CN113581474B - Sliding type air inlet ventilation mechanism of auxiliary power unit of airplane - Google Patents
Sliding type air inlet ventilation mechanism of auxiliary power unit of airplane Download PDFInfo
- Publication number
- CN113581474B CN113581474B CN202111054612.5A CN202111054612A CN113581474B CN 113581474 B CN113581474 B CN 113581474B CN 202111054612 A CN202111054612 A CN 202111054612A CN 113581474 B CN113581474 B CN 113581474B
- Authority
- CN
- China
- Prior art keywords
- intake valve
- air inlet
- intake
- sliding
- ventilation mechanism
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000007246 mechanism Effects 0.000 title claims abstract description 120
- 238000009423 ventilation Methods 0.000 title claims abstract description 58
- 230000033001 locomotion Effects 0.000 claims abstract description 28
- 230000005540 biological transmission Effects 0.000 claims abstract description 18
- 230000008901 benefit Effects 0.000 description 7
- 238000001816 cooling Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000005096 rolling process Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000010687 lubricating oil Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D41/00—Power installations for auxiliary purposes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0611—Environmental Control Systems combined with auxiliary power units (APU's)
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D2013/0603—Environmental Control Systems
- B64D2013/0685—Environmental Control Systems with ozone control
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- Air-Flow Control Members (AREA)
- Mechanically-Actuated Valves (AREA)
Abstract
A sliding type air inlet ventilation mechanism of an auxiliary power unit of an airplane is free in selection and arrangement of an air inlet valve actuator and free from affecting air inlet. The sliding type air inlet ventilation mechanism comprises an air inlet valve, a driving mechanism, two groups of transmission mechanisms, an air inlet valve rotating shaft, a driving shaft and two groups of motion limiting mechanisms, wherein the curved surface shape of the air inlet valve is matched with the skin of an airplane body, the air inlet valve is opened or closed through the driving mechanism, the transmission mechanisms are arranged on two sides of the length direction of the air inlet valve and are connected with the air inlet valve and the driving mechanism at two ends, the air inlet valve rotating shaft connects the end part of the transmission mechanism, close to the air inlet valve, with the air inlet valve, the driving shaft connects the end part of the transmission mechanism, close to the driving mechanism, with the driving mechanism, and the motion limiting mechanisms are respectively arranged on one side and the other side of the length direction of the air inlet valve, opposite to the outer side of the air inlet valve, in the length direction of the air inlet valve.
Description
Technical Field
The present invention relates to air intake and ventilation cooling of an aircraft auxiliary power unit, and more particularly to a sliding air intake and ventilation mechanism of an aircraft auxiliary power unit.
Background
The aircraft auxiliary power unit is mainly used for starting a main engine and supplying air to a passenger cabin, and provides auxiliary power for various airborne equipment. Typically, when the main engine of the aircraft is not operating on the ground, the primary air source and the power source are both from the auxiliary power unit of the aircraft. The auxiliary power unit of the aircraft needs to suck air flow from the outside of the aircraft body through an air inlet system and a ventilation cooling system, the air flow of the air inlet system is used for the auxiliary power unit of the aircraft to work, and the ventilation cooling air flow is used for cooling a lubricating oil radiator of the auxiliary power unit of the aircraft, an auxiliary power unit cabin of the aircraft and route replaceable units around the auxiliary power unit of the aircraft.
The air intake and ventilation mechanism of the auxiliary power unit (more specifically, the air intake valve used therein) isolates the external environment of the aircraft from the air intake duct of the auxiliary power unit and the interior compartment of the auxiliary power unit. When the auxiliary power unit of the aircraft is in operation, the inlet valve is opened to provide the required air for the operation of the auxiliary power unit of the aircraft. When the auxiliary power unit of the aircraft is closed, the air inlet valve is also closed, so that the purposes of isolating the external environment and protecting system equipment are achieved.
