A novel variable-thrust rotating detonation space engine and its usage method

Abstract

The present invention discloses a novel variable-thrust rotating detonation space engine and a usage method thereof, which includes a rotating detonation combustion device, a jet panel, a connecting plate, a fuel solenoid valve, and an oxidizer solenoid valve; the rotating detonation combustion device includes three detonation combustion chambers arranged coaxially from outside to inside and all in a ring shape; the jet panel can respectively inject fuel and oxidizer into the three detonation combustion chambers; the connecting plate is installed on the outer side of the jet panel and can be used to install the fuel solenoid valve and the oxidizer solenoid valve; both the fuel solenoid valve and the oxidizer solenoid valve include a solenoid valve seat and a valve stem; the valve stem can axially move left and right within the solenoid valve seat, thereby realizing four thrust working modes. The present invention can, without decoupling the detonation wave, adopt three coaxially arranged ring-shaped detonation combustion chambers and an improved solenoid valve to precisely control the injection of propellant and the flow rate in the combustion chamber, so as to achieve the combined operation of different detonation combustion chambers, and further realize the function of continuous variable thrust of the space engine.

Description

Technical Field

[0001] The present invention relates to a space engine, in particular to a novel variable-thrust rotating detonation space engine and a usage method thereof. Background Art

[0002] Detonation combustion is an approximately constant-volume and highly efficient combustion form, which has the advantages of self-pressurization, low entropy increase, and high thermal cycle efficiency. A rotating detonation engine is one or more detonation waves propagating in an annular combustion chamber or an empty-barrel combustion chamber at a frequency of thousands to tens of thousands of hertz, generating high-temperature and high-pressure products. The products expand and are ejected axially to generate stable thrust. Compared with existing rocket engines and ramjet engines, etc., a rotating detonation combustion chamber has a simpler and more compact structure and higher thermal cycle efficiency. Higher thermal cycle efficiency can output more useful work, thereby improving the utilization rate of propellants, manifested as the engine having higher specific impulse and total impulse performance.

[0003] The power systems of existing spacecraft are mainly small rocket engines based on chemical propulsion. This power form that organizes combustion in a deflagration form to utilize chemical energy has approached its performance limit. Therefore, spacecraft with chemical propulsion have been difficult to achieve long-term on-orbit operation due to their current power status, and need to increase their propellant carrying capacity to meet higher orbit transfer and attitude control requirements. If the chemical attitude and orbit control engine is changed to a detonation combustion engine, the utilization rate of propellants and the specific impulse of the engine can be significantly improved, and the same velocity increment adjustment can be achieved with relatively less propellants, enabling the spacecraft to perform on-orbit maneuvers and attitude adjustments for a longer time, or having stronger capabilities such as rendezvous and docking, landing, and return.

[0004] In the context of increasingly complex space missions, the need to improve the performance of spacecraft engines is becoming more urgent, especially to enhance the variable-thrust ability of the engine. Compared with fixed-thrust engines, variable-thrust engines are crucial for tasks such as space control, space station rendezvous and docking, orbit descent, hovering, and soft landing, and return in lunar and deep-space exploration. For example, when a satellite adjusts its orbit, a variable-thrust engine can provide accurate thrust control to ensure that the satellite can accurately enter the predetermined orbit. During the spacecraft rendezvous and docking process, a variable-thrust engine can achieve precise adjustment of the relative position and attitude of the spacecraft to ensure the accuracy and stability of the docking process. A variable-thrust orbit control engine has the ability to quickly respond to thrust adjustment and can achieve rapid thrust change in case of sudden dangerous situations such as debris impact. In addition, during the process of the detector's orbit descent, deceleration, and hovering, a variable-thrust engine can provide appropriate thrust according to different stages to achieve the smooth landing of the detector and reduce the impact received during the descent process.

[0005] Based on the advantages of the chemical energy utilization form of rotating detonation combustion and the functional characteristics of variable thrust space engines, the two can be combined to form a new type of variable thrust rotating detonation space engine, which can achieve farther and more complex space missions with lower costs and higher performance. It is expected to greatly improve the performance and lifespan of spacecraft, and has broad prospects for application in the field of space propulsion.

[0006] Currently, engines used for experiments or tests in the form of rotating detonation combustion do not perform thrust adjustment under detonation combustion. To achieve a large range of thrust adjustment, it is necessary to achieve an adjustment of the mass flow rate from dozens of grams per second to nearly one kilogram per second. The current difficulty in the rotating detonation design for achieving a large range of thrust adjustment is that when the mass flow rate is adjusted over a large range, the detonation wave becomes unstable during propagation, and even the detonation wave decouples, turning into deflagration or extinction. The mass flow rate of the combustion chamber with a steadily propagating detonation wave can only be adjusted and verified within a small range of dozens of grams per second. Summary of the Invention

[0007] The technical problem to be solved by the present invention is to provide a new type of variable thrust rotating detonation space engine and its usage method in view of the above-mentioned deficiencies of the prior art. This new type of variable thrust rotating detonation space engine and its usage method can achieve a large range of thrust adjustment for a detonation engine without decoupling the detonation wave, by adopting the method of coaxially arranging three combustion chambers. Without increasing the number of combustion chambers, it is very difficult to achieve a large range of thrust adjustment under detonation combustion with only one detonation combustion chamber, so the number is increased to three. The engine has three annular detonation combustion chambers arranged coaxially, and at the same time, two improved, highly efficient and reliable solenoid valves and flow control valves are used to precisely control the injection of propellants into the combustion chamber and the size of the flow rate respectively, so as to achieve the combined operation of different detonation combustion chambers, and further realize the function of continuous variable thrust of the space engine. The solenoid valve used in this engine is an improved solenoid valve based on a three-position four-way solenoid valve. To achieve the purpose of rapid response of the variable thrust rotating detonation engine, this engine uses self-igniting propellants. It solves the problem that under the condition of stable propagation of the current detonation wave, it is impossible to achieve a large range of adjustment of the propellant mass flow rate, that is, a large range of thrust adjustment.

[0008] To solve the above technical problems, the technical solution adopted by the present invention is:

[0009] A new type of variable thrust rotating detonation space engine, comprising a rotating detonation combustion device, a jet injection panel, a connecting plate, a fuel solenoid valve, and an oxidizer solenoid valve.

[0010] The rotating detonation combustion device includes a first detonation combustion chamber, a second detonation combustion chamber, and a third detonation combustion chamber that are coaxially arranged in sequence from the outside to the inside and are all annular.

