A reentry spacecraft safety landing system
By designing a safe landing system for spacecraft re-entering the atmosphere, and utilizing onboard system software, landing intelligence system, and self-rescue system, the problem of safe spacecraft recovery was solved, achieving efficient and safe spacecraft recovery, reducing costs, and ensuring the safety of spacecraft and personnel.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- INNOVATION ACAD FOR MICROSATELLITES OF CAS
- Filing Date
- 2026-03-17
- Publication Date
- 2026-06-05
AI Technical Summary
How to achieve safe and efficient recovery of spacecraft while reducing costs, and solve the problem of safely returning spacecraft to Earth and recovering them after completing space missions.
Design a safe landing system for spacecraft re-entering the atmosphere, including spacecraft onboard system software, landing intelligent system, global navigation satellite system, ground emergency command and control center and physical self-rescue system. The system will activate an emergency distress mode when the flight propulsion system is found to have no power output, and use self-rescue systems such as damping parachutes and inflatable boats to ensure the safe landing of the spacecraft.
It enables efficient rescue and safe landing of spacecraft when there is no power output, reduces human and financial losses, ensures the integrity of the spacecraft's interior and the safety of personnel, and provides emergency rescue support from an independent global navigation satellite system.
Smart Images
Figure CN122144193A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of spacecraft technology, and in particular to a safe landing system for spacecraft re-entering the atmosphere. Background Technology
[0002] As humanity's exploration and utilization of space deepens, the demand for sending satellites, manned spacecraft, and other payloads into space is growing. However, launching spacecraft to send satellites, humans, or other payloads into space is extremely costly, primarily due to the complexity of launch vehicle and spacecraft manufacturing technologies, long development cycles, and low reusability rates. To reduce the cost of accessing space, reusable spacecraft technology has become an important development direction in the aerospace field. Within reusable technology, the safe recovery of spacecraft is a crucial prerequisite and a core challenge for achieving reuse. Therefore, ensuring the safe return and recovery of spacecraft after completing a space mission has become a pressing technical problem for those skilled in the art. Summary of the Invention
[0003] The objective of this invention is to provide a safe landing system for spacecraft re-entering the atmosphere, which enables the safe and efficient recovery of spacecraft and reduces losses in human and financial resources.
[0004] This invention provides a safe landing system for a spacecraft re-entering the atmosphere, comprising: The spacecraft's onboard system software is configured to detect whether the spacecraft's flight propulsion system has power output and to continuously send a first signal to the landing intelligent system when no power output is detected. A landing intelligent system, which is connected in communication with the spacecraft's onboard system software, is configured to perform the following actions: receive a first signal and time it; enter an emergency distress mode when the duration of no power output reaches a first duration; send distress information and spacecraft positioning information; and activate a physical self-rescue system when the duration of no power output reaches a second duration, where the second duration is longer than the first duration; and The ground emergency command and control center is configured to perform the following actions: upon receiving a distress signal and the spacecraft's location information, activate the unmanned aerial vehicle (UAV) system to locate the spacecraft based on the location information.
[0005] Furthermore, it also includes the Global Navigation Satellite System, which communicates with the landing intelligence system and the ground emergency command and control system.
[0006] Furthermore, the global navigation satellite system comprises four groups of geostationary orbit satellites with an inclination of 55°. Each group consists of four satellites, and the “8”-shaped nodes of the four groups of satellites are evenly distributed along the equator at 90° intervals. The satellite orbital altitude is 36,000 km.
[0007] Furthermore, the global navigation satellite system may also be the GPS satellite system, the BeiDou satellite system, or the Galileo satellite system.
[0008] Furthermore, the landing intelligent system includes a lower-level machine and a BeiDou short message transceiver terminal connected via a bus.
[0009] Furthermore, the lower-level computer of the landing intelligent system is used to collect the first signal sent by the spacecraft's onboard system software and time it, and then control the Beidou short message transceiver terminal and the physical self-rescue system according to the duration of no power output.
[0010] Furthermore, in emergency distress mode, the landing intelligent system sends a message containing distress information and spacecraft positioning information to the global navigation satellite system, which then forwards it to the ground emergency command and control center closest to the spacecraft.
