NZ716755B - Multi-axis passenger-carrying aircraft - Google Patents
Multi-axis passenger-carrying aircraftInfo
- Publication number
- NZ716755B NZ716755B NZ716755A NZ71675516A NZ716755B NZ 716755 B NZ716755 B NZ 716755B NZ 716755 A NZ716755 A NZ 716755A NZ 71675516 A NZ71675516 A NZ 71675516A NZ 716755 B NZ716755 B NZ 716755B
- Authority
- NZ
- New Zealand
- Prior art keywords
- passenger
- air
- air outlet
- accommodating compartment
- communicated
- Prior art date
Links
- 238000001816 cooling Methods 0.000 claims abstract description 33
- 238000010438 heat treatment Methods 0.000 claims abstract description 33
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 24
- 239000004065 semiconductor Substances 0.000 claims description 9
- 238000005265 energy consumption Methods 0.000 description 4
- 231100000817 safety factor Toxicity 0.000 description 4
- 230000033228 biological regulation Effects 0.000 description 2
- 239000002826 coolant Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006011 modification reaction Methods 0.000 description 2
- 230000001737 promoting Effects 0.000 description 2
- 230000002708 enhancing Effects 0.000 description 1
Abstract
multi-axis passenger-carrying aircraft is provided, comprising: a heat exchange system; a cabin; and a passenger accommodating compartment arranged inside the cabin; wherein the electrical system is arranged inside the passenger accommodating compartment, and wherein the heat exchange system is at least communicated with an air inlet on the exterior of the cabin, an air outlet in communication with the passenger accommodating compartment, and a cooling and heating device with an air inlet end communicated with the air inlet and an air outlet end communicated with the air outlet. In operation, air outside the aircraft may enter the heat exchange system via the air inlet and the cooling and heating device via the air inlet end to be cooled or heated by the cooling and heating device as desired. The air after heat exchange may be discharged via the air outlet end and enter the passenger accommodating compartment via the air outlet, providing cool air or warm air to the passenger accommodating compartment, allowing more comfort for the passenger(s) in the passenger accommodating compartment. least communicated with an air inlet on the exterior of the cabin, an air outlet in communication with the passenger accommodating compartment, and a cooling and heating device with an air inlet end communicated with the air inlet and an air outlet end communicated with the air outlet. In operation, air outside the aircraft may enter the heat exchange system via the air inlet and the cooling and heating device via the air inlet end to be cooled or heated by the cooling and heating device as desired. The air after heat exchange may be discharged via the air outlet end and enter the passenger accommodating compartment via the air outlet, providing cool air or warm air to the passenger accommodating compartment, allowing more comfort for the passenger(s) in the passenger accommodating compartment.
Description
MULTI-AXIS PASSENGER-CARRYING AIRCRAFT
TECHNICAL FIELD
The present disclosure pertains to the field of aircrafts, especially a multi-axis
passenger-carrying aircraft.
BACKGROUND
The applications of multi-axis passenger-carrying aircraft are growing
nowadays because of its good maneuverability and mobility. During a flight, a
passenger is seated inside the passenger accommodating compartment of the
aircraft. However, a multi-axis passenger-carrying aircraft in the prior art cannot
provide cool air or warm air to the passenger accommodating compartment. The
temperature in the passenger accommodating compartment can be too warm
during summer and too cold during winter, greatly affect the comfort of the
passenger.
SUMMARY
In one aspect of the present disclosure, a multi-axis passenger-carrying
aircraft is provided, which is able to provide cool air or warm air to the passenger
accommodating compartment, enhancing comfort of the passenger.
Therefore, in this aspect of the disclosure, the following technical solutions
are disclosed.
A multi-axis passenger-carrying aircraft is provided, comprising: a heat
exchange system; a cabin; and a passenger accommodating compartment arranged
inside the cabin; wherein the electrical system is arranged inside the passenger
accommodating compartment, and wherein the heat exchange system at least
comprises an air inlet in communication with the exterior of the cabin, an air outlet
in communication with the passenger accommodating compartment, and a cooling
and heating device with an air inlet end communicated with the air inlet and an air
outlet end communicated with the air outlet.
