Dual rocket booster drone launcher

Abstract

The present invention relates to a dual-rocket booster UAV launch device, which is characterized by comprising a UAV, a launch landing gear, a rocket booster, and a rocket booster rack. A forward force transmission axis, a rear force transmission axis, and a rear fulcrum of the fuselage are arranged on the fuselage of the UAV. The forward force transmission axis and the rear force transmission axis are arranged on the side of the UAV fuselage, and the rear fulcrum of the fuselage is arranged at the tail of the UAV. Under the same UAV center of mass deviation, the launch stability of the rocket booster symmetrically arranged UAV launcher is significantly better than that of a single rocket booster. The device can simplify the pre-field launch preparation of the UAV and improve the UAV's rapid battlefield response capability.

Description

Technical Field

[0001] The invention relates to a launching device for a drone, and belongs to the technical field of unmanned aerial vehicles, in particular to the technical field of launching drones. Background Art

[0002] There are many ways for small fixed-wing UAVs to take off, such as catapult takeoff, rolling takeoff, vertical takeoff, and rocket-assisted zero-length takeoff. Rocket-assisted zero-length takeoff has the advantages of being convenient, fast, having no strict requirements on the launch site, and being suitable for field environments.

[0003] At present, the rocket-assisted takeoff method of UAVs is mainly single-rocket-assisted takeoff, which has the advantages of low launch cost and mature and reliable technology. Most domestic UAVs use single-rocket-assisted takeoff, such as the "ASN301" anti-radiation UAV and the "Sand Cone" UAV. Internationally, the dual-rocket-assisted takeoff method has been widely used in UAVs, such as the famous "BQM-74E" series and "BQM-177" series in the United States, and the "Mirachi" series of UAVs in Italy.

[0004] However, when the UAV adopts a single rocket booster takeoff method, the installation angle and thrust line position of the rocket booster must be strictly adjusted to make the thrust line pass through the center of gravity of the UAV as much as possible to ensure the safe launch of the UAV. In actual applications, single rocket booster takeoff UAVs usually adopt a combination of mass balancing and suspension adjustment to keep the deviation between the rocket booster thrust line and the center of gravity of the UAV within an allowable range.

[0005] In order to improve the competitiveness of UAV products, modern UAVs basically have the characteristics of low manufacturing cost and diversified mission payloads. This causes the overall center of gravity of the UAV to often deviate from the theoretical center of gravity. If a single rocket-assisted takeoff method is used, it is required that the position of the thrust line of the UAV rocket booster be strictly adjusted before each launch, that is, the launch site must be equipped with hanging support equipment and can only be on land. Therefore, the single rocket-assisted takeoff method causes the UAV to be unable to achieve go-around under the alternating replacement of multiple mission payloads in some field combat environments (such as on land without hanging support equipment, and on ships for training in the open sea), which greatly reduces the combat effectiveness of the UAV. Summary of the invention

[0006] The purpose of the present invention is to provide a dual-rocket booster UAV launch device, which is used to reduce the influence of the actual deviation of the UAV center of mass position on the launch stability, thereby reducing the pre-launch preparation work in the field and realizing a non-hanging go-around under certain conditions in the field environment.

[0007] The technical solution adopted by the present invention is: a dual rocket booster UAV launch device, comprising a UAV, a launch landing gear, a rocket booster, and a rocket booster rack, wherein a forward force transmission axis, a rear force transmission axis, and a rear fulcrum of the fuselage are arranged on the fuselage of the UAV, wherein the forward force transmission axis and the rear force transmission axis are arranged on the side of the fuselage of the UAV, and the rear fulcrum of the fuselage is arranged at the tail of the UAV;

[0008] The rocket booster bracket is in contact with the UAV, and the rocket booster bracket accommodates the rocket booster. A forward force transmission axis interface and a rear force transmission axis interface are provided at the front end and the rear end of the rocket booster bracket, and the forward force transmission axis interface and the rear force transmission axis interface are in contact with the forward force transmission axis and the rear force transmission axis respectively;

[0009] The launching landing gear is provided with a front support and a rear support, wherein the front support is in contact with the front force transmission axis of the UAV, and the rear support is in contact with the rear fulcrum of the fuselage of the UAV.

