Separable attitude control power control system

Abstract

The present invention provides a detachable attitude control power control system, comprising: a controller, an altitude sensor, a separation explosion device, a separation compression spring and an attitude control device mounting seat. The separation explosion device comprises a detonator, a detonating cord, explosives and a separation bolt, wherein the explosives are arranged in the separation bolt. The separation compression spring is located between the attitude control device mounting seat and the sealing cylinder in a compressed state; an installation space for the attitude control device is formed inside the attitude control device mounting seat, and the bottom of the attitude control device mounting seat is connected to the sealing cylinder on the control cabin through the separation bolt. When the aircraft flies to a preset altitude threshold, the controller controls the detonator to ignite the explosive to blow off the separation bolt, so that the attitude control device mounting seat is separated from the sealing cylinder. The present invention can separate the attitude control power system from the aircraft to reduce the weight redundancy of the aircraft and increase the range of the aircraft.

Description

Technical Field

[0001] The present invention relates to the technical field of launch vehicles, and in particular to a detachable attitude control power control system. Background Art

[0002] Hypersonic glide vehicles consist of a booster stage and a glide stage. After the booster stage boosts the vehicle to a predetermined altitude, it separates from the glide stage, and the glide stage relies on aerodynamic force to achieve long-distance non-ballistic loading flight. This type of aircraft abandons the ballistic mode of conventional aircraft and is attracting widespread attention from military powers around the world for its long range, good maneuverability, and difficulty in interception. In order to meet the requirements of maneuverability indicators, this type of aircraft mainly uses air rudders for attitude control. At the same time, the attitude control power system performs three-channel auxiliary control of the aircraft in a high-altitude rarefied flow environment. The attitude control equipment is generally installed at the bottom of the aircraft to improve control efficiency.

[0003] Since the attitude control power system of the gliding aircraft only needs to work in the rarefied flow environment at high altitude, its working time is relatively short. When the gliding altitude of the aircraft decreases and the atmospheric density increases, the efficiency of the air rudder increases, and the aircraft can completely rely on the air rudder for control. At this time, the attitude control equipment will stop working, and the weight of its system will become waste weight for the aircraft, affecting the flight performance and range of the aircraft.

[0004] In order to ensure the flight performance of the glider and increase the range of the aircraft, it is necessary to discard the attitude control power system equipment that has completed its mission to reduce the flight weight of the aircraft. Therefore, it is very necessary to design a detachable attitude control power system installation structure. Summary of the invention

[0005] An embodiment of the present invention provides a detachable attitude control power control system, which is used to separate the attitude control power system from the aircraft after the attitude control power system stops working, thereby reducing the flight weight of the aircraft, ensuring the flight performance of the gliding aircraft, and increasing the range of the aircraft.

[0006] The technical solution adopted by the present invention is:

[0007] The embodiment of the present invention provides a detachable attitude control power control system, comprising: a controller, an altitude sensor, a separation explosion device, a plurality of separation compression springs and an attitude control device mounting seat; the controller and the altitude sensor are arranged in a control cabin of an aircraft, the separation explosion device comprises a detonator, a detonating cord, explosives and a separation bolt, the explosives are arranged in the separation bolts and connected to the detonator through the detonating cord; the controller is respectively connected to the altitude sensor and the detonator for communication, the altitude sensor is used to detect the altitude of the aircraft from the take-off ground and send the detected altitude value to the controller; one end of the separation compression spring is connected to the control cabin The first end of the attitude control device is in contact with the sealing cylinder on the attitude control device mounting seat, and the other end is fixed on the top of the attitude control device mounting seat and is located between the sealing cylinder and the attitude control device mounting seat in a compressed state; an installation space for installing the attitude control device is formed inside the attitude control device mounting seat, and the bottom of the attitude control device mounting seat is connected to the sealing cylinder through the separation bolt; wherein, when the received height value is greater than the preset height threshold, the controller controls the detonator to perform an ignition operation to ignite the explosive, thereby blowing off the separation bolt at the connecting surface between the attitude control device mounting seat and the sealing cylinder, so that the attitude control device mounting seat and the sealing cylinder are separated under the elastic force of the separation compression spring.

