A total temperature sensor for structural anti-icing in eVTOL

Abstract

The present invention provides a total temperature sensor for structural anti-icing of eVTOL, wherein the air inlet is arranged on the top surface of the total temperature sensor, with an angle of 90° with the incoming flow, and the exhaust slot is arranged on the leeward side; the air inlet and the exhaust slot are both connected to the blocking cavity; the cross section of the total temperature sensor is a rhombus and / or a symmetrical wing shape. The air inlet is prevented from facing the incoming atmospheric flow in terms of structure, which reduces the risk of ice blockage, does not require electric heating / bleed air heating, is suitable for eVTOL, and does not require additional correction of the effect of the sensor's own heating on the temperature measurement.

Description

Technical Field

[0001] The present invention is applied to the technical field of developing temperature detection sensors in general aviation equipment, and specifically relates to a total temperature sensor for structural anti-icing of eVTOL. Background Art

[0002] Under the background of the development of general aviation industry, various new general aviation equipment with technical features of unmanned, electric and intelligent are booming. The total temperature sensor is an important device of aircraft atmospheric data system. It is installed on the fuselage of aircraft to sense the local atmospheric total temperature of the fuselage. Through conversion and calculation, the static temperature, true airspeed and other related atmospheric parameters of the aircraft are obtained for avionics indication and flight control.

[0003] The total temperature sensor is installed outside the aircraft skin and experiences various weather environments during flight, among which the icing weather environment has the greatest impact on the sensor function and performance.

[0004] Traditional total temperature sensors usually use electric heating to deal with icing weather conditions in the air, but electric heating is more suitable for military aircraft and civil medium and large transport aircraft with complex flight conditions or sufficient onboard power supply. General aviation aircraft, especially electric-driven aircraft represented by eVTOL, are constrained by the development of the battery industry and often have shortcomings such as short cruising range and low load capacity. Therefore, it is particularly important to design a structural anti-icing total temperature sensor that can adapt to the characteristics of general aviation aircraft. Summary of the invention

[0005] Aiming at the situation that the onboard power supply of a general aircraft is insufficient, the present invention provides a total temperature sensor for structural anti-icing of an eVTOL.

[0006] The present invention provides a total temperature sensor for structural anti-icing of eVTOL, wherein an air inlet is arranged on the top surface of the total temperature sensor, with an angle of 90° with the incoming flow, and an exhaust slot is arranged on the leeward side; the air inlet and the exhaust slot are both connected to the blocking cavity;

[0007] The cross section of the total temperature sensor is a diamond shape and / or a symmetrical wing shape.

[0008] Optionally, when the cross-section of the total temperature sensor is a symmetrical wing shape, an anti-icing boss is also provided on the windward surface;

[0009] The cross section of the anti-icing boss is triangular.

[0010] Optionally, the windward leading edge of the anti-icing boss is serrated.

[0011] Optionally, the anti-icing boss is located in the middle of the windward surface.

[0012] Optionally, the exhaust grooves are arranged along the height direction of the total temperature sensor.

[0013] Optionally, the exhaust groove is in the shape of an elongated strip, or the exhaust groove includes a plurality of exhaust holes.

[0014] Optionally, the air inlet is arranged at the middle and rear part of the top surface of the total temperature sensor;

[0015] Exhaust slots are arranged on the leeward sides of both sides of the total temperature sensor, and the exhaust slots are located obliquely behind the air inlet.

[0016] Optionally, the total temperature sensor adopts a rod-shaped armored inner-sealed temperature-sensitive element, or a wire-wound structure temperature-sensitive element, which is arranged in the blocking cavity.