[0011] The injection panel is arranged on the injection end face of the rotating detonation combustion device, and can inject fuel and oxidant into the detonation combustion chamber one, the detonation combustion chamber two and the detonation combustion chamber three respectively.

[0012] The connecting plate is installed on the outer side of the injection panel and can be used to install the fuel solenoid valve and the oxidizer solenoid valve.

[0013] Both the fuel solenoid valve and the oxidizer solenoid valve include a solenoid valve seat and a valve stem; the valve stem can move axially left and right in the solenoid valve seat, thereby realizing the following four thrust working modes.

[0014] Thrust working mode 1: The detonation combustion chamber works independently to provide thrust.

[0015] Thrust working mode two: Detonation combustion chamber two works independently to provide thrust.

[0016] Thrust working mode three: Detonation combustion chamber one and detonation combustion chamber two work together to provide thrust.

[0017] Thrust working mode four: Detonation combustion chamber one, detonation combustion chamber two and detonation combustion chamber three work together to provide thrust.

[0018] The first detonation combustion chamber, the second detonation combustion chamber and the third detonation combustion chamber are arranged equidistantly in the radial direction, and the annular area of the second detonation combustion chamber is greater than the annular area of the first detonation combustion chamber.

[0019] The solenoid valve seat includes a central valve cavity, a propellant inlet and seven annular cavities.

[0020] The central valve cavity is coaxially arranged at the center of the solenoid valve seat and is a sealed cavity.

[0021] The seven annular cavities are coaxially arranged on the outer periphery of the central valve cavity, and the diameter of each annular cavity is larger than the diameter of the central valve cavity; the seven annular cavities are cavity one, cavity two, cavity three, cavity four, cavity five, cavity six and cavity seven from front to back.

[0022] The second cavity, the fourth cavity and the sixth cavity are respectively connected to the propellant inlet and are filled with propellant.

[0023] Both cavity one and cavity seven can be used to supply propellant to detonation combustion chamber three.

[0024] Cavity three can be used to supply propellant to detonation combustion chamber one.

[0025] Cavity five can be used to supply propellant to detonation combustion chamber two.

[0026] The valve stem is coaxially arranged in the central valve cavity and can move left and right along the axial direction; five valve cores are axially arranged on the outer periphery of the valve stem, namely valve core one, valve core two, valve core three, valve core four and valve core five; the outer wall surface of each valve core can be sealed and matched with the inner wall surface of the central valve cavity.

[0027] The axial length of the second spool is greater than that of the second cavity, and it can seal both sides of the second cavity.

[0028] The axial length of the third spool is greater than that of the fourth cavity, and it can seal both sides of the fourth cavity.

[0029] The axial length of the fourth spool is greater than that of the sixth cavity, and it can seal both sides of the sixth cavity.

[0030] The distance between the inner side of the first spool and the opposite side of the fifth spool is L1, and the distance between the outer side of the first cavity and the outer side of the seventh cavity is L2, then L1 is greater than L2.

[0031] The injection panel includes a first annular injection plate, a second annular injection plate, and a third annular injection plate arranged coaxially from outside to inside in sequence.

[0032] The first annular injection plate, the second annular injection plate, and the third annular injection plate all include a fuel collection cavity and an oxidizer collection cavity arranged coaxially and all in an annular shape.

[0033] N fuel nozzles are arranged circumferentially in the fuel collection cavity.

[0034] N oxidizer nozzles are arranged circumferentially in the oxidizer collection cavity.

[0035] The connecting plate is installed on the outer side surface of the injection panel through a force transmission column, and the top of the connecting plate has two solenoid valve installation grooves, which are respectively used for installing a fuel solenoid valve and an oxidizer solenoid valve.

[0036] Each solenoid valve installation groove bottom has four propellant transfer pipes, namely transfer pipe one, transfer pipe two, transfer pipe three, and transfer pipe four.

[0037] The top end of transfer pipe one is communicated with the first cavity, and the bottom end is communicated with the fuel collection cavity or the oxidizer collection cavity in the third annular injection plate.

[0038] The top end of transfer pipe two is communicated with the third cavity, and the bottom end is communicated with the fuel collection cavity or the oxidizer collection cavity in the first annular injection plate.

[0039] The top end of transfer pipe three is communicated with the fifth cavity, and the bottom end is communicated with the fuel collection cavity or the oxidizer collection cavity in the second annular injection plate.

[0040] The top end of transfer pipe four is communicated with the seventh cavity, and the bottom end is communicated with the fuel collection cavity or the oxidizer collection cavity in the third annular injection plate.

[0041] The N fuel nozzles and N oxidizer nozzles in each annular injection plate together form N groups of propellant nozzle groups; the axes of the fuel nozzles and oxidizer nozzles in each group of propellant nozzle groups intersect.

[0042] The N groups of propellant nozzle groups in the annular injection plate one, the annular injection plate two, and the annular injection plate three are arranged circumferentially in a staggered manner.

[0043] The usage method of the new variable-thrust rotating detonation space engine includes the following steps.

[0044] Step 1: The combustion chamber does not work: The valve stem is in the reset state. At this time, the valve core two seals both sides of the chamber two; the valve core three seals both sides of the chamber four; the valve core four seals both sides of the chamber six; the fuel and the oxidant are respectively filled into the corresponding chamber two, chamber four, and chamber six from the corresponding propellant inlets.

[0045] Step 2: Three left-shift thrust modes: Move the valve stem in the reset state to the left three times in sequence, and the following three left-shift thrust modes can be achieved:

[0046] Left-shift thrust mode one: The detonation combustion chamber two works independently to provide thrust.

[0047] Left-shift thrust mode two: The detonation combustion chamber one and the detonation combustion chamber two work together to provide thrust.

[0048] Left-shift thrust mode three: The detonation combustion chamber one, the detonation combustion chamber two, and the detonation combustion chamber three work together to provide thrust.

[0049] Step 3: Three right-shift thrust modes: Move the valve stem in the reset state to the right three times in sequence, and the following three right-shift thrust modes can be achieved:

[0050] Right-shift thrust mode one: The detonation combustion chamber one works independently to provide thrust.

[0051] Right-shift thrust mode two: The detonation combustion chamber one and the detonation combustion chamber two work together to provide thrust.

[0052] Right-shift thrust mode three: The detonation combustion chamber one, the detonation combustion chamber two, and the detonation combustion chamber three work together to provide thrust.

[0053] In step 2, the implementation methods of the three left-shift thrust modes include the following steps:

[0054] Step 2-1: Left-shift thrust mode one: Move the valve stem in the reset state to the left once. At this time:

[0055] The valve core two still seals both sides of the chamber two.

