CN115817862A - Simple rope satellite pop-up releasing mechanism - Google Patents
Simple rope satellite pop-up releasing mechanism Download PDFInfo
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- CN115817862A CN115817862A CN202211436722.2A CN202211436722A CN115817862A CN 115817862 A CN115817862 A CN 115817862A CN 202211436722 A CN202211436722 A CN 202211436722A CN 115817862 A CN115817862 A CN 115817862A
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Abstract
The invention discloses a simple tethered satellite pop-up release mechanism, which is used for releasing action of a subsatellite. The mechanism comprises a guide mechanism (1), a pre-tightening and releasing mechanism (2) and a subsatellite connecting mechanism (3). The subsatellite connecting mechanism (3) is arranged in the rectangular through hole of the guide mechanism (1) and is separated through the restraint of a spring. The pre-tightening and releasing mechanism (2) is composed of a wire cutter bracket (2A), a wire cutter (2B), a spring push plate (2C), a spring (2D) and a pull wire (2E). The wire cutter (2B) is arranged on the wire cutter bracket (2A), and a lead of the wire cutter (2B) penetrates through the spring (2D); the spring (2D) is arranged between the spring push plate (2C) and the AC fixing frame (1C), and the stay wire (2E) is arranged on the wire shearing device (2B) and the AC fixing frame (1C). The mechanism has a simple and compact structure, can limit the displacement of the subsatellite in each direction before releasing an instruction, and can quickly respond when releasing. The release device is particularly suitable for release tasks of small tethered satellite systems in colleges and universities and small atmospheric sails and solar sails for tests.
Description
Technical Field
The invention relates to the technical field of space tethered satellite systems, in particular to a simple tethered satellite pop-up release mechanism.
Background
In the field of tethered satellite systems, spring compression release devices are widely used for release of subsateters. The spring pressing and releasing device can press and release the spring and fix the subsatellite on the main star before the subsatellite is released. After receiving the release signal, the spring compresses the release device to release the restraint of the subsatellite and the spring, the subsatellite and the main satellite can generate relative displacement, the compression spring automatically returns to the original length, the elastic potential energy of the spring is converted into the kinetic energy of the subsatellite, and the release of the subsatellite is completed.
At present, for a tethered satellite system, a spring compression and release device is mostly compressed by a mechanical structure. Particularly for colleges and universities, small rope system satellite systems for experiments, such as small atmospheric sails and small solar sails, are complicated and redundant in compaction by using mechanical structures, are not beneficial to simplification and light weight of the small rope system satellite systems, and simultaneously reduce the reliability of system release.
At present, for a small-sized test tethered satellite system, a specific spring pressing and releasing device needs to be designed independently aiming at a specific task, and a spring pressing and releasing product which is simple and easy to apply and wide in application range is lacking in the market.
Disclosure of Invention
The invention adopts the technical scheme that a spring pressing and releasing mechanism of a small tethered satellite system is provided and is arranged on a main satellite through fixing frames (1A and 1B). The spring compression release mechanism is assembled with the release mechanism (2) and the subsatellite connecting mechanism (3) into a whole through pre-tightening. The spring compression release mechanism comprises a guide mechanism (1), a pre-tightening and release mechanism (2) and a subsatellite connecting mechanism (3). The guide mechanism (1) is fixedly connected with the main star through the fixing frames (1A and 1B) and plays a role in guiding the release of the sub-star. The pre-tightening and releasing mechanism (2) is assembled with the AC fixing frame (1C) through the pull wire (2E), and plays a role in releasing the pre-tightening and releasing the subsatellite of the spring. The subsatellite connecting mechanism (3) is arranged in a guide rail of a rectangular through hole type of the guide mechanism (1) and is in contact with a wire cutter bracket (2A) of the pre-tightening release mechanism (2), and a subsatellite connecting base (3A) of the subsatellite connecting mechanism (3) is fixedly connected with a subsatellite through a bolt, so that the fixing and releasing actions of the subsatellite are transmitted.