[0008] The detachable attitude control power control system provided in the embodiment of the present invention can separate the attitude control power system from the aircraft after the attitude control power system stops working, thereby reducing the flight weight of the aircraft, ensuring the flight performance of the gliding aircraft, and increasing the range of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] Figure 1 A partial schematic diagram of a detachable attitude control power control system provided by an embodiment of the present invention;

[0010] Figure 2 A schematic diagram of an attitude control power system separated from an aircraft provided in an embodiment of the present invention;

[0011] Figure 3 Schematic diagram of the aircraft control cabin after being separated from the attitude control power system. DETAILED DESCRIPTION

[0012] In order to make the technical problems, technical solutions and advantages to be solved by the present invention clearer,

[0013] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.

[0014] The technical idea of ​​the present invention is to provide a detachable attitude control power control system, which is used to separate the attitude control power system and the aircraft after the attitude control power system stops working, thereby reducing the flight weight of the aircraft, ensuring the flight performance of the gliding aircraft, and increasing the range of the aircraft.

[0015] like Figures 1 to 3 As shown, an embodiment of the present invention provides a detachable attitude control power control system, including: a controller (not shown), an altitude sensor (not shown), a separation explosion device, a plurality of separation compression springs 1 and an attitude control device mounting seat.

[0016] Among them, in the embodiment of the present invention, the controller and the altitude sensor are arranged in the control cabin 8 of the aircraft, and the separation explosion device includes a detonator (not shown), a detonating cord 14, an explosive (not shown) and a separation bolt 13. The explosive is arranged in the separation bolt and connected to the detonator through the detonating cord 14; the controller is respectively connected to the altitude sensor and the detonator in communication, and the altitude sensor is used to detect the height of the aircraft from the take-off ground and send the detected altitude value to the controller. The controller can be any device with a control function, for example, a single chip microcomputer. The altitude sensor can be an existing product.

[0017] In the embodiment of the present invention, an installation space for the installation of the attitude control device 9 is formed inside the attitude control device mounting seat, and the bottom of the attitude control device mounting seat is connected to the sealing cylinder 7 provided on the control cabin 8 through the separation bolt 13. Specifically, the attitude control device mounting seat may include a compression spring mounting plate 2, a plurality of upper support rods 4, an attitude control device mounting plate 3, a plurality of lower support rods 5, and a bottom shielding cylinder 6 connected in sequence. The compression spring mounting plate 2, the upper support rod 4, the attitude control device mounting plate 3, the lower support rod 5 and the bottom shielding cylinder 6 are connected in sequence to form an installation space for the installation of the attitude control device, and the attitude control device 9 is installed on the attitude control device mounting plate 3. The attitude control device 9 is arranged on the attitude control device mounting plate 3. The bottom shielding cylinder 6 and the sealing cylinder 7 are connected to the control cabin 8 through the separation bolt 13. The bottom shielding cylinder 6 is also provided with a first separation socket 10 and an attitude control engine 11, and the first separation socket 10 is used for electrical connection between the attitude control device 9 and the carrier (not shown).

[0018] In an embodiment of the present invention, the separation compression spring 1, the compression spring mounting plate 2, the upper support rod 4, the attitude control device 9, the attitude control device mounting plate 3, the lower support rod 5, the bottom shielding tube 6, the attitude control engine 11 and the first separation socket 10 can constitute an attitude control power system.

[0019] Furthermore, in the embodiment of the present invention, the separation compression spring 1 is used to provide a driving force for the separation of the attitude control power system from the aircraft, and a plurality of separation compression springs 1 can be provided according to actual needs. Before the attitude control power system is separated from the aircraft, the separation compression spring 1 is located between the compression spring mounting plate 2 and the sealing cylinder 7 in a compressed state, one end of the separation compression spring 1 presses against the sealing cylinder 7, that is, elastically contacts the sealing cylinder 7, and the other end is fixed to the compression spring mounting plate 2, for example, it can be fixed to the compression spring mounting plate 2 by welding. In the embodiment of the present invention, the number, size and stiffness coefficient of the separation compression spring 1 can be specifically designed according to the mass, separation posture, separation speed, spatial layout requirements, etc. of the attitude control power system.

[0020] Furthermore, in an embodiment of the present invention, the compression spring mounting plate 2 may be a circular plate, and the compression spring mounting plate 2 is used to fix the separation compression spring 1 to ensure that the separation compression spring 1 can be separated from the aircraft together with the attitude control power system after the attitude control power system is separated from the aircraft.

