A modular electromagnetic powered backpack for satellite assisted orbit insertion and satellite orbit insertion method

Abstract

A modular electromagnetic-powered backpack for satellite-assisted orbital insertion includes a backpack body and an electric propulsion module, the backpack body includes a first connection part and a second connection part, the backpack body is connected to the electric propulsion module through the first connection part, and is connected to a satellite platform through the second connection part, the satellite platform includes a third connection part, the satellite platform and the modular electromagnetic-powered backpack for satellite-assisted orbital insertion are commonly connected to a carrier through the third connection part, wherein after the satellite platform and the modular electromagnetic-powered backpack for satellite-assisted orbital insertion are carried and launched by the carrier to a relatively low orbital altitude, the satellite platform and the modular electromagnetic-powered backpack for satellite-assisted orbital insertion are separated from the carrier, and the satellite platform is launched to the orbital altitude of a predetermined target orbit of the satellite platform under the electric propulsion of the modular electromagnetic-powered backpack for satellite-assisted orbital insertion.

Description

Technical Field

[0001] The present invention relates to the field of satellite launch, and in particular to a modular electromagnetic powered backpack used for satellite assisted orbit insertion and a satellite orbit insertion method. Background Art

[0002] Low-orbit satellite systems often adopt a batch launch method. my country's low-orbit satellites currently mainly use multi-stage rocket direct-orbit technology. For example, a carrier rocket carrying multiple satellites flies directly to the target orbit (usually above 500km) to release the satellites. This launch method has high requirements for the rocket's orbital altitude, resulting in limited weight of the satellites carried and high comprehensive satellite deployment costs for the satellite system. Summary of the invention

[0003] One purpose of the present invention is to provide a modular electromagnetic powered backpack for satellite assisted orbit insertion, which can reduce the launch cost of low-orbit satellites and improve the overall deployment efficiency.

[0004] The above-mentioned modular electromagnetic-powered backpack for satellite assisted orbital insertion includes a backpack body and an electric propulsion module, the backpack body includes a first connection part and a second connection part, the backpack body is connected to the electric propulsion module through the first connection part, and is connected to the satellite platform through the second connection part, the satellite platform includes a third connection part, the satellite platform and the modular electromagnetic-powered backpack for satellite assisted orbital insertion are commonly connected to the carrier through the third connection part; wherein, after the satellite platform and the modular electromagnetic-powered backpack for satellite assisted orbital insertion are carried and launched by the carrier to a relatively low orbital altitude, the satellite platform and the modular electromagnetic-powered backpack for satellite assisted orbital insertion are separated from the carrier, and the satellite platform is launched to the orbital altitude of the predetermined target orbit of the satellite platform under the electric propulsion of the modular electromagnetic-powered backpack for satellite assisted orbital insertion.

[0005] In one or more embodiments, the backpack body is detachably connected to the electric propulsion module via the first connecting part, the first connecting part includes a first fixing part and a first interface, the electric propulsion module includes a second fixing part and a second interface, the positioning and loading and unloading of the backpack body and the electric propulsion module are achieved through the cooperation between the first fixing part and the second fixing part, and power supply and data transmission are achieved through the cooperation between the first interface and the second interface.

[0006] In one or more embodiments, the electric propulsion module includes at least one electric thruster, and the satellite platform is launched to the orbital altitude of the predetermined target orbit under the electric propulsion of the electric thruster.

[0007] In one or more embodiments, the first fixing portion and the second fixing portion are connected by a snap-fit ​​connection to achieve positioning and quick assembly and disassembly of the backpack body and the electric propulsion module.

[0008] In one or more embodiments, the backpack body has a battery module, a first control module and a flight control module inside. The battery module is used to power the electric propulsion module, and the first control module is used to control the electric propulsion module. The flight control module is used to achieve attitude control and positioning navigation during the propulsion process of the modular electromagnetic power backpack used for satellite assisted orbit insertion; the carrier has a second control module inside, which is used to control the separation of the satellite platform and the carrier.

