CN112937915A - One-arrow-multi-star-arrow unlocking method without initiating explosive device and energy device - Google Patents
One-arrow-multi-star-arrow unlocking method without initiating explosive device and energy device Download PDFInfo
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- CN112937915A CN112937915A CN202110249439.8A CN202110249439A CN112937915A CN 112937915 A CN112937915 A CN 112937915A CN 202110249439 A CN202110249439 A CN 202110249439A CN 112937915 A CN112937915 A CN 112937915A
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Abstract
One embodiment of the invention discloses a method for unlocking a 'one-arrow-and-multiple-star' star arrow without initiating explosive devices and energy devices, which comprises the following steps: s101: the satellites to be launched are overlapped and pressed in a matching way through conical surfaces of bearing cylinders among the satellites and are installed on the rocket in an integral pressing way; s102: when the last stage of the rocket enters a preset orbit of a satellite, the rocket receives a separation signal and releases the compression freedom degree, and meanwhile, a last stage engine of the rocket is started to control a system formed by the whole rocket and the compression stacked satellites to rotate around an axis passing through the mass center of the rocket in the radial direction at a preset angular speed; s103: due to the difference of the distribution positions of the satellites, the initial linear velocity of each satellite at the unlocking moment is also different, the satellites and the rockets generate relative displacement according to the velocity difference between each satellite and the last stage of the rocket, and each satellite is separated from the rocket by the centrifugal force provided by the rotation of the last stage of the rocket to enter a preset orbit along with the time.
Description
Technical Field
The invention relates to the technical field of spaceflight, in particular to a one-arrow-multi-star-arrow unlocking method without initiating explosive devices and energy devices.
Background
The traditional one-rocket multi-satellite launching method is mainly characterized in that a central bearing cylinder structure is adopted, and a multi-satellite distributor is connected with the central bearing cylinder through an initiating explosive device, so that the connection between a satellite and a rocket is realized. After the separation instruction signal is received, the star and the arrow are unlocked after the initiating explosive device is ignited, the whole star utilizes the actuating push rod as a power source to push the satellite away from the adapter, and the unlocking and separation of the star and the arrow are realized. The existing star-rocket separation adapter unlocking modes comprise explosive bolt connection unlocking and belted connection unlocking, and a common energy separation device mainly comprises a spring push rod mechanism, a gunpowder actuating cylinder, a gas actuating cylinder, a small rocket and the like.
However, for reasons such as reliability, the unlocking and the separation of the star and the arrow need to be realized through the explosive separation of initiating explosive devices, and energy sources are needed to store energy in a certain structural form in an energy accumulation mode to serve as energy sources for the separation of the whole star. The main problems exist that firstly, each satellite needs to be independently connected with an adapter on a rocket final-stage central bearing cylinder and independently locked, and a large number of required separated initiating explosive devices occupy large resources; secondly, the multi-satellite distributor occupies a large amount of space in the fairing of the carrier rocket, so that the volumetric efficiency and the carrying capacity are reduced; thirdly, a large number of independent locking devices reduce the unlocking reliability of the system. The above problems all restrict the number of satellites launched by the 'one-arrow-and-multiple-star' and can not meet the high-frequency launching requirement of the 'one-arrow-and-multiple-star' in the future.
At present, the Starlink constellation of the SpaceX company in the United states has finished multiple times of 'one arrow 60 stars' emission, and is in a leading position on constellation networking; china realizes the emission of 'one arrow 20 stars' at most, and the emission satellites mainly comprise pico satellites and micro satellites. Due to the restriction of the problems, no substantial progress is made in the current 'one-arrow-more-star' launching.
Disclosure of Invention
The invention aims to provide a one-rocket multi-star satellite and rocket unlocking method without initiating explosive devices and energy devices, which is characterized in that the method effectively reduces the number of satellite and rocket interfaces, saves the space and the weight of a satellite and rocket adapter structure, greatly improves the utilization rate of the space in a fairing and simultaneously improves the carrying capacity of a rocket by matching and laminating conical surfaces of bearing cylinders among satellites and adopting an integral pressing mode; the method has no initiating explosive device or energy device, the power source is derived from the angular velocity of the rocket final stage, and the stacked one-rocket-multi-satellite separation is completed by utilizing different linear velocities and self-rigidity of satellites at different positions.
