A manned centrifuge capsule

Abstract

The application discloses a manned centrifuge seat cabin, which comprises an inner cabin door, an outer cabin door, a cabin skin, an aviation seat and a cabin framework; the cabin skin is arranged on the cabin framework; the cabin framework is formed in a cuboid shape; the cabin framework comprises two door frames, a bottom plate, two ear 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 oblique pull beams and two layers of vertical beams; the cabin is integrated and optimized in layout; inner and outer double-side side-opening doors are arranged; the convenience of entering and exiting the cabin, maintenance operation and auxiliary subject wearing operation is improved; and the difficulty of emergency rescue is reduced; the cabin framework structure is formed by welding high-strength hollow steel, so that the weight of the cabin is reduced, the processing difficulty is reduced, the manufacturing period is shortened, and the economy is improved.

Description

Technical Field

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

[0002] The sustained accelerations generated by modern high-performance fighter jets during maneuvering can easily cause pilots to experience G-induced loss of consciousness (G-LOC), reducing combat capabilities and threatening flight safety. Using manned centrifuges for flight simulation training allows pilots to practice and master G-resistance techniques, experience the physiological effects of acceleration loads, and enhance their awareness of high-load protection. This is the safest and most economical way to improve pilots' G-endurance. Furthermore, this training method is weather-independent and can be conducted around the clock. It has been widely adopted by various countries and has achieved excellent 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 rotational inertia. The interior space design of the cockpit is generally compact. In terms of the design of the cockpit entry and exit channel, 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 structure of a manned centrifuge cockpit mentioned in the document "Assembly Simulation of Manned Centrifuge Cockpit Based on DELMIA" is as follows: 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:

[0005] (1) When using a manned centrifuge 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 conducting inspections. Using an up-and-down door structure, considering the already compact cockpit space, will result in poor cockpit entry and exit, and increase the difficulty of maintenance operations. In addition, when using a manned centrifuge for endurance training, subjects sometimes faint, requiring emergency rescue. The cabin door is the only access point and also a lifeline. The narrow operating space of the up-and-down door undoubtedly increases the difficulty of rescue.

[0006] (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 operations result in a long cabin processing cycle and poor economic efficiency.

[0007] Cause:

[0008] (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 of 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 also 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.

[0009] (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. To reduce the drive scale of the system, the cockpit needs to have the characteristics of light mass and small moment of inertia. To achieve the lightweight design goal, considering that the cockpit and the fighter are subject to similar acceleration overload conditions, the conventional fighter frame optimization design method is adopted, that is, the material removal method is used to optimize the frame. 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 is difficult, the processing cycle is long, and the economic efficiency is poor.

[0010] Therefore, it is necessary to develop a manned centrifuge cabin to solve the above problems. Summary of the Invention

[0011] The purpose of the present invention is to design a manned centrifuge cabin in order to solve the above problems.

[0012] The present invention achieves the above-mentioned purpose through the following technical solutions:

[0013] A manned centrifuge cabin, comprising:

[0014] Inboard hatch;

[0015] Outboard doors;

[0016] cockpit skin;

[0017] Airline seats;

[0018] Cockpit frame; the cockpit skin covers the cockpit frame, which is formed into a rectangular parallelepiped. 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, middle and 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 beam are connected to the two layers of ring beams and the cross beam at the bottom respectively. 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 diagonal beam is set at an angle. The lower end of the diagonal 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 ring beam near the upper corner. 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 provided in the middle of the ear plate, and the connecting hole is connected to the rotating 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.

[0019] The beneficial effects of the present invention are:

[0020] 1. The cockpit is integrated and optimized with internal and external side doors, which increases the convenience of entering and exiting the cockpit, performing maintenance operations, and assisting test subjects in donning the equipment, thus reducing the difficulty of emergency rescue.

[0021] 2. The cockpit skeleton structure is welded with high-strength hollow steel to achieve lightweighting, reduce processing difficulty, shorten manufacturing cycle and improve economy. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 This is a schematic diagram of the installation structure of this application;

[0023] Figure 2 This is a schematic diagram of the structure of this application Figure 1 ;

[0024] Figure 3 This is a schematic diagram of the structure of this application Figure 2 ;

[0025] Figure 4 This is a schematic diagram of the structure of this application Figure 3 (remove the door);

[0026] Figure 5 This is a schematic diagram of the installation structure of the hollow steel pipe in this application;

[0027] Figure 6 It is a structural diagram of the prior art.

[0028] Legend:

[0029] 1—rotating arm;

[0030] 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—aviation 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-gravity oxygen supply system; 2-12—access platform;

[0031] 3—pin;

[0032] 4—cockpit frame;

[0033] 5—Cockpit door. DETAILED DESCRIPTION

[0034] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be described clearly and completely below in conjunction with the accompanying drawings of the embodiments of the present invention. It should be understood that the described embodiments are only a portion of the embodiments of the present invention, not all of them. Generally, the components of the embodiments of the present invention described and illustrated in the drawings herein may be arranged and designed in a variety of different configurations.

[0035] 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 as claimed, but rather merely represents selected embodiments of the present invention. All other embodiments derived by persons of ordinary skill in the art based on the embodiments of the present invention without creative effort are intended to fall within the scope of protection of the present invention.

