Rocket front-end attitude control power system
By designing a series layout and modular connection of the oxidizer tank, separation engine, pitch and yaw engine and fuel tank at the rocket's front end, the problem of insufficient space utilization and structural efficiency of traditional attitude control propulsion systems at the rocket's front end was solved, achieving efficient pitch and yaw control and fairing separation.
Patent Information
- Application Number
- CN202511094442.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-08-05
- Publication Date
- 2025-11-18
AI Technical Summary
Traditional attitude control propulsion systems are difficult to meet the requirements of space utilization and structural efficiency at the rocket's front end, especially when arranged inside the nose cone, making it impossible to achieve pitch and yaw control and fairing separation.
Design a rocket front-end attitude control propulsion system. Along the axis of the nose cone compartment at the top of the fairing, the oxidizer tank, separation engine, pitch and yaw engine and fuel tank are arranged sequentially. The system adopts X-shaped truss connection and modular design. By combining electric valves and connecting multiple pipelines, the engine modularization and series layout can be realized, thereby improving space utilization and structural efficiency.
It achieves pitch and yaw control of the first and second stages of rocket flight and fairing separation, improves space utilization and structural efficiency, shortens the length of liquid pipelines, reduces the impact of water hammer pressure during engine start-up and shutdown, and saves the amount of pressurized gas used.
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Figure CN120970402A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application relates to the field of aerospace technology, and particularly relates to a rocket front end attitude control power system. BACKGROUND
[0002] When a solid carrier rocket adopts a fixed nozzle engine, the pitch and yaw control of the first and second stages cannot be realized by relying on the rudder system only, and usually a fairing with a nose cone is adopted, and an attitude control power system is arranged at the front end of the rocket to provide the pitch and yaw control force of the rocket body during the first and second stage flight. When the fairing adopts a whole fairing separation scheme, the attitude control power system also needs to provide separation force.
[0003] The traditional attitude control power system is usually arranged in the control cabin, and the requirement for space utilization is not high. However, the front end attitude control power system of the rocket body is limited by the diameter and length of the nose cone cabin, and the requirement for space utilization is extremely high. Meanwhile, considering the influence on the effective load, the requirement for the structural efficiency of the front end attitude control power system of the rocket body is also high. If the traditional attitude control power system design scheme is adopted, the requirements for the structural efficiency and space utilization of the front end attitude control power system of the rocket body cannot be met. SUMMARY
[0004] The purpose of the present application is to provide a rocket front end attitude control power system, which can be arranged in the nose cone cabin to realize the pitch and yaw control of the rocket body during the first and second stage flight and the separation of the fairing, and improve the structural efficiency and space utilization of the power system.
[0005] To achieve the above object, the application provides a rocket front-end attitude control power system, comprising: an oxidant storage tank, a separation engine, a pitch-yaw engine, a fuel storage tank and a gas cylinder arranged in sequence along the axis direction of the head cone cabin at the top of the fairing; wherein the outlet of the gas cylinder is communicated with one end of a first pipeline; the other end of the first pipeline is communicated with one end of a second pipeline and one end of a third pipeline; an inflation valve, a gas pipeline electric explosion valve, a pressure reducing valve and a safety valve are sequentially arranged on the first pipeline in the direction from one end of the first pipeline to the other end of the first pipeline; one end of the second pipeline is also communicated with one end of the third pipeline; the other end of the second pipeline is communicated with the gas inlet of the oxidant storage tank; an oxidant check valve, an oxidant gas pipeline diaphragm valve and a first oxidant filling and discharge valve are sequentially arranged on the second pipeline in the direction from one end of the second pipeline to the other end of the second pipeline; the other end of the third pipeline is communicated with the gas inlet of the fuel storage tank; a fuel check valve, a fuel gas pipeline diaphragm valve and a first fuel storage tank filling and discharge valve are sequentially arranged on the third pipeline in the direction from one end of the third pipeline to the other end of the third pipeline; one end of a fourth pipeline is communicated with the first pipeline, and one end of the fourth pipeline is located between the safety valve and one end of the third pipeline; the other end of the fourth pipeline is communicated with a combined electric pneumatic valve; one end of a fifth pipeline is communicated with the liquid outlet of the oxidant storage tank, and the other end of the fifth pipeline is communicated with the combined electric pneumatic valve; a second oxidant filling and discharge valve and a first oxidant liquid pipeline electric explosion valve are sequentially arranged on the fifth pipeline in the direction from one end of the fifth pipeline to the other end of the fifth pipeline; one end of a sixth pipeline is communicated with the fifth pipeline, and one end of the sixth pipeline is located between the first oxidant liquid pipeline electric explosion valve and the combined electric pneumatic valve; the other end of the sixth pipeline is communicated with at least one separation engine; an oxidant pipeline throttle ring and a second oxidant liquid pipeline electric explosion valve are sequentially arranged on the sixth pipeline in the direction from one end of the sixth pipeline to the other end of the sixth pipeline; one end of a seventh pipeline is communicated with the liquid outlet of the fuel storage tank, and the other end of the seventh pipeline is communicated with the combined electric pneumatic valve; a second fuel storage tank filling and discharge valve and a first fuel liquid pipeline electric explosion valve are sequentially arranged on the seventh pipeline in the direction from one end of the seventh pipeline to the other end of the seventh pipeline; one end of an eighth pipeline is communicated with the seventh pipeline, and one end of the eighth pipeline is located between the first fuel liquid pipeline electric explosion valve and the combined electric pneumatic valve; the other end of the eighth pipeline is communicated with at least one separation engine; a fuel pipeline throttle ring and a second fuel liquid pipeline electric explosion valve are sequentially arranged on the eighth pipeline in the direction from one end of the eighth pipeline to the other end of the eighth pipeline; the combined electric pneumatic valve is communicated with four pitch-yaw engines.