In operation, air outside the aircraft may enter the heat exchange system via
the air inlet and the cooling and heating device via the air inlet end to be cooled or
heated by the cooling and heating device as desired. The air after heat exchange
may be discharged via the air outlet end and enter the passenger accommodating
compartment via the air outlet, providing cool air or warm air to the passenger
accommodating compartment, allowing more comfort for the passenger(s) in the
passenger accommodating compartment.
The technical solution will be further described below.
In addition to the above, the cooling and heating device may be provided with
a heat exchange air duct formed by a plurality of semiconductor chilling plates
arranged in a circle, with the air inlet end and the air outlet end both
communicated with the heat exchange air duct. The cooling and heating device
may perform heating or cooling with the semiconductor chilling plates, without
the need for a compressor or coolant, which is safe and environmental friendly,
providing higher safety factor of the aircraft. Meanwhile, it is small in volume and
light in weight, allowing lighter total weight of the aircraft. In addition, there is no
sliding component and thus high reliability and low noise, further promoting the
comfort during the ride.
Furthermore, the heat exchange system may further comprise a circulating
pipeline and a water row and a water pump provided in the circulating pipeline.
The cooling and heating device may be provided with a containing cavity for
placing the chilling plates and a water inlet and a water outlet communicated with
the containing cavity. The circulating pipeline may be communicated with the
water inlet at one end and with the water outlet at the other end. The
semiconductor chilling plates emit large amounts of heat during operation, which
may be dissipated via the water row, allowing good heat dissipation effects and
longer service life of the semiconductor chilling plates.
Furthermore, the multi-axis passenger-carrying aircraft may comprise an
accommodating compartment inside the cabin, wherein an electrical system is
provided inside the accommodating compartment, the heat exchange system is
provided with a heat dissipating vent communicated with the accommodating
compartment, and wherein the heat dissipating vent is communicated with the air
outlet end. During a flight, the electrical system powers each electric unit of the
aircraft, which generates large amounts of heat. The outside air is cooled and then
enters the heat dissipating vent via the air outlet end, providing cool air to the
accommodating compartment to dissipate heat from the electrical system. In this
way, it allows more stable operation of the electrical system and higher safety
factor of the aircraft to ensure its safety.
Furthermore, the heat exchange system further comprises a heat dissipating
duct and a first valve provided in the heat dissipating duct and wherein the heat
dissipating duct is communicated with the air outlet end at one end and with the
heat dissipating vent at the other end. The first valve is opened or closed to control
the opening or closing of the heat dissipating duct, according to the heat emitting
status of the electrical system, and thus the energy consumption is reduced.
Furthermore, the multi-axis passenger-carrying aircraft may further comprise
a temperature sensor provided inside the passenger accommodating compartment
and a controller electrically connected to the temperature sensor and electrically
connected to the first valve. The temperature sensor detects the temperature inside
the passenger accommodating compartment and then sends the data collected to
the controller. The controller regulates the temperature inside the passenger
accommodating compartment by controlling the opening and closing of the first
valve, resulting in smart regulation.
Furthermore, the heat exchange system may further comprise a return air inlet
communicated with the passenger accommodating compartment and with the heat
dissipating vent. The remaining cool air in the passenger accommodating
compartment is recovered by the return air inlet and provided to the
accommodating compartment via the heat dissipating vent to dissipate heat from
the electrical system. Therefore, it allows making best use of the cool air and
energy saving of the aircraft.
Furthermore, the return air inlet may be provided with a first centrifugal fan.
The remaining cooled air is sent to the heat dissipating vent by the first centrifugal
fan to allow smoother flow of air.
