Separation system and method for realizing separation of booster and aircraft

Abstract

The invention provides a separation system and method for achieving separation of a booster and an aircraft. The separation system comprises a control system, a separation firer device, a reverse thrust power device, a separation spring device and a separation double-hinge device. The control system is arranged on the aircraft, and the reverse thrust power device is arranged on the booster; the aircraft is connected with the booster through the separation spring device and the separation double-hinge device; and the separation pyrotechnic device is arranged between the aircraft and the booster and is used for unlocking the aircraft and the booster. The invention relates to a separation control system with separation robustness, provides a separation double-hinge device, not only can fully utilize the robustness of a spring separation device, but also can overcome the consecutive disturbance caused by the difference of two-stage aerodynamic characteristics, and particularly has advantages for the separation of aircrafts under the condition of large dynamic pressure disturbance.

Description

Technical Field

[0001] The present invention relates to the technical field of two-stage separation of aircraft, and in particular to a separation system and method for realizing separation of a booster and an aircraft, and in particular to a separation system for suppressing separation disturbance to realize stable separation of a booster and an aircraft. Background Art

[0002] In order to increase the speed of the aircraft, improve the overall performance and increase the carrying capacity, after the aircraft takes off to a certain height, the fuel-depleted carrier needs to be jettisoned from the aircraft body to reduce the subsequent flight weight. Traditional interstage separation includes cold separation and hot separation. Cold separation means that the connection between the aircraft and the booster is unlocked first, and then the booster is braked and decelerated (generally achieved by the reverse thrust engine). After the two sub-stages are separated by a certain distance, the main stage is ignited and started to push the main stage to continue flying. Hot separation means that the aircraft engine is ignited and started first, and then the connection between the aircraft and the booster is unlocked, relying on the gas flow of the aircraft tail nozzle to flush the sub-stage below to generate a separation force, pushing the aircraft and the booster to separate during flight. The cold separation process takes a long time, resulting in a long time of aircraft out of control, which has a greater impact on the stability of subsequent flight; during the hot separation process, the carrier fuel tank and the interstage are impacted by high-temperature and high-pressure gas, requiring additional protective measures, which is not conducive to reducing the weight of the aircraft.

[0003] For the separation of aircraft under high dynamic pressure and strong disturbance, especially the separation of active stage, the separation window is narrow and the thrust of descent stage is unstable, which requires the separation system to have the ability to overcome disturbance and have certain stability. Traditional hot separation and cold separation can no longer fully meet the needs. It is necessary to take into account the advantages of both separation methods through timing design and design a new separation mechanism to adapt to the separation environment.

[0004] The patent document with the publication number of CN107902111B discloses a separation device for a booster of an aircraft, comprising an aircraft body and a booster arranged at the rear of the aircraft body, a separation mounting seat being provided at the front end of the booster, a separator being installed at the front end of the separation mounting seat, a connecting column being provided at the front end of the separator, four card plates being evenly arranged on the side of the connecting column along the circumferential direction, a connecting hole being provided at the rear end of the aircraft body, four card slots corresponding to the card plates being provided in the connecting hole, a receiving chamber being provided at the front end of the connecting hole, a rotating shaft being provided at the center of the front end of the connecting column, a worm gear being provided on the rotating shaft, a worm being provided in the receiving chamber through a worm frame, the worm being meshed with the worm gear, a worm motor being provided at one end of the worm, a separation cylinder being provided in the receiving chamber, and the output end of the separation cylinder being directly opposite to the center of the rotating shaft. However, the patent document still has the defect of not being able to overcome disturbances. Summary of the invention

[0005] In view of the defects in the prior art, an object of the present invention is to provide a separation system and method for achieving separation of a booster and an aircraft.

[0006] A separation system for separating a booster and an aircraft according to the present invention comprises: a control system, a separation pyrotechnic device, a reverse thrust device, a separation spring device and a separation double hinge device;

[0007] The control system is arranged on the aircraft, and the reverse thrust device is arranged on the booster;

[0008] The aircraft is connected to the booster via the separation spring device and the separation double hinge device;

[0009] The separation pyrotechnic device is arranged between the aircraft and the booster, and is used for unlocking the aircraft and the booster.

[0010] Preferably, the split double hinge device comprises a first hinge structure and a second hinge structure;

[0011] The second hinge structure is arranged at the head of the booster, and the first hinge structure and the second hinge structure are connected by the separation spring device;

[0012] The first hinge structure is pushed against the tail of the aircraft by the elastic force of the separation spring device.

