Light suspension type cockpit of manned aircraft

Abstract

The light suspension type cockpit comprises a rack, a cabin body is arranged above the rack, the cabin body is made of carbon fiber reinforced plastics, outer protective plates are arranged on the outer surfaces of the two sides of the lower end of the cabin body, a plurality of suspension cavities are formed in the top end of the rack below the cabin body, and a base is arranged on one side of the bottom of the cabin body. A console is arranged at the bottom of the cabin on one side of the base, a seat is mounted at the bottom of the cabin on one side, far away from the base, of the console, second tempered glass windows are arranged on the outer surfaces of two sides of the upper end of the cabin, first tempered glass windows are arranged on the outer surfaces of the cabin on one sides of the second tempered glass windows, and a base is arranged at the bottom of the cabin on one side, far away from the console, of the seat. The purpose of purifying air on the inner side of the cabin body is achieved, the quality of the air on the inner side of the cabin body is guaranteed, the control effect of flight personnel on the console is guaranteed, and the cabin body with the light design is beneficial to improving the loading capacity, the fuel efficiency and the flight distance of the low-altitude aircraft.

Description

TECHNICAL FIELD

[0001] The utility model relates to aviation technology field, concretely is a manned aircraft light -duty suspension formula cockpit. BACKGROUND

[0002] The low-altitude aircraft cockpit is the cabin of the pilot controlling the low-altitude aircraft, is usually located in the front end of the low-altitude aircraft, provides the field of vision of overlooking the whole flight process for the pilot, and the low-altitude aircraft cockpit is one of important components in the low-altitude aircraft, and the excellent performance can determine the quality of the low-altitude aircraft, so it is particularly important to develop a manned aircraft light -duty suspension formula cockpit.

[0003] Referring to the announcement No. CN214608022U, a manned aircraft light -duty suspension formula cockpit, it includes frame and prefabricated cockpit, the top of frame is provided with prefabricated cockpit, four machine warehouse suspension plate connecting modules are arranged, four machine warehouse suspension plate connecting modules are fixedly connected to the top four corners of frame respectively, the cockpit is provided with prefabricated cockpit, prefabricated cockpit is carved from foam, and the outside is sprayed with polyurea coating, the specific gravity of foam material is greatly reduced compared to aluminum alloy material, so the weight of prefabricated cockpit can be greatly reduced, the weight of the whole aircraft becomes lighter, the strength of prefabricated cockpit is improved, so the endurance, speed and loading capacity of the whole aircraft are improved, according to the above, the cockpit can be better applied, but it is inconvenient to purify the air inside the cabin body, it is difficult to ensure that the flight personnel control the low-altitude aircraft in a good environment, and the user is often troubled. UTILITY MODEL CONTENTS

[0004] The utility model aims at providing a manned aircraft light -duty suspension formula cockpit to solve the problem that the cockpit can be better applied in the above background art, but it is inconvenient to purify the air inside the cabin body, and it is difficult to ensure that the flight personnel control the low-altitude aircraft in a good environment.

[0005] To achieve the above objectives, this utility model provides the following technical solution: a lightweight, suspended cockpit for a manned aircraft, comprising a frame, a cabin body on top of the frame, the cabin body being made of carbon fiber reinforced plastic, outer protective plates on both sides of the lower end of the cabin body, several suspension cavities on the top of the frame below the cabin body, a base on one side of the bottom of the cabin body, a control panel on the bottom of the cabin body on one side of the base, a seat installed on the bottom of the cabin body on the side of the control panel away from the base, second tempered glass windows on both sides of the upper end of the cabin body, first tempered glass windows on the outer surface of the cabin body on the side of the second tempered glass windows, a base on the bottom of the cabin body on the side of the seat away from the control panel, an exhaust hood on one side of the top of the base via a bracket, a purification box on the other side of the top of the base, an exhaust fan installed on the top of the purification box, a flexible hose installed at one end of the exhaust fan, the end of the flexible hose away from the exhaust fan being connected to the outer wall of the exhaust hood, and the other end of the exhaust fan being connected to the outer wall of the purification box via a duct.

[0006] Preferably, a lamp holder is provided on the inner wall at the upper end of the cabin, and a first support frame is provided at the center of the surface of the lamp holder. A photosensitive sensor is installed at the end of the first support frame away from the lamp holder. The photosensitive sensor is used to monitor and process the brightness inside the cabin.

[0007] Preferably, a second support frame is provided on both sides of the lamp holder surface, and a lighting lamp is installed at the end of the second support frame away from the lamp holder, so as to illuminate the interior of the cabin.

[0008] Preferably, the top of the frame inside the suspended cavity is provided with a lower connecting seat, and the bottom of the cabin above the lower connecting seat is provided with an upper connecting seat. The upper and lower connecting seats are provided to accommodate the telescopic rod.

[0009] Preferably, the top of the lower connecting seat is provided with a telescopic rod, the top of the telescopic rod is connected to the bottom of the upper connecting seat, and a damper is provided between the frame and the cabin between adjacent telescopic rods. The telescopic rods are provided to accommodate the inner and outer springs.

