Multi-stage carrier rocket system and operation method

Abstract

The multi-stage carrier rocket system comprises a main thrust rocket which is located in the center and provides main thrust of the whole system in the low-range stage, and a plurality of branch guide rockets which are located on the periphery of the main thrust rocket and connected with the main thrust rocket in parallel and are provided with liquid propellants and engine systems. Each branch guide rocket not only is separated from the main thrust rocket which stops providing the upward thrust at the elevation stage and independently provides thrust to send a top effective load to a preset position, but also provides thrust in the same direction as the main thrust rocket at the low-range stage; liquid propellants and engine systems of the branch guide rockets can obtain or come from a liquid propellant system of the self-propelled rocket through an external propellant conveying pipeline, or come from propellant supply or supplement of a liquid propellant sub-storage tank of the self-propelled rocket; according to the technology, the sub-guide rocket can play the role of a booster rocket at the same time, the total thrust, the acceleration and the carrying capacity of the multi-stage rocket in the low-range stage and the flexibility of entering different tracks are improved, and the overall height of the system and the requirement for a launching platform are obviously reduced.

Description

Technical Field

[0001] This technology belongs to aerospace engineering technology. Background Art

[0002] Since Tsiolkovsky proposed the aerospace theory relying on rocket engines at the beginning of the 20th century, aerospace exploration technology has made great progress. In order to enable rockets to smoothly ascend to high altitudes or enter space, most countries use multi-stage launch vehicles. A multi-stage rocket consists of multiple single-stage rockets, each with its own engine, propellant, control system, and servo mechanism. These single-stage rockets are generally connected in series by 2 or 3 stages. When needed, a single-stage rocket can be paralleled with multiple boosters to increase the thrust and accelerate it to the predetermined launch speed before separation.

[0003] Multiple boosters require a large cost. If the demand for boosters can be reduced while ensuring the total thrust, it is very beneficial to the technical effect of the launch vehicle. At the same time, due to various requirements of aerospace missions, the payload of a multi-stage launch vehicle often needs to enter different orbits. Therefore, after the payload fairing is opened when the last stage of the launch vehicle reaches the predetermined position, different payloads need to use their respective different jet power devices to enter their respective orbits in a separate guidance manner. If the differences in the predetermined orbits or even the predetermined flight directions of different payloads are relatively large, this separate guidance method will face the difficulty of insufficient jet power of the payload itself. If the ability of the payload's own jet engine is to be increased, it will significantly increase the burden on the entire multi-stage launch vehicle. This is a difficult problem that urgently needs to be solved in existing aerospace technology.

[0004] The purpose of this technology is to provide a new multi-stage launch vehicle technology that can not only greatly improve the flexibility of transporting separately guided payloads, but also improve the carrying capacity or efficiency of the entire multi-stage rocket system and reduce the requirements for the launch platform. Summary of the Invention

[0005] This technology proposes a multi-stage launch vehicle system for pushing the payload into a high orbit in two successive stages of low altitude and high altitude, including: a main propulsion rocket located at the center of the rocket system that provides the main thrust or maximum thrust for the entire system in the low altitude stage, multiple separately guided rockets with liquid propellant and engine systems located around and connected in parallel with the main propulsion rocket, the payloads are respectively located at the tops of the separately guided rockets, there is a connection and release mechanism between the main propulsion rocket and the separately guided rockets, and each separately guided rocket not only separates from the main propulsion rocket that stops providing upward thrust in the high altitude stage and independently provides thrust to send the payload to the predetermined position, but also provides thrust in the same direction as the main propulsion rocket in the low altitude stage;

[0006] The main propulsion rocket is a rocket using a liquid propellant engine or a rocket using a solid propellant engine with a liquid propellant sub-tank;

[0007] The liquid propellant and engine system of the independently guided rocket has an external propellant delivery pipeline, through which it is connected to the liquid propellant tank in the main rocket using the liquid propellant rocket engine, or to the liquid propellant sub-tank of the main rocket;

[0008] When each separate launch vehicle starts its engine and accelerates together with the main rocket in the low-range phase, its liquid propellant and engine system can be supplied or replenished with propellant from either the liquid propellant system of the main rocket or the liquid propellant sub-tank of the main rocket through an external propellant delivery pipeline, so that when the separate launch vehicles begin the high-range phase, the propellant tanks of their liquid propellants and engine systems are full or mostly full of propellant.

[0009] The main thrust rocket or the independently guided rocket can have its own engine, propellant, propellant tank, control system and servo mechanism. The main thrust rocket can also be called a core stage rocket.

[0010] When the main propulsion rocket uses a liquid propellant rocket engine, it can be equipped with a liquid propellant system including a liquid propellant tank, a propellant delivery pipeline, a control valve or a propellant delivery pump.

[0011] When a liquid propellant rocket engine is working, it needs to continuously supply propellant to its combustion chamber to maintain the combustion process. It can rely on high-pressure gas to squeeze the liquid propellant components in the tank and directly transport the propellant to the combustion chamber through pipelines, or it can rely on pump pressure to supply propellant to the combustion chamber.

