A recoverable rocket and its recovery deceleration method

Abstract

The present invention discloses a recyclable rocket and its recovery deceleration method, which relates to the field of aerospace. It includes a rocket body and two deceleration wings. The rocket body includes a structure system, a propulsion system, a control system and a tripod. One end of the deceleration wing is connected to the outer shell of the rocket body, and the other end is connected to a deceleration mechanism. The deceleration mechanism includes a turbo engine mechanism. The turbo engine mechanism is connected to the rocket body through a pipeline installed in the deceleration wing. The rocket body supplies the energy required for work to the turbo engine mechanism. A propeller mechanism is arranged below the turbo engine mechanism. The propeller is connected to the transmission shaft of the turbo engine mechanism. The propeller mechanism rotates driven by the turbo engine, and generates a thrust opposite to the movement direction of the rocket through the interaction with the air, so as to decelerate the rocket during the recovery process. The beneficial effect of the present invention is that it can effectively realize the recycling of the rocket.

Description

Technical Field

[0001] The present invention mainly relates to the field of aerospace, and specifically relates to a recoverable rocket and its recovery deceleration method. Background Art

[0002] The research on the technology of recovering and reusing launch vehicles aims to reduce the launch cost. As is well known, the cost of space launches has always been extremely high. Sending 1 kg of an object into space costs approximately 10,000 to 20,000 US dollars because launch vehicles are used only once. The fuel cost of a launch vehicle is only about 1 / 200 of the launch cost. Parts such as the rocket's navigation control system, fuel tank, and rocket engine are the truly most valuable parts.

[0003] In addition, as space exploration becomes more active, more and more private enterprises at home and abroad have joined space activities to experience brief weightlessness or even space tourism. The market demand is large and the development speed is fast. In this context, the recovery and reuse of rockets are particularly important.

[0004] To sum up, if rockets cannot be recovered and reused, it is not only costly, but the abandonment of rockets also causes damage to the environment, and even threatens the life and property safety on the ground, severely restricting the development of rocket technology and space exploration. Summary of the Invention

[0005] To solve the deficiencies of the prior art, the present invention provides a recoverable rocket and its recovery deceleration method, which can effectively achieve the recovery and reuse of rockets.

[0006] To achieve the above object, the present invention is realized through the following technical solutions:

[0007] A recoverable rocket includes a rocket main body and at least two deceleration wings. One end of each deceleration wing is connected to the outer shell of the rocket main body, and the other end is connected to a deceleration mechanism. The deceleration mechanism includes a turbo engine and a pair of propellers. The turbo engine is connected to the rocket main body through a pipeline installed in the deceleration wing, and the rocket main body supplies the energy required for the operation of the turbo engine. A pair of propellers is arranged below the turbo engine. The propeller mechanism is connected to the transmission shaft of the turbo engine. The propellers rotate under the drive of the turbo engine, and interact with the air to generate a thrust opposite to the direction of the rocket's movement, so as to decelerate the rocket during the recovery process. The rocket main body includes a structure system, a propulsion system, a control system, and a landing gear.

[0008] The described structural system is the base of the rocket, which is used to maintain the shape of the rocket and connect all components on the rocket into an integrated whole. The described propulsion system includes a jet engine, fuel, oxidizer, and propellant pump installed at the bottom of the rocket body, etc. The described control system includes a guidance and navigation system, an attitude control system, a power supply and distribution system, and software and hardware systems that connect each actuator and ensure the normal operation of each actuator.

[0009] The described guidance and navigation system is used for the spatial positioning of the rocket and guiding the rocket to move along a set orbit. The described attitude control system is used to understand and adjust the attitude of the rocket to keep the rocket in a correct flight attitude. The described power supply and distribution system is used to provide electrical energy for various instruments, equipment, sensors, and other devices that require electricity.

[0010] The described attitude control system also includes a liquid nitrogen attitude adjustment system, which includes a liquid nitrogen storage tank, a delivery pipeline, a jet thruster, and related sensors. The jet's reaction force is used to correct the three flight attitude angles (roll, yaw, and pitch) of the rocket's movement around its center of mass, ensuring that the rocket's attitude meets the requirements of the mission.

[0011] The bottom of the described rocket body is also provided with a tripod, which is the base for supporting and maintaining the stability of the rocket. The tripod is a collapsible tripod, which is in a retracted state during the rocket launch phase and will deploy during the landing phase of the rocket recovery.

[0012] One end of the described deceleration wing is connected to the upper half of the rocket body, and the connection position is significantly higher than the center of gravity of the rocket body. Its function is to help keep the rocket in an attitude suitable for activating each deceleration mechanism to decelerate it during the recovery process. During the stage of recovering the rocket, the interaction between the deceleration wing and its attached deceleration mechanism and the air generates a force that hinders forward movement, pulling the rocket body to decelerate together. When the deceleration pulling force of the deceleration wing acts significantly higher than the center of gravity of the rocket body, the forces on each part of the rocket body are unbalanced, and the rocket body adjusts its attitude to move its center of gravity towards the forward direction to seek balance, so that the attitude of the rocket body has a tendency to keep the jet engine at the bottom pointing in the direction of movement. This attitude is most suitable for activating each deceleration mechanism, including the jet engine, to decelerate the rocket. Similar to a badminton and a shuttlecock in flight, the part with greater resistance tends to be at the back and the center of gravity is towards the front. The deceleration wing can also install multiple deceleration mechanisms or install different types of deceleration mechanisms, such as a deceleration parachute, etc.