[0010] Preferably, an inner spring and an outer spring are wound around the outer wall of the telescopic rod, and the two ends of the inner spring and the outer spring are respectively connected to the top end of the lower connecting seat and the bottom end of the upper connecting seat. The inner spring and the outer spring are used to cushion the cabin.

[0011] Compared with the prior art, the manned aircraft light suspension cabin has the advantages that: the cabin body inside air is purified to ensure the air quality inside the cabin body, and the control effect of the flight personnel on the console is ensured, and the light weight design of the cabin body is beneficial to improve the load capacity, fuel efficiency and flight distance of the aircraft.

[0012] (1) By starting the air extractor, the air inside the cabin is sucked into the purification box through the hose and the air extraction cover, and the air is purified by the purification box and discharged through the exhaust port of the rear outer wall, so that the air inside the cabin is purified, thereby ensuring the air quality inside the cabin body;

[0013] (2) The light intensity inside the cabin is monitored by the photosensitive sensor, and if the light intensity inside the cabin is low, the lighting lamp is powered on for lighting operation to reduce the phenomenon that the low light intensity inside the cabin makes it difficult for personnel to control the console, thereby ensuring the control effect of the flight personnel on the console;

[0014] (3) The cabin body is made of carbon fiber reinforced plastic, which greatly reduces the weight of the cabin body under the premise of meeting the flight safety standards, while maintaining sufficient structural strength and rigidity of the cabin body, thereby improving the load capacity, fuel efficiency and flight distance of the aircraft. BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 It is a three-dimensional structure schematic diagram of the utility model;

[0016] Figure 2 It is a front view cross-sectional structure schematic diagram of the utility model;

[0017] Figure 3 It is a lamp holder side view structure schematic diagram of the utility model;

[0018] Figure 4 It is a Figure 2 enlarged structure schematic diagram of the utility model at A.

[0019] In the figure: 1, rack; 2, cabin body; 3, suspension cavity; 4, first tempered glass window; 5, second tempered glass window; 6, outer guard plate; 7, base; 8, console; 9, seat; 10, lamp holder; 11, photosensitive sensor; 12, lighting lamp; 13, damper; 14, first bearing frame; 15, second bearing frame; 16, lower connecting seat; 17, upper connecting seat; 18, telescopic rod; 19, inner spring; 20, outer spring; 21, base; 22, purification box; 23, air extractor; 24, hose; 25, air extraction cover. DETAILED DESCRIPTION

[0020] The technical solutions in the embodiments of the utility model will be clearly and completely described below with reference to the drawings in the embodiments of the utility model. Based on the embodiments in the utility model, all other embodiments obtained by the person skilled in the art without creative labor belong to the protection scope of the utility model.

[0021] Please refer to Figures 1-4 The utility model provides an embodiment: a manned aircraft light -duty suspension type cockpit, including frame 1, the top of frame 1 is equipped with cabin body 2, the inner wall on the upper end of cabin body 2 is equipped with lamp holder 10, the central position of the surface of lamp holder 10 is equipped with first bearing frame 14, and the end, away from lamp holder 10, of first bearing frame 14 is installed with photosensitive sensor 11;

[0022] When using, the photosensitive sensor 11 is arranged to monitor the brightness inside the cabin body 2.

[0023] The two sides of the surface of the lamp holder 10 are provided with second bearing frames 15, and the ends, away from the lamp holder 10, of the second bearing frames 15 are installed with illuminating lamps 12.

[0024] When using, the illuminating lamps 12 are arranged to illuminate the inside of the cabin body 2.

[0025] The cabin body 2 is made of carbon fiber reinforced plastic, the outer surfaces of the two sides of the lower end of the cabin body 2 are provided with outer protective plates 6, the top end of the frame 1 below the cabin body 2 is provided with a plurality of suspension cavities 3, the top end of the frame 1 inside the suspension cavities 3 is provided with lower connecting seats 16, and the bottom end of the cabin body 2 above the lower connecting seats 16 is provided with upper connecting seats 17.

[0026] When using, the upper connecting seats 17 and the lower connecting seats 16 are arranged to arrange the telescopic rods 18.

[0027] The top end of the lower connecting seat 16 is provided with a telescopic rod 18, the top end of the telescopic rod 18 is connected with the bottom end of the upper connecting seat 17, and the frame 1 and the cabin body 2 between adjacent telescopic rods 18 are provided with dampers 13.

[0028] When using, the telescopic rods 18 are arranged to arrange the inner springs 19 and the outer springs 20.

[0029] The outer wall of the telescopic rod 18 is respectively wound with the inner spring 19 and the outer spring 20, and the two ends of the inner spring 19 and the outer spring 20 are respectively connected with the top end of the lower connecting seat 16 and the bottom end of the upper connecting seat 17.

[0030] When using, the inner spring 19 and the outer spring 20 are arranged to buffer the cabin body 2.