[0006] As described above, the pitch and yaw engine and the combined electric valve form the engine module; the fuel tank's inlet integrates a fuel check valve, a fuel gas diaphragm valve, and a first fuel tank filling and drain valve; the oxidizer tank's inlet integrates an oxidizer check valve, an oxidizer gas diaphragm valve, and a first oxidizer filling and drain valve; the fuel tank's outlet integrates a second fuel tank filling and drain valve and a first fuel liquid circuit electric explosion valve; the oxidizer tank's outlet integrates a second oxidizer filling and drain valve and a first oxidizer liquid circuit electric explosion valve; and the gas cylinder's outlet integrates a filling valve and a gas circuit electric explosion valve.
[0007] As shown above, the four pitch and yaw engines are arranged in an X-shape, and the axis of each separate engine has a preset angle with the axis of the fairing.
[0008] As shown above, a gas cylinder mounting skirt is provided on the outer side of one end of the gas cylinder, which is connected to the fuel storage tank.
[0009] As described above, the fuel tank has a fuel tank docking flange at the front end, which connects to one end of the truss; the fuel tank has an installation flange in the middle, which connects to the head cone compartment at the top of the fairing; and the fuel tank has a fuel tank mounting skirt at the rear end, which connects to the gas cylinder mounting skirt. After connection, there is a mounting skirt space between the fuel tank mounting skirt and the gas cylinder mounting skirt, and the charging valve, gas circuit electric explosion valve, pressure reducing valve and safety valve are all located in the mounting skirt space.
[0010] As described above, the fuel tank has an internal fuel tank partition with at least one fuel tank partition window, and a fuel tank accumulator at the bottom. The fuel tank outlet is located at the top of the fuel tank, and an outlet pipe is located at the top of the fuel tank accumulator, connected to the fuel tank outlet. Multiple fuel tank collection channels are arranged around the fuel tank accumulator. The fuel tank accumulator, fuel tank collection channels, and outlet pipes are internally connected. The fuel tank partition window is a screen structure. The fuel tank accumulator is a frustum-shaped hollow structure with a screen on its surface. The outlet pipe is a hollow metal pipe. The fuel tank collection channels are rectangular or circular hollow structures with a screen on their surface.
[0011] As shown above, the rear end of the oxidizer tank is provided with an oxidizer tank docking flange, which is connected to the other end of the truss through the oxidizer tank docking flange. After connection, there is a truss space between the oxidizer tank, the fuel tank and the truss. An upper frame and a lower frame are provided in the truss space. The separate engine, the combined electric pneumatic valve and the pitch and yaw engine are installed on the upper frame and / or the lower frame.
[0012] The inner part of the oxidant tank is provided with an oxidant tank partition plate, and the center of the oxidant tank partition plate is provided with an oxidant tank partition plate window; the liquid outlet nozzle of the oxidant tank is located at the bottom of the oxidant tank; an oxidant tank accumulator is arranged above the liquid outlet nozzle of the oxidant tank; a plurality of oxidant tank collection channels are arranged around the oxidant tank accumulator, and the oxidant tank accumulator is in communication with the inside of the oxidant tank collection channels; wherein the oxidant tank partition plate window is a screen structure; the oxidant tank accumulator is a circular truncated cone hollow structure, and the surface of the oxidant tank accumulator is provided with a screen; the oxidant tank collection channel is a rectangular cross-section hollow structure or a circular cross-section hollow structure, and the surface of the oxidant tank collection channel is provided with a screen.
[0013] The truss is an X-shaped truss.
[0014] The rocket front end attitude control power system is installed in the nose cone cabin at the top of the fairing, and the fairing is separated by the separation guide rod to complete the fairing separation.
