Divided-guiding multi-stage carrier rocket system

Abstract

A split-guide multistage 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 split-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; each branch guide rocket liquid propellant and engine system can obtain or come from a liquid propellant system of the self-propelled rocket or come from propellant supply or supplement of a liquid propellant sub-storage tank of the self-propelled rocket through an external propellant conveying pipeline. 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 theory of space exploration based on rocket engines in the early 20th century, space exploration technology has made great progress. In order to allow rockets to ascend to high altitudes or enter space smoothly, most countries use multi-stage launch vehicles. Multi-stage rockets have multiple single-stage rockets, each with its own engine, propellant, control system and servo mechanism. These single-stage rockets are generally composed of 2 or 3 stages in series. When necessary, a first-stage rocket has multiple boosters in parallel to increase thrust to accelerate it to the predetermined launch speed before detaching.

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

[0004] The purpose of this technology is to provide a new multi-stage launch vehicle technology, which can not only greatly improve the flexibility of transporting separate guided-missile 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] The present technology proposes a multi-stage launch vehicle system for pushing a payload into a high orbit through two stages, low-range and high-range, comprising: a main thrust rocket located in the center of the rocket system and providing the main thrust or maximum thrust of the entire system in the low-range stage, a plurality of sub-target rockets with liquid propellant and engine systems located around the main thrust rocket and connected in parallel with it, the payload is respectively located on the top of each sub-target rocket, and a connection and release mechanism is provided between the main thrust rocket and the sub-target rockets. Each sub-target rocket not only separates from the main thrust rocket that stops providing upward thrust in the high-range stage and provides thrust alone to deliver the payload to a predetermined position, but also provides thrust in the same direction as the main thrust rocket in the low-range 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] The main rocket using a liquid propellant engine may or may not have a liquid propellant sub-tank inside or on top.

[0012] Each of the independently guided rockets uses a liquid propellant rocket engine and may be provided with a liquid propellant system including a propellant tank, a propellant delivery pipeline and a control valve. The liquid propellant system may be provided with a propellant delivery pump when necessary.

[0013] 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 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;

[0014] The multiple pilot rockets located around the main rocket and connected in parallel with it may be 2 or 3 or more.

[0015] The main rocket may use an engine with a different liquid propellant from that of the pilot rocket.

[0016] The said independently targetable reentry vehicle system, wherein the said main rocket may have a liquid propellant sub-tank at the top or other position, which may be isolated from other liquid propellant tanks in the main rocket and may store liquid propellant different from other tanks but the same as that of the independently targetable reentry vehicles;

[0017] The main propulsion rocket may use a solid fuel engine. The solid rocket engine may be composed of a grain column, a combustion chamber, a nozzle assembly, an ignition device, etc. The main propulsion rocket may have a liquid propellant sub-tank at the top or other parts, which is isolated from the solid propellant in the main propulsion rocket;

[0018] The main propulsion rocket may be connected to a booster rocket at the side, and a connection release mechanism may be provided between the main propulsion rocket and the booster rocket. The booster rocket may use a liquid propellant rocket engine or a solid propellant rocket engine; when a liquid propellant rocket engine is used, it is provided with a liquid propellant system including a liquid propellant tank, a propellant delivery pipeline, a control valve or a propellant delivery pump.

[0019] The top of the booster rocket may or may not have a liquid propellant sub-tank. The liquid propellant system of the independently targetable rocket has an external propellant delivery pipeline, which can be connected to the liquid propellant tank in the booster rocket using a liquid propellant rocket engine or to the liquid propellant sub-tank of the booster rocket. The sub-tank can be located on the upper part or top of the booster rocket.

[0020] The liquid propellant, liquid propellant tank, liquid propellant sub-tank, control valve, propellant delivery pipeline, and propellant delivery pump can be liquid fuel or liquid oxidant, liquid fuel or liquid oxidant tank, liquid fuel or liquid oxidant sub-tank, liquid fuel or liquid oxidant control valve, liquid fuel or liquid oxidant delivery pipeline, and liquid fuel or liquid oxidant delivery pump, respectively.

[0021] During the low-range phase of a multi-stage rocket's takeoff acceleration, the engines of both the main rocket and the pilot rocket can provide lift until the main rocket completes its lift-providing mission and separates from the pilot rocket to enter the falling or descent recovery phase, while the pilot rocket's engine can continue to work and provide power to push the payload into the air.