[0013] The described turbine engine includes a compressor, a turbine, a combustion chamber, and a transmission shaft. The turbine engine obtains the oxidizer and fuel required for combustion from the rocket body through a delivery pipeline provided in the deceleration wing flank, and the high-temperature and high-pressure gas after the combustion reaction in the combustion chamber blows the turbine to do work. The transmission shaft drives the propeller located below to rotate.

[0014] A recovery deceleration method for a recoverable rocket. The recovery method generally includes the following steps during a single rocket recovery process:

[0015] Step 1 - Using the interaction between the deceleration mechanism on the deceleration wing flank and the air, adjust the rocket to a posture suitable for each deceleration mechanism to exert its deceleration effect.

[0016] In the initial stage of rocket recovery, taking the example of the rocket rising to the highest point and then falling vertically, the posture of the rocket is not necessarily exactly vertical. At this time, start the deceleration mechanism of the deceleration wing flank, the rocket will deploy the propeller, start the turbine engine, and make the propeller rotate. Because the deceleration wing flank is installed at a position significantly higher than the center of gravity of the rocket, as the rocket falls and the air density gradually increases, the interaction between the propeller and the air also increases, and the rocket will tend to become vertical. If other deceleration mechanisms are installed on the deceleration wing flank, such as a deceleration parachute, the deceleration parachute will also be opened in this step, and the air resistance received by the deceleration parachute also helps the rocket to adjust to a vertical posture, which is most suitable for the propeller, deceleration parachute, and jet engine to exert their deceleration effects on the rocket.

[0017] Step 2 - Control the power of the turbine engine to make the rate of the rocket when it falls near the ground meet the requirements of a soft landing.

[0018] The lower the altitude, the greater the air density, and the propeller of the turbine engine can obtain a greater lifting force from the air to decelerate the rocket. The control system will evaluate based on the rate and altitude of the rocket and control the power of the turbine engine to ensure that the falling rate of the rocket is reduced to meet the requirements of a soft landing when approaching the ground, avoiding crashing into the ground out of control.

[0019] Step 3 - Move the rocket to the target landing site.

[0020] When the rocket falls close to the ground, the control system will set an optimal route close to the target landing site according to conditions such as the optional landing site and the spatial position of the rocket itself, and control the movement of the rocket in the horizontal and vertical directions to move it to the target landing site.

[0021] Step 4 - Let the rocket land.

[0022] After reaching the target landing site, first open the tripod at the bottom of the rocket, then slowly descend to the ground, and turn off the turbine engine to complete the entire landing process.

[0023] In the above step one, when the attitude of the rocket cannot be adjusted by the interaction between the deceleration mechanism on the deceleration flank and the air, or the attitude adjustment is unsuccessful, the liquid nitrogen attitude adjustment system will be activated to adjust the rocket to the required attitude. In some launch missions, the recovered rocket may be in a high-vacuum state far from the ground, and the attitude adjustment before decelerating by the rocket jet engine cannot be achieved by the interaction between the deceleration mechanism and the air. Or in some missions, the rocket may roll violently due to an accident when releasing the load, and the interaction between the deceleration mechanism and the air may not be sufficient to adjust the rocket attitude within the required time. In these situations, the liquid nitrogen attitude adjustment system needs to be activated to help correct the attitude and ensure the smooth progress of the subsequent steps.

[0024] In the above step one or step two, if the control system of the rocket believes that the moving speed of the rocket is too fast and threatens the structural safety of the rocket or the goal of soft landing, the jet engine of the rocket will be activated to help the rocket decelerate to the required range. The control system will monitor parameters such as the height and speed of the rocket and make judgments based on its own conditions. For example, when falling too fast, the power of the turbine engine driving the propeller may not be sufficient to ensure that the rocket speed is reduced to meet the landing requirements before reaching near the ground. Or it is considered that the current speed is too fast, which may cause some weak parts to exceed the load, or it is easy to be damaged due to friction with the air when heating, and the jet engine of the rocket will be activated to help the rocket decelerate to the safe range.

[0025] The above step two and step three can be carried out synchronously, so that the rocket moves towards the target landing point while falling. While using the deceleration mechanism of the rocket to decelerate the rocket during the descent, the control system can also call the function of translating the rocket to accurately control the descent trajectory of the rocket, so that the rocket moves towards the target landing point while falling, or minimizes the deviation from the landing point.

[0026] Compared with the prior art, the beneficial effects of the present invention are:

[0027] 1. The suspension of the rocket relies on the thrust of the propeller, and its landing method is non-jet type, with lower requirements for the landing site.