[0012] The main rocket using a liquid propellant engine may or may not have a liquid propellant sub-tank inside or on top.

[0013] Each of the independently guided rockets uses a liquid propellant rocket engine and can be provided with a liquid propellant system comprising a propellant tank, a propellant delivery pipeline and a control valve. The liquid propellant system can be provided with a propellant delivery pump when necessary.

[0014] The liquid propellant system of the independently targetable rocket may have a propellant delivery pipeline connecting its own rocket engine and an internal propellant tank, and may also have an interface connecting an external propellant delivery pipeline and its own rocket engine or connecting an external propellant delivery pipeline and its own propellant tank.

[0015] The multiple pilot rockets located around the main rocket and connected in parallel with it may be 2 or 3 or more.

[0016] The main rocket may use an engine with a different liquid propellant from that of the pilot rocket.

[0017] The multi-stage launch vehicle system, wherein the main launch vehicle may have a liquid propellant sub-tank at the top or other locations, which can be isolated from other liquid propellant tanks within the main launch vehicle and is capable of storing a liquid propellant different from that of other tanks but the same as that of the multiple reentry vehicles.

[0018] The main launch vehicle may use a solid fuel engine. The solid rocket engine may consist of a grain, a combustion chamber, a nozzle assembly, an ignition device, etc. The main launch vehicle may have a liquid propellant sub-tank at the top or other locations, which is isolated from the solid propellant within the main launch vehicle.

[0019] The main launch vehicle may be connected with booster rockets on the side, and there may be a connection and release mechanism between the main launch vehicle and the booster rockets. The booster rockets may use liquid propellant rocket engines or solid propellant rocket engines; when using liquid propellant rocket engines, they are equipped with a liquid propellant system including a liquid propellant tank, a propellant delivery pipeline, a control valve, or a propellant delivery pump.

[0020] The top of the booster rocket may or may not have a liquid propellant sub-tank. The liquid propellant system of the multiple reentry vehicles may have an external propellant delivery pipeline, which can be connected to the liquid propellant tank within the booster rocket using a liquid propellant rocket engine or to the liquid propellant sub-tank of the booster rocket. The sub-tank may be located at the upper part or the top of the booster rocket.

[0021] The liquid propellant, liquid propellant tank, liquid propellant sub-tank, control valve, propellant delivery pipeline, propellant delivery pump may be a liquid fuel or a liquid oxidizer, a liquid fuel or a liquid oxidizer tank, a liquid fuel or a liquid oxidizer sub-tank, a liquid fuel or a liquid oxidizer control valve, a liquid fuel or a liquid oxidizer delivery pipeline, a liquid fuel or a liquid oxidizer delivery pump, respectively.

[0022] During the low-altitude stage of the multi-stage rocket's takeoff acceleration and ascent, the engines of both the main launch vehicle and the multiple reentry vehicles can provide lift until the main launch vehicle completes its lift-providing task, separates from the multiple reentry vehicles, and enters the falling or descending recovery stage, while the engines of the multiple reentry vehicles can continue to operate to provide power to push the payload to continue ascending.

[0023] It can be arranged that when each multiple reentry vehicle starts its engine to accelerate together with the main launch vehicle and the booster rockets during the low-altitude stage, its liquid propellant system can obtain or receive the supply or replenishment of propellant from the liquid propellant system of the main launch vehicle, or from the liquid propellant sub-tank of the main launch vehicle, or from the liquid propellant system of the booster rocket, or from the liquid propellant sub-tank at the top of the booster rocket via the external propellant delivery pipeline.

[0024] The main thrust rocket can use an engine with a liquid propellant different from that of the MIRV rocket.

[0025] The multi-stage launch vehicle system, wherein the main thrust rocket can have a liquid propellant sub-tank at the top or other positions, which can be isolated from other liquid propellant tanks in the main thrust rocket and can store a liquid propellant different from other tanks but the same as that of the MIRV rocket.

[0026] The main thrust rocket can use a solid fuel engine, and its solid rocket engine can be composed of a grain, a combustion chamber, a nozzle assembly, an ignition device, etc., and can have a liquid propellant sub-tank at the top or other positions, which can be isolated from the solid propellant in the main thrust rocket.

[0027] The booster rocket can use an engine with a liquid fuel different from that of the MIRV rocket.

[0028] The multi-stage launch vehicle system, wherein the booster rocket can have a liquid propellant sub-tank at the top or other positions, which can be isolated from other liquid propellant tanks in the booster rocket and can store a liquid propellant different from other tanks but the same as that of the MIRV rocket.

[0029] The booster rocket can use a solid fuel engine.

[0030] The multi-stage launch vehicle system, wherein the booster rocket can have a liquid propellant sub-tank at the top or other positions, which is isolated from the solid propellant in the booster rocket.

[0031] The multi-stage launch vehicle system, wherein the top liquid propellant tank of the main thrust rocket or the booster rocket can be located inside the rocket shell or above the rocket shell and has a fairing.