Furthermore, the heat exchange system may further comprise an air outlet
duct and a second valve provided in the air outlet duct, the air outlet duct being
communicated with the air outlet end at one end and with the air outlet at the other
end. The second valve is opened or closed to control the opening or closing of the
air outlet duct, according to the temperature inside the passenger accommodating
compartment, and thus the energy consumption is reduced.
Furthermore, a second centrifugal fan may be provided at the air inlet. The air
outside may be sent to the air outlet by the second centrifugal fan to allow smooth
air flow.
In comparison with prior art, the disclosure as disclosed in the present
application provides the following benefits.
In operation, air outside the aircraft may enter the heat exchange system via
the air inlet and the cooling and heating device via the air inlet end to be cooled or
heated by the cooling and heating device as desired, allowing more comfort for the
passenger(s) in the passenger accommodating compartment.
BRIEF DESCRIPTION OF DRAWINGS
Figure 1 shows a structural schematic of the multi-axis passenger-carrying
aircraft according to one embodiment of the present disclosure.
Description of the reference signs:
. air inlet
110. air duct
. air outlet
. cooling and heating device
310. air inlet end
320. air outlet end
330. water inlet
340. water outlet
410. circulating pipeline
420. water row
430. water pump
50. air outlet duct
60. heat dissipating vent
70. heat dissipating duct
80. return air inlet
810. passenger accommodating compartment adapting piece
910. first centrifugal fan
920. second centrifugal fan
80. Air duct
DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS
Examples for the purpose of illustrating the embodiments of the present
disclosure only will be described in details with reference to the drawings.
As shown in Figure 1, a multi-axis passenger-carrying aircraft is provided,
comprising: a heat exchange system; a cabin (not labeled in the figure); a
passenger accommodating compartment (not labeled in the figure) arranged inside
the cabin; wherein the electrical system is arranged inside the passenger
accommodating compartment, and wherein the heat exchange system at least
comprises an air inlet 10 in communication with the exterior of the cabin, an air
outlet 20 in communication with the passenger accommodating compartment, and
a cooling and heating device 30 with an air inlet end 310 communicated with the
air inlet 10 and an air outlet end 320 communicated with the air outlet 20.
In operation, air outside the aircraft may enter the heat exchange system via
the air inlet 10 and the cooling and heating device 30 via the air inlet end 310 to be
cooled or heated by the cooling and heating device 30 as desired. The air after heat
exchange may be discharged via the air outlet end 320 and enter the passenger
accommodating compartment via the air outlet 20, providing cool air or warm air
to the passenger accommodating compartment, allowing more comfort for the
passenger(s) in the passenger accommodating compartment.
In this embodiment, the cooling and heating device 30 may be provided with
a heat exchange air duct (not labeled in the figure) formed by a plurality of
semiconductor chilling plates arranged in a circle (not labeled in the figure), with
the air inlet end 310 and the air outlet end 320 both communicated with the heat
exchange air duct. The cooling and heating device 30 may perform heating or
cooling with the semiconductor chilling plates, without the need for a compressor
or coolant, which is safe and environmental friendly, providing higher safety
factor of the aircraft. Meanwhile, it is small in volume and light in weight,
allowing lighter total weight of the aircraft. In addition, there is no sliding
component and thus high reliability and low noise, further promoting the comfort
during the ride. Other heat exchange forms may be adopted by the cooling and
heating device 30 as desired in practice.
As shown in Figure 1, the heat exchange system may further comprise a
circulating pipeline 410 and a water row 420 and a water pump 430 provided in
the circulating pipeline 410. The cooling and heating device 30 may be provided
with a containing cavity (not labeled in the figure) for placing the chilling plates
and a water inlet 330 and a water outlet 340 communicated with the containing
cavity. The circulating pipeline 410 may be communicated with the water inlet 330
at one end and with the water outlet 340 at the other end. The semiconductor
chilling plates emit large amounts of heat during operation, which may be
dissipated via the water row 420, allowing good heat dissipation effects and longer
service life of the semiconductor chilling plates.