[0028] 2. Compared with the jet landing method, the present invention is easier to simulate on the ground, with lower development difficulty and cost.

[0029] 3. The present invention achieves landing without relying on rocket jets, without modifying the original propulsion system of the rocket, and has good compatibility with various types of rockets. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] AttachmentFigure 1 It is a schematic front view structure diagram of removing the protection cylinder in Embodiment 1 of the present invention;

[0031] Appendix Figure 2 It is a schematic diagram of the turbine engine mechanism of the present invention;

[0032] Appendix Figure 3 It is a schematic diagram of the deceleration parachute mechanism of the present invention;

[0033] Appendix Figure 4 It is a schematic diagram of the deceleration thin plate structure of the present invention;

[0034] Appendix Figure 5 It is a schematic top view structure diagram of Embodiment 2 of the present invention;

[0035] Appendix Figure 6 It is a schematic front view structure diagram of Embodiment 3 of the present invention.

[0036] Reference numerals shown in the drawings: 1, rocket body; 11, folding leg; 12, jet engine; 2, deceleration flank; 21, rotating device; 3, turbine engine mechanism; 31, turbine; 32, combustion chamber; 33, transmission shaft; 34, fairing; 4, propeller mechanism; 41, first movable joint; 42, protection cylinder; 43, propeller blade; 5, deceleration parachute mechanism; 51, deceleration thin plate; 52, second movable joint; 53, steel wire; 54, lattice frame; 541, ventilation opening; 542, shaft hole; 55, guide vane; 551, rotating shaft. Detailed Embodiments

[0037] In combination with the drawings and specific embodiments, the present invention will be further described. It should be understood that these embodiments are only used to illustrate the present invention and not to limit the scope of the present invention. In addition, it should be understood that after reading the content taught by the present invention, those skilled in the art can make various changes or modifications to the present invention, and these equivalent forms also fall within the scope defined by the present application.

[0038] Embodiment 1:

[0039] As shown in the appendix Figure 1 shown, it includes a rocket body 1 and two deceleration flanks 2. One end of the deceleration flank 2 is connected to the outer shell of the rocket body 1, and the other end is connected to a deceleration mechanism. The deceleration mechanism includes a turbine engine mechanism 3 and a propeller mechanism 4. The turbine engine mechanism 3 is connected to the rocket body 1 through a pipeline installed in the deceleration flank 2, and the rocket body 1 supplies the energy required for work to the turbine engine mechanism 3. A propeller mechanism 4 is arranged below the turbine engine mechanism 3, and the propeller mechanism 4 is connected to the transmission shaft 33 of the turbine engine mechanism 3 (Appendix Figure 2) The propeller mechanism 4 rotates under the drive of the turbine engine mechanism 3, and the interaction with the air generates a thrust opposite to the direction of the rocket's movement, decelerating the rocket during the recovery process. The rocket body 1 includes a structure system, a propulsion system, a control system, and a landing gear 11.

[0040] As shown in the Figure 2 accompanying drawings, the turbine engine mechanism 3 is a turbine engine without an air compressor. The oxidizer and fuel required for its operation are provided by a pump installed on the rocket body 1. The pump controls the flow rates of the oxidizer and fuel respectively, thereby adjusting the power of the turbine engine mechanism 3. The turbine engine mechanism 3 includes a turbine 3_{1}, a combustion chamber 3_{2}, and a transmission shaft 3_{3}. The turbine engine mechanism 3 obtains the oxidizer and fuel required for combustion from the rocket body 1 through a delivery pipeline provided in the deceleration wing 2. The high-temperature and high-pressure gas after the combustion reaction in the combustion chamber 3_{2} blows the turbine 3_{1} above to do work. The transmission shaft 3_{3} drives the propeller mechanism 4 located below to rotate. A conical fairing 3_{4} is also provided above the turbine engine mechanism 3. The fairing 3_{4} protects the engine and reduces air resistance during the rocket launch phase. When the rocket enters the recovery phase, the fairing 3_{4} will be discarded so that the combustion exhaust gas can be discharged from above.

[0041] In this embodiment, the propulsion system of the rocket body 1 uses liquid oxygen as the oxidizer and kerosene as the fuel. When the fuel burns in pure oxygen, the temperature is often too high, shortening the life of the turbine mechanism 3. The reaction temperature can be reduced by deviating from the ratio of sufficient reaction between oxygen and kerosene. For example, injecting too much oxygen or too much kerosene into the combustion chamber 3_{2} to keep the reaction temperature within the stable operating range of the turbine engine mechanism 3.

[0042] The propeller mechanism 4 is a foldable propeller. A first movable joint 4_{1} is provided between the root of each propeller blade and the transmission shaft 3_{3} of the turbine engine. In the non-operating state, all the propeller blades are folded together, and the direction is parallel to the transmission shaft 3_{3}. The first movable joint 4_{1} is an elastic movable joint with a spring inside. Its elasticity makes each propeller blade 4_{3} of the propeller mechanism 4 tend to unfold when there is no external force constraint, and it needs to be constrained by a certain external force to be folded together. There is a protective cylinder 4_{2} outside the propeller mechanism 4. The protective cylinder 4_{2} constrains the propeller mechanism 4 to keep it in the folded state, reducing the air resistance on the propeller during the rocket launch phase. When the rocket enters the recovery phase, the protective cylinder 4_{2} will be untied and discarded, and the propeller mechanism 4 is released from the constraint, allowing the propeller blades 4_{3} to unfold and be driven by the transmission shaft 3_{3} to rotate.

