A reusable satellite with variable configuration on orbit

Abstract

The present invention discloses a reusable satellite with a variable configuration on-orbit, comprising: a heat protection module, a platform cabin and a parachute cabin module; the two ends of the platform cabin are respectively connected to the heat protection module and the parachute cabin module. In the above-mentioned reusable satellite with a variable configuration on-orbit, the reusable satellite has a variable configuration during launch, on-orbit and recovery. The typical recovery process of a satellite is as follows: the solar panels of the deployable solar wing are folded; the flexible heat protection airbag is inflated and unfolded, and the platform cabin is covered in the flexible heat protection airbag; the satellite enters the atmosphere to decelerate after attitude adjustment and braking; when the satellite reaches a certain height, the controllable parachute pops up and unfolds, and the rigid heat protection outsole is thrown away at the same time; after the controllable parachute is unfolded, the satellite is further decelerated and homing control is performed. At this time, the landing buffer airbag is inflated to make the satellite reach the designated landing site, realizing the safe and controllable landing recovery of the satellite. The present invention can realize the safe recovery and rapid reuse of the whole system at a low cost, and improve the application benefits of spacecraft reuse.

Description

Technical Field

[0001] The present invention belongs to the technical field of reusable spacecraft, and in particular relates to a reusable satellite with a variable configuration on orbit. Background Art

[0002] Reusable spacecraft refers to spacecraft that can pass through the atmosphere, freely travel between the earth's surface and space, and can be reused after completing various space missions. The reuse of spacecraft is an effective way to reduce mission costs and improve system application benefits, and is an important development direction in the future aerospace field. According to the degree of reusability, reusable aircraft can be divided into: 1) system-level reuse; 2) module reuse.

[0003] 1) System-level reuse: The spacecraft is recyclable and reusable as a whole, with a high system reuse ratio. Spacecraft usually adopts a lifting body shape, has a wing structure, and a lift-to-drag ratio greater than 1. The space shuttle is the most typical. Taking the space shuttle as an example, the five advantages of the space shuttle originally envisioned are: First, the launch is cheap, and the expected cost of each launch is only 30 million US dollars. Second, it is powerful and can carry 4 to 7 people and 20 to 30 tons of cargo each time. Third, it is safer and can glide accurately to the predetermined runway. Fourth, it is very comfortable. During the entire process from takeoff to returning to the ground, the space shuttle has a small acceleration and deceleration overload. Fifth, the interval is very short. It was originally planned to launch once every 1-2 weeks. However, practice has shown that the space shuttle has serious inherent deficiencies: due to the complexity of the system, a large amount of maintenance work is required after returning to the ground. The cost of each launch is as high as 400 million to 500 million US dollars. The time interval between each launch of each space shuttle is also very long. In particular, due to its large size and complex shape, the space shuttle orbiter can only be connected in parallel with the external tank during launch. The orbiter is easily hit by the insulation material falling from the external tank, which poses a great safety hazard. Therefore, all space shuttles were retired immediately.

[0004] 2) Reusable cabin: Only the recovery cabin is reused, and other cabins are not reused. They are usually blunt-headed, such as NASA's multi-purpose manned spacecraft MPCV, SpaceX's second-generation Dragon V2, Boeing's CST-100, and Russia's new manned space transportation system PPTS. This solution has a good technical foundation, simple system configuration, and high safety. It has become the main research direction for subsequent reusable spacecraft, but there is also a relatively low reuse rate due to the reuse of only the recovery cabin. At the same time, it is limited by the aerodynamic shape of the return cabin, and the recoverable payload is limited. There is a contradiction between the need for system openness for on-orbit missions and the thermal protection of the return process system. In addition, compared with the horizontal landing method of the space shuttle, the landing accuracy is relatively low, and the ground search and recovery efficiency is insufficient. Summary of the invention

[0005] The technology of the present invention solves the problem: overcome the shortcomings of the prior art, provide an on-orbit variable configuration reusable satellite, can achieve low-cost full system safe recovery and rapid reuse, and improve the reuse application benefits of spacecraft.

