A solid carrier rocket orbit-keeping final stage design method and device
By designing a solid-propellant launch vehicle with an orbital final stage, and utilizing the remaining propellant and functional modules, space experiments on small satellites can be conducted. This solves the problems of high launch costs and orbital debris for small satellites and improves the utilization rate of the launch vehicle's final stage.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- AEROSPACE SCI & IND KET TECH CO LTD
- Filing Date
- 2023-05-26
- Publication Date
- 2026-05-29
AI Technical Summary
In existing technologies, the launch cost of small satellites is relatively high, and the final stage of the launch vehicle becomes space debris after deorbiting, failing to effectively utilize its remaining propellant and functionality.
Design a solid-propellant launch vehicle with a final stage that remains in orbit after separating from the main satellite, carrying a small satellite. The remaining propellant will provide energy for the experimental payload. The rocket will also be equipped with attitude control, telemetry, and orbital maneuvering functions, as well as solar panels and debris retrieval devices, to achieve long-term orbital operation.
It provides more opportunities for space experiments, reduces the cost of small satellite experiments, improves the utilization rate of the final stage of launch vehicles, and reduces orbital debris.
Smart Images
Figure CN116608737B_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of launch vehicle technology, and in particular to a design method and apparatus for a solid-propellant launch vehicle's orbital final stage. Background Technology
[0002] Currently, satellite launch density is high. Most satellites require launch vehicles to enter orbit. After the rocket enters orbit, the final stage of the launch vehicle separates from the satellite. When the distance between the main satellite and the final stage meets safety requirements, the final stage undergoes deorbiting and passivation, becoming space debris. When the final stage undergoes deorbiting and passivation, it generally still retains some propellant, and the final stage itself possesses attitude adjustment, telemetry, and orbital maneuvering capabilities. However, launching some small satellites individually is costly.
[0003] Therefore, reducing the testing costs of small satellites is a technical problem that we need to solve. Summary of the Invention
[0004] In view of the above problems, this invention is proposed to provide a design method and apparatus for a solid-propellant launch vehicle's orbital-deployed final stage. After the main satellite separates from the final stage, a small satellite can remain in orbit to conduct space experiments. This provides more opportunities for space experiments and significantly reduces the testing costs of small satellites.
[0005] According to a first aspect of the present invention, a method for designing a solid-propellant launch vehicle's final stage to remain in orbit is provided. The final stage carries a main satellite and an experimental payload. After the main satellite detaches from the final stage, the experimental payload remains in orbit with the final stage. The method includes:
[0006] Spatial test requirements for obtaining test loads for track-delayed operations;
[0007] Determine the installation location of the test load according to the requirements of the space test;
[0008] The final stage of the solid-propellant launch vehicle is used as the platform for the test payload. After the final stage detaches from the main satellite, the remaining propellant of the final stage provides energy for the final stage and the test payload to operate in orbit.
[0009] Optionally, the installation location of the test load may be determined according to the requirements of the space test, including:
[0010] If the space test requirements for the test load are space environment requirements, then the test load will be installed in the propulsion control compartment of the final stage.
[0011] Optionally, a space debris retrieval device can be installed on the head-mounted structure of the final stage. The space debris retrieval device is used to retrieve debris on the orbit. After the test payload completes the space test, the remaining propellant of the final stage will deorbit the final stage and burn up in the atmosphere.
[0012] Optionally, the installation location of the test load may be determined according to the requirements of the space test, including:
[0013] If the space test requirements for the test payload are space environment requirements, then the adapter structure of the final stage head used to carry the main satellite will be hollowed out, and the test payload will be installed in the hollow part of the adapter structure.
[0014] Optionally, the installation location of the test load may be determined according to the requirements of the space test, including:
[0015] If the space test requirement of the test payload is space exploration, the test payload is installed between the final stage and the adapter structure. At least one main satellite is mounted on the periphery of the adapter structure. When the main satellite is detached from the final stage, the adapter structure is detached from the final stage.
