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51.发明申请
公开(公告)号：WO99019211A1
公开(公告)日：1999-04-22
申请号：PCT/US1998/021844
申请日：1998-10-15
摘要： A method for controlling the acceleration of a vehicle (10) reentering the sensible atmosphere, comprising executing a lofting translational rocket burn at an altitude of greater than about 40 km whereby the vehicle (10) reenters the sensible atmosphere at a maximum accelerative force of less than 4g.
摘要翻译： 一种用于控制重新进入敏感气氛的车辆（10）的加速度的方法，包括在高于约40km的高度执行放样平移火箭燃烧，由此车辆（10）以较小的最大加速力重新输入感觉气氛 比4g。
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公开(公告)号：WO99016668A1
公开(公告)日：1999-04-08
申请号：PCT/US1998/019958
申请日：1998-09-25
摘要： A method for use in a spacecraft (10) for controlling yaw angle deviations from a desired yaw angle profile. The method includes the steps of: (a) operating a profile generator (12) to output roll angle, pitch angle, yaw momentum, and yaw angle profiles, the profiles being calculated to meet spacecraft pointing requirements while operating in an inclined orbit; (b) inputting to an observer (30) raw roll-axis sensor measurements, commanded and measured yaw-axis wheel momentum storage, measured pitch-axis wheel momentum storage, and external roll-axis and yaw-axis torques, the observer (30) generating a yaw angle estimate and a yaw momentum estimate; (c) subtracting the yaw angle profile from the yaw angle estimate to obtain a difference value; and (d) using the difference value and the yaw momentum estimate to control roll-axis thruster firings to limit spacecraft yaw angle deviations from the yaw angle profile.
摘要翻译： 一种用于在航天器（10）中用于控制偏航角偏离所需偏航角分布的方法。 该方法包括以下步骤：（a）操作轮廓发生器（12）以输出侧倾角，俯仰角，横摆角度和偏航角分布，所述轮廓被计算以满足航空器指向要求，同时在倾斜轨道中操作; （b）向观察者（30）输入原始滚轴轴传感器测量，指令和测量的偏航轴轮动量存储，测量的俯仰轴轮动量存储以及外部滚动轴和偏航轴转矩，观察者（30 ）产生偏航角估计和偏航动量估计; （c）从所述偏航角估计值减去所述偏航角分布以获得差值; 和（d）使用差值和横摆动量估计来控制侧倾轴推进器发射，以限制航空器偏航角与偏航角分布的偏差。
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53.发明申请METHOD FOR LOW-FUEL, COMPUTER-ASSISTED CONTROL OF ANY NUMBER OF THRUSTERS ARRANGED ON A SPACECRAFT 审中-公开METHOD FOR FUEL最小，计算机辅助控制任何在太空船内的ARRANGED JETS
公开(公告)号：WO98049058A1
公开(公告)日：1998-11-05
申请号：PCT/EP1998/001595
申请日：1998-03-19
CPC分类号： B64G1/26
摘要： The invention relates to a method for low-fuel, computer-assisted control of any number of thrusts mounted in any given arrangement on a spacecraft, which solves the problem of linear optimization by reducing computational effort in a very short time. The method is based on the dual simplex algorithm and suitable provision of a dual admission start table. The dual admission start table is set up on the basis of a previously calculated optimum table and a transformation of the actual force/power vector pertaining to the chosen optimum table. Given processing steps of the dual simplex algorithm are skipped totally or are substituted by processing steps which require substantially less computational effort. Finally, a reduced table as opposed to the simplex table is used. Said reduced table consists solely of an identification number for selecting a thruster from the entire number of thrusters and the vector of the control values of the thrusters which are contained in said selection. Reduction in computational effort is achieved by carrying out given processing steps in advance and by providing the corresponding results in the form of data fields and index or identification number matrixes in the working memory of the computer. Said results from the initialization phase of the method need only to be addressed and retrieved in order to calculate thruster control.
