Double-wing two-engine embedded flight state conversion field quality guarantee unmanned aerial vehicle

Abstract

The invention discloses a double-wing two-engine embedded flight state conversion field quality assurance unmanned aerial vehicle based on injection molding as a main part. The unmanned aerial vehicle comprises a box body group, a wing group, an empennage group, a double-engine group, a spraying device, a landing device, a camera and the like. The problems of tedious production process, high manufacturing cost and the like are solved through an injection molding process; through attitude conversion during cruising flight, namely buoyancy / lift force generated by wings including empennages in a cruising flight mode, energy saving during cruising is achieved like aircraft flight. The unmanned aerial vehicle is shaped like a box body in a static state, lifts off like a helicopter during takeoff, and flies like an aircraft with air buoyancy / lift during cruising flight. In short, the production cost is reduced through the injection molding process; the air holding capability and the cruising capability of cruising flight are brought through the conversion of flight attitude; therefore, the device is suitable for field quality assurance, can be remotely controlled by a mobile phone, and brings opportunities for popularization and use.

Description

Technical Field

[0001] The invention relates to the technical fields of injection molding and unmanned aerial vehicle (UAV), in particular to a field quality assurance UAV with double wings and two engines and flight posture changes. Background Art

[0002] With the continuous development of rural modernization, the extensive use of Beidou navigation technology, and the fact that everyone has a 5G mobile phone today; with the help of Beidou navigation and 5G information transmission, including video APP transmission, the speed and convenience of field quality assurance drones have been favored by farm workers, showing a good application prospect. However, most of the current farmland operations are carried out by helicopters. Since all loads need to be borne by the engine (including the battery pack) when the helicopter is flying, it is not efficient as a transportation method; moreover, it is difficult to meet people's demands for long-distance flights because the battery needs to be charged or replaced from time to time. If the drone is expanded to fly with wings, the energy-saving effect will be greatly improved due to the clamping of flight buoyancy / or lift, that is, like an airplane flying; it also greatly expands the flight distance and hovering ability of the drone in the field, which means that this will bring about gratifying changes.

[0003] Imagine if the aircraft took off like a helicopter, taking off from a very low altitude such as a courtyard or a threshing floor, and then converted to a wingspan-like aircraft when it reached a cruising altitude; the efficiency could be doubled by virtue of the buoyancy and / or lift generated by the headwind; not only that, with the support of 5G communications and Beidou navigation technology, we can now develop the battery-driven drones with variable driving states that we need to meet the needs of field workers. Summary of the invention

[0004] In view of the above, the purpose of the present invention is to provide a dual-wing, dual-engine embedded flight state conversion field quality assurance UAV, through the flight attitude conversion of the UAV, with the expansion of the main and auxiliary wing projection area, the air buoyancy / or lift in the forward direction is achieved to achieve the cruise capability in accordance with the time limit. Further, when the main wing is unfolded (including the auxiliary wing can be unfolded at the same time), the flight attitude conversion of the cruise flight is achieved under the action of gravity. Further, the electromechanical reality of the flight attitude conversion is based on the injection molding process to meet the characteristics of innovation and optimization, that is, the device has a certain structural strength, performance and appearance, and the purpose of lightweight is achieved to the maximum extent. Further, the injection molding process is used for one-time molding, which significantly reduces its production process and processing difficulty, and the production cost is controlled. Further, in order to reduce the headwind resistance, the organic integration of the box body with the attitude conversion mechanism and the motor makes the UAV body structure compact. Further, with the dual-wing expansion method, the wing projection area is expanded (including the tail), and after the flight attitude conversion is achieved, the efficiency is higher and simple and reliable. Furthermore, it also solves the physical indicators of reliability, stability, installation and maintenance very well.

[0005] To achieve the above object, the present invention provides a dual-wing dual-engine embedded flight state conversion field quality assurance UAV, which is characterized by comprising:

[0006] The box group, as a basic part, is used to embed the flight attitude conversion motor to achieve flight attitude conversion after liftoff. It also includes a storage space for quality assurance liquid to achieve field spraying.