[0013] Preferably, the first articulated structure is arranged on the central axis of the aircraft, and the second articulated structure is arranged on the central axis of the booster.

[0014] Preferably, the separation spring device comprises a first sleeve structure, a second sleeve structure and a separation spring;

[0015] The second sleeve structure is slidably disposed in the first sleeve structure, one end of the separation spring is connected to the inner bottom wall of the second sleeve structure, and the other end of the separation spring is connected to the inner bottom wall of the first sleeve structure;

[0016] The outer bottom wall of the first sleeve structure is connected to the first hinge structure, and the outer bottom wall of the second sleeve structure is connected to the second hinge structure.

[0017] Preferably, the first sleeve structure is provided with a first limiting structure, and the second sleeve structure is provided with a second limiting structure, and the first limiting structure and the second limiting structure are used to limit the second limiting structure from separating from the first sleeve structure.

[0018] Preferably, a third limiting structure is provided on the second sleeve structure, and the third limiting structure is used to abut against the opening end of the first sleeve structure.

[0019] Preferably, the separation pyrotechnic device is a separation cable, a separation surface is provided between the aircraft and the booster, and the separation cable is provided on the separation surface.

[0020] Preferably, the booster is provided with an interstage cabin, and the separation pyrotechnic device, the separation spring device and the separation double-hinged device are installed in the interstage cabin.

[0021] Preferably, a servo cabin is provided on both sides of the nozzle of the booster, and the reverse thrust device is arranged in the servo cabin.

[0022] The present invention also provides a separation method for separating a booster from an aircraft. The separation system for separating a booster from an aircraft comprises the following steps:

[0023] Step S1: after the control system determines whether the separation condition is met, if yes, an ignition command is issued to the reverse thrust device, otherwise, the separation action is not performed;

[0024] Step S2: after issuing an ignition command, building up pressure through the reverse thrust device, and after building up pressure, issuing an ignition command to the separation pyrotechnic device through the control system;

[0025] Step S3: After the separation pyrotechnic device is unlocked, the reverse thrust device provides the booster with a thrust in the opposite direction of the movement, and the separation spring device pushes the aircraft forward and the booster backward, so that the distance between the aircraft and the booster is gradually increased;

[0026] Step S4: determining whether the aircraft meets the start-up control conditions through the control system, and if so, starting the control of the aircraft to enter the next flight phase.

[0027] Compared with the prior art, the present invention has the following beneficial effects:

[0028] 1. The present invention solves the problem of active section separation with narrow separation window, large dynamic pressure and strong disturbance, which can significantly suppress separation disturbance, enhance the robustness of the separation system and realize stable start-up control of the main stage;

[0029] 2. The present invention proposes for the first time a separation system having both a separation spring and a separation double-hinged device, which innovatively utilizes the separation double-hinged device to eliminate the attitude disturbance between the aircraft and the carrier, and can utilize the stability of the separation spring device and suppress the attitude disturbance caused by the carrier to the aircraft;

[0030] 3. The present invention utilizes a tight timing design, taking into account the advantages of both hot separation and cold separation methods, and can achieve rapid and stable separation, ensuring that the aircraft has stable start-up control conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0032] Figure 1 A schematic diagram of the separation system for separating the booster and the vehicle;

[0033] Figure 2 It is a structural schematic diagram of a separation spring device and a separation double hinge device;

[0034] Figure 3 is a schematic diagram of the separation sequence;

[0035] Figure 4 A structural diagram showing the installation form of the cutting rope;

[0036] Figure 5 A structural diagram showing the relative motion of the spacecraft and booster stages.

[0037] The figure shows:

[0038] Control system 1 Second articulated structure 402

[0039] Reverse thrust device 2 Aircraft 5

[0040] Separation spring device 3 Booster 6

[0041] First sleeve structure 301 Separation cable 601

[0042] First limiting structure 3011 Separation surface 602

[0043] Second sleeve structure 302 interstage compartment 7

[0044] Second limiting structure 3021 nozzle 8

[0045] The third limiting structure 3022 servo cabin 9

[0046] Separation spring 303 Pressure ring 10

[0047] Separation double hinge device 4 Shaped explosive rope 11

[0048] First hinge structure 401 Separation zone housing 12 DETAILED DESCRIPTION

[0049] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0050] Embodiment 1:

[0051] like Figures 1 to 5 As shown, this embodiment provides a separation system for realizing separation of a booster and an aircraft, comprising: a control system 1, a separation pyrotechnic device, a reverse thrust device 2, a separation spring device 3 and a separation double-hinged device 4; the control system 1 is arranged on the aircraft 5, and the reverse thrust device 2 is arranged on the booster 6; the aircraft 5 is connected to the booster 6 via the separation spring device 3 and the separation double-hinged device 4; the separation pyrotechnic device is arranged between the aircraft 5 and the booster 6, and is used to unlock the aircraft 5 and the booster 6.

[0052] After the control system 1 determines that the separation conditions are met, it sends an ignition command to the reverse thrust device 2. After the reverse thrust device 2 builds up pressure, the control system 1 sends an ignition command to the separation pyrotechnic device. The separation spring device 3, the separation double-comparison device 4 and the reverse thrust device 2 act simultaneously to increase the distance between the booster 6 and the aircraft 5.

[0053] A servo cabin 9 is respectively arranged on both sides of the nozzle 8 of the booster 6 , and the reverse thrust device 2 is arranged in the servo cabin 9 .

[0054] The separation double hinge device 4 includes a first hinge structure 401 and a second hinge structure 402; the second hinge structure 402 is arranged at the head of the booster 6, and the first hinge structure 401 and the second hinge structure 402 are connected by a separation spring device 3; the first hinge structure 401 and the large plate are pushed against the tail of the aircraft 5 by the elastic force of the separation spring device 3. The first hinge structure 401 is arranged on the central axis of the aircraft 5, and the second hinge structure 402 is arranged on the central axis of the booster 6. Figure 1 As shown, A is the central axis of the aircraft 5, and B is the central axis of the booster 6.

[0055] The separation spring device 3 includes a first sleeve structure 301, a second sleeve structure 302 and a separation spring 303; the second sleeve structure 302 is slidably arranged in the first sleeve structure 301, one end of the separation spring 303 is connected to the inner bottom wall of the second sleeve structure 302, and the other end of the separation spring 303 is connected to the inner bottom wall of the first sleeve structure 301; the outer bottom wall of the first sleeve structure 301 is connected to the first hinge structure 401, and the outer bottom wall of the second sleeve structure 302 is connected to the second hinge structure 402.

[0056] The separation pyrotechnic device is a separation cable 601, a separation surface 602 is provided between the aircraft 5 and the booster 6, and the separation cable 601 is arranged on the separation surface 602. The booster 6 is provided with an interstage compartment 7, and the separation pyrotechnic device, the separation spring device 3 and the separation double hinge device 4 are arranged in the interstage compartment 7. The first sleeve structure 301 is provided with a first limiting structure 3011, and the second sleeve structure 302 is provided with a second limiting structure 3021, and the first limiting structure 3011 and the second limiting structure 3021 are used to limit the second limiting structure 3021 from separating from the first sleeve structure 301. The second sleeve structure 302 is provided with a third limiting structure 3022, and the third limiting structure 3022 is used to abut against the open end of the first sleeve structure 301.

[0057] The separation pyrotechnic device can use a cutting cord or an explosive bolt, which are respectively line cutting and point cutting. The present embodiment uses a separation cord. The cutting cord solution is to pre-lay a detonating cord at the place where a weakening groove is opened, i.e., the separation surface. After the aircraft enters the separation sequence, the detonating cord is ignited, and the impulse generated by the pyrotechnic product cuts off the separation surface, and the two stages are unlocked accordingly. Figure 4 As shown, a is the state before separation, b is the state after separation, and the shaped charge rope 11 is fixed to the separation zone shell 12 by the pressure ring 10.

