provided at the upper end of the limiting block 7, and a long groove matching the long convex platform is provided in the middle of the support frame 12, and the long convex platform is clamped into the long groove.

[0028] The dual-screen support device of the present invention can provide more stable and flexible support for the tablet computer in the aircraft cockpit through a dual support structure. At the same time, the design of the shock-absorbing ring and the torque hinge also makes the device have strong earthquake resistance, adapt to various vibrations and impacts during flight, and ensure the safe use of the tablet computer. Most importantly, the present invention can support two tablet computers at the same time, enabling the pilot to more efficiently classify and operate multi-screen information, thereby improving the convenience and safety of flight work.

[0029] The above embodiments are only relatively preferred embodiments of the present invention, but cannot be used as a limitation of the invention. Any variations and improvements made based on the concept of the present invention should fall within the protection scope of the present invention, and the specific protection scope shall be subject to the claims.

Claims

1. A flexible adjustable dual-screen support device inside an aircraft cockpit, comprising a cylindrical base with a connecting bottom plate and a tablet tray for installing a tablet computer, characterized in that, An anti-vibration ring and an outer cylinder are sleeved on the outside of the cylindrical base from bottom to top. The cylindrical base is a hollow structure with a support pillar installed inside. The cylindrical base, the outer cylinder and the support pillar are fixedly connected into an integral bottom support through locking pins. A first torque hinge is installed inside the support pillar. The upper end of the first torque hinge is connected to a rotatable limit block. The upper end of the limit block is fixedly connected to a support frame. Two sets of movable components are connected to both ends of the support frame. Each set of movable components includes a second torque hinge, a lower support arm, a third torque hinge, an upper support arm, a fourth torque hinge and a quick-release joint. The end of the support frame is connected to the lower support arm through the second torque hinge. The lower support arm is connected to the upper support arm through the third torque hinge. The upper support arm is connected to the quick-release joint through the fourth torque hinge. The quick-release joint is detachably clamped and fixed to the flat tray through a concave-convex fitting structure.

2. The double-screen support device that can be flexibly adjusted inside the aircraft cockpit according to claim 1, wherein: A cover is arranged at the upper end of the outer cylinder. A first hollow hole is arranged in the middle of the cover. The limit block passes through the first hollow hole of the cover and then is connected to the support frame.

3. The double-screen support device that can be flexibly adjusted inside the aircraft cockpit according to claim 2, wherein: A snap ring is installed on the upper part of the limit block. The snap ring is installed above the cover and is used to fix the cover.

4. The flexible adjustable dual-screen support device in the aircraft cockpit according to claim 1, characterized in that: A support disc is fixedly connected to the bottom of the support frame. A second hollow hole is arranged in the middle of the support disc. The limit block passes through the second hollow hole of the support disc and then is connected to the support frame.

5. The flexible adjustable dual-screen support device in the aircraft cockpit according to claim 1, characterized in that: A long convex platform is arranged at the upper end of the limit block. A long groove matching the long convex platform is formed in the middle of the support frame. The long convex platform is clamped into the long groove.

6. The flexible adjustable dual-screen support device in the aircraft cockpit according to claim 1, characterized in that: The lower support arm and the upper support arm form an L-shaped movable adjusting arm.

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