[0007] The main and auxiliary wing groups are hinged to the hinge seats on the vertical plates on both sides of the box body, and are used for the conversion of flight attitude, including the expansion of the projected area when the main and auxiliary wing groups are unfolded, like the wings of an airplane, to achieve windward buoyancy / or lift enhancement;

[0008] The tail assembly is hinged to the rear crossbar hinge seat on the box body and is used for stabilizing and adjusting the flight attitude. Like the tail of an airplane, it completes level and turning control, including the expansion of the projected area, which is conducive to improving buoyancy and / or lift.

[0009] The two engines embedded in the main wings complete the natural attitude transition from vertical takeoff to cruising flight under the action of gravity.

[0010] Preferably, the flight attitude conversion drone is characterized in that the box group includes:

[0011] There are four flange cuts in the two side vertical plates of the box body, and the upper and lower main and auxiliary wing attitude control motors are inserted into the end holes to be embedded, which are used to synchronously and / or asynchronously drive the main and auxiliary wings to change between horizontal and vertical, so as to realize the transformation from takeoff to flight attitude; and there is a built-in tail attitude control motor embedded in the rear horizontal bar, which is used to drive each white tail to change between super horizontal and vertical, so as to realize the height and azimuth adjustment in the air position when changing from takeoff to flight attitude, including the adjustment of the center of mass during vertical takeoff.

[0012] Preferably, the flight attitude conversion drone is characterized in that

[0013] The cabinet set also includes:

[0014] The rocker arms of the spraying mechanism on both sides of the rear end of the box group are connected to a submersible pump with a hose for deployment during flight operations to achieve spraying operations of pesticides and plant nutrient solutions.

[0015] Preferably, the flight attitude conversion drone is characterized in that the box group further includes:

[0016] A window is provided at the back of the box assembly for internal installation of the spray mechanism and future maintenance work; at the same time, a hose is used to form an external connection to achieve a flexible connection with the spray rocker arm.

[0017] Preferably, the flight attitude conversion drone is characterized in that the box group further comprises:

[0018] There is a cover plate on the upper part of the box group, which is used for the flat embedding of the battery / circuit box, that is, to realize the effective installation of lithium batteries, flight control drive circuits, attitude sensing circuits including altitude and azimuth, Beidou navigation signal receiving circuits, 5G signal input and processing circuits, video transmission circuits, etc.; there is a window design on the back, which is sealed for the installation and debugging of the water pump body.

[0019] The double-wing two-engine embedded flight state conversion field quality assurance UAV provided by the present invention is lightweight through the optimization of various components of the device, including modular design, especially the main parts are made by injection molding process. Furthermore, the attitude change motor of the UAV is embedded in the box, which fully demonstrates the characteristics of simple structure, reduced process difficulty and manufacturing cost, and easy inspection and maintenance. Obviously, the UAV has low cost, guaranteed structural strength, simple process, easy implementation, and can be mass-produced. Most importantly, it has good adaptability and practicality, which is convenient for promoting the popularization and application of the UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The above and other objects, features and advantages of the present invention will become more apparent through the following description of the embodiments of the present invention with reference to the accompanying drawings, in which:

[0021] Figure 1 This is a schematic diagram of equipment for a UAV cruising during flight attitude conversion according to an embodiment of the present invention;

[0022] Figure 2 This is a schematic diagram of equipment for vertical takeoff of a UAV with flight attitude conversion according to an embodiment of the present invention;

[0023] Figure 3 This is a schematic diagram of a flight attitude conversion UAV box assembly equipment according to an embodiment of the present invention;

[0024] Figure 4 This is a schematic diagram of the main and auxiliary wings of a UAV for flight attitude conversion according to an embodiment of the present invention;

[0025] Figure 5 This is a schematic diagram of the tail wing equipment of the UAV for flight attitude conversion according to an embodiment of the present invention;

[0026] Figure 6 This is a schematic diagram of equipment for a second embodiment of the present invention when a UAV with flight attitude conversion is cruising;

[0027] Figure 7 This is a schematic diagram of equipment for a third embodiment of the present invention when a UAV with flight attitude conversion is cruising;

[0028] Figure 8 This is a schematic diagram of equipment for a UAV cruising during flight attitude conversion according to the fourth embodiment of the present invention;

[0029] Fig. 9 This is a schematic diagram of equipment for taking off of a UAV with flight attitude conversion according to the fourth embodiment of the present invention;