The invention relates to a simple rope-tied satellite popup release mechanism which comprises a guide mechanism (1), a pre-tightening and release mechanism (2) and a subsatellite connecting mechanism (3);
an AA fixing frame (1A), an AB fixing frame (1B), an AC fixing frame (1C) and a bottom panel (1D) are arranged on the guide mechanism (1); the AA fixing frame (1A), the AB fixing frame (1B) and the AC fixing frame (1C) are arranged on the bottom panel (1D);
the front end part of the bottom panel (1D) is provided with an AE through hole (1D 1) used for being installed with the main star connecting plate;
the AA fixing frame (1A) and the AB fixing frame (1B) have the same structure;
an AA type frame (1A 1), an AA lug panel (1A 2) and an AB lug panel (1A 3) are arranged on the AA fixing frame (1A);
the joint of the AA type frame (1A 1), the AA convex lug panel (1A 2) and the AB convex lug panel (1A 3) forms an AA rectangular hole (1A 11); the AA rectangular hole (1A 11) is used for the front end of a sub-satellite connecting support arm (3B) of the sub-satellite connecting mechanism (3) to penetrate through;
an AA through hole (1A 21) used for being installed with the main star connecting plate is formed in the AA lug panel (1A 2);
an AB through hole (1A 31) used for being installed with the main star connecting plate is formed in the AB lug panel (1A 3);
the AB fixing frame (1B) is provided with an AB type frame (1B 1), an AC lug panel (1B 2) and an AD lug panel (1B 3);
the engagement of the AB type frame (1B 1) with the AC lug panel (1B 2) and the AD lug panel (1B 3) forms an AB rectangular hole (1B 11); the AB rectangular hole (1B 11) is used for the front end of a subsatellite connecting support arm (3B) of the subsatellite connecting mechanism (3) to pass through;
the AC lug panel (1B 2) is provided with an AC through hole (1B 21) used for being mounted with the main star connecting plate;
the AD lug panel (1B 3) is provided with an AD through hole (1B 31) used for being mounted with the main star connecting plate;
the AC fixing frame (1C) is provided with a vertical plate (1C 1) and a hollow convex cylinder (1C 2), and the hollow convex cylinder (1C 2) is arranged on the outer side of the vertical plate (1C 1); the central through hole (1C 3) is used for placing a pull wire (2E) of the pre-tightening and releasing mechanism (2);
the pre-tightening and releasing mechanism (2) consists of a wire cutter bracket (2A), a wire cutter (2B), a spring push plate (2C), a spring (2D) and a pull wire (2E); the wire cutter (2B) is powered by a main satellite power supply;
the wire cutter support (2A) is provided with a front panel (2A 1), a rear panel (2A 2) and an arc-shaped plate (2A 3), the arc-shaped plate (2A 3) is positioned between the front panel (2A 1) and the rear panel (2A 2), and a wire cutter (2B) is placed on the arc-shaped plate (2A 3); a BA through hole (2A 11) is formed in the front panel (2A 1), and the BA through hole (2A 11) is used for a BA lead (2B 2) and a BB lead (2B 3) on the wire cutter (2B) to pass through;
the wire cutter (2B) is provided with a BB through hole (2B 1), and the BB through hole (2B 1) is used for the stay wire (2E) to pass through;
a BC through hole (2C 1) for the BA lead wire (2B 2) and the BB lead wire (2B 3) to pass through is arranged on the spring push plate (2C);
the spring (2D) is arranged between the spring push plate (2C) and a vertical plate (1C 1) of the AC fixing frame (1C), one end of the spring (2D) is fixed with the spring push plate (2C), and the other end of the spring (2D) is fixed with the AC fixing frame (1C) and is coaxially arranged with the axis direction of the sub-star connecting support arm (3B);
one end of a stay wire (2E) is arranged in a central through hole (1C 3) of a hollow convex cylinder (1C 2) of the AC fixing frame (1C), and the other end of the stay wire (2E) is arranged in a BB through hole (2B 1) of the thread trimmer (2B);
the subsatellite connecting mechanism (3) is provided with a subsatellite connecting base (3A) and a subsatellite connecting support arm (3B);
