Manned centrifugal machine cabin

Abstract

The manned centrifugal machine cabin comprises an inner side cabin door, an outer side cabin door, a cabin skin, an aero seat and a cabin framework. The cockpit skin covers the cockpit framework, the cockpit framework is in a cuboid shape, and the cockpit framework comprises two door frames, a bottom plate, two lug plates, a hollow steel pipe and a plurality of equipment supports; the hollow steel pipe comprises three layers of cross beams, two layers of ring beams, four inclined pull beams and two layers of vertical beams; the cabin integrated optimization layout is adopted, the inner side door and the outer side door are arranged, convenience of entering and exiting the cabin, overhauling operation and auxiliary testee wearing operation is improved, and the emergency rescue difficulty is reduced; the cabin framework structure formed by welding the high-strength hollow profile steel is light, the machining difficulty is reduced, the manufacturing period is shortened, and the economical efficiency is improved.

Description

Technical Field

[0001] The invention relates to the technical field of manned centrifuge training, and in particular to a manned centrifuge cockpit. Background Art

[0002] The continuous acceleration generated by the maneuvering flight of modern high-performance fighters can easily cause pilots to lose consciousness (G-induced loss of consciousness, G-LOC), reduce combat capabilities, and threaten flight safety. Using manned centrifuges to carry out flight simulation training can enable pilots to practice and master anti-g-action skills, experience the physiological effects of acceleration loads, and enhance high-load protection awareness. It is the safest and most economical way to improve pilots' own G endurance. Moreover, this training method is not affected by weather and can be carried out all-weather. It has been widely adopted by various countries and has achieved good training results.

[0003] Among them, the cockpit is the core component of the manned centrifuge and is located at the end of the manned centrifuge. In order to reduce the drive scale of the system, the cockpit must have the characteristics of light weight and small moment of inertia. The interior space design of the cockpit is generally compact. In terms of the cockpit access design, an upward or downward flip door structure is adopted; in addition, in order to achieve the lightweight design goal, the existing manned centrifuge cockpit adopts a milled thin-walled reinforced metal frame, and the frames are connected by screws or rivets. For example, the cockpit structure of a manned centrifuge mentioned in the document "Assembly Simulation of Manned Centrifuge Cockpit Based on DELMIA" Figure 6 As shown, the manned centrifuge cabin structure includes a cabin frame 4, a cabin door 5, and a cabin skin 2-3.

[0004] The problems with the cockpit in the prior art are: (1) When using manned centrifuges for daily training, pilots need to enter and exit the cockpit, and operators also need to frequently enter the cockpit to assist pilots in donning and inspection. The use of an upward or downward flipping door structure, considering the already compact cockpit space, will lead to poor cockpit entry and exit and increase the difficulty of maintenance operations. In addition, when using manned centrifuges for endurance training, subjects sometimes faint, and emergency rescue is required. The cabin door is the only access to the cabin and also a life channel. The narrow operating space of the upward or downward flipping door undoubtedly increases the difficulty of rescue.

[0005] (2) Conventional manned centrifuge cabins use a thin-walled metal frame structure that is milled. The frames are connected by a large number of screws or rivets. The complex processing technology and a large number of standard parts result in a long cabin processing cycle and poor economic efficiency.

[0006] Cause: (1) When conventional cockpits are designed with flip-up or flip-down doors, they do not take into account the convenience of entering and exiting the cockpit and the needs of emergency rescue in emergency situations. Considering the requirements for lightweight cockpit design, the space inside the cockpit is relatively compact. The cockpit is generally equipped with aviation seats, rudder and throttle, sound and vision, anti-gravity oxygen supply, lighting, air supply, and data acquisition systems to simulate the driving environment, making the space inside the cockpit even more cramped. Conventional cockpits use flip-up or flip-down doors, resulting in limited entry and exit channels. When the doors are opened, they will occupy the space above or under the head, making it difficult for the subjects, auxiliary wearers, and maintenance personnel to enter and exit the cockpit. In the event of an emergency such as the subject fainting, it will increase the difficulty of rescue.

[0007] (2) The cockpit is located at the end of the manned centrifuge. Its mass and moment of inertia will directly affect the drive scale of the system. In order to reduce the drive scale of the system, the cockpit must have the characteristics of light mass and small moment of inertia. In order to achieve the lightweight design goal, considering that the cockpit and the fighter are subjected to similar acceleration overload conditions, the fighter frame optimization design method is conventionally adopted, that is, the material removal method is used to optimize the frame design. The designed frame is mostly a thin-walled reinforced structure, and the frames are connected by a large number of screws or rivets. The process is complex, the manufacturing difficulty is high, the processing cycle is long, and the economy is poor.

[0008] Therefore, it is necessary to develop a manned centrifuge cabin to solve the above problems. Summary of the invention

[0009] The purpose of the present invention is to design a manned centrifuge cabin in order to solve the above problems.