[0022] It can be arranged that: when each guided rocket starts its engine at the low-range stage and accelerates together with the main rocket and the booster rocket, its liquid propellant system can be supplied or supplemented with propellant from the liquid propellant system of the main rocket, from the liquid propellant sub-tank of the main rocket, from the liquid propellant system of the booster rocket, or from the liquid propellant sub-tank on the top of the booster rocket through the external propellant delivery pipeline;

[0023] The main rocket may use an engine with a different liquid propellant from that of the pilot rocket.

[0024] The said independently targetable reentry vehicle system, wherein the said main rocket has a liquid propellant sub-tank at the top or other position, which is isolated from other liquid propellant tanks in the main rocket and can store liquid propellant different from other tanks but the same as that of the independently targetable reentry vehicles;

[0025] The main propulsion rocket may use a solid fuel engine, and its solid rocket engine may be composed of a grain column, a combustion chamber, a nozzle assembly, an ignition device, etc., and may have a liquid propellant sub-tank at the top or other parts, which is isolated from the solid propellant in the main propulsion rocket;

[0026] The booster rocket may use an engine that uses a different liquid fuel than the MIRV.

[0027] The described MIRV system, wherein the booster rocket has a liquid propellant sub-tank at the top or other position, which is isolated from other liquid propellant tanks in the booster rocket and can store liquid propellant that is different from other tanks but the same as that of the MIRV.

[0028] The booster rocket may use a solid fuel engine.

[0029] The described MIRV system, wherein the booster rocket may have a liquid propellant sub-tank at the top or other position, which is isolated from the solid propellant in the booster rocket.

[0030] The described independently targetable launch vehicle system, wherein the top liquid propellant tank of the main rocket or the booster rocket can be located inside the rocket shell or above the rocket shell and have a fairing.

[0031] The described independently targetable reentry vehicle system, wherein the connection and release mechanism between the main rocket and the independently targetable reentry vehicles comprises: a connecting rod or a frame connecting the main rocket and the independently targetable reentry vehicles, and an explosive bolt or an explosive cord fixing or contacting the connecting rod or the frame.

[0032] When the main rocket and the pilot rocket need to separate during the ascent flight process, the control device activates the explosive bolts or explosive cords to explode, causing the connecting rod or frame to lose its connection ability, and the pilot rocket separates from the main rocket and continues to accelerate its flight.

[0033] The connection distances between each independently guided rocket and the main rocket are not the same, and the widths or lengths of the connection release mechanisms are not the same.

[0034] The described multi-stage launch vehicle system, in which the multiple independently targetable reentry vehicles located around the main rocket and connected in parallel with it, can be located in symmetrical positions with the main rocket as the axis, and each independently targetable reentry vehicle including its payload can have the same weight or the same engine thrust.

[0035] The said MIRV system, wherein the said multiple MIRVs connected to the main rocket are not all located at symmetrical positions corresponding to the axis of the main rocket, but the total mass of all MIRVs including the total mass center or mass center of the internal propellant and the payload thereon is located at or close to the axis of the main rocket;

[0036] The total mass of all the independently targetable rockets includes the mass of the propellant inside each independently targetable rocket and the payload thereon.

[0037] The described independently targetable reentry vehicle system, wherein the resultant line of thrust of the multiple independently targetable reentry vehicles engines connected to the main rocket is located at or close to the central axis of the main rocket.

[0038] The described independently targetable reentry vehicle system, wherein the resultant line of thrust of the multiple independently targetable reentry vehicle engines connected to the main thrust rocket is located at or close to the total mass center of the independently targetable reentry vehicle.

[0039] In the described MIRV system, when the resultant force line of the thrusts of the engines of the multiple MIRVs deviates from the total mass center of the MIRVs, the thrusts or rudders of the engines of some rockets can be adjusted during operation.

[0040] The described independently targetable reentry vehicle system, wherein the resultant line of the engine thrust of the main rocket and the multiple independently targetable reentry vehicles connected thereto is consistent with or close to the total mass center of the rocket system.

[0041] In the described multi-stage launch vehicle system, when the resultant line of the engine thrust of the main rocket and the multiple independently guided rockets connected thereto deviates from the total mass center of the rocket system, the thrust or rudder of the engine of some rockets can be adjusted during operation.