[0010] A main load-bearing surface and a side limit surface are arranged on the rocket booster bracket. The top of the rocket booster contacts the main load-bearing surface, and the side contacts the side limit surface. A rocket booster fixing belt is also arranged on the side limit surface, and the fixing belt is wrapped around the middle part of the rocket booster.

[0011] The front support is arranged at the front end of the launch landing gear, and the rear support is arranged at the rear end of the launch landing gear. The front support is rotatably connected to the launch landing gear. A front support groove for accommodating the front force transmission axis is arranged at the top of the front support, and a rear support groove for supporting the rear fulcrum of the fuselage arranged at the tail of the UAV is arranged at the top of the rear support.

[0012] A limit pin groove is also provided on the front support, and a limit pin is provided at the interface of the front force transmission shaft, and the limit pin interferes with the limit pin groove;

[0013] The front force transmission shaft interface is semicircular, and the rear force transmission shaft interface is semicircular hook-shaped.

[0014] The front force transmission shaft and the rear force transmission shaft are provided in two groups, which are respectively located on the left and right sides of the fuselage and arranged symmetrically; the roots of the front force transmission shaft and the rear force transmission shaft extend into the fuselage and are fixedly connected to the reinforcement frame inside the fuselage.

[0015] By comparing with the commonly used single rocket booster, the following conclusion can be drawn: under the same UAV center of mass deviation, the launch stability of the rocket booster symmetrical arrangement UAV launcher is significantly better than that of the single rocket booster. This device can simplify the UAV's field pre-launch preparation work and improve the UAV's battlefield rapid response capability. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is the appearance diagram of the present invention.

[0017] Figure 2This is a diagram of the coordination structure of the drone and the rear support of the present invention.

[0018] Figure 3 This is a diagram of the rear support structure of the present invention.

[0019] Figure 4 This is a diagram of the coordination structure of the drone and the front support of the present invention.

[0020] Figure 5 It is a schematic diagram of the combination of the rocket booster and the pylon of the UAV of the present invention.

[0021] Figure 6 This is a structural diagram of the UAV rocket booster bracket of the present invention.

[0022] Figure 7 This is a schematic diagram of a state in which the rocket booster-rocket booster rack-limit pin-rocket booster rack fixing belt assembly of the present invention and the UAV have been completely separated.

[0023] Figure 8 This is a time-course curve of pitch angle change for rocket booster symmetrically arranged booster takeoff.

[0024] Fig. 9 This is a single rocket-assisted takeoff - pitch angle change time course curve.

[0025] Fig.10 This is a time-course curve of the roll angle change during rocket booster symmetrically arranged booster takeoff.

[0026] Fig.11 This is the time course curve of roll angle change during single rocket-assisted takeoff.

[0027] Fig.12 This is a time-course curve of pitch angle change for rocket booster symmetrically arranged booster takeoff.

[0028] Fig.13 This is a time-course curve of the rocket booster's symmetrically arranged booster takeoff and the change in center of mass height.

[0029] Fig.14 This is a single rocket-assisted takeoff - pitch angle change time course curve.

[0030] Fig.15 This is a single rocket boosted takeoff-center of mass height change time course curve.