[0016] Optionally, the final stage houses an orbit control engine, an attitude control engine, a central computer, a battery, and an inertial navigation system (INS). The orbit control engine, located at the tail of the final stage, provides power to ensure the rocket's orbital insertion before separation; after separation, it provides orbit-changing power for the remaining payload. The attitude control engine, located near the orbit control engine on a toroidal surface at the tail end, exerts thrust perpendicular to the rocket's direction of motion to change the rocket's attitude. A circular plate is installed within the final stage section, upon which the central computer, battery, and INS are mounted. The central computer contains flight control algorithms that control the entire rocket's flight; the INS provides the rocket with its current attitude angular velocity and axial acceleration, providing data for the flight control algorithms.
[0017] Optionally, the final stage may also be equipped with a star sensor and / or a tertiary sensor connected to the central computer; both the tertiary sensor and the star sensor may be installed on the surface of the final stage column section, behind the solar panel, in order to correct attitude drift caused by the inertial navigation system exceeding its operating conditions due to prolonged operation of the final stage.
[0018] The final stage is also equipped with a ground telemetry system, which communicates bidirectionally with the ground base station.
[0019] In addition, the outer surface of the final stage is also equipped with solar panels. The solar panels are located in the column section of the final stage. The solar panels do not unfold before the main satellite separates from the final stage and are folded up in the column section of the final stage. After the main satellite separates from the final stage, the solar panels unfold to power the central computer, batteries, inertial navigation system, solar sensor and star sensor and other devices of the final stage.
[0020] According to a second aspect of the present invention, a design device for a solid-propellant launch vehicle's final stage to remain in orbit is provided. The final stage carries a main satellite and an experimental payload. After the main satellite detaches from the final stage, the experimental payload remains in orbit with the final stage. The device includes:
[0021] The acquisition module is used to acquire the spatial test requirements for the test load of the track-deployed test.
[0022] The installation position module is used to determine the installation position of the test load according to the space test requirements;
[0023] The operation module is used to use the final stage of the solid-propellant launch vehicle as a platform for carrying test payloads. After the final stage detaches from the main satellite, the remaining propellant of the final stage provides energy for the final stage and the test payload to operate in orbit.
[0024] According to a third aspect of the present invention, a solid-propellant launch vehicle is provided, which applies the aforementioned solid-propellant launch vehicle orbital final stage design method.
[0025] The above-described one or more technical solutions in the embodiments of this specification have at least the following technical effects:
[0026] This specification provides a design method and apparatus for a solid-propellant launch vehicle's final stage designed for orbital deployment. The method involves obtaining the space test requirements of the deployed test payload; determining the payload's installation location based on these requirements; and using the final stage of the solid-propellant launch vehicle as the payload's platform. After the final stage detaches from the main satellite, its remaining propellant provides energy for both the final stage and the test payload during orbital deployment. This allows for the deployment of small satellites for space experiments even after the main satellite separates from the final stage, providing more space test opportunities, significantly reducing the testing cost of small satellites, and improving the utilization rate of the launch vehicle's final stage.
[0027] The above description is merely an overview of the technical solution of the present invention. In order to better understand the technical means of the present invention and to implement it in accordance with the contents of the specification, and in order to make the above and other objects, features and advantages of the present invention more apparent and understandable, specific embodiments of the present invention are described below. Attached Figure Description
[0028] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Furthermore, the same reference figures denote the same parts throughout the drawings.
[0029] In the attached diagram:
[0030] Figure 1 A flowchart of a solid-propellant launch vehicle orbital final stage design method according to an embodiment of the present invention is shown.
[0031] Figure 2 A block diagram of a solid rocket launch vehicle orbital-delayed final stage design device is shown in an embodiment of the present invention. Detailed Implementation
[0032] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.
[0033] Therefore, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the invention without inventive effort are within the scope of protection of the invention.
[0034] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.
[0035] In the description of this invention, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.
