CN215944939U - Novel drag slow release device of carrier rocket - Google Patents

Abstract

The utility model provides a novel drag slow release device of a carrier rocket, which is provided with a plurality of slow release structures, wherein the slow release structures are arranged on a launching platform and used for dragging and pressing the tail end of the rocket. The slow release structure is controlled by the telescopic rod to hold or release the tail end of the rocket. The plurality of slow release structures are uniformly distributed around the tail end of the rocket and are used for applying uniform drag force to the tail end of the rocket. The drag slow release device has the advantages of simple structure, few parts, easy production and maintenance and stable operation. In addition, the controlled slow release device can realize automatic control, has high reaction speed and good release synchronism. The traction sustained-release device can not generate vibration impact load on the rocket tail structure when releasing the rocket tail, thereby ensuring the safety and stability of rocket launching.

Description

Novel drag slow release device of carrier rocket

Technical Field

The utility model relates to the technical field of rocket restraining and slow-releasing devices, in particular to a novel restraining and slow-releasing device of a carrier rocket.

Background

At the moment of rocket launching, the engine usually delays for several seconds to reach full thrust. Meanwhile, in order to improve the launching reliability and guarantee the safety of a launching station, a containment slow release device is a necessary technical means when the carrier rocket is launched.

Currently, the drag-and-drop devices are mainly classified into two categories: mechanical configurations and explosive bolts. The mechanical structure type drag slow release device is mainly driven by pneumatics or hydraulics, and mechanical parts act to achieve the purpose of dragging and slowly releasing the rocket. The mechanical parts are more, the manufacturing and assembling precision is required to be high, and the synchronization of slow release is poor. The explosive bolt type containment slow-release device comprises an explosive bolt and a slow-release pin, is generally designed in a group, and is required to meet the requirement that the bolt explodes instantly after the thrust of a rocket engine reaches a preset value and overcome the generated additional impact load by the slow-release device. The rocket body has the advantages of simple structure, good synchronism, poor slow release effect and vibration impact load acting on the tail end structure of the rocket body.

Therefore, there is a need for a sustained release device with simple structure, fast reaction speed and good release synchronization.

Disclosure of Invention

The utility model aims to overcome the defects of the prior art and provide a novel drag slow release device of a carrier rocket. The traction sustained-release device has the advantages of simple structure, few parts, easy production and maintenance, capability of realizing automatic control, good release synchronism, and no vibration impact load on the tail structure of the rocket when the tail of the rocket is released, thereby ensuring the safety of rocket launching.

The utility model provides a novel drag slow release device of a carrier rocket, which is provided with a plurality of slow release structures, wherein the slow release structures are arranged on a launching platform and used for dragging and pressing the tail end of the rocket; the slow release structure is controlled by a telescopic rod to hold or release the tail end of the rocket; the plurality of slow release structures are uniformly distributed around the rocket tail end and are used for applying uniform drag force to the rocket tail end.

Furthermore, the rocket tail end is provided with a bearing shaft, and the slow release structure is in contact with the bearing shaft and is used for applying a traction force to the rocket tail end.

Furthermore, the slow release structure is also provided with a pressure lever and a rotating arm, wherein one end of the rotating arm is movably connected to the launching platform through a first support; the other end of the rotating arm is provided with a U-shaped groove, and the pressing rod is movably connected in the U-shaped groove; one end of the pressure lever is movably connected with the telescopic rod, and the other end of the pressure lever is used for being in contact with the bearing shaft and exerting a traction force on the bearing shaft under the action of the telescopic rod.

Furthermore, the other end of the telescopic rod is movably connected to the launching platform through a second support, and is used for providing supporting force for the telescopic rod.

In an embodiment of the present invention, the slow release structure further comprises a force sensor, and the force sensor is disposed on the telescopic rod and is configured to detect an axial force of the telescopic rod; the force sensor circuit is connected with the control end, and feeds back the axial force data of the telescopic rod to the control end for controlling the drag slow-release process.

Further, when the difference between the rocket thrust and the rocket gravity is larger than or equal to the sum of the preset traction forces of the plurality of slow release structures, the controller controls the telescopic rod to drive the pressure rod to rotate, and the traction force applied by the pressure rod to the bearing shaft is gradually cancelled.