[0031] The bottom of the cabin body 2 is provided with a base 7, the bottom of the cabin body 2 on one side of the base 7 is provided with a control console 8, the bottom of the cabin body 2 away from the side of the base 7 is provided with a seat 9, the outer surface of both sides of the upper end of the cabin body 2 is provided with a second tempered glass window 5, the outer surface of the cabin body 2 on one side of the second tempered glass window 5 is provided with a first tempered glass window 4, the bottom of the cabin body 2 away from the side of the control console 8 is provided with a base 21, one side of the top of the base 21 is provided with an air extraction cover 25 through a support, the other side of the top of the base 21 is provided with a purification box 22, the top of the purification box 22 is provided with an air extractor 23, one end of the air extractor 23 is provided with a hose 24, the end of the hose 24 away from the air extractor 23 is in communication with the outer wall of the air extraction cover 25, the other end of the air extractor 23 is in communication with the outer wall of the purification box 22 through a pipeline.

[0032] In use, the cabin body 2 is made of carbon fiber reinforced plastic to greatly reduce the weight of the cabin body 2 while meeting the flight safety standards, and to maintain sufficient structural strength and rigidity of the cabin body 2 to improve the load capacity, fuel efficiency and flight distance of the low-altitude aircraft, a plurality of suspension cavities 3 are arranged between the frame 1 and the cabin body 2, the frame 1 and the cabin body 2 inside the suspension cavities 3 are provided with telescopic rods 18 through the lower connecting seat 16 and the upper connecting seat 17, the inner spring 19 and the outer spring 20 are wound and installed on the outer wall of the telescopic rod 18, and the damper 13 is arranged between the adjacent telescopic rods 18 to suspend the cabin body 2 above the frame 1, thereby effectively isolating the external vibration of the cabin body 2 and reducing the fatigue of the pilot to improve the operation precision of the personnel, then the light-sensitive sensor 11 monitors the light brightness inside the cabin body 2, if the light brightness inside the cabin body 2 is low, the lighting lamp 12 is powered on for lighting operation to reduce the phenomenon that the low light brightness inside the cabin body 2 makes it difficult for personnel to control the control console 8, finally the air extractor 23 is started to suck the air inside the cabin body 2 to the purification box 22 through the hose 24 and the air extraction cover 25, the air is purified by the purification box 22 and discharged through the exhaust port of the rear outer wall, which achieves the purpose of purifying the air inside the cabin body 2 to improve the air quality inside the cabin body 2, thereby completing the use of the cockpit.

Claims

1. A lightweight, suspended cockpit for a manned aircraft, characterized in that: The device includes a frame (1), above which is a cabin (2) made of carbon fiber reinforced plastic. The lower sides of the cabin (2) are fitted with outer protective plates (6). Several suspended cavities (3) are located at the top of the frame (1) below the cabin (2). A base (7) is located on one side of the bottom of the cabin (2). A control panel (8) is located at the bottom of the cabin (2) on the side of the base (7). A seat (9) is installed at the bottom of the cabin (2) on the side of the control panel (8) away from the base (7). Second tempered glass windows (5) are located on both sides of the upper surface of the cabin (2). One side of the cabin (2) is provided with a first tempered glass window (4) on its outer surface. The bottom of the cabin (2) on the side of the seat (9) away from the control panel (8) is provided with a base (21). One side of the top of the base (21) is provided with an exhaust hood (25) via a bracket. The other side of the top of the base (21) is provided with a purification box (22). The top of the purification box (22) is equipped with an exhaust fan (23). One end of the exhaust fan (23) is equipped with a hose (24). The end of the hose (24) away from the exhaust fan (23) is connected to the outer wall of the exhaust hood (25). The other end of the exhaust fan (23) is connected to the outer wall of the purification box (22) via a duct.

2. The lightweight, suspended cockpit for a manned aircraft according to claim 1, characterized in that: A lamp holder (10) is provided on the inner wall at the upper end of the cabin (2). A first support frame (14) is provided at the center of the surface of the lamp holder (10). A photosensitive sensor (11) is installed at the end of the first support frame (14) away from the lamp holder (10).

3. The lightweight, suspended cockpit for a manned aircraft according to claim 2, characterized in that: The lamp holder (10) has a second support frame (15) on both sides of its surface, and a lighting lamp (12) is installed on the end of the second support frame (15) away from the lamp holder (10).

4. The lightweight, suspended cockpit for a manned aircraft according to claim 1, characterized in that: The top of the frame (1) inside the suspended cavity (3) is provided with a lower connecting seat (16), and the bottom of the cabin (2) above the lower connecting seat (16) is provided with an upper connecting seat (17).

5. A lightweight, suspended cockpit for a manned aircraft according to claim 4, characterized in that: The lower connecting seat (16) is provided with a telescopic rod (18) at its top end. The top end of the telescopic rod (18) is connected to the bottom end of the upper connecting seat (17). A damper (13) is provided between the frame (1) and the cabin (2) between adjacent telescopic rods (18).

6. A lightweight, suspended cockpit for a manned aircraft according to claim 5, characterized in that: The outer wall of the telescopic rod (18) is wound with an inner spring (19) and an outer spring (20), and the two ends of the inner spring (19) and the outer spring (20) are respectively connected to the top end of the lower connecting seat (16) and the bottom end of the upper connecting seat (17).

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