[0056] The valve core three only seals the front side of the chamber four, and the rear side of the chamber four is connected to the chamber five.

[0057] The valve core four still seals both sides of the chamber six.

[0058] The propellant will be transported from chamber five through delivery pipe three to the fuel collection chamber or oxidizer collection chamber in the annular injection plate two; and will be injected through the propellant nozzle group into the detonation combustion chamber two for combustion to achieve thrust.

[0059] Step 2-2, Left Thrust Mode Two: Move the valve stem in the Left Thrust Mode One to the left for the second time. At this time:

[0060] The valve core two only seals and blocks the front side of chamber two, and the rear side of chamber two is connected to chamber three.

[0061] The valve core three only seals and blocks the front side of chamber four, and the rear side of chamber four is connected to chamber five.

[0062] The valve core four still seals and blocks both sides of chamber six.

[0063] On the one hand, the propellant is transported from chamber three through delivery pipe two to the fuel collection chamber or oxidizer collection chamber in the annular injection plate one; and is injected through the corresponding propellant nozzle group into the detonation combustion chamber one for combustion.

[0064] The propellant will also be transported from chamber five through delivery pipe three to the fuel collection chamber or oxidizer collection chamber in the annular injection plate two; and will be injected through the corresponding propellant nozzle group into the detonation combustion chamber two for combustion.

[0065] At this time, the detonation combustion chamber one and the detonation combustion chamber two work together to provide thrust.

[0066] Step 2-3, Left Thrust Mode Three: Move the valve stem in the Left Thrust Mode Two to the left for the third time. At this time:

[0067] The valve core two only seals and blocks the front side of chamber two, and the rear side of chamber two is connected to chamber three.

[0068] The valve core three only seals and blocks the front side of chamber four, and the rear side of chamber four is connected to chamber five.

[0069] The valve core four only seals and blocks the front side of chamber six, and the rear side of chamber six is connected to chamber seven.

[0070] On the one hand, the propellant is transported from chamber three through delivery pipe two to the fuel collection chamber or oxidizer collection chamber in the annular injection plate one; and is injected through the corresponding propellant nozzle group into the detonation combustion chamber one for combustion.

[0071] The propellant will also be transported from chamber five through delivery pipe three to the fuel collection chamber or oxidizer collection chamber in the annular injection plate two; and will be injected through the corresponding propellant nozzle group into the detonation combustion chamber two for combustion.

[0072] The propellant will also be transported from chamber seven through delivery pipe four to the fuel collection chamber or oxidizer collection chamber in the annular injection plate three; and will be injected through the corresponding propellant nozzle group into the detonation combustion chamber three for combustion.

[0073] At this time, the detonation combustion chamber one, the detonation combustion chamber two, and the detonation combustion chamber three work together to provide thrust.

[0074] In step 3, the implementation methods of the three rightward thrust modes include the following steps:

[0075] Step 3-1, rightward thrust mode one: Move the valve stem in the reset state to the right once. At this time:

[0076] The valve core two still seals both sides of chamber two.

[0077] The valve core three only seals the rear side of chamber four, and the front side of chamber four is connected to chamber three.

[0078] The valve core four still seals both sides of chamber six.

[0079] The propellant is transported from chamber three to the fuel collection chamber or the oxidizer collection chamber in the annular injection plate one through the delivery pipe two; and is injected into the detonation combustion chamber one through the corresponding propellant nozzle group for combustion; at this time, only the detonation combustion chamber one provides thrust.

[0080] Step 3-2, rightward thrust mode two: Move the valve stem in the rightward thrust mode one to the right a second time. At this time:

[0081] The valve core two still seals both sides of chamber two.

[0082] The valve core three only seals the rear side of chamber four, and the front side of chamber four is connected to chamber three.

[0083] The valve core four only seals the rear side of chamber six, and the front side of chamber six is connected to chamber five;

[0084] On the one hand, the propellant is transported from chamber three to the fuel collection chamber or the oxidizer collection chamber in the annular injection plate one through the delivery pipe two; and is injected into the detonation combustion chamber one through the corresponding propellant nozzle group for combustion.

[0085] The propellant will also be transported from chamber five to the fuel collection chamber or the oxidizer collection chamber in the annular injection plate two through the delivery pipe three; and is injected into the detonation combustion chamber two through the corresponding propellant nozzle group for combustion.

[0086] At this time, the detonation combustion chamber one and the detonation combustion chamber two work together to provide thrust.

[0087] Step 3-3, rightward thrust mode three: Move the valve stem in the rightward thrust mode two to the right a third time. At this time:

[0088] The valve core two only seals the rear side of chamber two, and the front side of chamber two is connected to chamber one.

[0089] The valve core three only seals the rear side of chamber four, and the front side of chamber four is connected to chamber three.

[0090] The valve core four only seals and plugs the rear side of the chamber six, and the front side of the chamber six is communicated with the chamber five.

[0091] On the one hand, the propellant is transported from the chamber one to the fuel collection chamber or the oxidizer collection chamber in the annular injection plate three through the transport pipe one; and is sprayed into the detonation combustion chamber three through the corresponding propellant nozzle group for combustion.

[0092] The propellant will also be transported from the chamber three to the fuel collection chamber or the oxidizer collection chamber in the annular injection plate one through the transport pipe two; and is sprayed into the detonation combustion chamber one through the corresponding propellant nozzle group for combustion.

[0093] The propellant will also be transported from the chamber five to the fuel collection chamber or the oxidizer collection chamber in the annular injection plate two through the transport pipe three; and is sprayed into the detonation combustion chamber two through the corresponding propellant nozzle group for combustion.

[0094] At this time, the detonation combustion chamber one, the detonation combustion chamber two and the detonation combustion chamber three work together to provide thrust.

[0095] The present invention has the following beneficial effects:

[0096] 1. The present invention adopts the rotating detonation combustion form, and the rotating detonation space engine has a higher thermal cycle efficiency. This means that the rotating detonation engine can not only achieve more efficient energy conversion, explore farther into the unknown space, but also improve the utilization rate of the propellant, extend the life of the spacecraft, and reduce the mission cost of deep space exploration. It can enable the detector to explore deeper into the unknown space.

[0097] 2. The three annular detonation combustion chambers arranged coaxially in the rotating detonation space engine of the present invention can work independently, and the flow rate of the propellant in the combustion chamber can be accurately adjusted within a small range by highly efficient and reliable solenoid valves and flow regulating valves. It can achieve continuous adjustment of the mass flow rate within a large range without decoupling of the detonation wave in the detonation engine, that is, achieve stable and continuous adjustment of the thrust. This engine can work stably under medium and low chamber pressures of about 1 MPa.