the sub-star connecting base (3A) is provided with a CA through hole (3A 1), a CA threaded hole (3A 2), a CB threaded hole (3A 3), a CC threaded hole (3A 4) and a CD threaded hole (3A 5); a sub-star support rod (4) is arranged in the CA through hole (3A 1); after the sub-star support rod (4) is installed in the CA through hole (3A 1), the sub-star support rod (4) and the sub-star connecting base (3A) are fixed by installing bolts in the CA threaded hole (3A 2), the CB threaded hole (3A 3), the CC threaded hole (3A 4) and the CD threaded hole (3A 5) respectively;
a lightening hole (3B 2) is arranged on the body of the sub-star connecting support arm (3B); the center of the sub-satellite connecting support arm (3B) is a CA rectangular cavity (3B 1);
before the subsatellite connecting mechanism (3) is released, the subsatellite connecting mechanism (3) is limited in a fixing frame of the guide mechanism (1) under the action of the pull wire (2E); after the pull wire (2E) is sheared, the constraint of the sub-star connecting arm (3B) of the sub-star connecting mechanism (3) in the axial direction is released, the spring (2D) returns to the original length, and the sub-star connecting arm (3B) is ejected under the pushing of the spring push plate (2C).
The spring pressing release mechanism of the small tethered satellite system has the advantages that: the guide mechanism (1), the pre-tightening and releasing mechanism (2) and the subsatellite connecting mechanism (3) designed by the invention have simple and compact structures, can limit the displacement of the subsatellite in each direction before releasing an instruction, and can quickly respond when releasing. The spring pressing release mechanism has wide application range, and can complete the specified release action by selecting springs of different types and pull wires of different materials and different geometric dimensions aiming at the tasks of different masses of subsategories and different release speeds. The subsatellite connecting mechanism is manufactured by adopting a 3D printing technology, and can realize the fixed connection with subsategories with different geometric shapes. The spring compression release mechanism has reliable effect and low manufacturing cost, and is particularly suitable for releasing tasks of small rope satellite systems in colleges and universities and small atmospheric sails and solar sails for tests.
Drawings
Fig. 1 is a block diagram of the simple tethered satellite pop-up release mechanism of the present invention.
Fig. 1A is another view of the release mechanism for ejecting a tethered satellite according to the present invention.
Fig. 1B is a sectional structural view of fig. 1A.
Fig. 1C is an exploded view of the simple tethered satellite pop-up release mechanism of the present invention.
FIG. 2 is a block diagram of the pretension and release mechanism of the simple tethered satellite pop-up release mechanism of the present invention.
Fig. 2A is a structural view of the assembly of the wire trimmer of the present invention with the wire trimmer holder.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
Referring to fig. 1, fig. 1A, fig. 1B and fig. 1C, the simple tethered satellite ejection release mechanism for release of a subsatellite action, which is designed by the present invention, comprises a guide mechanism 1, a pretension and release mechanism 2 and a subsatellite connection mechanism 3.
Guide mechanism 1
Referring to fig. 1, 1A, 1B and 1C, in the present invention, the guide mechanism 1 is an integrally formed structural member. The guide mechanism 1 is provided with an AA fixing frame 1A, an AB fixing frame 1B, an AC fixing frame 1C and a bottom panel 1D. AA mount 1A, AB mount 1B, and AC mount 1C are provided on bottom panel 1D.
The front end of the bottom panel 1D is provided with an AE through hole 1D1. The front end of the bottom panel 1D is fixed to the main star connection panel by placing screws in the AE through holes 1D1.
The AA fixing frame 1A and the AB fixing frame 1B have the same structure.
Referring to fig. 1C, an AA fixture 1A is provided with an AA jig 1A1, an AA lug panel 1A2, and an AB lug panel 1A3.