[0021] In the embodiment of the present invention, Figure 1 and Figure 2 As shown, the attitude control device mounting plate 3 may be a circular plate with a mounting hole formed in the middle, and the attitude control device 9 is mounted in the mounting hole. In the embodiment of the present invention, the attitude control device 9 may be an existing product, and may be fixed to the attitude control device mounting plate 3 by, for example, bolts. By fixing the attitude control device 9 to the attitude control device mounting plate 3, compared with the existing method of directly fixing the attitude control device 9 to the control cabin 8, the attitude control device 9 can be separated from the control cabin as the bottom shielding tube and the sealing tube are separated. The specific shape of the attitude control device mounting plate 3 may be optimized and designed according to the size and layout of the attitude control device product.

[0022] In the embodiment of the present invention, a plurality of upper support rods 4 are arranged at intervals between the compression spring mounting plate 2 and the attitude control device mounting plate 3, and are used to connect and fix the compression spring mounting plate 2 and the attitude control device mounting plate 3 together, for example, they can be connected to the compression spring mounting plate 2 and the attitude control device mounting plate 3 by bolts or other connection methods. The upper support rods 4 can be evenly arranged along the circumferential direction of the attitude control device mounting plate 3, and the number and size of the upper support rods can be designed according to the mass of the attitude control device and the installation space, and the preferred number can be 10 to 40, so as to achieve a weight reduction effect while providing sufficient support force.

[0023] In the embodiment of the present invention, a plurality of lower support rods 5 are arranged at intervals between the attitude control device mounting plate 3 and the bottom shielding tube 6, and are used to connect and fix the attitude control device mounting plate 3 and the bottom shielding tube 6 together, for example, they can be connected to the attitude control device mounting plate 3 and the bottom shielding tube 6 by bolts or other connection methods. The lower support rods 5 can be evenly arranged along the circumferential direction of the attitude control device mounting plate 3, and the number and size of the lower support rods can be designed according to the mass of the attitude control device and the installation space, and the preferred number can be 10 to 40, so as to achieve a weight reduction effect while providing sufficient support force.

[0024] In the embodiment of the present invention, since the attitude control device mounting plate 3 is respectively connected to the compression spring mounting plate and the bottom shielding cylinder by using support rods to form an installation space for the attitude control device, that is, an attitude control cabin, compared with forming the attitude control cabin by a closed cylinder, the overall mass of the attitude control power system can be reduced, so that the attitude control power system can be more easily separated from the aircraft under the action of the elastic force of the separation compression spring.

[0025] Furthermore, in the embodiment of the present invention, the bottom shielding cylinder 6 and the sealing cylinder 7 are formed to fit together to form a receiving space, and the separation compression spring 1, the compression spring mounting plate 2, the upper support rod 4, the attitude control device mounting plate 3 with the attitude control device mounted thereon, and the lower support rod 5 are arranged in the receiving space. Figures 1 to 3 As shown, the bottom shield 6 may include a cylindrical first cylindrical portion 61 with an opening at the upper end and a first connecting portion 62 extending in the circumferential direction of the opening of the first cylindrical portion. The attitude control engine 11 and a plurality of first separation sockets 10 are arranged on the first cylindrical portion 61. In an embodiment of the present invention, the plurality of first separation sockets 10 are used for electrical connection between the attitude control device and the carrier (not shown), and are in a plug-in state before the attitude control cabin is separated from the carrier. When the attitude control power system is separated from the control cabin, it only serves to separate together with the bottom shield. The first separation socket 10 may be an existing product for realizing electrical connection between the attitude control device 9 and the carrier, and the specific number may be set according to actual needs. The attitude control engine 11 is used for the nozzle to be in a working state before the attitude control cabin is separated from the carrier, providing power and attitude control for the carrier, and is separated together with the attitude control power system when the attitude control system is separated.

[0026] In the embodiment of the present invention, the sealing tube 7 is arranged at the rear end of the control cabin 8. When the attitude control equipment assembly is separated from the aircraft, the sealing tube 7 is used to prevent the external heat flow from entering the interior of the aircraft cabin. Figure 1 As shown, an opening is formed at the rear end of the control cabin 8, and the sealing tube 7 extends into the opening and is fixedly connected to both ends of the opening, for example, by welding.