[0011] Furthermore, the physical self-rescue system includes: An air resistance system includes: a damping parachute, which is placed in a parachute storage compartment when not deployed; a parachute bursting action actuator configured to deploy the damping parachute; and an attitude adjustment mechanism configured to adjust the parachute lines of the damping parachute according to real-time wind direction and predetermined landing point coordinates to control the drift direction. A ground-launching buffer system is configured to eject an inflatable boat to the ground when the spacecraft's altitude above the ground is less than or equal to an altitude threshold; the ground-launching buffer system includes: The inflatable boat, which is placed in the boat's storage compartment in a folded state; The ejection mechanism is configured to eject the inflatable boat onto the ground. An altitude sensor, configured to monitor the spacecraft's altitude above the ground in real time; and The central controller is configured to receive data from the altitude sensor and, when the altitude is detected to reach a preset trigger threshold, control the ejection mechanism to eject the inflatable boat onto the ground.
[0012] Furthermore, when the period of no power output reaches the second duration, the landing intelligent system activates the air resistance system and the ground-penetrating buffer system, including: The umbrella pop-out mechanism deploys the damping umbrella, and the attitude adjustment mechanism adjusts the umbrella lines according to the real-time wind direction and the coordinates of the predetermined landing point to control the drift direction. When the altitude sensor of the ground buffer system detects that the spacecraft's altitude has reached the trigger threshold, the central controller controls the ejection mechanism to eject the inflatable boat from the ship's storage compartment.
[0013] The present invention has at least the following beneficial effects: The spacecraft safe landing system of the present invention utilizes a landing intelligent system to support efficient rescue operations. When the flight propulsion system has no power output for a first duration, it enters an emergency distress mode, sends distress information and spacecraft positioning information to the ground emergency command and control center, and activates a physical self-rescue system when the no power output duration reaches a second duration. The spacecraft safe landing system of this invention integrates the spacecraft onboard system software, landing intelligent system, physical self-rescue system, ground emergency command and control center, and global navigation satellite system to enable the spacecraft to land safely. Damping parachutes, inflatable boats, and other components protect the integrity of most of the spacecraft's cabins, ensuring the safety of the spacecraft's internal life support system, important data media, and the lives of the spacecraft's personnel, minimizing human and financial losses. This invention employs an independent global navigation satellite system to provide support for emergency rescue; When the period of no power output reaches the first duration, a distress signal and the spacecraft's location information are sent to the ground emergency command and control center. After that, the ground emergency command and control center autonomously activates the UAV system to search for the spacecraft and provide information support for the rescue operation. Attached Figure Description
[0014] To further illustrate the above and other advantages and features of the various embodiments of the present invention, a more specific description of the embodiments of the invention will be presented with reference to the accompanying drawings. It is to be understood that these drawings depict only typical embodiments of the invention and are therefore not intended to limit its scope. In the drawings, identical or corresponding parts will be indicated by identical or similar reference numerals for clarity.
[0015] Figure 1 A schematic diagram of a spacecraft safe landing system according to an embodiment of the present invention is shown. Detailed Implementation
[0016] It should be noted that the components in the accompanying drawings may be shown exaggerated for illustrative purposes and may not be to scale.
[0017] In this invention, the various embodiments are merely intended to illustrate the solutions of the invention and should not be construed as limiting.
[0018] In this invention, unless otherwise specified, the quantifiers “a” and “one” do not exclude scenarios involving multiple elements.
[0019] It should also be noted that, in the embodiments of the present invention, only a portion of the parts or components may be shown for clarity and simplicity. However, those skilled in the art will understand that, under the teachings of the present invention, the required parts or components can be added as needed for specific scenarios.
[0020] It should also be noted that within the scope of this invention, the terms "same", "equal", and "equal to" do not mean that the two values are absolutely equal, but allow for a certain reasonable error. In other words, the terms also cover "substantially the same", "substantially equal", and "substantially equal to".
[0021] It should also be noted that in the description of this invention, the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not explicitly or implicitly suggest that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.
[0022] Furthermore, the embodiments of the present invention describe the process steps in a specific order. However, this is only for the convenience of distinguishing each step, and is not a limitation on the order of each step. In different embodiments of the present invention, the order of each step can be adjusted according to the process.
[0023] Figure 1 A schematic diagram of a safe landing system for a spacecraft re-entering the atmosphere is shown according to an embodiment of the present invention.
[0024] like Figure 1 As shown, a safe landing system for a spacecraft re-entering the atmosphere includes: spacecraft onboard system software 100, landing intelligent system 200, physical self-rescue system 300, global navigation satellite system (GNSS) 600, ground emergency command center 700, and unmanned aerial vehicle system 800.