The engagement of the AA-style fixture 1A1 with the AA lug panel 1A2 and the AB lug panel 1A3 forms an AA rectangular aperture 1a11. The AA rectangular hole 1a11 is used for the front end of the subsatellite connection arm 3B of the subsatellite connection mechanism 3 to pass through.
An AA through hole 1A21 is formed in the AA lug panel 1A2, and a screw penetrates through the AA through hole 1A21 and then is matched with a threaded hole in the main star connecting plate, so that the guide mechanism 1 and the main star connecting plate are fixedly installed.
Referring to fig. 1A and 1C, an AB through hole 1A31 is formed in the AB lug panel 1A3, and a screw passes through the AB through hole 1A31 and then is matched with a threaded hole in the main star connecting plate, so that the guide mechanism 1 and the main star connecting plate are fixedly mounted.
Referring to fig. 1C, the AB holder 1B is provided with an AB type holder 1B1, an AC tab panel 1B2, and an AD tab panel 1B3.
The engagement of the AB-type shelf 1B1 with the AC lug panel 1B2 and the AD lug panel 1B3 forms an AB rectangular hole 1B11. The AB rectangular hole 1B11 is used for the front end of the subsatellite connecting arm 3B of the subsatellite connecting mechanism 3 to pass through.
An AC through hole 1B21 is formed in the AC lug panel 1B2, and a screw penetrates through the AC through hole 1B21 and then is matched with a threaded hole in the main star connecting plate, so that the guide mechanism 1 and the main star connecting plate are fixedly mounted.
Referring to fig. 1A and 1C, an AD through hole 1B31 is formed in the AD lug panel 1B3, and a screw passes through the AD through hole 1B31 and then is matched with a threaded hole in the main star connecting plate, so that the guide mechanism 1 and the main star connecting plate are fixedly mounted.
Referring to fig. 1C, an upright plate 1C1 and a hollow convex cylinder 1C2 are disposed on the AC fixing frame 1C, and the hollow convex cylinder 1C2 is disposed on the outer side of the upright plate 1C 1. The central through hole 1C3 is used for placing a pull wire 2E of the pre-tightening and releasing mechanism 2.
In the invention, the guide mechanism 1 is designed into a channel structure of the fixing frames (AA fixing frame 1A and AB fixing frame 1B) of two separated U-shaped thin plates, and the two fixing frame thin plates are coaxially arranged on the bottom panel 1D at a certain distance, which is beneficial to the sliding of the subsatellite connecting support arm 3B of the subsatellite connecting mechanism 3 during the releasing.
In the present invention, the material of the guide mechanism 1 is a 2-series or 7-series aluminum alloy material.
Pretension and release mechanism 2
Referring to fig. 1, 1A, 1B, 1C, 2A, in the present invention, the pretension and release mechanism 2 is composed of a thread trimmer holder 2A, a thread trimmer 2B, a spring push plate 2C, a spring 2D, and a pulling wire 2E. The wire cutter 2B is powered by a main satellite power supply. In the invention, the thread trimmer 2B adopts an AOXI model computer vehicle thread trimming electromagnet of Taizhou Zaojiang cheno sewing equipment.
Be equipped with front panel 2A1, rear panel 2A2, arc 2A3 on the wire cutter support 2A, arc 2A3 is located between front panel 2A1 and the rear panel 2A2, and has placed wire cutter 2B on the arc 2A 3. A BA through hole 2A11 is arranged on the front panel 2A1, and the BA through hole 2A11 is used for the BA conducting wire 2B2 and the BB conducting wire 2B3 on the wire cutter 2B to pass through. In the invention, the BA lead 2B2 and the BB lead 2B3 are respectively connected with a spring constraint control signal end of the main star and used for receiving a command of cutting the relay pull wire 2E.
The wire cutter 2B is provided with a BB through hole 2B1, and the BB through hole 2B1 is used for the wire 2E to pass through.
