CN210707910U - Environment control system for airborne pod of transportation aircraft - Google Patents
Environment control system for airborne pod of transportation aircraft Download PDFInfo
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- CN210707910U CN210707910U CN201921569698.3U CN201921569698U CN210707910U CN 210707910 U CN210707910 U CN 210707910U CN 201921569698 U CN201921569698 U CN 201921569698U CN 210707910 U CN210707910 U CN 210707910U
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Abstract
The utility model belongs to airborne vehicle flight test field, concretely relates to transportation type aircraft machine carries nacelle environmental control system. The system comprises: the system comprises an original aircraft air distribution pipeline, a newly-added bleed air pipeline, an electric valve, a controller, a sealed nacelle and an aircraft cabin; the outlet of the original aircraft air distribution pipeline is communicated with the aircraft cabin, the newly-added bleed air pipeline is communicated with the original aircraft air distribution pipeline through an electric valve, the outlet of the newly-added bleed air pipeline is communicated with the sealed nacelle, the sealed nacelle is communicated with the aircraft cabin through an electric valve, and the control end of the electric valve are both connected to the output end of the controller, so that the controller controls the opening or closing of the electric valve and controls the opening degree of the electric valve. The utility model discloses a hang the nacelle of dress on transportation type aircraft and provide environmental control ability, guarantee nacelle in test equipment's operational environment.
Description
Technical Field
The utility model belongs to airborne vehicle flight test field, concretely relates to transportation type aircraft machine carries nacelle environmental control system.
Background
The transportation type airplane has large internal space, strong loading capacity, long dead time and low test cost, and is an ideal platform for other airplane hanging flights of various test equipment. The transport plane is provided with an environment control system with complete functions, and can meet the requirements of cabin temperature control and pressure regulation. The externally hung nacelle is an external independent cabin body, generally does not have the internal environment control and regulation capacity, and needs to be modified individually when the test equipment meets the requirements on the environmental temperature and pressure.
The environmental control of the nacelle is generally divided into two parts, temperature control and pressure control. The temperature in the hanging cabin is regulated by adopting the modes of electric heating/refrigeration, environment-controlled bleed air heating/refrigeration and the like; the pressure regulation of the nacelle is usually realized by installing a pressure regulating valve and a safety valve in the nacelle, i.e. installing an independent pressure regulating system in the nacelle. The traditional modification method has the defects of high development difficulty, long period, high maintenance requirement and the like.
SUMMERY OF THE UTILITY MODEL
The utility model aims at:
the utility model aims at providing a transportation type aircraft airborne pod environmental control method reduces transportation type aircraft airborne pod environmental control function and realizes risk and cost, shortens transportation type aircraft airborne pod and hangs flight test repacking cycle, simplifies the maintenance work flow.
The technical scheme of the utility model:
the utility model provides a transportation type aircraft machine carries nacelle environmental control system, include: the system comprises an original aircraft air distribution pipeline, a newly-added bleed air pipeline, an electric valve, a controller, a sealed nacelle and an aircraft cabin;
the outlet of the original aircraft air distribution pipeline is communicated with the aircraft cabin, the newly-added bleed air pipeline is communicated with the original aircraft air distribution pipeline through an electric valve, the outlet of the newly-added bleed air pipeline is communicated with the sealed nacelle, the sealed nacelle is communicated with the aircraft cabin through an electric valve, and the control end of the electric valve are both connected to the output end of the controller, so that the controller controls the opening or closing of the electric valve and controls the opening degree of the electric valve.
Further, when the controller controls the electric valve to be opened and controls the electric valve to be opened, the sealed nacelle is communicated with the airplane cabin, so that the air pressure of the sealed nacelle and the air pressure of the airplane cabin are balanced, and the air pressure of the sealed nacelle is further regulated by a pressure regulating system of the airplane cabin.
Further, the system further comprises: a temperature sensor disposed within the sealed nacelle; the output end of the temperature sensor is electrically connected with the control end of the controller; the temperature sensor detects the internal temperature of the sealed nacelle and transmits the detected temperature to the controller; the controller adjusts the opening degree of the electric valve according to the internal temperature so that the internal temperature of the sealed nacelle is within a preset temperature range.
Further, when the internal temperature is higher than a preset high threshold, the controller reduces the opening degree of the electric valve so as to achieve the effect of reducing the temperature in the sealed nacelle; when the internal temperature is lower than the preset low threshold, the controller increases the opening of the electric valve so as to achieve the effect of quickly increasing the temperature in the sealed nacelle.
Further, the system further comprises: a cabin communication pipeline for communicating the sealed nacelle and the aircraft cabin; an electric valve is arranged on the cabin communicating pipeline to close and open the cabin communicating pipeline.