[0043] Another way to deploy the propeller blade 43 can also be adopted. The first movable joint 41 is connected to an electric drive mechanism, and the electric drive mechanism can deploy the blade from the folded state into a state suitable for work.

[0044] As shown in the appendix Figure 3 As shown, a rotating device 21 is provided between the deceleration side wing 2 and the turbine engine mechanism 3. The rotating device 21 can make the turbine engine mechanism 3 rotate relative to the deceleration side wing 2, so that the airflow direction generated by the propeller mechanism 4 during operation can be adjusted within a certain angle range. Thus, while the propeller mechanism 4 can generate an upward thrust, it can also generate a force that makes the rocket body 1 rotate around its own central axis, enabling the rocket to move in all directions in the air only by the thrust of the propellers on both side deceleration side wings.

[0045] Currently, the most common situation is that the first-stage rocket in a multi-stage rocket is recovered. In this embodiment, the present invention will be described as the first-stage rocket. When the first-stage rocket is launched to a predetermined height and separated from the second-stage rocket, the first-stage rocket still rises by inertia and then turns into an accelerated fall after reaching a certain height. Taking this as an example, the first-stage rocket realizes recovery through the following steps.

[0046] Step 1 - Adjust the rocket to an approximately vertical attitude.

[0047] The control system will discard the protective cylinder 42 of the propeller mechanism 4 to deploy the propeller mechanism 4. At the same time, it will also discard the fairing 34 of the turbine engine mechanism 3 and start the turbine engine mechanism 3 to make the propeller mechanism 4 rotate. When the air is extremely thin, the energy consumed by rotating the propeller is very little, equivalent to an idling state. As the rocket accelerates downward and the air density gradually increases, the interaction between the propeller mechanism 4 and the air becomes larger. The deceleration side wing 2 will move backward and the center of gravity of the rocket will move forward, tending to become a vertical attitude, that is, the jet engine 12 at the bottom of the rocket body 1 points in the direction of its movement.

[0048] Step 2 - Control the power of the turbine engine to make the rate of the rocket when it falls near the ground meet the requirements of a soft landing.

[0049] As the altitude of the rocket continuously decreases, the air density increases accordingly. At the same rotational speed, the air resistance received by the propeller mechanism 4 is greater, and the obtained reaction thrust is also greater, which has a better deceleration effect on the rocket. The control system will evaluate according to the rate and altitude of the rocket and control the power of the turbine engine mechanism 3 to make the falling rate of the rocket approach 0 m / s when it is near the ground. The main task at this stage is to decelerate the rocket, and at the same time, use the rocket's moving ability in the horizontal direction to move towards the target landing point during the fall, so as to be as close as possible to the landing point when it falls near the ground.

[0050] Step Three - Move the rocket towards the target landing site.

[0051] When the rocket descends close to the ground, it may not be exactly directly above the target landing point. At this time, the suspension of the rocket entirely depends on the thrust of the propeller mechanism 4. The control system controls the movement of the rocket to move the rocket towards the target landing site. For the rocket with only two flanks in this embodiment, by controlling the magnitude of the thrust of the propeller mechanisms 4 on both sides and coordinating with the rotating device 21 between the flank 2 and the turbo engine mechanism 3, the horizontal movement of the rocket can be controlled.

[0052] Step Four - Let the rocket land.

[0053] Upon reaching above the target landing point, first open the folding leg frame 11 at the bottom of the rocket main body 1, then slowly descend to the ground, and turn off the turbo engine mechanism 3. Thus, the entire landing process is completed.

[0054] In addition, in the above Steps One and Two, the control system of the rocket monitors the height and speed of the rocket. If it is considered that the falling speed of the rocket is too fast, which may exceed the range that its structure can withstand or make it difficult to achieve the soft landing target, the jet engine 12 of the rocket main body 1 will be activated to help the rocket decelerate to a safe range.

[0055] In this embodiment, another deceleration mechanism can be installed on the deceleration flank 2 to enhance the deceleration effect. The deceleration mechanism is one or more deceleration parachute mechanisms 5. The deceleration parachute mechanism 5 is a pair of deceleration thin plates 51 installed on both sides of the deceleration flank 2. One end of the deceleration thin plate 51 is connected to the upper half of the deceleration flank 2 through a second movable joint 52. The movement of the second movable joint 52 is controlled by a driving device. The driving device can unfold the deceleration thin plate 51 from the retracted state into a flat state. When the deceleration thin plate 51 is in the retracted state, it adheres to the surface of the deceleration flank 2, reducing the air resistance suffered by the rocket during the ascending stage; during the recovery stage when the rocket is falling, the deceleration thin plate 51 will be unfolded to use the air resistance to help the rocket decelerate.