[0032] The multi-stage launch vehicle system, wherein the connection release mechanism between the main thrust rocket and the MIRV rocket can include: a connecting rod or frame connecting the main thrust rocket and the MIRV rocket, and an explosive bolt or explosive cord fixed or in contact with the connecting rod or frame.

[0033] When it is necessary to separate the main thrust rocket from the MIRV rocket during the ascending flight process, the control device can initiate the explosion of the explosive bolt or explosive cord, causing the connecting rod or frame to lose its connection ability, and the MIRV rocket is separated from the main thrust rocket and continues to accelerate in flight.

[0034] The present invention may further include an operating method for the multi-stage launch vehicle system: during the low-altitude stage of the multi-stage rocket taking off and accelerating into the sky, the engines of the main propulsion rocket and the sub-guided rockets can both participate in providing lift until the main propulsion rocket completes its lift-providing task, separates from the sub-guided rockets, and enters the falling or descending recovery stage, while the engines of the sub-guided rockets can continue to operate to provide power and push the payload to continue ascending; during the low-altitude stage, each liquid propellant system of the sub-guided rockets can obtain or receive propellant supply or replenishment from the liquid propellant system of the main propulsion rocket, or from the liquid propellant sub-tank of the main propulsion rocket, or from the liquid propellant system of the booster rocket, or from the liquid propellant sub-tank at the top of the booster rocket via an external propellant transfer pipeline.

[0035] The multi-stage launch vehicle system or operating method, wherein the distances between each of the sub-guided rockets and the main propulsion rocket may be different, and the widths or lengths of each of the connecting and releasing mechanisms may be different.

[0036] The multi-stage launch vehicle system or operating method, wherein the multiple sub-guided rockets connected side by side around the main propulsion rocket may be located at symmetric positions with the main propulsion rocket as the axis, and each sub-guided rocket including the payload may have the same weight or the same engine thrust.

[0037] The multi-stage launch vehicle system or operating method, wherein the multiple sub-guided rockets connected to the main propulsion rocket may not all be located at symmetric positions relative to the axis of the main propulsion rocket.

[0038] The multi-stage launch vehicle system or operating method, wherein the total mass center or centroid of all the sub-guided rockets, including the internal propellant and the upper payload, may be located on or near the axis of the main propulsion rocket, which helps to improve the stability of the multi-stage launch vehicle system before or after launch. The total mass of all the sub-guided rockets may include the internal propellant and the payload mass of each sub-guided rocket.

[0039] The sub-guided multi-stage launch vehicle system or operating method, wherein the resultant force line of the thrusts of the engines of the multiple sub-guided rockets connected to the main propulsion rocket may be located on or near the central axis of the main propulsion rocket, providing balanced or relatively balanced thrust for the multi-stage launch vehicle system.

[0040] The multi-stage launch vehicle system, wherein the resultant force line of the thrusts of the engines of the multiple sub-guided rockets connected to the main propulsion rocket may be located on or near the total mass center of the sub-guided rockets, providing balanced or relatively balanced thrust for the multi-stage launch vehicle system.

[0041] The multi-stage launch vehicle system, in which when the resultant force line of the thrusts of the multiple guided rockets' engines deviates from the total mass center of these guided rockets, the thrust or rudder of the engines of some rockets can be adjusted during operation.

[0042] The multi-stage launch vehicle system or operation method, in which the resultant force line of the thrusts of the engines of the main launch rocket and the multiple guided rockets connected thereto can be kept consistent with or close to the total mass center of the rocket system, providing balanced or relatively balanced thrust for the multi-stage launch vehicle system.

[0043] The multi-stage launch vehicle system or operation method, in which when the resultant force line of the thrusts of the engines of the main launch rocket and the multiple guided rockets connected thereto deviates from the total mass center of the rocket system, the thrust or rudder of the engines of some rockets can be adjusted during operation.

[0044] The multi-stage launch vehicle system or operation method, in which the resultant force line of the thrusts of the engines of the main launch rocket and the multiple guided rockets connected thereto, with or without booster rockets included, can be kept consistent with or close to the total mass center of the rocket system, contributing to improving the stability of the multi-stage launch vehicle system after launch.

[0045] The multi-stage launch vehicle system or operation method, in which when the resultant force line of the thrusts of the engines of the main launch rocket and the multiple guided rockets connected thereto, with or without booster rockets included, deviates from the total mass center of the rocket system, the thrust or rudder of the engines of some rockets can be adjusted during operation.

[0046] The multi-stage launch vehicle system or operation method, in which when the resultant force line of the thrusts of the engines of the main launch rocket and the multiple guided rockets connected thereto, with or without booster rockets included, deviates from the total mass center of the rocket system, the thrust or rudder of the engines of some of the main launch rocket can be adjusted first during operation, and when necessary, the thrust or rudder of the engines of the guided rockets can be adjusted simultaneously or instead.