[0009] In one or more embodiments, the modular electromagnetic power backpack used for assisting satellite orbit insertion also includes a solar wing mechanism, which is connected to the backpack body. The solar wing mechanism is in a folded state during the process of launching the satellite platform with the carrier. After the satellite platform is separated from the carrier, the solar wing mechanism is unfolded to supply power to the electric propulsion module.

[0010] In one or more embodiments, the modular electromagnetic-powered backpack for satellite-assisted orbital insertion is detachably connected to the satellite platform via the second connecting portion, and a third control module is provided inside the satellite platform for controlling the separation of the satellite platform from the modular electromagnetic-powered backpack for satellite-assisted orbital insertion.

[0011] In one or more embodiments, the second connection portion includes an electromagnetic interface, and the modular electromagnetic power backpack applied to satellite assisted orbit insertion is magnetically connected to the satellite platform via the electromagnetic interface.

[0012] Another object of the present invention is to provide a satellite orbit insertion method that can reduce the launch cost of low-orbit satellites and improve the overall deployment efficiency.

[0013] The satellite comprises a satellite platform, on which the modular electromagnetic power backpack for satellite assisted orbital insertion is installed, and the satellite platform and the modular electromagnetic power backpack for satellite assisted orbital insertion are connected to a carrier together and can be separated from the carrier;

[0014] The satellite orbit insertion method comprises the following steps: 1) the satellite platform and the modular electromagnetic-powered backpack for satellite-assisted orbit insertion are carried by the carrier and launched to a relatively low orbital altitude; 2) the satellite platform and the modular electromagnetic-powered backpack for satellite-assisted orbit insertion are released and separated from the carrier; 3) the satellite platform is launched to the orbital altitude of the predetermined target orbit of the satellite platform under the electric propulsion of the modular electromagnetic-powered backpack for satellite-assisted orbit insertion.

[0015] In one or more embodiments, the relatively low orbital altitude is 200-300 km, and the orbital altitude of the predetermined target orbit is 500 km.

[0016] Compared with the prior art, this application has at least the following beneficial effects:

[0017] This application uses a backpack to install the electric propulsion device on the satellite platform. Each satellite platform is equipped with a modular electromagnetic power backpack for satellite assisted orbital insertion. The carrier only needs to fly to a relatively low orbital altitude to release the satellite platform. After the satellite platform and the modular electromagnetic power backpack for satellite assisted orbital insertion are separated from the carrier, the modular electromagnetic power backpack for satellite assisted orbital insertion autonomously assists the satellite to "climb" into orbit. Since the carrier only needs to fly to a relatively low orbital altitude, the carrier can carry more heavy satellites for launch, reduce satellite launch costs, and improve the comprehensive deployment efficiency of low-orbit satellite systems. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which:

[0019] Figure 1 It is a stereoscopic diagram of a modular electromagnetic powered backpack and a satellite platform for satellite assisted orbit insertion according to one embodiment, wherein the modular electromagnetic powered backpack for satellite assisted orbit insertion is in a folded state.

[0020] Figure 2 It is a stereoscopic diagram of a modular electromagnetic powered backpack and a satellite platform for satellite assisted orbit insertion according to one embodiment, wherein the modular electromagnetic powered backpack for satellite assisted orbit insertion is in an unfolded state.

[0021] Figure 3 It is a stereoscopic diagram of a modular electromagnetic powered backpack in a folded state for satellite assisted orbit insertion according to one embodiment.

[0022] Figure 4 It is a side view of a modular electromagnetic powered backpack in a folded state for satellite assisted orbit insertion according to one embodiment.

[0023] Figure 5 It is a stereoscopic diagram of a modular electromagnetic powered backpack in an unfolded state for use in satellite assisted orbit insertion according to one embodiment.

[0024] Figure 6 It is an exploded view of a modular electromagnetic powered backpack for satellite assisted orbit insertion according to one embodiment.