[0042] The described independently targetable launch vehicle system, wherein the resultant line of thrust of the main rocket and its connected multiple independently targetable launch vehicles and the engine thrust including or excluding the booster rocket is consistent with or close to the total mass center of the rocket system.

[0043] In the described multi-stage launch vehicle system, when the resultant line of thrust of the main rocket and its connected multiple independently guided rockets and the engines including or excluding the booster rocket 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] In the described MIRV system, when the resultant line of thrust of the main rocket and its connected multiple MIRVs and engines including or excluding the booster rocket deviates from the total mass center of the rocket system, the thrust or rudder of the main rocket engine can be adjusted first during operation, and when necessary, the thrust or rudder of the engines of the MIRVs can be adjusted simultaneously or instead.

[0045] In the described MIRV system, when the resultant line of thrust of the main rocket and its connected multiple MIRVs and engines including or excluding the booster rocket deviates from the total mass center of the rocket system, the thrust or rudder of some engines of the MIRVs can be adjusted first during operation, and when necessary, the thrust or rudder of the main rocket engine can be adjusted simultaneously or instead.

[0046] When the resultant line of the engine thrust is biased toward one side of the total mass center of the rocket system, it is necessary to reduce the thrust of the engine of the independently targetable rocket part on that side, or increase the thrust of the engine of the independently targetable rocket part on the opposite side.

[0047] The described MIRV system, wherein the MIRV itself can be composed of two stages, the lower stage first provides thrust to push the upper stage, and after the lower stage is separated, the upper stage works to push the payload.

[0048] The described independently targetable reentry vehicle system, in which a sub-stage rocket or a second-stage rocket carrying a payload can be arranged on top of the main rocket, which separates from the main rocket that stops providing upward thrust during the altitude phase and independently provides thrust to deliver its own payload to a predetermined location.

[0049] The second-stage sub-rocket of the existing multi-stage rocket completely relies on the thrust of the first-stage main rocket to rise in the low-range stage, while this technology is equivalent to the sub-guided rocket of the second-stage sub-rocket. On the one hand, it can play the role of part or all of the bundled booster rocket in the low-range stage, improve the total thrust and acceleration of the multi-stage rocket in the low-range stage, increase the speed or total weight of the sub-guided rocket or the second-stage sub-rocket at the end of the low-range stage, and improve the carrying capacity or efficiency of the entire multi-stage rocket system. On the other hand, it can enter the sub-guided carrying mode in advance in the high-range stage, greatly improving the flexibility of the payload to enter very different orbits; this technology can also significantly shorten the overall height or length of the multi-stage rocket system, reduce the stringent requirements for the launch rack or launch platform, for example, it can use a shorter ocean platform, land platform or device, making the launch more stable and convenient, and reducing the cost. This innovation can bring significant progress and outstanding practical effects to space launch technology. BRIEF DESCRIPTION OF THE DRAWINGS

[0050] Figure 1 This is a schematic diagram of the operation of the multi-stage rocket system of Example 1 of the present invention, wherein A is the low-range stage and B is the high-range stage;

[0051] Figure 2 It is a partial cross-sectional schematic diagram of a multi-stage rocket system of Example 1 of the present invention;

[0052] Figure 3It is a partial cross-sectional schematic diagram of a multi-stage rocket system of Example 2 of the present invention;

[0053] Figure 4 It is a partial cross-sectional schematic diagram of a multi-stage rocket system of Example 3 of the present invention;

[0054] Figure 5 A is a schematic cross-sectional view of the layout of a multi-stage rocket system in Example 4 of the present invention;

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

[0056] Figure 6 It is a schematic cross-sectional view of the layout of a multi-stage rocket system according to Embodiment 6 of the present invention;

[0057] Figure 7 This is a schematic diagram of a multi-stage rocket system according to Embodiment 7 of the present invention;

[0058] Figure 8 This is a schematic diagram of a multi-stage rocket system according to Example 8 of the present invention.

[0059] Among them, 11 is the main rocket, 12 is the MIRV, 13 is the payload, 14 is the MIRV connection and release mechanism, 21 is the liquid oxidizer tank, 22 is the liquid fuel tank, 23 is the external oxidizer delivery pipeline, 24 is the external fuel delivery pipeline, 25 is the MIRV engine, 26 is the oxidizer delivery pipeline, 31 is the liquid oxidizer sub-tank, 32 is the liquid fuel sub-tank, 41 is the rocket engine solid grain, 42 is the solid fuel main rocket, 61 is the booster rocket, 62 is the booster rocket connection and release mechanism, 63 is the MIRV one, 64 is the MIRV two, 65 is the MIRV three, 66 is the MIRV four, 67 is the connection and release mechanism of the MIRV one and 63, 81 is the sub-stage rocket, and 82 is the payload of the sub-stage rocket.