[0056] A number of steel wires 53 can also be arranged on the deceleration thin plate 51 to be connected to the deceleration flank 2. The deceleration flank 2 obliquely pulls the unfolded deceleration thin plate 51 through the steel wires 53, transferring a part of the air pressure received by the deceleration thin plate 51 to the deceleration flank 2 through the steel wires 53, avoiding damage to the second movable joint 52 due to excessive torsion and also helping to reduce the weight of the deceleration thin plate 51.

[0057] The deceleration parachute mechanism 5 installed on the deceleration flank 2 can also be installed at the vacant position of the outer shell of the rocket body 1. The rocket outer shell should be regarded as an equivalent replacement of the deceleration flank 2. Similar to the situation of being installed on the deceleration flank 2, for the deceleration parachute installed on the outer shell of the rocket body, its deceleration thin plate is close to the outer shell of the rocket body in the closed state and only expands into a flat state during operation. The provided steel wires are connected to the outer shell of the rocket body and obliquely pull the expanded deceleration thin plate.

[0058] The installed deceleration parachute mechanism 5 is opened in Step 1 of the aforementioned rocket recovery process. Its beneficial effects include:

[0059] 1. In the initial stage of the rocket's descent, the air resistance received by the deceleration parachute mechanism 5 is also helpful for adjusting the rocket body 1 to a vertical attitude.

[0060] 2. The deceleration parachute mechanism 5 has a direct deceleration effect on the rocket itself, prolonging the time of the rocket's descent process, which in turn prolongs the working time of the propeller mechanism 4 in the air, indirectly increasing the deceleration effect of the propeller mechanism 4 on the rocket.

[0061] 3. A single large-area deceleration parachute can be used, or multiple small-area deceleration parachutes can be used. The advantage of using multiple small deceleration parachutes is that even if an individual deceleration parachute fails, it will not cause the failure of the soft landing target.

[0062] As shown in the appendix Figure 4 In this embodiment, as shown, the deceleration thin plate 51 constituting the deceleration parachute mechanism 5 can adopt a structure of a lattice frame 54 plus a flow guiding blade 55. There are several square ventilation openings 541 in the lattice frame 54, and each ventilation opening 541 is paired with a flow guiding blade 55. The flow guiding blade 55 is fixed on a rotating shaft 551. The inner wall of the ventilation opening 541 has a shaft hole 542 for cooperating with the rotating shaft 551. The rotating shaft 551 is connected to an electric mechanism. The rotation of the electric mechanism can change the angle of the flow guiding blade 55. By controlling the angle of the flow guiding blade 55, the direction and magnitude of the pressure of the airflow flowing through the ventilation opening 541 acting on the flow guiding blade 55 can be adjusted.

[0063] The lattice frame 54 can be provided with multiple ventilation openings 541. The rotating shafts 551 of the flow guiding blades 55 of some ventilation openings 541 are placed perpendicular to the rotating shafts 551 of the flow guiding blades 55 of other ventilation openings 541. By individually adjusting different flow guiding blades 55, a resultant force with a larger angle range can be generated. Thus, during the rocket's landing process, its movement direction and attitude can be adjusted by the deceleration parachute mechanism 5 to a certain extent, enabling the rocket to approach the target landing point while descending.

[0064] In this embodiment, the driving device of the second movable joint 52 of the deceleration parachute mechanism 5 adopts a one-way driving mode. The movement of the driving device only expands the deceleration thin plate 51 from the retracted state to the flat state, and will not change the deceleration thin plate 51 from the flat state to the retracted state during reset. Therefore, when the driving device is reset, how the deceleration thin plate 51 moves is determined by the external force it receives. When the rocket is in the initial stage of recovery and the deceleration parachute mechanism 5 is opened, since the rocket is always falling, the deceleration thin plate 51 is subjected to an upward wind pressure, and the deceleration thin plate 51 remains in the flat-expanded state. When the rocket approaches the ground, its falling speed is close to zero, and the upward wind pressure on the deceleration thin plate 51 is also close to zero; in addition, the rotation of the propeller mechanism 4 causes the air above to flow downward, and the air pressure on the deceleration thin plate 51 becomes downward. At this time, the deceleration parachute mechanism 5 is preferably retracted. The advantage of adopting one-way driving for the second movable joint 52 of the deceleration thin plate 51 is that when the external force received by the deceleration thin plate 51 causes it to close, the deceleration thin plate 51 closes along with the external force.