[0025] Figure 7 is a back view of an electric propulsion module according to one embodiment.

[0026] Figure 8 is a side view of an electric propulsion module according to one embodiment.

[0027] Fig. 9 is a perspective view of an electric propulsion module according to one embodiment.

[0028] Fig.10 is a perspective view of an electric propulsion module according to another embodiment.

[0029] Fig.11 is a perspective view of an electric propulsion module according to yet another embodiment.

[0030] Fig.12 is based on Fig. 9 A front view of a modular electromagnetic powered backpack for satellite assisted orbit insertion, composed of an electric propulsion module assembly.

[0031] Fig.13 is based on Fig.10 A front view of a modular electromagnetic powered backpack for satellite assisted orbit insertion, composed of an electric propulsion module assembly.

[0032] Fig.14 is based on Fig.11 A front view of a modular electromagnetic powered backpack for satellite assisted orbit insertion, composed of an electric propulsion module assembly.

[0033] Fig.15 is a three-dimensional view of the interior of a backpack body according to an embodiment.

[0034] Fig.16 is a three-dimensional diagram of a backpack body according to an embodiment.

[0035] Fig.17 is a back view of a backpack body according to an embodiment. DETAILED DESCRIPTION

[0036] The present invention is further described below in conjunction with specific embodiments and drawings. More details are described in the following description to facilitate a full understanding of the present invention, but the present invention can obviously be implemented in a variety of other ways different from the description. Those skilled in the art can make similar generalizations and deductions based on actual application situations without violating the connotation of the present invention. Therefore, the protection scope of the present invention should not be limited by the content of this specific embodiment. It should be noted that these and other subsequent drawings are only examples, which are not drawn according to the conditions of equal proportions, and should not be used as a limitation on the protection scope of the actual requirements of the present invention.

[0037] The common way to put low-orbit satellites into orbit is to carry the satellite on a launch vehicle, which will fly directly to the satellite's target orbit and then release the satellite into orbit. However, this method of orbital entry requires the rocket to fly to a high orbital altitude, and the total weight of satellites it can carry is limited, which increases the deployment cost of the satellite system.

[0038] In order to solve at least one of the problems existing in the aforementioned low-orbit satellite insertion methods, the present application provides a modular electromagnetic powered backpack for satellite assisted insertion, such as Figures 1 to 3 As shown, the modular electromagnetic powered backpack 1 for satellite assisted orbital insertion includes a backpack body 11 and an electric propulsion module 12, the backpack body 11 includes a first connection part 111 and a second connection part 112, the backpack body 11 is connected to the electric propulsion module 12 through the first connection part 111, and is connected to the satellite platform 2 through the second connection part 112, the satellite platform 2 includes a third connection part 21, the satellite platform 2 and the modular electromagnetic powered backpack 1 for satellite assisted orbital insertion are connected to a carrier (not shown in the figure) through the third connection part 21, wherein, after the satellite platform 2 and the modular electromagnetic powered backpack 1 for satellite assisted orbital insertion are carried and launched by the carrier to a relatively low orbital altitude, the satellite platform 2 and the modular electromagnetic powered backpack 1 for satellite assisted orbital insertion are separated from the carrier, and the satellite platform 2 is launched to the orbital altitude of the predetermined target orbit of the satellite platform 2 under the electric propulsion of the modular electromagnetic powered backpack 1 for satellite assisted orbital insertion.

[0039] In this article, the satellite platform 2 refers to the main structure of the satellite and the basic functional modules of the satellite, excluding the payload. For example, the payload can be a camera supported on the satellite platform 2, and the functional modules in the satellite platform 2 realize the control and power supply of the camera.