The spring push plate 2C is provided with a BC through hole 2C1, and the BC through hole 2C1 is used for the BA lead 2B2 and the BB lead 2B3 on the wire cutter 2B to pass through.
The spring 2D is installed between the spring push plate 2C and the vertical plate 1C1 of the AC fixing frame 1C, one end of the spring 2D is fixed with the spring push plate 2C, the other end of the spring 2D is fixed with the AC fixing frame 1C, and the spring 2D and the subsatellite are coaxially arranged in the axis direction of the connecting support arm 3B. In the invention, two ends of the spring 2D are fixedly connected with the spring push plate 2C and the vertical plate 1C1 in a bonding mode.
One end of the stay wire 2E is arranged in a central through hole 1C3 of a hollow convex cylinder 1C2 of the AC fixing frame 1C, and the other end of the stay wire 2E is arranged in a BB through hole 2B1 of the thread trimmer 2B.
In the invention, the pull wire 2E on the pre-tightening and releasing mechanism 2 is respectively installed with the AC fixing frame 1C and the thread trimmer 2B and is used for limiting the pull wire 2E to slide in the axial direction of the subsatellite connecting support arm 3B. Spring push pedal 2C is used for precompressing spring 2D to promote sub-star coupling mechanism 3 and accomplish the release at spring 2D reply original long in-process, spring push pedal 2C is the square plate structure of middle trompil, and one side links firmly with spring 2D, and the another side has linked firmly wire cutter support 2A for arrange wire cutter 2B.
In the present invention, as shown in fig. 1A and 1B, one end of the pulling wire 2E passes through the central through hole 1C3 of the hollow convex cylinder 1C2 of the AC fixing frame 1C → the lightening hole 3B2 (one side) → BB through hole 2B1 of the thread trimmer 2B → the lightening hole 3B2 (other side) → in the sub star connecting arm 3B, and a closed rope segment is formed at the position returning to the central through hole 1C3, the closed pulling wire 2E can compress the spring 2D at a specified position, and when the pulling wire 2E is cut, the spring 2D returns to the original length to release the action of the sub star connecting mechanism 3.
Referring to fig. 1, 1A, 1B and 1C, in the present invention, the sub star connection mechanism 3 is manufactured as an integrally formed structural member by using a 3D printing technology. The subsatellite connecting mechanism 3 is provided with a subsatellite connecting base 3A and a subsatellite connecting support arm 3B. The material of the subsatellite connecting mechanism 3 is nylon carbon fiber.
The sub-star connection base 3A is provided with a CA through hole 3A1, a CA threaded hole 3A2, a CB threaded hole 3A3, a CC threaded hole 3A4 and a CD threaded hole 3A5. A sub-star supporting rod 4 is arranged in the CA through hole 3A 1. When the subsatellite support rod 4 is arranged in the CA through hole 3A1, the subsatellite support rod 4 and the subsatellite connection base 3A are fixed by respectively arranging bolts in the CA threaded hole 3A2, the CB threaded hole 3A3, the CC threaded hole 3A4 and the CD threaded hole 3A5.
The body of the sub-star connecting support arm 3B is provided with a lightening hole 3B2. The center of the subsatellite connecting arm 3B is a CA rectangular cavity 3B1. In the invention, the subsatellite connecting supporting arm 3B adopts a hollow design, so that the weight of the subsatellite connecting mechanism 3 can be reduced.
In the invention, the hollow-out subsatellite connecting mechanism 3 slides in the AA rectangular hole 1A and the AB rectangular hole 1B1A of the guide mechanism 1, and due to the limitation of a working environment, airflow generated by sliding is lost through a gap between the lightening hole 3B2 and the CA rectangular cavity 3B1, so that the sliding effect of the subsatellite connecting mechanism 3 on the guide mechanism 1 is better.