[0058] This embodiment also provides a separation method for separating a booster from an aircraft, based on the above separation system for separating a booster from an aircraft, comprising the following steps:

[0059] Step S1: After the control system 1 determines whether the separation condition is met, if yes, an ignition command is issued to the reverse thrust device 2, otherwise, the separation action is not performed;

[0060] Step S2: After issuing the ignition command, the pressure is established through the reverse thrust device 2. After the pressure is established, the ignition command is issued to the separation pyrotechnic device through the control system 1;

[0061] Step S3: After the separation pyrotechnic device (separation cable) is unlocked, the anti-thrust device 2 provides a thrust to the booster 6 in the opposite direction of the movement, and the separation spring device 3 pushes the aircraft 5 forward and pushes the booster 6 backward at the same time;

[0062] Step S4: As the distance between the aircraft 5 and the booster 6 is pulled apart, the spring mechanism can be extended and retracted, and at the same time, the main stage, the spring and the carrier can rotate relative to each other. The force of the spring is transmitted to the main stage through the hinge and the large plate. Figure 5 As shown. The relative rotation constraint between the two stages is released, the angular velocity of the carrier will not be transmitted to the main stage, and the angular velocity of the main stage will not interfere with the carrier;

[0063] Step S5: As the separation spring device 3 reaches the action distance and the fuel combustion of the anti-thrust device 2 is completed, the relative distance between the two stages is gradually increased;

[0064] Step S6: After the control system 1 determines whether the aircraft 5 control start conditions are met, the aircraft 5 starts control and enters the next flight phase.

[0065] This embodiment proposes for the first time a separation control system that suppresses separation disturbances and has separation robustness, and innovatively proposes a separation double-hinged device, which can not only fully utilize the robustness of the spring separation device, but also overcome the involved disturbances caused by the difference in the two-stage aerodynamic characteristics, especially for the separation of aircraft in the case of large dynamic pressure disturbances.

[0066] Embodiment 2:

[0067] Those skilled in the art may understand this embodiment as a more specific description of Embodiment 1.

[0068] like Figure 1 As shown, this embodiment provides a separation system for suppressing separation disturbance and achieving stable separation of booster and aircraft, including a control computer for real-time resolution of aircraft attitude, a separation pyrotechnic device, a reverse thrust device, a separation spring device and a separation double hinge device. The devices are connected to each other through the electrical interface and mechanical interface of the aircraft to form a separation system, so as to achieve stable separation of the aircraft and booster.

[0069] 1) Control computer 1, obtains and processes aircraft information, gives separation ignition instructions according to the time sequence, and determines aircraft attitude information and electrical plug-in information in real time, and gives aircraft start-up control instructions;

[0070] 2) Separation pyrotechnic device 2, used to release the connection between the aircraft and the booster cabin, so that the postures of the aircraft and the booster are no longer the same after detonation;

[0071] 3) Reverse thrust device 3, which is used to offset the residual thrust of the booster and provide reverse thrust to achieve separation of the aircraft and the booster when the aircraft and the booster cabin are disconnected;

[0072] 4) The separation spring device and the separation double-hinged device 4, which are composed of a separation mechanism located in the interstage cabin. When the cabins of the aircraft and the booster are disconnected, the two work together to provide a reverse force to the aircraft and the booster at the same time, and to overcome the disturbance of the booster attitude divergence to the main stage.

[0073] like Figure 2 As shown, the separation spring device and the separation double-hinge device are connected to the front and rear bodies via hinges.

[0074] like Figure 3As shown, through the separation timing design, hot separation and cold separation are taken into consideration to achieve two-stage rapid and smooth separation.

[0075] The aircraft enters the separation window; after the control computer determines that the separation conditions are met, it sends an ignition command to the reverse thrust device; after the reverse thrust device builds up pressure, the control computer gives an ignition command to the separation pyrotechnic device; the separation pyrotechnic device detonates, and the aircraft and the carrier are disconnected; the separation spring device, the separation double-hinged device, and the reverse thrust device act simultaneously, and the booster and the aircraft are pulled apart; the control computer switches the autopilot to start control of the aircraft after real-time calculation, sampling the electrical separation signal or determining that the attitude and attitude angular velocity meet the start-up control conditions.

[0076] The separation sequence is closely linked, and the ignition command of the separation pyrotechnic device is executed after reverse pressure building; after the two stages are disconnected, the electrical interlocking signal or the attitude and attitude angular velocity discrimination conditions are used as the main stage start control mark.

[0077] A separation spring device and a separation double hinge device are adopted at the same time.

[0078] This embodiment solves the problem that when using the traditional separation method, the aircraft separation stability is poor under large dynamic pressure and strong disturbance conditions, and the main stage is easy to diverge after starting control.

[0079] The present invention proposes for the first time a separation system with both a separation spring and a separation double-hinged device, and innovatively utilizes the separation double-hinged device to eliminate the attitude disturbance between the aircraft and the carrier. It can not only utilize the stability of the separation spring device, but also suppress the attitude disturbance caused by the carrier to the aircraft. At the same time, it utilizes a tight timing design and takes into account the advantages of hot separation and cold separation methods, so as to achieve rapid and stable separation and ensure that the aircraft has smooth start-up control conditions.