[0015] The beneficial effects achieved by the present application are as follows:
[0016] (1) The rocket front end attitude control power system of the present application can be arranged in the nose cone cabin to realize the pitch and yaw control of the rocket body during the first and second stage flight and the separation of the fairing.
[0017] (2) The rocket front end attitude control power system of the present application adopts an X-shaped truss to connect the oxidant tank and the fuel tank, and the pitch and yaw engines and the separation engine are arranged in the middle, and the bottom and top liquid supply modes are used respectively, which on the one hand improves the space utilization rate, and on the other hand shortens the length of the liquid path pipeline, improves the engine response time, and reduces the influence of the water hammer pressure of the engine start and stop.
[0018] (3) The rocket front end attitude control power system of the present application adopts constant pressure extrusion and drop pressure work, which not only meets the pitch and yaw control force demand during the first and second stage flight, but also saves the amount of pressurized gas, reduces the volume and mass of the gas cylinder.
[0019] (4) The rocket front end attitude control power system of the present application adopts a series layout of the oxidant tank, the separation engine, the pitch and yaw engine, the fuel tank and the gas cylinder, which improves the structural efficiency and space utilization rate of the power system. BRIEF DESCRIPTION OF DRAWINGS
[0020] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description are only some embodiments described in the present application, and other drawings can also be obtained by those skilled in the art according to these drawings.
[0021] Figure 1 A structural schematic diagram of an embodiment of the installation state of the rocket front end attitude control power system and the fairing;
[0022] Figure 2 A layout diagram of an embodiment of the rocket front end attitude control power system;
[0023] Figure 3 A structural schematic diagram of an embodiment of the rocket front end attitude control power system;
[0024] Figure 4 A structural schematic diagram of an embodiment of the oxidizer storage tank;
[0025] Figure 5 A structural schematic diagram of an embodiment of the fuel storage tank. DETAILED DESCRIPTION
[0026] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only some of the embodiments of the present application, but not all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of the present application.
[0027] As shown in Figures 1-5 The present application provides a rocket front end attitude control power system 1, comprising: an oxidizer storage tank 15, a separation engine 14, a pitch and yaw engine 13, a fuel storage tank 12 and a gas cylinder 11 arranged in sequence along the axis direction of the head cone cabin 3 at the top of the fairing 2.
[0028] The outlet of the gas cylinder 11 is in communication with one end of a first pipeline; the other end of the first pipeline is in communication with one end of a second pipeline and one end of a third pipeline; in the direction from one end of the first pipeline to the other end of the first pipeline, an inflation valve 111, a gas circuit electric explosion valve 112, a pressure reducing valve 113 and a safety valve 114 are arranged in sequence on the first pipeline.
[0029] One end of the second pipeline is also in communication with one end of the third pipeline.
[0030] The other end of the second pipeline is in communication with an air inlet 151 of the oxidizer storage tank 15; in the direction from one end of the second pipeline to the other end of the second pipeline, an oxidizer check valve 152, an oxidizer gas circuit diaphragm valve 153 and a first oxidizer filling and discharge valve 154 are arranged in sequence on the second pipeline.
[0031] The other end of the third pipeline is communicated with the gas inlet 121 of the fuel tank 12; in the third pipeline, in the direction from the one end of the third pipeline to the other end of the third pipeline, the fuel check valve 122, the fuel gas pipeline diaphragm valve 123 and the first fuel tank filling discharge valve 124 are sequentially arranged.
[0032] The one end of the fourth pipeline is communicated with the first pipeline, and the one end of the fourth pipeline is located between the safety valve 114 and the one end of the third pipeline; the other end of the fourth pipeline is communicated with the combined electro-pneumatic valve 16.
[0033] The one end of the fifth pipeline is communicated with the liquid outlet 155 of the oxidant tank 15, and the other end of the fifth pipeline is communicated with the combined electro-pneumatic valve 16; in the fifth pipeline, in the direction from the one end of the fifth pipeline to the other end of the fifth pipeline, the second oxidant filling discharge valve 156 and the first oxidant liquid pipeline electric explosion valve 157 are sequentially arranged.
[0034] The one end of the sixth pipeline is communicated with the fifth pipeline, and the one end of the sixth pipeline is located between the first oxidant liquid pipeline electric explosion valve 157 and the combined electro-pneumatic valve 16; the other end of the sixth pipeline is communicated with at least one separate engine 14; in the sixth pipeline, in the direction from the one end of the sixth pipeline to the other end of the sixth pipeline, the oxidant pipeline throttle ring 158 and the second oxidant liquid pipeline electric explosion valve 159 are sequentially arranged.
