A self-locking multi-air supply port synchronous control system
By introducing a synchronous control structure of the air supply valve and valve plate into the helicopter bleed air heating system, the problem of uncontrollable temperature is solved, and real-time adjustment of the cockpit and cabin temperature and improvement of comfort are achieved.
Patent Information
- Application Number
- CN202211588523.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2022-12-09
- Publication Date
- 2025-09-19
- Estimated Expiration
- 2042-12-09
AI Technical Summary
The existing helicopter bleed air heating system cannot effectively control the temperature of the heated gas, resulting in excessively high temperatures in the cockpit and cabin, affecting comfort and flight safety.
An air supply valve and valve plate synchronous control structure is introduced into the air supply pipeline of the bleed air heating system. The air supply valve is synchronously controlled and position locked by a self-locking handle and a rotating rocker arm assembly to prevent the valve plate from shifting due to vibration or accidental collision.
It realizes real-time adjustment of cockpit and cabin temperature, improves comfort and safety, and prevents position displacement of the valve plate due to vibration or accidental collision.
Smart Images
Figure CN115817819B_ABST
Abstract
Description
Technical Field
[0001] The invention belongs to the technical field of aircraft environment control system design, and in particular relates to a self-locking multi-air supply port synchronous control system. Background Art
[0002] Since a certain type of helicopter is limited by many factors such as onboard installation space, system design cost, and system distribution weight, the heating system of this type of helicopter adopts the simplest design scheme to heat the aircraft cabin. The heating system consists of parts such as bleed air shut-off valve, bleed air pipeline, one-way valve, ejector, and air distribution pipeline. The heating system is relatively simple. When the pilot uses the heating system to heat the cabin, he only needs to turn on the engine bleed air switch. After the engine bleed air switch is turned on, the high-temperature, high-pressure, and high-speed gas output from the engine flows out from the nozzle to form a high-speed jet, and then enters the ejector, mixes with the ambient air at normal temperature to form heated gas, and then is transported to the helicopter cockpit and cabin area.
[0003] Since the bleed air heating system uses the principle that engine bleed air enters the ejector and mixes with ambient air at normal temperature to form heated gas, the temperature of the mixed heater outlet cannot be controlled. If the temperature of the heated gas is too high, it will cause the temperature of people in the cockpit and cabin areas to be too high, affecting the comfort of the pilot and cabin, and also affecting flight safety. Summary of the Invention
[0004] The purpose of the present invention is to add an air supply valve and a valve plate synchronous control structure to the air supply pipe air port of the bleed air heating system. During the use of the heating system, the pilot manually adjusts the valve plate opening, and the control device can lock the valve plate position of the air supply valve to prevent the valve plate position from shifting due to aircraft vibration or accidental collision by the pilot during flight.
[0005] The technical solution of the present invention:
[0006] A self-locking multi-air supply port synchronous control system consists of an air supply distribution system and a valve plate synchronous control structure. The air supply distribution system consists of four adjustable air supply valves, two of which are located in the cockpit and two in the middle of the passenger cabin. The four adjustable air supply valves are controlled by the valve plate synchronous control structure; the valve plate synchronous control structure consists of a self-locking handle, a valve plate rotating shaft, a rotating rocker arm assembly, a first rocker arm fixing pin, a double steel cable fixing pin, a second rocker arm fixing pin, a double steel cable fixing seat, a steel cable locking pin, a fixing clamp, a first operating steel cable, a second operating steel cable and other parts.