[0031] Among them, the drone 1, the front support 2, the launch landing gear 3, the rear support 4, the rocket booster 5, the rocket booster bracket 6, the front force transmission shaft 7, the rear force transmission shaft 8, the front force transmission shaft interface 9, the rear force transmission shaft interface 10, the limit pin 11, the limit pin groove 12, the rear fulcrum of the fuselage 13, the rear support groove 14, the front support groove 15, the rocket booster bracket fixing belt 16, the rocket booster bracket main load-bearing surface 17 and the rocket booster bracket side limit surface 18. DETAILED DESCRIPTION

[0032] The technology of the present invention is further described in detail below:

[0033] The present invention relates to a dual-rocket UAV launching device, such as Figure 1-6 As shown, the launching device includes a UAV 1, a front support 2, a launching landing gear 3, a rear support 4, a rocket booster 5, a rocket booster rack 6, a front force transmission shaft 7, a rear force transmission shaft 8, a front force transmission shaft interface 9, a rear force transmission shaft interface 10, a limit pin 11, a limit pin groove 12, a rear fulcrum of the fuselage 13, a rear support groove 14, a front support groove 15, a rocket booster rack fixing belt 16, a rocket booster rack main bearing surface 17 and a rocket booster rack side limit surface 18.

[0034] A rotation constraint is adopted between the front support 2 and the launcher 3. During the launch of the UAV, as the fuselage moves forward, the front force transmission shaft 7 pushes the front support 2 to rotate forward. Fixed constraints are adopted between the rear support 4 and the launcher 3 and the rear support groove 14, thereby realizing the support of the rear fulcrum 13 of the fuselage during the launch and launch of the UAV.

[0035] The launcher is a three-point support method. When the UAV is installed on the launcher, the left (right) side front force transmission shaft 7 attached to the fuselage contacts the left (right) side front support groove 15 on the front support 2, and the rear support point 13 of the fuselage contacts the rear support groove 14.

[0036] The rocket booster 5 and the rocket booster rack 6 are symmetrically arranged on both sides of the fuselage. Before the UAV 1 is launched, the rocket booster 5, the rocket booster rack 6, the limit pin 11, and the rocket booster rack fixing belt 16 are first installed together, and then the assembly is installed to the corresponding position on the UAV 1. The front end surface of the rocket booster 5 is a plane and is in close contact with the main bearing surface 17 of the rocket booster rack; under the action of the rocket booster rack fixing belt 16, the cylindrical section of the rocket booster 5 is in close contact with the side limit surface 18 of the rocket booster rack.

[0037] After the assembly of the rocket booster 5, the rocket booster bracket 6, the limit pin 11, and the rocket booster bracket fixing belt 16 is installed on the UAV, the forward force transmission shaft interface 9 of the rocket booster bracket 6 cooperates with the forward force transmission shaft 7 attached to the fuselage, and the rear force transmission shaft interface 10 cooperates with the rear force transmission shaft 8 attached to the fuselage, thereby realizing the transmission of the thrust of the rocket booster to the UAV. The shape of the forward force transmission shaft interface 9 is designed to be semicircular, and the shape of the rear force transmission shaft interface 10 is designed to be semicircular hook.

[0038] A limit pin groove 12 is provided at the top of the front support 2, and a limit pin 11 is provided at the front end of the rocket booster bracket 6. After the combination of the rocket booster 5 and the rocket booster bracket 6 is installed on the UAV 1, the front limit pin 11 of the rocket booster bracket 6 will fall into the limit pin groove 12 at the top of the front support 2, thereby realizing the limit along the axial direction of the UAV fuselage. The cooperation of the limit pin 11 and the limit pin groove 12 can effectively prevent the rocket booster 5 and the rocket booster bracket 6 from sliding along the front force transmission axis 7 and the rear force transmission axis 8 toward the tail of the fuselage under the action of the gravity field before the rocket booster 5 is ignited. In addition, the outlet profile of the limit pin groove 12 is matched and optimized to achieve that the limit pin 11 will not cause structural interference with the limit pin groove 12 during the process of the UAV 1 leaving the frame.

[0039] The four front and rear force transmission shafts 7 and 8 attached to the UAV fuselage are located on the left and right sides of the fuselage and are arranged symmetrically; the roots of the force transmission shafts extend into the fuselage and are fixedly connected to the reinforcement frame inside the fuselage.

[0040] After the rocket booster 5 and the rocket booster bracket 6 are installed, there is a certain angle α between the axis of the rocket booster 5 and the symmetry plane of the fuselage, and generally speaking, the angle is between 15° and 20°.