[0030] Fig.10 This is a schematic diagram of equipment for a fifth embodiment of the present invention when a flight attitude conversion drone is cruising;

[0031] Fig.11 This is a schematic diagram of equipment for taking off of a UAV with flight attitude conversion according to the fifth embodiment of the present invention;

[0032] Fig.12 This is a schematic diagram of equipment for a sixth embodiment of the present invention when a flight attitude conversion drone is cruising;

[0033] Fig.13 It is a schematic diagram of the equipment for taking off of a UAV with flight attitude conversion according to the sixth embodiment of the present invention. Specific implementation plan

[0034] Various embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. In each of the accompanying drawings, the same elements are represented by the same or similar reference numerals. For the sake of clarity, the various parts in the accompanying drawings are drawn to scale as much as possible, for example, based on the width and height dimensions of the box. In addition, some well-known parts may not be shown in the drawings.

[0035] The specific implementation of the present invention is further described in detail below in conjunction with the accompanying drawings and examples. Many specific details of the present invention, such as the structure, materials, dimensions, processing technology and techniques of the components are described below to provide a clearer understanding of the present invention. However, as those skilled in the art will appreciate, the present invention may be implemented without following these specific details.

[0036] Figure 1 Schematic diagram of equipment for a cruising UAV with flight attitude conversion according to an embodiment of the present invention; the UAV in the figure includes: a box group 1, a main wing group 2, an auxiliary wing group 3, a tail group 4, an attitude control motor 5 (including a main wing group, an auxiliary wing group, a tail group, an engine group, and a rocker arm control), a dual engine group 6, a spray rocker arm mechanism 7 (including a rocker arm, a nozzle and a quick-connect connector, a hose, etc.), and a camera 8.

[0037] The box body 1 is made by injection molding, as the main part, and is placed in the center; when viewed from the front, the four corners of the vertical plates on both sides of the box body group form longitudinal barrel-shaped column division flanges, which are used to form a hinge seat structure, so as to realize the hinge connection of the main and auxiliary wings 2 and 3 made by injection molding, so as to complete the expansion transformation during flight - that is, to achieve low-power flight like an airplane; wherein, the box body, as the main part, is placed in the center; when viewed from the front, the four corners of the vertical plates on both sides of the box body group form longitudinal barrel-shaped column division flanges, which are used to form a hinge seat structure, so as to realize the hinge connection of the main and auxiliary wings 2 and 3 made by injection molding, so as to complete the expansion transformation during flight - that is, to achieve low-power flight like an airplane; wherein, in the front end flange holes on both sides, the reduction control motor 5 (the attitude control motor in the figure is generally referred to as 5) of the attitude rectangular axis of the main and auxiliary wings is glued and inserted, which is used to complete the linkage and support of the main and auxiliary wings (including the square axis connection in the flange holes of the main and auxiliary wings) to realize the attitude control of the main and auxiliary wings from drooping during takeoff to expansion during flight. In the upper horizontal bar on the back, there is also a transverse barrel-shaped column dividing the flange to form a hinge seat structure for the tail machine 4 made by injection molding to be hinged to complete the real-time adjustment of the level and steering after the attitude conversion; in the flange holes on both sides of the rear end, the reduction control motor 5 (the attitude control motor is generally referred to as 5 in the figure) which is glued and inserted into the rectangular axis of the tail attitude is used to complete the tail (including the square axis connection in the tail flange hole, see Figure 5) linkage and support, to achieve attitude control from the drooping of the tail during takeoff to the unfolding during flight; at the same time, the addition of the tail has expanded the projection area, that is, in the case of wind duct, it is also very helpful for the buoyancy / or lift of the drone during low-speed flight. There is a cover plate on the upper part of the box, and the lower part is used for the power supply / circuit box (see Figure 3 ) is embedded, that is, lithium batteries, flight control circuits, attitude sensing circuits including altitude and direction, 5G or Beidou positioning circuits, camera control and other circuits are installed.

[0038] The box group structure provided by the above embodiment of the present invention, as a basic component, is formed by a one-time injection molding process, the process is simple, and the structural strength is guaranteed; at the same time, the attitude control motor is glued and embedded in the flange hole to form an integrated structure, which also makes the structure simple and reliable; there is a window design on the back of the box for the installation and maintenance of the submersible pump and spraying mechanism inside the box.