[0035] The one end of the seventh pipeline is communicated with the liquid outlet 138 of the fuel tank 12, and the other end of the seventh pipeline is communicated with the combined electro-pneumatic valve 16; in the seventh pipeline, in the direction from the one end of the seventh pipeline to the other end of the seventh pipeline, the second fuel tank filling discharge valve 125 and the first fuel liquid pipeline electric explosion valve 126 are sequentially arranged.
[0036] The one end of the eighth pipeline is communicated with the seventh pipeline, and the one end of the eighth pipeline is located between the first fuel liquid pipeline electric explosion valve 126 and the combined electro-pneumatic valve 16; the other end of the eighth pipeline is communicated with at least one separate engine 14; in the eighth pipeline, in the direction from the one end of the eighth pipeline to the other end of the eighth pipeline, the fuel pipeline throttle ring 127 and the second fuel liquid pipeline electric explosion valve 128 are sequentially arranged.
[0037] The combined electro-pneumatic valve 16 is communicated with the four pitch and yaw engines 13.
[0038] Specifically, as Figure 3As shown, the rocket front end attitude control power system of the present application adopts a modular design, which is composed of pitch and yaw engines 13 and combined electric valves 16 to form an engine module; the gas inlet nozzles of fuel tanks 12 and oxidant tanks 15 are integrated with check valves, diaphragm valves, and filling and discharge valves, and the liquid outlet nozzles of the fuel tanks 12 and the oxidant tanks 15 are integrated with electric explosion valves and filling and discharge valves; the outlet of the gas cylinder 11 is integrated with a charging valve 111 and a gas path electric explosion valve 112. The rocket front end attitude control power system of the present application is installed in the nose cone cabin 3 at the top of the fairing 2, which is used to provide pitch and yaw control moments during the flight of the first and second stages of the rocket, and to provide power for the overall fairing 2 separation, and can complete the fairing 2 separation in combination with the fairing 2 separation guide rod 4.
[0039] Due to the structural limitations of the nose cone cabin 3, the rocket front end attitude control power system of the present application is arranged in the axial direction of the nose cone cabin 3 at the top of the fairing 2 in sequence, that is, the oxidant tank 15, the separation engine 14, the pitch and yaw engine 13, the fuel tank 12, and the gas cylinder 11, thereby forming a series layout, improving the structural efficiency and space utilization, and being able to provide pitch and yaw control forces for the first and second stages of the rocket body and the fairing separation force.
[0040] Further, the specific number of separation engines 14 is set according to actual conditions, and the present application preferably has four separation engines 14.
[0041] Further, the four pitch and yaw engines 13 adopt an X-shaped layout to provide pitch and yaw control forces for the rocket body.
[0042] Further, each separation engine 14 has a preset angle between the axis and the axis of the fairing 2, which is used to provide axial and radial thrust for the separation of the fairing 2.
[0043] Specifically, the specific value of the preset angle is set according to actual conditions.
[0044] Further, the outer side of one end of the gas cylinder 11 is provided with a gas cylinder mounting skirt, which is connected with the fuel tank 12 through the gas cylinder mounting skirt.
[0045] Specifically, the gas cylinder 11 usually adopts a composite material winding titanium alloy or aluminum alloy inner liner gas cylinder, but is not limited to a composite material winding titanium alloy or aluminum alloy inner liner gas cylinder. One end of the gas cylinder 11 is wound with a gas cylinder mounting skirt, which is connected with the fuel tank 12 in the radial direction by bolts, but is not limited to the radial connection by bolts.
[0046] Further, as shown in Figure 2 and Figure 5As shown, the front end of the fuel tank 12 is provided with a fuel tank docking flange 129, which is connected with one end of the truss 17 through the fuel tank docking flange 129; the middle part of the fuel tank 12 is provided with a mounting flange 130, which is connected with the head cone cabin 3 at the top of the fairing 2 through the mounting flange 130; the rear end of the fuel tank 12 is provided with a fuel tank mounting skirt 131, which is connected with the gas cylinder mounting skirt, after the connection, the fuel tank mounting skirt 131 and the gas cylinder mounting skirt have a mounting skirt space, and the inflation valve 111, the gas path electric explosion valve 112, the pressure reducing valve 113 and the safety valve 114 are all located in the mounting skirt space.
[0047] Specifically, the fuel tank docking flange 129 is axially connected with one end of the truss 17 by bolts, but is not limited to be axially connected by bolts. The inflation valve 111, the gas path electric explosion valve 112, the pressure reducing valve 113 and the safety valve 114 are arranged between the fuel tank 12 and the gas cylinder 11, thereby improving the space utilization.
[0048] Further, the fuel tank mounting skirt 131 and the gas cylinder mounting skirt of the gas cylinder 11 are radially connected by bolts, but are not limited to be radially connected by bolts.
