Heatproof device for leading edge of rudder (wing) of hypersonic aircraft

Abstract

The invention provides a thermal protection device for the leading edge of a rudder (wing) of a hypersonic aircraft, belongs to the field of aerospace hypersonic aircrafts, and relates to a quartz / phenolic aldehyde composite material process and a carbon / phenolic aldehyde composite material process. Comprising a high-temperature-resistant carbon / ceramic front edge, a carbon / phenolic aldehyde connecting piece, a quartz / phenolic aldehyde heat-proof layer and a metal bearing structure. The high-temperature-resistant rudder (wing) front edge (1), the carbon / phenolic aldehyde high-temperature-resistant heat-insulation connecting piece (2), the quartz / phenolic aldehyde rudder (wing) surface heat-proof layer (3) and the rudder (wing) metal bearing structure (4) are arranged from top to bottom. Wherein the carbon / phenolic aldehyde high-temperature-resistant heat-insulating connecting piece (2) and the quartz / phenolic aldehyde rudder (wing) surface heat-proof layer (3) are connected together in a weaving manner when the prefabricated body is woven, so that the integrity of the structure is enhanced. The invention provides a low-cost hypersonic aircraft rudder (wing) front edge heat-proof device in a mode of combining a high-temperature-resistant front edge with an ablation rudder (wing) surface heat-proof layer, and the temperature-resistant grade of the front edge can be 2500 DEG C or above.

Description

Technical Field

[0001] The invention belongs to the field of aerospace hypersonic aircraft. Background Art

[0002] In recent years, with the intensification of local tensions and the development of weapons and equipment, the offensive and defensive situation between the enemy and us has undergone subtle changes following the continuous innovation of high-precision weapons. Among them, traditional ballistic missiles have high flight speeds, but poor maneuverability, and the ballistic flight trajectory is easy to predict. With the development of mid-course anti-missile weapons, the penetration capability has gradually weakened; cruise missiles have low flight speeds and are easily intercepted by air defense weapons. In this situation, hypersonic weapons that fly throughout the atmosphere have a huge advantage in penetration capability. Their flight altitude is low, generally below 60km in airspace, and they are difficult to be captured by radar at long distances. They have high flight speeds and are difficult to track with air defense weapons. Their control wing surfaces can provide them with maneuverability throughout the atmosphere, greatly improving their penetration performance. However, the development of hypersonic aircraft also has huge challenges. Due to long-term flight at high Mach numbers in the atmosphere, their surface temperature and heating amount increase exponentially compared to traditional weapons. In particular, the nose cone and rudder (wing) leading edge are under extreme heat loads, and it is necessary to take into account both the high surface temperature and long-term thermal insulation issues. Traditional rudders (wings) generally use ablative heat protection layers and metal bearing structures, or high-temperature resistant leading edges installed on the bearing structure, or high-temperature heat protection and bearing integrated rudder (wing) structures. Among them, the single ablative heat protection layer can no longer withstand the long-term high heat flux heating environment at the leading edge; the high-temperature resistant leading edge is directly installed on the bearing structure, and the high thermal conductivity of the high-temperature resistant material makes it difficult for the bearing structure to withstand the heat conduction effect of long-term flight; the high-temperature heat protection and bearing integrated rudder (wing) also has difficult-to-solve high-temperature insulation problems at the installation and connection parts, and its cost is very high. The present invention utilizes the characteristic that the miniaturized leading edge structure is subjected to a small aerodynamic load, and enables it to be installed on a traditional heat protection layer, thereby solving the key technologies of load bearing and heat insulation. Summary of the invention

[0004] In view of the fact that the leading edge of the current traditional rudder (wing) cannot meet the long-term high-temperature thermal environment of hypersonic aircraft, the present invention utilizes the characteristic that the miniaturized leading edge structure is subject to a small aerodynamic load, and installs the high-temperature resistant leading edge strip on the traditional heat protection layer, thereby solving the key technologies of load-bearing and heat insulation.

[0005] The technical solution of the present invention is as follows: a miniaturized high-temperature resistant and anti-oxidation leading edge strip is embedded in a traditional rudder (wing) surface heat protection layer; the high-temperature area where the heat protection layer contacts the leading edge strip is woven with carbon fiber; and then the quartz braid of the rest of the heat protection layer is connected together by adding yarn and reducing yarn; the entire fabric is formed by RTM on a metal bearing structure; during use, the carbon / phenolic and quartz / phenolic still have some load-bearing capacity after high-temperature carbonization, which can ensure the connection stability of the small leading edge strip and play a dual role of heat insulation and load-bearing.