[0007] The self-locking handle is composed of a self-locking handle locking rod, a handle pull rod, a spring, a clamping nut, a handle sliding sleeve, a steel ball and other parts. The handle sliding sleeve is fixed to the aircraft floor by a clamping nut. The self-locking handle locking rod is used to lock the handle pull rod and the handle sliding sleeve to prevent the valve pieces of the first air supply valve, the second air supply valve, the third air supply valve and the fourth air supply valve from being displaced due to aircraft vibration or accidental contact by the pilot. There is a wedge-shaped groove under the self-locking handle locking rod, which cooperates with the steel ball. The self-locking handle locking rod is installed in the handle pull rod. There is a compression spring under the self-locking handle locking rod. In the free state, the spring is in a compressed state, and the spring force forces the self-locking handle locking rod to move upward. During the movement, the wedge-shaped groove pushes the steel ball outward, and finally the steel ball fits with the handle sliding sleeve. Under the action of friction, the steel ball and the handle sliding sleeve are locked. After locking, the handle pull rod cannot move up and down.
[0008] When you need to move the handle rod up or down, press the self-locking handle rod downward with your hand, and the self-locking handle rod moves downward. During the movement, the gap between the wedge-shaped groove and the steel ball gradually increases until the fitting part of the steel ball and the handle sliding sleeve is disengaged, and the friction force is reduced. While pressing the self-locking handle rod, move the handle rod up or down, and you can easily realize the function of opening, closing or stopping the valve at any position.
[0009] The first air supply valve consists of a first air outlet grid, a first air supply pipe, and a first valve plate. Heated air from the air distribution system enters the valve's inlet in the direction of the arrow, then flows out of the first air outlet grid and into the cockpit. When the valve plate is perpendicular to the axis of the first air supply pipe, the valve is fully closed. When the valve plate is parallel to the axis of the first air supply pipe, the valve is fully open.
[0010] The third air supply valve consists of a third air outlet grid, a third air supply pipe, and a third valve plate. Heated air from the air distribution system enters the valve's inlet in the direction of the arrow, then flows out of the third air outlet grid and into the cabin. When the valve plate is perpendicular to the axis of the third air supply pipe, the valve is fully closed. When the valve plate is parallel to the axis of the third air supply pipe, the valve is fully open.
[0011] The rocker arm assembly is composed of a rocker arm shaft, a rocker arm pin hole, a rocker arm, a rocker arm fixing pin sliding groove and other parts. The rocker arm shaft is sleeved on the valve plate shaft. During assembly, the second rocker arm fixing pin is inserted into the rocker arm pin hole for locking, and the rocker arm assembly is fixed to the valve plate shaft. After locking, the two perform synchronous rotation. The rocker arm and the self-locking handle are locked by the first rocker arm fixing pin. During the up and down movement of the self-locking handle, the first rocker arm fixing pin slides in the rocker arm fixing pin sliding groove to ensure that the self-locking handle can move up and down freely. During the up and down movement of the self-locking handle, the rocker arm assembly rotates around the valve plate shaft. During the up and down movement of the self-locking handle, the distance between the valve plate shaft and the first rocker arm fixing pin changes. The function of the rocker arm fixing pin sliding groove is used to adjust the distance between the valve plate shaft and the first rocker arm fixing pin.
[0012] The first air supply valve and the second air supply valve in the air supply distribution system are located on the left and right sides of the cockpit respectively, and are used to provide heated air to the captain and co-pilot; the third air supply valve and the fourth air supply valve are located in the middle of the cabin, and are used to supply air to the passengers on the left and right sides of the cabin. The opening of these four air supply valves is controlled by the valve plate synchronous control structure.
[0013] The valve plate synchronization control structure is used to simultaneously control the opening, closing, or stopping of the first, second, third, and fourth air supply valves. The first and second air supply valves share the same design structure, with their valve plates driven by a common valve plate pivot shaft, and the two valve plates move synchronously around the pivot shaft. The self-locking handle is secured to the double cable holder with a double cable fixing pin, which in turn is connected to the first and second control cables with two cable locking pins. The first and second control cables are secured to the aircraft structure via two fixing clamps. Once these connections are complete, the self-locking handle and the first, second, third, and fourth air supply valves can achieve synchronized movement. The self-locking handle drives the rotating rocker arm assembly to rotate during the upward movement, and drives the rotating rocker arm assembly to rotate within the range of 0 to 90 degrees during the up and down movement. The up and down stroke of the self-locking handle is 5 cm. The third air supply valve is driven by the first operating steel cable, and the fourth air supply valve is driven by the first operating steel cable. The telescopic stroke of the first operating steel cable and the first operating steel cable required for the third air supply valve and the fourth air supply valve to be opened to closed is just 5 cm, that is, the self-locking handle just makes the first air supply valve, the second air supply valve, the third air supply valve and the fourth air supply valve realize synchronous movement during the up and down movement, realizing the function of opening, closing or stopping the first air supply valve, the second air supply valve, the third air supply valve and the fourth air supply valve at any position.