[0098] 3. Each combustion chamber can work independently in the form of detonation combustion, or can work simultaneously. In addition, the thrust of each combustion chamber can be accurately adjusted to meet the task requirements of large-range thrust adjustment in deep space exploration. It can play a crucial role in tasks such as satellite orbit change, rendezvous and docking, deep space exploration, orbit descent, hovering and soft landing of lunar and Mars detectors. Description of the Drawings

[0099] Figure 1 Shows a three-dimensional structural schematic diagram of a novel variable-thrust rotating detonation space engine of the present invention.

[0100] Figure 2Shows a schematic cross-sectional structure diagram of a novel variable-thrust rotary detonation space engine of the present invention.

[0101] Figure 3 Shows a schematic cross-sectional structure diagram of the rotary detonation combustion device in the present invention.

[0102] Figure 4 Shows a three-dimensional cross-sectional structure diagram of the rotary detonation combustion device and the injection panel in the present invention.

[0103] Figure 5 Shows a schematic plan view of the layout of the propellant nozzle in the rotary detonation combustion device in the present invention.

[0104] Figure 6 Shows the three-dimensional solid of the connecting plate in the present invention Figure 1 。

[0105] Figure 7 Shows the three-dimensional solid of the connecting plate in the present invention Figure 2 。

[0106] Figure 8 Shows a three-dimensional solid diagram of the fuel solenoid valve or the oxidizer solenoid valve in the present invention.

[0107] Figure 9 Shows a three-dimensional cross-sectional schematic diagram of the fuel solenoid valve or the oxidizer solenoid valve in the present invention.

[0108] Figure 10 Shows a schematic structural diagram of the valve stem in the present invention.

[0109] Figure 11 Shows a schematic structural diagram of the connection hole communicating with chamber two and chamber six in the present invention.

[0110] Figure 12 Shows a schematic structural diagram of the valve stem in the reset state in the present invention.

[0111] Figure 13 Shows a schematic diagram of the valve stem moving left to achieve three thrust modes in the present invention; among them, (a), (b), and (c) are respectively schematic structural diagrams when the valve stem moves left for the first time, the second time, and the third time.

[0112] Figure 14 Shows a schematic diagram of the valve stem moving right to achieve three thrust modes in the present invention; among them, (a), (b), and (c) are respectively schematic structural diagrams when the valve stem moves right for the first time, the second time, and the third time.

[0113] Among them are:

[0114] 10. Rotary detonation combustion device;

[0115] 11. Detonation combustion chamber one; 12. Detonation combustion chamber two; 13. Detonation combustion chamber three; 14. Central cone; 15. Housing mounting plate;

[0116] 20. Injection panel; 21. Annular injection plate one; 22. Annular injection plate two; 23. Annular injection plate three; 24. Fuel collection chamber; 26. Oxidizer collection chamber; 26. Fuel nozzle; 27. Oxidizer nozzle;

[0117] 30. Connecting plate;

[0118] 31. Delivery pipe one; 32. Delivery pipe two; 33. Delivery pipe three; 34. Delivery pipe four;

[0119] 35. Solenoid valve mounting groove; 351. Hole one; 352. Hole two; 353. Hole three; 354. Hole four;

[0120] 36. Transmission column;

[0121] 40. Solenoid valve seat;

[0122] 41. Chamber one; 42. Chamber two; 43. Chamber three; 44. Chamber four; 45. Chamber five; 46. Chamber six; 47. Chamber seven;

[0123] 48. Central valve chamber; 481. Propellant inlet; 482. Valve stem sliding hole; 483. Distribution hole; 484. Connection hole;

[0124] 50. Valve stem; 51. Valve core one; 52. Valve core two; 53. Valve core three; 54. Valve core four; 55. Valve core five;

[0125] 60. Fuel solenoid valve; 70. Oxidizer solenoid valve. Detailed implementation manners

[0126] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific preferred embodiments.

[0127] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by terms such as "left side", "right side", "upper part", "lower part", etc. is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. "First", "second", etc. do not indicate the importance of components, so it cannot be understood as a limitation to the present invention. The specific dimensions adopted in this embodiment are only for illustrating the technical solution by way of example, and do not limit the protection scope of the present invention.

[0128] As Figure 1 and Figure 2As shown, a new type of variable-thrust rotary detonation space engine includes a rotary detonation combustion device 10, a jet panel 20, a connecting plate 30, a fuel solenoid valve 60, and an oxidizer solenoid valve 70.

[0129] As Figure 2 and Figure 3 shown, the rotary detonation combustion device includes a detonation combustion chamber one 11, a detonation combustion chamber two 12, and a detonation combustion chamber three 13 that are coaxially arranged from the outside to the inside in sequence and are all annular.

[0130] Among them, a central cone 14 is arranged at the center of the detonation combustion chamber three, and the outside of the detonation combustion chamber one is installed through a housing mounting plate 15.

[0131] Furthermore, the detonation combustion chamber one, the detonation combustion chamber two, and the detonation combustion chamber three are preferably arranged at equal intervals in the radial direction. The annular area of the detonation combustion chamber two is larger than the annular area of the detonation combustion chamber one, which can achieve different thrusts.

[0132] Furthermore, heat insulation layers are preferably arranged on the inner and outer wall surfaces of the detonation combustion chamber one, the detonation combustion chamber two, and the detonation combustion chamber three to prevent the wall surfaces from being ablated.

[0133] The jet panel is arranged at the jet end face of the rotary detonation combustion device and can spray fuel and oxidizer into the detonation combustion chamber one, the detonation combustion chamber two, and the detonation combustion chamber three respectively.

[0134] As Figure 4 shown, the jet panel includes an annular jet plate one 21, an annular jet plate two 22, and an annular jet plate three 23 that are coaxially arranged from the outside to the inside in sequence.

[0135] The annular jet plate one, the annular jet plate two, and the annular jet plate three all include a fuel collecting cavity 24 and an oxidizer collecting cavity 25 that are coaxially arranged and are all annular.

[0136] N fuel nozzles 26 are arranged along the circumferential direction in the fuel collecting cavity.

[0137] N oxidizer nozzles 27 are arranged along the circumferential direction in the oxidizer collecting cavity.

