High-performance cold gas attitude control engine system based on turbine exhaust pipe heat exchanger

Abstract

The present invention relates to a high-performance cold gas attitude control engine system based on a turbine exhaust pipe heat exchanger. The system includes a cold gas attitude control engine provided with a cold gas pipeline and a turbine exhaust pipe heat exchanger. The turbine exhaust pipe heat exchanger heats the cold gas in the cold gas pipeline of the cold gas attitude control engine and discharges it from the nozzle to generate thrust. The beneficial effects are as follows: This system meets the requirements of non-toxic, easy to maintain and store, and reusable for reusable launch vehicles; by heating the high-pressure cold gas, the nozzle specific impulse can be increased, enabling the attitude control engine to have a high specific impulse performance, and it can be applied to large-impulse and large-thrust attitude control; the working medium generated in the gas generator is used to heat the high-pressure cold gas, eliminating the need for additional heating equipment, saving space and reducing the total system mass.

Description

Technical Field

[0001] The present invention relates to the technical field of cold gas attitude control engines in the field of aerospace propulsion technology, and particularly relates to a high-performance cold gas attitude control engine system based on a turbine exhaust pipe heat exchanger. Background Art

[0002] An attitude control engine is an auxiliary power device of a space launch vehicle, which has characteristics such as multiple starts, long-pulse steady-state operation, and short-pulse transient operation. Usually, an attitude control engine needs to be installed to provide a roll-direction control torque. The cost of traditional single-use rockets is high, and it has gradually become unable to meet the needs of large-scale and low-cost launches in commercial aerospace. Reusability has become the key development direction of current launch vehicles. This requires that the reusable attitude control engine is non-toxic, safe and reliable, easy to maintain, and suitable for long-term storage. Currently, only cold gas engines meet the requirements. Therefore, for the reusability of rockets and the payload into orbit, the attitude control engine needs to adopt a cold gas scheme and have high performance. For example, the specific impulse performance of cold gas engines needs to be improved urgently.

[0003] A turbine exhaust pipe heat exchanger uses a turbine to pressurize and heat the gas passing through it. The heated gas enters the heat exchange chamber to exchange heat with the structure that needs heat exchange. If the structure that needs heat exchange is the cold gas pipeline of a cold gas engine, it will undoubtedly increase the temperature of the propellant of the cold gas engine, thereby increasing the specific impulse of the cold gas engine. Summary of the Invention

[0004] Aiming at the current reusability of rockets and the payload into orbit, the present invention requires the attitude control engine to adopt a cold gas scheme to solve the problem that the specific impulse performance of cold gas engines needs to be improved urgently.

[0005] To achieve the above object, the present invention provides a high-performance cold gas attitude control engine system based on a turbine exhaust pipe heat exchanger, including a cold gas attitude control engine provided with a cold gas pipeline and a turbine exhaust pipe heat exchanger. The turbine exhaust pipe heat exchanger heats the cold gas in the cold gas pipeline of the cold gas attitude control engine and discharges it from the nozzle to generate thrust.

[0006] Further, the turbine exhaust pipe heat exchanger sequentially includes a turbine intake pipe, a pressurizing and heating turbine (turbine shaft and turbine disk), a heat exchange chamber, and a turbine exhaust pipe (a Laval nozzle, and its nozzle outlet is the hot gas outlet) along the gas flow direction, forming an integral structure in sequence. The cold gas pipeline passes through the heat exchange chamber, and the cold gas is heated by the cold gas pipeline passing through the heat exchange chamber.

[0007] Specifically, the cold gas attitude control engine further includes a charging and discharging hand valve arranged on the cold gas pipeline along the gas flow direction, a cold gas cylinder group composed of multiple cold gas cylinders connected in parallel, a main path solenoid valve, a pressure reducing valve, multiple branch path solenoid valves, and corresponding multiple groups of nozzles.

[0008] Specifically, there are two of the multiple branch solenoid valves, and correspondingly, there are two branch paths.