[0010] The present invention achieves the above-mentioned purpose through the following technical solutions: A manned centrifuge cabin, comprising: Inboard hatch; Outer hatch; Cockpit skin; Airline seats; Cockpit frame; the cockpit skin covers the cockpit frame, which is formed into a rectangular shape. The cockpit frame includes two door frames, a bottom plate, two ear plates, a hollow steel pipe, and a plurality of equipment brackets; the hollow steel pipe includes three layers of cross beams, two layers of ring beams, four cable-stayed beams and two layers of vertical beams. The ring beam is formed into a rectangle. The two layers of ring beams are arranged in parallel. The two layers of ring beams are respectively arranged on the first and second sides opposite to the cockpit frame. The cross beam is formed into a rectangle. The three layers of cross beams are arranged in parallel. The three layers of cross beams are respectively placed between the top, the middle and the bottom of the two layers of ring beams. The two layers of vertical beams are arranged in parallel. The two layers of vertical beams are respectively arranged on the second and third sides opposite to the cockpit frame. The three sides of one layer of vertical beams are respectively connected with the two layers of ring beams and the cross beam at the bottom. The other layer The four sides of the vertical beam are respectively connected to the two layers of ring beams and the cross beams at the bottom and the middle. Each door frame includes two door frame columns parallel to each other. The two door frames are respectively installed vertically in the two layers of ring beams. The cable-stayed beam is inclined. The lower end of the cable-stayed beam is connected to the lower end of the door frame column, and the upper end of the door frame column is connected to the upper corner of the ring beam. The bottom plate is installed on the cross beam at the bottom. The two ear plates are set at the same height. The two ear plates are parallel to each other. The two ear plates are respectively installed on the two layers of vertical beams. A connecting hole is set in the middle of the ear plate, which is connected to the swivel arm through a pin shaft. Multiple equipment brackets are installed under the cross beam at the top. The inner door and the outer door are respectively installed on the two door frames. The inner door is set close to the rotating shaft of the centrifuge, and the aviation seat is placed on the center of the bottom plate.

[0011] The beneficial effects of the present invention are: 1. The cockpit is integrated and optimized, with internal and external doors on both sides, which increases the convenience of entering and exiting the cockpit, maintenance operations, and assisting subjects in wearing the equipment, and reduces the difficulty of emergency rescue; 2. The cockpit skeleton structure is welded with high-strength hollow steel to achieve lightweight, reduce processing difficulty, shorten manufacturing cycle and improve economy. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 This is a schematic diagram of the installation structure of this application; Figure 2 This is a schematic diagram of the structure of this application Figure 1 ; Figure 3 This is a schematic diagram of the structure of this application Figure 2 ; Figure 4 This is a schematic diagram of the structure of this application Figure 3 (remove the door); Figure 5 This is a schematic diagram of the installation structure of the hollow steel pipe in this application; Figure 6 It is a structural schematic diagram of the prior art.

[0013] Legend: 1—Rotating arm; 2—cockpit; 2-1—inner door; 2-2—outer door; 2-3—cockpit skin; 2-4—data acquisition system; 2-5—lighting system; 2-6—sound and visual system; 2-7—rudder and throttle system; 2-8—aircraft seat; 2-9—cockpit frame; 2-9-1—door frame; 2-9-2—bottom plate; 2-9-3—ear plate; 2-9-4—hollow steel pipe; 2-9-5—equipment bracket; 2-9-6—crossbeam; 2-9-7—ring beam; 2-9-8—cable-stayed beam; 2-9-9—vertical beam; 2-10—air supply system; 2-11—anti-load oxygen supply system; 2-12—entry and exit platform; 3—pin; 4—cockpit frame; 5—Cockpit door. DETAILED DESCRIPTION

[0014] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0015] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. 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.

[0016] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0017] In the description of the present invention, it should be understood that the terms "upper", "lower", "inside", "outside", "left", "right", etc. indicate directions or positional relationships based on the directions or positional relationships shown in the accompanying drawings, or are directions or positional relationships in which the product of the invention is usually placed when in use, or are directions or positional relationships commonly understood by those skilled in the art. These directions or positional relationships are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore should not be understood as a limitation on the present invention.

[0018] Furthermore, the terms “first”, “second”, etc. are merely used for distinguishing descriptions and are not to be understood as indicating or implying relative importance.

[0019] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms such as "setting" and "connection" should be understood in a broad sense. For example, "connection" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0020] The specific implementation modes of the present invention are described in detail below in conjunction with the accompanying drawings.