[0065] Embodiment 2:

[0066] As shown in the attached Figure 5 figure, it includes a rocket body 1 and three deceleration flanks 2. One end of the deceleration flank 2 is connected to the outer shell of the rocket body 1, and the other end is connected to a deceleration mechanism, and the deceleration mechanism includes a turbo engine mechanism 3 and a propeller mechanism 4. The turbo engine mechanism 3 is connected to the rocket body 1 through a pipeline installed in the deceleration flank 2, and the rocket body 1 supplies the energy required for work to the turbo engine mechanism 3. A propeller mechanism 4 is arranged below the turbo engine mechanism 3, and the propeller mechanism 4 is connected to the transmission shaft of the turbo engine mechanism 3. The propeller mechanism 4 rotates under the drive of the turbo engine mechanism 3, and generates a thrust opposite to the movement direction of the rocket through the interaction with the air to decelerate the rocket during the recovery process. The rocket body 1 includes a structure system, a propulsion system, a control system and a landing gear.

[0067] The differences between this embodiment and the previous Embodiment 1 are as follows:

[0068] 1. In Embodiment 1, there are only two deceleration flanks 2, while in this embodiment, there are three.

[0069] 2. In Embodiment 1, at least one deceleration flank 2 must be equipped with a rotating device 21 that can rotate the turbine engine mechanism 3 in order to enable the rocket to move in all directions. The rotating device 21 in the deceleration flank 2 of this embodiment is not necessary. If the rotating device 21 is installed in one or more deceleration flanks 2, the movement of the rocket will be more flexible. If the rotating device 21 is not installed, by controlling the thrust of the propeller blades 43 of the three propeller mechanisms 4, the rocket body 1 can also be tilted and moved in any direction.

[0070] In this embodiment, the steps of rocket recovery are the same as those described in the previous embodiment. In this embodiment, a deceleration parachute mechanism can also be installed on the deceleration flank 2. The structure, use, and usage method of the deceleration parachute are the same as those in the previous embodiment. The design of three flanks in this embodiment has the beneficial effect that it is more suitable for heavier rockets than two flanks, and the design of three or more than three flanks can omit the rotating device 21 between the deceleration flank 2 and the turbine engine mechanism 3 and still achieve free movement in the water screen direction.

[0071] In summary, the discussion of this embodiment can be applied to the situation where more than three flanks are installed on the rocket body.

[0072] Embodiment 3:

[0073] As shown in the attached Figure 6 , a recoverable rocket includes a rocket body 1 and two deceleration flanks 2. The rocket body 1 includes a structure system, a propulsion system, a control system, and a tripod 11. One end of the deceleration flank 2 is connected to the upper half of the rocket body 1, and the connection position is significantly higher than the center of gravity of the rocket body 1. Its function is to help keep the rocket in a posture suitable for calling various deceleration mechanisms to decelerate it during the recovery process. A deceleration mechanism is installed on the deceleration flank 2. The deceleration mechanism includes one or more deceleration parachutes 5. The deceleration parachute 5 is a pair of deceleration thin plates 51 (attached Figure 3 ) installed on both sides of the deceleration flank 2. One end of the deceleration thin plate 51 is connected to the upper half of the deceleration flank 2 through a second movable joint 52. The movement of the second movable joint 52 is controlled by a driving device, and the driving device can unfold the deceleration thin plate 51 from the retracted state to the straight state. The deceleration thin plate 51 adopts a structure of a lattice frame 54 plus flow guiding blades 55 (attached Figure 4The lattice frame 54 contains several square vents 541, each equipped with a guide vane 55. The guide vanes 55 are fixed to a rotating shaft 551. The inner wall of the vents 541 has an axial hole 542 that fits the rotating shaft 551. The rotating shaft 551 is connected to an electric mechanism. Rotation of the electric mechanism changes the angle of the guide vanes 55. By controlling the angle of the guide vanes 55, the direction and magnitude of the pressure exerted on the guide vanes 55 by the airflow passing through the vents 541 can be adjusted. The guide vanes 55 convert the vertical pressure acting on the deceleration plate 51 into a horizontal force, thereby enabling the parachute 5 to decelerate the rocket using air resistance while also driving the rocket horizontally. The propulsion system includes several jet engines 12 located at the bottom of the rocket body 1. These jet engines 12 are used to reduce the rocket's speed to the required level for a soft landing before landing.

[0074] This embodiment differs from the aforementioned embodiment 1 in that the only deceleration mechanism installed on the deceleration wing 2 in this embodiment is a parachute 5. In contrast to the deceleration mechanism in embodiment 1, which consists of a turbine engine mechanism 3 and a propeller mechanism 4, the parachute 5 is merely an additional deceleration mechanism to enhance the deceleration effect. Because the wind pressure acting on the parachute 5 originates from its relative motion with the air, the parachute's deceleration capability is driven by the rocket's motion and cannot reduce the rocket's speed to near zero. Therefore, this embodiment must utilize the rocket's jet engine 12 to help reduce the rocket's speed to a near-zero landing speed during landing. The advantage of installing the parachute 5 only on the deceleration wing 2 in this embodiment is that it eliminates the complex structure of the turbine engine mechanism 3 and the propeller mechanism 4. However, this requires greater precision in the ability to position the rocket and control its descent trajectory.

[0075] Currently, the most common scenario involves recovering the first stage of a multi-stage rocket. In this embodiment, the present invention will be described using the first stage as an example. After the first stage reaches a predetermined altitude and separates from the second stage, it continues its inertial ascent until reaching a certain altitude, transitioning to an accelerated descent. Using this example, the first stage is recovered using the following steps.