[0138] The N fuel nozzles and the N oxidizer nozzles in each annular jet plate together form N groups of propellant nozzle groups; the axes of the fuel nozzles and the oxidizer nozzles in each group of propellant nozzle groups intersect, that is, they can collide with each other in the corresponding detonation combustion chamber.

[0139] As Figure 5 shown, the N groups of propellant nozzle groups in the annular jet plate one, the annular jet plate two, and the annular jet plate three are preferably arranged staggeredly along the circumferential direction.

[0140] The connecting plate is installed on the outer side surface of the jet panel and can be used to install the fuel solenoid valve and the oxidizer solenoid valve.

[0141] As Figure 6 and Figure 7 shown, the connecting plate is installed on the outer side of the injection panel through a number of force - transmitting columns 36. There are two solenoid valve mounting grooves 35 at the top of the connecting plate, which are respectively used for installing the fuel solenoid valve and the oxidizer solenoid valve.

[0142] At the bottom of each solenoid valve mounting groove, there are four holes, namely hole one 351, hole two 352, hole three 353 and hole four 354; the four holes are used for installing four propellant transfer pipes, namely transfer pipe one 31, transfer pipe two 32, transfer pipe three 33 and transfer pipe four 34.

[0143] The top end of transfer pipe one is connected to chamber one in the subsequent solenoid valve seat, and the bottom end is connected to the fuel collection chamber or the oxidizer collection chamber in the annular injection plate three.

[0144] The top end of transfer pipe two is connected to chamber three in the subsequent solenoid valve seat, and the bottom end is connected to the fuel collection chamber or the oxidizer collection chamber in the annular injection plate one.

[0145] The top end of transfer pipe three is connected to chamber five in the subsequent solenoid valve seat, and the bottom end is connected to the fuel collection chamber or the oxidizer collection chamber in the annular injection plate two.

[0146] The top end of transfer pipe four is connected to chamber seven in the subsequent solenoid valve seat, and the bottom end is connected to the fuel collection chamber or the oxidizer collection chamber in the annular injection plate three.

[0147] Both the fuel solenoid valve and the oxidizer solenoid valve include Figure 8 、 Figure 9 the solenoid valve seat 40 shown in Figure 10 and the valve stem 50 shown in

[0148] As Figure 9 shown, the solenoid valve seat includes a central valve cavity 48, a propellant inlet 481 and seven annular cavities.

[0149] The central valve cavity is coaxially arranged at the center of the solenoid valve seat and is a sealed cavity.

[0150] The seven annular cavities are all coaxially arranged outside the central valve cavity, and the diameter of each annular cavity is larger than that of the central valve cavity.

[0151] The seven annular cavities are, from front to back, chamber one 41, chamber two 42, chamber three 43, chamber four 44, chamber five 45, chamber six 46 and chamber seven 47.

[0152] The above - mentioned chamber two, chamber four and chamber six are respectively connected to the propellant inlet through distribution holes 483 and Figure 11 the connecting holes 484 shown in

[0153] The chamber one supplies propellant to the detonation combustion chamber three through the through hole one 351 and the delivery pipe one 31.

[0154] The chamber seven supplies propellant to the detonation combustion chamber three through the through hole four 354 and the delivery pipe four 34.

[0155] The chamber three supplies propellant to the detonation combustion chamber one through the through hole two 352 and the delivery pipe two 32.

[0156] The chamber five supplies propellant to the detonation combustion chamber two through the through hole three 353 and the delivery pipe three 33.

[0157] The valve stem is coaxially arranged in the central valve chamber and can move left and right axially.

[0158] As Figure 10 shown, five valve cores are axially arranged on the outer periphery of the valve stem, which are respectively the valve core one 51, the valve core two 52, the valve core three 53, the valve core four 54 and the valve core five 55 in sequence; the outer wall surface of each valve core can be in sealing fit with the inner wall surface of the central valve chamber.

[0159] The axial length of the valve core two is greater than the axial length of the chamber two, and can seal both sides of the chamber two.

[0160] The axial length of the valve core three is greater than the axial length of the chamber four, and can seal both sides of the chamber four.

[0161] The axial length of the valve core four is greater than the axial length of the chamber six, and can seal both sides of the chamber six.

[0162] The distance between the inner side edge of the valve core one and the opposite side edge of the valve core five is L1, and the distance between the outer side edge of the chamber one and the outer side edge of the chamber seven is L2, then preferably L1 is greater than L2.

[0163] The valve stem can move left and right axially in the solenoid valve seat, so as to realize the following four thrust working modes.

[0164] Thrust working mode one: The detonation combustion chamber one works independently to provide thrust.

[0165] Thrust working mode two: The detonation combustion chamber two works independently to provide thrust.

[0166] Thrust working mode three: The detonation combustion chamber one and the detonation combustion chamber two work together to provide thrust.

[0167] Thrust working mode four: The detonation combustion chamber one, the detonation combustion chamber two and the detonation combustion chamber three work together to provide thrust.

[0168] The using method of the novel variable-thrust rotating detonation space engine includes the following steps.

[0169] Step 1, the combustion chamber does not work: As Figure 12As shown, the valve stem is in the reset state. At this time, the second valve core seals both sides of chamber two; the third valve core seals both sides of chamber four; the fourth valve core seals both sides of chamber six; fuel and oxidant are respectively filled into the corresponding chamber two, chamber four and chamber six from the corresponding propellant inlets.

[0170] Step 2. Three leftward movement thrust modes: As Figure 13 shown, move the valve stem in the reset state to the left three times in sequence, and the following three leftward movement thrust modes can be achieved:

[0171] Leftward movement thrust mode one: The detonation combustor two works independently to provide thrust.

[0172] Leftward movement thrust mode two: The detonation combustor one and the detonation combustor two work together to provide thrust.

[0173] Leftward movement thrust mode three: The detonation combustor one, the detonation combustor two and the detonation combustor three work together to provide thrust.

[0174] The implementation methods of the three leftward movement thrust modes include the following steps.

[0175] Step 2-1. Leftward movement thrust mode one

[0176] As Figure 13 (a) shown, move the valve stem in the reset state to the left once. At this time:

[0177] The second valve core still seals both sides of chamber two.

[0178] The third valve core only seals the front side of chamber four, and the rear side of chamber four is connected to chamber five.

[0179] The fourth valve core still seals both sides of chamber six.

[0180] The propellant will be transported from chamber five to the fuel collection chamber or the oxidant collection chamber in the annular injection plate two through the transfer pipe three; and is injected into the detonation combustor two through the propellant nozzle group for combustion to achieve thrust.

