Floor structure of cockpit of navigation coach aircraft

Abstract

The utility model discloses a navigation coach aircraft cockpit floor structure which comprises a floor body, the floor body comprises a floor bottom, a middle supporting portion extending upwards is formed on the top face of the middle of the floor bottom, an inserting groove is formed in the middle of the middle supporting portion, and the bottom face of the inserting groove extends out of the bottom face of the middle of the floor bottom. A rear vertical plate part extending upwards is formed on the top face of the rear end of the floor bottom, and the rear end of the middle supporting part is formed on the front wall face of the middle of the rear vertical plate part. The wall plate is an integrally formed part, so that the thickness of the wall plate at the corresponding position is controlled, and the wall plate is integrally formed, does not need to be spliced, only needs to be directly mounted on a machine body, and is convenient to mount.

Description

Technical field:

[0001] The utility model relates to the technical field related to general aircraft equipment, and more specifically to a cockpit floor structure of a general aviation training aircraft. Background technology:

[0002] The cockpit space of general aircraft is relatively small, especially for trainer aircraft. The left and right positions of the cockpit serve the flight instructor and the trainee respectively, and two sets of rudder pedal systems need to be arranged. This requires the design of the cockpit to be compact and light in weight, and to be convenient for the pilot to operate. The existing cockpit floor is generally composed of multiple panels spliced ​​together. Because they are spliced ​​together, the thickness of the panels at the splicing parts increases, which makes the overall area of ​​the cockpit floor large, and the available space in the cockpit is reduced. The effect is not ideal, and it needs to be spliced ​​and installed, which has a poor effect. Utility model content:

[0003] The purpose of the utility model is to overcome the shortcomings of the prior art and provide a general aviation training aircraft cockpit floor structure, which is an integrally formed part so that the thickness of the wall panels at corresponding positions can be controlled, and it is integrally formed and does not require splicing. It only needs to be directly installed on the fuselage, and is easy to install.

[0004] The solution of the utility model to solve the technical problem is:

[0005] A general aviation training aircraft cockpit floor structure, comprising a floor main body, the floor main body comprising a floor bottom, a middle support portion extending upward is formed on the middle top surface of the floor bottom, a plug-in slot is formed in the middle of the middle support portion, and the bottom surface of the plug-in slot extends to the middle bottom surface of the floor bottom;

[0006] A rear vertical plate portion extending upward is formed on the top surface of the rear end of the bottom of the floor, and a rear end of the middle supporting portion is formed on the front wall surface of the middle portion of the rear vertical plate portion.

[0007] The left and right sides of the front wall surface of the intermediate support portion are formed with transverse connecting portions, and the transverse connecting portions and the front wall surface of the intermediate support portion are fixed on the front structure of the fuselage.

[0008] The rear wall surface of the rear vertical plate portion is connected to the transverse structure of the fuselage.

[0009] A bent edge bent backwards is formed on the top of the rear vertical plate portion, and the bent edge is fixed to the front portion of the rear pilot seat.

[0010] The left and right side edges of the floor bottom and the left and right side walls of the rear vertical plate are both formed with connecting flanges, and the connecting flanges are bonded to the fuselage through an adhesive.

[0011] Connecting flanges are formed on the left and right side walls of the bending edge.

[0012] The outstanding effects of the utility model are:

[0013] It is an integrally formed part, so that the thickness of the wall panel at its corresponding position is controlled and no assembly is required;

[0014] The front wall surface of the bottom of its floor can be directly connected to two rudder pedal assemblies, the bent edge is fixed at the front part of the rear pilot seat to achieve connection with the pilot seat, the top surface of the middle support part can be installed with a console, and the connecting flange can be bonded to the fuselage by an adhesive, so that it can be connected to some related parts of the entire cockpit, and the connection and installation are convenient. Description of the drawings:

[0015] Figure 1 It is a partial structural schematic diagram of the utility model. Specific implementation method:

[0016] For example, see Figure 1 As shown, a general aviation training aircraft cockpit floor structure includes a floor body 10, wherein the floor body 10 includes a floor bottom 11, a middle support portion 12 extending upward is formed on the middle top surface of the floor bottom 11, a plug-in slot 121 is formed in the middle of the middle support portion 12, a front end of the plug-in slot 121 extends out of the front wall surface of the middle support portion 12, and a bottom surface of the plug-in slot 121 extends out of the middle bottom surface of the floor bottom 11;

[0017] The rear end top surface of the floor bottom 11 is formed with a rear vertical plate portion 13 extending upward, the rear end of the intermediate support portion 12 is formed on the middle front wall surface of the rear vertical plate portion 13 , and the rear vertical plate portion 13 is formed with a plurality of connecting through holes.

[0018] The front wall surfaces of the left and right parts of the floor bottom 11 are fixed to the rear wall surfaces of the corresponding rudder pedal assemblies;

[0019] The left and right sides of the front wall of the intermediate support part 12 are formed with transverse connecting parts 122, and the transverse connecting part 122 and the front wall of the intermediate support part 12 are fixed to the front structure of the fuselage. The upper part of the front wall of the floor bottom 11 is formed with a front connecting plate part 111 extending upward, and the front connecting plate part 111 is fixed to the rear wall surfaces of the rudder pedal assembly on both sides of the front structure of the fuselage. The front connecting plate part 111 and the transverse connecting part 122 are both formed with connecting mounting through holes.