[0027] In addition, the sealing cylinder 7 is provided with a plurality of second separation sockets 12 for electrical connection between the aircraft and the attitude control device as required, and is used for electrical connection between the aircraft and the attitude control device. Figure 1 As shown, the sealing cylinder 7 may include a cylindrical second cylindrical portion 71 with an opening at the lower end and a second connecting portion 72 extending in the circumferential direction of the opening of the second cylindrical portion. The second cylindrical portion 71 extends into the interior of the control cabin 8 and is provided with a second separation socket 12 for electrical connection between the attitude control device and the aircraft. The first connecting portion 61 and the second connecting portion 71 are connected by a separation bolt 13. Before the attitude control power system is separated, the second separation socket 12 connects the control cabin and the attitude control power system. When the attitude control power system is separated from the control cabin, due to the force of the separation compression spring 1, the second separation socket 12 will be separated from the attitude control power system. The second separation socket 12 can be an existing product for realizing electrical connection between the attitude control device 9 and the aircraft, and the specific number can be set according to actual needs.

[0028] In the embodiment of the present invention, there may be multiple separation explosive devices, and a suitable number of separation explosive devices may be provided according to actual needs. In this way, the detonators of the multiple separation explosive devices are all connected to the controller, and corresponding operations are performed based on the control instructions of the controller. The controller may send ignition operation instructions to all detonators at the same time, or send ignition operation instructions to the detonators in sequence according to a preset order. Preferably, the ignition operation instructions are sent at the same time, so as to achieve the separation of the attitude control power system and the aircraft as soon as possible.

[0029] In the embodiment of the present invention, the detonating cord 14 is used to control the automatic disconnection of the separation bolt 13. When the internal explosive of the detonating cord 14 is ignited by the detonator, it will be transferred to the separation bolt 13 and explode at the separation surface between the sealing tube 7 and the bottom shield 6.

[0030] In the embodiment of the present invention, the separation bolt 13 may be an existing explosive bolt, for example, it may include a first connection section and a second connection section connected to each other, a through hole is formed in the middle of the first connection section, and the second connection section is inserted into the through hole from the bottom of the through hole, for example, it may be fixed in the through hole by interference fit. Explosives are arranged in the through hole. When the sealing cylinder and the bottom shielding cylinder are connected, the first connection section extends into the interior of the control cabin and is connected to the nut, and the second connection section extends out of the control cabin and is connected to the nut, so as to achieve a fixed connection between the sealing cylinder and the bottom shielding cylinder. In addition, a weakening groove is formed at the connection position of the first connection section and the second connection section, and the weakening groove may be arranged at a position corresponding to the connection surface (hereinafter also referred to as the separation surface) of the sealing cylinder and the bottom shielding cylinder, so that it can be more easily exploded by the explosives. In order to make the separation bolt explode just at the separation surface between the sealing cylinder and the bottom shielding cylinder, it can be achieved by controlling the amount of explosives, that is, the amount of explosives placed in the separation bolt just enables the separation bolt to explode at the separation surface between the sealing cylinder and the bottom shielding cylinder. To avoid redundant description, the present invention omits the specific introduction of the separation bolt.

[0031] In addition, in order to prevent other electrical components in the control cabin 8 from being damaged after the explosion, a separation bolt protection device may be provided, for example, the explosive bolt buffer device disclosed in patent document CN108033038B. Before the attitude control power system is separated from the aircraft, the separation bolt 13 has the same function as the ordinary bolt, mainly serving the function of connection and fixing. When the attitude control power system is separated, the separation bolt 13 is automatically disconnected from the separation surface between the sealing tube 7 and the bottom shielding tube 6 under the action of the explosive, so that the entire attitude control power system is separated from the control cabin above.

[0032] In an embodiment of the present invention, while the aircraft continues to fly after separating from the carrier, the altitude sensor will perform real-time detection of the flight altitude of the aircraft. If the altitude value received by the controller from the altitude sensor is greater than a preset altitude threshold, for example, greater than 200 km, all detonators will be controlled to perform ignition operations simultaneously or in a preset order to ignite the explosives through the detonating cord, thereby causing all separation bolts to automatically disconnect from the separation surface between the sealing cylinder and the bottom shielding cylinder. After the separation bolts are blown off, the bottom shielding cylinder and the sealing cylinder will be separated, and then the separation compression spring in a compressed state will separate from the sealing cylinder, thereby generating an elastic force downward, causing the bottom shielding cylinder and the sealing cylinder to move downward under the elastic force of the separation compression spring. At this time, the second separation socket will separate from the attitude control device, thereby realizing the separation of the attitude control power system from the aircraft, that is, the attitude control power system can be discarded with the cooperation of the separation compression spring and the separation explosive device, thereby reducing the flight weight of the aircraft, ensuring the flight performance of the aircraft, and increasing the range of the aircraft.