[0181] Step 2-2. Leftward movement thrust mode two:

[0182] As Figure 13 (b) shown, move the valve stem in the leftward movement thrust mode one to the left for the second time. At this time:

[0183] The second valve core only seals the front side of chamber two, and the rear side of chamber two is connected to chamber three.

[0184] The third valve core only seals the front side of chamber four, and the rear side of chamber four is connected to chamber five.

[0185] The fourth valve core still seals both sides of chamber six.

[0186] On the one hand, the propellant is transported from chamber three through delivery pipe two to the fuel collection chamber or oxidizer collection chamber in the annular injection plate one; and is injected through the corresponding propellant nozzle group into detonation combustion chamber one for combustion.

[0187] The propellant will also be transported from chamber five through delivery pipe three to the fuel collection chamber or oxidizer collection chamber in the annular injection plate two; and is injected through the corresponding propellant nozzle group into detonation combustion chamber two for combustion.

[0188] At this time, detonation combustion chamber one and detonation combustion chamber two work together to provide thrust.

[0189] Step 2-3, left shift thrust mode three:

[0190] As Figure 13 (c) shows, move the valve stem in the left shift thrust mode two to the left for the third time. At this time:

[0191] Valve core two only seals and plugs the front side of chamber two, and the rear side of chamber two is connected to chamber three.

[0192] Valve core three only seals and plugs the front side of chamber four, and the rear side of chamber four is connected to chamber five.

[0193] Valve core four only seals and plugs the front side of chamber six, and the rear side of chamber six is connected to chamber seven.

[0194] On the one hand, the propellant is transported from chamber three through delivery pipe two to the fuel collection chamber or oxidizer collection chamber in the annular injection plate one; and is injected through the corresponding propellant nozzle group into detonation combustion chamber one for combustion.

[0195] The propellant will also be transported from chamber five through delivery pipe three to the fuel collection chamber or oxidizer collection chamber in the annular injection plate two; and is injected through the corresponding propellant nozzle group into detonation combustion chamber two for combustion.

[0196] The propellant will also be transported from chamber seven through delivery pipe four to the fuel collection chamber or oxidizer collection chamber in the annular injection plate three; and is injected through the corresponding propellant nozzle group into detonation combustion chamber three for combustion.

[0197] At this time, detonation combustion chamber one, detonation combustion chamber two and detonation combustion chamber three work together to provide thrust.

[0198] Step 3, three right shift thrust modes: As Figure 14 shown, move the valve stem in the reset state to the right three times in sequence, and the following three right shift thrust modes can be achieved:

[0199] Right shift thrust mode one: Detonation combustion chamber one works independently to provide thrust.

[0200] Right shift thrust mode two: Detonation combustion chamber one and detonation combustion chamber two work together to provide thrust.

[0201] Right-shift thrust mode three: The detonation combustor one, the detonation combustor two, and the detonation combustor three work together to provide thrust.

[0202] The implementation methods of the above three right-shift thrust modes include the following steps:

[0203] Step 3-1, right-shift thrust mode one

[0204] As Figure 14 (a) shows, move the valve stem in the reset state to the right once. At this time:

[0205] The valve core two still seals both sides of chamber two.

[0206] The valve core three only seals the rear side of chamber four, and the front side of chamber four is connected to chamber three.

[0207] The valve core four still seals both sides of chamber six.

[0208] The propellant is transported from chamber three to the fuel collection chamber or the oxidizer collection chamber in the annular injection plate one through the delivery pipe two; and is injected into the detonation combustor one through the corresponding propellant nozzle group for combustion; at this time, only the detonation combustor one provides thrust.

[0209] Step 3-2, right-shift thrust mode two

[0210] As Figure 14 (b) shows, move the valve stem in the right-shift thrust mode one to the right for the second time. At this time:

[0211] The valve core two still seals both sides of chamber two.

[0212] The valve core three only seals the rear side of chamber four, and the front side of chamber four is connected to chamber three.

[0213] The valve core four only seals the rear side of chamber six, and the front side of chamber six is connected to chamber five;

[0214] On the one hand, the propellant is transported from chamber three to the fuel collection chamber or the oxidizer collection chamber in the annular injection plate one through the delivery pipe two; and is injected into the detonation combustor one through the corresponding propellant nozzle group for combustion.

[0215] The propellant will also be transported from chamber five to the fuel collection chamber or the oxidizer collection chamber in the annular injection plate two through the delivery pipe three; and is injected into the detonation combustor two through the corresponding propellant nozzle group for combustion.

[0216] At this time, the detonation combustor one and the detonation combustor two work together to provide thrust.

[0217] Step 3-3, right-shift thrust mode three:

[0218] As Figure 14As shown in (c), the valve stem in the right-shift thrust mode II is moved to the right for the third time. At this time:

[0219] The second spool only seals the rear side of chamber II, and the front side of chamber II is connected to chamber I.

[0220] The third spool only seals the rear side of chamber IV, and the front side of chamber IV is connected to chamber III.

[0221] The fourth spool only seals the rear side of chamber VI, and the front side of chamber VI is connected to chamber V.

[0222] On the one hand, the propellant is transported from chamber I to the fuel collection chamber or oxidizer collection chamber in the annular injection plate III through the first transfer pipe; and is injected into the detonation combustion chamber III through the corresponding propellant nozzle group for combustion.

[0223] The propellant will also be transported from chamber III to the fuel collection chamber or oxidizer collection chamber in the annular injection plate I through the second transfer pipe; and is injected into the detonation combustion chamber I through the corresponding propellant nozzle group for combustion.

[0224] The propellant will also be transported from chamber V to the fuel collection chamber or oxidizer collection chamber in the annular injection plate II through the third transfer pipe; and is injected into the detonation combustion chamber II through the corresponding propellant nozzle group for combustion.

[0225] At this time, the detonation combustion chamber I, the detonation combustion chamber II, and the detonation combustion chamber III work together to provide thrust.

[0226] The variable-thrust engine is mainly applied to orbital maneuvering and can achieve continuous thrust adjustment of chemical fuels.

[0227] When performing large-range orbital transfer, two or three combustion chambers can be selected to work simultaneously according to the mission requirements, the specific requirements of the target orbit, and the status of the spacecraft itself, so as to enter the predetermined orbit with one orbital transfer. That is, the left-shift thrust mode II, the left-shift thrust mode III, the right-shift thrust mode II, or the right-shift thrust mode III can be selected.

[0228] When the spacecraft performs small-range orbit maintenance in various set states in space, a single combustion chamber can be selected to work. That is, the left-shift thrust mode I or the right-shift thrust mode I can be selected.