In the invention, the subsatellite connecting mechanism 3 is of a hollow thin-wall square tube structure, is simultaneously provided with a subsatellite connecting base 3A and a subsatellite connecting support arm 3B, and is fixedly connected with a support on a subsatellite body into a whole through two bolts. The subsatellite connecting support arm 3B of the subsatellite connecting mechanism 3 is arranged in the AA rectangular hole 1A1A and the AB rectangular hole 1B1A of the guide mechanism 1 and is contacted with the spring push plate 2C of the pre-tightening and releasing mechanism 2, and before the subsatellite connecting mechanism 3 is released, the subsatellite connecting support arm is limited to move in the axis direction of the subsatellite connecting support arm 3B through the pull wire 2E.
In the invention, before the subsatellite connecting mechanism 3 is released, the subsatellite connecting mechanism 3 is limited in a fixed frame of the guide mechanism 1 under the action of the pull wire 2E; after the pulling wire 2E is cut, the constraint of the star connection arm 3B of the star connection mechanism 3 in the axial direction is released, the spring 2D is restored to the original length, and the star connection arm 3B is ejected by the urging of the spring pushing plate 2C. The subsatellite supporting rod 4 is arranged in a CA through hole 3A1 of the subsatellite connecting base 3A and is fixedly connected through a bolt, the fixedly connected subsatellite connecting mechanism 3 and the subsatellite are integrated, and after release is completed, the subsatellite supporting rod and the subsatellite connecting mechanism are still connected together.
Working process of simple tethered satellite ejection release mechanism
(A) The spring 2D is fixedly connected with the spring push plate 2C and the AC fixing frame 1C, the wire cutter 2B is installed at the arc-shaped plate 2A3 of the wire cutter support 2A, and a lead ( 2B 2 and 2B 3) on the wire cutter 2B is led out from the gap of the spring 2D after passing through the BC through hole 2C1 in the middle of the spring push plate 2C and the inner through hole of the spring 32 and then is connected with the spring constraint control signal end of the main star to receive the spring constraint control signal of the main star.
The guide mechanism 1 is fixedly connected with the main star through a bolt. The subsatellite connecting base 3A of the subsatellite connecting mechanism 3 is fixedly connected with the subsatellite through a bolt.
And (3) placing the wire cutter bracket 2A in the assembled pre-tightening and releasing mechanism 2 in a sub-star connecting support arm 3B of the sub-star connecting mechanism 3, and connecting the wire cutter bracket 2A to an AC fixing frame 1C of the guide mechanism 1 through a pull wire 2E to complete the assembly of the guide mechanism 1 and the pre-tightening and releasing mechanism 2. So far, the sub-star connecting support arm 3B of the sub-star connecting mechanism 3 is only required to be arranged in the rectangular through hole of the guide mechanism 1, and the spring 2D is pressed.
After the conducting wires ( 2B 2, 2B 3) on the wire cutter 2B are adjusted to proper positions, the conducting wires can be fixedly connected on the vertical plate 1C1 by glue. After the adjusting spring 2D is compressed to a preset position, the stay wire 2E is penetrated through a central through hole of the AC fixing frame 1C on the guide mechanism 1, and the head end and the tail end of the stay wire 2E are bound. And connecting a lead on the wire cutter 2B with a spring constraint control signal end of the main star. And finishing the assembly of the simple tethered satellite ejection release mechanism.
(B) When the wire cutter 2B receives the release signal, the wire cutter 2B cuts the pull wire 2E, the constraint of the spring 2D and the subsatellite connecting mechanism 3 is released, the spring 2D restores to be original, the spring push plate 2C pushes the subsatellite connecting support arm 3B, the subsatellite connecting support arm 3B is popped out from the guide mechanism 1, and the subsatellite release task is completed.
The invention designs a simple tethered satellite pop-up release mechanism for action release of a subsatellite, and aims to solve the problem of how to design a spring pressing and releasing device of a space tethered satellite system, which can meet different task requirements, and the spring pressing and releasing device has the advantages of compact structure, high releasing performance and reliability and light weight, so that a satellite with multiple tasks of the space tethered satellite system can be met by applying one satellite pop-up release mechanism.