[0036] Combination Figure 1 As shown, the design method for the orbital-deployed final stage of this solid-propellant launch vehicle includes steps 101 to 103:
[0037] Step 101: Obtain the spatial test requirements for the test load of the track-deposited test;
[0038] It should be noted that the test payload refers to a small satellite that needs to be launched into space by a launch vehicle for space experiments. Unlike the main satellite, when the main satellite separates from the final stage, the test payload remains on the final stage and does not detach from it. The final stage can also be called the upper stage. Because the launch vehicle has multiple stages, the final stage is the last stage to separate from the main satellite. After separating from the main satellite, the final stage will still have some propellant remaining. This remaining propellant is used to maintain the operation of the final stage and the test payload on it in orbit. During this operation, the test payload will complete the corresponding space experiments according to the space experiment requirements. The test payload is located below the main satellite at the front of the rocket. Space is reserved below the main satellite in the design, and the design is adapted to work with it. Alternatively, the test payload can be installed inside the final stage section.
[0039] Space experiment requirements can be broadly categorized into two types: space environment requirements and space exploration requirements. The main difference lies in whether or not photographic exploration of space is necessary. It's easy to understand that for space environment requirements, only a suitable microgravity environment needs to be provided for the experimental payload; the space experiment conducted by the payload only requires this microgravity environment. For example, placing a chemical substance in the space environment and observing its changes. For space exploration requirements, the experimental payload needs to photograph and explore the external environment.
[0040] Step 102: Determine the installation location of the test load according to the space test requirements;
[0041] The installation position of the test payload on the final stage is influenced by the space test requirements. If the space test requirement is a space environment requirement, then only the space environment needs to be provided for the test payload, and the test payload can be optimized in conjunction with the structure of the final stage. If the space test requirement is a space exploration requirement, then the test payload needs to be able to take pictures and explore the outside world, and therefore the test payload cannot be placed entirely inside the final stage. Based on this, determining the installation position of the test payload according to the space test requirements can include the following implementation methods:
[0042] In one optional implementation, if the space testing requirements for the test payload are space environment requirements, the test payload is installed in the propulsion control compartment of the final stage. The propulsion control compartment is part of the power system. Since the test payload itself is relatively small, it can be optimally installed in the propulsion control compartment. Of course, in specific designs, it can also be installed in other locations inside the final stage depending on the actual situation.
[0043] In another optional implementation, if the space test requirements for the test payload are space environment requirements, the adapter structure used to carry the main satellite at the end stage head is hollowed out, and the test payload is installed in the hollow part of the adapter structure. It should be noted that the main satellite can be side-mounted on the periphery of the adapter structure via a multi-satellite separation method, with the adapter structure being columnar. For example, depending on the number of main satellites, two satellites can be side-mounted in one ring, or multiple rings can be used; if the number of main satellites is small, such as only three, they can also be side-mounted in one ring at a 120-degree angle. To reduce weight, the interior of the adapter structure can be hollowed out, and the test payload is then placed inside the adapter structure. When the main satellite detaches from the end stage, the main satellite separates from the adapter structure, while the adapter structure remains on the end stage.
[0044] In another optional implementation, if the space test requirement of the test payload is space exploration, the test payload is installed between the final stage and the adapter structure. At least one main satellite is mounted on the periphery of the adapter structure. When the main satellite detaches from the final stage, the adapter structure also detaches from the final stage. It is easy to understand that since the test payload needs to perform photographic exploration, it cannot be completely placed within the final stage; it needs to be exposed. In this example, the test payload can be set up as a plate, with one end connected to the head of the final stage and the other end connected to the adapter structure. When the main satellite detaches from the final stage, both the main satellite and the adapter structure detach together, while the test payload remains on the final stage.
[0045] Step 103: Use the final stage of the solid-propellant launch vehicle as the platform for the test payload. After the final stage separates from the main satellite, the remaining propellant of the final stage will provide energy for the final stage and the test payload to operate in orbit.