In the prior art, an intake and ventilation mechanism 10 of an auxiliary power unit for an aircraft is mainly composed of an intake valve 11, an intake valve rotation shaft 12, and an intake valve actuator 13 as shown in fig. 6, and the intake valve actuator 13 rotationally pushes the intake valve 11 open and close via the intake valve rotation shaft 12. More specifically, the intake valve actuator 13 is linearly actuated, when the intake valve 11 needs to be opened, the push rod 13a of the intake valve actuator 13 is moved forward, the intake valve 11 is rotated about the intake valve rotation shaft 12 so that the intake valve 11 is opened, and when the intake valve 11 needs to be closed, the push rod 13a of the intake valve actuator 13 is moved backward, and the intake valve 11 is rotated in the opposite direction so that the intake valve 11 is closed.
The operation mode of the air intake and ventilation mechanism (the air intake valve 11) of the auxiliary power unit of the aircraft in the prior art has relatively simple design form, but has the following defects:
(1) The arrangement position of the intake valve actuator 13 is relatively fixed. Specifically, the intake valve actuator 13 needs to be disposed in front of and below the intake valve 11, ensuring that the intake valve 11 is opened with a certain rotational moment. In addition, in some large civil aircraft designs, the power of the auxiliary power device of the aircraft is larger, the air inflow is larger, the area of the air inlet valve is larger, and at the moment, the air inlet valve actuator 13 also needs to be correspondingly selected to be of a larger specification, which causes certain difficulty in arrangement and structural installation;
(2) The pushrod 13a of the intake valve actuator 13 is located in the passage of the intake air flow, and causes unnecessary disturbance to the intake air. In particular, when the intake valve 11 is opened, the pushrod 13a passes through the middle of the intake duct 14, which has a certain influence on the intake air.
Therefore, how to design an air intake ventilation mechanism of an auxiliary power unit of an aircraft, which is more free in selection and arrangement of an air intake valve actuator and does not influence air intake, is needed to solve the technical problem.
Disclosure of Invention
The present invention has been made to solve the above-mentioned problems, and an object of the present invention is to provide a sliding type air intake and ventilation mechanism for an auxiliary power unit of an aircraft, in which the selection and arrangement of intake valve actuators are more free and no influence is exerted on the intake air.
In order to achieve the above object, the present invention provides a sliding type intake ventilation mechanism of an auxiliary power unit for an aircraft, comprising an intake valve having a curved surface shape matching with a skin of a fuselage of the aircraft, the intake valve being opened or closed by a driving mechanism, characterized in that both sides of the intake valve in a longitudinal direction are each provided with a set of transmission mechanisms for converting movement of the driving mechanism into movement of the intake valve in a direction to open or close the intake valve, the transmission mechanisms are connected at both ends to the intake valve and the driving mechanism, the sliding type intake ventilation mechanism further comprises an intake valve rotation shaft connecting an end of the transmission mechanism located on both sides of the intake valve in the longitudinal direction on one side of the intake valve with the intake valve, and a driving shaft connecting an end of the transmission mechanism located on both sides of the intake valve in the longitudinal direction on one side of the driving mechanism, and the driving shaft is connected with the driving mechanism, and both sets of movement restricting mechanisms are each provided on the outer side of the intake valve in the longitudinal direction with respect to the intake valve.
Preferably, the transmission mechanism is a rotary link that is driven by the drive shaft to rotate, thereby driving the intake valve to move from a position in which it is in a closed state with respect to the intake port to a position in which it is in an open state with respect to the intake port.
Preferably, the motion limiting mechanism includes a slide rail, a slide rail rolling shaft, and a slide rail supporting structure, the slide rail has a linear structure for the slide rail rolling shaft to slide along a straight line therein, the slide rail rolling shaft is formed at the intake valve and connects the slide rail with the intake valve, and the slide rail supporting structure is fixed on an aircraft structure and is used for supporting the slide rail.
Preferably, the driving mechanism is a rotary intake valve actuator or a linear actuator that changes the output of the intake valve actuator to a linear drive through a gear.