[0025] The spacecraft onboard system software 100 is configured to detect whether the spacecraft's flight propulsion system has power output, and to continuously send a first signal to the landing intelligent system when no power output is detected.
[0026] The landing intelligent system 200 is communicatively connected to the spacecraft onboard system software 100 and is configured to perform the following actions: receive a first signal and start timing; enter emergency distress mode when the duration of no power output reaches a first duration; send distress information and spacecraft positioning information; and activate the physical self-rescue system 300 when the duration of no power output reaches a second duration.
[0027] The first duration could be, for example, 5 seconds, and the second duration could be, for example, 10 seconds.
[0028] In one embodiment, the landing intelligent system 200 includes a lower-level computer and a BeiDou short message transceiver terminal connected via a bus. The lower-level computer is used to acquire the first signal sent by the spacecraft's onboard system software and time it, and then control the BeiDou short message transceiver terminal and the physical self-rescue system based on the duration of no power output.
[0029] In one embodiment, in emergency distress mode, the landing intelligent system 200 sends a message containing distress information and spacecraft positioning information to the global navigation satellite system 600, which is then forwarded by the global navigation satellite system 600 to the ground emergency command and control center 700 closest to the spacecraft.
[0030] In one embodiment, the landing intelligence system 200 is powered by a UPS (Uninterruptible Power Supply).
[0031] The physical self-rescue system 300 includes an air resistance system 400 and a ground buffer system 500, both of which are communicatively connected to the landing intelligence system 200.
[0032] The ground emergency command and control center 700 is configured to perform the following actions: upon receiving a distress signal and the spacecraft's location information, activate the unmanned aerial vehicle (UAV) system to locate the spacecraft based on the location information.
[0033] The Unmanned Aerial Vehicle System 800 comprises multiple drones used to search for spacecraft and transmit real-time data back to the ground-based emergency command and control center for further support and decision-making.
[0034] The Global Navigation Satellite System 600 communicates with the Landing Intelligence System 200 and the Ground Emergency Command and Control Center 700.
[0035] In one embodiment, the Global Navigation Satellite System 600 includes four groups of geostationary orbit satellites with an inclination of 55°. Each group consists of four satellites, and the “8”-shaped nodes of the four groups of satellites are evenly distributed along the equator at 90° intervals. The satellite orbital altitude is 36,000 km.
[0036] The four groups of satellites are evenly distributed at 45° intervals along the equator at the figure-eight nodes, enabling the global navigation satellite system to provide near real-time coverage of global ground targets or near-Earth space targets, which is beneficial for carrying out spacecraft rescue missions that re-enter the atmosphere.
[0037] In another embodiment, the global navigation satellite system 600 is a GPS satellite system, a BeiDou satellite system, or a Galileo satellite system.
[0038] In one embodiment, the air resistance system 400 includes: a damping umbrella, which is placed in a umbrella storage compartment when not deployed; an umbrella pop-out action actuator configured to deploy the damping umbrella; and an attitude adjustment mechanism configured to adjust the lines of the damping umbrella according to real-time wind direction and predetermined landing point coordinates to control the drift direction.
[0039] The 400 air resistance system can slow down spacecraft weighing 5,000 kg to 10,000 kg for a safe landing.
[0040] In one embodiment, the ground buffer system 500 is configured to eject an inflatable boat to the ground when the spacecraft's altitude above the ground is less than or equal to an altitude threshold.
[0041] The ground-cushioning system 500 includes: an inflatable boat, which is placed in a boat storage compartment in a folded state; an ejection mechanism configured to eject the inflatable boat to the ground; an altitude sensor configured to monitor the spacecraft's altitude above the ground in real time; and a central controller configured to receive data from the altitude sensor and, when the detected altitude reaches a preset trigger threshold, control the ejection mechanism to eject the inflatable boat to the ground.
[0042] This inflatable boat can support spacecraft weighing 5,000 kg to 10,000 kg on the sea surface and keep them afloat.
[0043] In one embodiment, when the period of no power output reaches a second duration, the landing intelligent system 200 activates the air resistance system and the ground buffer system, including: The umbrella pop-out mechanism deploys the damping umbrella, and the attitude adjustment mechanism adjusts the umbrella lines according to the real-time wind direction and the coordinates of the predetermined landing point to control the drift direction. When the altitude sensor of the ground buffer system detects that the spacecraft's altitude has reached the trigger threshold, the central controller controls the ejection mechanism to eject the inflatable boat from the ship's storage compartment.