In an embodiment of the utility model, one end of the pressure lever, which is in contact with the bearing shaft, is a curved end, and the concave side of the curved end is arranged at the lower part of the pressure lever; when the pressure rod applies a traction force to the bearing shaft, the bearing shaft is arranged at the lower part of the pressure rod and is used for keeping the pressure rod applying the traction force to the bearing shaft in the process that the traction slow release device releases the rocket.

Further, in the process that the rocket is lifted to the preset height, the drag force exerted on the bearing shaft by the pressure rod is gradually reduced to zero.

In an embodiment of the present invention, the telescopic rod is a hydraulic rod or an electric rod.

In an embodiment of the present invention, the rotating arm is connected to the first support through a bolt or a bolt; the pressure lever is connected with the rotating arm through a bolt or a bolt; the telescopic rod is connected with the second support through a bolt or a bolt.

According to the embodiment, the novel containment slow release device of the carrier rocket has the following advantages:

compared with the prior art, the traction slow release device has the advantages of simple integral structure and few parts, so that the failure rate of the device can be reduced, and the production and the later maintenance are facilitated. In addition, the drag slow release device can realize automatic control, the start of the device is controlled by presetting the drag force value, the synchronous release of a plurality of drag slow release devices can be ensured, the stability of the rocket in the ascending process is ensured, and the takeoff drift amount of rocket launching is greatly reduced. Compared with the existing explosive bolt type containment slow-release device, the containment slow-release device does not generate vibration impact load to the tail end of the rocket when releasing the tail end of the rocket, thereby improving the reliability of the launching task of the rocket and ensuring the safety of the launching process.

It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the utility model, as claimed.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the utility model and together with the description, serve to explain the principles of the utility model.

Fig. 1 is a use state diagram of a novel drag slow release device of a carrier rocket provided by the utility model.

Fig. 2 is a partial view at a in fig. 1.

FIG. 3 is a schematic diagram of the structure of a novel drag slow release device of a carrier rocket.

Fig. 4 is a motion state diagram of a novel drag slow release device of a carrier rocket provided by the utility model.

FIG. 5 is a diagram showing a first usage state of a first embodiment of a novel drag slow release device of a launch vehicle provided by the utility model.

Fig. 6 is a usage state diagram of a second embodiment of the novel drag slow release device of the launch vehicle provided by the utility model.

Fig. 7 is a usage state diagram of a third embodiment of the novel drag slow release device of a carrier rocket provided by the utility model.

Description of reference numerals:

1-slow release structure, 2-launching platform, 3-rocket tail end;

11-telescopic rod, 12-compression bar, 13-rotating arm, 14-first support, 15-second support, 16-force sensor and 31-bearing shaft.

Detailed Description

Reference will now be made in detail to various exemplary embodiments of the utility model, the detailed description should not be construed as limiting the utility model but as a more detailed description of certain aspects, features and embodiments of the utility model.

It will be apparent to those skilled in the art that various modifications and variations can be made in the specific embodiments of the present disclosure without departing from the scope or spirit of the disclosure. Other embodiments will be apparent to those skilled in the art from consideration of the specification. The specification and examples are exemplary only.

The utility model provides a novel drag slow release device of a carrier rocket, and a use state diagram of the drag slow release device is shown in figure 1. The captive sustained release apparatus has a plurality of sustained release structures 1. Wherein, a plurality of slow release structures 1 are arranged on the launching platform 2 and used for restraining and compressing the rocket tail end 3. The slow release structure 1 is controlled by the telescopic rod 11, so that the slow release structure 11 can hold or release the rocket tail end 3. Specifically, one slow release structure 11 corresponds to one telescopic rod and drives the slow release structure to move.

The plurality of sustained-release structures 1 are uniformly distributed around the rocket tail end 3 and are used for applying uniform drag force to the rocket tail end 3. In order to ensure the stability of the rocket state, the drag force of the rocket tail end needs to be kept uniform, so that a plurality of slow release structures 11 need to be uniformly arranged around the rocket tail end, and the drag force of the rocket tail end in multiple directions is ensured.

