Spacecraft load power control method and spacecraft

Abstract

The invention discloses a spacecraft load power control method and a spacecraft. The spacecraft load power control method comprises the following steps: acquiring a sampling voltage of a state sampling assembly; determining the number of relays conducted in the load switch module according to the sampling voltage of the state sampling assembly; calculating the bearing power of the load switch module according to the number of the relays conducted in the load switch module and the bearing power of the relays; wherein the bearing power is the maximum power capable of being borne by the equipment; if the bearing power of the load switch module is greater than or equal to the load power of the load, ending the control; if the bearing power of the load switch module is smaller than the load power of the load, the load power of the load is adjusted according to the bearing power of the load switch module. According to the spacecraft load power control method provided by the embodiment of the invention, the load power of the load is prevented from exceeding the bearing power of the load switch module, and the service life of the spacecraft is prolonged.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a spacecraft payload power control method and a spacecraft. Background Art

[0002] With the development of aerospace technology and the needs of the times, satellite power is getting larger and larger. In order to cope with the power distribution of high-power loads, multiple relays must be connected in parallel to provide load power supply capacity.

[0003] The more relays there are, the greater the driving current required to control the relays. Limited by the life span of relay switching times, the risk of relay switching failure increases with the increase of spacecraft on-orbit time. When a relay switching failure occurs, the load power of the spacecraft load switch (the maximum power that the load switch can withstand) also decreases.

[0004] At present, most spacecraft have redundant power distribution designs, but it is unknown how many relays in the spacecraft will fail while in orbit. This can easily lead to the situation where the power of the spacecraft's payload exceeds the load switch's carrying power, resulting in a reduction in the spacecraft's service life. Summary of the invention

[0005] The present invention provides a spacecraft payload power control method and a spacecraft, so as to prevent the payload power of the payload from exceeding the bearing power of the load switch module, thereby increasing the service life of the spacecraft.

[0006] According to one aspect of the present invention, a spacecraft payload power control method is provided, wherein the spacecraft comprises a load switch module and a payload, wherein the load switch module comprises a state sampling component and a plurality of relays connected in parallel, wherein the state sampling component generates a sampling voltage according to the number of conduction states of the relays; the spacecraft payload power control method comprises:

[0007] Acquiring a sampling voltage of the state sampling component;

[0008] Determine the number of relays that are turned on in the load switch module according to the sampled voltage of the state sampling component;

[0009] Calculating the load power of the load switch module according to the number of relays turned on in the load switch module and the load power of the relays; wherein the load power is the maximum power that the device can withstand;

[0010] If the carrying power of the load switch module is greater than or equal to the load power of the load, then the control is terminated;

[0011] If the load power of the load switch module is less than the load power of the load, the load power of the load is adjusted according to the load power of the load switch module.

[0012] Optionally, the sampling voltage generated by the state sampling component is inversely correlated with the number of relays turned on in the load switch module; the specific method for determining the number of relays turned on in the load switch module according to the sampling voltage of the state sampling component includes:

[0013] Determine the number of faulty relays in the load switch module according to the sampling voltage generated by the state sampling component;

[0014] Calculate the number of relays turned on in the load module according to the total number of relays in the load module and the number of faulty relays in the load switch module.

[0015] Optionally, the load includes a heater; the specific method for adjusting the load power of the load according to the carrying power of the load switch module includes:

[0016] Obtain the peak power of the load;

[0017] If the load power of the load is the same as the peak power, turn off the heater;

[0018] If the load power of the load is different from the peak power, adjust the temperature control threshold of the heater until the load power of the load is less than the carrying power of the load switch module.

[0019] Optionally, the load includes a camera; the specific method for adjusting the load power of the load according to the carrying power of the load switch module includes:

[0020] Adjust the resolution of the camera until the load power of the load is less than the carrying power of the load switch module.

[0021] According to another aspect of the present invention, there is also provided a spacecraft, which includes: a load switch module, a turn-on drive module, a turn-off drive module, a first control module, and a second control module;

[0022] The load switch module includes a state sampling component and a plurality of relays. The relays are respectively connected to a load power supply, a load, the turn-on drive module, the turn-off drive module, and the state sampling component. The state sampling component, the turn-on drive module, and the turn-off drive module are also connected to the first control module. The second control module is respectively connected to the load and the first control module;

[0023] The relay is used to control the conduction or cut-off of the power supply circuit between the load and the load power supply; the state sampling component is used to output a sampling voltage according to the number of the conducted relays; the first control module is used to control the conduction driving module to drive the load switch module to conduct, or control the cut-off driving module to drive the load switch module to cut off; the second control module is used to execute the spacecraft load power control method described in any of the above embodiments.