[0080] In the description of the present application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0081] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A separation system for separating a booster from an aircraft, characterized in that: include: A control system (1), a separation pyrotechnic device, a reverse thrust device (2), a separation spring device (3) and a separation double hinge device (4); The control system (1) is arranged on the aircraft (5), and the reverse thrust device (2) is arranged on the booster (6); The aircraft (5) is connected to the booster (6) via the separation spring device (3) and the separation double hinge device (4); The separation pyrotechnic device is arranged between the aircraft (5) and the booster (6) and is used to unlock the aircraft (5) and the booster (6).

2. The separation system for separating a booster and an aircraft according to claim 1, characterized in that: The separated double hinge device (4) comprises a first hinge structure (401) and a second hinge structure (402); The second hinge structure (402) is arranged at the head of the booster (6), and the first hinge structure (401) and the second hinge structure (402) are connected via the separation spring device (3); The first hinged structure (401) is pushed against the tail of the aircraft (5) by the elastic force of the separation spring device (3).

3. The separation system for separating a booster from an aircraft according to claim 2, characterized in that: The first hinged structure (401) is arranged on the central axis of the aircraft (5), and the second hinged structure (402) is arranged on the central axis of the booster (6).

4. The separation system for separating a booster from an aircraft according to claim 2, characterized in that: The separation spring device (3) comprises a first sleeve structure (301), a second sleeve structure (302) and a separation spring (303); The second sleeve structure (302) is slidably disposed in the first sleeve structure (301), one end of the separation spring (303) is connected to the inner bottom wall of the second sleeve structure (302), and the other end of the separation spring (303) is connected to the inner bottom wall of the first sleeve structure (301); The outer bottom wall of the first sleeve structure (301) is connected to the first hinge structure (401), and the outer bottom wall of the second sleeve structure (302) is connected to the second hinge structure (402).

5. The separation system for separating a booster from an aircraft according to claim 4, characterized in that: The first sleeve structure (301) is provided with a first limiting structure (3011), and the second sleeve structure (302) is provided with a second limiting structure (3021), and the first limiting structure (3011) and the second limiting structure (3021) are used to limit the second limiting structure (3021) from separating from the first sleeve structure (301).

6. The separation system for separating a booster from an aircraft according to claim 4, characterized in that: The second sleeve structure (302) is provided with a third limiting structure (3022), and the third limiting structure (3022) is used to abut against the opening end of the first sleeve structure (301).

7. The separation system for separating a booster from an aircraft according to claim 2, characterized in that: The separation pyrotechnic device is a separation rope (601), a separation surface (602) is provided between the aircraft (5) and the booster (6), and the separation rope (601) is provided on the separation surface (602).

8. The separation system for separating a booster from an aircraft according to claim 7, characterized in that: The booster (6) is provided with an interstage cabin (7), and the separation pyrotechnic device, the separation spring device (3) and the separation double hinge device (4) are arranged in the interstage cabin (7).

9. The separation system for achieving separation of a booster and an aircraft according to claim 1, characterized in that: A servo cabin (9) is respectively arranged on both sides of the nozzle (8) on the booster (6), and the reverse thrust device (2) is arranged in the servo cabin (9).

10. A separation method for separating a booster and an aircraft, characterized in that: The separation system for realizing separation of a booster and an aircraft according to any one of claims 1 to 9 comprises the following steps: Step S1: after the control system (1) determines whether the separation condition is met, if yes, an ignition command is issued to the reverse thrust device (2); if no, the separation action is not performed; Step S2: after issuing an ignition command, pressure is established through the reverse thrust device (2), and after the pressure is established, an ignition command is issued to the separation pyrotechnic device through the control system (1); Step S3: After the separation pyrotechnic device is unlocked, the reverse thrust device (2) provides the booster (6) with a thrust in the opposite direction of the movement, and the separation spring device (3) pushes the aircraft (5) forward and pushes the booster (6) backward, so that the distance between the aircraft (5) and the booster (6) is gradually increased; Step S4: determining, by the control system (1), whether the aircraft (5) meets the start-up control conditions; if so, starting the control of the aircraft (5) to enter the next flight phase.

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