[0046] The final stage functions similarly to the test payload's operating platform, possessing attitude adjustment, telemetry, and orbital maneuvering capabilities. Optionally, the final stage may include a track control engine, attitude control engine, central computer, battery, and inertial navigation system (INS). The track control engine, attitude control engine, battery, and INS are all connected to the central computer.
[0047] The orbit control engine is located at the tail of the rocket's final stage. Before the main satellite separates from the final stage, it provides power to the rocket, ensuring its entry into orbit. After separation, it provides orbit-changing power for the test payloads remaining in orbit. The attitude control engine is located near the orbit control engine, on a ring at the tail end. Its thrust direction is perpendicular to the rocket's direction of motion, used to change the rocket's attitude. A circular plate is installed inside the final stage section, on which the central computer, batteries, and inertial navigation system (INS) are mounted. The central computer contains the flight control algorithm, controlling the entire rocket's flight process; the INS provides the rocket with its current attitude angular velocity and axial acceleration, providing data for the flight control algorithm. It should be noted that the above description of the final stage mostly refers to the functional modules already present in existing final stages. Test payloads can rely on the aforementioned final stage as a platform for space experiments.
[0048] This specification provides an embodiment of a solid-propellant launch vehicle's orbital-deployed final stage design method. This method allows a small satellite to remain in orbit after the main satellite separates from the final stage, enabling space experiments. This provides more space experiment opportunities, significantly reduces the testing cost of small satellites, and improves the utilization rate of the launch vehicle's final stage.
[0049] However, existing final stages may face problems when the test load needs to remain on track for an extended period, such as insufficient power and attitude drift. Therefore, this embodiment proposes the following implementation method.
[0050] Optionally, the final stage is also equipped with a star sensor and / or a tertiary sensor connected to the central computer; the tertiary sensor and / or star sensor can be installed on the surface of the final stage column section, behind the solar panel, in order to correct attitude drift caused by the inertial navigation system exceeding its operating conditions due to prolonged operation of the final stage.
[0051] The final stage is also equipped with a ground telemetry system, which communicates bidirectionally with the ground base station.
[0052] In addition, considering the limited power provided by the battery, in order to ensure that the space test of the test load can be completed, this embodiment also installs a solar panel on the outer surface of the final stage. The solar panel converts light energy into electrical energy to power the central computer, battery, inertial navigation system, terrestrial sensor and star sensor of the final stage.
[0053] The solar panels are located in the final stage column section, and their deployment is subject to certain conditions. Before the main satellite separates from the final stage, the solar panels are not deployed; at this time, they are folded up in the final stage column section. Only after the main satellite separates from the final stage will the solar panels deploy to power the central computer, batteries, inertial navigation system, solar sensors, and star sensors in the final stage.
[0054] In this embodiment, the final stage serves as the operational platform for the test payload. Furthermore, the final stage carries the test payload into orbit. After the final stage detaches from the main satellite, it retains some propellant, which provides energy for both the final stage and the test payload to remain in orbit. However, considering that the remaining propellant is limited, and to ensure the test payload has sufficient testing time in orbit, this embodiment also installs solar panels on the outer surface of the final stage to provide the necessary energy for its long-term operation.
[0055] During this period, the test payload conducts space experiments. Because the final stage also needs to be controlled during the experiment, the final stage may optionally include a star sensor and / or a terrestrial sensor; the final stage is also equipped with a ground telemetry system, which communicates bidirectionally with the ground.
[0056] It is worth mentioning that, due to the current high frequency of launches, there is a lot of debris in low Earth orbit. To reduce this debris, this embodiment installs a space debris retrieval device on the headstock of the final stage. This device is used to retrieve debris from the orbit. After the test payload completes the space experiment, the remaining propellant in the final stage will deorbit the final stage and burn up in the atmosphere. Space debris retrieval devices are relatively mature technologies, and will not be described in detail in this embodiment.
