Field of Invention:
The present invention relates to the measurement of outside
temperature of aircraft.
Background of Invention:
The modem Aircrafts which can fly upto 0.9 Mach requires very
accurate measurements to calculate air data parameters using
Air Data Computer. During various flight operating conditions
the probability of water or ice accumulation shall increase and
lead to inaccurate values of the measured temperature. To
overcome the temperature error, the Aircraft structure shall
provide an inertial separator to avoid Ice accumulation on the tip
of temperature sensor.
3.1 Prior Art
US10151641
A total air temperature probe includes a probe head having
an airflow inlet, a main airflow outlet, a main probe head wall
extending from the airflow inlet to the main airflow outlet and
a flow separation bend wall positioned between the airflow
inlet and the main airflow outlet. The flow separation bend
wall is opposite the main probe head wall across a primary
flow passage defined through the probe head from the airflow
inlet to the main airflow outlet. A flow separation trip feature
is defined on an interior surface of the main probe head wall
for tripping a boundary layer flow separation in flow in the primary flow passage, e.g., for reduction of deicing heater
error. The scope of the invention limits to the flow control.
CA2927639C
The anti-icing device comprises a heating element thermally
insulated from the probe body by a thermal insulator and a
hydrophobic coating covering the heating element and
defining an outer surface for exposure to an airflow. The
heating element any be deposited using a direct write
process. The scope of the invention limits to the Coatings,
thermal insulation and bonding.
4. Brief summary of Invention
A total air temperature probe (TATP) with DC heater on the
aircraft includes a probe body having an Aerofoil structure with
air inlet for sensing the outside temperature and an air vent slot.
The size, shape 8; location of air vent] slot is determined based on
air load calculations.
The structure is designed with aerofoil shape to withstand severe
vibration levels and air load dun'rig aircraft manoeuvre. It is
contemplated that an inertial separator of 1mm thick is provided
at the leading edge of the structure. It provides air flow
separation from the leading edge and substantially avoids any
damage due to direct hit of air mass on temperature sensor tip.
It also helps to separate the dust/water particles and to prevent
Ice accumulation on the tip of temperature sensor.
It is also contemplated that the ’Aerofoil structure also embodies
the temperature sensor and a DC heater with positive fixing
using M2 screws. Both the temperature sensor and DC heater are physically isolated from each other to avoid any heating
effect on temperature measurement.
5. Brief description of drawings
5 Figure: 1 shows the TATP containing,
1-> TATP
2 ->Probe body with Aerofoil structure
3 ->Aerofoil shape
4 ->Inertial separator
10 5->Temperature sensor tip
6—>Mounting flange
7-> Electrical Connector
Figure: 2 shows the exploded view of TATP (1) that explains
about the assembly of Probe body(2) with other parts viz,
8 ->Temperature sensor
9 ->DC heater
10 ->Metric M2 screws
11 ->Connector housing
12 ->Connector EMI Gasket
20 Figure: 3 shows the Cross sectional View of TATP (1) containing,
13-> Air flow
14 —>Air inlet
15 ->Air vent slot
6. Detailed Description of Invention
In the following detailed description, reference is made to the
accompanying drawings, which form a part hereof, is shown by
way of illustration specific embodiments in which the inventions.
are practiced. The following detailed description is therefore, not to be taken in a limiting sense, and the scope of the present
invention is defined only by the claims and equivalents thereof.
Figure 1 is a diagrammatic illustration of the total air
temperature probe (TATP) (1) includes a probe body with Aerofoil
structure (2) with Aerofoil shape (3) to withstand severe vibration
levels and airload during aircraft manoeuvers. An 'Inertial
Separator (4) is designed with 1.5mm thickness to separate air
flow from leading edge of TATP (l) and substantially avoids any
damage to the Temperature Sensor Tip (5) due to direct hit of air
mass. A Mounting Flange (6) with 6 fixing holes of’ 3.3mm
diameter are equispaced at 60° provides a base to install the
TATP (1) on any aircraft. A 6 pin Electrical Connector (7) is
provided for communicating the measured temperature to the
other aircraft electronic units.
Figure .2 shows the exploded view of TATP (1) with internal
assembly details of the temperature sensor (8) of size 45mm (L) x
4mm (Dia.) and comprises of Platinum wire of 500 ohms with 3
wire configuration, Also shown a DC Heater (9) of size 40mm (L)
6mm (Dia.) that works on 28V DC power supply with a low
power consumption of 35 watts with 2 wire configuration. Both
the temperature sensor (8) 85 DC Heater (9) are positively fixed to
the Aerofoil structure (2) using four Metric M2 screws (10). The
free end wires of temperature sensor (8) 8t. DC Heater (9) are
soldered to the Electrical Connector (7). A Connector EMI Gasket
(12) is placed in between the Electrical Connector (7) 85
Connector Housing (11) for radiated emission protection.
Figure 3 shows the cross sectional view of the TATP (2). Air‘
Flow (13) passes over the temperature sensor (8) and enters the
Air-inlet (14) and exits through the air vent (15) thus helps to
sense the air temperature outside the aircraft.
7.CLAIMS
We claim,
1. Total Air Temperature Probe(TATP) with DC Heater for aircraft with
an Aerofoil Structure provides outside temperature of the Aircraft
comprises:
a DC Heater (9) of size 40mm (L) x 6mm (Dia.) that works on
28V DC power supply with a power consumption of 35 watts
with 2 wire configuration.
a Temperature Sensor (8) of size 45mm (L) x 4mm (Dia.)
compfises of Platinum Wire of 500 ohms with 3 wire
configuration.
2. TATP in accordance with claim 1 has positive fixing of temperature
sensor and DC heater using Metric M2 screws in a Aerofoil structure.