[0006] In order to solve the above technical problems, the present invention discloses an on-orbit reusable satellite with variable configuration, comprising: a thermal protection module, a platform cabin and a parachute cabin module; wherein both ends of the platform cabin are respectively connected to the thermal protection module and the parachute cabin module.

[0007] In the above-mentioned on-orbit variable-configuration reusable satellite, the thermal protection module includes: a rigid thermal protection outsole, a flexible thermal protection airbag and a landing cushion airbag; wherein, the flexible thermal protection airbag and the landing cushion airbag are folded into the rigid thermal protection outsole, and the flexible thermal protection airbag is located outside the landing cushion airbag.

[0008] In the above-mentioned on-orbit variable-configuration reusable satellite, the platform cabin includes: a payload, a platform service system and retractable solar wings; wherein the retractable solar wings are installed on the outside of the platform service system, and the payload is installed inside the platform service system.

[0009] In the above-mentioned on-orbit variable-configuration reusable satellite, the parachute cabin module includes: a controllable wing parachute, a propulsion system tank and a satellite-rocket docking device; wherein, the satellite-rocket docking device is provided with a propulsion system tank on one side close to the platform cabin, and a controllable wing parachute on the other side.

[0010] In the above-mentioned reusable satellite with variable configuration on-orbit, the reusable satellite can be configured differently during the launch, on-orbit and recovery processes.

[0011] In the above-mentioned reusable satellite with variable configuration on orbit, at the time of launch, there are:

[0012] The solar sail panels with retractable solar wings are in a retracted state;

[0013] The flexible heat-resistant airbag is in a compressed, uninflated, and unexpanded state;

[0014] The heat protection module is facing upward as a whole;

[0015] The satellite-rocket docking device connects the satellite and the carrier.

[0016] In the above-mentioned reusable satellite with variable configuration on orbit, after the satellite enters orbit, there are:

[0017] The satellite-rocket docking device works to separate the satellite from the carrier;

[0018] The solar panels with retractable solar wings are unfolded in orbit to establish an in-orbit flight state.

[0019] In the above-mentioned reusable satellite with variable configuration in orbit, before the satellite re-enters, the solar panels with retractable solar wings are folded, and the flexible heat-resistant airbags are inflated and deployed.

[0020] In the above-mentioned on-orbit variable-configuration reusable satellite, during the recovery process: a controllable parachute is opened.

[0021] In the above-mentioned reusable satellite with variable configuration on orbit, the typical recovery process of the satellite is as follows:

[0022] The solar sail panels that can be deployed and retracted are folded;

[0023] The flexible heat-proof airbag is inflated and expanded, covering the platform cabin in the flexible heat-proof airbag;

[0024] The satellite adjusts its attitude and brakes before entering the atmosphere to slow down;

[0025] When the satellite reaches a certain altitude, the controllable parafoil pops up and unfolds, and the rigid heat-resistant outsole is thrown away at the same time;

[0026] After the controllable parafoil is deployed, the satellite is further decelerated and homing control is performed. At this time, the landing cushion airbag is inflated to enable the satellite to reach the designated landing site, achieving safe and controllable landing and recovery of the satellite.

[0027] The present invention has the following advantages:

[0028] (1) The present invention discloses a reusable satellite with a variable configuration on-orbit. The satellite adopts a combination of rigid heat protection and flexible heat protection. By changing the configuration on-orbit, the satellite can be recovered and reused. At the same time, the satellite can effectively take into account the mission requirements of different stages such as launch, on-orbit, and re-entry, and support the reuse of the entire spacecraft.

[0029] (2) The present invention discloses an on-orbit reusable satellite with a variable configuration. The satellite adopts a parachute recovery method to realize a change from an uncontrollable landing point to a controllable landing point during the landing process. The landing point accuracy is improved from tens of kilometers to within 200 meters, ensuring that the entire satellite lands at a fixed point on a landing field with a buffering capacity, which is beneficial to improving the satellite recovery conditions and improving the recovery efficiency.