The heat exchange system may further comprise an air outlet duct 50 and a
second valve (not labeled in the figure) provided in the air outlet duct 50, the air
outlet duct 50 being communicated with the air outlet end 320 at one end and with
the air outlet 20 at the other end. The second valve is opened or closed to control
the opening or closing of the air outlet duct 50, according to the temperature inside
the passenger accommodating compartment, and thus the energy consumption is
reduced.
As shown in Figure 1, the multi-axis passenger-carrying aircraft may
comprise an accommodating compartment (not labeled in the figure) inside the
cabin, wherein an electrical system is provided inside the accommodating
compartment, the heat exchange system is provided with a heat dissipating vent 60
communicated with the accommodating compartment, and wherein the heat
dissipating vent 60 is communicated with the air outlet end 320. During a flight,
the electrical system powers each electric unit of the aircraft, which generates
large amounts of heat. The outside air is cooled and then enters the heat dissipating
vent 60 via the air outlet end 320, providing cool air to the accommodating
compartment to dissipate heat from the electrical system. In this way, it allows
more stable operation of the electrical system and higher safety factor of the
aircraft to ensure its safety.
As shown in Figure 1, the heat exchange system further comprises a heat
dissipating duct 70 and a first valve provided in the heat dissipating duct 70 and
wherein the heat dissipating duct 70 is communicated with the air outlet end 320 at
one end and with the heat dissipating vent 60 at the other end. The first valve (not
labeled in the figure) is opened or closed to control the opening or closing of the
heat dissipating duct 70, according to the heat emitting status of the electrical
system, and thus the energy consumption is reduced.
In this embodiment, the cooling and heating device 30 is communicated with
a three-way pipe at its air outlet end 320, one outlet of the three-way pipe
communicated with the air outlet end 320, one outlet serving as an air outlet duct,
and the third outlet serving as heat dissipating duct 70.
As shown in Figure 1, the heat exchange system may further comprise a
return air inlet 80 communicated with the passenger accommodating compartment
and with the heat dissipating vent 60. The remaining cool air in the passenger
accommodating compartment is recovered by the return air inlet 80 and provided
to the accommodating compartment via the heat dissipating vent 60 to dissipate
heat from the electrical system. Therefore, it allows making best use of the cool air
and energy saving of the aircraft.
As shown in Figure 1, the return air inlet 80 may be communicated with the
heat exchange duct via a passenger accommodating compartment adapting piece
810. The return air inlet 80 may be provided with a first centrifugal fan 910. The
remaining cooled air is sent to the heat dissipating vent 60 via the air outlet end
320 by the first centrifugal fan 910 to allow smoother flow of air.
In this embodiment, the multi-axis passenger-carrying aircraft is provided
with two air inlets 10, and a second centrifugal fan 920 is provided at the air inlet
.The air outlet duct 50 is communicated with two air outlets 20. The heat
exchange duct is provided with two heat dissipating vents 60 and two return air
inlets 80. The cabin is provided with the second centrifugal fan 920 in the roof, the
cooling and heating device 30 in the lateral plate, and the passenger
accommodating compartment in the floor. The air sucked in may be sent to the
cooling and heating device 30 by the second centrifugal fan 920 via an air duct
110 and then to the passenger accommodating compartment and the
accommodating compartment via the three-way pipe of the air outlet end 320. The
second centrifugal fan 920, the cooling and heating device 30, and the passenger
accommodating compartment may be located anywhere else inside the cabin as
desired in practice. The numbers of the air inlet 10, the air outlet 20, the heat
dissipating vent 60, and the return air inlet 80 may be more than one, as desired in
practice.