[0076] Step 1 - Adjust the rocket to a nearly vertical position.

[0077] The control system deploys the parachute 5. As the rocket accelerates downward and the air density gradually increases, the interaction between the parachute 5 and the air increases, the deceleration wing 2 moves backward, and the center of gravity of the rocket moves forward, tending to become a vertical posture, that is, the jet engine 12 at the bottom of the rocket body 1 points in the direction of its movement.

[0078] Step 2 - Control the deflector blades of the deceleration parachute to decelerate the rocket while moving the rocket towards the target landing point.

[0079] It is very difficult to decelerate the rocket to meet the requirements of a soft landing with a limited deceleration parachute area, and the jet engine 12 has very weak ability to move the rocket horizontally. This means that the rocket has to seize the opportunity to move towards the target landing point while falling. The control system will control the deflector blades 55 of the deceleration parachute 5, and use the combined force coordinated by each deflector blade 55 to change the rocket's movement in the horizontal direction, so that the rocket approaches the target landing point while falling.

[0080] Step 3 - Start the jet engine to reduce the rocket's descent speed to meet the requirements of a soft landing and achieve landing.

[0081] When the rocket descends close to the ground, its speed has not yet reached the requirements of a soft landing. The control system will monitor the rocket's descent speed and altitude, calculate the appropriate time point to start the jet engine 12, and ensure that the rocket's speed is reduced to close to zero when landing. Then turn off the engine 12 and open the landing gear 11 at the bottom of the rocket body to complete the landing.

[0082] In addition, in the above Steps 1 and 2, the rocket's control system will monitor the rocket's altitude and speed. If it is considered that the rocket's descent speed is too fast, which may exceed the range that its structure can withstand or make it difficult to achieve the soft landing target, the jet engine 12 of the rocket body 1 will be started to help the rocket decelerate to a safe range.

Claims

1. A recoverable rocket comprising a rocket body and two deceleration wings, wherein the rocket body comprises a structural system, a propulsion system, a control system, and a tripod, and is characterized by: One end of the deceleration wing is connected to the outer shell of the rocket body, and the other end is connected to a deceleration mechanism. The deceleration mechanism includes a turbine engine mechanism. The turbine engine mechanism is connected to the rocket body through a pipe installed in the deceleration wing. The rocket body supplies the turbine engine mechanism with energy required for operation. A propeller mechanism is provided below the turbine engine mechanism. The propeller mechanism is connected to the transmission shaft of the turbine engine mechanism. The propeller mechanism rotates under the drive of the turbine engine, and the interaction with the air generates a thrust opposite to the direction of the rocket's movement, thereby decelerating the rocket during the recovery process. A deceleration mechanism is installed on the deceleration wing. The deceleration mechanism is one or more deceleration parachute mechanisms. The deceleration parachute mechanism includes a pair of deceleration thin plates installed on both sides of the deceleration wing. One end of the deceleration thin plate is connected to the upper half of the deceleration wing via a second movable joint. The movement of the second movable joint is controlled by a driving device. The driving device can unfold the deceleration thin plate from a folded state to a flat state. In the folded state, the deceleration thin plate is attached to the surface of the deceleration wing to reduce the air resistance encountered by the rocket during the ascent stage. During the recovery stage of the rocket's descent, the deceleration thin plate will be unfolded to use air resistance to help decelerate the rocket. A plurality of steel wires are provided on the deceleration plate and connected to the deceleration side wings. The deceleration side wings obliquely pull the unfolded deceleration plate through the steel wires, and transmit part of the air pressure exerted on the deceleration plate to the deceleration side wings through the steel wires, thereby preventing the second movable joint from being damaged by excessive torque and also helping to reduce the weight of the deceleration plate.

2. A reusable rocket according to claim 1, characterized in that: One end of the deceleration wing is connected to the upper part of the rocket body, and the connection position is significantly higher than the center of gravity of the rocket body. Its function is to help keep the rocket in a posture suitable for calling various deceleration mechanisms to slow it down during the recovery process.

3. A reusable rocket according to claim 1, characterized in that: The main body of the turbine engine mechanism is a turbine engine without an air compressor. The oxidant and fuel required for its operation are provided by a pumper installed on the rocket body. The pumper controls the flow of the oxidant and fuel respectively, thereby adjusting the power of the turbine engine. The turbine engine mechanism includes a turbine, a combustion chamber, and a transmission shaft. The turbine engine mechanism obtains the oxidant and fuel required for combustion from the rocket body through a delivery pipe arranged in the deceleration wing. The high-temperature and high-pressure gas after the combustion reaction in the combustion chamber blows the turbine above to perform work, and drives the propeller mechanism located below to rotate through the transmission shaft.

4. A reusable rocket according to claim 1, characterized in that: The propeller mechanism includes propeller blades, which are foldable propellers. A first movable joint is provided between the root of each blade and the transmission shaft of the turbine engine. In a non-working state, all the blades are folded up and their directions are parallel to the transmission shaft.