[0229] During the process of orbital rendezvous and spacecraft rendezvous, the working state of the combustion chamber can be flexibly adjusted according to the mission requirements and the actual situation. In addition, during the process of the detector landing on the moon, the engine needs to provide continuous and stable thrust, and the thrust is adjustable. Therefore, the engine can increase the number of working combustion chambers to achieve thrust adjustment during the process of the detector landing on the moon. That is, it can be selected between the left-shift thrust mode I to III, or the right-shift thrust mode I to III.

[0230] The preferred embodiments of the present invention have been described in detail above. However, the present invention is not limited to the specific details in the above embodiments. Within the scope of the technical concept of the present invention, various equivalent transformations can be made to the technical solutions of the present invention, and these equivalent transformations all fall within the protection scope of the present invention.

Claims

1. A variable-thrust rotating detonation space engine, characterized in that: It includes a rotary detonation combustion device, a jet panel, a connecting plate, a fuel solenoid valve, and an oxidizer solenoid valve; The rotary detonation combustion device includes a first detonation combustion chamber, a second detonation combustion chamber, and a third detonation combustion chamber that are coaxially arranged from outside to inside in sequence and are all annular; The jet panel is arranged on the jet end face of the rotary detonation combustion device and can spray fuel and oxidizer into the first detonation combustion chamber, the second detonation combustion chamber, and the third detonation combustion chamber respectively; The connecting plate is installed on the outer side of the jet panel and can be used to install the fuel solenoid valve and the oxidizer solenoid valve; Both the fuel solenoid valve and the oxidizer solenoid valve include a solenoid valve seat and a valve rod; the valve rod can axially move left and right within the solenoid valve seat, so as to realize the following four thrust working modes; Thrust working mode 1: The first detonation combustion chamber works independently to provide thrust; Thrust working mode 2: The second detonation combustion chamber works independently to provide thrust; Thrust working mode 3: The first detonation combustion chamber and the second detonation combustion chamber work together to provide thrust; Thrust working mode 4: The first detonation combustion chamber, the second detonation combustion chamber, and the third detonation combustion chamber work together to provide thrust; The solenoid valve seat includes a central valve cavity, a propellant inlet, and seven annular cavities; The central valve cavity is coaxially arranged at the center of the solenoid valve seat and is a sealed cavity; The seven annular cavities are all coaxially arranged outside the central valve cavity, and the diameter of each annular cavity is greater than the diameter of the central valve cavity; the seven annular cavities are the first cavity, the second cavity, the third cavity, the fourth cavity, the fifth cavity, the sixth cavity, and the seventh cavity in sequence from front to back; The second cavity, the fourth cavity, and the sixth cavity are respectively connected to the propellant inlet and filled with propellant; Both the first cavity and the seventh cavity can be used to supply propellant to the third detonation combustion chamber; The third cavity can be used to supply propellant to the first detonation combustion chamber; The fifth cavity can be used to supply propellant to the second detonation combustion chamber; The valve rod is coaxially arranged in the central valve cavity and can move left and right along the axis; five valve cores are arranged along the axis on the outer periphery of the valve rod, which are the first valve core, the second valve core, the third valve core, the fourth valve core, and the fifth valve core in sequence; the outer wall surface of each valve core can be hermetically matched with the inner wall surface of the central valve cavity; The axial length of the second valve core is greater than the axial length of the second cavity and can seal both sides of the second cavity; The axial length of the third valve core is greater than the axial length of the fourth cavity and can seal both sides of the fourth cavity; The axial length of the fourth valve core is greater than the axial length of the sixth cavity and can seal both sides of the sixth cavity.

2. The variable thrust rotating detonation space engine according to claim 1, wherein: The first detonation combustion chamber, the second detonation combustion chamber, and the third detonation combustion chamber are arranged at equal radial distances, and the annular area of the second detonation combustion chamber is greater than the annular area of the first detonation combustion chamber.

3. The variable-thrust rotating detonation space engine according to claim 1, wherein: The distance between the inner side edge of the first valve core and the opposite side edge of the fifth valve core is L1, and the distance between the outer side edge of the first cavity and the outer side edge of the seventh cavity is L2, then L1 is greater than L2.

4. The variable-thrust rotating detonation space engine according to claim 1, characterized in that: The jet panel includes a first annular jet plate, a second annular jet plate, and a third annular jet plate that are coaxially arranged from outside to inside in sequence; Both the first annular jet plate, the second annular jet plate, and the third annular jet plate include a fuel collecting cavity and an oxidizer collecting cavity that are coaxially arranged and are all annular; N fuel nozzles are arranged circumferentially in the fuel collecting cavity; N oxidizer nozzles are arranged circumferentially in the oxidizer collecting cavity; The connecting plate is installed on the outer side of the jet panel through a force transmission column. The top of the connecting plate has two solenoid valve installation slots, which are respectively used to install the fuel solenoid valve and the oxidizer solenoid valve; At the bottom of each solenoid valve installation groove, there are four propellant transfer pipes, namely transfer pipe one, transfer pipe two, transfer pipe three, and transfer pipe four; The top end of transfer pipe one is connected to chamber one, and the bottom end is connected to the fuel collection chamber or oxidizer collection chamber in annular injection plate three; The top end of transfer pipe two is connected to chamber three, and the bottom end is connected to the fuel collection chamber or oxidizer collection chamber in annular injection plate one; The top end of transfer pipe three is connected to chamber five, and the bottom end is connected to the fuel collection chamber or oxidizer collection chamber in annular injection plate two; The top end of transfer pipe four is connected to chamber seven, and the bottom end is connected to the fuel collection chamber or oxidizer collection chamber in annular injection plate three.

5. The variable-thrust rotating detonation space engine according to claim 4, characterized in that: The N fuel nozzles and N oxidizer nozzles in each annular injection plate together form N groups of propellant nozzle groups; the axes of the fuel nozzles and oxidizer nozzles in each group of propellant nozzle groups intersect; The N groups of propellant nozzle groups in annular injection plate one, annular injection plate two, and annular injection plate three are arranged staggered along the circumferential direction.