In the specific embodiment of the utility model, as shown in fig. 2, the rocket tail end 3 is provided with a bearing shaft 31, and the slow release structure 1 is in contact with the bearing shaft 31 and is used for applying acting force to the bearing shaft 31 through the slow release structure 1 and further applying a traction force to the rocket tail end 3. The bearing shaft 31 can rotate relative to the rocket tail end 3, and is used for realizing rolling contact between the slow release structure 1 and the bearing shaft 31, reducing friction force when the slow release structure 1 and the bearing shaft 31 move mutually, and enabling relative movement of the slow release structure 1 and the bearing shaft 31 to be more flexible.

Specifically, the slow-release structure 1 further includes a pressure lever 12 and a rotating arm 13. Wherein, one end of the rotating arm 13 is movably connected on the launching platform 2 through a first support 14. Preferably, the swivel arm 13 is connected to the first support 14 by a latch or bolt.

The other end of the rotating arm 13 is provided with a U-shaped groove, and the pressure lever 12 is movably connected in the U-shaped groove. Preferably, the pressure lever 12 is connected with the rotating arm 13 through a bolt or a bolt.

One end of the pressure lever 12 is movably connected with the telescopic rod 11, the other end of the pressure lever 12 is used for contacting with the bearing shaft 31, and the pressure lever 12 exerts a drag force on the bearing shaft 31 under the thrust action of the telescopic rod 11. And under the action of the pulling force of the telescopic rod 11, the compression rod 12 is gradually separated from the contact with the bearing shaft 31.

The other end of the telescopic rod 11 is movably connected to the launching platform 2 through a second support 15, and the second support 15 is used for providing supporting force for the telescopic rod 11. Preferably, the telescopic rod 11 is connected with the second support 15 by means of a pin or a bolt. In the specific embodiment of the present invention, the telescopic rod 11 is a hydraulic rod or an electric rod, which can realize remote control of the telescopic rod 11.

As shown in fig. 3, during the telescopic movement of the telescopic rod 11, the rotating arm 13 swings in the limited direction of the first support 14, and the pressing rod 12 ascends or descends under the limit of the rotating arm 13 and the driving of the telescopic rod 11.

In the embodiment of the present invention, the sustained release structure 1 further has a force sensor 16 thereon. As shown in fig. 3, a force sensor 16 is disposed on the telescopic rod 11 for detecting the axial force of the telescopic rod 11. The magnitude of the force applied by the pressure lever 12 to the bearing shaft 31 can be further known by detecting the axial force condition of the telescopic rod 11, and the magnitude of the force applied by the bearing shaft 31 to the pressure lever 12 can be obtained because the forces act on each other.

In addition, the force sensor 16 is connected with the control end through a circuit, axial force data of the telescopic rod 11 are fed back to the control end, and the control end further controls the process that the pressure lever 12 restrains and slowly releases the bearing shaft 31 according to the magnitude of the axial force fed back in real time.

Specifically, when the difference between the rocket thrust and the rocket gravity is greater than or equal to the sum of the preset drag forces of the plurality of slow-release structures 1, the force sensor 16 transmits the detected axial force data to the controller, and the controller controls the telescopic rod 11 to gradually retract. The pressure lever 12 is driven by the telescopic rod 11 to rotate and gradually raises under the limit of the rotating arm 13, and in the process of raising the pressure lever 12, the traction force applied by the pressure lever 12 to the bearing shaft 31 is gradually reduced until the traction force is zero. The pressure lever 12 is separated from the bearing shaft 31, and the tail end of the rocket is released. In the releasing process, the plurality of slow-release structures 1 are synchronously carried out under the control of the controller, so that the condition that the stress at the tail end of the rocket is uneven in the process of lifting the rocket is avoided as much as possible. In addition, the rocket may shake due to the influence of wind force and other factors before takeoff, the axial force detected by the force sensors 16 on the sustained-release structures 1 is different due to the rocket shaking, and in order to prevent misjudgment, the difference between the rocket thrust and the rocket gravity needs to be set to be slightly larger than the sum of the preset drag forces of the sustained-release structures 1, so that the safety and reliability of the rocket launching process can be ensured.