5. A reusable rocket according to claim 4, characterized in that: The first movable joint is an elastic movable joint with a spring inside. Its elasticity makes each propeller blade tend to be in an expanded state when there is no external force constraint, and requires a certain external force constraint to close. There is a protective tube on the outside of the propeller blade, and the protective tube constrains the propeller blade to keep it in a closed state.

6. A reusable rocket according to claim 4, characterized in that: The first movable joint is connected to an electric drive mechanism, and the electric drive mechanism can unfold the blade from a folded state to a state suitable for working.

7. A recoverable rocket according to claim 4, characterized in that: A rotating device is arranged between the deceleration wing and the turbine engine mechanism. The rotating device can rotate the turbine engine mechanism relative to the deceleration wing, so that the direction of the airflow generated by the propeller mechanism during operation can be adjusted within a certain angle range, so that the propeller blades can generate upward thrust while also generating a force that allows the rocket body to rotate around its own central axis.

8. The recoverable rocket according to claim 1, characterized in that: The driving device of the second movable joint adopts a unidirectional driving method. The movement of the driving device will only unfold the deceleration plate from a folded state to a straight state, and will not change the deceleration plate from a straight state to a folded state when resetting. Therefore, when the driving device is reset, how the deceleration plate moves is determined by the external force it receives.

9. The reusable rocket according to claim 1, characterized in that: The deceleration plate adopts a structure of a lattice frame plus guide blades. There are several square vents in the lattice frame, each vent is equipped with a guide blade, and the guide blade is fixed on a rotating shaft. The inner wall of the vent has an axial hole that matches the above-mentioned rotating shaft. The rotating shaft is connected to an electric mechanism. The rotation of the electric mechanism can change the angle of the guide blade. By controlling the angle of the guide blade, the direction and magnitude of the pressure of the airflow flowing through the vent on the guide blade can be adjusted.

10. A recoverable rocket according to claim 9, characterized in that: The lattice frame is provided with a plurality of vents, and the rotating shafts of the guide vanes of some vents are placed perpendicular to the rotating shafts of the guide vanes of other vents. By adjusting different guide vanes individually, a resultant force with a larger angle range can be generated.

11. A method for recovering and decelerating a recoverable rocket according to any one of claims 1 to 10, characterized in that: The recycling process usually includes the following steps: Step 1: Using the interaction between the deceleration mechanisms on the deceleration wing and the air, adjust the rocket to a posture suitable for each deceleration mechanism to play a deceleration role; Step 2: Control the turbine engine power so that the rocket falls near the ground at a rate that meets the requirements for a soft landing; Step 3 – Move the rocket toward the target landing site; Step 4 – Land the rocket. In the first step, when the interaction between the deceleration mechanism on the deceleration wing and the air cannot be used to adjust the attitude of the rocket, or when the attitude adjustment is unsuccessful, the liquid nitrogen attitude adjustment system will be activated to adjust the rocket to the desired attitude; In step one or step two, if the rocket's control system believes that the rocket's movement speed is too fast and threatens the rocket's structural safety or the goal of soft landing, it will start the rocket's jet engine to help the rocket slow down to within the required range.

12. The recovery and deceleration method according to claim 11, characterized in that: The steps 2 and 3 can be performed simultaneously, so that the rocket falls while moving toward the target landing point.

13. A recoverable rocket comprising a rocket body and two deceleration wings, wherein the rocket body comprises a structural system, a propulsion system, a control system, and a tripod, and wherein: One end of the deceleration wing is connected to the upper part of the rocket body, and the connection position is significantly higher than the center of gravity of the rocket body. Its function is to help keep the rocket in a posture suitable for calling various deceleration mechanisms to decelerate it during the recovery process. A deceleration mechanism is installed on the deceleration wing, and the deceleration mechanism includes one or more deceleration parachutes. The deceleration parachute is a pair of deceleration plates installed on both sides of the deceleration wing. One end of the deceleration plate is connected to the upper part of the deceleration wing via a second movable joint. The movement of the second movable joint is controlled by a driving device. The driving device can unfold the deceleration plate from a folded state to a flat state. The deceleration plate adopts a lattice frame plus guide vane structure. There are a number of square vents in the lattice frame, and each vent The vent is equipped with a guide blade, which is fixed on a rotating shaft. The inner wall of the vent has an axial hole that matches the above-mentioned rotating shaft. The rotating shaft is connected to an electric mechanism. The rotation of the electric mechanism can change the angle of the guide blade. By controlling the angle of the guide blade, the direction and magnitude of the pressure of the airflow flowing through the vent on the guide blade can be adjusted. The function of the guide blade is to convert the vertical pressure acting on the surface of the deceleration plate into a horizontal force, so that the deceleration parachute can use air resistance to decelerate the rocket while also driving the rocket to move in the horizontal direction. The propulsion system includes a number of jet engines arranged at the bottom of the rocket body. The jet engines are used to reduce the speed of the rocket to the requirement of achieving a soft landing before landing.

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