[0014] After the technical solution of the present invention is applied to the bleed air heating system of a certain type of helicopter, it will have the function of temperature regulation. The pilot can adjust the air distribution amount entering the cockpit in real time according to actual needs. The pilot only needs to move the handle lever up and down to manually adjust the opening of the first air supply valve, the second air supply valve, the third air supply valve, and the fourth air supply valve in the cockpit and the passenger cabin to achieve the valve plate fully open, fully closed or stopped at any position. The implementation of the present invention can improve the comfort of the aircraft cockpit and passenger cabin. BRIEF DESCRIPTION OF THE DRAWINGS
[0015] Figure 1 Position diagram of the air supply valve at the upper limit position of the self-locking handle;
[0016] Figure 2 Position diagram of the air supply valve at the lower limit position of the self-locking handle;
[0017] Figure 3 Structural diagram of the lower limit position of the self-locking handle;
[0018] Figure 4 Structural diagram of the upper limit position of the self-locking handle;
[0019] Figure 5 Internal structure diagram of the first air supply valve;
[0020] Figure 6 Internal structure diagram of the third air supply valve;
[0021] Figure 7 Structural diagram of the rotating rocker arm assembly;
[0022] 1. Self-locking handle 2. First air supply valve 3. Second air supply valve 4. Valve plate pivot 5. Third air supply locking lever 1b. Handle pull rod 1c. Spring 1d. Clamping nut 1e. Handle sliding sleeve 1f. Steel ball 2a. First air outlet grid 2b. First air supply pipe 2c. First valve plate 5a. Third air outlet grid 5b. Third air supply pipe 5c. Third valve plate 5d. Valve plate pivot 5e. Cable mounting assembly
[0023] 6. Fourth air supply valve 7. Rotating rocker arm assembly 8. First rocker arm fixing pin 9. Dual cable fixing pin 10. Second rocker arm fixing pin 11. Dual cable fixing base 12. Cable locking pin 13. Fixing clamp 14. First control cable 15. Second control cable 16. Aircraft floor;
[0024] 1a. Self-locking handle locking rod 1b. Handle pull rod 1c. Spring 1d. Clamping nut 1e. Handle sliding sleeve 1f. Steel ball 2a. First air outlet grid 2b. First air supply pipe 2c. First valve plate 5a. Third air outlet grid 5b. Third air supply pipe 5c. Third valve plate 5d. Valve plate rotating shaft 5e. Steel cable fixing assembly 7a. Rocker arm rotating shaft 7b. Rocker arm pin hole 7c. Rocker arm 7d. Rocker arm fixing pin sliding groove. DETAILED DESCRIPTION
[0025] The present invention will be further described in detail below with reference to the accompanying drawings.
[0026] A control device capable of adjusting the opening of the cockpit and cabin heating air supply ports needs to be introduced into the heating system of a certain type of existing helicopter. During the use of the heating system, the pilot manually adjusts the opening of the heating pipe air inlet valve to adjust the temperature of the cockpit and cabin, thereby adjusting the cabin temperature. This solves the problem of the cabin temperature being unable to be adjusted due to the omission of the cabin temperature control system, and ensures the comfort of the cockpit and cabin.