Furthermore, the original air distribution pipeline is an air distribution pipeline of an environment control system of the transport aircraft.
Furthermore, the newly-added bleed air pipeline is a bleed air pipeline which is led out from the original air distribution pipeline and used for ventilating the nacelle.
Further, the electrically operated valve is an emergency switch, and the controller is closed to avoid the decompression of the cabin in an emergency state.
Furthermore, the controller is a control unit for controlling the temperature in the hanging cabin, a temperature value is set on the controller, and the controller receives the detected temperature and controls the opening of the electric valve.
Furthermore, the aircraft cabin is a transport aircraft cabin and has environment control capability.
The utility model has the advantages that:
the technology of the utility model utilizes the environmental control capability of the platform of the transportation aircraft to realize the environmental control of the external hanging nacelle, has simple technical principle, low difficulty in use and maintenance and low realization cost; the influence on the airplane is small, and the flight test risk is low; the modification workload is small, the preparation period is short, and the method is particularly suitable for demonstrating verification type hanging flight tasks.
Drawings
Fig. 1 is a schematic structural diagram of an airborne pod environmental control system of a transportation aircraft provided by the present invention; the system comprises an air distribution pipeline, a bleed air pipeline, an electric valve, a temperature sensor, a communication pipeline, a controller, a sealed nacelle and an airplane cabin, wherein the air distribution pipeline, the bleed air pipeline, the electric valve, the temperature sensor, the communication pipeline, the electric valve, the controller, the sealed nacelle and the airplane cabin are 1-1.
Detailed Description
The specific structure of the embodiment of the present invention is shown in fig. 1.
Nacelle environmental control system constitutes including former quick-witted air distribution pipeline 1, newly-increased bleed pipeline 2, electric valve 3, temperature sensor 4, passenger cabin intercommunication pipeline 5, motorised valve 6, controller 7, sealed nacelle 8, aircraft cabin 9.
Preferably, the original air distribution pipeline 1 is an air distribution pipeline of an environmental control system of a transport aircraft. Preferably, the newly added bleed air line 2 is a bleed air line leading from the original aircraft air distribution line for ventilating the nacelle. Preferably, the electric valve 3 is an electric valve installed in the bleed air pipeline and is controlled by the controller 7. Preferably, the temperature sensor 4 is a temperature sensor mounted in the nacelle to measure the ambient temperature inside the nacelle, which is fed back to the controller 7 as feedback for the control of the electrically operated shutter 3. Preferably, the cabin communication pipeline 5 is a pipeline for communicating the external hanging pod with the cabin, so that the two cabins can share one set of pressure regulating system. Preferably, the electric valve 6 is an emergency switch, and is closed by the controller in an emergency state to avoid the decompression of the cabin. Preferably, the controller 7 is a control unit for controlling the temperature in the nacelle, a temperature value is set on the controller, and the controller receives a temperature signal of a sensor in the nacelle and controls the opening of the electric valve. Preferably, the sealing pod 8 is an external body for mounting the test equipment and is manufactured according to a sealing structure design. The system can adjust the temperature and the pressure in the lifting cabin, and ensure the normal work of the test equipment. Preferably, the aircraft cabin 9 is a transport-type aircraft cabin, with environmental control capabilities.
The working principle of the utility model is as follows:
the pressurized air of an air distribution pipeline of the environment control system of the transport aircraft is taken as a heating source of the nacelle, the nacelle is communicated with the cabin, and the integrated pressure control of the cabin/the nacelle is realized by utilizing the capacity of a cabin pressure regulating system. The controller is used for controlling the opening degree of an electric valve on the bleed air pipeline to adjust the bleed air flow so as to realize temperature control in the nacelle, and a temperature sensor arranged in the nacelle is used as feedback of the temperature control.
The specific workflow is as follows:
a sealed nacelle 8 is hung outside a transport type airplane cabin 9 and used as a test equipment hanging and flying platform.
According to the figure 1, a newly-added bleed air pipeline 2 and an electric valve 3 are additionally arranged on an original aircraft air distribution pipeline 1 to introduce pressurized air into a sealed nacelle 8, a communication pipeline 5 is additionally arranged between the sealed nacelle 8 and an aircraft cabin 9 to form a pressurized air circulation loop, and meanwhile, the cabin/nacelle integrated pressure regulation is realized by a pressure regulation and regulation system of the aircraft cabin 9.
A controller 7 is additionally arranged in an aircraft cabin 9, and a temperature sensor 4 is additionally arranged in a sealed nacelle 8, so that the temperature control of the nacelle is realized. When the pod environment temperature sensed by the temperature sensor 4 is lower than the set temperature, the controller 7 sends an instruction to increase the opening degree of the electric valve 3, and when the pod environment temperature sensed by the temperature sensor 4 is higher than the set temperature, the controller 7 sends an instruction to decrease the opening degree of the electric valve 3, so that the pod temperature control is realized.