[0024] Optionally, the state sampling component includes: a first resistor and a plurality of second resistors;

[0025] The resistance value of the first resistor is equal to that of the second resistor. The first end of the first resistor is connected to the power supply voltage, and the second end of the first resistor is connected to the first control module. The plurality of second resistors are connected in series to form a resistor string. The first second resistor in the resistor string is also connected to the second end of the first resistor. The last second resistor in the resistor string is also grounded. Each of the second resistors in the resistor string corresponds to one of the relays. The first end of the second resistor is also connected to the state detection input end of the corresponding relay, and the second end of the second resistor is also connected to the first state detection output end of the corresponding relay. The input ends of the relays are all connected to the load power supply, the output ends of the relays are all connected to the load, the conduction control input end of the relay is connected to the command power supply, the conduction control output end of the relay is connected to the conduction driving module, the cut-off control input end of the relay is connected to the command power supply, and the cut-off control output end of the relay is connected to the cut-off driving module.

[0026] Optionally, the state sampling component includes: a first resistor and a plurality of second resistors;

[0027] The resistance value of the first resistor is equal to that of the second resistor. The first end of the first resistor is connected to the power supply voltage, and the second end of the first resistor is connected to the first control module. A plurality of the second resistors are connected in series to form a resistor string. The first of the second resistors in the resistor string is also connected to the second end of the first resistor, and the last of the second resistors in the resistor string is also grounded. Each of the second resistors in the resistor string corresponds to one of the relays. The first end of the second resistor is also connected to the status detection input end of the corresponding relay, and the second end of the second resistor is also connected to the second status detection output end of the corresponding relay. The input ends of the relays are all connected to the load power supply, the output ends of the relays are all connected to the load, the conduction control input end of the relay is connected to the command power supply, the conduction control output end of the relay is connected to the conduction drive module, the turn-off control input end of the relay is connected to the command power supply, and the turn-off control output end of the relay is connected to the turn-off drive module.

[0028] Optionally, the conduction drive module includes: a conduction isolation unit and a conduction drive unit;

[0029] Each of the relays is connected to the conduction isolation unit, the conduction isolation unit is further connected to the conduction drive unit, and the conduction drive unit is further connected to the first control module;

[0030] The conduction isolation unit is used to isolate the relay from the conduction drive unit; the conduction drive unit is used to drive the relay to conduct.

[0031] Optionally, the turn-off drive module includes: a turn-off isolation unit and a turn-off drive unit;

[0032] Each of the relays is connected to the turn-off isolation unit, the turn-off isolation unit is further connected to the turn-off drive unit, and the turn-off drive unit is further connected to the first control module;

[0033] The turn-off isolation unit is used to isolate the relay from the turn-off drive unit; the turn-off drive unit is used to drive the relay to turn off.

[0034] Optionally, both the first control module and the second control module include a computer.

[0035] In the embodiment of the present invention, the sampling voltage of the state sampling component is used to determine the number of relays that are turned on in the load switch module. The carrying power of the load switch module is calculated based on the number of relays that are turned on in the load switch module and the carrying power of the relays. When the carrying power of the load switch module is less than the load power of the load, the load power of the load is limited according to the carrying power of the load switch module. In the embodiment of the present invention, the carrying power of the load switch module at present is calculated through the normal relays in the load switch module, and the load power of the load is adjusted according to the carrying power of the load switch module at present, which is beneficial to avoiding the load power of the load exceeding the carrying power of the load switch module and improving the service life of the spacecraft.

[0036] It should be understood that the content described in this part is not intended to identify the key or important features of the embodiments of the present invention, nor is it used to limit the scope of the present invention. Other features of the present invention will become easily understood through the following description. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required for the description of the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0038] Figure 1 is a schematic diagram of a spacecraft provided by an embodiment of the present invention;

[0039] Figure 2 is a schematic diagram of another spacecraft provided by an embodiment of the present invention;

[0040] Figure 3 is a schematic diagram of yet another spacecraft provided by an embodiment of the present invention;

[0041] Figure 4 is a method for controlling the load power of a spacecraft provided by an embodiment of the present invention;

[0042] Figure 5 is another method for controlling the load power of a spacecraft provided by an embodiment of the present invention;

[0043] Figure 6 is another method for controlling the load power of a spacecraft provided by an embodiment of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0044] To enable those skilled in the art to better understand the solution of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0045] It should be noted that the terms "first", "second", etc. in the description and claims of the present invention and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged under appropriate circumstances, so that the embodiments of the present invention described herein can be implemented in an order different from those illustrated or described herein. In addition, the terms "comprising" and "having" and any variations thereof are intended to cover non-exclusive inclusion. For example, a process, method, system, product or device comprising a series of steps or units does not necessarily have to be limited to those steps or units clearly listed, but may include other steps or units not clearly listed or inherent to these processes, methods, products or devices.

[0046] The embodiment of the present invention provides a method for controlling the power of a spacecraft payload. To facilitate the understanding of the method for controlling the power of a spacecraft payload provided by the embodiment of the present invention, the electrical structure of the spacecraft to which the method for controlling the power of a spacecraft payload is applied will be described first.

[0047] Figure 1 is a schematic diagram of a spacecraft provided by an embodiment of the present invention. Refer to Figure 1 This spacecraft includes: a load switch module 110, a conduction drive module 120, a turn-off drive module 130, a first control module 140, and a second control module 150.

[0048] The load switch module 110 includes a status sampling component 111 and a plurality of relays J1. The input ends of the relays J1 are all connected to the load power supply 10, the output ends of the relays J1 are all connected to the load 20, the conduction control input ends of the relays J1 are connected to the command power supply 30, the conduction control output ends of the relays J1 are connected to the conduction drive module 120, the turn-off control input ends of the relays J1 are connected to the command power supply 30, the turn-off control output ends of the relays J1 are connected to the turn-off drive module 130, the status detection input ends and status detection output ends of the relays J1 are both connected to the status sampling component 111, the status sampling component 111, the conduction drive module 120, and the turn-off drive module 130 are also connected to the first control module 140, and the second control module 150 is respectively connected to the load 20 and the first control module 140.

[0049] The relay J1 is used to control the conduction or cut-off of the power supply circuit between the load 20 and the load power supply 10; the status sampling component 111 is used to output a sampling voltage according to the number of the conducting relays J1; the first control module 140 is used to control the conduction driving module 120 to drive the load switch module 110 to conduct, or control the cut-off driving module 130 to drive the load switch module 110 to cut off; the second control module 150 is used for the spacecraft load power control method provided by any embodiment.

[0050] Specifically, the control module 140 controls the operation of the conduction driving module 120 and the operation of the cut-off driving module 130 at different times. That is to say, the conduction driving module 120 and the cut-off driving module 130 drive the load switch module 110 at different times. When the conduction driving module 120 drives the load switch module 110, the load switch module 110 conducts; when the cut-off driving module 130 drives the load switch module 110, the load switch module 110 cuts off.

[0051] The status sampling component 111 outputs a sampling voltage according to the number of the relays J1 in the conducting state. Exemplarily, the relay J1 can be a magnetic latching relay. The first control module 140 obtains the sampling voltage output by the status sampling component 111 and outputs the sampling voltage to the second control module 150. The second control module 150 can obtain the number of the faulty relays J1 or the number of the conducting relays J1 in the load switch module 110 according to the sampling voltage output by the status sampling component 111. Exemplarily, both the first control module 140 and the second control module 150 can be computers. Among them, the first control module 140 can be an on-board computer, and the second control module 150 can be a load computer.

[0052] Figure 2 It is a schematic diagram of another spacecraft provided by the embodiment of the present invention. On the basis of the above embodiment, optionally, referring to Figure 2 , the status sampling component 111 includes: a first resistor R1 and a plurality of second resistors R2.

[0053] The first end of the first resistor R1 is connected to the power supply voltage VCC, and the second end of the first resistor R1 is connected to the first control module 140. A plurality of second resistors R2 are connected in series to form a resistor string. The first second resistor R2 in the resistor string is also connected to the second end of the first resistor R1. The last second resistor R2 in the resistor string is also grounded. Each of the second resistors R2 in the resistor string corresponds to one of the relays J1. The first end of the second resistor R2 is also connected to the status detection input terminal of the corresponding relay J1, and the second end of the second resistor R2 is also connected to the first status detection output terminal of the corresponding relay J1. The input terminals of the relays J1 are all connected to the load power supply 10, the output terminals of the relays are all connected to the load 20, the conduction control input terminal of the relay J1 is connected to the command power supply 30, the conduction control output terminal of the relay J1 is connected to the conduction drive module 120, the turn-off control input terminal of the relay J1 is connected to the command power supply 30, and the turn-off control output terminal of the relay J1 is connected to the turn-off drive module 130.

[0054] Specifically, referring to Figure 2 , in the case where each second resistor R2 is connected between the status detection input terminal of the corresponding relay J1 and the first status detection output terminal.

[0055] If the relay J1 is normal, under the drive of the conduction drive module 120, the relay J1 conducts, and at this time, the second resistor R2 connected to the relay J1 is short-circuited, and the potential between the first resistor R1 and the resistor string increases, and the sampling voltage output by the status sampling component 111 increases. On the contrary, when the relay J1 fails, under the drive of the conduction drive module 120, the relay J1 cannot conduct, and the relay J1 remains in the off state. At this time, the second resistor R2 connected to the relay J1 is still connected in the resistor string. At this time, the potential between the first resistor R1 and the resistor string is lower, and the sampling voltage output by the status sampling component 111 decreases.

[0056] That is to say, when each second resistor R2 is connected between the state detection input terminal and the first state detection output terminal of the corresponding relay J1, the sampling voltage output by the state sampling component 111 is positively correlated with the number of relays J1 that are turned on in the load switch module 110. Exemplarily, when the relay J1 is turned on, the second resistor R2 corresponding to the relay J1 is short-circuited. Therefore, when the conduction driving module 120 drives the load switch module 110 to conduct, the number of second resistors R2 in the state sampling component 111 is the same as the number of relays J1 with faults (turned off). Thus, the sampling voltage of the state sampling component 111 is 1 / (M - N + 1) times the power supply voltage. Where M is the number of relays J1 in the load switch module 110, and N is the number of relays J1 with faults in the load switch module 110. Since the total number of relays J1 in the load switch module 110 and the power supply voltage are both constant values, the number of relays J1 with faults in the load switch module 110 can be obtained based on the sampling voltage of the state sampling component 111.

[0057] Figure 3 is a schematic diagram of another spacecraft provided by an embodiment of the present invention. On the basis of the above embodiment, optionally, referring to Figure 3 , each second resistor R2 in the state sampling component 111 can also be connected between the state detection input terminal and the second state detection output terminal of the corresponding relay J1. Wherein, the connection relationship of the first resistor R1 in the state sampling component 111, as well as the connection relationships of the input terminal, output terminal, conduction control input terminal, conduction control output terminal, turn-off control input terminal, and turn-off control output terminal of the relay J1 remain unchanged, and details can be referred to Figure 2 , which will not be elaborated herein.

[0058] Specifically, when each second resistor R2 is connected between the state detection input terminal and the second state detection output terminal of the corresponding relay J1.

[0059] When the relay J1 fails, under the drive of the conduction driving module 120, the relay J1 cannot be turned on and remains in the off state. At this time, the second resistor R2 connected to the relay J1 is short-circuited, and the potential between the first resistor R1 and the resistor string increases, and the sampling voltage output by the state sampling component 111 increases. On the contrary, if the relay J1 is normal, under the drive of the conduction driving module 120, the relay J1 is turned on. At this time, the second resistor R2 connected to the relay J1 is still connected in the resistor string, and the potential between the first resistor R1 and the resistor string is relatively low, and the sampling voltage output by the state sampling component 111 decreases.

[0060] That is to say, when each second resistor R2 is connected between the state detection input terminal and the second state detection output terminal of the corresponding relay J1, the sampling voltage output by the state sampling component 111 is inversely correlated with the number of conducting relays J1 in the load switch module 110. Exemplarily, when the relay J1 fails, the relay J1 is turned off, and the second resistor R2 corresponding to the relay J1 is short-circuited. Therefore, the number of second resistors R2 in the state sampling component 111 is the same as the number of conducting relays J1. Thus, the sampling voltage of the state sampling component 111 is 1 / (N'+1) times the power supply voltage. Where N' is the number of conducting relays J1 in the load switch module 110. Since the number of relays J1 in the load switch module 110 and the power supply voltage are both fixed values, the number of conducting relays J1 in the load switch module 110 can be obtained according to the sampling voltage of the state sampling component 111.

[0061] Based on the above embodiments, optionally, continue to refer to Figure 2 and Figure 3 , the conduction drive module 120 includes: a conduction isolation unit 121 and a conduction drive unit 122.

[0062] Each relay J1 is connected to the conduction isolation unit 121, the conduction isolation unit 121 is further connected to the conduction drive unit 122, and the conduction drive unit 122 is further connected to the first control module 140; the conduction isolation unit 121 is used to isolate the relay J1 from the conduction drive unit 122; the conduction drive unit 122 is used to drive the relay J1 to conduct.

[0063] Wherein, continue to refer to Figure 2 and Figure 3 , the conduction drive unit 122 includes: at least one conduction drive relay J2 and at least one conduction drive diode D1.

[0064] Specifically, the control input terminal of the conduction drive relay J2 is connected to the command power supply 30, the control output terminal of the conduction drive relay J2 is connected to the anode terminal of the conduction drive diode D1, the cathode terminal of the conduction drive diode D1 is connected to the control module 140, the input terminal of the conduction drive relay J2 is connected to the conduction isolation unit 121, and the output terminal of the conduction drive relay 121 is grounded.

[0065] Continue to refer to Figure 2 and Figure 3 , the conduction isolation unit 121 includes: at least one conduction isolation diode D2.

[0066] Specifically, the anode terminals of the conduction isolation diodes D2 are respectively connected to the relays J1 one by one, and the cathode terminals of the conduction isolation diodes J2 are all connected to the conduction drive unit 122.

[0067] Based on the above embodiments, optionally, continue to refer to Figure 2 and Figure 3 , the turn-off driving module 130 includes: a turn-off isolation unit 131 and a turn-off driving unit 132.

[0068] Each relay J1 is connected to the turn-off isolation unit 131, the turn-off isolation unit 131 is further connected to the turn-off driving unit 132, and the turn-off driving unit 132 is further connected to the first control module.

[0069] The turn-off isolation unit 131 is used to isolate the relay J1 from the turn-off driving unit 132; the turn-off driving unit 132 is used to drive the relay J1 to turn off.

[0070] Wherein, continue to refer to Figure 2 and Figure 3 , the turn-off driving unit 132 includes: at least one turn-off driving relay J3 and at least one turn-off driving diode D3.

[0071] Specifically, the control input terminal of the turn-off driving relay J3 is connected to the command power supply 30, the control output terminal of the turn-off driving relay J3 is connected to the anode terminal of the turn-off driving diode D3, the cathode terminal of the turn-off driving diode D3 is connected to the control module 140, the input terminal of the turn-off driving relay J3 is connected to the turn-off isolation unit 131, and the output terminal of the turn-off driving relay J3 is grounded.

[0072] Continue to refer to Figure 2 and Figure 3 , the turn-off isolation unit 131 includes: at least one turn-off isolation diode D4.

[0073] Specifically, the anode terminals of the turn-off isolation diodes D4 are respectively connected to the relays J1 in one-to-one correspondence, and the cathode terminals of the turn-off isolation diodes D4 are all connected to the turn-off driving unit 132.

[0074] The embodiment of the present invention also provides a method for controlling the power of a spacecraft payload. The method for controlling the power of a spacecraft payload is applied to a spacecraft. The method for controlling the power of a spacecraft payload in this embodiment calculates the current carrying power of the payload switch module through the normal relays in the payload switch module, and adjusts the payload power according to the current carrying power of the payload switch module, which is beneficial to avoiding the payload power exceeding the carrying power of the payload switch module and improving the service life of the spacecraft. Among them, the spacecraft includes a payload switch module and a payload. The payload switch module has a state sampling component and a plurality of mutually parallel relays. The state sampling component generates a sampling voltage according to the conduction number of the relays, and the sampling voltage of the state sampling component is inversely related to the conduction number of the relays. The following embodiments will specifically describe the method for controlling the power of a spacecraft payload executed by the second control module 150.

[0075] Figure 4 This is a spacecraft payload power control method provided by an embodiment of the present invention. Refer to Figure 4 , the spacecraft payload power control method includes:

[0076] S110. Obtain the sampling voltage of the status sampling component.

[0077] Exemplarily, in combination with Figure 2 , the second control module generates an acquisition instruction, the first control module obtains the acquisition instruction, acquires the sampling voltage of the status sampling component according to the acquisition instruction, and sends the obtained sampling voltage of the status sampling component to the second control module.

[0078] S120. Determine the number of conducting relays in the load switch module according to the sampling voltage of the status sampling component.

[0079] Specifically, the sampling voltage output by the status sampling component may be positively correlated or negatively correlated with the number of conducting relays in the load switch module.

[0080] Refer to Figure 2 , when the relay is normal, under the drive of the conduction drive module, the relay conducts, at this time the second resistor connected to the relay is short-circuited, the potential between the first resistor and the resistor string increases, and the sampling voltage output by the status sampling component increases. On the contrary, when the relay fails, under the drive of the conduction drive module, the relay cannot conduct, and the relay remains in the off state. At this time, the second resistor connected to the relay is still connected in the resistor string. At this time, the potential between the first resistor and the resistor string is relatively low, and the sampling voltage output by the status sampling component decreases. At this time, the sampling voltage output by the status sampling component is positively correlated with the number of conducting relays in the load switch module.