[0060] Specific implementation method

[0061] The following is a detailed description with reference to the accompanying drawings.

[0062] Example 1 (reference Figure 1 , Figure 2 ) is a multi-stage launch vehicle system, wherein a liquid fuel main rocket 11 is connected in parallel with two or more symmetrically distributed sub-guided rockets 12 of the same liquid fuel, and a payload 13 is located on the top of each sub-guided rocket 12, and a connecting release mechanism 14 is provided between the main rocket and the sub-guided rocket, which can be a connecting rod connected by an explosive bolt. This explosive bolt is hollow and contains explosives inside. When powered on, it will explode and break the bolt, disconnect the connecting rod, and separate the booster rocket from the sub-guided rocket. The rocket has its own engine, propellant, control system and servo mechanism.

[0063] The main rocket has a liquid oxidizer tank 21 and a liquid fuel tank 22 inside, which are connected to the main 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 provide liquid fuel and liquid oxidizer to the main rocket engine when it is working.

[0064] The liquid oxidizer tank 21 and liquid fuel tank 22 of the main rocket are also connected to the independently guided rocket engine 25, or connected to the liquid oxidizer tank and liquid fuel tank inside the independently guided rocket, 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 rocket or the independently guided rocket, to provide liquid fuel and liquid oxidizer when needed.

[0065] This launch vehicle system needs to push the payload into high orbit through two stages successively at low range and altitude. In the low range stage, the main thrust rocket and the engines of the parallel-connected guided rockets are ignited respectively to accelerate the whole rocket system to high altitude. At this moment, the control valve (not shown) or the transfer pump can be opened, and the liquid fuel and liquid oxidant provided from the main thrust rocket can be provided for the engines of the guided rockets by the external oxidant delivery pipeline 23 and the external fuel delivery pipeline 24, so as to maintain its work. The liquid fuel and liquid oxidant provided by the internal liquid oxidant tank and the liquid fuel tank of the guided rocket can also be directly consumed when the engines of the guided rockets work at this stage, and by the liquid fuel and liquid oxidant from the main thrust rocket, the internal liquid oxidant tank and the liquid fuel tank of the guided rocket are supplemented by the external oxidant delivery pipeline and the external fuel delivery pipeline and the control valve or the transfer pump opened.

[0066] When the low-range stage ends and the main rocket stops providing ascent thrust, the control valve or delivery pump of the external delivery pipeline is closed according to the control system signal, and the explosive bolts on the connecting rod of the connection release mechanism 14 connected to the sub-recommendation rocket explode, so that the connecting rod is disconnected, the sub-recommendation rocket is ejected, the external delivery pipeline is disconnected, and the separated main rocket enters the falling or descending recovery stage. At this time, the liquid oxidizer tank and liquid fuel tank inside the sub-recommendation rocket are preferably full or basically full, the engine continues to work to provide thrust, and the sub-recommendation rockets accelerate their ascent respectively until the payloads are sent into their respective orbits.

[0067] Example 2 (reference Figure 3) is a multi-stage launch vehicle system similar to Example 1, wherein a liquid fuel main rocket 11 is connected in parallel with two or more symmetrically distributed sub-guided rockets 12 of the same liquid fuel, and a payload 13 is respectively located on the top of each sub-guided rocket 12, and a connecting release mechanism 14 similar to Example 1 is provided between the main rocket and the sub-guided rocket, and the mechanism can be a connecting rod connected by explosive bolts. The rocket has its own engine, propellant, control system and servo mechanism. The main rocket has its own liquid oxidant tank and liquid fuel tank inside, which are connected to the main rocket engine through a liquid fuel or liquid oxidant delivery pipeline 26, a control valve (not shown in the figure), and a delivery pump (not shown in the figure), and provide liquid fuel A and liquid oxidant A to it when it is working.