An electric valve 6 is additionally arranged at the outlet of the communication pipeline 5, and when the sealing nacelle 8 fails in sealing, the controller 7 sends an instruction to close the electric valve 3 and the electric valve 6, so that the normal function of the original machine is prevented from being influenced.
Claims (10)
1. An airborne pod environmental control system for a transport-type aircraft, comprising: the system comprises an original aircraft air distribution pipeline, a newly-added bleed air pipeline, an electric valve, a controller, a sealed nacelle and an aircraft cabin;
the outlet of the original aircraft air distribution pipeline is communicated with the aircraft cabin, the newly-added bleed air pipeline is communicated with the original aircraft air distribution pipeline through an electric valve, the outlet of the newly-added bleed air pipeline is communicated with the sealed nacelle, the sealed nacelle is communicated with the aircraft cabin through an electric valve, and the control end of the electric valve are both connected to the output end of the controller, so that the controller controls the opening or closing of the electric valve and controls the opening degree of the electric valve.
2. The system of claim 1, wherein the sealed pod is in communication with the aircraft cabin when the controller controls the electric valve to open and the electric valve to open, such that the air pressure of the sealed pod is balanced with the air pressure of the aircraft cabin, and the air pressure of the sealed pod is further regulated by the pressure regulating system of the aircraft cabin.
3. The system of claim 1, further comprising: a temperature sensor disposed within the sealed nacelle; the output end of the temperature sensor is electrically connected with the control end of the controller; the temperature sensor detects the internal temperature of the sealed nacelle and transmits the detected temperature to the controller; the controller adjusts the opening degree of the electric valve according to the internal temperature so that the internal temperature of the sealed nacelle is within a preset temperature range.
4. The system as claimed in claim 3, wherein when the internal temperature is higher than a preset high threshold, the controller decreases the opening degree of the electric valve to achieve the effect of cooling in the sealed pod; when the internal temperature is lower than the preset low threshold, the controller increases the opening of the electric valve so as to achieve the effect of quickly increasing the temperature in the sealed nacelle.
5. The system of claim 1, further comprising: a cabin communication pipeline for communicating the sealed nacelle and the aircraft cabin; an electric valve is arranged on the cabin communicating pipeline to close and open the cabin communicating pipeline.
6. The system of claim 1, wherein the original aircraft air distribution pipeline is a transport type aircraft environmental control system air distribution pipeline.
7. The system of claim 1, wherein the added bleed line is a bleed line leading from the original air distribution line for ventilating the pod.
8. The system of claim 1, wherein the electrically operated valve is a panic switch, and the controller is configured to close to avoid loss of cabin pressure during a panic state.
9. The system of claim 3, wherein the controller is a control unit for controlling the temperature in the nacelle, a temperature value is set on the controller, and the controller receives the detected temperature and controls the opening degree of the electric valve.
10. System according to any of claims 1-9, characterized in that the aircraft cabin is a transport-type aircraft cabin, with environmental control capabilities.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921569698.3U CN210707910U (en) | 2019-09-20 | 2019-09-20 | Environment control system for airborne pod of transportation aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921569698.3U CN210707910U (en) | 2019-09-20 | 2019-09-20 | Environment control system for airborne pod of transportation aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210707910U true CN210707910U (en) | 2020-06-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921569698.3U Active CN210707910U (en) | 2019-09-20 | 2019-09-20 | Environment control system for airborne pod of transportation aircraft |
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| Country | Link |
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| CN (1) | CN210707910U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114084354A (en) * | 2021-11-18 | 2022-02-25 | 新乡航空工业(集团)有限公司 | Micro-differential pressure balance adjustment drying system for pod |
| CN114560089A (en) * | 2021-12-30 | 2022-05-31 | 中国航空工业集团公司西安飞机设计研究所 | Ultrasonic motor valve and temperature adjusting system |
-
2019
- 2019-09-20 CN CN201921569698.3U patent/CN210707910U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114084354A (en) * | 2021-11-18 | 2022-02-25 | 新乡航空工业(集团)有限公司 | Micro-differential pressure balance adjustment drying system for pod |
| CN114084354B (en) * | 2021-11-18 | 2023-09-12 | 新乡航空工业(集团)有限公司 | Micro-pressure difference balance adjustment drying system for nacelle |
| CN114560089A (en) * | 2021-12-30 | 2022-05-31 | 中国航空工业集团公司西安飞机设计研究所 | Ultrasonic motor valve and temperature adjusting system |
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