[0030] (3) The present invention discloses an on-orbit reusable satellite with a variable configuration. The low-impact landing cushion airbag design is adopted to greatly reduce the landing impact. Compared with the existing recoverable satellites, the landing impact is reduced by more than 90%, ensuring the lossless recovery of the entire satellite. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 Schematic diagram of a reusable satellite module with a variable configuration on-orbit according to an embodiment of the present invention;

[0032] Figure 2 1 is a schematic diagram of an explosion of a reusable satellite with a variable configuration on orbit according to an embodiment of the present invention;

[0033] Figure 3 This is a schematic diagram of a satellite launch state in an embodiment of the present invention;

[0034] Figure 4 This is a schematic diagram of a satellite in orbit flight state according to an embodiment of the present invention;

[0035] Figure 5 This is a schematic diagram of a satellite re-entry state in an embodiment of the present invention;

[0036] Figure 6 This is a schematic diagram of a satellite parachute opening and recovery state in an embodiment of the present invention;

[0037] Figure 7 It is a schematic diagram of a typical recycling process in an embodiment of the present invention. DETAILED DESCRIPTION

[0038] In order to make the objectives, technical solutions and advantages of the present invention more clear, the embodiments disclosed in the present invention will be further described in detail below with reference to the accompanying drawings.

[0039] In view of the problems of full-system reuse of winged lifting bodies represented by the space shuttle, such as complex system, high development and launch costs, insufficient system safety, and low reuse ratio and relatively large landing point dispersion in cabin recovery and reuse, the present invention proposes a reusable satellite platform based on an on-orbit variable configuration design, which can achieve full-system safe recovery and rapid reuse at low cost, thereby improving the application benefits of spacecraft reuse.

[0040] like Figure 1 In this embodiment, the on-orbit reusable satellite with a variable configuration includes: a heat protection module 1, a platform cabin 2 and a parachute cabin module 3. The two ends of the platform cabin 2 are connected to the heat protection module 1 and the parachute cabin module 3 respectively.

[0041] In this embodiment, if Figure 2 As shown, the heat protection module 1 may specifically include: a rigid heat protection outsole 101, a flexible heat protection airbag 102 and a landing cushion airbag 103. The flexible heat protection airbag 102 and the landing cushion airbag 103 are folded in the rigid heat protection outsole 101, and the flexible heat protection airbag 102 is located outside the landing cushion airbag 103.

[0042] In this embodiment, if Figure 2 As shown, the platform cabin 2 may specifically include: a payload 201, a platform service system 202, and a retractable solar wing 203. Among them, the retractable solar wing 204 is installed outside the platform service system 202, and the payload 201 is installed inside the platform service system 202.

[0043] In this embodiment, if Figure 2 As shown, the parachute module 3 may specifically include: a controllable parafoil 301, a propulsion system tank 302 and a satellite-rocket docking device 303. The satellite-rocket docking device 303 is provided with a propulsion system tank 302 on one side close to the platform cabin 2, and a controllable parafoil 301 on the other side.

[0044] In this embodiment, the reusable satellite can be configured differently during launch, in-orbit and recovery.

[0045] like Figure 3 During launch, the solar panels of the deployable solar wing 203 are in a folded state; the flexible heat-resistant airbag 102 is in a compressed, uninflated, and undeployed state; the heat-resistant module 1 is facing upward as a whole; and the satellite-rocket docking device 303 connects the satellite to the carrier.

[0046] like Figure 4 After the satellite enters orbit, the satellite-rocket docking device 303 works to separate the satellite from the carrier; the solar panels of the retractable solar wings 203 are unfolded in orbit to establish an in-orbit flight state.

[0047] like Figure 5 Before the satellite re-enters, the solar panels of the deployable solar wing 203 are folded, and the flexible heat-proof airbag 102 is inflated and deployed.

[0048] like Figure 6 During the recovery process, the controllable parafoil 301 is opened.

[0049] It can be seen that Figure 7 The typical recovery process of a satellite is as follows: the solar panels of the retractable solar wing 203 are folded; the flexible heat-proof airbag 102 is inflated and expanded, and the platform cabin 2 is covered in the flexible heat-proof airbag 102; the satellite adjusts its attitude and brakes to enter the atmosphere to decelerate; when the satellite reaches a certain height, the controllable parafoil 301 pops out and unfolds, and the rigid heat-proof bottom 101 is thrown away at the same time; after the controllable parafoil 301 is unfolded, the satellite is further decelerated and homing control is performed. At this time, the landing buffer airbag 103 is inflated to make the satellite reach the designated landing site, realizing the safe and controllable landing recovery of the satellite.