[0020] The rear wall surface of the rear vertical plate portion 13 is connected to the transverse structure of the fuselage.

[0021] A bent edge 131 bent backwards is formed on the top of the rear vertical plate portion 13 , and the bent edge 131 is fixed to the front portion of the rear pilot seat.

[0022] The left and right side edges of the floor bottom 11 and the left and right side walls of the rear vertical plate 13 are both formed with connecting flanges 1, and the connecting flanges 1 are bonded to the fuselage by an adhesive.

[0023] Connecting flanges 1 are formed on the left and right side walls of the bending edge 131 , and all the connecting flanges 1 on the same side are formed together.

[0024] A slot is formed in the middle of the bending edge 131 , and a rear end of the slot extends out of the rear wall surface of the bending edge 131 .

[0025] A middle through hole 123 is formed in the middle of the top surface of the inserting slot 121 .

[0026] A plurality of side through grooves 124 are formed on a front side wall of one side wall of the insertion slot 121 .

[0027] In this embodiment, the floor body 10 is directly integrally formed by using a glass fiber composite material. The glass fiber composite material is used so that it is light in weight and easy to form.

[0028] The bottom surface of the floor bottom 1 is pressed against the top surface of the bottom plate of the fuselage body, bearing the weight of the people and structures in the cabin.

[0029] The transverse connecting portion 122 and the front wall surface of the intermediate supporting portion 12 are fixed to the front structure of the fuselage, and the rudder pedal assemblies on both sides are also connected to the front connecting plate portion 111 .

[0030] The rear vertical plate portion 13 is connected to the fuselage transverse structure and can be used to fix the front part of the control rod bracket. The bent edge 131 is fixed to the front part of the rear pilot seat to support the front part of the pilot seat.

[0031] The connecting flange 1 is bonded to the fuselage by an adhesive so that it is glued to the fuselage.

[0032] The middle support part 12 constitutes the cockpit center console, which is used to arrange the control system.

[0033] The system pipeline can extend into the cockpit through the top surface of the middle through hole 123; the control console (including various control handles) is fixed on the top surface of the middle support part 12, and the system pipeline is electrically connected to the control console to facilitate operation by pilots on both sides.

[0034] The floor body 10 in this embodiment adopts a composite material structure, is integrally formed, and is light in weight. It has a compact structure and saves space. It is connected to the rudder pedal assembly and integrates the control console, so that pilots on both sides can operate conveniently; the integration effect is good, making the entire cockpit clean and refreshing, and the design is reasonable.

Claims

1. A general aviation training aircraft cockpit floor structure, comprising a floor body (10), characterized in that: The floor body (10) comprises a floor bottom (11), a middle support portion (12) extending upward is formed on the middle top surface of the floor bottom (11), a plug-in slot (121) is formed in the middle of the middle support portion (12), and the bottom surface of the plug-in slot (121) extends to the middle bottom surface of the floor bottom (11); The rear end top surface of the floor bottom (11) is formed with a rear vertical plate portion (13) extending upward, and the rear end of the middle support portion (12) is formed on the middle front wall surface of the rear vertical plate portion (13).

2. The cockpit floor structure of a general aviation training aircraft according to claim 1, characterized in that: The left and right sides of the front wall surface of the intermediate support part (12) are formed with transverse connecting parts (122); the transverse connecting parts (122) and the front wall surface of the intermediate support part (12) are fixed to the front structure of the fuselage; and the front wall surfaces of the left and right parts of the floor bottom (11) are fixed to the rear wall surfaces of the corresponding rudder pedal assemblies.

3. The cockpit floor structure of a general aviation training aircraft according to claim 1, characterized in that: The rear wall surface of the rear vertical plate portion (13) is connected to the transverse structure of the fuselage.

4. The cockpit floor structure of a general aviation training aircraft according to claim 3, characterized in that: A bent edge (131) bent backwards is formed on the top of the rear vertical plate portion (13), and the bent edge (131) is fixed to the front of the rear pilot seat.

5. The cockpit floor structure of a general aviation training aircraft according to claim 1, characterized in that: The left and right side edges of the floor bottom (11) and the left and right side walls of the rear vertical plate (13) are both formed with connecting flanges (1), and the connecting flanges (1) are bonded to the fuselage by an adhesive.

6. The cockpit floor structure of a general aviation training aircraft according to claim 4, characterized in that: Connecting flanges (1) are formed on the left and right side walls of the bending edge (131), and all the connecting flanges (1) on the same side are formed together.

7. The cockpit floor structure of a general aviation training aircraft according to claim 4, characterized in that: A clamping groove is formed in the middle of the bending edge (131), and the rear end of the clamping groove extends out of the rear wall surface of the bending edge (131).

8. The cockpit floor structure of a general aviation training aircraft according to claim 1, characterized in that: A middle through hole (123) is formed in the middle of the top surface of the insertion slot (121).

9. The cockpit floor structure of a general aviation training aircraft according to claim 1, characterized in that: A plurality of side through grooves (124) are formed on a front side wall of one side wall of the insertion groove (121).

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