6. A method for using a variable-thrust rotating detonation space engine according to any one of claims 1-5, characterized in that: It includes the following steps: Step 1, the combustion chamber is not working: The valve stem is in the reset state. At this time, valve core two seals both sides of chamber two; valve core three seals both sides of chamber four; valve core four seals both sides of chamber six; fuel and oxidizer are respectively filled into the corresponding chamber two, chamber four, and chamber six from the corresponding propellant inlets; Step 2, three leftward thrust modes: Move the valve stem in the reset state to the left three times in sequence, and the following three leftward thrust modes can be achieved: Leftward thrust mode one: Detonation combustion chamber two works independently to provide thrust; Leftward thrust mode two: Detonation combustion chamber one and detonation combustion chamber two work together to provide thrust; Leftward thrust mode three: Detonation combustion chamber one, detonation combustion chamber two, and detonation combustion chamber three work together to provide thrust; Step 3, three rightward thrust modes: Move the valve stem in the reset state to the right three times in sequence, and the following three rightward thrust modes can be achieved: Rightward thrust mode one: Detonation combustion chamber one works independently to provide thrust; Rightward thrust mode two: Detonation combustion chamber one and detonation combustion chamber two work together to provide thrust; Rightward thrust mode three: Detonation combustion chamber one, detonation combustion chamber two, and detonation combustion chamber three work together to provide thrust.

7. The method for using a variable-thrust rotating detonation space engine according to claim 6, characterized in that: In step 2, the implementation methods of the three leftward thrust modes include the following steps: Step 2-1, leftward thrust mode one: Move the valve stem in the reset state to the left once. At this time: Valve core two still seals both sides of chamber two; Valve core three only seals the front side of chamber four, and the rear side of chamber four is connected to chamber five; Valve core four still seals both sides of chamber six; Propellant will be transported from chamber five to the fuel collection chamber or oxidizer collection chamber in annular injection plate two through transfer pipe three; and is sprayed through the propellant nozzle group into detonation combustion chamber two for combustion to achieve thrust; Step 2-2, leftward thrust mode two: Move the valve stem in leftward thrust mode one to the left for the second time. At this time: Valve core two only seals the front side of chamber two, and the rear side of chamber two is connected to chamber three; Valve core three only seals the front side of chamber four, and the rear side of chamber four is connected to chamber five; Valve core four still seals both sides of chamber six; On the one hand, the propellant is transported from chamber three through delivery pipe two to the fuel collecting chamber or oxidizer collecting chamber in the annular injection plate one; and is injected through the corresponding propellant nozzle group into detonation combustion chamber one for combustion; The propellant will also be transported from chamber five through delivery pipe three to the fuel collecting chamber or oxidizer collecting chamber in the annular injection plate two; and is injected through the corresponding propellant nozzle group into detonation combustion chamber two for combustion; At this time, detonation combustion chamber one and detonation combustion chamber two work together to provide thrust; Step 2-3, left-shift thrust mode three: Move the valve stem in the left-shift thrust mode two to the left for the third time. At this time: The valve core two only seals and plugs the front side of chamber two, and the rear side of chamber two is connected to chamber three; The valve core three only seals and plugs the front side of chamber four, and the rear side of chamber four is connected to chamber five; The valve core four only seals and plugs the front side of chamber six, and the rear side of chamber six is connected to chamber seven; On the one hand, the propellant is transported from chamber three through delivery pipe two to the fuel collecting chamber or oxidizer collecting chamber in the annular injection plate one; and is injected through the corresponding propellant nozzle group into detonation combustion chamber one for combustion; The propellant will also be transported from chamber five through delivery pipe three to the fuel collecting chamber or oxidizer collecting chamber in the annular injection plate two; and is injected through the corresponding propellant nozzle group into detonation combustion chamber two for combustion; The propellant will also be transported from chamber seven through delivery pipe four to the fuel collecting chamber or oxidizer collecting chamber in the annular injection plate three; and is injected through the corresponding propellant nozzle group into detonation combustion chamber three for combustion; At this time, detonation combustion chamber one, detonation combustion chamber two and detonation combustion chamber three work together to provide thrust.

8. The method for using a variable-thrust rotating detonation space engine according to claim 6, characterized in that: In step 3, the implementation methods of the three right-shift thrust modes include the following steps: Step 3-1, right-shift thrust mode one: Move the valve stem in the reset state to the right once. At this time: The valve core two still seals and plugs both sides of chamber two; The valve core three only seals and plugs the rear side of chamber four, and the front side of chamber four is connected to chamber three; The valve core four still seals and plugs both sides of chamber six; The propellant is transported from chamber three through delivery pipe two to the fuel collecting chamber or oxidizer collecting chamber in the annular injection plate one; and is injected through the corresponding propellant nozzle group into detonation combustion chamber one for combustion; at this time, only detonation combustion chamber one provides thrust; Step 3-2, right-shift thrust mode two: Move the valve stem in the right-shift thrust mode one to the right for the second time. At this time: The valve core two still seals and plugs both sides of chamber two; The valve core three only seals and plugs the rear side of chamber four, and the front side of chamber four is connected to chamber three; The valve core four only seals and plugs the rear side of chamber six, and the front side of chamber six is connected to chamber five; On the one hand, the propellant is transported from chamber three through delivery pipe two to the fuel collecting chamber or oxidizer collecting chamber in the annular injection plate one; and is injected through the corresponding propellant nozzle group into detonation combustion chamber one for combustion; The propellant will also be transported from chamber five through delivery pipe three to the fuel collecting chamber or oxidizer collecting chamber in the annular injection plate two; and is injected through the corresponding propellant nozzle group into detonation combustion chamber two for combustion; At this time, detonation combustion chamber one and detonation combustion chamber two work together to provide thrust; Step 3-3, right-shift thrust mode three: Move the valve stem in the right-shift thrust mode two to the right for the third time. At this time: The valve core two only seals and plugs the rear side of chamber two, and the front side of chamber two is connected to chamber one; The spool three only seals and plugs the rear side of the chamber four, and the front side of the chamber four is communicated with the chamber three; The spool four only seals and plugs the rear side of the chamber six, and the front side of the chamber six is communicated with the chamber five; On the one hand, the propellant is transported from the chamber one to the fuel collecting chamber or the oxidizer collecting chamber in the annular injection plate three through the delivery pipe one; and is injected into the detonation combustion chamber three through the corresponding propellant nozzle group for combustion; The propellant will also be transported from the chamber three to the fuel collecting chamber or the oxidizer collecting chamber in the annular injection plate one through the delivery pipe two; and is injected into the detonation combustion chamber one through the corresponding propellant nozzle group for combustion; The propellant will also be transported from the chamber five to the fuel collecting chamber or the oxidizer collecting chamber in the annular injection plate two through the delivery pipe three; and is injected into the detonation combustion chamber two through the corresponding propellant nozzle group for combustion; At this time, the detonation combustion chamber one, the detonation combustion chamber two and the detonation combustion chamber three work together to provide thrust.

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