[0039] Figure 2 This is a schematic diagram of the equipment for the vertical takeoff of the flight attitude conversion UAV according to an embodiment of the present invention; in the vertical takeoff attitude, it is composed of: a box 1, a main wing group 2, an auxiliary wing group 3, a tail group 4, an attitude conversion motor 5 (attitude control motors are collectively referred to as 5), a dual engine group 6, a spraying mechanism 7 (including: attitude control motor, rocker arm, submersible pump, nozzle, hose, quick connector, etc.), and a camera 8. It can be seen from the figure that the main and auxiliary wings and the tail are in a compact posture before takeoff; the key is that the body shape is like a box, which reduces the projected area and facilitates reducing the resistance and energy consumption of vertical takeoff. Comparison Figure 1 When the main and auxiliary wings 2 and 3 are unfolded, the projected area of ​​the two wings is enlarged (including the tail group 4), which is convenient for forming a larger windward buoyancy / lift, greatly reducing the engine drive energy consumption, and ensuring long-distance flight capability and longer air-holding capability.

[0040] Figure 3 Schematic diagram of the equipment of the flight attitude conversion unmanned aerial vehicle box group according to an embodiment of the present invention; as shown in the figure, the box group can be divided into two parts, the upper and lower parts, which are completed by thin-wall injection molding; in the upper part, the vertical plates on both sides of the box group form four-corner longitudinal barreled column dividing flanges for forming a hinge seat structure, realizing the hinge connection of the main and auxiliary wings made by injection molding technology, so as to complete the deployment transformation from take-off to cruising flight, that is, to generate buoyancy and / or lift in the case of headwind - that is, to form a low-power flight like an airplane; wherein, in the frontal flange hole, the main and auxiliary wing state conversion long shafts are inserted with glue and the plane reduction motor 5 (generally referred to as the attitude control motor 5) and the greased sleeves are inserted between the flanges to form a support for forming the main and auxiliary wings (including the square shaft connection in the flange holes of the main and auxiliary wings, see Figure 4) linkage to achieve attitude control from the drooping of the main and auxiliary wings at takeoff to the unfolding during flight. On the upper back, there is a transverse barrel-shaped column dividing the flange to form a hinge seat structure, which is used for the hinge of the tail group to complete the timely adjustment of the level and steering after the state attitude conversion; wherein, the rubber-coated tail attitude long axis is equipped with a plane control motor 5 (all state control motors are collectively referred to as 5), and a greased sleeve is inserted into the flange hole of the box body to complete the linkage of the tail (including the square axis connection in the tail flange hole) to achieve the attitude control from the drooping of the tail at takeoff to the upward pitch during flight; obviously, the addition of the tail expands the projection area, and in the presence of a wind duct, it is also a great help to the buoyancy and / or lift of the drone during cruising flight; at the lower part In the water storage space of the thin-walled spray liquid, there is a quality assurance liquid such as fertilizer liquid and pesticide spraying; in the internal liquid storage space, a submersible pump 9 is installed at the bottom; at the same time, hoses are connected to the rubber rings embedded in the back plate on both sides of the water pump to form a passage for the hose, and then connected to the nozzle of the spray rocker arm to complete the spraying operation; a window is set on the back of the box for the installation and maintenance of the water pump, and it is sealed in a flat manner; in addition, a lithium battery pack and a circuit system are also placed under the upper cover plate; at the two corners of the bottom surface, there are posture motors for the spray rocker arm (not shown in the figure, all state control motors are collectively referred to as 5), which are inserted and fixed with glue to form the retraction and expansion control of the rocker arm.

[0041] The box assembly structure provided by the above embodiment of the present invention, as a basic component, is formed by one-step injection molding, which is simple in process and has guaranteed structural strength; at the same time, the attitude control motor is glued and embedded in the flange hole, forming an integrated structure, which also makes the structure simple and reliable. There is a window design on the back of the box, which solves the installation and maintenance of the internal submersible pump and spraying mechanism.