In the embodiment of the present invention, as shown in fig. 3, one end of the pressure rod 12 contacting the bearing shaft 31 is a curved end, and the concave side of the curved end is at the lower part of the pressure rod 12, i.e. the concave side is the side of the pressure rod 12 facing the bottom of the rocket. When the pressure lever 12 applies a traction force to the bearing shaft 31, the bearing shaft 31 is arranged at the lower part of the pressure lever 12, namely the bearing shaft 31 is contacted with the curved end of the pressure lever 12, and the pressure lever 12 keeps applying the traction force to the bearing shaft 31 in the process that the traction slow release device releases the rocket. The bottom surface of the pressure lever 12 is tangent to the surface of the bearing shaft 31, force is transferred in a line contact mode, and then downward pressure is applied to the tail end of the rocket to restrain the motion of the rocket. In addition, the friction force is smaller in a line contact mode compared with a surface contact mode, when the rocket is lifted off, the relative movement between the bearing shaft 31 and the pressure rod 12 is smoother, the blocking condition is avoided, the dragging force applied to each direction of the tail of the rocket is more uniform when the rocket is lifted off, and the stability of the rocket in the lifting off process is ensured. Before the rocket is not lifted off, the restraining force applied to the bearing shaft 31 by the concave side of the curved end of the compression rod 12 comprises a horizontal force and a vertical force. Wherein the horizontal force is used to constrain the takeoff drift motion of the rocket launch. The vertical force is used for pressing the tail of the rocket.

In addition, the pressure lever 12 has a fixed maximum raising height, and the bearing shaft 31 is gradually separated from the pressure lever 12 in the raising process of the pressure lever 12. That is, the restraining force of the pressure lever 12 on the bearing shaft 31 is gradually reduced to zero during the process of lifting the rocket to the preset height. In the process, the drag force changes in a curve, so that the rocket releasing process is more stable.

Fig. 4 shows different state diagrams of the sustained-release structure 1 during the rocket ascent. Before the rocket is lifted off, the slow release structures 1 are in a state, and the difference between the lifting force of the rocket and the gravity of the rocket is smaller than the sum of the preset drag force of the slow release structures 1 on the bearing shaft 31. When the difference between the lifting force of the rocket and the gravity of the rocket is greater than or equal to the sum of the preset drag force of the plurality of slow release structures 1 on the bearing shaft 31, the control end controls the telescopic rod 11 to gradually retract, and the compression rod 12 gradually performs upward movement under the limiting of the rotating arm 13, the thrust action of the bearing shaft 31 and the thrust action of the telescopic rod 11. In the lifting process, the thrust of the rocket is gradually increased, and the height of the rocket is gradually increased. When the slow release structure 1 moves to the position b in fig. 4, the bearing shaft 31 moves to the tail end of the compression bar 12, and the restraining force applied to the bearing shaft 31 by the compression bar 12 is gradually reduced to zero in the process from a to b. Then the compression bar 12 is lifted continuously in the retracting process of the telescopic bar 11 to reach the state c, the bearing shaft 31 is separated from the compression bar 12 in the process from b to c, the rocket reaches the full thrust state in the process, the rocket ascends, and the rocket is lifted off.

In an embodiment of the utility model, as shown in fig. 5, when the rocket tail end has one main body, 4 sustained-release structures 1 are uniformly distributed around the rocket tail end, and the angle between every two sustained-release structures 1 is 90 degrees, so that the sustained-release force applied to the rocket tail end in each direction is uniform, and the probability of rocket inclination is greatly reduced.

In one embodiment of the present invention, as shown in fig. 6, when the rocket tail has three bodies, and the three bodies are fixedly connected side by side, a plurality of the containment slow release devices are respectively arranged at the axis of each body. Two slowly-releasing structures 1 of fixed connection on the main part vertical axis in the middle of promptly, on the rocket main part of both sides, set up two slowly-releasing structures respectively on vertical axis, set up a slowly-releasing structure on the horizontal axis. The distribution ensures that the slow release force applied to the tail end of the rocket in all directions is uniform, and greatly reduces the probability of inclination of the rocket.