[0050] In summary, in response to the need for the reuse of the entire satellite, the present invention adopts a combination of rigid heat protection and flexible heat protection, and realizes the recycling and reuse of the entire satellite by configuring functional modules such as a rigid heat protection outsole, a shapeable flexible heat protection airbag, and a controllable wing parachute. Among them, the heat protection outsole can adopt a mature rigid heat protection solution, and further carry out a lightweight design based on the existing technology. The side wall adopts a flexible heat protection system, which is in a folded and retracted state during launch and in orbit, and is expanded by inflation before returning, so as to achieve effective protection of complex configuration spacecraft and ensure that the entire satellite can withstand the high heat flow during the re-entry process. At the same time, a reusable flexible solar wing is adopted. Through the expansion and folding of the solar wing, it can effectively take into account the mission requirements of different stages such as launch, in orbit, and re-entry. To further improve the recovery conditions, the wing parachute bird landing precise recovery method is adopted to effectively control the recovery landing point and improve the landing point accuracy. Through the above method, the safe recovery and rapid reuse of the whole system can be achieved at a low cost.

[0051] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

[0052] The contents not described in detail in the specification of the present invention belong to the common knowledge of professionals in the field.

Claims

1. A reusable satellite with a variable configuration on orbit, characterized in that: include: A heat protection module (1), a platform cabin (2) and a parachute cabin module (3); wherein two ends of the platform cabin (2) are respectively connected to the heat protection module (1) and the parachute cabin module (3); The heat protection module (1) comprises: a rigid heat protection outsole (101), a flexible heat protection airbag (102) and a landing cushioning airbag (103); wherein the flexible heat protection airbag (102) and the landing cushioning airbag (103) are folded into the rigid heat protection outsole (101), and the flexible heat protection airbag (102) is located outside the landing cushioning airbag (103); A platform cabin (2) comprises: a payload (201), a platform service system (202) and a retractable solar wing (203); wherein the retractable solar wing (203) is installed outside the platform service system (202), and the payload (201) is installed inside the platform service system (202); The parachute module (3) comprises: a controllable parafoil (301), a propulsion system tank (302) and a satellite-rocket docking device (303); wherein the satellite-rocket docking device (303) is provided with the propulsion system tank (302) on one side close to the platform cabin (2), and the controllable parafoil (301) on the other side; The reusable satellite can be configured in a variable manner during launch, in orbit, and during recovery; At launch, there are: The solar sail panel with the deployable solar wing (203) is in a folded state; The flexible heat-protection airbag (102) is in a compressed, uninflated, and unexpanded state; The heat protection module (1) is facing upward as a whole; The satellite-rocket docking device (303) connects the satellite with the carrier; After the satellite enters orbit, there are: The satellite-rocket docking device (303) works to separate the satellite from the carrier; The solar sail panel with a retractable solar wing (203) is unfolded on-orbit to establish an on-orbit flight state; Before the satellite re-enters, the solar sail panels of the deployable solar wing (203) are folded, and the flexible heat-resistant airbag (102) is inflated and deployed; During the recovery process, there are: the controllable parafoil (301) is opened; The typical satellite recovery process is as follows: The solar sail panel of the deployable solar wing (203) is folded; The flexible heat-proof airbag (102) is inflated and expanded, and the platform cabin (2) is covered in the flexible heat-proof airbag (102); The satellite adjusts its attitude and brakes before entering the atmosphere to slow down; When the satellite reaches a certain altitude, the controllable parafoil (301) pops out and unfolds, and the rigid heat-proof bottom (101) is thrown away at the same time; After the controllable parafoil (301) is deployed, the satellite is further decelerated and homing control is performed. At this time, the landing cushion airbag (103) is inflated to enable the satellite to reach the designated landing site, thereby achieving safe and controllable landing and recovery of the satellite.

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