Claims (6)
1.A simple tethered satellite pop-up release mechanism is characterized in that: comprises a guide mechanism (1), a pre-tightening and releasing mechanism (2) and a subsatellite connecting mechanism (3);
an AA fixing frame (1A), an AB fixing frame (1B), an AC fixing frame (1C) and a bottom panel (1D) are arranged on the guide mechanism (1); the AA fixing frame (1A), the AB fixing frame (1B) and the AC fixing frame (1C) are arranged on the bottom panel (1D);
the front end part of the bottom panel (1D) is provided with an AE through hole (1D 1) used for being installed with the main star connecting plate;
the AA fixing frame (1A) and the AB fixing frame (1B) have the same structure;
an AA type frame (1A 1), an AA lug panel (1A 2) and an AB lug panel (1A 3) are arranged on the AA fixing frame (1A);
the joint of the AA type frame (1A 1), the AA convex lug panel (1A 2) and the AB convex lug panel (1A 3) forms an AA rectangular hole (1A 11); the AA rectangular hole (1A 11) is used for the front end of a subsatellite connecting support arm (3B) of the subsatellite connecting mechanism (3) to pass through;
an AA through hole (1A 21) used for being installed with the main star connecting plate is formed in the AA lug panel (1A 2);
an AB through hole (1A 31) used for being installed with the main star connecting plate is formed in the AB lug panel (1A 3);
the AB fixing frame (1B) is provided with an AB type frame (1B 1), an AC lug panel (1B 2) and an AD lug panel (1B 3);
the engagement of the AB type frame (1B 1) with the AC lug panel (1B 2) and the AD lug panel (1B 3) forms an AB rectangular hole (1B 11); the AB rectangular hole (1B 11) is used for the front end of a subsatellite connecting support arm (3B) of the subsatellite connecting mechanism (3) to pass through;
the AC lug panel (1B 2) is provided with an AC through hole (1B 21) used for being mounted with the main star connecting plate;
the AD lug panel (1B 3) is provided with an AD through hole (1B 31) used for being mounted with the main star connecting plate;
the AC fixing frame (1C) is provided with a vertical plate (1C 1) and a hollow convex cylinder (1C 2), and the hollow convex cylinder (1C 2) is arranged on the outer side of the vertical plate (1C 1); the central through hole (1C 3) is used for placing a pull wire (2E) of the pre-tightening and releasing mechanism (2);
the pre-tightening and releasing mechanism (2) consists of a wire cutter bracket (2A), a wire cutter (2B), a spring push plate (2C), a spring (2D) and a pull wire (2E); the wire cutter (2B) is powered by a main satellite power supply;
the wire cutter support (2A) is provided with a front panel (2A 1), a rear panel (2A 2) and an arc-shaped plate (2A 3), the arc-shaped plate (2A 3) is positioned between the front panel (2A 1) and the rear panel (2A 2), and a wire cutter (2B) is placed on the arc-shaped plate (2A 3); a BA through hole (2A 11) is formed in the front panel (2A 1), and the BA through hole (2A 11) is used for a BA lead (2B 2) and a BB lead (2B 3) on the wire cutter (2B) to pass through;
the wire cutter (2B) is provided with a BB through hole (2B 1), and the BB through hole (2B 1) is used for the stay wire (2E) to pass through;
a BC through hole (2C 1) for the BA lead wire (2B 2) and the BB lead wire (2B 3) to pass through is arranged on the spring push plate (2C);
the spring (2D) is arranged between the spring push plate (2C) and a vertical plate (1C 1) of the AC fixing frame (1C), one end of the spring (2D) is fixed with the spring push plate (2C), and the other end of the spring (2D) is fixed with the AC fixing frame (1C) and is coaxially arranged with the axis direction of the sub-star connecting support arm (3B);
one end of a stay wire (2E) is arranged in a central through hole (1C 3) of a hollow convex cylinder (1C 2) of the AC fixing frame (1C), and the other end of the stay wire (2E) is arranged in a BB through hole (2B 1) of the thread trimmer (2B);
the subsatellite connecting mechanism (3) is provided with a subsatellite connecting base (3A) and a subsatellite connecting support arm (3B);