Preferably, when the intake valve of the sliding type air intake and ventilation mechanism is in a closed state, the intake valve is flush with the aircraft body skin to close the air intake port, the slide rail roller is located on one side in the sliding direction in the slide rail, and when the intake valve of the sliding type air intake and ventilation mechanism is in an open state, the intake valve is inclined relative to the aircraft body skin to open the air intake port, and the slide rail roller is located on the other side in the sliding direction in the slide rail.
Preferably, the sliding rail is used for limiting and maintaining the movement direction of the intake valve, and the overall movement of the intake valve is a combination of sliding and rotating during the movement of the intake valve from the closed state to the open state and vice versa.
Preferably, a portion of the intake valve is retracted into the intake port during movement from the closed state to the open state to reduce the area of the intake valve protruding out of the fuselage.
The sliding type air inlet ventilation mechanism of the auxiliary power unit of the airplane has the following technical effects:
(1) Basic function
The sliding type air inlet ventilation mechanism can complete the actions of closing and opening the air inlet. When the air inlet valve is in the open position, air flow can be provided for the air inlet pipeline and the ventilation cooling pipeline of the auxiliary power unit of the aircraft, and when the air inlet valve is in the closed position, the air inlet valve is flush with the airframe, and no additional resistance is generated, so that the main functions of the existing air inlet ventilation mechanism are fully covered in functional aspects.
(2) Advantages of the invention
Advantage 1: the actuator is flexible in selection and arrangement.
The invention drives the intake valve to open and close through the rotation shaft of the intake valve, so that the driving mechanism can take various forms, and a rotary type intake valve actuator can be directly adopted, and a linear actuator can also be adopted. In addition, the arrangement position and the mode of the driving mechanism are more flexible.
Advantage 2: no interference in the inlet air flow area
The intake valve actuators are positioned on two sides of the intake valve, are connected through the rotation shaft of the intake valve and are positioned on the outer side of the air inlet pipe of the auxiliary power unit of the aircraft, so that no interference is caused to the air flow passage in the air inlet pipe.
Advantage 3: when the air inlet valve is opened, the operation of the auxiliary power unit of the aircraft is facilitated
The operation of the auxiliary power unit of the aircraft can be mainly divided into two states of ground and air according to different air inlet states. When the aircraft works on the ground, the air inlet of the auxiliary power unit of the aircraft enters the air inlet channel due to the suction effect of the air compressor. Reducing the flow resistance of the inlet channel is beneficial to the air intake of the auxiliary power unit of the aircraft. The invention has larger opening area under the condition of the same rotation angle. Meanwhile, when the air-conditioner operates in the air, the air inlet valve blocks air flow, so that higher air inlet pressure in front of the air inlet is formed. The larger the area blocked by the intake valve, the higher the pressure. The excessive pressure is unfavorable for the auxiliary power unit of the aircraft to start in the air, and the sliding air door generates smaller pressure than the air inlet valve of the traditional design because part of the area is taken into the air inlet channel and the area protruding out of the airframe is smaller.
Advantage 4: the slide rail plays a limiting role
When the air inlet valve of the auxiliary power unit of the airplane is opened in the air, the air inlet valve actuator needs to have a certain holding moment in order to keep the opened state due to the air impact. The sliding rail can play a limiting role, so that the requirement on the actuator can be reduced, and a possible precondition is provided for reducing and lightening the design of the actuator.
Drawings
Fig. 1 is a perspective view showing the constitution of a sliding type intake and ventilation mechanism of an auxiliary power unit for an aircraft according to an embodiment of the present invention, wherein a driving mechanism (intake valve actuator) provided in the sliding type intake and ventilation mechanism is not shown.
Fig. 2 is a schematic diagram showing an arrangement of a driving mechanism (intake valve actuator) with respect to an intake valve and a transmission mechanism in a sliding type intake ventilation mechanism according to an embodiment of the present invention.
Fig. 3 is a side view of a sliding intake vent mechanism of an auxiliary power unit for an aircraft according to an embodiment of the present invention with an intake valve in a closed position.