In one embodiment of the present invention, as shown in fig. 7, when the rocket tail end has five bodies, one body is disposed in the middle, and the other four bodies are respectively located in the horizontal and vertical axial directions of the middle body, i.e. located around the middle body, and are distributed in 90 degrees between every two bodies and are all fixedly connected with the middle body. In the embodiment, 4 slow-release structures are arranged, and 4 slow-release structures 1 are respectively arranged at the outer sides of the four surrounding main bodies, so that the plurality of slow-release structures can apply uniform restraining force to the surrounding main bodies.

The foregoing is merely an illustrative embodiment of the present invention, and any equivalent changes and modifications made by those skilled in the art without departing from the spirit and principle of the present invention should fall within the protection scope of the present invention.

Claims (10)

1. A novel drag slow release device of a carrier rocket is characterized in that the drag slow release device is provided with a plurality of slow release structures (1), wherein,

the plurality of slow release structures (1) are arranged on the launching platform (2) and used for restraining and compacting the rocket tail end (3);

the slow release structure (1) is used for controlling or releasing the rocket tail end (3) through a telescopic rod (11);

the slow release structures (1) are uniformly distributed around the rocket tail end (3) and are used for applying uniform drag force to the rocket tail end (3).

2. The hold-down slow release device for a novel launch vehicle according to claim 1, characterised in that the rocket tail end (3) is provided with a bearing shaft (31), the slow release structure (1) being in contact with the bearing shaft (31) for exerting a hold-down force on the rocket tail end (3).

3. The hold-down slow release device for a novel launch vehicle according to claim 2, characterized in that the slow release structure (1) further has a pressure lever (12) and a swivel arm (13), wherein,

one end of the rotating arm (13) is movably connected to the launching platform (2) through a first support (14);

the other end of the rotating arm (13) is provided with a U-shaped groove, and the pressure lever (12) is movably connected in the U-shaped groove;

one end of the pressure lever (12) is movably connected with the telescopic rod (11), the other end of the pressure lever (12) is used for being in contact with the bearing shaft (31), and the bearing shaft (31) is applied with a traction force under the action of the telescopic rod (11).

4. The novel launch vehicle contain release device according to claim 3, characterized in that the other end of the telescoping rod (11) is movably connected to the launch pad (2) by a second support (15) for providing support to the telescoping rod (11).

5. The novel launch vehicle containment slow-release device according to claim 3, characterized in that the slow-release structure (1) is further provided with a force sensor (16), wherein the force sensor (16) is arranged on the telescopic rod (11) and is used for detecting the axial force of the telescopic rod (11);

the force sensor (16) is connected with the control end through a circuit, and feeds back the axial force data of the telescopic rod (11) to the control end for controlling the traction slow-release process.

6. The novel drag release device of a launch vehicle according to claim 5, wherein when the difference between the rocket thrust and the rocket gravity is greater than or equal to the sum of the preset drag forces of the plurality of slow release structures (1), the controller controls the telescopic rod (11) to drive the compression rod (12) to rotate, and gradually withdraws the drag force applied by the compression rod (12) to the bearing shaft (31).

7. The novel drag controlled slow release device of a launch vehicle according to claim 3, characterized in that the end of the strut (12) in contact with the bearing shaft (31) is a curved end, the concave side of which is at the lower part of the strut (12);

when the pressure rod (12) applies a traction force to the bearing shaft (31), the bearing shaft (31) is arranged at the lower part of the pressure rod (12), and the pressure rod (12) keeps applying the traction force to the bearing shaft (31) in the process that the traction slow-release device releases the rocket.

8. The device for the controlled release of the drag of a novel launch vehicle according to claim 7, characterized in that the drag force exerted by said strut (12) on said bearing shaft (31) is gradually reduced to zero during the raising of the rocket to a predetermined height.

9. The new launch vehicle containment slow release device according to claim 1, characterized in that the telescopic rod (11) is a hydraulic or electric rod.

10. The hold-down slow release device of a novel launch vehicle according to claim 4, characterized in that the pivoted arm (13) is connected with the first support (14) by means of a pin or a bolt;

the pressure lever (12) is connected with the rotating arm (13) through a bolt or a bolt;

the telescopic rod (11) is connected with the second support (15) through a bolt or a bolt.

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