The multi-axis passenger-carrying aircraft may further comprise a
temperature sensor (not labeled in the figure) provided within the passenger
accommodating compartment and the accommodating compartment and a
controller (not labeled in the figure) electrically connected to the temperature
sensor. The first valve in the heat dissipating duct 70, the second valve in the air
outlet duct 50, and the cooling and heating device 30 are all electrically connected
to the controller. The temperature sensor inside the passenger accommodating
compartment detects the temperature within the passenger accommodating
compartment and sends the detected temperature to the controller. The controller
controls the cooling and heating device 30 to perform cooling or heating according
to the information received, and regulates the temperature inside the passenger
accommodating compartment by opening or closing the second valve. The
temperature sensor inside the accommodating compartment detects the
temperature within the accommodating compartment and then sends the data
collected to the controller. The controller regulates the temperature inside the
accommodating compartment by controlling the opening and closing of the first
valve, resulting in smart regulation.
The technical features in the embodiments above may be implemented in any
combination. For the purpose of simplicity, not all combinations are described
herein. However, such combination should all be considered within the scope of
the present disclosure provide that there is no contradiction.
The detailed embodiments described herein are only for the purpose of
illustrating the present disclosure, and are not intended to limit the scope of the
present disclosure in any way. It would be understand by a person skilled in the art
that various changes and modifications can be made to the embodiments described
herein without departing from the scope and spirit of the present disclosure. Such
changes and modifications are contemplated by the present disclosure, the scope
of which should only be defined by the following claims.
Claims (8)
1. A multi-axis passenger-carrying aircraft, characterized in that it comprises: a heat exchange system; a cabin; and a passenger accommodating compartment arranged inside the cabin; wherein the heat exchange system at least comprises: an air inlet in communication with an exterior of the cabin, an air outlet in communication with the passenger accommodating compartment, a cooling and heating device, provided with an air inlet end communicated with the air inlet, an air outlet end communicated with the air outlet, and a heat exchange air duct formed by a plurality of semiconductor chilling plates arranged in a circle, in communication with both the air inlet end and the air outlet end; and a circulating pipeline, in which a water row and a water pump are provided; wherein the cooling and heating device is provided with a containing cavity for placing the chilling plates and a water inlet and a water outlet communicated with the containing cavity, and the circulating pipeline is communicated with the water inlet at one end and with the water outlet at the other end.
2. The multi-axis passenger-carrying aircraft according to Claim 1, characterized in that it further comprises an accommodating compartment inside the cabin, wherein an electrical system is provided inside the accommodating compartment, the heat exchange system is provided with a heat dissipating vent communicated with the accommodating compartment, and wherein the heat dissipating vent is communicated with the air outlet end.
3. The multi-axis passenger-carrying aircraft according to Claim 2, characterized in that the heat exchange system further comprises a heat dissipating duct and a first valve provided in the heat dissipating duct, wherein the heat dissipating duct is communicated with the air outlet end at one end and with the heat dissipating vent at the other end.
4. The multi-axis passenger-carrying aircraft according to Claim 3, characterized in that it further comprises a temperature sensor provided within the passenger accommodating compartment and a controller electrically connected to the temperature sensor and electrically connected to the first valve.
5. The multi-axis passenger-carrying aircraft according to Claim 2, characterized in that the heat exchange system further comprises a return air inlet communicated with the passenger accommodating compartment and with the heat dissipating vent.
6. The multi-axis passenger-carrying aircraft according to Claim 7, characterized in that the return air inlet is provided with a first centrifugal fan.
7. The multi-axis passenger-carrying aircraft according to Claim 1, characterized in that the heat exchange system further comprises an air outlet duct and a second valve provided in the air outlet duct, the air outlet duct being communicated with the air outlet end at one end and with the air outlet at the other end.
8. The multi-axis passenger-carrying aircraft according to any one of Claims 1-9, characterized in that a second centrifugal fan is provided at the air inlet.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201521110856.0 | 2015-12-25 |
Publications (1)
Publication Number | Publication Date |
---|---|
NZ716755B true NZ716755B (en) | 2017-03-24 |
Family
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