[0057] In summary, this specification provides a design method for a solid-propellant launch vehicle's final stage for orbital deployment. The method involves obtaining the space test requirements of the orbital test payload; determining the installation location of the test payload based on these requirements; and using the final stage of the solid-propellant launch vehicle as the payload carrier platform. After the final stage detaches from the main satellite, the remaining propellant provides energy for both the final stage and the test payload during orbital deployment. This allows for the continued deployment of small satellites for space experiments after the main satellite separates from the final stage, providing more space test opportunities, significantly reducing the testing cost of small satellites, and improving the utilization rate of the launch vehicle's final stage.
[0058] Based on the same inventive concept, combined with Figure 2 As shown, this embodiment of the invention also provides a design device for a solid-propellant launch vehicle to remain in orbit for an extended period. The final stage carries a main satellite and an experimental payload. After the main satellite separates from the final stage, the experimental payload remains in orbit with the final stage. The device includes an acquisition module, an installation position module, and an operation module.
[0059] The acquisition module is used to acquire the spatial test requirements for the test load of the track-deposited test.
[0060] The installation position module is used to determine the installation position of the test load according to the space test requirements;
[0061] The operation module is used to use the final stage of the solid rocket as a platform for carrying test payloads. After the final stage detaches from the main satellite, the remaining propellant of the final stage provides energy for the final stage and the test payload to operate in orbit.
[0062] In one alternative implementation, the mounting location module is further configured to:
[0063] If the space test requirements for the test load are space environment requirements, then the test load will be installed in the propulsion control compartment of the final stage.
[0064] In one alternative implementation, the mounting location module is further configured to:
[0065] A space debris retrieval device is installed on the head-mounted structure of the final stage to retrieve debris from the orbit. After the test payload completes the space test, the remaining propellant of the final stage will deorbit the final stage and burn up in the atmosphere.
[0066] In one alternative implementation, the mounting location module is further configured to:
[0067] If the space test requirements for the test payload are space environment requirements, then the adapter structure of the final stage head used to carry the main satellite will be hollowed out, and the test payload will be installed in the hollow part of the adapter structure.
[0068] In one alternative implementation, the mounting location module is further configured to:
[0069] If the space test requirement of the test payload is space exploration, the test payload is installed between the final stage and the adapter structure. At least one main satellite is mounted on the periphery of the adapter structure. When the main satellite is detached from the final stage, the adapter structure is detached from the final stage.
[0070] In one alternative implementation, the final stage includes an orbit control engine, an attitude control engine, a central computer, a battery, and an inertial navigation system.
[0071] In one alternative embodiment, the outer surface of the final stage is further equipped with a solar panel.
[0072] In one alternative implementation, the final stage further includes a star sensor and / or a terrestrial sensor; the final stage is also equipped with a ground telemetry system that communicates bidirectionally with the ground.
[0073] In summary, this specification provides a design device for a solid-propellant launch vehicle's final stage that remains in orbit. It obtains the space test requirements of the test payload to be left in orbit; determines the installation location of the test payload based on these requirements; and uses the final stage of the solid-propellant launch vehicle as the platform for the test payload. After the final stage detaches from the main satellite, the remaining propellant provides energy for both the final stage and the test payload during their orbital operation. This allows for the continued operation of small satellites after the main satellite separates from the final stage, enabling more space test opportunities, significantly reducing the testing cost of small satellites, and improving the utilization rate of the launch vehicle's final stage.
[0074] Those skilled in the art will understand that, for the sake of convenience and brevity, the specific working process of the solid-propellant launch vehicle orbital final stage design device described above can be referred to the corresponding process in the aforementioned method, and will not be elaborated further here.
[0075] Based on the same inventive concept, this invention also provides a solid-propellant launch vehicle that applies the solid-propellant launch vehicle orbit-delayed final stage design method described in the foregoing embodiments.