[0027] The embodiment of the present invention provides a self-locking multi-air supply port synchronous control structure, which consists of two parts: an air supply distribution system and a valve plate synchronous control structure. The air supply distribution system consists of a first air supply valve 2, a second air supply valve 3, a third air supply valve 5, and a fourth air supply valve 6; the valve plate synchronous control structure consists of a self-locking handle 1, a valve plate rotating shaft 4, a rotating rocker arm assembly 7, a first rocker arm fixing pin 8, a double steel cable fixing pin 9, a second rocker arm fixing pin 10, a double steel cable fixing seat 11, a steel cable locking pin 12, a fixing clamp 13, a first operating steel cable 14, a second operating steel cable 15 and other parts. Figure 1 、 Figure 2 .
[0028] The self-locking handle 1 is composed of a self-locking handle locking rod 1a, a handle pull rod 1b, a spring 1c, a clamping nut 1d, a handle sliding sleeve 1e, a steel ball 1f and other parts. The handle sliding sleeve 1e is fixed to the aircraft floor 16 through the clamping nut 1d. The self-locking handle locking rod 1a is used to lock the handle pull rod 1b and the handle sliding sleeve 1e to prevent the valve plates of the first air supply valve 2, the second air supply valve 3, the third air supply valve 5 and the fourth air supply valve 6 from shifting due to aircraft vibration or accidental contact by the pilot. There is a wedge-shaped groove under the locking rod 1a, which cooperates with the steel ball 1f. The self-locking handle locking rod 1a is installed in the handle pull rod 1b. There is a compression spring under the self-locking handle locking rod 1a. In the free state, the spring is in a compressed state. The spring force forces the self-locking handle locking rod 1a to move upward. During the movement, the wedge-shaped groove pushes the steel ball 1f to move outward. Finally, the steel ball 1f fits with the handle sliding sleeve 1e. Under the action of friction, the steel ball 1f and the handle sliding sleeve 1e are locked. After locking, the handle pull rod 1b cannot move up and down. When it is necessary to move the handle rod 1b up or down, press the self-locking handle lock rod 1a downward by hand, and the self-locking handle lock rod 1a moves downward. During the movement, the gap between the wedge-shaped groove and the steel ball 1f gradually increases until the fitting part of the steel ball 1f and the handle sliding sleeve 1e is disengaged, and the friction force is reduced. While pressing the self-locking handle lock rod 1a, move the handle rod 1b up or down, and you can easily realize the function of opening, closing or stopping the valve at any position. When the valve pieces of the first air supply valve 2, the second air supply valve 3, the third air supply valve 5, and the fourth air supply valve 6 are in the fully open position, the position of the handle rod 1b is shown in FIG. Figure 3 When the valve plates of the first air supply valve 2, the second air supply valve 3, the third air supply valve 5 and the fourth air supply valve 6 are in the fully closed position, the position of the handle rod 1b is shown in FIG. Figure 4 .
[0029] The first air supply valve 2 consists of a first air outlet grid 2a, a first air supply pipe 2b, and a first valve plate 2c. The heated air output from the air supply distribution system enters the air supply valve 2 from the inlet in the direction of the arrow, then flows out of the first air outlet grid 2a and into the cockpit. When the valve plate is perpendicular to the axis of the first air supply pipe 2b, the air supply valve is fully closed. When the valve plate is parallel to the axis of the first air supply pipe 2b, the air supply valve is fully open. Figure 5 .
[0030] The third air supply valve 5 consists of a third air outlet grid 5a, a third air supply pipe 5b, and a third valve plate 5c. Heated air from the air supply distribution system enters the air supply valve 5 from its inlet in the direction of the arrow, then flows out of the third air outlet grid 5a and into the passenger cabin. When the valve plate is perpendicular to the axis of the third air supply pipe 5b, the air supply valve is fully closed. When the valve plate is parallel to the axis of the third air supply pipe 5b, the air supply valve is fully open. Figure 6 .