[0049] Further, the gas inlet nozzle 121 of the fuel tank 12 is located at the top of the fuel tank 12, the inside of the fuel tank 12 is provided with a fuel tank partition plate 132, which divides the fuel tank 12 into upper and lower cabins, at least one fuel tank partition plate window 133 is arranged on the fuel tank partition plate 132; the liquid outlet nozzle 138 of the fuel tank 12 is arranged at the top of the fuel tank 12; the bottom of the fuel tank 12 is provided with a fuel tank liquid accumulator 134; the top of the fuel tank liquid accumulator 134 is provided with a liquid outlet pipe 135, which communicates with the liquid outlet nozzle 138 of the fuel tank 12; a plurality of fuel tank collection channels 136 are arranged around the fuel tank liquid accumulator 134; the inside of the fuel tank liquid accumulator 134, the fuel tank collection channels 136 and the liquid outlet pipe 135 are in communication, which can realize the non-air-trapped supply of fuel.
[0050] The fuel tank partition plate window 133 is a screen structure, which can ensure that the upper cabin propellant is consumed first, then the lower cabin propellant is consumed, and at the same time, prevent the upper cabin pressurized gas from entering the lower cabin when the propellant in the tank shakes greatly.
[0051] The specific number of the fuel tank partition plate window 133 is set according to the actual situation, and the application preferably has four.
[0052] The four fuel tank partition plate windows 133 are circumferentially and uniformly arranged on the fuel tank partition plate 132.
[0053] The specific structure of the fuel tank accumulator 134 is set according to actual conditions, and preferably, the fuel tank accumulator 134 is a hollow structure in the shape of a circular truncated cone, and the surface of the fuel tank accumulator 134 is provided with a screen to ensure that there is no air in the liquid outlet pipe.
[0054] The specific number of the fuel tank collection channels 136 is set according to actual conditions, and preferably, the number is 4, 6 or 8.
[0055] The specific structure of the fuel tank collection channels 136 is set according to actual conditions, and preferably, the fuel tank collection channels 136 are hollow structures in the shape of a rectangular cross section or a circular cross section, and the surface of the fuel tank collection channels 136 is provided with a screen to ensure that there is no air in the liquid outlet pipe.
[0056] Further, as shown in Figure 2 and Figure 4 , the rear end of the oxidizer tank 15 is provided with an oxidizer tank butt flange 160, which is connected to the other end of the truss 17. After connection, the oxidizer tank 15, the fuel tank 12 and the truss 17 have a truss space therebetween, and the upper end frame 18 and the lower end frame 19 are arranged in the truss space. The separate engine 14, the combined electrically operated valve 16 and the pitch and yaw engine 13 are installed on the upper end frame 18 and / or the lower end frame 19.
[0057] Specifically, the oxidizer tank butt flange 160 and the other end of the truss 17 are connected by bolts in the axial direction, but are not limited to being connected by bolts in the axial direction.
[0058] Further, as shown in Figure 4 , the air inlet 151 of the oxidizer tank 15 is located at the top of the oxidizer tank 15, and the inside of the oxidizer tank 15 is provided with an oxidizer tank partition plate 161, which divides the oxidizer tank 15 into an upper cabin and a lower cabin. The center of the oxidizer tank partition plate 161 is provided with an oxidizer tank partition plate window 162. The liquid outlet 155 of the oxidizer tank 15 is located at the bottom of the oxidizer tank 15. An oxidizer tank accumulator 163 is arranged above the liquid outlet 155 of the oxidizer tank 15. A plurality of oxidizer tank collection channels 164 are arranged around the oxidizer tank accumulator 163, and the oxidizer tank accumulator 163 is in communication with the inside of the oxidizer tank collection channels 164, so that the oxidizer can be supplied without being trapped.
[0059] Among them, the oxidizer tank partition plate window 162 is a screen structure, which ensures that the upper cabin propellant is consumed first, and then the lower cabin propellant is consumed, and at the same time prevents the upper cabin pressurization gas from entering the lower cabin when the propellant in the tank shakes greatly.
[0060] The specific structure of the oxidant storage tank accumulator 163 is set according to actual conditions, and the application is preferably that the oxidant storage tank accumulator 163 is a circular truncated cone hollow structure, and the surface of the oxidant storage tank accumulator 163 is provided with a screen. The surface of the oxidant storage tank accumulator 163 is provided with a screen to ensure that there is no air in the liquid outlet pipe.
[0061] The specific number of the oxidant storage tank collection channels 164 is set according to actual conditions, and the application is preferably 4, 6 or 8.
[0062] The specific structure of the oxidant storage tank collection channel 164 is set according to actual conditions, and the application is preferably that the oxidant storage tank collection channel 164 is a rectangular cross-section hollow structure or a circular cross-section hollow structure, and the surface of the oxidant storage tank collection channel 164 is provided with a screen to ensure that there is no air in the liquid outlet pipe.