[0081] Exemplarily, when the relay conducts, the second resistor corresponding to the relay is short-circuited. Therefore, when the conduction drive module drives the load switch module to conduct, the number of second resistors in the status sampling component is the same as the number of faulty (off) relays. Therefore, the sampling voltage of the status sampling component is 1 / (M - N + 1) times the power supply voltage. Where M is the number of relays in the load switch module, and N is the number of faulty relays in the load switch module. Since the total number of relays in the load switch module and the power supply voltage are both fixed values, the number of faulty relays in the load switch module can be obtained according to the sampling voltage of the status sampling component.

[0082] After determining the number of faulty relays in the load switch module based on the sampling voltage generated by the status sampling component, the number of conducting relays in the load module can be calculated according to the total number of relays in the load module and the number of faulty relays in the load switch module. Specifically, the difference between the total number of relays in the load module and the number of faulty relays in the load switch module is the number of conducting relays in the load module.

[0083] Refer to Figure 3 , when a relay fails, under the drive of the conduction drive module, the relay cannot conduct and remains in the off state. At this time, the second resistor connected to the relay is short-circuited, and the potential between the first resistor and the resistor string increases, and the sampling voltage output by the status sampling component increases. On the contrary, if the relay is normal, under the drive of the conduction drive module, the relay conducts. At this time, the second resistor connected to the relay is still connected in the resistor string, and the potential between the first resistor and the resistor string is lower, and the sampling voltage output by the status sampling component decreases. At this time, the sampling voltage output by the status sampling component is inversely correlated with the number of conducting relays in the load switch module.

[0084] Exemplarily, when a relay fails, the relay turns off, and the second resistor corresponding to the relay is short-circuited. Therefore, the number of second resistors in the status sampling component is the same as the number of conducting relays. Therefore, the sampling voltage of the status sampling component is 1 / (N'+1) times the power supply voltage. Where N' is the number of conducting relays in the load switch module. Since the number of relays in the load switch module and the power supply voltage are both fixed values, the number of conducting relays in the load switch module can be obtained according to the sampling voltage of the status sampling component.

[0085] S130. Calculate the carrying power of the load switch module according to the number of conducting relays in the load switch module and the carrying power of the relay; where the carrying power is the maximum power that the device can withstand.

[0086] Specifically, the carrying power of the relay represents the maximum power that the relay can withstand. The relays in the load switch module are the same, so the carrying power of each relay is also the same. Therefore, the carrying power of the load switch module can be calculated according to the number of conducting relays in the load switch module and the carrying power of the relay. Where the product of the number of conducting relays in the load switch module and the carrying power of the relay is the carrying power of the load switch module.

[0087] S140. Determine whether the carrying power of the load switch module is greater than or equal to the load power of the load; if so, execute S150; if not, execute S160.

[0088] Specifically, when the carrying power of the load switch module is greater than or equal to the load power of the load, it indicates that the power distribution carrying capacity of the load switch module at this time meets the power demand of the load, and there is no need to adjust and reduce the load power of the load; when the carrying power of the load switch module is less than the load power of the load, it indicates that the power distribution carrying capacity of the load switch module cannot meet the power demand of the load, and at this time, it is necessary to adjust and reduce the load power of the load.

[0089] S150. End control.

[0090] S160. Adjust the load power according to the carrying power of the load switch module.

[0091] Specifically, different loads adjust the load power in different ways. Exemplarily, the load includes at least one core load and at least one auxiliary load. The adjustment of the load power of the load can be achieved by turning off the auxiliary loads in the load according to the preset priority of the auxiliary loads, so as to reduce the load power of the load, ensure the normal operation of the core load of the load, and guarantee the operation of the load. When the carrying power of the load switch module is greater than or equal to the load power of the load, the turning off of the auxiliary loads is stopped. Among them, when turning off the auxiliary loads in the load according to the preset priority of the auxiliary loads, the turning off is carried out from the auxiliary load with a lower priority to the auxiliary load with a higher priority.

[0092] In the embodiment of the present invention, the sampling voltage of the state sampling component is used to determine the number of turned-on relays in the load switch module, the carrying power of the load switch module is calculated according to the number of turned-on relays in the load switch module and the carrying power of the relays, and when the carrying power of the load switch module is less than the load power of the load, the load power of the load is limited according to the carrying power of the load switch module. In the embodiment of the present invention, the current carrying power of the load switch module is calculated by the normal relays in the load switch module, and the load power of the load is adjusted according to the current carrying power of the load switch module, which is beneficial to avoiding the load power of the load exceeding the carrying power of the load switch module and improving the service life of the spacecraft.