the sub-star connecting base (3A) is provided with a CA through hole (3A 1), a CA threaded hole (3A 2), a CB threaded hole (3A 3), a CC threaded hole (3A 4) and a CD threaded hole (3A 5); a sub-star support rod (4) is arranged in the CA through hole (3A 1); after the sub-star support rod (4) is installed in the CA through hole (3A 1), the sub-star support rod (4) and the sub-star connecting base (3A) are fixed by installing bolts in the CA threaded hole (3A 2), the CB threaded hole (3A 3), the CC threaded hole (3A 4) and the CD threaded hole (3A 5) respectively;
a weight-reducing hole (3B 2) is arranged on the body of the subsatellite connecting support arm (3B); the center of the subsatellite connecting support arm (3B) is a CA rectangular cavity (3B 1);
before the sub-satellite connecting mechanism (3) is released, the sub-satellite connecting mechanism (3) is limited in a fixing frame of the guide mechanism (1) under the action of the pull wire (2E); after the pull wire (2E) is cut off, the constraint of the subsatellite connecting arm (3B) of the subsatellite connecting mechanism (3) in the axial direction is released, the spring (2D) restores to the original length, and the subsatellite connecting arm (3B) is ejected under the pushing of the spring push plate (2C).
2. The simple tethered satellite pop-up release mechanism of claim 1, wherein: the two ends of the spring (2D) are fixedly connected with the spring push plate (2C) and the vertical plate (1C 1) in a bonding mode.
3. The simple tethered satellite pop-up release mechanism of claim 1, wherein: the spring push plate (2C) is used for pre-compressing the spring (2D) and pushing the sub-star connecting mechanism (3) to complete releasing in the process that the spring (2D) returns to the original length.
4. The simple tethered satellite pop-up release mechanism of claim 1, wherein: the layout of the pull wire (2E) is that one end of the pull wire (2E) penetrates through a central through hole (1C 3) of a hollow convex cylinder (1C 2) of an AC fixed frame (1C) → weight reducing holes (3B 2) on one side of the subsatellite connecting support arm (3B) → BB through hole (2B 1) of the wire cutter (2B) → weight reducing holes (3B 2) on the other side of the subsatellite connecting support arm (3B) → a closed rope section is formed at the position returning to the central through hole (1C 3), the closed pull wire (2E) can compress the spring (2D) at a specified position, and after the pull wire (2E) is cut, the spring (2D) returns to the original length to realize the action release of the subsatellite connecting mechanism (3).
5. The simple tethered satellite pop-up release mechanism of claim 1, wherein: the subsatellite connecting support arm (3B) adopts a hollow design, so that the weight of the subsatellite connecting mechanism (3) can be reduced.
6. The simple tethered satellite pop-up release mechanism of claim 1, wherein: the spring for the space tethered satellite system compresses and releases.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111460817 | 2021-12-02 | ||
| CN2021114608173 | 2021-12-02 |
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| Publication Number | Publication Date |
|---|---|
| CN115817862A true CN115817862A (en) | 2023-03-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211436722.2A Pending CN115817862A (en) | 2021-12-02 | 2022-11-16 | Simple rope satellite pop-up releasing mechanism |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115959308A (en) * | 2023-01-31 | 2023-04-14 | 北京理工大学 | Low-cost electrically-driven electrodynamic force rope releasing device and off-track experimental device |
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2022
- 2022-11-16 CN CN202211436722.2A patent/CN115817862A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115959308A (en) * | 2023-01-31 | 2023-04-14 | 北京理工大学 | Low-cost electrically-driven electrodynamic force rope releasing device and off-track experimental device |
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