[0040] The present application adopts the form of a backpack to install the electric propulsion device on the satellite platform 2. Each satellite platform 2 is equipped with a modular electromagnetic power backpack 1 applied to satellite assisted orbital entry. The carrier only needs to fly to a relatively low orbital altitude to release the satellite platform 2. For example, when the predetermined target orbital altitude of the satellite is 500km, the carrier only needs to fly to an orbital altitude of 200-300km. After the satellite platform 2 and the modular electromagnetic power backpack 1 applied to satellite assisted orbital entry are separated from the carrier, the modular electromagnetic power backpack 1 applied to satellite assisted orbital entry autonomously assists the satellite to "climb" into orbit. "Climbing" into orbit means that the satellite platform 2 can climb to the predetermined target orbit under the propulsion of the modular electromagnetic power backpack 1 applied to satellite assisted orbital entry. Since the carrier only needs to fly to a relatively low orbital altitude, the carrier can carry more satellites for launch, reduce the cost of satellite launch, and improve the comprehensive deployment efficiency of the low-orbit satellite system.

[0041] Compared with the traditional chemical propulsion method that uses chemical fuel as an energy source, the electric propulsion method has the advantages of high specific impulse and high efficiency. Specific impulse is the impulse generated by a unit mass of propellant. For a space mission, the required impulse is certain. Therefore, under the condition of providing the same impulse, the mass of propellant required by the electric propulsion system is much smaller than the mass of fuel required by the chemical propulsion system. Therefore, the weight of the payload can be increased on the basis of the total weight of the carrier unchanged, so that the carrier can carry more satellites for launch and reduce the cost of satellite launch.

[0042] On the other hand, the modular electromagnetic power backpack for satellite assisted orbit insertion provided by this application can be used to achieve "drag-free control", can be applied to basic physical science exploration missions in space, and meet the requirements of "low noise, high precision, and high stability" for satellite platforms. The thrust provided by the modular electromagnetic power backpack for satellite assisted orbit insertion using electric propulsion can offset the interference forces such as solar pressure and atmospheric drag during the satellite orbit insertion process, and the thrust stability and thrust accuracy generated by electric propulsion have obvious advantages over traditional chemical propulsion.

[0043] The following combination Figures 3 to 17 A specific embodiment of the modular electromagnetic powered backpack 1 provided in the present application for satellite assisted orbit insertion is described.

[0044] Figure 3 and Figure 4 The schematic diagram of the structure of the modular electromagnetic power backpack 1 used for satellite assisted orbit insertion is shown when the electric propulsion module 12 is not turned on. At this time, the electric propulsion module 12 is stored inside the backpack body 11. Figure 5The schematic diagram of the structure of the modular electromagnetic power backpack 1 used for satellite assisted orbit insertion is shown when the electric propulsion module 12 is turned on. At this time, the backpack body 11 is in the unfolded state to expose the electric propulsion module 12, so that the satellite platform 2 can climb and enter the predetermined target orbit under the propulsion of the reaction force generated by the operation of the electric propulsion module 12.

[0045] refer to Figures 6 to 8 The first connecting portion 111 of the backpack body 11 includes a first fixing portion 113 and a first interface 114, and the electric propulsion module 12 includes a second fixing portion 121 and a second interface 122. The positioning and loading and unloading of the backpack body 11 and the electric propulsion module 12 are achieved through the cooperation between the first fixing portion 113 and the second fixing portion 121, and power supply and data transmission are achieved through the cooperation between the first interface 114 and the second interface 122.

[0046] The first connecting portion 111 of the backpack body 11 is a concave surface, and the electric propulsion module 12 has a convex surface corresponding thereto. Taking the electric propulsion module 12 as an example, the multiple second fixing portions 121 of the electric propulsion module 12 are respectively located at the corners of the convex surface, and the multiple second interfaces 122 are located at the center of the convex surface. After the backpack body 11 and the electric propulsion module 12 are simply positioned by the cooperation of the concave and convex surfaces, the electric propulsion module 12 is fixedly installed on the backpack body 11 by the cooperation of the second fixing portion 121 and the first fixing portion 113, and at the same time, the second interface 122 is docked with the first interface 114, so as to realize the functions of the backpack body 11 supplying power to the electric propulsion module 12 and controlling the electric propulsion module 12.