Fig. 4 is a side view of a sliding intake vent mechanism of an auxiliary power unit for an aircraft according to an embodiment of the present invention with an intake valve in an open state.
Fig. 5 is a schematic view showing the movement directions of the respective members of the sliding intake and ventilation mechanism of the auxiliary power unit for an aircraft according to an embodiment of the present invention when the intake valve is operated from the closed state to the open state.
Fig. 6 is a schematic diagram showing an operation mode of an intake ventilation mechanism of a conventional auxiliary power unit for an aircraft.
Fig. 7 is a comparative schematic diagram showing the minimum flow cross-sectional area of a sliding type intake and ventilation mechanism of an auxiliary power unit for an aircraft according to an embodiment of the present invention and an intake and ventilation mechanism of a conventional auxiliary power unit for an aircraft when an intake valve is in an open state.
(symbol description)
100. Sliding type air inlet ventilation mechanism
110. Intake valve
120. Rotary connecting rod
130. Intake valve rotating shaft
140. Driving shaft
150. Sliding rail
160. Sliding rail roller
170. Sliding rail supporting structure
180. Intake valve actuator
181. Gear wheel
Detailed Description
Hereinafter, the sliding type air intake and ventilation mechanism 100 of the auxiliary power unit for an aircraft according to the present invention will be described in detail with reference to fig. 1 and 2. Fig. 1 is a perspective view showing the configuration of a sliding intake and ventilation mechanism 100 of an auxiliary power unit for an aircraft according to an embodiment of the present invention, in which a driving mechanism (intake valve actuator) included in the sliding intake and ventilation mechanism 100 is not shown, and fig. 2 is a schematic view showing the arrangement of the driving mechanism (intake valve actuator) with respect to an intake valve 110 and a transmission mechanism in the sliding intake and ventilation mechanism 100 according to an embodiment of the present invention.
As shown in fig. 1, the sliding type air intake and ventilation mechanism 100 of the auxiliary power unit of the aircraft of the present invention comprises an air intake valve 110 with a curved surface shape matched with the shape of the aircraft, when the air intake valve 110 is opened by a driving mechanism, the air intake valve 110 can provide the required air for the operation of the auxiliary power unit of the aircraft, and when the air intake valve 110 is closed by the driving mechanism, the air intake valve 110 can be used for isolating the external environment so as to protect the system equipment.
A set of transmission mechanisms for converting the motion of the driving mechanism into motion (opening and closing) of the intake valve 110 are provided on both sides of the intake valve 110 in the longitudinal direction.
More specifically, as shown in fig. 1, the sliding type intake and ventilation mechanism 100 includes a rotating link 120 on each of both sides in the longitudinal direction of the intake valve 110. That is, the sliding type air intake and ventilation mechanism 100 includes two rotating links 120 as a transmission mechanism.
In addition, the sliding type intake ventilation mechanism 100 further includes an intake valve rotation shaft 130 and a drive shaft 140.
The intake valve rotation shaft 130 is a member that connects an end portion of one rotation link 120 located on one side in the longitudinal direction of the intake valve 110 on the intake valve 110 side and an end portion of the other rotation link 120 located on the other side in the longitudinal direction of the intake valve 110 on the intake valve 110 side to the intake valve 110.
The driving shaft 140 is a member connecting an end portion of one of the rotation links 120 located on one side in the longitudinal direction of the intake valve 110 on the side of the driving mechanism with an end portion of the other rotation link 120 located on the other side in the longitudinal direction of the intake valve 110 on the side of the driving mechanism, and the shaft body of the driving shaft 140 is connected to the driving mechanism.
In addition, as shown in fig. 1, the sliding type intake ventilation mechanism 100 is provided on one side and the other side in the length direction of the intake valve 110 with respect to the intake valve 110 with a slide rail 150, a slide rail roller 160, and a slide rail support structure 170 as motion limiting mechanisms, that is, the sliding type intake ventilation mechanism 100 includes two slide rails 150, two slide rail rollers 160, and two slide rail support structures 170 as two sets of motion limiting mechanisms.