[0076] In summary, this specification provides an embodiment of a solid-propellant launch vehicle. It obtains the space experiment requirements of the test payload to be kept in orbit; determines the installation location of the test payload based on the space experiment requirements; and uses the final stage of the solid-propellant launch vehicle as the platform for carrying the test payload. After the final stage separates from the main satellite, the remaining propellant of the final stage provides energy for the final stage and the test payload during their orbital operation. In this way, after the main satellite separates from the final stage, a small satellite can continue to be carried in orbit to conduct space experiments, thereby providing more space experiment opportunities, greatly reducing the testing cost of small satellites, and improving the utilization rate of the launch vehicle's final stage.
[0077] The above are merely various embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.
Claims
1. A design method for a solid-propellant launch vehicle's orbital-delayed final stage, characterized in that, The final stage carries the main satellite and experimental payloads. After the main satellite detaches from the final stage, the experimental payload remains in orbit on the final stage. The method includes: Spatial test requirements for obtaining test loads for track-delayed operations; Determine the installation location of the test load according to the space test requirements; The final stage of the solid-propellant launch vehicle is used as the platform for the test payload. After the final stage detaches from the main satellite, the remaining propellant of the final stage provides energy for the final stage and the test payload to operate in orbit. Determining the installation position of the test load according to the space test requirements includes: If the space test requirement of the test payload is a space environment requirement, then the test payload is installed in the propulsion and control module of the final stage; or, if the space test requirement of the test payload is a space environment requirement, then the adapter structure of the final stage head used to carry the main satellite is hollowed out, and the test payload is installed in the hollow part of the adapter structure. If the space test requirement of the test payload is a space exploration requirement, then the test payload is installed between the final stage and the adapter structure. At least one main satellite is mounted on the periphery of the adapter structure. When the main satellite is detached from the final stage, the adapter structure is detached from the final stage.
2. The method according to claim 1, characterized in that, The final stage is equipped with an orbit control engine, an attitude control engine, a central computer, a battery, and an inertial navigation system (INS). The orbit control engine, located at the tail of the final stage, provides the rocket with orbital insertion propulsion before the main satellite separates from the final stage; after separation, it provides orbit-changing propulsion for test payloads remaining in orbit. The attitude control engine, located on a ring at the tail end of the final stage, thrusts perpendicular to the rocket's direction of motion and is used to change the rocket's attitude. A circular plate is installed inside the final stage, on which the central computer, battery, and INS are mounted. The central computer controls the entire rocket's flight process; the INS provides the rocket with attitude angular velocity and axial acceleration, providing data for controlling the entire rocket's flight.
3. The method according to claim 1, characterized in that, The outer surface of the final stage is also equipped with a solar panel.
4. The method according to claim 3, characterized in that, The solar panels do not deploy before the main satellite separates from the final stage; after the main satellite separates from the final stage, the solar panels deploy to supply power to the final stage.
5. The method according to claim 2, characterized in that, The final stage is also equipped with a star sensor and / or a tertiary sensor connected to the central computer; the tertiary sensor and / or star sensor are both installed on the surface of the column section of the final stage to correct the attitude drift of the final stage; the final stage is also equipped with a ground telemetry system, which communicates bidirectionally with a ground base station.
6. A design device for a solid-propellant launch vehicle's orbital final stage, characterized in that, Use the solid-propellant launch vehicle orbit-delayed final stage design method according to any one of claims 1-5; The final stage carries the main satellite and experimental payloads. After the main satellite detaches from the final stage, the experimental payload remains in orbit on the final stage. The device includes: The acquisition module is used to acquire the spatial test requirements for the test load of the track-deployed test. The installation position module is used to determine the installation position of the test load according to the space test requirements; The operation module is used to use the final stage of the solid-propellant launch vehicle as a platform for carrying the test payload. After the final stage detaches from the main satellite, the remaining propellant of the final stage provides energy for the final stage and the test payload to operate in orbit.
7. A solid-propellant launch vehicle, characterized in that, Includes the solid-propellant launch vehicle orbital final stage design device as described in claim 6.