[0047] In the present embodiment, the backpack body 11 and the electric propulsion module 12 are designed to adopt a concave and convex surface matching form, which can quickly position and install the electric propulsion module 12 on the backpack body 11, and the first fixing part 113 and the second fixing part 121 can be connected by snap-fitting to achieve the positioning and quick loading and unloading of the backpack body 11 and the electric propulsion module 12. For example, the first fixing part 113 can be a connecting fastener, and the second fixing part 121 can be a snap-fitting part. By snap-fitting the snap-fitting part with the connecting fastener, the electric propulsion module 12 and the backpack body 11 can be installed with one click, thereby improving the assembly efficiency.

[0048] refer to Fig. 9 The electric propulsion module 12 includes at least one electric propulsion unit 123 and a tank (not shown in the figure). The tank is installed inside the electric propulsion module 12 and is used to store working fluids such as propellants. The satellite platform 2 is launched to the orbital height of the predetermined target orbit of the satellite platform 2 under the electric propulsion of the electric propulsion unit 123. In this embodiment, the electric propulsion unit 123 can be a Hall thruster. The electric propulsion module 12 with a corresponding thrust level and number of Hall thrusters can be selected according to the mission requirements. The electric propulsion module 12 is connected to the first interface 114 of the backpack body 11 through the second interface 122, and is controlled and operated by the backpack body 11.

[0049] Taking the common Hall thruster as an example, after the propellant is ionized, it forms a Hall current under the action of the magnetic field, rotates around the middle axis, and uses the Hall effect to separate electrons (negative electricity) and ions (positive electricity). The plasma is accelerated and ejected in the Hall thruster by the electric field to generate thrust. There is a hollow cathode outside the thruster that releases electrons and combines with ions (positive electricity) to make the tail flow in an electrically neutral state.

[0050] In other embodiments, an electrothermal propulsion method may be used to heat the working fluid to expand it and eject it backward to obtain thrust. Alternatively, an ion thruster may be used, in which a mesh screen with a large potential difference is provided at the end of the thruster. After passing through the mesh screen, the cations are greatly accelerated and ejected backward to obtain thrust.

[0051] The above-mentioned modular electromagnetic power backpack 1 for satellite assisted orbital insertion is modularized by designing the electric propulsion module 12 as a separate module independent of the backpack body 11, so that the electric propulsion module 12 and the backpack body 11 can be modularly separated and modularly combined. The backpack body 11 has a first interface 114 for standard power supply and data information transmission, which can be connected and plug-and-play with the second interface 122 on the electric propulsion module 12. The modular design of the modular electromagnetic power backpack 1 for satellite assisted orbital insertion is conducive to the quantitative production of the modular electromagnetic power backpack 1 for satellite assisted orbital insertion, which can further reduce the cost of satellite launch. Users can select the corresponding electric propulsion module 12 according to actual needs to form a modular electromagnetic power backpack 1 for satellite assisted orbital insertion that can meet the satellite propulsion needs.

[0052] The modular design of the electric propulsion module 12 can be reflected in many aspects. Taking the number of electric thrusters 123 as an example, different electric propulsion modules 12 have different numbers of electric thrusters 123. Figures 9 to 11 The electric propulsion module 12 with a single nozzle, a double nozzle, or a quad nozzle in one or more embodiments is shown respectively. Figure 12 to Figure 14 A modular electromagnetic powered backpack 1 for satellite assisted orbit insertion equipped with a corresponding number of electric thrusters 123 in one or more embodiments is shown. In the above multiple embodiments, each electric thruster 123 can generate a thrust of 40 mN. Figures 9 to 11 The three electric propulsion modules 12 shown correspond to electric propulsion modules 12 that can generate thrusts of 40mN, 80mN, and 160mN, respectively, so that they can be assembled with the backpack body 11 to form a modular electromagnetic power backpack 1 with different thrusts for satellite assisted orbit insertion to meet different usage requirements.