[0047] The multi-stage launch vehicle system or operation method, in which when the resultant force line of the thrusts of the engines of the main launch rocket and the multiple guided rockets connected thereto, with or without booster rockets included, deviates from the total mass center of the rocket system, the thrust or rudder of the engines of some of the guided rockets can be adjusted first during operation, and when necessary, the thrust or rudder of the engines of the main launch rocket can be adjusted simultaneously or instead. When the resultant force line of the engine thrusts biases towards one side of the total mass center of the rocket system, the thrust of some engines of the guided rockets located on that side can be reduced as needed, or the thrust of some engines of the guided rockets located on the opposite side can be increased.

[0048] The multi-stage launch vehicle system or operation method, wherein the MIRV rocket itself can consist of two stages of rockets. The lower stage first provides thrust to push the upper stage, and after the lower stage detaches, the upper stage operates to push the payload.

[0049] The multi-stage launch vehicle system or operation method, wherein above the top of the main thrust rocket, there can be a sub-rocket or a second-stage rocket carrying a payload, which can separate from the main thrust rocket that stops providing upward thrust during the elevation stage and independently provide thrust to send the self-carried payload to a predetermined position.

[0050] In the prior art, the second-stage sub-rocket of a multi-stage rocket relies entirely on the thrust of the first-stage main thrust rocket or plus boosters to ascend during the low-altitude stage. However, the MIRV rocket in this technology, which is equivalent to the second-stage sub-rocket, on the one hand, can play the role of part or all of the bundled booster rockets during the low-altitude stage, providing balanced assistance for the multi-stage rocket system, increasing the total thrust and acceleration of the multi-stage rocket during the low-altitude stage, increasing the speed or total weight of the MIRV rocket or second-stage sub-rocket at the end of the low-altitude stage, and improving the carrying capacity or efficiency of the entire multi-stage rocket system. On the other hand, it can enter the MIRV launch mode in advance during the elevation stage, greatly improving the flexibility of the payload to enter extremely different orbits. This technology can also significantly shorten the overall height or length of the multi-stage rocket system, reducing the harsh requirements for the launch rack or launch platform. For example, a shorter ocean platform, land platform or device can be used, making the launch smoother, more convenient and less costly. This innovation can bring significant progress and outstanding practical effects to space launch technology. Brief Description of the Drawings

[0051] Figure 1 It is a schematic diagram of the operation of the multi-stage rocket system of Embodiment 1 of the present invention, where A is the low-altitude stage and B is the elevation stage;

[0052] Figure 2 It is a partial cross-sectional view schematic diagram of the multi-stage rocket system of Embodiment 1 of the present invention;

[0053] Figure 3 It is a partial cross-sectional view schematic diagram of the multi-stage rocket system of Embodiment 2 of the present invention;

[0054] Figure 4 It is a partial cross-sectional view schematic diagram of the multi-stage rocket system of Embodiment 3 of the present invention;

[0055] Figure 5 A is a schematic cross-sectional view of the layout of the multi-stage rocket system of Embodiment 4 of the present invention;

[0056] Figure 5 B is a schematic cross-sectional view of the layout of the multi-stage rocket system of Embodiment 5 of the present invention;

[0057] Figure 6Cross-sectional schematic diagram of the layout of the multi-stage rocket system according to Embodiment 6 of the present invention;

[0058] Figure 7 Schematic diagram of the multi-stage rocket system according to Embodiment 7 of the present invention;

[0059] Figure 8 Schematic diagram of the multi-stage rocket system according to Embodiment 8 of the present invention.

[0060] Among them, 11 is the main propulsion rocket, 12 is the guided rocket, 13 is the payload, 14 is the connection and release mechanism of the guided rocket, 21 is the liquid oxidizer storage tank, 22 is the liquid fuel storage tank, 23 is the external oxidizer delivery pipeline, 24 is the external fuel delivery pipeline, 25 is the guided rocket engine, 26 is the oxidizer delivery pipeline, 31 is the liquid oxidizer sub-tank, 32 is the liquid fuel sub-tank, 41 is the solid propellant of the rocket engine, 42 is the solid fuel main propulsion rocket, 61 is the booster rocket, 62 is the connection and release mechanism of the booster rocket, 63 is the first guided rocket, 64 is the second guided rocket, 65 is the third guided rocket, 66 is the fourth guided rocket, 67 is the connection and release mechanism of the first guided rocket 63, 81 is the sub-stage rocket, and 82 is the payload of the sub-stage rocket.

[0061] Specific implementation manner

[0062] The following is a specific description with reference to the drawings.

[0063] Embodiment 1 (refer to Figure 1 、 Figure 2 ) is a multi-stage launch vehicle system. The liquid fuel main propulsion rocket 11 is connected in parallel with 2 or more identical liquid fuel guided rockets 12 symmetrically distributed. The payloads 13 are respectively located at the tops of the guided rockets 12. There is a connection and release mechanism 14 between the main propulsion rocket and the guided rocket. This mechanism can be a connecting rod, connected by an explosive bolt. This explosive bolt is hollow and filled with explosives inside. When it is electrified, it will explode and break the bolt, disconnecting the connecting rod and separating the booster rocket from the guided rocket. The rocket has its own engine, propellant, control system and servo mechanism.