[0009] Preferably, the cold gas cylinder group includes four cylinders connected in parallel.

[0010] Preferably, a filter is further provided on the cold gas pipeline between the cold gas cylinder group and the main path solenoid valve.

[0011] Preferably, the heated cold gas pipeline is the cold gas pipeline on the branch path.

[0012] The high-performance cold gas attitude control engine system based on the turbine exhaust pipe heat exchanger proposed by the present invention has the following beneficial effects:

[0013] (1) This system meets the requirements of non-toxic, easy to maintain and store, and reusable for reusable launch vehicles.

[0014] (2) By heating the high-pressure cold gas, the nozzle specific impulse can be increased, enabling the attitude control engine to have a high specific impulse performance, and it can be applied to large-impulse and large-thrust attitude control.

[0015] (3) Using the working medium generated in the gas generator to heat the high-pressure cold gas, there is no need to additionally increase heating equipment, saving space and reducing the total system mass. Description of the Drawings

[0016] Figure 1 It is a schematic structural diagram of the high-performance cold gas attitude control engine system based on the turbine exhaust pipe heat exchanger of the present invention.

[0017] Wherein: 1 - turbine exhaust pipe heat exchanger, 11 - turbine intake pipe, 12 - supercharging and heating turbine, 121 - turbine shaft, 122 - turbine disk, 13 - heat exchange chamber, 14 - turbine exhaust pipe, 2 - cold gas attitude control engine, 21 - cold gas pipeline, 211 - serpentine pipe, 22 - charging and discharging hand valve, 23 - cold gas cylinder, 24 - main path solenoid valve, 25 - pressure reducing valve, 26 - branch path solenoid valve, 27 - cold gas nozzle, 28 - filter. Detailed Embodiments

[0018] The following further describes the present invention in combination with specific embodiments.

[0019] It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0020] It should be noted that in the description of the present invention, the orientation or positional relationship indicated by terms such as "lateral", "longitudinal", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be construed as a limitation to the present invention.

[0021] The present invention provides a high-performance cold gas attitude control engine system based on a turbine exhaust pipe heat exchanger, which includes a cold gas attitude control engine provided with a cold gas pipeline and a turbine exhaust pipe heat exchanger. The turbine exhaust pipe heat exchanger heats the cold gas in the cold gas pipeline of the cold gas attitude control engine and discharges it from the nozzle to generate thrust.

[0022] The turbine exhaust pipe heat exchanger sequentially includes a turbine intake pipe, a supercharging and heating turbine (including a turbine shaft and a turbine disk), a heat exchange chamber, and a turbine exhaust pipe (a Laval nozzle, and its nozzle outlet is the hot gas outlet) along the gas flow direction, and forms an integral structure in sequence. The cold gas pipeline passes through the heat exchange chamber, and the cold gas in the cold gas pipeline passing through the heat exchange chamber is heated. The heat exchange chamber is a hollow circular tubular chamber, and the heated cold gas pipeline is the cold gas pipeline on the branch road. The turbine shaft and the turbine disk are arranged in a closed turbine intake housing, and the turbine intake pipe, the supercharging and heating turbine arranged in the closed turbine intake housing, the heat exchange chamber, and the turbine exhaust pipe form a connected gas flow space.

[0023] The gas entering the turbine intake pipe is the gas generated by the reaction of the gas generator on the rocket.

[0024] The heat exchange chamber is a hollow circular tubular chamber. The gas in the heat exchange chamber performs heat exchange with the cold gas pipeline that needs heat exchange, and the cold gas in the cold gas pipeline is heated. After the cold gas passes through the exhaust pipe heat exchanger, the gas energy increases and the specific impulse of the cold gas attitude control engine is improved.

[0025] The turbine exhaust pipe is a Laval nozzle, and its outlet is the hot gas outlet.