[0053] The present application aims to provide a modular electromagnetic power backpack 1 for satellite assisted orbital insertion that can achieve low-cost satellite orbital insertion. In other embodiments, the modular design of the electric propulsion module 12 can also be reflected in other aspects. For example, different electric propulsion modules 12 can have electric thrusters 123 of different thrust types to adapt to a wider range of mission thrust requirements.

[0054] refer to Fig.15 The backpack body 11 has a battery module 115, a first control module (not shown in the figure) and a flight control module 116. The battery module 115 is used to power the electric propulsion module 12, and the first control module is used to control the electric propulsion module 12. The flight control module 116 is used to achieve attitude control and positioning navigation during the propulsion process of the modular electromagnetic power backpack 1 used for satellite assisted orbit insertion. The carrier has a second control module inside, which is used to control the separation of the satellite platform 2 and the carrier.

[0055] Specifically, the battery module 115 can use a lithium battery module to power the electric propulsion module 12, and the flight control module 116 can be integrated with a GNSS navigation module, an IMU inertial navigation module, a module energy control module, and an integrated control module. The combined navigation system composed of the GNSS navigation module and the IMU inertial navigation module can make full use of the advantages of the satellite navigation system (i.e., the GNSS navigation module) and the inertial navigation system (i.e., the IMU inertial navigation module) to obtain the best navigation results, especially when the satellite navigation system cannot work properly, the inertial navigation system can continue to work to ensure the normal operation of the combined navigation system and improve the stability and reliability of the navigation system. The module energy control module is used to control the charging and discharging state of the battery module 115, and the integrated control module is used to comprehensively process the data generated by each module in the modular electromagnetic power backpack 1 used for satellite-assisted orbital insertion, and autonomously regulate the operating state of each module.

[0056] In this embodiment, the modular electromagnetic power backpack 1 used for assisting satellite orbit insertion also includes a solar wing mechanism 13, which is connected to the backpack body 11. The solar wing mechanism 13 is in a folded state during the process of the satellite platform 2 being carried and launched by the carrier. After the satellite platform 2 is separated from the carrier, the solar wing mechanism 13 is unfolded to supply power to the electric propulsion module 12.

[0057] Specifically, during the launch of the satellite platform 2 along with the carrier, the modular electromagnetic powered backpack 1 used for assisting the satellite into orbit is in Figure 3 In the folded state shown in the figure, the solar wing mechanism 13 is folded and the electric propulsion module 12 is wrapped inside the modular electromagnetic power backpack 1 for satellite assisted orbit insertion. After the satellite platform 2 is separated from the carrier, the modular electromagnetic power backpack 1 for satellite assisted orbit insertion is in Figure 5In the unfolded state shown, the solar wing mechanism 13 is unfolded and the electric propulsion module 12 is exposed. The modular electromagnetic power backpack 1 used for satellite assisted orbital entry can autonomously obtain solar energy through the solar wing mechanism 13, and has power supply and power storage functions, and then realizes the "climbing" function of the satellite platform 2 through the efficient operation of the electric propulsion module 12. In the process of the satellite platform 2 "climbing" into orbit, the solar wing mechanism 13 and the battery module 115 in the backpack body 11 can jointly power the electric propulsion module 12. For example, under good lighting conditions, only the solar wing mechanism 13 can be used to power continuous climbing and charge the battery module 115. When the satellite enters a dark area, the battery module 115 can be enabled to continue climbing. In addition, the satellite sometimes has an emergency avoidance requirement in the space environment. At this time, the battery module 115 participates in the power supply to enable the propeller to operate at full power, thereby achieving avoidance.