[0021] like Figure 1-5 As shown, a manned centrifuge cabin 2 includes: Inboard door 2-1; Outer door 2-2; inner door 2-1 and outer door 2-2 are arranged opposite to each other; wherein, outer door 2-2 is used as an entry and exit passage for normal training, and inner door 2-1 is used as an inspection passage and an emergency rescue passage at the same time, that is, at the beginning and end of training, the pilot enters and exits cockpit 2 through outer door 2-2, and when the manned centrifuge is running, inner door 2-1 and outer door 2-2 are both in a closed state and locked; when an emergency occurs, such as when a pilot faints during training, inner door 2-1 and outer door 2-2 are opened at the same time for emergency rescue; Cockpit skin 2-3; Airline seats 2-8; The cockpit frame 2-9; the cockpit skin 2-3 covers the cockpit frame 2-9, the cockpit frame 2-9 is formed into a rectangular parallelepiped, and the four corners of the cockpit frame 2-9 are formed into a large rounded transition structure; the cockpit frame 2-9 includes two door frames 2-9-1, a bottom plate 2-9-2, two ear plates 2-9-3, a hollow steel pipe 2-9-4, and a plurality of equipment brackets 2-9-5; the hollow steel pipe 2-9-4 includes three layers of cross beams 2-9-6, two layers of ring beams 2-9-7, four cable-stayed beams 2-9-8 and two layers of vertical beams 2-9-9, and the ring beam 2-9-7 is formed into a rectangle, Two layers of ring beams 2-9-7 are arranged in parallel, and the two layers of ring beams 2-9-7 are respectively arranged on the first and second sides opposite to the cabin frame 2-9. The cross beam 2-9-6 is formed into a rectangle. The three layers of cross beams 2-9-6 are arranged in parallel, and the three layers of cross beams 2-9-6 are respectively placed between the top, the middle and the bottom of the two layers of ring beams 2-9-7. The two layers of vertical beams 2-9-9 are arranged in parallel, and the two layers of vertical beams 2-9-9 are respectively arranged on the second and third sides opposite to the cabin frame 2-9. The three sides of one layer of vertical beams 2-9-9 are respectively connected to the two layers of ring beams 2-9-7 and the cross beam at the bottom. 2-9-6, wherein the four sides of another layer of vertical beams 2-9-9 are respectively connected to the two layers of ring beams 2-9-7 and the cross beams 2-9-6 located at the bottom and the middle. Each door frame 2-9-1 includes two door frame 2-9-1 columns parallel to each other. The two door frames 2-9-1 are respectively vertically installed in the two layers of ring beams 2-9-7. The inclined beam 2-9-8 is inclinedly arranged. The lower end of the inclined beam 2-9-8 is connected to the lower end of the door frame 2-9-1 column. The upper end of the door frame 2-9-1 column is connected to the corner near the upper part of the ring beam 2-9-7. The bottom plate 2-9-2 is installed on the cross beam located at the bottom On 2-9-6, the two ear plates 2-9-3 are set at the same height, the two ear plates 2-9-3 are parallel to each other, and the two ear plates 2-9-3 are respectively installed on the two layers of vertical beams 2-9-9. A connecting hole is set in the middle of the ear plate 2-9-3, and the connecting hole is connected to the rotating arm 1 through a pin shaft 3. A plurality of equipment brackets 2-9-5 are installed under the cross beam 2-9-6 located at the top. The inner door 2-1 and the outer door 2-2 are respectively installed on the two door frames 2-9-1. The inner door 2-1 is set close to the rotating shaft of the centrifuge. The aviation seat 2-8 is placed on the center of the bottom plate 2-9-2.

[0022] The four corners of the cockpit frame 2-9 are formed into a large rounded transition structure to reduce stress concentration. The cockpit frame 2-9 is provided with threaded holes for connecting with the cockpit skin 2-3. In addition to closing the cockpit 2, the cockpit skin 2-3 can further strengthen the rigidity of the cockpit frame 2-9 and withstand overload in the Gz direction.

[0023] In some embodiments, the cockpit 2 further comprises: Data acquisition system 2-4; the data acquisition system 2-4 is installed on the cross beam 2-9-6 located in the middle and is placed above the aviation seat 2-8.

[0024] Lighting system 2-5; the lighting system 2-5 is installed on the equipment bracket 2-9-5 and placed above the aviation seat 2-8.

[0025] Sound-visual system 2-6; The sound-visual system 2-6 is installed on the inner side of the vertical beam 2-9-9 and is placed directly in front of the aviation seat 2-8.

[0026] The rudder and throttle system 2-7 is placed on the bottom plate 2-9-2 and directly in front of the aviation seat 2-8. The rudder and throttle system 2-7 is arranged adjacent to the aviation seat 2-8 with reference to the pilot's body size and is set with the pilot's sitting posture as a reference point.

[0027] Air supply system 2-10; the air supply system 2-10 is installed behind the aviation seat 2-8.