[0041] When the thrust of the rocket booster 5 drops to zero after the work is finished, the combination of the rocket booster 5 and the rocket booster bracket 6 gradually slides in the opposite direction of the movement of the UAV 1 under the joint constraints of aerodynamic force, gravity, and the forward force shaft 7 and the rear force shaft 8. When the sliding distance exceeds the radius of the forward force shaft 7, the constraints of the forward force shaft 7 on the forward force shaft interface 9 and the rear force shaft 8 on the rear force shaft interface 10 disappear at the same time, and the combination of the rocket booster 5 and the rocket booster bracket 6 is completely separated from the UAV 1, and the combination gradually moves toward the rear and lower rear of the fuselage, and enters the rocket booster separation state.

[0042] The deviation of the actual position of the UAV's center of mass along the three directions of the body coordinate system was compared and analyzed, and the impact of the deviation on the UAV's launch stability under the two launch methods was compared and analyzed.

[0043] 1. Analysis of the impact of the X-axis position deviation of the center of mass of a UAV on takeoff safety

[0044] The X-axis position deviation of the drone's center of mass mainly affects the pitch attitude and height of the drone during takeoff.

[0045] Taking two working conditions, the center of mass is at the theoretical position and the center of mass moves forward 30 mm along the X-axis of the body coordinate system, and calculating the pitch angle and height changes of the UAV under the two boosting modes, as shown in the figure. Figure 8-9 The comparison results are shown in Table 1. Figure 8-9 As can be seen from Table 1:

[0046] (1) The minimum pitch angles of the UAV using the rocket booster symmetrical arrangement takeoff mode are 13.5° and 9.5° respectively, and the pitch angle deviation under the two working conditions is about 22%; the minimum pitch angles of the UAV using the single rocket booster takeoff mode are 5° and -21° respectively, and the pitch angle deviation under the two working conditions is about 502%;

[0047] (2) At 10 seconds, the center of mass heights of the UAV using the rocket booster symmetrical arrangement booster takeoff method were 114m and 90m respectively, and the pitch angle deviation under the two working conditions was about 21%; the center of mass heights of the UAV using the single rocket booster takeoff method were 100m and -39m respectively, and the pitch angle deviation under the two working conditions was about 139%;

[0048] (3) At 2.8s, the pitch angle of the drone is close to -22°; at 3.95s, the center of mass of the drone is close to zero. Under this condition, the drone will fall to the ground soon after takeoff.

[0049] Table 1 Comparison results of evaluation parameters

[0050]

[0051] 2. Analysis of the impact of the Y-axis position deviation of the center of mass of the UAV on takeoff safety

[0052] The Y-axis position deviation of the center of mass of the drone mainly affects the rolling attitude and yaw attitude of the drone during take-off. The present invention only analyzes the influence of the Y-axis position deviation of the center of mass of the drone on the rolling attitude.

[0053] Taking the center of mass at the theoretical position and the center of mass shifted 3 mm to the left along the Y axis of the body coordinate system, the changes in the roll angle of the UAV under the two boost modes are calculated. Figure 10-11 The comparison results are shown in Table 2. Figure 10-11 As can be seen in Table 2;

[0054] (1) When the center of mass is at the theoretical position, the rolling attitude angle of the UAV is almost 0° in both propulsion modes;

[0055] (2) The maximum roll angle of a UAV using a symmetrical rocket booster takeoff method is 9.6°, and the maximum roll angle of a UAV using a single rocket booster takeoff method is 18°;

[0056] (3) From the perspective of the maximum roll angle, the single rocket booster takeoff method is 88% higher than the rocket booster symmetrical arrangement takeoff method.

[0057] Evaluation parameters Symmetrical boost takeoff Single rocket boost takeoff Deviation (based on the symmetrically arranged boost takeoff value) / % Maximum roll angle 9.6° 18° 88%

[0058] 3. Analysis of the impact of the Z-axis position deviation of the center of mass of a UAV on takeoff safety

[0059] The Z-axis position deviation of the drone's center of mass mainly affects the pitch attitude and height of the drone during takeoff.