[0031] The rocker arm assembly 7 is composed of a rocker arm shaft 7a, a rocker arm pin hole 7b, a rocker arm 7c, a rocker arm fixing pin sliding groove 7d and other parts. The rocker arm shaft 7a is sleeved on the shutter plate shaft 4. During assembly, the second rocker arm fixing pin 10 is inserted into the rocker arm pin hole 7b for locking, and the rocker arm assembly 7 is fixed to the shutter plate shaft 4. After locking, the two perform synchronous rotation. The rocker arm 7c and the self-locking handle 1 are locked by the first rocker arm fixing pin 8. During the up and down movement of the self-locking handle 1, the first rocker arm fixing pin 8 slides in the rocker arm fixing pin sliding groove 7d to ensure that the self-locking handle 1 can move freely up and down. During the up and down movement of the self-locking handle 1, the rocker arm assembly 7 rotates around the shutter plate shaft 4. During the up and down movement of the self-locking handle 1, the distance between the shutter plate shaft 4 and the first rocker arm fixing pin 8 changes. The function of the rocker arm fixing pin sliding groove 7d is to adjust the distance between the shutter plate shaft 4 and the first rocker arm fixing pin 8. Figure 7 .
[0032] The first air supply valve 2 and the second air supply valve 3 in the air supply distribution system are respectively located on the left and right sides of the cockpit, and are used to provide heated air to the captain and co-pilot; the third air supply valve 5 and the fourth air supply valve 6 are located in the middle of the cabin, and are used to supply air to the occupants on the left and right sides of the cabin. The opening of these four air supply valves is controlled by the valve plate synchronous control structure.
[0033] The valve plate synchronization control structure is used to simultaneously control the opening, closing, or stopping of the first, second, third, and fourth air supply valves 2, 3, 5, and 6. The first and second air supply valves 2, 3 utilize the same design. Their valve plates 2c are driven by the same valve plate rotating shaft 4, and the two valve plates move synchronously about this shaft. The self-locking handle 1 is secured to the dual cable holder 11 with a dual cable fixing pin 9. The dual cable holder 11 is connected to the first and second control cables 14, 15 with two cable locking pins 12. The first and second control cables 14, 15 are secured to the aircraft structure via two fixing clamps 13. Once these connections are complete, the self-locking handle 1 and the first, second, third, 5, and fourth air supply valves 6 can achieve synchronized movement. The self-locking handle 1 drives the rotating rocker arm assembly 7 to rotate during the upward movement, and drives the rotating rocker arm assembly 7 to rotate within the range of 0 to 90 degrees during the up and down movement. The up and down stroke of the self-locking handle 1 is 5 cm. The third air supply valve 5 is driven by the first operating cable 14, and the fourth air supply valve 6 is driven by the second operating cable 15. The telescopic stroke of the first operating cable 14 and the second operating cable 15 required for the third air supply valve 5 and the fourth air supply valve 6 to go from opening to closing is just 5 cm, that is, the self-locking handle 1 just makes the first air supply valve 2, the second air supply valve 3, the third air supply valve 5, and the fourth air supply valve 6 achieve synchronous movement during the up and down movement, realizing the function of opening, closing or stopping the first air supply valve 2, the second air supply valve 3, the third air supply valve 5, and the fourth air supply valve 6 at any position. When the first air supply valve 2, the second air supply valve 3, the third air supply valve 5, and the fourth air supply valve 6 are in the fully open position, Figure 1 , when the first air supply valve 2, the second air supply valve 3, the third air supply valve 5, and the fourth air supply valve 6 are in the fully closed position Figure 2 .
[0034] After the implementation of the present invention, the bleed air heating system of a certain type of helicopter will have the function of temperature regulation. The pilot can adjust the air distribution amount entering the cockpit in real time according to actual needs. The pilot only needs to move the handle lever 1b up and down to manually adjust the opening of the first air supply valve 2, the second air supply valve 3, the third air supply valve 5, and the fourth air supply valve 6 in the cockpit and the passenger cabin to realize the valve piece being fully opened, fully closed, or stopped at any position. The implementation of the present invention can improve the comfort of the aircraft cockpit and passenger cabin.