[0058] refer to Fig.16 and Fig.17 The modular electromagnetic power backpack 1 used for satellite assisted orbital insertion is detachably connected to the satellite platform 2 through the second connection part 112. The satellite platform 2 has a third control module inside, which is used to control the separation of the satellite platform 2 and the modular electromagnetic power backpack 1 used for satellite assisted orbital insertion. The modular electromagnetic power backpack 1 used for satellite assisted orbital insertion is connected to the satellite platform 2 in a detachable manner, so that it can be separated by itself and fly off the orbit after the satellite platform 2 is transported to the predetermined target orbit, thereby reducing the dead weight of the satellite platform 2 after entering the orbit, improving the control accuracy of the satellite platform 2, and improving the overall performance. At the same time, it can also reduce the energy consumption of the satellite platform 2 when it is in orbit and increase its in-orbit life.

[0059] The modular electromagnetic power backpack 1 used for satellite assisted orbit insertion and the satellite platform 2 can realize controllable separation of the two by means of magnetic connection. Specifically, the second connection part 112 of the modular electromagnetic power backpack 1 used for satellite assisted orbit insertion includes an electromagnetic interface, and the satellite platform 2 is provided with a corresponding electromagnetic connection part. The magnetic connection between the two is realized through the cooperation of the electromagnetic interface and the electromagnetic connection part, and the separation of the two can be realized by the control of the third control module.

[0060] The present application also provides a satellite orbit insertion method, wherein the satellite includes a satellite platform 2, on which is mounted a modular electromagnetic power backpack 1 for satellite assisted orbit insertion in one or more of the above-mentioned embodiments, and the satellite platform 2 and the modular electromagnetic power backpack 1 for satellite assisted orbit insertion are connected to a carrier and can be separated from the carrier. The satellite orbit insertion method includes the following steps:

[0061] 1) The satellite platform 2 and the modular electromagnetic powered backpack 1 used for satellite assisted orbit insertion are launched by a carrier to a relatively low orbital altitude;

[0062] 2) The satellite platform 2 and the modular electromagnetic powered backpack 1 used for satellite assisted orbit insertion are released and separated from the carrier;

[0063] 3) The satellite platform 2 is launched to the orbital height of the predetermined target orbit of the satellite platform 2 under the electric propulsion of the modular electromagnetic power backpack 1 applied to satellite assisted orbit insertion.

[0064] The traditional way of inserting a low-orbit satellite into orbit is to launch a satellite directly to the target orbit of the satellite (usually above 500km) by a carrier rocket, and then release the satellite. The orbital altitude that the carrier rocket needs to fly into is relatively high, and the total weight of the satellite it can carry is limited by the launch altitude. The satellite insertion method of the present application adopts a modular electromagnetic power backpack applied to satellite assisted orbit insertion, and the modular electromagnetic power backpack applied to satellite assisted orbit insertion is installed on the satellite platform. The carrier only needs to carry the satellite to a relatively low orbital altitude to release the satellite (for example, when the predetermined target orbital altitude of the satellite is 500km, the carrier only needs to fly to an orbital altitude of 200 to 300km), and then the modular electromagnetic power backpack applied to satellite assisted orbit insertion will propel the satellite to the predetermined target orbit to complete the orbital insertion, so that the carrier can carry more satellites for launch, reduce the cost of satellite launch, and improve the comprehensive deployment efficiency of the low-orbit satellite system.

[0065] Although the present invention is disclosed as above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and modification made to the above embodiments according to 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 defined by the claims of the present invention.