[0044] While some embodiments of the present invention have been described in this application, those skilled in the art will understand that these embodiments are merely illustrative. Numerous variations, alternatives, and improvements will arise in those skilled in the art under the teachings of this invention without departing from its scope. The appended claims are intended to define the scope of the invention and thereby cover methods and structures within the scope of the claims themselves and their equivalents.
Claims
1. A safe landing system for a spacecraft re-entering the atmosphere, characterized in that, include: The spacecraft's onboard system software is configured to detect whether the spacecraft's flight propulsion system has power output and to continuously send a first signal to the landing intelligent system when no power output is detected. A landing intelligent system, which is connected in communication with the spacecraft's onboard system software, is configured to perform the following actions: receive a first signal and time it; enter an emergency distress mode when the duration of no power output reaches a first duration; send distress information and spacecraft positioning information; and activate a physical self-rescue system when the duration of no power output reaches a second duration, where the second duration is longer than the first duration; and The ground emergency command and control center is configured to perform the following actions: upon receiving a distress signal and the spacecraft's location information, activate the unmanned aerial vehicle (UAV) system to locate the spacecraft based on the location information.
2. The safe landing system for spacecraft re-entering the atmosphere according to claim 1, characterized in that, It also includes the Global Navigation Satellite System, which communicates with the landing intelligence system and the ground emergency command and control system.
3. The safe landing system for spacecraft re-entering the atmosphere according to claim 2, characterized in that, The global navigation satellite system consists of four groups of geostationary orbit satellites with an inclination of 55°. Each group consists of four satellites, and the "8"-shaped nodes of the four groups are evenly distributed along the equator at 90° intervals. The satellite orbital altitude is 36,000 km.
4. The safe landing system for spacecraft re-entering the atmosphere according to claim 2, characterized in that, The global navigation satellite system mentioned is either the GPS satellite system, the BeiDou satellite system, or the Galileo satellite system.
5. The safe landing system for spacecraft re-entering the atmosphere according to claim 2, characterized in that, The landing intelligent system includes a lower-level computer and a Beidou short message transceiver terminal connected via a bus.
6. The safe landing system for spacecraft re-entering the atmosphere according to claim 5, characterized in that, The lower-level computer of the landing intelligent system is used to collect the first signal sent by the spacecraft's onboard system software and time it, and then control the Beidou short message transceiver terminal and physical self-rescue system according to the duration of no power output.
7. The safe landing system for spacecraft re-entering the atmosphere according to claim 2, characterized in that, In emergency distress mode, the landing intelligent system sends a message containing distress information and spacecraft positioning information to the global navigation satellite system, which then forwards it to the ground emergency command and control center closest to the spacecraft.
8. The safe landing system for spacecraft re-entering the atmosphere according to claim 1, characterized in that, The physical self-rescue system includes: An air resistance system includes: a damping parachute, which is placed in a parachute storage compartment when not deployed; a parachute bursting action actuator configured to deploy the damping parachute; and an attitude adjustment mechanism configured to adjust the parachute lines of the damping parachute according to real-time wind direction and predetermined landing point coordinates to control the drift direction. A ground-launching buffer system is configured to eject an inflatable boat to the ground when the spacecraft's altitude above the ground is less than or equal to an altitude threshold; the ground-launching buffer system includes: The inflatable boat, which is placed in the boat's storage compartment in a folded state; The ejection mechanism is configured to eject the inflatable boat onto the ground. An altitude sensor, configured to monitor the spacecraft's altitude above the ground in real time; and The central controller is configured to receive data from the altitude sensor and, when the altitude is detected to reach a preset trigger threshold, control the ejection mechanism to eject the inflatable boat onto the ground.
9. The safe landing system for spacecraft re-entering the atmosphere according to claim 8, characterized in that, When the period of no power output reaches the second duration, the landing intelligent system activates the air resistance system and the ground buffer system, including: The umbrella pop-out mechanism deploys the damping umbrella, and the attitude adjustment mechanism adjusts the umbrella lines according to the real-time wind direction and the coordinates of the predetermined landing point to control the drift direction. When the altitude sensor of the ground buffer system detects that the spacecraft's altitude has reached the trigger threshold, the central controller controls the ejection mechanism to eject the inflatable boat from the ship's storage compartment.