The rail 150 has a linear structure in which the rail roller 160 slides in a straight line, and the rail roller 160 is formed at the intake valve 110 and connects the rail 150 and the intake valve 110. In addition, the rail support structure 170 is fixed to the aircraft structure and is used for supporting the rail 150.
The drive mechanism differs from the prior art intake and ventilation mechanism 10 shown in fig. 6 in that only a linear actuation drive mechanism (intake valve actuator 13) can be used, other actuation types of drive mechanisms can be selected and a more flexible arrangement can be used.
For example, the driving mechanism can directly employ a rotary intake valve actuator, and this type of driving mechanism can be provided on either side of the length direction of the intake valve 110. In addition, the driving mechanism can also change the output of the intake valve actuator 180 to a linear drive through the gear 181 as shown in fig. 2, and after being converted to a linear actuator, this type of driving mechanism can be flexibly arranged according to actual needs, for example, disposed on either side of the length direction of the intake valve 110, even in any direction, as shown by a broken line in fig. 2.
Next, with reference to fig. 3 and 4, different operation states of the sliding type air intake and ventilation mechanism 100 will be described. Fig. 3 is a side view of the sliding type intake ventilation mechanism 100 of the auxiliary power unit of the present invention in a closed state, and fig. 4 is a side view of the sliding type intake ventilation mechanism 100 of the auxiliary power unit of the present invention in an open state.
In fig. 3 and 4, assuming that the horizontal plane is the plane in which the intake port is located, as shown in fig. 3, when the intake valve 110 of the sliding type intake and ventilation mechanism 100 is in the closed state, the intake valve 110 is located horizontally, while the slide rail roller 160 is located on one side in the sliding direction (right side in fig. 3) in the slide rail 150, as shown in fig. 3, when the intake valve 110 of the sliding type intake and ventilation mechanism 100 is in the open state, the intake valve 110 is inclined with respect to the horizontal plane, while the slide rail roller 160 is located on the other side in the sliding direction (left side in fig. 3) in the slide rail 150
Fig. 5 is a schematic view showing the movement directions of the respective components of the intake valve 110 of the sliding intake ventilation mechanism 100 of the auxiliary power unit for an aircraft according to an embodiment of the present invention when the intake valve moves from the closed state to the open state.
As shown in fig. 5, when the intake valve 110 of the sliding intake ventilation mechanism 100 of the auxiliary power unit of the aircraft is actuated from the closed state to the open state,
(1) The driving shaft 140 is driven to rotate in a counterclockwise direction, thereby driving the rotating link 120 to move in a counterclockwise direction;
(2) The intake valve rotation shaft 130 rotates following the counterclockwise movement of the rotation link 120, thereby driving the intake valve 110 to move from a horizontal (closed position) to an inclined (open position) with respect to the horizontal;
(3) Both sides of the intake valve 110 in the length direction limit and maintain the movement direction thereof by the slide rail 150;
(4) The slide rail roller 160 slides in a straight line in the slide rail 150;
(5) The slide rail support structure 170 is fixed to the aircraft structure, thereby enabling the movement of the intake valve 110 as a whole to be a combination of rearward sliding and rotation;
(6) After the driving shaft 140 rotates to a predetermined angle, the intake valve 110 is completely opened, and at this time, the slide rail supporting structure 170 also plays a role of motion limiting protection.
The operation of the auxiliary power unit of the aircraft can be mainly divided into two states of ground and air according to different air inlet states. When the aircraft works on the ground, the air inlet of the auxiliary power unit of the aircraft enters from the air inlet channel due to the suction effect of the air compressor. Reducing the flow resistance of the inlet channel is beneficial to the air intake of the auxiliary power unit of the aircraft. The invention has larger opening area under the condition of the same rotation angle.