[0028] Anti-G oxygen supply system 2-11: The anti-G oxygen supply system 2-11 is installed on the bottom plate 2-9-2 and placed on one side of the aviation seat 2-8, so as to facilitate the pilot's breathing and anti-G suit air supply.

[0029] Entry and exit platform 2-12; The entry and exit platform 2-12 is installed on the bottom plate 2-9-2 and is placed in front of the aviation seat 2-8.

[0030] With the above integrated layout design, sufficient entry and exit space is reserved on both sides of the pilot, and entry and exit platforms 2-12 are respectively arranged in front of the left and right sides of the aviation seat 2-8 to facilitate personnel to enter and exit the cockpit 2 from the inner and outer doors 2-2.

[0031] Analyzing the working load of cabin 2, the maximum load is always in the Gz direction (e.g. Figure 4 As shown in the figure, unlike fighter jets which also need to withstand loads such as wind pressure, the ear plate 2-9-3 which needs to withstand shear loads is designed with a solid structure. Considering that the skeleton mainly bears bending loads, the high-strength hollow steel pipe 2-9-4 with excellent bending resistance is selected in the design. Considering that the door frame 2-9-1, the bottom plate 2-9-2 and the equipment bracket 2-9-5 all need to install equipment, they are made of solid structure cutting.

[0032] The cockpit frame 2-9 is formed by welding, and has good manufacturing processability, short cycle and good economy.

[0033] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the technical principles of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A manned centrifuge cabin, characterized in that: include: Inboard hatch; Outer hatch; Cockpit skin; Airline seats; Cockpit frame; The cockpit skin covers the cockpit frame, which is formed into a rectangular shape. The cockpit frame includes two door frames, a bottom plate, two ear plates, a hollow steel pipe, and a plurality of equipment brackets; the hollow steel pipe includes three layers of cross beams, two layers of ring beams, four cable-stayed beams and two layers of vertical beams. The ring beam is formed into a rectangle, and the two layers of ring beams are arranged in parallel. The two layers of ring beams are respectively arranged on the first and second sides opposite to the cockpit frame. The cross beam is formed into a rectangle, and the three layers of cross beams are arranged in parallel. The three layers of cross beams are respectively placed between the top, the middle and the bottom of the two layers of ring beams. The two layers of vertical beams are arranged in parallel. The two layers of vertical beams are respectively arranged on the second and third sides opposite to the cockpit frame. The three sides of one layer of vertical beams are respectively connected to the two layers of ring beams and the cross beam at the bottom. The four sides are respectively connected with the two layers of ring beams and the cross beams at the bottom and the middle. Each door frame includes two door frame columns parallel to each other. The two door frames are respectively vertically installed in the two layers of ring beams. The cable-stayed beam is inclined. The lower end of the cable-stayed beam is connected to the lower end of the door frame column, and the upper end of the door frame column is connected to the upper corner of the ring beam. The bottom plate is installed on the cross beam at the bottom. The two ear plates are set at the same height. The two ear plates are parallel to each other. The two ear plates are respectively installed on the two layers of vertical beams. A connecting hole is set in the middle of the ear plate, which is connected to the swivel arm through a pin shaft. Multiple equipment brackets are installed under the cross beam at the top. The inner door and the outer door are respectively installed on the two door frames. The inner door is set close to the rotating shaft of the centrifuge, and the aviation seat is placed on the center of the bottom plate.

2. A manned centrifuge cabin according to claim 1, characterized in that: The cockpit also includes a data acquisition system, which is mounted on a centrally located crossbar and placed above the aviation seats.

3. The manned centrifuge cabin according to claim 1, characterized in that: The cockpit also includes a lighting system, which is mounted on an equipment bracket and placed above the airline seats.

4. The manned centrifuge cabin according to claim 1, characterized in that: The cockpit also includes a sound-visual system, which is installed on the inside of the vertical beam and placed directly in front of the aviation seat.

5. The manned centrifuge cabin according to claim 1, characterized in that: The cockpit also includes a lever, rudder, and throttle system, which is placed on the bottom plate and directly in front of the aviation seat.

6. The manned centrifuge cabin according to claim 1, characterized in that: The cockpit also includes an air supply system, which is installed behind the aviation seats.

7. The manned centrifuge cabin according to claim 1, characterized in that: The cockpit also includes an anti-G oxygen supply system, which is installed on the floor and placed on one side of the aviation seat.

8. The manned centrifuge cabin according to claim 1, characterized in that: The cockpit also includes an entry and exit platform, which is mounted on the floor and placed in front of the aviation seat.

9. The manned centrifuge cabin according to claim 1, characterized in that: The four corners of the cockpit frame are formed into large rounded transition structures.

10. The manned centrifuge cabin according to claim 1, characterized in that: The inner door and the outer door are arranged opposite to each other.

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