[0060] Taking two working conditions, the center of mass is at the theoretical position and the center of mass is moved down 3mm along the Z axis of the body coordinate system, and the pitch angle and height changes of the UAV under two rocket-assisted take-off modes are calculated. Figure 12-15 The comparison results are shown in Table 3. Figure 12-15 As can be seen from Table 3:

[0061] (1) The minimum pitch angles of the UAV using the rocket booster symmetrical arrangement takeoff mode are 13.5° and 11° respectively, and the pitch angle deviation under the two working conditions is about 19%; the minimum pitch angles of the UAV using the single rocket booster takeoff mode are 4.9° and -11° respectively, and the pitch angle deviation under the two working conditions is about 324%;

[0062] (2) At 10 seconds, the center of mass heights of the UAV using the rocket booster symmetrical arrangement booster takeoff method were 114m and 95m respectively, and the pitch angle deviation under the two working conditions was about 17%; the center of mass heights of the UAV using the single rocket booster takeoff method were 100m and 25m respectively, and the center of mass height deviation under the two working conditions was about 75%;

[0063] (3) Using a single rocket-assisted takeoff method, the pitch angle of the UAV was close to -11° at 3.0s, and the center of mass height of the UAV had dropped to about 12.3m at 6.5s.

[0064] Table 3 Comparison results of evaluation parameters

[0065]

[0066] The above are only specific steps of the present invention, which can be extended to the launch field of unmanned aerial vehicles, including drones, missiles, cruise missiles, etc.

Claims

1. A dual rocket booster UAV launch device, characterized in that: It includes a drone, a launch landing gear, a rocket booster, and a rocket booster rack. A forward force transmission axis, a rear force transmission axis, and a rear fulcrum of the fuselage are arranged on the fuselage of the drone. The forward force transmission axis and the rear force transmission axis are arranged on the side of the fuselage of the drone, and the rear fulcrum of the fuselage is arranged at the tail of the drone. The rocket booster bracket is in contact with the UAV, and the rocket booster bracket accommodates the rocket booster. A forward force transmission axis interface and a rear force transmission axis interface are provided at the front end and the rear end of the rocket booster bracket, and the forward force transmission axis interface and the rear force transmission axis interface are in contact with the forward force transmission axis and the rear force transmission axis respectively; A front support and a rear support are arranged on the launching landing gear, wherein the front support contacts the front force transmission axis of the UAV, and the rear support contacts the rear fulcrum of the fuselage of the UAV; The rocket booster rack is provided with a main load-bearing surface and a side limit surface, the top of the rocket booster contacts the main load-bearing surface, and the side contacts the side limit surface. A rocket booster fixing belt is also provided on the side limit surface, and the fixing belt is wound around the middle of the rocket booster; The front support is arranged at the front end of the launch landing gear, and the rear support is arranged at the rear end of the launch landing gear. The front support is rotatably connected to the launch landing gear. A front support groove for accommodating the front force transmission axis is arranged at the top of the front support, and a rear support groove for supporting the rear fulcrum of the fuselage arranged at the tail of the UAV is arranged at the top of the rear support.

2. The dual rocket booster UAV launch device according to claim 1, characterized in that: A limit pin groove is also arranged on the front support, and a limit pin is arranged at the interface of the front force transmission shaft, and the limit pin interferes with the limit pin groove.

3. The dual rocket booster UAV launch device according to claim 1, characterized in that: The front force transmission shaft interface is semicircular, and the rear force transmission shaft interface is semicircular hook-shaped.

4. The dual rocket booster UAV launcher according to claim 1, characterized in that: The front force transmission shaft and the rear force transmission shaft are provided in two groups, which are respectively located on the left and right sides of the fuselage and arranged symmetrically; the roots of the front force transmission shaft and the rear force transmission shaft extend into the fuselage and are fixedly connected to the reinforcement frame inside the fuselage.

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