[0033] The above-described embodiments are only specific implementations of the present invention, which are used to illustrate the technical solutions of the present invention, rather than to limit them. The protection scope of the present invention is not limited thereto. Although the present invention is described in detail with reference to the above-described embodiments, it should be understood by those skilled in the art that any person familiar with the technical field can still modify the technical solutions recorded in the above-described embodiments within the technical scope disclosed by the present invention, or can easily think of changes, or perform equivalent replacements on some of the technical features thereof; and these modifications, changes or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention, and should all be included in the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims

1. A detachable attitude control power control system, characterized in that: include: A controller, an altitude sensor, a separation explosive device, a plurality of separation compression springs and an attitude control device mounting seat; the controller and the altitude sensor are arranged in a control cabin of an aircraft, the separation explosive device comprises a detonator, a detonating cord, explosives and a separation bolt, the explosives are arranged in the separation bolts and connected to the detonator through the detonating cord; the controller is respectively connected to the altitude sensor and the detonator for communication, the altitude sensor is used to detect the altitude of the aircraft from the take-off ground and send the detected altitude value to the controller; One end of the separation compression spring contacts the sealing cylinder on the control cabin, and the other end is fixed to the top of the attitude control device mounting seat and is located between the sealing cylinder and the attitude control device mounting seat in a compressed state; An installation space for installing the attitude control device is formed inside the attitude control device installation seat, and the bottom of the attitude control device installation seat is connected to the sealing cylinder through the separation bolt; When the received height value is greater than a preset height threshold, the controller controls the detonator to perform an ignition operation to ignite the explosive, thereby blowing off the separation bolt at the connecting surface between the attitude control device mounting seat and the sealing cylinder, so that the attitude control device mounting seat and the sealing cylinder are separated under the elastic force of the separation compression spring.

2. The detachable attitude control power control system according to claim 1 is characterized in that: The attitude control device mounting seat comprises a compression spring mounting plate, a plurality of upper support rods, an attitude control device mounting plate, a plurality of lower support rods, and a bottom shielding tube connected in sequence; The attitude control device is arranged on the attitude control device mounting plate; The bottom shielding cylinder and the sealing cylinder are connected by the separation bolts.

3. The detachable attitude control power control system according to claim 2 is characterized in that: Includes multiple discrete explosive devices; When the received altitude value is greater than a preset altitude threshold, the controller controls all detonators to perform ignition operations simultaneously or in a preset order.

4. The detachable attitude control power control system according to claim 3 is characterized in that: The bottom shielding tube and the sealing tube cooperate with each other to form a containing space, and the separation compression spring, the compression spring mounting plate, the upper support rod, the attitude control device mounting plate on which the attitude control device is mounted, and the lower support rod are arranged in the containing space.

5. The detachable attitude control power control system according to claim 4, characterized in that: The bottom shielding cylinder comprises a first cylindrical portion with an opening at the upper end and a first connecting portion extending outwardly in the circumferential direction of the opening of the first cylindrical portion; The sealing cylinder includes a second cylindrical portion with an opening at the lower end and a second connecting portion extending outwardly along the circumferential direction of the opening of the second cylindrical portion.

6. The detachable attitude control power control system according to claim 5, characterized in that: The first cylindrical portion is connected to the lower support rod, the second cylindrical portion extends into the control cabin, and the first connecting portion and the second connecting portion are connected by the separation bolt.

7. The detachable attitude control power control system according to claim 6, characterized in that: The second cylindrical portion is provided with a second separation socket for electrical connection between the attitude control device and the aircraft.

8. The detachable attitude control power control system according to claim 2, characterized in that: The separation compression spring is welded on the compression spring mounting plate.

9. The detachable attitude control power control system according to claim 2, characterized in that: The attitude control device mounting plate is a circular plate with a mounting hole formed in the middle, and the attitude control device is mounted in the mounting hole.

10. The detachable attitude control power control system according to claim 1, characterized in that: The sealing cylinder is arranged at the rear end of the control cabin.

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