[0042] Figure 4 This is a schematic diagram of the main and auxiliary wings of the UAV for flight attitude conversion according to an embodiment of the present invention; Figure 1 and 2 The main and auxiliary wings are placed on both sides of the box group, corresponding to each other, and are made by injection molding. There is a flange body on one side of the upper part of the two pieces, forming a hinge body structure, which is hinged with the hinge seat in the box to form a posture change during cruising. A square hole is reserved in the hole on the flange for inserting the long-axis wing attitude control motor 5 with a reducer to form a connection with the square hole of the flange hole, and a greased sleeve is placed in the alternate flange holes of the hinge seat on the box to complete the lubrication support of the long square axis - that is, to complete the synchronous rotation. An arc-shaped notch is reserved between the flanges to facilitate barrier-free fixed-axis rotation with the hinge seat in the box. There is a flange near the middle of the main wing for embedding the engine drive motor to complete the drive of the aircraft; the main and auxiliary wings are thin-sheet-like cantilever beams designed to reduce the wind resistance caused by the cross section; there is a corner structure at the lower end of the two pieces, similar to the tail of an aircraft, which can play a role in stabilizing flow, which is beneficial to resisting wind and stabilizing flight during flight cruising.

[0043] The main and auxiliary wings provided by the above embodiment of the present invention are hinge-type rotating parts, which are completed by injection molding process, which is simple and convenient to implement. The expanded projection area of ​​the main and auxiliary wings when deployed is the fundamental guarantee for the formation of lift and / or buoyancy during cruising.

[0044] Figure 5 The present invention is a schematic diagram of the tail structure of the flight attitude conversion drone according to the embodiment of the present invention; as shown in the figure, the tail 4 is the right and left side part, which is placed at the top corner of the upper rear side of the box group and is made by injection molding. There is a flange at the front, which is used for hinge connection with the box hinge seat to form a posture change during cruising. A square hole is reserved in the hole on the flange for inserting the long axis 5 of the tail attitude control motor (all state control motors are collectively referred to as 5) to form a connection, and a greased sleeve is placed in the alternate flange hole of the hinge seat on the box to form a long axis for necessary support to complete the synchronous rotation. There is a reserved arc notch on the flange for unobstructed free rotation when cooperating with the link seat in the box. There is an arc edge at the bottom, which is used to form an overflow effect when cruising to solve the vortex caused by the lower section. There are vertical corner surfaces on both sides, which are used to be like the tail of an aircraft in the cruising posture, playing a good role in stabilizing flow and resisting wind.

[0045] According to the above embodiment of the present invention, the tail wing provided by the flight attitude conversion drone is a rotating part, which is completed by injection molding process, and the process is simple and convenient to implement. The two tail wings can rotate asynchronously to achieve horizontal flight during cruising and attitude conversion during turning.

[0046] Figure 6 This is a schematic diagram of the equipment of the second embodiment of the present invention when the flight attitude conversion drone is cruising; Figure 1 , in the middle of the upper front crossbar, an additional flange is added for mounting three twin engines, i.e. forming a three-engine drive; the rest, Figure 1 The description is basically the same and will not be explained here.

[0047] Figure 7 This is a schematic diagram of the equipment for the UAV during the cruising of the flight attitude conversion according to the third embodiment of the present invention; Figure 1 There are flanges on both sides of the main wing for embedding the drive engine, that is, four-engine drive; others, similar to Figure 1 The description is basically the same and will not be explained here.

[0048] Figure 8 This is a schematic diagram of the equipment of the fourth embodiment of the present invention when the flight attitude conversion drone is cruising; it is a cruising attitude for small field spraying, driven by two engines, the nozzle is set at the bottom, and the camera is set at the front end of the bottom, and the lower plane sits on the ground; other Figure 1 The description is basically the same and will not be explained here.

[0049] Fig. 9Schematic diagram of equipment for taking off of a UAV with flight attitude conversion according to the fourth embodiment of the present invention; Figure 2 The description is basically the same and will not be explained here.

[0050] Fig.10 This is a schematic diagram of the equipment of the fifth embodiment of the present invention when the flight attitude conversion drone is cruising; it is used for small field spraying, and there is a recessed flange in the middle of the upper front crossbar for installing the third engine, that is, forming a three-engine drive; others, Figure 1 The description is basically the same and will not be explained here.