[0064] Inside the main propulsion rocket, there are a liquid oxidizer storage tank 21 and a liquid fuel storage tank 22, which are connected to the main propulsion rocket engine through liquid fuel or liquid oxidizer delivery pipelines 26, control valves (not shown in the figure), and delivery pumps (not shown in the figure), and supply liquid fuel and liquid oxidizer to it when it is working.

[0065] The liquid oxidizer tank 21 and the liquid fuel tank 22 of the main thrust rocket are also respectively connected to the multiple warhead rockets' engines 25, or to the liquid oxidizer tank and the liquid fuel tank inside the multiple warhead rockets, through an external oxidizer delivery pipeline 23, an external fuel delivery pipeline 24, a control valve (not shown in the figure) or a delivery pump (not shown in the figure) located in the main thrust rocket or the multiple warhead rockets, to supply liquid fuel and liquid oxidizer to them when needed.

[0066] The launch vehicle system needs to push the payload into a high orbit in two stages: a low-altitude stage and a high-altitude stage. In the low-altitude stage, the engines of the main thrust rocket and the multiple warhead rockets connected in parallel are ignited and work respectively to accelerate the entire rocket system into the sky. At this time, the control valve (not shown in the figure) or the delivery pump can be opened, and liquid fuel and liquid oxidizer from the main thrust rocket can be provided to the engines of the multiple warhead rockets through the external oxidizer delivery pipeline 23 and the external fuel delivery pipeline 24 to maintain their operation. It is also possible to make the engines of the multiple warhead rockets mainly directly consume the liquid fuel and liquid oxidizer provided by the liquid oxidizer tank and the liquid fuel tank inside the multiple warhead rockets during this stage of operation, and the liquid fuel and liquid oxidizer from the main thrust rocket can supplement the liquid oxidizer tank and the liquid fuel tank inside the multiple warhead rockets through the external oxidizer delivery pipeline, the external fuel delivery pipeline, and the opened control valve or delivery pump.

[0067] When the low-altitude stage ends and the main thrust rocket stops providing upward thrust, according to the control system signal, the control valve or the delivery pump of the external delivery pipeline is closed, and the explosive bolts on the connecting rod of the connecting and releasing mechanism 14 connecting the multiple warhead rockets explode, disconnecting the connecting rod, ejecting the multiple warhead rockets, disconnecting the external delivery pipeline, and the separated main thrust rocket enters the falling or descending recovery stage. At this time, the liquid oxidizer tank and the liquid fuel tank inside the multiple warhead rockets are preferably full or substantially full, and the engines continue to work to provide thrust, and the multiple warhead rockets accelerate upward respectively until the payloads are sent into their respective orbits.

[0068] Embodiment 2 (reference Figure 3 ) is a multi-stage launch vehicle system similar to Embodiment 1. The liquid fuel main thrust rocket 11 is connected in parallel with two or more identical liquid fuel multiple warhead rockets 12 symmetrically distributed. The payloads 13 are respectively located at the tops of the multiple warhead rockets 12. There is a connecting and releasing mechanism 14 similar to that in Embodiment 1 between the main thrust rocket and the multiple warhead rockets. This mechanism can be a connecting rod connected by explosive bolts. The rocket has its own engine, propellant, control system, and servo mechanism. The main thrust rocket has a liquid oxidizer tank and a liquid fuel tank for itself, which are connected to the main thrust rocket engine through a liquid fuel or liquid oxidizer delivery pipeline 26, a control valve (not shown in the figure), and a delivery pump (not shown in the figure), and supply liquid fuel A and liquid oxidizer A to it during its operation.

[0069] The difference between Example 2 and Example 1 is that the staged rockets use different liquid fuel B and liquid oxidizer B from the main thrust rocket. Inside the main thrust rocket, there are also a sub-tank 31 for storing liquid oxidizer B and a sub-tank 32 for storing liquid fuel B located at the end. The external delivery pipelines of the staged rockets are connected to the liquid oxidizer sub-tank and the liquid fuel sub-tank of the main thrust rocket.

[0070] In the low-altitude stage, the control valve or the delivery pump is opened to open the external oxidizer delivery pipeline 23 and the external fuel delivery pipeline 24, providing liquid fuel B and liquid oxidizer B from the sub-tanks of the main thrust rocket for the engines of the staged rockets to maintain their operation. It is also possible to make the engines of the staged rockets mainly directly consume the liquid fuel B and liquid oxidizer B provided by the internal liquid oxidizer tank and liquid fuel tank of the staged rockets during this stage of operation, and the liquid fuel B and liquid oxidizer B from the sub-tanks of the main thrust rocket replenish the internal liquid oxidizer tank and liquid fuel tank of the staged rockets through the external oxidizer delivery pipeline, the external fuel delivery pipeline, and the opened control valve or delivery pump. After the main thrust rocket stops providing upward thrust at the end of the low-altitude stage, the operations in the high-altitude stage of this Example 2 are the same as or similar to those of Example 1.