In order to achieve the purpose, the invention adopts the following technical scheme:
the invention provides a one-arrow-multi-star-arrow unlocking method without initiating explosive devices and energy devices, which comprises the following steps:
s101: the satellites to be launched are overlapped and pressed in a matching way through conical surfaces of bearing cylinders among the satellites and are installed on the rocket in an integral pressing way;
s102: when the last stage of the rocket enters a preset orbit of a satellite, the rocket receives a separation signal and releases the compression freedom degree, and meanwhile, a last stage engine of the rocket is started to control a system formed by the whole rocket and the compression stacked satellites to rotate around an axis passing through the mass center of the rocket in the radial direction at a preset angular speed;
s103: due to the difference of the distribution positions of the satellites, the initial linear velocity of each satellite at the unlocking moment is also different, the satellites and the rockets generate relative displacement according to the velocity difference between each satellite and the last stage of the rocket, and each satellite is separated from the rocket by the centrifugal force provided by the rotation of the last stage of the rocket to enter a preset orbit along with the time.
In one embodiment, in step S101, the speed and the separation attitude of each satellite in the subsequent separation can be controlled by changing the angle of the conical surface of the bearing cylinder between the satellites.
In one embodiment, the angles of the carrier cone surfaces can be the same or different from satellite to satellite.
In a particular embodiment, by controlling said preset angular velocity, the same satellite can be separated at different velocities.
In one embodiment, the initial angular velocities of all the satellites are the preset angular velocities.
In one embodiment, in step S103, each satellite is simultaneously separated from the rocket at different locations and at different speeds.
The invention has the following beneficial effects:
the invention provides a one-rocket multi-star satellite and rocket unlocking method without initiating explosive devices and energy devices, which is based on the thought of a stacked launching satellite technology, realizes the separation of the satellite and rocket non-initiating explosive devices, releases the degree of freedom without initiating explosive device detonation process, effectively reduces the number of satellite and rocket interfaces by matching and laminating bearing cylinder conical surfaces between satellites and integrally compresses, saves the space and the weight of a satellite and rocket adapter structure, greatly improves the utilization rate of the space in a fairing, and simultaneously improves the carrying capacity of a rocket.
Drawings
In order to more clearly illustrate the embodiments of the present application or the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are one embodiment of the present application, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 shows a flow chart of a method for unlocking a rocket without initiating explosive devices and energy sources according to one embodiment of the invention.
Figure 2 shows a schematic view of a system of a whole rocket and a compacted stack of satellites rotating at a preset angular velocity about an axis in a radial direction through the rocket's center of mass according to one embodiment of the invention.
FIG. 3 shows a diagram of initial linear velocity at a multi-star unlocking instant, in accordance with one embodiment of the present invention.
Fig. 4 shows a schematic diagram of multi-satellite on-orbit synchronization separation unlocking according to an embodiment of the invention.
Detailed Description
In order to make the technical solution of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and examples. The present invention will be described in detail with reference to specific examples, but the present invention is not limited to these examples. Variations and modifications may be made by those skilled in the art without departing from the principles of the invention and should be considered within the scope of the invention.
The embodiment provides a method for unlocking a 'one-arrow-and-multiple-star' star arrow without initiating explosive devices and energy devices, as shown in fig. 1, the method includes:
s101: the satellites to be launched are overlapped and pressed in a matching way through conical surfaces of bearing cylinders among the satellites and are installed on the rocket in an integral pressing way;
s102: when the last stage of the rocket enters a preset orbit of a satellite, the rocket receives a separation signal and releases the compression freedom degree, and meanwhile, a last stage engine of the rocket is started to control a system formed by the whole rocket and the compression stacked satellites to rotate around an axis passing through the mass center of the rocket in the radial direction at a preset angular velocity omega; as shown in fig. 2; setting the initial angular velocities of the satellites at different positions to be the preset angular velocity; the rotation is performed at a preset angular velocity all the time during the rotation.
S103: due to the difference of the distribution positions of the satellites, the initial linear velocity of each satellite at the unlocking moment is also different, as shown in fig. 3, the satellites and the rockets generate relative displacement according to the velocity difference between each satellite and the last stage of the rocket, so that the collision possibly occurring between the satellites is avoided, and each satellite is separated from the rocket at different positions and enters a preset orbit at different speeds through the centrifugal force provided by the rotation of the last stage of the rocket along with the time.