[0006] The beneficial effects of the present invention are as follows: based on the traditional rudder (wing) leading edge heat protection structure, the key technology of applying the rudder (wing) leading edge heat protection structure on hypersonic aircraft is solved at a lower cost and with a simpler process; with its structural characteristics, it can also be applied to near-space aircraft or other returning aircraft in similar use environments. BRIEF DESCRIPTION OF THE DRAWINGS

[0007] Figure 1 It is a schematic diagram of a hypersonic aircraft rudder (wing) leading edge heat protection device of the present invention. DETAILED DESCRIPTION

[0008] The present invention will be further described below in conjunction with the accompanying drawings.

[0009] See attached Figure 1 The present invention provides a hypersonic aircraft rudder (wing) leading edge heat protection device, comprising a high temperature resistant rudder (wing) leading edge [1], a carbon / phenolic high temperature resistant heat insulating connector [2], a quartz / phenolic rudder (wing) surface heat protection layer [3], and a rudder (wing) metal bearing structure [4]. The carbon / phenolic high temperature resistant heat insulating connector [2] and the quartz / phenolic rudder (wing) surface heat protection layer [3] are connected together by weaving when the preform is woven, thereby enhancing the integrity of the structure. The specific implementation steps are as follows: 1) According to the shape of the rudder (wing) leading edge and the thermal environment of use, select a high temperature resistant carbon / ceramic material suitable for the rudder (wing) leading edge. Generally, C / SiC is selected for temperatures below 1700°C, C / ZrC is selected for temperatures between 1700 and 2500°C, and C / HfC is selected for temperatures above 2500°C. Alternatively, a composite carbon / ceramic material may be selected according to environmental requirements. The span length of the rudder (wing) leading edge is generally not greater than the leading edge diameter. A connection structure matching the dovetail groove of the carbon / phenolic high temperature resistant heat insulating connector [2] is machined below the high temperature resistant rudder (wing) leading edge [1]. 2) The carbon / phenolic high temperature resistant heat insulating connector [2] and the quartz / phenolic rudder (wing) surface heat protection layer [3] fiber preform are mixed and woven. During the weaving process, the high temperature resistant rudder (wing) leading edge [1] is embedded into the preform fabric. The preform weaving method is generally a three-dimensional weaving method such as 2.5D, three-dimensional five-way, three-dimensional four-way, etc., to enhance the connection stability. 3) The hybrid braided preform embedded with the leading edge of the high-temperature resistant rudder (wing) [1] is wrapped on the metal bearing structure [4], and the whole is placed in an RTM mold with the same shape as the rudder (wing), and the phenolic resin required for the composite is injected, and then placed in an oven for high-temperature curing and molding.

Claims

1. A hypersonic aircraft rudder (wing) leading edge heat protection device, characterized in that include: The leading edge of the rudder (wing) is made of high-temperature resistant and anti-oxidation carbon / ceramic materials near the stationary point area. Anti-oxidation composite materials such as C / HfC, C / ZrC or C / SiC can be selected according to the temperature resistance level to ensure that it maintains a good aerodynamic shape in a long-term high-temperature environment. The span length of the leading edge structure generally does not exceed the leading edge diameter, so that a smaller mechanical load is generated during high-speed flight, so that the carbon / phenolic and quartz / phenolic have sufficient ability to ensure their connection strength after high-temperature carbonization.

2. A hypersonic aircraft rudder (wing) leading edge heat protection device, characterized in that include: The high temperature resistant leading edge of the rudder (wing) is connected to the carbon / phenolic aldehyde to fix the carbon / ceramic leading edge and to provide heat insulation, so that the temperature of the contact interface with the quartz phenolic aldehyde is not higher than the melting temperature of quartz (1650°C). The carbon fiber preform of the carbon / phenolic aldehyde and the quartz fiber preform of the quartz / phenolic aldehyde are mixed and woven to form an integral braid, which is then formed by integrated RTM.

3. A hypersonic aircraft rudder (wing) leading edge heat protection device, characterized in that include: The rudder (wing) heat protection layer plays a role in heat protection and insulation in areas with relatively low temperatures, ensuring that the load-bearing structure operates normally at the allowable temperature.

4. A hypersonic aircraft rudder (wing) leading edge heat protection device, characterized in that include: The rudder (wing) metal load-bearing structure mainly bears the aerodynamic load of the rudder (wing) during high-speed flight, and generally uses titanium alloy with high temperature resistance and high specific strength.

5. The hypersonic vehicle rudder (wing) leading edge heat protection device according to claim 1, characterized in that: At a smaller span length, it should be ensured that the ablation retreat during flight is not greater than the aerodynamic shape requirements, and generally should not be greater than 1 / 2 of the leading edge radius.

6. A hypersonic aircraft rudder (wing) leading edge heat protection device according to claim 3, characterized in that: In the area in contact with carbon / phenolic formaldehyde, the side thickness of the heat protection layer shall not be less than the ablation setback amount to prevent the oxidation of carbon / phenolic formaldehyde by aerodynamic heating.

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