[0071] Example 3 (reference Figure 4 ) is a multi-stage launch vehicle system approximately the same as Example 2, but its main thrust rocket is a solid fuel main thrust rocket 42, which uses a solid fuel rocket engine including a solid propellant grain 41, a combustion chamber, a nozzle assembly, and an ignition device, etc. The propellant grain is a hollow cylinder made of a propellant and a small amount of additives (the hollow part is the combustion surface, and its cross-sectional shape can be circular, star-shaped, etc.). The propellant grain is placed in the combustion chamber (generally the engine casing), and a heat insulation lining is installed between it and the combustion inner wall. The ignition device is used to ignite the propellant grain to generate gas, which is expanded and accelerated through the nozzle to generate thrust. After the propellant grain burns out, the engine stops working.

[0072] Two identical liquid fuel staged rockets 12 symmetrically distributed are connected in parallel to the solid fuel main thrust rocket 42, and the payloads 13 are respectively located at the tops of the staged rockets 12. There is a connection and release mechanism 14 similar to that in Example 1 between the main thrust rocket and the staged rockets. This mechanism can be a connecting rod connected by an explosive bolt. The rocket has its own engine, propellant, control system, and servo mechanism. The main thrust rocket has a solid fuel engine with a solid propellant grain 41 of the engine.

[0073] Above the solid propellant grain 41 inside the main thrust rocket, there are also a sub-tank for storing liquid oxidizer and a sub-tank for storing liquid fuel. The external delivery pipelines of the staged rockets are connected to the liquid oxidizer sub-tank and the liquid fuel sub-tank of the main thrust rocket.

[0074] During takeoff, the solid fuel main propulsion rocket 42 ignites and operates, entering the low-altitude stage. The control valve or transfer pump is opened, and the external oxidant transfer pipeline 23 and the external fuel transfer pipeline 24 are opened to supply liquid fuel and liquid oxidant from the sub-tank of the solid fuel main propulsion rocket to the engines of the multiple guided rockets to maintain their operation. It is also possible to make the engines of the multiple guided rockets mainly directly consume the liquid fuel and liquid oxidant provided by the internal liquid oxidant tank and liquid fuel tank of the multiple guided rockets during operation at this stage, and the liquid fuel and liquid oxidant from the sub-tank of the main propulsion rocket are used to supplement the internal liquid oxidant tank and liquid fuel tank of the multiple guided rockets through the external oxidant transfer pipeline, the external fuel transfer pipeline, and the opened control valve or transfer pump.

[0075] At the end of the low-altitude stage, the operation after the solid fuel of the main propulsion rocket stops providing upward thrust is similar to that of Embodiment 1. At this time, according to the control system command, the control valve or transfer pump of the external transfer pipeline is closed, and the explosive bolts on the connecting rod of the connecting and releasing mechanism 14 connecting the multiple guided rockets explode, disconnecting the connecting rod, ejecting the multiple guided rockets, disconnecting the external transfer pipeline, and the separated solid fuel main propulsion rocket enters the falling or descending recovery stage. At this time, the multiple guided rockets enter the high-altitude stage. It is preferable that the internal liquid oxidant tank and liquid fuel tank are in a full or basically full state. The engines continue to operate to provide thrust, and two or more multiple guided rockets accelerate upward respectively until the payloads are sent into their respective orbits respectively.

[0076] Embodiment 4 (refer to Figure 5 A) is a multi-stage launch vehicle system similar to Embodiment 1 or 2 or 3. There are 4 multiple guided rockets connected in parallel around the main propulsion rocket, located at symmetrical positions with the main propulsion rocket as the axis. Each multiple guided rocket includes a payload that can have the same weight or the same engine thrust, and the angles between their respective central axes and the line connecting the central axis of the main propulsion rocket are each 90 degrees.

[0077] Embodiment 5 (refer to Figure 5 B) is a multi-stage launch vehicle system similar to Embodiment 1 or 2 or 3. There are 3 multiple guided rockets connected in parallel around the main propulsion rocket, located at symmetrical positions with the main propulsion rocket as the axis. Each multiple guided rocket includes a payload that can have the same weight or the same engine thrust, and the angles between their respective central axes and the line connecting the central axis of the main propulsion rocket are each 120 degrees.

[0078] Embodiment 6 (refer to Figure 6) is a multi-stage launch vehicle system. The four guided rockets connected to the main propulsion rocket 11 have different weights and are not all located at symmetric positions relative to the axis of the main propulsion rocket. Among them, the smaller guided rocket 63 is farther away from the main propulsion rocket, and its connecting and releasing mechanism 67 is longer. The larger guided rockets 64, 65, and 66 are closer to the main propulsion rocket, and their respective connecting and releasing mechanisms 14 are shorter. This can make the total mass center of each guided rocket located at or near the axis of the main propulsion rocket. It is also possible to make the resultant force center of the thrusts of the engines of each guided rocket located at or near the axis of the main propulsion rocket, which is beneficial to the stability of the attitude or flight direction of this rocket system.