[0068] The difference between Example 2 and Example 1 is that the independently guided rocket uses liquid fuel B and liquid oxidizer B which are different from those of the main rocket. The main rocket also has a sub-tank for storing liquid oxidizer B and a sub-tank for storing liquid fuel B located at the end, and the external delivery pipeline of the independently guided rocket is connected to the liquid oxidizer sub-tank and liquid fuel sub-tank of the main rocket.

[0069] In the low-range stage, the control valve or the delivery pump is opened, the external oxidant delivery pipeline 23 and the external fuel delivery pipeline 24 are opened, and the liquid fuel B and the liquid oxidant B from the main rocket sub-tank are provided to the engines of the guided missile launchers to maintain their operation. It is also possible that the engines of the guided missile launchers are mainly directly consuming the liquid fuel B and the liquid oxidant B provided by the internal liquid oxidant tank and the liquid fuel tank of the guided missile launcher during operation at this stage, and the liquid fuel B and the liquid oxidant B from the main rocket sub-tank are replenished to the internal liquid oxidant tank and the liquid fuel tank of the guided missile launcher through the external oxidant delivery pipeline and the external fuel delivery pipeline and the opened control valve or the delivery pump. After the low-range stage ends and the main rocket stops providing the ascending thrust, the operation of the high-range stage is the same or similar to that of the embodiment 1.

[0070] Example 3 (reference Figure 4 ) is a multi-stage launch vehicle system similar to Example 2, but its main propulsion rocket is a solid-fuel main propulsion rocket 42, which uses a solid-fuel rocket engine including a solid charge 41, a combustion chamber, a nozzle assembly and an ignition device.

[0071] The solid fuel main rocket 42 is connected in parallel with two symmetrically distributed identical liquid fuel guided rockets 12, and the payload 13 is respectively located on the top of each guided rocket 12. There is a similar connection release mechanism 14 between the main rocket and the guided rocket, which can be a connecting rod connected by explosive bolts. The rocket has its own engine, propellant, control system and servo mechanism. The main rocket has a solid fuel engine with an engine solid grain 41.

[0072] There are also a sub-tank for storing liquid oxidizer and a sub-tank for storing liquid fuel above the solid powder column 41 inside the main propulsion rocket, and the external delivery pipeline of the guided missile is connected to the liquid oxidizer sub-tank and liquid fuel sub-tank of the main propulsion rocket.

[0073] During takeoff, the solid fuel main rocket 42 is ignited and enters the low-range stage, the control valve or the delivery pump is opened, the external oxidant delivery pipeline 23 and the external fuel delivery pipeline 24 are opened, and the engine of the guided rocket is provided with liquid fuel and liquid oxidant from the solid fuel main rocket sub-tank to maintain its operation. The engine of the guided rocket can also be made to directly consume the liquid fuel and liquid oxidant provided by the internal liquid oxidant tank and the liquid fuel tank of the guided rocket during operation at this stage, and the liquid fuel and liquid oxidant from the main rocket sub-tank are replenished to the internal liquid oxidant tank and the liquid fuel tank of the guided rocket through the external oxidant delivery pipeline and the external fuel delivery pipeline and the opened control valve or the delivery pump.

[0074] After the low-range stage is over and the main rocket solid fuel stops providing the lifting thrust, the operation of this embodiment is similar to that of embodiment 1. At this time, according to the control system instruction, the control valve or the delivery pump of the external delivery pipeline is closed, and the explosive bolt on the connecting rod of the connection release mechanism 14 connected to the guided missile is exploded, so that the connecting rod is disconnected, the guided missile is ejected, the external delivery pipeline is disconnected, and the separated solid fuel main rocket enters the falling or descending recovery stage. At this time, the guided missile enters the high-range stage, and its internal liquid oxidant tank and liquid fuel tank are preferably in a full or substantially full state, the engine continues to work to provide thrust, and the two or more guided missiles are accelerated to rise respectively until the payload is sent into their respective orbits.

[0075] Example 4 (reference Figure 5 A) is a multi-stage launch vehicle system similar to embodiment 1, 2 or 3, with a main rocket having four pilot rockets connected in parallel therewith, located at symmetrical positions with the main rocket as the axis, each pilot rocket including a payload having the same weight or engine thrust, and an angle between their respective central axes and a line connecting the central axis of the main rocket is 90 degrees.