[0017] The present invention provides a total temperature sensor for structural anti-icing of eVTOL, which solves the problem that the traditional electric heating total temperature sensor has a large heating power, imposes a large load on low-altitude economic general aviation aircraft with weak onboard power supply capacity, and leads to a shortened cruising range of low-altitude economic aircraft represented by eVTOL. The total temperature sensor provided by the present invention does not require additional power supply on the basis of having an anti-icing function; the traditional active heating total temperature sensor needs to consider the influence of self-heating error, and the total temperature sensor provided by the present invention does not have an active heating function, so there is no need to additionally correct the influence of the sensor's own heating on temperature measurement; the structural anti-icing total temperature sensor provided in the present invention can be promoted and applied in general aviation aircraft and bomb products. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 The structure of the total temperature sensor is shown in Figure 2. Figure 1 ;

[0019] Figure 2 The structure of the total temperature sensor is shown in Figure 2. Figure 2 ;

[0020] Figure 3 The structure of the total temperature sensor is shown in Figure 2. Figure 3 ;

[0021] Figure 4 The structure of the total temperature sensor is shown in Figure 2. Figure 4 ;

[0022] Description of reference numerals:

[0023] 1- Air inlet;

[0024] 2- Exhaust slot;

[0025] 3- Anti-ice bosses. DETAILED DESCRIPTION

[0026] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0027] The features and illustrative embodiments of various aspects of the present invention will be described in detail below. In the detailed description below, many specific details are proposed to provide a comprehensive understanding of the present invention. However, it is obvious to those skilled in the art that the present invention can be implemented without the need for some of these specific details. The following description of the embodiments is only to provide a better understanding of the present invention by illustrating examples of the present invention. The present invention is by no means limited to any specific settings and methods proposed below, but covers any improvements, replacements and modifications of structures, methods, devices without departing from the spirit of the present invention. In the accompanying drawings and the following description, known structures and technologies are not shown to avoid unnecessary ambiguity in the present invention.

[0028] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other, and the embodiments can refer to and quote each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0029] The present invention is further described in detail below in conjunction with embodiments and drawings, but the embodiments of the present invention are not limited thereto.

[0030] like Figure 1-4 As shown, the present invention provides a total temperature sensor for structural anti-icing of eVTOL, wherein the air inlet 1 is arranged on the top surface of the total temperature sensor, with an angle of 90° with the incoming flow, and the exhaust slot 2 is arranged on the leeward side; the air inlet 1 and the exhaust slot 2 are both connected to the blocking cavity;

[0031] The cross section of the total temperature sensor is a diamond shape and / or a symmetrical wing shape.

[0032] Optionally, when the cross-section of the total temperature sensor is a symmetrical wing shape, an anti-icing boss 3 is also provided on the windward surface;

[0033] The cross section of the anti-icing boss 3 is triangular.

[0034] Optionally, the windward leading edge of the anti-icing boss 3 is serrated.

[0035] Optionally, the anti-icing boss 3 is located in the middle of the windward surface.

[0036] Optionally, the exhaust grooves are arranged along the height direction of the total temperature sensor.

[0037] Optionally, the exhaust groove is in the shape of an elongated strip, or the exhaust groove includes a plurality of exhaust holes.

[0038] Optionally, the air inlet is arranged at the middle and rear part of the top surface of the total temperature sensor;

[0039] Exhaust slots are arranged on the leeward sides of both sides of the total temperature sensor, and the exhaust slots are located obliquely behind the air inlet.

[0040] Optionally, the total temperature sensor adopts a rod-shaped armored inner-sealed temperature-sensitive element, or a wire-wound structure temperature-sensitive element, which is arranged in the blocking cavity.

[0041] The present invention takes into account that the pneumatic blocking chamber of the conventional total temperature sensor is designed to face the incoming flow, and the temperature sensing element is in direct contact with the incoming flow, which is easily contaminated by moisture and impurities in the air and affects the measurement accuracy.

[0042] The total temperature sensor solution provided by the present invention realizes the total temperature measurement function by using the negative pressure suction principle. The total temperature sensor is designed with an air inlet and an exhaust slot. When the aircraft is in normal flight, the atmospheric flow passes through the total temperature sensor and forms a negative pressure at the sensor exhaust slot, causing the pressure balance in the blocking cavity to be broken, and the clean airflow at the air inlet position is sucked into the blocking cavity. After the clean airflow entering the blocking cavity is blocked on the surface of the temperature measuring component, it is converted into an electrical signal and transmitted to the atmospheric data computer to complete the measurement of the total temperature.