[0079] When needed, the main propulsion rocket 11 of this embodiment can be connected with two booster rockets 61 on the side. There is a connecting and releasing mechanism between the main propulsion rocket and the booster rockets, and this mechanism includes a connecting rod connected by an explosive bolt. The two booster rockets have the same weight and thrust and are symmetrically distributed on both sides of the main propulsion rocket, which can make the total mass center and thrust center of each booster rocket located at or near the axis of the main propulsion rocket. This is also beneficial to the stability of the attitude or flight direction of this rocket system.

[0080] When the resultant force line of the thrusts of the main propulsion rocket and the engines of multiple guided rockets or the thrusts of the booster rockets deviates from the total mass center of this multi-stage rocket system, the thrust or rudder of the engines of some rockets can be adjusted during operation.

[0081] Example 7 (reference Figure 7 ) is a multi-stage launch vehicle system. The main propulsion rocket is connected with a guided rocket 12 and a booster rocket 61 on the side. There is a connecting and releasing mechanism between the main propulsion rocket and the booster rocket. When this rocket system rises to a certain height, the main propulsion rocket separates from the booster rocket that has completed the boosting task. This booster rocket 61 uses a liquid propellant rocket engine or a solid propellant rocket engine; when using a liquid propellant rocket engine, it is equipped with a liquid propellant system including a liquid propellant tank, a propellant delivery pipeline, and a control valve. This liquid propellant system can be equipped with a propellant delivery pump when necessary.

[0082] When needed, this booster rocket can have the ability to support the liquid propellant system of the guided rocket. For this purpose, this booster rocket 61 can have a liquid propellant tank inside or a liquid propellant sub-tank on the top. At the same time, the liquid propellant system of the guided rocket 12 has an external propellant delivery pipeline, which is either connected to the liquid propellant tank of the booster rocket or connected to the liquid propellant sub-tank on the top of the booster rocket.

[0083] When takeoff or ascent is required, the control valve or transfer pump is opened, and liquid fuel and liquid oxidizer from the booster rocket tank or sub-tank are supplied to the engines of the multiple independently targetable rockets through the external oxidizer transfer pipeline and the external fuel transfer pipeline to maintain their operation. Alternatively, during this stage of operation, the engines of the multiple independently targetable rockets can mainly directly consume the liquid fuel and liquid oxidizer provided by the internal liquid oxidizer tank and liquid fuel tank of the multiple independently targetable rockets, and the liquid fuel and liquid oxidizer from the booster rocket tank or sub-tank are used to supplement the internal liquid oxidizer tank and liquid fuel tank of the multiple independently targetable rockets through the external oxidizer transfer pipeline, the external fuel transfer pipeline, and the opened control valve or transfer pump.

[0084] After the booster rocket engine stops providing upward thrust, according to the control system command, the control valve or transfer pump of the external transfer pipeline is closed, and the explosive bolts on the connecting rod of the connecting and releasing mechanism 14 connecting the booster rocket explode, disconnecting the connecting rod, ejecting the booster rocket, disconnecting the external transfer pipeline, and the booster rocket separated from the main booster rocket enters the falling or descending recovery stage. At this time, the multiple independently targetable rockets either continue to ascend together with the main booster rocket, and the main booster rocket continues to or starts to or continuously or intermittently supply propellant to the engines or propellant tanks of the multiple independently targetable rockets. Later, the multiple independently targetable rockets separate from the main booster rocket that has stopped providing upward power and enter the altitude stage. Its internal liquid oxidizer tank and liquid fuel tank are preferably full or substantially full, and the engines continue to operate to provide thrust, and the multiple independently targetable rockets accelerate upward respectively until the payloads are sent into their respective orbits respectively.

[0085] Example 8 (reference Figure 8 ) is a multi-stage launch vehicle system similar to Example 1. Two symmetrically distributed and identical liquid fuel multiple independently targetable rockets 12 are connected in parallel to the liquid fuel main booster rocket 11, and the payloads 13 are respectively located at the tops of the multiple independently targetable rockets 12. The difference is that there is a sub-stage rocket 81 or a second-stage rocket with a payload 82 above the top of the main booster rocket 11. When the multiple independently targetable rockets separate from the main booster rocket at the beginning of the altitude stage, the sub-stage rocket also separates from the main booster rocket 11 that has stopped providing upward thrust, its engine ignites, and it independently provides thrust to send the self-carried payload 82 to the predetermined position. The engine of the sub-stage rocket does not provide thrust during the low-altitude stage of the operation of this launch vehicle system.

[0086] The main booster rocket and the sub-stage are connected by a connecting member with a ring-shaped explosive cord. At the beginning of the altitude stage, the ring-shaped explosive cord detonates according to the control system command, the connecting member disconnects, and the main booster rocket separates from the sub-stage rocket.

[0087] Embodiment 9 (refer to the figure) is a parallel multi-stage launch vehicle system similar to Embodiment 1. The difference is that some of the guided rockets have their own sub-rockets at the top. The sub-rocket engines start when the guided rocket engines stop providing thrust, and can send the payloads into higher orbits respectively.