[0051] Fig.11 Schematic diagram of equipment for taking off of a UAV with flight attitude conversion according to the fifth embodiment of the present invention; Figure 2 The description is basically the same and will not be explained here.

[0052] Fig.12 This is a schematic diagram of the equipment of the sixth embodiment of the present invention when the flight attitude conversion drone is cruising; it is used for spraying small fields, compared with Figure 1 , twin engines are introduced from the flanges on both sides of the upper main wing, forming a total of four engines for drive; the others, Figure 1 The description is basically the same and will not be explained here.

[0053] Fig.13 Schematic diagram of equipment for taking off of a UAV with flight attitude conversion according to the sixth embodiment of the present invention; Figure 2 The description is basically the same and will not be explained here.

[0054] In summary, the embodiment of the present invention has a double-wing two-engine embedded flight state conversion field quality assurance drone, which has obvious structural compactness characteristics during takeoff and double-wing expansion characteristics during flight attitude, which greatly reduces energy consumption from takeoff to cruising flight; especially the cruising capability is greatly enhanced. The main parts are prepared by injection molding process, which is well optimized including lightweight structure, making the structure concise, bringing convenience to the overall manufacturing, and also making the cost well controlled.

[0055] The attitude control motor embedded in the box brings a good organic coordination to the control of the engine, main wing, auxiliary wing and tail wing, and the volume is reduced; at the same time, the separate control of the engine, main auxiliary wing and tail wing can strengthen the good control of the flight attitude. In short, the flight attitude conversion of the twin-engine double-wing injection molding component of the Datian quality assurance drone is drawn by the actual size, which can be refined to guide production; it also plays a role in further promoting the popularization and application of drone technology.

[0056] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. Double-wing two-engine embedded flight state conversion field quality assurance drone, characterized by: include: The box group, as a basic part, is used to embed the flight attitude conversion motor to achieve flight attitude conversion after liftoff. It also includes a storage space for quality assurance liquid to achieve field spraying. The main and auxiliary wing groups are hinged to the hinge seats on the vertical plates on both sides of the box body, and are used for the conversion of flight attitude, including the expansion of the projected area when the main and auxiliary wing groups are unfolded, like the wings of an airplane, to achieve windward buoyancy / or lift enhancement; The tail assembly is hinged to the rear crossbar hinge seat on the box body and is used for stabilizing and adjusting the flight attitude. Like the tail of an airplane, it completes level and turning control, including the expansion of the projected area, which is conducive to improving buoyancy and / or lift. The two engines embedded in the main wings complete the natural attitude transition from vertical takeoff to cruising flight under the action of gravity.

2. The flight attitude conversion UAV according to claim 1, characterized in that: The box group includes: There are four flange cuts in the two side vertical plates of the box body, and the upper and lower main and auxiliary wing attitude control motors are inserted into the end holes to be embedded, which are used to synchronously and / or asynchronously drive the main and auxiliary wings to change between horizontal and vertical, so as to realize the transformation from takeoff to flight attitude; and there is a built-in tail attitude control motor embedded in the rear horizontal bar, which is used to drive each white tail to change between super horizontal and vertical, so as to realize the height and azimuth adjustment in the air position when changing from takeoff to flight attitude, including the adjustment of the center of mass during vertical takeoff.

3. The flight attitude conversion UAV according to claim 2, characterized in that: The box group also includes: The rocker arms of the spraying mechanism on both sides of the rear end of the box group are connected to a submersible pump with a hose for deployment during flight operations to achieve spraying operations of pesticides and plant nutrient solutions.

4. The flight attitude conversion UAV according to claim 2, characterized in that: The box group also includes: A window is provided at the back of the box assembly for internal installation of the spray mechanism and future maintenance work; at the same time, a hose is used to form an external connection to achieve a flexible connection with the spray rocker arm.

5. The flight attitude conversion UAV according to claim 2, characterized in that: The box group also includes: There is a cover plate on the upper part of the box group, which is used for the flat embedding of the battery / circuit box, that is, to realize the effective installation of lithium batteries, flight control drive circuits, attitude sensing circuits including altitude and azimuth, Beidou navigation signal receiving circuits, 5G signal input and processing circuits, video transmission circuits, etc.; there is a window design on the back and a sealing treatment for the installation and debugging of the water pump body.

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