[0043] The present invention takes into account that the air inlet of the traditional total temperature sensor faces the atmospheric flow. Under icing weather conditions, the total temperature air inlet is prone to blockage, which leads to the failure of the total temperature sensor function. The total temperature sensor solution provided by the present invention has an air inlet at an angle of 90° to the incoming flow, is located in the water vapor shielding area of ​​the local position of the sensor, and is far away from the windward side of the sensor, so there is no risk of ice blockage at the air inlet.

[0044] The present invention takes into account that the electric heating mode and engine bleed air mode of the existing total temperature sensor are not suitable for general aviation aircraft in the context of low-altitude economy. And the total temperature sensor without anti-icing function is difficult to cope with possible icing climate conditions. The present invention provides a total temperature sensor solution with structural anti-icing. The air inlet, blocking cavity, exhaust groove and temperature measurement component of the sensor are all in the water vapor shielding area. Under icing meteorological conditions, ice will only accumulate on the windward side of the sensor, which will not affect the total temperature measurement area of ​​the product.

[0045] The present invention takes into account that the pneumatic blocking chamber of the traditional total temperature sensor is directly facing the incoming flow. When a bird strikes, the air inlet will directly collide with the bird, resulting in failure of the total temperature measurement function. The total temperature sensor solution provided by the present invention does not cause a head-on collision between the air inlet and the bird body when a bird strikes, greatly reducing the risk of failure of the total temperature sensor.

[0046] For example, Figure 1 and Figure 2 The windward side adopts sharp edge design, the difference lies in the size of positive pressure area and negative pressure area. Figure 3 and Figure 4 The windward side adopts a blunt edge and smooth transition, but adds an anti-icing boss design. The difference lies in the leading edge of the anti-icing boss: Figure 3 Designed for sharp edges. Figure 4 Designed for a serrated structure.

[0047] The above is only a specific embodiment of the present invention, and the present invention is described in detail. The unexplained part is a conventional technology. However, the protection scope of the present invention is not limited to this. Any changes or substitutions that can be easily thought of by any technician familiar with the technical field within the technical scope disclosed by the present invention should be included in the protection scope of the present invention. The protection scope of the present invention shall be based on the protection scope of the claims.

Claims

1. A total temperature sensor for structural anti-icing of eVTOL, characterized in that: The air inlet is set on the top surface of the total temperature sensor, with an angle of 90° to the incoming flow, and the exhaust slot is set on the leeward side; the air inlet and the exhaust slot are both connected to the blocking cavity; The cross section of the total temperature sensor is a diamond shape and / or a symmetrical wing shape.

2. The total temperature sensor for structural anti-icing of eVTOL according to claim 1, characterized in that: When the cross section of the total temperature sensor is a symmetrical wing shape, an anti-icing boss is also provided on the windward surface; The cross section of the anti-icing boss is triangular.

3. The total temperature sensor for structural anti-icing of eVTOL according to claim 2, characterized in that: The windward leading edge of the anti-icing boss is serrated.

4. The total temperature sensor for structural anti-icing of eVTOL according to claim 2, characterized in that: The anti-icing boss is located in the middle of the windward side.

5. The total temperature sensor for structural anti-icing of eVTOL according to claim 1, characterized in that: The exhaust slots are arranged along the height direction of the total temperature sensor.

6. The total temperature sensor for structural anti-icing of eVTOL according to claim 5, characterized in that: The exhaust groove is in the shape of an elongated strip, or the exhaust groove includes a plurality of exhaust holes.

7. The total temperature sensor for structural anti-icing of eVTOL according to claim 1, characterized in that: The air inlet is arranged at the middle and rear part of the top surface of the total temperature sensor; Exhaust slots are arranged on the leeward sides of both sides of the total temperature sensor, and the exhaust slots are located obliquely behind the air inlet.

8. The total temperature sensor for structural anti-icing of eVTOL according to claim 1, characterized in that: The total temperature sensor adopts a rod-shaped armored inner-sealed temperature-sensitive element, or a wire-wound structure temperature-sensitive element, which is arranged in the blocking cavity.

Images