[0076] Example 5 (reference Figure 5 B) is a multi-stage launch vehicle system similar to embodiment 1, 2 or 3, with the main rocket having three pilot rockets connected in parallel therewith, located at symmetrical positions with the main rocket as the axis, each pilot rocket including the payload may have the same weight or the same engine thrust, and the angle between their respective central axes and the line connecting the central axis of the main rocket is 120 degrees.

[0077] Example 6 (reference Figure 6 ) is a multi-stage launch vehicle system, and the four guided rockets connected to the main rocket 11 have different weights and are not all located in symmetrical positions relative to the axis of the main rocket. Among them, the smaller guided rocket 63 is farther away from the main rocket, and its connection release mechanism 67 is longer, while the larger guided rockets 64, 65, 66 are closer to the main rocket, and their connection release mechanisms 14 are shorter, so that the total mass center of each guided rocket can be located at or close to the axis of the main rocket. It is also possible to make the combined force center of the thrust of each guided rocket engine located at or close to the axis of the main rocket, which is conducive to the stability of the attitude or flight direction of the rocket system.

[0078] When necessary, the main rocket 11 of this embodiment can be connected to two booster rockets 61 on the side, and there is a connection release mechanism 62 between the main rocket and the booster rocket, which includes a connecting rod connected by an explosive bolt. The weight and thrust of the two booster rockets are the same, and they are symmetrically distributed on both sides of the main rocket, so that the total mass center and thrust center of each booster rocket can be located at or close to the axis of the main rocket. This is also conducive to the stability of the attitude or flight direction of the rocket system.

[0079] When the resultant line of thrust of the main rocket and multiple independently guided rocket engines or the thrust of the booster rocket deviates from the total mass center of the multi-stage rocket system, the thrust or rudder of the engine of some rockets can be adjusted during operation.

[0080] Example 7 (reference Figure 7 ) is a multi-stage launch vehicle system. The main rocket is connected to a pilot rocket 12 and a booster rocket 61 on the side. There is a connection release mechanism between the main rocket and the booster rocket. When the rocket system rises to a certain height, the main rocket is separated from the booster rocket that completes the boosting mission. The booster rocket 61 uses a liquid propellant rocket engine or a solid propellant rocket engine. When a liquid propellant rocket engine is used, it is equipped with a liquid propellant system including a liquid propellant tank, a propellant delivery pipeline and a control valve. The liquid propellant system can be equipped with a propellant delivery pump when necessary.

[0081] When necessary, the booster rocket can have the ability to support the liquid propellant system of the independently targetable reentry rocket. To this end, the 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 independently targetable reentry rocket 12 has an external propellant delivery pipeline, which is either connected to the liquid propellant tank of the booster rocket or to the liquid propellant sub-tank on the top of the booster rocket.

[0082] When takeoff or ascent is required, the control valve or delivery pump is opened to provide the engine of the independently guided rocket with liquid fuel and liquid oxidizer from the booster rocket tank or sub-tank through the external oxidizer delivery pipeline and the external fuel delivery pipeline to maintain its operation. It is also possible to make the engine of the independently guided rocket mainly directly consume the liquid fuel and liquid oxidizer provided by the liquid oxidizer tank and liquid fuel tank inside the independently guided rocket during operation at this stage, and the liquid fuel and liquid oxidizer from the booster rocket tank or sub-tank are replenished to the liquid oxidizer tank and liquid fuel tank inside the independently guided rocket through the external oxidizer delivery pipeline and the external fuel delivery pipeline and the opened control valve or delivery pump.

[0083] After the booster rocket engine stops providing the ascending thrust, according to the control system instruction, the control valve or the delivery pump of the external delivery pipeline is closed, and the explosive bolt on the connecting rod of the link release mechanism 14 connected to the booster rocket explodes, so that the connecting rod is disconnected, the booster rocket is ejected, and the external delivery pipeline is disconnected, and the booster rocket separated from the main thrust rocket enters the falling or descending recovery stage. At this time, the sub-guided rocket or continues to rise together with the main thrust rocket, and the main thrust rocket continues or begins to provide propellant to the engine or propellant tank of the sub-guided rocket continuously or intermittently. Later, the sub-guided rocket is separated from the main thrust rocket that stops providing the ascending power and enters the altitude stage. Its internal liquid oxidant tank and liquid fuel tank are preferably in a full or substantially full state, and the engine continues to work to provide thrust, and the sub-guided rockets are accelerated to rise respectively until the payload is sent into their respective orbits.