[0026] Specifically, the cold gas attitude control engine further includes a charging and discharging hand valve arranged on the cold gas pipeline along the gas flow direction, a cold gas cylinder group formed by connecting multiple cold gas cylinders in parallel, a main road solenoid valve, a pressure reducing valve, two branch road solenoid valves, and corresponding multiple groups of nozzles. A pressure reducing valve is provided to ensure the stability of the pressure in front of the nozzle. One solenoid valve controls two nozzles to generate a roll direction attitude control torque (reducing the number of solenoid valves and ensuring the engine startup synchronization).

[0027] The two branch road solenoid valves are provided, and the corresponding branch roads are two.

[0028] The cold gas cylinder group includes four cylinders connected in parallel. The parallel cylinder group is convenient for installation and has a low cost compared with a single cylinder.

[0029] A filter is also provided on the cold gas pipeline between the cold gas cylinder group and the main path solenoid valve. The filter is provided at the cylinder outlet to ensure the normal operation of the pressure reducing valve and the solenoid valve. Otherwise, impurities will cause the valve to jam.

[0030] The heated cold gas pipeline is the cold gas pipeline on the branch path, such as Figure 1 the serpentine pipeline shown in

[0031] The turbine exhaust gas heat exchanger and the cold gas attitude control engine are integrally or separately designed and processed.

[0032] The separate design and processing is to process the three parts of the system: the pressurized and heated gas end (including components such as the turbine intake pipeline, the pressurized and heated turbine, and the turbine intake housing), the heat exchanger (including the heat exchange chamber, the heat exchange pipeline, i.e., the cold gas pipeline, the turbine exhaust pipe, etc.), and the cold gas engine. Then, the above three parts are processed separately and connected through flanges.

Claims

1. A high-performance cold gas attitude control engine system based on a turbine exhaust pipe heat exchanger, characterized in that, It includes a cold gas attitude control engine with a cold gas pipeline and a turbine exhaust pipe heat exchanger. The turbine exhaust pipe heat exchanger heats the cold gas in the cold gas pipeline of the cold gas attitude control engine and discharges it from the nozzle to generate thrust. The turbine exhaust pipe heat exchanger successively includes a turbine intake pipe, a supercharging and heating turbine, a heat exchange chamber, and a turbine exhaust pipe along the gas flow direction, forming an integral structure in sequence. The cold gas pipeline passes through the heat exchange chamber, and the cold gas is heated by passing through the cold gas pipeline in the heat exchange chamber. It also includes a gas generator on the rocket, and the gas entering the turbine intake pipe is the gas generated by the reaction of the gas generator on the rocket.

2. The high-performance cold gas attitude control engine system based on a turbine exhaust pipe heat exchanger according to claim 1, wherein The cold gas attitude control engine further includes a charging and discharging hand valve arranged on the cold gas pipeline along the gas flow direction, a cold gas cylinder group composed of multiple cold gas cylinders in parallel, a main road solenoid valve, a pressure reducing valve, multiple branch road solenoid valves, and corresponding multiple groups of nozzles.

3. The high-performance cold gas attitude control engine system based on a turbine exhaust pipe heat exchanger according to claim 2, wherein, The multiple branch road solenoid valves are two, and the corresponding branch roads are two.

4. The high-performance cold gas attitude control engine system based on a turbine exhaust pipe heat exchanger according to claim 2 or 3, characterized in that, The cold gas cylinder group includes four cylinders in parallel.

5. The high-performance cold gas attitude control engine system based on a turbine exhaust pipe heat exchanger according to claim 2 or 3, characterized in that, A filter is also arranged on the cold gas pipeline between the cold gas cylinder group and the main road solenoid valve.

6. The high-performance cold gas attitude control engine system based on a turbine exhaust pipe heat exchanger according to claim 4, wherein A filter is also arranged on the cold gas pipeline between the cold gas cylinder group and the main road solenoid valve.

7. The high-performance cold gas attitude control engine system based on a turbine exhaust pipe heat exchanger according to any one of claims 1-3, characterized in that The heated cold gas pipeline is the cold gas pipeline on the branch road.

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