[0063] Specifically, the oxidant storage tank 15 and the fuel storage tank 12 both adopt a compartment management scheme, and the accumulators (i.e., the oxidant storage tank accumulator 163 and the fuel storage tank accumulator 134) and the collection channels (i.e., the oxidant storage tank collection channel 164 and the fuel storage tank collection channel 136) are arranged below the partition (i.e., the oxidant storage tank partition 161 and the fuel storage tank partition 132), so that the oxidant and the fuel are supplied without air entrapment.
[0064] Further, as shown in FIG. 1, the truss 17 is an X-shaped truss, but is not limited to an X-shaped truss. Figure 2
[0065] Specifically, the rocket front end attitude control power system of the application is connected with the nose cone cabin 3 through the installation flange 130 arranged in the middle of the fuel storage tank 12 as the main connection structure and through the X-shaped truss as the auxiliary connection structure.
[0066] Further, as an embodiment, the oxidant storage tank 15 and the fuel storage tank 12 supply oxidant and fuel to the combined electric pneumatic valve 16 from the bottom and the top thereof, respectively. The combined electric pneumatic valve 16 is provided with at least five interfaces, of which four interfaces are respectively used to supply propellants to four pitch and yaw engines 13, and one interface is used to supply a gas source to control the movement of the valve core.
[0067] Specifically, the oxidant storage tank 15 and the fuel storage tank 12 are connected by the X-shaped truss, the pitch and yaw engines 13 and the separation engine 14 are arranged in the middle of the X-shaped truss, and the bottom and the top of the pitch and yaw engines 13 and the separation engine 14 are respectively supplied with liquid, which on the one hand improves the space utilization rate and on the other hand shortens the length of the liquid path pipeline, improves the engine response time, and reduces the influence of water hammer pressure on the engine start and stop.
[0068] The oxidant storage tank 15 and the fuel storage tank 12 adopt an X-shaped truss connection scheme, and the fuel storage tank 12 and the gas cylinder 11 adopt a mounting skirt connection scheme, so that the structural efficiency of the attitude control power system is improved under the premise of ensuring the connection strength and rigidity.
[0069] Further, the gas cylinder 11, the fuel storage tank 12 and the oxidant storage tank 15 all adopt spherical cylindrical storage tanks, but are not limited to spherical cylindrical storage tanks.
[0070] Specifically, the shell of the gas cylinder 11, the fuel storage tank shell 137 of the fuel storage tank 12 and the oxidant storage tank shell 165 of the oxidant storage tank 15 are all spherical cylindrical, but are not limited to spherical cylindrical.
[0071] The gas cylinder 11, the fuel storage tank 12 and the oxidant storage tank 15 of the rocket front end attitude control power system adopt spherical cylindrical storage tanks, and are arranged in series in the nose cone cabin 3, so that the structural efficiency and space utilization rate are improved, and the first and second flight pitch and yaw control forces of the rocket body and the fairing separation force can be provided.
[0072] Specifically, the working method of the rocket front end attitude control power system is as follows:
[0073] Before the engine works, the control system sends a control signal to open the gas circuit electric explosion valve 112, the high-pressure gas circuit forms a passage, and the high-pressure gas is supplied by the gas cylinder 11. After the high-pressure gas is reduced and stabilized by the pressure reducing valve, it breaks the gas circuit isolation diaphragm (i.e. oxidant gas circuit diaphragm valve 153, fuel gas circuit diaphragm valve 123) to pressurize the oxidant storage tank and the fuel storage tank. At the same time, the gas after pressure reduction acts on the combined electrically operated valve 16 to provide driving force for valve opening; the control system sends a control signal to open the propellant liquid circuit main road electric explosion valve (i.e. first fuel liquid circuit electric explosion valve 126, first oxidant liquid circuit electric explosion valve 157), and the propellant filling liquid pipeline reaches the control valve group and the liquid circuit branch electric explosion valve (i.e. second fuel liquid circuit electric explosion valve 128, second oxidant liquid circuit electric explosion valve 159) before it. When the pitch and yaw engine 13 needs to work, the control valve group opens the corresponding passage, and the oxidant and fuel enter the thrust chamber to generate high-temperature and high-pressure gas to generate thrust. As the rocket flies, the required pitch and yaw control force gradually decreases, and the attitude control power system adopts a constant pressure extrusion working mode in the early stage and a falling pressure working mode in the later stage. Before the fairing 2 needs to separate, the control system sends a signal to open the liquid circuit branch electric explosion valve (i.e. second fuel liquid circuit electric explosion valve 128, second oxidant liquid circuit electric explosion valve 159), and the separation engine liquid circuit forms a passage. The oxidant and fuel enter the thrust chamber to generate high-temperature and high-pressure gas to generate thrust, and the separation engine 14 works until the propellant is consumed. The separation of the fairing 2 is completed by the separation engine 14 on the fairing 2 to provide positive thrust and side thrust to complete the lateral separation. In order to avoid collision with the satellite during the fairing 2 pulling process, the separation guide rod 4 is arranged, and the fairing completes separation along the separation guide rod 4.