[0036] 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, it does not need to be further defined or explained in subsequent drawings.

[0037] In the description of the present invention, it should be understood that the terms "upper", "lower", "inside", "outside", "left", "right", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, or are the orientations or positional relationships in which the inventive product is conventionally placed when in use, or are the orientations or positional relationships conventionally understood by those skilled in the art. These are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or component referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0038] Furthermore, the terms “first”, “second”, etc. are merely used for distinguishing descriptions and should not be understood as indicating or implying relative importance.

[0039] In the description of the present invention, it should also be noted that, unless otherwise expressly specified or limited, terms such as "disposed" and "connected" should be understood in a broad sense. For example, "connected" can mean 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; it can also mean internal communication between two components. Those skilled in the art will be able to understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0040] The specific embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0041] like Figure 1-5 As shown, a manned centrifuge cabin 2 includes:

[0042] Inboard door 2-1;

[0043] 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 entrance and exit passage for normal training, and inner door 2-1 is used as an inspection passage and also as an emergency rescue passage, that is, at the beginning and end of training, the pilot enters and exits the cockpit 2 through outer door 2-2. When the manned centrifuge is running, both inner door 2-1 and outer door 2-2 are closed and locked. When an emergency occurs, such as a pilot fainting during training, both inner door 2-1 and outer door 2-2 are opened simultaneously for emergency rescue;

[0044] Cockpit skin 2-3;

[0045] Airline seats 2-8;

[0046] The cockpit frame 2-9; the cockpit skin 2-3 covers the cockpit frame 2-9, and the cockpit frame 2-9 is formed into a rectangular parallelepiped. 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 multiple equipment brackets 2-9-5; the hollow steel pipe 2-9-4 includes three layers of horizontal 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. 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 each other in the cabin frame 2-9. The cross beam 2-9-6 is formed into a rectangle, and 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, middle and bottom of the two layers of ring beams 2-9-7. 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 each other in the cabin frame 2-9. One layer of vertical beams 2-9-9 is respectively connected to the two layers of ring beams 2-9-7 and the cross beam at the bottom on three sides. 2-9-6, where another layer of vertical beams 2-9-9 are connected on all four sides to the two layers of ring beams 2-9-7 and the cross beams 2-9-6 at the bottom and in the middle. Each door frame 2-9-1 includes two parallel door frame columns 2-9-1. The two door frames 2-9-1 are vertically installed in the two layers of ring beams 2-9-7. The diagonal beam 2-9-8 is tilted. The lower end of the diagonal beam 2-9-8 is connected to the lower end of the door frame column 2-9-1. The upper end of the door frame column 2-9-1 is connected to the upper corner of the ring beam 2-9-7. The bottom plate 2-9-2 is installed on the cross beam 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. Multiple equipment brackets 2-9-5 are installed under the cross beam 2-9-6 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.

[0047] 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.

[0048] In some embodiments, the cockpit 2 further comprises:

[0049] Data acquisition system 2-4; the data acquisition system 2-4 is installed on the crossbeam 2-9-6 located in the middle and is placed above the aviation seat 2-8.

[0050] Lighting system 2-5; lighting system 2-5 is installed on the equipment bracket 2-9-5 and placed above the aviation seat 2-8.

[0051] 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.

[0052] The throttle and rudder system 2-7 is located on the base plate 2-9-2 and directly in front of the aircraft seat 2-8. The throttle and rudder system 2-7 is positioned adjacent to the aircraft seat 2-8 based on the pilot's body size and is set with the pilot's sitting posture as the reference point.

[0053] Air supply system 2-10; the air supply system 2-10 is installed behind the aviation seat 2-8.

[0054] Anti-G oxygen supply system 2-11: 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. It is convenient for the pilot to breathe and supply air to the anti-G suit.

[0055] Access platform 2-12; the access platform 2-12 is installed on the base plate 2-9-2 and is placed in front of the aviation seat 2-8.

[0056] With the above-mentioned integrated layout design, sufficient entry and exit space is reserved on both sides of the pilots, and entry and exit platforms 2-12 are respectively provided 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.

[0057] 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 design uses high-strength hollow steel pipe 2-9-4 with excellent bending resistance. Considering that the door frame 2-9-1, bottom plate 2-9-2 and equipment bracket 2-9-5 all need to be installed with equipment, they are cut and processed from solid structures.

[0058] The cockpit frame 2-9 is formed by welding, which has good manufacturing processability, short cycle and good economy.

[0059] 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 within the scope of protection of the present invention.

Claims

1. A manned centrifuge cabin, characterized in that: include: Inboard hatch; Outboard doors; 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, middle and 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 two opposite sides of the cockpit frame, one layer of vertical beams is connected to the two layers of ring beams and the cross beam at the bottom on three sides, and the other layer of vertical beams is connected to the two layers of ring beams and the cross beam at the bottom on four sides. The two door frames 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 installed vertically in the two layers of ring beams. The diagonal beam is inclined. The lower end of the diagonal 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 ring beam near the upper corner. 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 provided in the middle of the ear plate, and the connecting hole is connected to the rotating 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. The manned centrifuge cabin according to claim 1, characterized in that: The cockpit also includes a data acquisition system, which is installed on a central beam 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 aviation 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 throttle and rudder system, which is placed on the floor 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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