[0088] Embodiment 10 is a parallel multi-stage launch vehicle system similar to Embodiment 1 or Embodiment 7. Its feature is that during the operation, the main launch rocket or the booster rocket detaches from the guided rocket or the main launch rocket and performs a soft landing recovery in a controllable state. When the falling rocket body is close to the ground, the rocket engine is started again to decelerate and land.

Claims

1. A multistage launch vehicle system for pushing a payload into a high orbit in two successive stages, namely a low-altitude stage and a high-altitude stage, comprising: A main rocket located at the center of the rocket system, which provides the main thrust or maximum thrust for the whole system during the low-altitude stage; multiple sub-guided rockets with liquid propellants and engine systems, located side by side around the main rocket and connected to it; payloads are respectively located on the tops of the sub-guided rockets; there is a connecting and releasing mechanism between the main rocket and the sub-guided rockets; each sub-guided rocket not only separates from the main rocket that stops providing upward thrust during the high-altitude stage and independently provides thrust to send the payload to the predetermined position, but also provides thrust in the same direction as the main rocket during the low-altitude stage; The main rocket is a rocket using a liquid-propellant engine or a rocket using a solid-propellant engine with a liquid-propellant sub-tank; The liquid-propellant and engine system of the sub-guided rocket has an external propellant delivery pipeline, which is connected to the liquid-propellant tank in the main rocket using a liquid-propellant rocket engine or the liquid-propellant sub-tank of the main rocket through this pipeline; When each sub-guided rocket starts its engine and accelerates together with the main rocket during the low-altitude stage, its liquid-propellant and engine system can obtain propellant supply or replenishment from either the liquid-propellant system of the main rocket or the liquid-propellant sub-tank of the main rocket via the external propellant delivery pipeline, so that at the beginning of the high-altitude stage, the propellant tank of its liquid-propellant and engine system is in a state of being full or mostly full of propellant.

2. The multi-stage launch vehicle system according to claim 1, wherein the liquid-propellant system of the sub-guided rocket has a propellant delivery pipeline connecting its own rocket engine and the internal propellant tank, and at the same time has an interface connecting the external propellant delivery pipeline to its own rocket engine or connecting the external propellant delivery pipeline to its own propellant tank.

3. The multi-stage launch vehicle system according to claim 1, wherein the main rocket has a liquid-propellant sub-tank at the top or other parts, which is isolated from other liquid-propellant tanks in the main rocket and can store a liquid propellant different from that of other tanks but the same as that of the sub-guided rockets.

4. The multi-stage launch vehicle system according to claim 1, wherein during the low-altitude stage of the multi-stage rocket taking off, accelerating and ascending, the engines of the main rocket and the sub-guided rockets both provide lift until the main rocket completes the lift-providing task, separates from the sub-guided rockets, and enters the falling or descending recovery stage, while the engines of the sub-guided rockets continue to work to provide power to push the payload to continue ascending.

5. The multi-stage launch vehicle system according to claim 1, wherein the main rocket is connected with booster rockets on the side, and there is a connecting and releasing mechanism between the main rocket and the booster rockets.

6. The multi-stage launch vehicle system according to claim 1, wherein the total mass center or centroid of the total mass of all sub-guided rockets, including the internal propellants and the payloads above, is located at or near the axis of the main rocket, and the total mass of all sub-guided rockets includes the internal propellants and the payload masses of each sub-guided rocket.

7. The multi-stage launch vehicle system according to claim 1, wherein in the separately guided multi-stage launch vehicle system, the resultant force line of the thrusts of the multiple separately guided rocket engines connected to the main thrust rocket is located on or near the central axis of the main thrust rocket.

8. The multi-stage launch vehicle system according to claim 1, wherein in the separately guided multi-stage launch vehicle system, the resultant force line of the thrusts of the engine of the main thrust rocket and the multiple separately guided rockets connected thereto is kept consistent with or close to the total mass center of the rocket system.

9. The multi-stage launch vehicle system according to claim 1, wherein there may be a sub-stage rocket or a second-stage rocket with a payload above the top of the main thrust rocket, which separates from the main thrust rocket that stops providing upward thrust during the altitude stage and independently provides thrust to send the self-carried payload to a predetermined position.

10. A method for operating the multi-stage launch vehicle system according to claim 1, comprising: In the low-altitude stage of the multi-stage rocket taking off and accelerating into the sky, the engines of both the main thrust rocket and the separately guided rockets can participate in providing lift until the main thrust rocket completes the lift-providing task, separates from the separately guided rockets, and enters the falling or descending recovery stage, while the separately guided rocket engines can continue to work to provide power to push the payload to continue ascending into the sky; wherein in the low-altitude stage, each separately guided rocket liquid propellant system can obtain or receive the supply or replenishment of propellant from the liquid propellant system of the main thrust rocket, or from the liquid propellant sub-tank of the main thrust rocket, or from the liquid propellant system of the booster rocket, or from the liquid propellant sub-tank at the top of the booster rocket via an external propellant delivery pipeline.

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