Wherein the content of the first and second substances,
by controlling the preset angular velocity, the same satellite can be separated at different velocities; meanwhile, according to the different positions of each satellite in the stacking state and the unnecessary angle of the conical surface of the bearing cylinder, the satellites in the stacking state can be separated at different positions at different initial linear speeds. The whole separation process can be completed without independent separation of initiating explosive devices and energy devices as power sources.
In the multi-satellite synchronous separation process, because conical surface fit is utilized among the satellites, the initial angular velocities of the satellites are the same. Through the conical surface connection mode designed among the satellites, the acting force is decomposed into a force F1 along the conical surface direction and a force F2 perpendicular to the conical surface direction through the conical surface action, the force F2 perpendicular to the conical surface direction provides satellite separation power, and the force F1 along the conical surface direction provides a separation speed direction. In the design process, the separation speed and the separation attitude of each satellite can be controlled by redesigning the conical surface angle. As shown in fig. 4. The angles of the conical surfaces of the bearing cylinders among the satellites can be the same or different; the conical surface angle of the bearing cylinder is designed through separation acceleration distribution and actual stress conditions, and meanwhile, the conical surface angle of the bearing cylinder is possibly different according to different positions of the satellite in a stacking state, and the separation speed requirement and the actual kinematics simulation calculation result are specifically considered.
The 'one-rocket-multi-star' satellite unlocking method without initiating explosive devices and energy devices provided by the embodiment is based on the idea of stacking and launching satellite technology, the separation of the satellite-rocket-non-initiating explosive devices and the energy-free devices is realized, the release freedom degree does not need initiating explosive device ignition process, the method effectively reduces the number of satellite-rocket interfaces through the matching and overlapping of conical surfaces of bearing cylinders among satellites and improves the carrying capacity of a rocket through the integral pressing mode, the space and the weight of a satellite-rocket adapter structure are saved, the utilization rate of the space in a fairing is greatly improved, and meanwhile, the method has no initiating explosive device and no energy device, the power source is derived from the angular speed of the last stage of the rocket, the satellite-rocket-multi-star satellite separation of a stack is completed by utilizing different linear speeds and different self rigidities of satellites at different positions, the integral structure is simpler, and the system reliability is higher.
It should be understood that the above-mentioned embodiments of the present invention are only examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention, and it will be obvious to those skilled in the art that other variations or modifications may be made on the basis of the above description, and all embodiments may not be exhaustive, and all obvious variations or modifications may be included within the scope of the present invention.
Claims (6)
1. A method for unlocking a rocket with one rocket and multiple stars without initiating explosive devices and energy devices is characterized by comprising the following steps:
s101: the satellites to be launched are overlapped and pressed in a matching way through conical surfaces of bearing cylinders among the satellites and are installed on the rocket in an integral pressing way;
s102: when the last stage of the rocket enters a preset orbit of a satellite, the rocket receives a separation signal and releases the compression freedom degree, and meanwhile, a last stage engine of the rocket is started to control a system formed by the whole rocket and the compression stacked satellites to rotate around an axis passing through the mass center of the rocket in the radial direction at a preset angular speed;
s103: due to the difference of the distribution positions of the satellites, the initial linear velocity of each satellite at the unlocking moment is also different, the satellites and the rockets generate relative displacement according to the velocity difference between each satellite and the last stage of the rocket, and each satellite is separated from the rocket by the centrifugal force provided by the rotation of the last stage of the rocket to enter a preset orbit along with the time.
2. The method of claim 1, wherein in step S101, the speed and separation attitude of each satellite can be controlled by changing the angle of the conical surface of the bearing cylinder between each satellite.
3. The method of claim 2, wherein the angles of the cone of the carrier can be the same or different from satellite to satellite.
4. Method according to claim 1, characterized in that by controlling said preset angular speed, the same satellite can be separated at different speeds.
5. The method of claim 1, wherein the initial angular velocities of all satellites are the predetermined angular velocities.
6. The method of claim 1, wherein in step S103, each satellite is simultaneously decoupled from the rocket at different locations and at different velocities.