In air operation, a higher intake pressure before the intake port 110 is created due to the blocking of air flow by the intake valve 110. The greater the area blocked by the intake valve 110, the higher the pressure. The excessive pressure is detrimental to the aircraft auxiliary power unit starting in the air, as shown in fig. 7, the sliding type intake ventilation mechanism 100 has a smaller area protruding outside the fuselage due to the partial area being received in the intake duct, and thus the pressure generated by the intake valve 110 of the sliding type intake ventilation mechanism 100 according to an embodiment of the present invention is smaller than that of the intake valve of conventional design.
Additional advantages and modifications will readily appear to those skilled in the art. Therefore, the invention in its broader aspects is not limited to the specific details and representative embodiments shown and described herein. Accordingly, modifications may be made without departing from the spirit or scope of the general inventive concept as defined by the appended claims and their equivalents.
In the description of the above embodiment, the description of the counterclockwise rotation or the like with the specific directivity is used, but the present invention is not limited to the description of the specific directivity, since the direction of rotation thereof is related to the specific arrangement of the driving mechanism, and since in the present invention, there is an advantage in that the specific arrangement of the driving mechanism is flexible, the direction of rotation may also be clockwise rotation.
Claims (5)
1. A sliding type air inlet and ventilation mechanism (100) of an auxiliary power unit of an airplane comprises an air inlet valve (110) with a curved surface shape matched with a skin of the fuselage of the airplane, and the air inlet valve (110) is opened or closed by a driving mechanism,
two sides of the length direction of the intake valve (110) are respectively provided with a group of transmission mechanisms for converting the motion of the driving mechanism into the motion of the intake valve (110) towards the direction of opening or closing the air inlet, the transmission mechanisms are connected with the intake valve (110) and the driving mechanism at two ends,
the sliding type intake ventilation mechanism (100) further comprises an intake valve rotation shaft (130) and a drive shaft (140), the intake valve rotation shaft (130) connects an end of the transmission mechanism located at both sides of the intake valve (110) in the length direction and the intake valve (110), the drive shaft (140) connects an end of the transmission mechanism located at both sides of the intake valve (110) in the length direction and the drive mechanism, and the drive shaft (140) is connected with the drive mechanism,
the sliding type intake ventilation mechanism (100) is provided on one side and the other side in the length direction of the intake valve (110), two sets of movement restricting mechanisms are each provided on the outer side in the length direction of the intake valve (110) with respect to the intake valve (110),
the motion limiting mechanism comprises a sliding rail (150), a sliding rail roller (160) and a sliding rail supporting structure (170),
the slide rail (150) has a linear structure in which the slide rail roller (160) slides in a linear direction,
the slide rail roller (160) is formed on the intake valve (110) and connects the slide rail (150) with the intake valve (110),
the slide rail supporting structure (170) is fixed on the aircraft structure and is used for supporting the slide rail (150),
when the air inlet valve (110) of the sliding air inlet ventilation mechanism (100) is in a closed state, the air inlet valve (110) is flush with the aircraft fuselage skin to close the air inlet, the sliding rail roller (160) is positioned on one side of the sliding rail (150) in the sliding direction,
when the intake valve (110) of the sliding type intake ventilation mechanism (100) is in an open state, the intake valve (110) is inclined relative to the aircraft fuselage skin to open the intake port, and the slide rail roller (160) is located on the other side in the sliding direction in the slide rail (150).
2. A sliding air intake ventilation mechanism (100) as claimed in claim 1, characterized in that,
the transmission mechanism is a rotary connecting rod (120),
the rotary link (120) is driven by the rotational drive of the drive shaft (140), thereby driving the intake valve (110) to move from a position in a closed state with respect to the intake port to a position in an open state with respect to the intake port.
3. A sliding air intake ventilation mechanism (100) as claimed in claim 2, characterized in that,
the driving mechanism is a rotary intake valve actuator or a linear actuator which changes the output of the intake valve actuator (180) into linear drive through a gear (181).