Claims

1. A modular electromagnetic powered backpack for satellite assisted orbit insertion, characterized in that: The backpack body comprises a backpack body and an electric propulsion module, wherein the backpack body comprises a first connection part and a second connection part, wherein the backpack body is connected to the electric propulsion module through the first connection part, and is connected to a satellite platform through the second connection part, wherein the satellite platform comprises a third connection part, and wherein the satellite platform and the modular electromagnetic power backpack applied to satellite auxiliary orbit insertion are connected to a carrier through the third connection part; Wherein, after the satellite platform and the modular electromagnetic powered backpack for satellite assisted orbital insertion are carried and launched by the carrier to a relatively low orbital altitude, the satellite platform and the modular electromagnetic powered backpack for satellite assisted orbital insertion are separated from the carrier, and the satellite platform is launched to the orbital altitude of a predetermined target orbit of the satellite platform under the electric propulsion of the modular electromagnetic powered backpack for satellite assisted orbital insertion; The electric propulsion module has electric thrusters of different thrust types and / or different numbers of electric thrusters; The first connecting portion includes a concave surface, the electric propulsion module has a convex surface corresponding to the concave surface, the backpack body and the electric propulsion module are positioned by the cooperation of the concave and convex surfaces, and the satellite platform is launched to the orbital height of the predetermined target orbit under the electric propulsion of the electric propulsion device; The backpack body also has a flight control module inside, and the flight control module is used to realize attitude control and positioning navigation during the propulsion process of the modular electromagnetic power backpack used for satellite assisted orbit insertion; the backpack body is detachably connected to the electric propulsion module through the first connecting part, the first connecting part includes a first fixing part and a first interface, and the electric propulsion module includes a second fixing part and a second interface, and the positioning and loading and unloading of the backpack body and the electric propulsion module are realized through the cooperation of the first fixing part and the second fixing part, and power supply and data transmission are realized through the cooperation of the first interface and the second interface; the first fixing part and the second fixing part are connected by a snap-on connection to realize the positioning and quick loading and unloading of the backpack body and the electric propulsion module.

2. The modular electromagnetic powered backpack for satellite assisted orbit insertion as claimed in claim 1, characterized in that: The backpack body has a battery module and a first control module inside, the battery module is used to power the electric propulsion module, and the first control module is used to control the electric propulsion module; The carrier has a second control module inside, which is used to control the separation of the satellite platform from the carrier.

3. The modular electromagnetic powered backpack for satellite assisted orbit insertion as claimed in claim 1, characterized in that: The modular electromagnetic powered backpack used for assisting satellite orbit insertion also includes a solar wing mechanism, which is connected to the backpack body. The solar wing mechanism is in a retracted state during the process of the satellite platform being carried and launched by the carrier. After the satellite platform is separated from the carrier, the solar wing mechanism is unfolded to supply power to the electric propulsion module.

4. The modular electromagnetic powered backpack for satellite assisted orbit insertion as claimed in claim 1, characterized in that: The modular electromagnetic powered backpack for satellite assisted orbital insertion is detachably connected to the satellite platform via the second connecting portion, and a third control module is provided inside the satellite platform for controlling the separation of the satellite platform and the modular electromagnetic powered backpack for satellite assisted orbital insertion.

5. The modular electromagnetic powered backpack for satellite assisted orbit insertion as claimed in claim 4, characterized in that: The second connection part includes an electromagnetic interface, and the modular electromagnetic power backpack used for satellite assisted orbit insertion is magnetically connected to the satellite platform through the electromagnetic interface.

6. A satellite orbit insertion method, characterized in that: The satellite comprises a satellite platform, on which is mounted a modular electromagnetic powered backpack for satellite assisted orbit insertion as claimed in any one of claims 1 to 5, wherein the satellite platform and the modular electromagnetic powered backpack for satellite assisted orbit insertion are connected to a carrier and can be separated from the carrier; The satellite orbit insertion method comprises the following steps: 1) The satellite platform and the modular electromagnetic powered backpack for satellite assisted orbit insertion are carried and launched by the carrier to a relatively low orbital altitude; 2) The satellite platform and the modular electromagnetic powered backpack for satellite assisted orbit insertion are released and separated from the carrier; 3) The satellite platform is launched to the orbital altitude of the predetermined target orbit of the satellite platform under the electric propulsion of the modular electromagnetic powered backpack for satellite assisted orbit insertion.

7. The satellite orbit insertion method according to claim 6, characterized in that: The relatively low orbital altitude is 200-300 km, and the orbital altitude of the predetermined target orbit is 500 km.

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