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| CN202110249439.8A CN112937915B (en) | 2021-03-08 | 2021-03-08 | One-arrow-multi-star-arrow unlocking method without initiating explosive device and energy device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114739240A (en) * | 2022-03-30 | 2022-07-12 | 蓝箭航天空间科技股份有限公司 | Carrier rocket stage cold separation time sequence optimization method and device |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2649667A1 (en) * | 1989-07-17 | 1991-01-18 | Centre Nat Etd Spatiales | METHOD FOR LAUNCHING IN THE SPACE OF A CAPSULE AND MEANS FOR LAUNCHING THE SAME |
| DE19856670A1 (en) * | 1998-12-09 | 2000-06-15 | Daimlerchrysler Aerospace Ag | Satellite launching device |
| CN208412189U (en) * | 2018-05-09 | 2019-01-22 | 成鑫 | A kind of satellite adapter and satellite-launching facility |
| CN111891397A (en) * | 2020-08-12 | 2020-11-06 | 中国科学院微小卫星创新研究院 | One-rocket multi-satellite self-series-connection launching structure of small high-orbit satellite |
| CN111954625A (en) * | 2020-04-22 | 2020-11-17 | 中国科学院微小卫星创新研究院 | Satellite configuration and method of separation thereof |
| CN112027121A (en) * | 2020-08-28 | 2020-12-04 | 上海宇航系统工程研究所 | Tensioning type star-arrow connecting and unlocking mechanism |
| CN112078835A (en) * | 2020-09-30 | 2020-12-15 | 北京最终前沿深空科技有限公司 | Connection and separation device for multi-satellite transmission |
| CN112319853A (en) * | 2020-11-16 | 2021-02-05 | 三亚中科遥感研究所 | Microsatellite configuration design adapting to cylindrical fairing space one-rocket multi-satellite launching |
| CN112373734A (en) * | 2020-11-24 | 2021-02-19 | 东方红卫星移动通信有限公司 | Low-orbit satellite group emission satellite-arrow separation unlocking module and satellite-arrow separation method |
| CN112373735A (en) * | 2020-12-01 | 2021-02-19 | 航天科工火箭技术有限公司 | One-rocket-multi-star parallel opposite separation rocket adapter device |
-
2021
- 2021-03-08 CN CN202110249439.8A patent/CN112937915B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2649667A1 (en) * | 1989-07-17 | 1991-01-18 | Centre Nat Etd Spatiales | METHOD FOR LAUNCHING IN THE SPACE OF A CAPSULE AND MEANS FOR LAUNCHING THE SAME |
| DE19856670A1 (en) * | 1998-12-09 | 2000-06-15 | Daimlerchrysler Aerospace Ag | Satellite launching device |
| CN208412189U (en) * | 2018-05-09 | 2019-01-22 | 成鑫 | A kind of satellite adapter and satellite-launching facility |
| CN111954625A (en) * | 2020-04-22 | 2020-11-17 | 中国科学院微小卫星创新研究院 | Satellite configuration and method of separation thereof |
| CN111891397A (en) * | 2020-08-12 | 2020-11-06 | 中国科学院微小卫星创新研究院 | One-rocket multi-satellite self-series-connection launching structure of small high-orbit satellite |
| CN112027121A (en) * | 2020-08-28 | 2020-12-04 | 上海宇航系统工程研究所 | Tensioning type star-arrow connecting and unlocking mechanism |
| CN112078835A (en) * | 2020-09-30 | 2020-12-15 | 北京最终前沿深空科技有限公司 | Connection and separation device for multi-satellite transmission |
| CN112319853A (en) * | 2020-11-16 | 2021-02-05 | 三亚中科遥感研究所 | Microsatellite configuration design adapting to cylindrical fairing space one-rocket multi-satellite launching |
| CN112373734A (en) * | 2020-11-24 | 2021-02-19 | 东方红卫星移动通信有限公司 | Low-orbit satellite group emission satellite-arrow separation unlocking module and satellite-arrow separation method |
| CN112373735A (en) * | 2020-12-01 | 2021-02-19 | 航天科工火箭技术有限公司 | One-rocket-multi-star parallel opposite separation rocket adapter device |
Non-Patent Citations (1)
| Title |
|---|
| 刘进军: "卫星与多星发射", 《卫星与网络》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114739240A (en) * | 2022-03-30 | 2022-07-12 | 蓝箭航天空间科技股份有限公司 | Carrier rocket stage cold separation time sequence optimization method and device |
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