4. A sliding air intake ventilation mechanism (100) according to claim 3, characterized in that,
the sliding rail (150) is used for limiting and maintaining the movement direction of the intake valve (110),
the overall movement of the intake valve (110) during movement from the closed state to the open state and vice versa is a combination of sliding and rotating.
5. A sliding air intake ventilation mechanism (100) as claimed in claim 4, characterized in that,
the intake valve (110) is retracted into the intake port during movement from a closed state to an open state to reduce the area of the intake valve (100) protruding out of the fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111054612.5A CN113581474B (en) | 2021-09-09 | 2021-09-09 | Sliding type air inlet ventilation mechanism of auxiliary power unit of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111054612.5A CN113581474B (en) | 2021-09-09 | 2021-09-09 | Sliding type air inlet ventilation mechanism of auxiliary power unit of airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113581474A CN113581474A (en) | 2021-11-02 |
| CN113581474B true CN113581474B (en) | 2023-05-09 |
Family
ID=78241569
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111054612.5A Active CN113581474B (en) | 2021-09-09 | 2021-09-09 | Sliding type air inlet ventilation mechanism of auxiliary power unit of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113581474B (en) |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7540142B2 (en) * | 2006-02-21 | 2009-06-02 | Honeywell International Inc. | Multiple auxiliary power unit system inlet ducts controlled by a single actuator |
| US8322981B2 (en) * | 2009-03-02 | 2012-12-04 | Hamilton Sundstrand Corporation | Aircraft fluid diversion inlet louver |
| CN105201653B (en) * | 2015-09-10 | 2017-03-29 | 中国商用飞机有限责任公司 | The actuation mechanism of the inlet flap of auxiliary power unit gas handling system |
| CN106956782A (en) * | 2017-05-04 | 2017-07-18 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft auxiliary power plant cabin formula punching press inlet duct |
-
2021
- 2021-09-09 CN CN202111054612.5A patent/CN113581474B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN113581474A (en) | 2021-11-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| RU2470205C2 (en) | Linear telescopic actuator for movement of first and second elements relative to fixed element | |
| US10830089B2 (en) | Turbofan comprising a series of rotatable blades for blocking off the bypass flow duct | |
| CN102459856B (en) | Thrust reversing device | |
| RU2494009C2 (en) | Aircraft fresh air intake | |
| CN102449294B (en) | Thrust reverser for a dual-flow turbine engine nacelle | |
| US8141816B2 (en) | AFT inlet duct mounted door actuator | |
| US7600714B2 (en) | Diffusing air inlet door assembly | |
| CN102597475B (en) | Reverse thrust device | |
| US11193379B2 (en) | Turbofan comprising a set of rotatable blades for blocking off the bypass flow duct | |
| US11542028B2 (en) | Aircraft comprising an air intake | |
| CN102859168B (en) | Turbojet engine nacelle | |
| CN103732949A (en) | Double-acting linear actuator | |
| CN103314207A (en) | Aircraft turbojet engine thrust reverser with a reduced number of latches | |
| CN103917766A (en) | Thrust reverser device | |
| US11401886B2 (en) | Turbofan comprising a set of rotatable blades for blocking off the bypass flow duct | |
| CN103180209A (en) | Turbojet engine nacelle with variable ventilation outlet cross section | |
| CN111319778B (en) | Turbofan engine and aircraft | |
| CN102395776A (en) | Control system for a turboreactor nacelle | |
| CN113581474B (en) | Sliding type air inlet ventilation mechanism of auxiliary power unit of airplane | |
| RU2521906C2 (en) | Turbojet nacelle moving panel drive system | |
| CN103201489B (en) | For the actuating system of aircraft propulsion unit | |
| US11635042B2 (en) | Turbofan having a set of rotatable blades for blocking off the duct for the bypass flow | |
| US10344710B2 (en) | Engine with a thrust reverser lockout mechanism | |
| US9885316B2 (en) | Actuating device including a primary locking device | |
| US11802524B2 (en) | Turbofan comprising a series of rotary blades for closing off the duct for the secondary stream |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |