Multi-satellite separation timing design method

Abstract

This invention provides a multi-satellite separation timing design method, including: unlocking a separation mechanism; controlling the separation of the satellite assembly from the launch vehicle; controlling the separation of satellites; the satellite assembly has N layers from bottom to top, where N is an even number greater than five; after the separation mechanism is unlocked, separation signals are sequentially transmitted to the Nth layer satellite, the first layer satellite, the (N-1)th layer satellite, the second layer satellite, ..., the 1st layer satellite at the top of the satellite assembly; after a first preset time interval between the separation of the satellite assembly and the launch vehicle, the Nth layer satellite separates; after the Nth layer satellite separates, at second preset time intervals, the first layer satellite, the (N-1)th layer satellite, the second layer satellite, ..., the 1st layer satellite separate sequentially; ensuring that the satellite assembly itself is not affected by the launch vehicle's attitude control during separation; and under the given separation timing and differentiated separation speed conditions, the separation timing meets the safe distance and time requirements during the separation process, ensuring the safe separation of all satellites.

Description

Technical Field

[0001] This invention belongs to the field of multi-star separation technology, and particularly relates to a multi-star separation timing design method. Background Technology

[0002] Multi-satellite stacking launch mode is gradually becoming the preferred launch mode for launching multiple satellites with a single rocket due to its advantages such as no adapter, lightweight structure, high space utilization, and low launch cost.

[0003] In this launch mode, satellite separation mainly adopts a disordered separation mode. That is, before separation, the launch vehicle and the satellite as a whole have a certain rotational angular velocity. After the separation mechanism is unlocked, the satellites with different stacking heights have different linear velocities, thereby achieving inter-satellite separation.

[0004] However, due to the small number of satellites launched in a single launch and some control issues with the launch vehicle, this disordered separation method is prone to collisions when separating satellites with different stacking heights, and cannot guarantee the safety of separating stacked satellites. Summary of the Invention

[0005] The purpose of this invention is to address the structural shortcomings of existing technologies by proposing a multi-satellite separation timing design method that can eliminate collision problems between satellites, launch vehicles, and separation mechanisms, and achieve safe separation of stacked launch satellites under a specified separation timing.

[0006] According to one aspect of the present invention, a technical solution is provided as follows: a multi-star separation timing design method, comprising the following steps:

[0007] Unlock the control separation mechanism;

[0008] Control the separation of the satellite assembly from the launch vehicle;

[0009] Control satellite separation;

[0010] The satellite assembly has N layers from bottom to top, where N is an odd number greater than four. After the separation mechanism is unlocked, the separation signal is sequentially transmitted to the Nth layer satellite, the first layer satellite, the (N-1)th layer satellite, ..., the 1st layer satellite at the top of the satellite assembly. Layered satellites;

[0011] After a first preset time following the separation of the satellite assembly from the launch vehicle, the Nth layer of satellites separates.

[0012] After the Nth layer of satellites separates, at a second preset time interval, the first layer of satellites, the (N-1)th layer of satellites, ..., the ... The satellites separated in sequence.

[0013] Optional, the first preset time is 3s±50ms.

[0014] Optionally, the second preset time is 3s±1s.

[0015] Optionally, the separating the satellite assembly from the carrier specifically comprises:

[0016] After the separating mechanism is unlocked, the separating mechanism is controlled to complete locking after a third preset time;

[0017] The separating signal is sent to the satellite assembly;

[0018] The pyrotechnics between the satellite assembly and the carrier is controlled to explode, and the satellite assembly is separated from the carrier.

[0019] Optionally, after the separating signal is sequentially transmitted to the Nth satellite at the top of the satellite assembly, the separating mechanism is controlled to complete locking after a third preset time.

[0020] Optionally, the third preset time is 4s±100ms.

[0021] Optionally, the signal collection time of each satellite is 2s±20ms.

[0022] Optionally, the interval time from receiving the signal to separating of each satellite is 5s.

[0023] Optionally, the relative separation speed gradient between each two adjacent satellites is 0.1m / s±0.05m / s, and the angular velocity of each two adjacent satellites after separating is less than 3° / s.

[0024] Optionally, N is five, and the separating order of the satellite assembly is the fifth satellite, the first satellite, the fourth satellite, and the second satellite.

[0025] According to another aspect of the present application, another technical solution is provided as follows: a multi-satellite separating timing design method, comprising the following steps:

[0026] The separating mechanism is unlocked;

[0027] The satellite assembly is separated from the carrier;

[0028] The satellite is separated from the satellite;

[0029] The satellite assembly has N layers from the bottom to the top, and N is an even number greater than five; after the separating mechanism is unlocked, the separating signal is sequentially transmitted to the Nth satellite, the first satellite, the N-1th satellite, the second satellite,..., and the th satellite at the top of the satellite assembly;

[0030] After the satellite assembly is separated from the carrier for a first preset time, the Nth satellite is separated;

[0031] After the Nth satellite separates, every second preset time, the first layer satellite, the N-1th satellite, the second layer satellite, the N-2th satellite, the third layer satellite, the N-3th satellite, the fourth layer satellite, the N-4th satellite and the fifth layer satellite are separated in turn. The first layer satellite, the N-1th satellite, the second layer satellite, the N-2th satellite, the third layer satellite, the N-3th satellite, the fourth layer satellite, the N-4th satellite and the fifth layer satellite are separated in turn.

[0032] Optionally, the first preset time is 3s±50ms.

[0033] Optionally, the second preset time is 3s±1s.

[0034] Optionally, the control of the separation of the satellite combination and the carrier specifically comprises:

[0035] After the separation mechanism is unlocked, the control of the separation mechanism is completed after a third preset time.

[0036] The separation signal is sent to the satellite combination.

[0037] The control of the pyrotechnics between the satellite combination and the carrier is exploded, and the separation of the satellite combination and the carrier is completed.

[0038] Optionally, after the separation signal is sequentially transmitted to the Nth satellite at the top position of the satellite combination, the control of the separation mechanism is completed after a third preset time.

[0039] Optionally, the third preset time is 4s±100ms.

[0040] Optionally, the signal acquisition time of each satellite is 2s±20ms.

[0041] Optionally, the interval time from the reception of the signal to the separation of each satellite is 5s.

[0042] Optionally, the relative separation speed gradient between every two adjacent satellites is 0.1m / s±0.05m / s, and the angular velocity after the separation of every two adjacent satellites is less than 3° / s.

[0043] Optionally, N is six, and the separation order of the satellite combination is the sixth layer satellite, the first layer satellite, the fifth layer satellite, the second layer satellite, the fourth layer satellite and the third layer satellite.

[0044] Compared with the prior art, the application has the following advantages and positive effects:

[0045] In the application, the unlocking of the separation mechanism, the separation of the satellite combination and the carrier and the separation of the satellites are controlled, the satellite combination itself is ensured to be not affected by the attitude control of the carrier during the separation, and the satellites are separated in turn from the outermost layer to the innermost layer, and the separation time sequence meets the safety distance time requirement during the separation process under the condition of the given separation time sequence and the differential separation speed, so that the safety separation of all the satellites is ensured. BRIEF DESCRIPTION OF DRAWINGS

[0046] Figure 1 This is a flowchart of the multi-star separation timing design method proposed in this invention. Detailed Implementation

[0047] To better understand the above-mentioned objectives, features, and advantages of the present invention, the present invention will be further described below in conjunction with the accompanying drawings and embodiments. It should be noted that, unless otherwise specified, the embodiments and features described in these embodiments can be combined with each other.

[0048] Numerous specific details are set forth in the following description in order to provide a full understanding of the invention. However, the invention may also be practiced in other ways than those described herein, and therefore the invention is not limited to the specific embodiments disclosed in the following specification.

[0049] Example 1

[0050] like Figure 1 As shown, as an embodiment of the present invention, this embodiment discloses a multi-star separation timing design method for the separation of a six-star stacked assembly, including the following steps:

[0051] The separation mechanism is unlocked; specifically, the pyrotechnic device controlling the separation mechanism is detonated to unlock the separation mechanism, and at the same time, the separation signal is transmitted to the satellite at the top of the satellite assembly.

[0052] The satellite assembly is controlled to separate from the launch vehicle. Specifically, the launch vehicle controls the detonation of the pyrotechnic devices in the satellite assembly. Under the action of the separation spring, the satellite assembly separates from the launch vehicle, and at the same time, the separation signal is transmitted to the satellite at the bottom of the satellite assembly.

[0053] After the satellite assembly separates from the launch vehicle, the separation of the satellites is controlled. Specifically, in this embodiment, the satellite assembly has six layers from bottom to top. After the separation mechanism is unlocked, the separation signal is sequentially transmitted to the sixth layer satellite, the first layer satellite, the fifth layer satellite, the second layer satellite, and the fourth layer satellite at the top of the satellite assembly. That is, in other embodiments, when the number of satellites in the satellite assembly is even, let's say there are N layers of satellites, where N is an even number greater than four; after the separation mechanism is unlocked, the separation signal is sequentially transmitted to the Nth layer satellite, the first layer satellite, the (N-1)th layer satellite, the second layer satellite, ..., the... Layered satellites; for example, an eight-layered satellite system, the signal transmission sequence would be the eighth-layered satellite, the first-layered satellite, the seventh-layered satellite, the second-layered satellite, the sixth-layered satellite, the third-layered satellite, and the fifth-layered satellite.

[0054] As is easily understood, each pair of adjacent satellites is connected by an inter-satellite separation unlocking mechanism, a limit switch, and a separation spring. The inter-satellite separation unlocking mechanism ensures the connection between the satellites in the assembly before separation, the limit switch transmits signals, and the separation spring provides the power for separation. It is noteworthy that the separation initiation signals for the top and bottom satellites are transmitted when the separation mechanism unlocks and when the assembly separates from the launch vehicle, respectively; the separation initiation signals for the remaining satellites are transmitted when the preceding satellite in the aforementioned separation sequence separates. The signal acquisition time for each satellite is 2s ± 20ms, and the interval between signal reception and separation for each satellite is 5s.

[0055] Then, after the satellite assembly separates from the launch vehicle at a first preset time interval, the sixth layer of satellites separates; the first preset time interval is 3s ± 50ms. After the sixth layer of satellites separates, at second preset time intervals, the first layer of satellites, the fifth layer of satellites, the second layer of satellites, and the fourth layer of satellites separate sequentially. The second preset time interval is 3s ± 1s.

[0056] Furthermore, the separation of the control satellite assembly from the launch vehicle in this embodiment specifically includes:

[0057] After the separation mechanism is unlocked, the control mechanism completes locking after a third preset time; the third preset time is 4s±100ms.

[0058] Send the separation signal to the satellite assembly;

[0059] The pyrotechnics between the satellite assembly and the launch vehicle are detonated to complete the separation of the satellite assembly from the launch vehicle.

[0060] Furthermore, in this embodiment, the control separation mechanism completes locking after a third preset time, which is done after the separation signal is sequentially transmitted to the sixth layer of satellites at the top of the satellite assembly.

[0061] Furthermore, in this embodiment, the relative separation velocity gradient between any two adjacent satellites is 0.1 m / s ± 0.05 m / s, and the angular velocity after separation between any two adjacent satellites is less than 3° / s.

[0062] The table below is the separation timing table of the six-star stacked assembly in this embodiment.

[0063] Time Separation signal Separation mechanism Satellite assembly 06 satellite 01 satellite 05 satellite 02 satellite 04 satellite T0 Launch sends separation mechanism unlock signal Separation mechanism unlocks T0+2 06 satellite receives separation signal 06 satellite range switch multiple repeated collection confirms separation signal T0+4 Launch sends satellite assembly separation signal Separation mechanism moves and locks Assembly and launch separate T0+6 01 satellite receives separation signal 01 satellite range switch multiple repeated collection confirms separation signal T0+7 06 satellite sends own separation signal Assembly pulls away safe distance for 3 seconds 06 satellite separates T0+9 05 satellite receives separation signal 05 satellite range switch multiple repeated collection confirms separation signal T0+11 01 satellite sends own separation signal 06 satellite pulls away safe distance for 4 seconds 01 satellite separates T0+13 02 satellite receives separation signal 02 satellite range switch multiple repeated collection confirms separation signal T0+14 05 satellite sends own separation signal 01 satellite pulls away safe distance for 3 seconds 05 satellite separates T0+16 04 satellite receives separation signal 04 satellite range switch multiple repeated collection confirms separation signal T0+18 02 satellite sends own separation signal 05 satellite pulls away safe distance for 4 seconds 02 satellite separates T0+21 04 satellite sends own separation signal 02 satellite pulls away safe distance for 3 seconds 04 satellite separates

[0064] As can be seen from the table above, the last timing sequence is the separation of the fourth-layer satellite from the third-layer satellite. After separation is controlled by the fourth-layer satellite, the fourth-layer satellite and the third-layer satellite are gradually pulled apart under the action of the separation spring, completing the separation of all satellites, preventing collisions during the separation process, and ensuring separation safety.

[0065] Example 2

[0066] As another embodiment of the present invention, this embodiment discloses a multi-star separation timing design method for the separation of a five-star stacked assembly, comprising the following steps:

[0067] The separation mechanism is unlocked; specifically, the pyrotechnic device controlling the separation mechanism is detonated to unlock the separation mechanism, and at the same time, the separation signal is transmitted to the satellite at the top of the satellite assembly.

[0068] The satellite assembly is controlled to separate from the launch vehicle. Specifically, the launch vehicle controls the detonation of the pyrotechnic devices in the satellite assembly. Under the action of the separation spring, the satellite assembly separates from the launch vehicle, and at the same time, the separation signal is transmitted to the satellite at the bottom of the satellite assembly.

[0069] It is worth noting that the satellite assembly in this embodiment has five layers from bottom to top. After the separation mechanism is unlocked, the separation signal will be sequentially transmitted to the fifth layer of satellites, the first layer of satellites, the fourth layer of satellites, and the second layer of satellites at the top of the satellite assembly. That is, in other embodiments, when the number of satellites in the satellite assembly is odd (assuming there are N layers, where N is an odd number greater than four), after the separation mechanism is unlocked, the separation signal will be sequentially transmitted to the Nth layer of satellites, the first layer of satellites, the (N-1)th layer of satellites, ..., the... Layered satellites; for example, a seven-layered satellite system, the signal transmission sequence would be: seventh-layer satellite, first-layer satellite, sixth-layer satellite, second-layer satellite, fifth-layer satellite, and third-layer satellite.

[0070] As is easily understood, each pair of adjacent satellites is connected by an inter-satellite separation unlocking mechanism, a limit switch, and a separation spring. The inter-satellite separation unlocking mechanism ensures the connection between the satellites in the assembly before separation, the limit switch transmits signals, and the separation spring provides the power for separation. It is noteworthy that the separation initiation signals for the top and bottom satellites are transmitted when the separation mechanism unlocks and when the assembly separates from the launch vehicle, respectively; the separation initiation signals for the remaining satellites are transmitted when the preceding satellite in the aforementioned separation sequence separates. The signal acquisition time for each satellite is 2s ± 20ms, and the interval between signal reception and separation for each satellite is 5s.

[0071] Then, after a first preset time interval following the separation of the satellite assembly from the launch vehicle, the fifth layer of satellites separates; the first preset time interval is 3s ± 50ms. After the fifth layer of satellites separates, the first layer of satellites, the fourth layer of satellites, and the second layer of satellites separate sequentially at second preset time intervals. The second preset time interval is 3s ± 1s.

[0072] Furthermore, the separation of the control satellite assembly from the launch vehicle in this embodiment specifically includes:

[0073] After the separation mechanism is unlocked, the control mechanism completes locking after a third preset time; the third preset time is 4s±100ms.

[0074] Send the separation signal to the satellite assembly;

[0075] The pyrotechnics between the satellite assembly and the launch vehicle are detonated to complete the separation of the satellite assembly from the launch vehicle.

[0076] Furthermore, in this embodiment, the control separation mechanism completes locking after a third preset time, which is done after the separation signal is sequentially transmitted to the fifth layer of satellites at the top of the satellite assembly.

[0077] Furthermore, in this embodiment, the relative separation velocity gradient between any two adjacent satellites is 0.1 m / s ± 0.05 m / s, and the angular velocity after separation between any two adjacent satellites is less than 3° / s.

[0078] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention in any other way. Any person skilled in the art may make changes or modifications to the above-disclosed technical content to create equivalent embodiments that can be applied to other fields. However, any simple modifications, equivalent changes, and modifications made to the above embodiments based on the technical essence of the present invention without departing from the scope of the present invention shall still fall within the protection scope of the present invention.