[0035] The present invention relates to a self-locking multi-air supply port synchronous control structure, which introduces a control device capable of adjusting the opening of the cockpit and cabin heating air supply ports in a heating system. During the use of the heating system, the driver can adjust the air distribution amount entering the cockpit according to actual needs. The driver can achieve the cockpit and cabin temperature adjustment function by moving the self-locking handle up and down and manually adjusting the cockpit and cabin air supply valve openings to achieve the valve plate fully open, fully closed or stopped at any position. The valve plates of the first air supply valve, the second air supply valve, the third air supply valve and the fourth air supply valve can rotate within the range of 0 to 90 degrees. The implementation of the present invention can improve the comfort of the aircraft cockpit and cabin. The self-locking handle design scheme can prevent the valve plates from being offset due to aircraft vibration or accidental contact by the driver. The present invention introduces a self-locking multi-air supply port synchronous control structure in the bleed air heating system, which solves the problem that the cabin temperature of a certain type of helicopter cannot be adjusted due to the omission of the cabin temperature control system.
Claims
1. A self-locking multi-air supply port synchronous control system, characterized in that: The system consists of an air supply distribution structure and a valve plate synchronous control structure. The air supply distribution structure consists of a first air supply valve (2), a second air supply valve (3), a third air supply valve (5), and a fourth air supply valve (6); the valve plate synchronous control structure consists of a self-locking handle (1), a valve plate rotating shaft (4), a rotating rocker arm assembly (7), a first rocker arm fixing pin (8), a double steel cable fixing pin (9), a second rocker arm fixing pin (10), a double steel cable fixing seat (11), a steel cable locking pin (12), a fixing clamp (13), a first operating steel cable (14), and a second operating steel cable (15). The first air supply valve (2) and the second air supply valve (3) are located on the left and right sides of the cockpit, respectively, and are used to provide heating air to the pilot and co-pilot; the third air supply valve (5) and the fourth air supply valve (6) are located in the middle of the cabin, and are used to provide air to the passengers on the left and right sides of the cabin. The openings of these four air supply valves are controlled by a valve plate synchronous control structure; The first air supply valve (2) and the second air supply valve (3) adopt the same design structure. The valve plates of the first air supply valve (2) and the second air supply valve (3) are driven by the same valve plate rotating shaft (4). The two valve plates move synchronously around the valve plate rotating shaft (4). The self-locking handle (1) is fixed to the double steel cable fixing seat (11) by a double steel cable fixing pin (9), the double steel cable fixing seat (11) is connected to the first control steel cable (14) and the second control steel cable (15) by two steel cable locking pins (12), and the first control steel cable (14) and the second control steel cable (15) are fixed to the aircraft structure by two fixing clamps (13); The rotating rocker arm assembly (7) is composed of a rocker arm rotating shaft (7a), a rocker arm pin hole (7b), a rocker arm (7c), and a rocker arm fixing pin sliding groove (7d); The rocker arm shaft (7a) is sleeved on the shutter plate shaft (4). During assembly, the second rocker arm fixing pin (10) is inserted into the rocker arm pin hole (7b) for locking. The rotating rocker arm assembly (7) is fixed to the shutter plate shaft (4). After locking, the two perform synchronous rotation. The rocker arm (7c) and the self-locking handle (1) are locked by the first rocker arm fixing pin (8). When the self-locking handle (1) moves up and down, the first rocker arm fixing pin (8) is in the rocker arm fixing pin sliding groove (7d). ) to ensure that the self-locking handle (1) can move freely up and down. During the up and down movement of the self-locking handle (1), the rotating rocker arm assembly (7) rotates around the shutter plate shaft (4). During the up and down movement of the self-locking handle (1), the distance between the shutter plate shaft (4) and the first rocker arm fixing pin (8) changes. The function of the rocker arm fixing pin sliding groove (7d) is to adjust the distance between the shutter plate shaft (4) and the first rocker arm fixing pin (8).
2. A self-locking multi-air supply port synchronous control system according to claim 1, characterized in that: The self-locking handle (1) is composed of a self-locking handle locking rod (1a), a handle pull rod (1b), a spring (1c), a clamping nut (1d), a handle sliding sleeve (1e), and a steel ball (1f); The handle sliding sleeve (1e) is fixed to the aircraft floor (16) through a clamping nut (1d), and the self-locking handle locking rod (1a) is used to lock the handle pull rod (1b) and the handle sliding sleeve (1e) to prevent the valve plates of the first air supply valve (2), the second air supply valve (3), the third air supply valve (5), and the fourth air supply valve (6) from being displaced due to aircraft vibration or accidental contact by the pilot.
3. A self-locking multi-air supply port synchronous control system according to claim 2, characterized in that: There is a wedge-shaped groove below the self-locking handle lock rod (1a), which cooperates with the steel ball (1f). The self-locking handle lock rod (1a) is installed in the handle pull rod (1b). There is a compression spring below the self-locking handle lock rod (1a). In the free state, the spring is in a compressed state. The spring force forces the self-locking handle lock rod (1a) to move upward. During the movement, the wedge-shaped groove pushes the steel ball (1f) to move outward. Finally, the steel ball (1f) fits with the handle sliding sleeve (1e). Under the action of friction, the steel ball (1f) and the handle sliding sleeve (1e) are locked. After locking, the handle pull rod (1b) cannot move up and down.
4. A self-locking multi-air supply port synchronous control system according to claim 3, characterized in that: When the handle rod (1b) needs to be moved up or down, the self-locking handle locking rod (1a) is pressed downward by hand, and the self-locking handle locking rod (1a) moves downward. During the movement, the gap between the wedge groove and the steel ball (1f) gradually increases until the fitting part of the steel ball (1f) and the handle sliding sleeve (1e) is disengaged, and the friction force is reduced. While pressing the self-locking handle locking rod (1a), the handle rod (1b) is moved upward or downward to realize the function of opening, closing or stopping the valve at any position.
5. The self-locking multi-air supply port synchronous control system according to claim 1, characterized in that: The first air supply valve (2) is composed of a first air outlet grid (2a), a first air supply pipe (2b), and a first valve plate (2c); The heated gas output from the air supply distribution structure enters from the inlet of the first air supply valve (2), then flows out from the first air outlet grid (2a) and enters the cockpit. When the valve plate is perpendicular to the axis of the first air supply pipe (2b), the air supply valve is fully closed. When the valve plate is parallel to the axis of the first air supply pipe (2b), the air supply valve is fully opened.
6. The self-locking multi-air supply port synchronous control system according to claim 1, characterized in that: The third air supply valve (5) is composed of a third air outlet grid (5a), a third air supply pipe (5b), and a third valve plate (5c); The heated gas output from the air supply distribution structure enters from the inlet of the third air supply valve (5), then flows out from the third air outlet grid (5a) and enters the passenger cabin. When the valve plate is perpendicular to the axis of the third air supply pipe (5b), the air supply valve is fully closed. When the valve plate is parallel to the axis of the third air supply pipe (5b), the air supply valve is fully opened.
7. The self-locking multi-air supply port synchronous control system according to claim 1, characterized in that: The self-locking handle (1) drives the rotating rocker arm assembly (7) to rotate within the range of 0 to 90 degrees during the up and down movement. The up and down stroke of the self-locking handle (1) is 5 cm. The third air supply valve (5) is driven by the first operating steel cable (14), and the fourth air supply valve (6) is driven by the second operating steel cable (15). The telescopic stroke of the first operating steel cable (14) and the second operating steel cable (15) required for the third air supply valve (5) and the fourth air supply valve (6) to move from opening to closing is also 5 cm. Therefore, the self-locking handle (1) enables the first air supply valve (2), the second air supply valve (3), the third air supply valve (5), and the fourth air supply valve (6) to achieve synchronous movement during the up and down movement.
Citation Information
Patent Citations
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CN112413183A
Alpine region non-pressurized cabin aircraft heating system
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