[0074] Further, the rocket front end attitude control power system of the present application can not only be used for the front end of the launch vehicle, but also be applied to the top of the escape spacecraft.
[0075] The beneficial effects achieved by the present application are as follows:
[0076] (1) The rocket front end attitude control power system of the present application can be arranged in the nose cone cabin to realize pitch and yaw control of the rocket body during first and second stage flight and fairing separation.
[0077] (2) The rocket front end attitude control power system of the present application adopts X-shaped truss connection for the oxidant storage tank and the fuel storage tank, and arranges the pitch and yaw engine and the separation engine in the middle, and adopts bottom and top liquid supply methods respectively. On the one hand, it improves the space utilization rate, and on the other hand, it shortens the length of the liquid circuit pipeline, improves the engine response time, and reduces the influence of water hammer pressure on engine start and stop.
[0078] (3) The rocket front end attitude control power system of the present application adopts constant pressure extrusion and falling pressure working mode, which not only meets the pitch and yaw control force demand during first and second stage flight, but also saves the amount of pressurized gas, reduces the volume and mass of the gas cylinder.
[0079] (4) The rocket front-end attitude control power system of the application adopts the series layout of oxidant storage tank, separation engine, pitch and yaw engine, fuel storage tank and gas cylinder, thereby improving the structural efficiency and space utilization of the power system.
[0080] While the preferred embodiments of the application have been described, additional variations and modifications can be made to the embodiments by those skilled in the art once they learn of the basic inventive concepts. Therefore, the scope of the application is intended to include all such changes and modifications as fall within the scope of the application. It will be apparent to those skilled in the art that various modifications and variations can be made to the present application without departing from the spirit or scope of the application. Thus, it is intended that the present application cover modifications and variations of this application provided they come within the scope of the appended claims and their equivalents.
Claims
1. A rocket front-end attitude control propulsion system, characterized in that, include: The oxidizer tank, separation engine, pitch and yaw engine, fuel tank and gas cylinder are arranged sequentially along the axial direction of the nose cone compartment at the top of the fairing. The outlet of the gas cylinder is connected to one end of the first pipeline; the other end of the first pipeline is connected to one end of the second pipeline and one end of the third pipeline respectively; in the direction from one end of the first pipeline to the other end of the first pipeline, an inflation valve, a gas circuit electric explosion valve, a pressure reducing valve and a safety valve are installed in sequence on the first pipeline. One end of the second pipeline is also connected to one end of the third pipeline; The other end of the second pipeline is connected to the inlet of the oxidant storage tank; an oxidant check valve, an oxidant gas diaphragm valve, and a first oxidant filling and draining valve are sequentially installed on the second pipeline in the direction from one end of the second pipeline to the other end; The other end of the third pipeline is connected to the air inlet of the fuel tank; a fuel check valve, a fuel gas diaphragm valve and a first fuel tank filling and drain valve are installed sequentially on the third pipeline in the direction from one end of the third pipeline to the other end; One end of the fourth pipeline is connected to the first pipeline, and one end of the fourth pipeline is located between the safety valve and one end of the third pipeline; the other end of the fourth pipeline is connected to the combined electric pneumatic valve. One end of the fifth pipeline is connected to the outlet of the oxidant storage tank, and the other end of the fifth pipeline is connected to the combined electric valve; in the direction from one end of the fifth pipeline to the other end of the fifth pipeline, a second oxidant filling and draining valve and a first oxidant liquid circuit electric explosion valve are installed in sequence on the fifth pipeline; One end of the sixth pipeline is connected to the fifth pipeline, and one end of the sixth pipeline is located between the first oxidant liquid circuit electro-explosion valve and the combined electric pneumatic valve; the other end of the sixth pipeline is connected to at least one separate engine; in the direction from one end of the sixth pipeline to the other end of the sixth pipeline, an oxidant circuit throttle ring and a second oxidant liquid circuit electro-explosion valve are sequentially installed on the sixth pipeline; One end of the seventh pipeline is connected to the liquid outlet of the fuel tank, and the other end of the seventh pipeline is connected to the combined electric air valve; in the direction from one end of the seventh pipeline to the other end of the seventh pipeline, a second fuel tank filling and draining valve and a first fuel liquid circuit electric explosion valve are installed in sequence on the seventh pipeline; One end of the eighth pipeline is connected to the seventh pipeline, and one end of the eighth pipeline is located between the first fuel liquid circuit electric explosion valve and the combined electric air valve; the other end of the eighth pipeline is connected to at least one separate engine; in the direction from one end of the eighth pipeline to the other end of the eighth pipeline, a fuel circuit throttle ring and a second fuel liquid circuit electric explosion valve are sequentially installed on the eighth pipeline. The combined electric valves are connected to four pitch and yaw engines.