[0084] Example 8 (reference Figure 8 ) is a multi-stage launch vehicle system similar to Example 1, wherein a liquid fuel main propulsion rocket 11 is connected in parallel to two symmetrically distributed liquid fuel sub-launching rockets 12, and a payload 13 is located on the top of each sub-launching rocket 12. The difference is that a sub-stage rocket 81 or a second-stage rocket with a payload 82 is located on the top of the main propulsion rocket 11. When the sub-launching rockets separate from the main propulsion rocket at the beginning of the altitude phase, the sub-stage rocket also separates from the main propulsion rocket 11 that stops providing upward thrust, and its engine ignites and provides thrust alone to deliver the self-carried payload 82 to a predetermined position. The sub-stage rocket engine does not provide thrust during the low-altitude phase of the launch vehicle system.

[0085] The main propulsion rocket and the sub-stage are connected by a connector with an annular explosive cord. At the beginning of the altitude phase, the annular explosive cord is detonated according to the command of the control system, the connector is disconnected, and the main propulsion rocket is separated from the sub-stage rocket.

[0086] Example 9 is a parallel multi-stage launch vehicle system similar to Example 1, with the difference being that some independently targetable reentry vehicles have their own sub-rocket at the top, and the sub-rocket engine is started when the independently targetable reentry vehicle engine stops providing thrust, and can send the payload into a higher orbit separately.

[0087] Embodiment 10 is a parallel multi-stage launch vehicle system similar to Embodiment 1 or Embodiment 7, wherein the main rocket or the booster rocket thereof is softly landed and recovered in a controllable state after being separated from the secondary launch vehicle or the main launch vehicle during operation.

Claims

1. A multi-stage launch vehicle system for pushing a payload into a high orbit in two stages, low range and high range, comprising: A main thrust rocket located in the center of the rocket system provides the main thrust or maximum thrust of the whole system in the low-range stage, and a plurality of guided missiles with liquid propellant and engine systems are located around the main thrust rocket and connected in parallel with it. The payload is located on the top of each guided missile. There is a connection release mechanism between the main thrust rocket and the guided missile. Each guided missile not only separates from the main thrust rocket that stops providing upward thrust in the high-range stage and provides thrust independently to deliver the payload to a predetermined position, but also provides thrust in the same direction as the main thrust rocket in the low-range stage. 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; 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; 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.

2. A multi-stage launch vehicle system according to claim 1, wherein the liquid propellant system of the independently targetable reentry vehicle has a propellant delivery pipeline connecting its own rocket engine and an internal propellant tank, and also has an interface for connecting an external propellant delivery pipeline with its own rocket engine or connecting an external propellant delivery pipeline with its own propellant tank.

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

4. A multi-stage launch vehicle system according to claim 1, wherein in the low-range stage of takeoff acceleration of the multi-stage rocket, the engines of the main rocket and the independent reentry rockets both provide lift until the main rocket completes the lift-providing task and separates from the independent reentry rockets to enter the falling or descent recovery stage, while the engines of the independent reentry rockets continue to work to provide power to push the payload to continue to rise.

5. The multi-stage launch vehicle system according to claim 1, wherein the main rocket uses a solid fuel engine.

6. A multi-stage launch vehicle system according to claim 5, wherein the main rocket has a liquid propellant sub-tank at the top or other part, which is isolated from the solid propellant in the main rocket.

7. A multi-stage launch vehicle system according to claim 1, wherein the main rocket is connected to a booster rocket at the side, and a connection and release mechanism is provided between the main rocket and the booster rocket.

8. A multi-stage launch vehicle system according to claim 1, wherein the resultant line of engine thrust of the main rocket and its connected multiple independently targetable launch vehicles is consistent with or close to the total mass center of the rocket system.

9. According to the multi-stage launch vehicle system as described in claim 1, when the resultant line of force of the engine thrust is biased toward one side of the total mass center of the rocket system, it is necessary to reduce the thrust of the engine of the multi-stage launch vehicle part located on that side, or increase the thrust of the engine of the multi-stage launch vehicle part located on the opposite side.

10. According to the multi-stage launch vehicle system of claim 1, there can be a sub-stage rocket or a second-stage rocket carrying a payload on top of the main rocket, which separates from the main rocket that stops providing upward thrust during the altitude stage and provides thrust alone to deliver its own payload to a predetermined position.

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