[0093] Figure 5 This is another spacecraft load power control method provided by the embodiment of the present invention. On the basis of the above embodiment, optionally, the load includes a heater. Refer to Figure 5 , and the specific method for adjusting the load power according to the carrying power of the load switch module includes:

[0094] S161. Obtain the peak power of the load.

[0095] Exemplarily, the peak power of the load can be detected by a power meter or calculated by the voltage, current and power factor of the load. This embodiment does not limit this.

[0096] S162. Determine whether the load power of the load is the same as the peak power; if so, execute S163; if not, execute S164.

[0097] Specifically, when the load power of the load is the same as the peak power, it indicates that the load power of the load has reached the maximum power of the load. At this time, turn off the heater to maximize the reduction of the load power of the load; when the load power of the load is different from the peak power, it indicates that the load power of the load has not reached the maximum power of the load. At this time, the temperature control threshold of the heater can be adjusted to reduce the load power of the load.

[0098] S163. Turn off the heater.

[0099] Exemplarily, after turning off the heater, the load power of the load can be detected in real time. When the load power of the load is less than the peak power, the heater can be restarted to provide a suitable working temperature for the load. When restarting the heater, the temperature control threshold of the heater can be set according to the carrying power of the load switch module to ensure that the load power of the load is less than the carrying power of the load switch module.

[0100] S164. Adjust the temperature control threshold of the heater until the load power of the load is less than the carrying power of the load switch module.

[0101] Specifically, when the carrying power of the load switch module is less than the load power of the load and the load power of the load is different from the peak power, the power of the heater can be limited by widening the temperature control threshold of the heater, thereby reducing the load power of the load. The temperature control threshold refers to a specific numerical limit used to define the temperature range in the temperature control process, which can be divided into an upper threshold and a lower threshold. For example, the temperature control threshold is 10 degrees - 30 degrees. When the ambient temperature of the load is greater than or equal to 30 degrees, the heater stops heating. When the ambient temperature of the load is less than or equal to 10 degrees, the heater starts heating. It should be noted that when widening the temperature control threshold of the heater, the load power of the load can be continuously detected, and the adjustment of the temperature control threshold of the heater is stopped when the load power of the load is less than the carrying power of the load switch module.

[0102] Figure 6 It is another method for controlling the load power of a spacecraft provided by an embodiment of the present invention. On the basis of the above embodiment, optionally, the load includes a camera. Refer to Figure 6 , the specific method for adjusting the load power of the load according to the carrying power of the load switch module includes:

[0103] S165. Adjust the resolution of the camera until the load power of the load is less than the carrying power of the load switch module.

[0104] Specifically, the power of the camera is related to the resolution of the camera. When the resolution of the camera is higher, the number of pixels of the camera is higher, and at this time, the power consumption of the camera is also greater. Therefore, when the carrying power of the load switch module is less than the load power of the load and the load power of the load is different from the peak power, the resolution of the camera can be adjusted and reduced to reduce the load power of the load. It should be noted that when reducing the resolution of the camera, the load power of the load can be continuously detected, and the adjustment of the resolution of the camera is stopped when the load power of the load is less than the carrying power of the load switch module.

[0105] It should be understood that various forms of the processes shown above can be used, steps can be reordered, added or deleted. For example, the steps described in the present invention can be executed in parallel, sequentially or in different orders, as long as the desired results of the technical solution of the present invention can be achieved, and no limitation is made herein.

[0106] The above specific embodiments do not constitute a limitation to the protection scope of the present invention. Those skilled in the art should understand that various modifications, combinations, sub-combinations and substitutions can be made according to design requirements and other factors. Any modifications, equivalent substitutions and improvements made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A spacecraft payload power control method, characterized in that: The spacecraft comprises a load switch module and a load, wherein the load switch module comprises a state sampling component and a plurality of relays connected in parallel with each other, wherein the state sampling component generates a sampling voltage according to the number of conduction states of the relays; The spacecraft payload power control method comprises: Acquiring a sampling voltage of the state sampling component; Determine the number of relays that are turned on in the load switch module according to the sampled voltage of the state sampling component; Calculating the load power of the load switch module according to the number of relays turned on in the load switch module and the load power of the relays; wherein the load power is the maximum power that the device can withstand; If the carrying power of the load switch module is greater than or equal to the load power of the load, then the control is terminated; If the load power of the load switch module is less than the load power of the load, the load power of the load is adjusted according to the load power of the load switch module.