2. The rocket front-end attitude control propulsion system according to claim 1, characterized in that, The engine module consists of a pitch and yaw engine and a combination of electric pneumatic valves. The fuel tank's air inlet integrates a fuel check valve, a fuel gas diaphragm valve, and a first fuel tank filling and drain valve; The oxidant storage tank has an integrated oxidant check valve, an oxidant gas diaphragm valve, and a first oxidant filling and drain valve at the inlet. The fuel tank outlet integrates a second fuel tank filling and draining valve and a first fuel liquid circuit electric explosion valve; The outlet of the oxidant storage tank integrates a second oxidant filling and draining valve and a first oxidant liquid circuit electro-explosion valve; The gas cylinder's outlet integrates a filling valve and a gas circuit electric explosion valve.
3. The rocket front-end attitude control propulsion system according to claim 1, characterized in that, The four pitch and yaw engines are arranged in an X-shape, with each engine's axis having a preset angle relative to the fairing's axis.
4. The rocket front-end attitude control propulsion system according to claim 1, characterized in that, A gas cylinder mounting skirt is provided on the outer side of one end of the gas cylinder, and the gas cylinder mounting skirt is connected to the fuel storage tank.
5. The rocket front-end attitude control propulsion system according to claim 4, characterized in that, The front end of the fuel tank is equipped with a fuel tank docking flange, which is connected to one end of the truss. The fuel tank is equipped with a mounting flange in the middle, which connects to the head cone compartment at the top of the fairing. The fuel tank is equipped with a fuel tank mounting skirt at the rear end, which is connected to the gas cylinder mounting skirt. After connection, there is a mounting skirt space between the fuel tank mounting skirt and the gas cylinder mounting skirt. The filling valve, gas circuit electric explosion valve, pressure reducing valve and safety valve are all located in the mounting skirt space.
6. The rocket front-end attitude control propulsion system according to claim 5, characterized in that, The fuel tank has an internal fuel tank partition with at least one fuel tank partition window. A fuel tank accumulator is located at the bottom of the fuel tank. The fuel tank outlet is located at the top of the fuel tank, and an outlet pipe is located at the top of the fuel tank accumulator, connecting to the fuel tank outlet. Multiple fuel tank collection channels are located around the fuel tank accumulator. The fuel tank accumulator, fuel tank collection channels, and outlet pipe are internally connected. The fuel tank partition window is a screen structure; The fuel tank accumulator has a frustum-shaped hollow structure, and the surface of the fuel tank accumulator is equipped with a screen. The outlet pipe is a hollow metal tube; The fuel tank collection channel has a hollow structure with a rectangular or circular cross-section, and the surface of the fuel tank collection channel is equipped with a screen.
7. The rocket front-end attitude control propulsion system according to claim 5, characterized in that, An oxidizer tank docking flange is provided at the rear end of the oxidizer tank, which is connected to the other end of the truss through the oxidizer tank docking flange. After connection, there is a truss space between the oxidizer tank, the fuel tank and the truss. An upper frame and a lower frame are provided in the truss space. The separate engine, the combined electric pneumatic valve and the pitch and yaw engine are installed on the upper frame and / or the lower frame.
8. The rocket front-end attitude control propulsion system according to claim 7, characterized in that, The oxidant storage tank is equipped with an oxidant storage tank partition, and an oxidant storage tank partition window is located at the center of the partition. The outlet of the oxidant storage tank is located at the bottom of the tank. An oxidant storage tank accumulator is located above the outlet. Multiple oxidant storage tank collection channels are arranged around the accumulator, and the accumulator is internally connected to the collection channels. The partition window of the oxidant storage tank is a screen structure; The oxidant storage tank accumulator has a frustum-shaped hollow structure, and a screen is provided on the surface of the oxidant storage tank accumulator; The oxidant storage tank collection channel has a hollow rectangular or circular cross-section, and a screen is provided on the surface of the oxidant storage tank collection channel.
9. The rocket front-end attitude control propulsion system according to claim 5 or 7, characterized in that, The truss is an X-shaped truss.
10. The rocket front-end attitude control propulsion system according to claim 1, characterized in that, The rocket's attitude control propulsion system is installed in the nose cone compartment at the top of the fairing, and works in conjunction with the fairing's separation guide rod to complete the fairing's separation.