Claims

1. A multi-star separation timing design method, characterized in that: Includes the following steps: The separation mechanism is unlocked, and the pyrotechnic device controlling the separation mechanism is detonated to unlock the separation mechanism. At the same time, the separation signal is transmitted to the satellite at the top of the satellite assembly. The satellite assembly is controlled to separate from the launch vehicle. The launch vehicle controls the detonation of the pyrotechnic devices in the satellite assembly. Under the action of the separation spring, the satellite assembly separates from the launch vehicle and transmits the separation signal to the satellite at the bottom of the satellite assembly. The system controls the separation of satellites. Between every two adjacent satellites, there is an inter-satellite separation unlocking mechanism, a limit switch, and a separation spring. The inter-satellite separation unlocking mechanism is used to ensure the connection relationship of each satellite in the assembly before separation. The limit switch is used to transmit signals, and the separation spring provides the power for separation. The satellite assembly has N layers from bottom to top, where N is an odd number greater than four. After the separation mechanism is unlocked, the separation signal is sequentially transmitted to the Nth layer satellite, the first layer satellite, the (N-1)th layer satellite, ..., the 1st layer satellite at the top of the satellite assembly. Layered satellites; After the satellite assembly separates from the launch vehicle for a first preset time, the Nth layer of satellites separates. After the Nth layer satellites separate, at a second preset time interval, the first layer satellites, the (N-1)th layer satellites, ..., the Nth layer satellites... The satellites separated in sequence.

2. A multi-star separation timing design method, characterized in that: Includes the following steps: The separation mechanism is unlocked, and the pyrotechnic device controlling the separation mechanism is detonated to unlock the separation mechanism. At the same time, the separation signal is transmitted to the satellite at the top of the satellite assembly. The satellite assembly is controlled to separate from the launch vehicle. The launch vehicle controls the detonation of the pyrotechnic devices in the satellite assembly. Under the action of the separation spring, the satellite assembly separates from the launch vehicle and transmits the separation signal to the satellite at the bottom of the satellite assembly. The system controls the separation of satellites. Between every two adjacent satellites, there is an inter-satellite separation unlocking mechanism, a limit switch, and a separation spring. The inter-satellite separation unlocking mechanism is used to ensure the connection relationship of each satellite in the assembly before separation. The limit switch is used to transmit signals, and the separation spring provides the power for separation. The satellite assembly has N layers from bottom to top, where N is an even number greater than five; After the separation mechanism is unlocked, the separation signal is sequentially transmitted to the Nth layer satellite, the first layer satellite, the (N-1)th layer satellite, the second layer satellite, ..., the Nth layer satellite at the top of the satellite assembly. Layered satellites; After the satellite assembly separates from the launch vehicle for a first preset time, the Nth layer of satellites separates. After the Nth layer satellites separate, at a second preset time interval, the first layer satellites, the (N-1)th layer satellites, the second layer satellites, ..., the Nth layer satellites... The satellites separated in sequence.

3. The multi-star separation timing design method according to claim 1 or 2, characterized in that: The first preset time is 3s ± 50ms.

4. The multi-star separation timing design method according to claim 1 or 2, characterized in that: The second preset time is 3s ± 1s.

5. The multi-star separation timing design method according to claim 1 or 2, characterized in that: The specific steps of controlling the separation of the satellite assembly from the launch vehicle include: After the separation mechanism is unlocked, the separation mechanism is controlled to lock after a third preset time. The separation signal is sent to the satellite assembly; The pyrotechnic devices between the satellite assembly and the launch vehicle are detonated to complete the separation of the satellite assembly from the launch vehicle.

6. The multi-star separation timing design method according to claim 5, characterized in that: After the separation signal is sequentially transmitted to the Nth layer of satellites at the top of the satellite assembly, the separation mechanism is controlled to complete the locking after a third preset time.

7. The multi-star separation timing design method according to claim 6, characterized in that: The third preset time is 4s±100ms.

8. The multi-star separation timing design method according to claim 1 or 2, characterized in that: The signal acquisition time for each satellite is 2s ± 20ms.

9. The multi-star separation timing design method according to claim 1 or 2, characterized in that: The interval between each satellite receiving the signal and separating is 5 seconds.

10. The multi-star separation timing design method according to claim 1 or 2, characterized in that: The relative separation velocity gradient between any two adjacent satellites is 0.1 m / s ± 0.05 m / s, and the angular velocity after separation between any two adjacent satellites is less than 3° / s.

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