2. The spacecraft payload power control method according to claim 1, characterized in that: The sampling voltage generated by the state sampling component is inversely correlated with the number of relays turned on in the load switch module; the specific method for determining the number of relays turned on in the load switch module according to the sampling voltage of the state sampling component includes: determining the number of faulty relays in the load switch module based on the sampled voltage generated by the state sampling component; The number of relays that are turned on in the load module is calculated according to the total number of relays in the load module and the number of failed relays in the load switch module.

3. The spacecraft payload power control method according to any one of claims 1-2, characterized in that: The load includes a heater; the specific method of adjusting the load power of the load according to the load power of the load switch module includes: Obtaining the peak power of the load; If the load power of the load is the same as the peak power, turning off the heater; If the load power of the load is different from the peak power, the temperature control threshold of the heater is adjusted until the load power of the load is less than the carrying power of the load switch module.

4. The spacecraft payload power control method according to any one of claims 1-2, characterized in that: The load includes a camera; the specific method of adjusting the load power of the load according to the load power of the load switch module includes: The resolution of the camera is adjusted until the load power of the load is less than the carrying power of the load switch module.

5. A spacecraft, characterized in that: include: A load switch module, a conduction drive module, a shutdown drive module, a first control module and a second control module; The load switch module includes a state sampling component and a plurality of relays, wherein the relays are respectively connected to a load power supply, a load, the on-drive module, the off-drive module and the state sampling component, wherein the state sampling component, the on-drive module and the off-drive module are also connected to the first control module, and the second control module is respectively connected to the load and the first control module; The relay is used to control the conduction or disconnection of the power supply circuit between the load and the load power supply; the state sampling component is used to output a sampling voltage according to the number of the relays that are turned on; the first control module is used to control the conduction drive module to drive the load switch module to turn on, or control the shutdown drive module to drive the load switch module to turn off; the second control module is used to execute the spacecraft payload power control method as described in any one of claims 1-4.

6. The spacecraft according to claim 5, characterized in that The state sampling component includes: a first resistor and a plurality of second resistors; The resistance value of the first resistor is equal to the resistance value of the second resistor, the first end of the first resistor is connected to the power supply voltage, the second end of the first resistor is connected to the first control module, and multiple second resistors are connected in series to form a resistor string, the first second resistor in the resistor string is also connected to the second end of the first resistor, and the last second resistor in the resistor string is also grounded, each second resistor in the resistor string corresponds to each relay one by one, the first end of the second resistor is also connected to the state detection input end of the corresponding relay, and the second end of the second resistor is also connected to the first state detection output end of the corresponding relay, the input end of the relay is connected to the load power supply, and the output end of the relay is connected to the load, the conduction control input end of the relay is connected to the instruction power supply, the conduction control output end of the relay is connected to the conduction drive module, the shutdown control input end of the relay is connected to the instruction power supply, and the shutdown control output end of the relay is connected to the shutdown drive module.

7. The spacecraft according to claim 5, characterized in that: The state sampling component includes: a first resistor and a plurality of second resistors; The resistance value of the first resistor is equal to the resistance value of the second resistor, the first end of the first resistor is connected to the power supply voltage, the second end of the first resistor is connected to the first control module, and multiple second resistors are connected in series to form a resistor string, the first second resistor in the resistor string is also connected to the second end of the first resistor, and the last second resistor in the resistor string is also grounded, each second resistor in the resistor string corresponds to each relay one by one, the first end of the second resistor is also connected to the state detection input end of the corresponding relay, and the second end of the second resistor is also connected to the second state detection output end of the corresponding relay, the input end of the relay is connected to the load power supply, and the output end of the relay is connected to the load, the conduction control input end of the relay is connected to the instruction power supply, the conduction control output end of the relay is connected to the conduction drive module, the shutdown control input end of the relay is connected to the instruction power supply, and the shutdown control output end of the relay is connected to the shutdown drive module.

8. The spacecraft according to claim 6, characterized in that The conduction driving module comprises: a conduction isolation unit and a conduction driving unit; Each of the relays is connected to the conduction isolation unit, the conduction isolation unit is also connected to the conduction drive unit, and the conduction drive unit is also connected to the first control module; The conduction isolation unit is used to isolate the relay from the conduction drive unit; the conduction drive unit is used to drive the relay to conduct.

9. The spacecraft according to claim 6, characterized in that The shutdown driving module comprises: a shutdown isolation unit and a shutdown driving unit; Each of the relays is connected to the shutoff isolation unit, the shutoff isolation unit is also connected to the shutoff drive unit, and the shutoff drive unit is also connected to the first control module; The shutdown isolation unit is used to isolate the relay from the shutdown drive unit; the shutdown drive unit is used to drive the relay to shut down.

10. The spacecraft according to claim 6, characterized in that The first control module and the second control module both include a computer.

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