摘要翻译： 它应在航天器被指定为用于通过减少在最短的时间内计算的复杂性解决了这个线性优化问题的一个任意确定数目的总燃料最小计算机辅助控制和喷嘴的任意指定结构的过程。 该方法是基于双单纯形算法和双审定起飞面板的适当规定。 双可行起始画面是由一个预先计算的最佳画面，并与当前权力矩向量的该选择的开始画面转变。 双单纯形算法的某些Verarbeitungssschritte完全省去或通过处理需要显著较少的计算步骤所取代。 最后，你不单纯工作表中，但减少了面板。 这种减小表只包括用于从喷嘴的总数和控制值的被包括在该喷嘴选择那些喷嘴载体的喷嘴的选择的识别号码的。 的计算复杂性在某些处理步骤实现的减少被预先执行，并且然后准备在数据字段和Indizes- Identifikationsnummernmatrizen的形式或在计算机的存储器中的相应的结果。 该过程Initialisierungsteils的这些结果然后只需要加以解决，以计算喷嘴驱动和检索。
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公开(公告)号：WO2022200189A1
公开(公告)日：2022-09-29
申请号：PCT/EP2022/057080
申请日：2022-03-17
发明人： MAY, Lutz
摘要： A fluid pump for generating a fluid stream (55) is provided. The fluid pump includes a first actuator (20) with a first vibration element, a second actuator (30) with a second vibration element, and a power source that is connected to the first actuator and second actuator to supply energy to the first actuator and second actuator. The fluid pump further includes a controller that is connected to the power source and controls the power source to vary the energy supplied to the first actuator and second actuator. The first actuator (20) and the second actuator (30) are arranged opposite to each other so that a first movement direction of the first vibration element is inclined with respect to a second movement direction of the second vibration element. The controller controls the power source so that the first vibration element moves towards the second actuator and the second vibration element moves towards the first actuator in a synchronous manner and thereby cyclically soaks in a fluid from the surroundings and ejects the fluid in a directed manner.
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公开(公告)号：WO2021161873A1
公开(公告)日：2021-08-19
申请号：PCT/JP2021/003950
申请日：2021-02-03
申请人： 三菱重工業株式会社
IPC分类号： B60F5/00 , B64C27/04 , B64D25/00 , B64D27/20 , B64D45/00 , F02K9/30 , F02K9/32 , F02K1/78 , B64G1/26
摘要： 推進装置は、ガスジェネレータと、複数のスラスタとを備える。ガスジェネレータは、飛行体が緊急条件を満たすときに、燃焼ガスを生成する。ここで、複数のスラスタは、下向きに燃焼ガスを出力する。また、飛行体の進行方向から見ると、複数のスラスタは、ガスジェネレータとオーバーラップしてもよい。さらに、複数のスラスタは、飛行体の姿勢を制御してもよい。また、複数のスラスタは、飛行体の少なくとも一部の着陸に基づき、燃焼ガスの出力を第１出力に低下してもよい。
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公开(公告)号：WO2021074910A1
公开(公告)日：2021-04-22
申请号：PCT/IB2020/059821
申请日：2020-10-19
摘要： An on-orbit servicing spacecraft (1) comprising an engagement system (4) to engage a space vehicle or object (5) to be serviced or tugged, so as to form a space system (6); and an electronic reaction control system (7) to cause the spacecraft (1) to rotate about roll, yaw, and pitch axes to control attitude and displacement along given trajectories to cause the spacecraft (1) to carry out given manoeuvres. The electronic reaction control system (7 ) comprises a sensory system (8 ) to directly sense physical quantities or allow physical quantities to be indirectly computed based on sensed physical quantities comprising one or more of position, attitude, angular rates, available fuel, geometrical features, and onboard systems state; attitude control thrusters (9) mounted so as to allow their positions and orientations to be adjustable; and an attitude control computer (10) in communication with the sensory system (8) and the attitude control thrusters (9) and programmed to receive data from the sensory system (8) and to control, based on the received data, positions, orientations, and operating states of the attitude control thrusters (9) so as to control attitude and position of the spacecraft (l).The attitude control computer (10) is programmed to cause the spacecraft (1) to carry out a given mission comprising an engagement step, in which the engagement system (4) and the attitude control thrusters (9) are controlled by the attitude control computer (10) to engage a space vehicle or object (5) to be serviced or tugged, and one or more operating steps, in each of which the attitude control thrusters (9) are controlled by the attitude control computer (10) to meet one or more requirements established for the operating step. Each operating step may comprise at least one stabilisation sub-step (FS), during which the attitude of the space system (6) is stabilised in accordance with the requirements of the operating step and with a given optimisation criterion, followed by a steady operating sub-step (FR), which starts when the stabilisation sub-step of the attitude of the space system (6) ends. In each operating step the attitude control computer (10) is further programmed to optimise a configuration of the attitude control thrusters (9) in accordance with the requirements of the operating step by implementing an iterative process of optimisation of the configuration of the attitude control thrusters (9).
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公开(公告)号：WO2020257649A1
公开(公告)日：2020-12-24
申请号：PCT/US2020/038735
申请日：2020-06-19
发明人： CAVITT, Ryan, C. , ORMONDE, Trevor, P. , CAREY, Jake, W. , SATYSHUR, Patrick, D. , ST. CLAIR, Christopher, P. , MUNSON, Scott, M.
摘要： Various embodiments of a vortex thruster system is described herein that is configured to create at least three discrete thrust levels. In some embodiments, the vortex thruster system is configured to decompose a monopropellant and deliver the decomposed monopropellant into a vortex combustion chamber for generating various thrust levels. In some embodiments, the vortex thruster system includes a secondary propellant valve configured to deliver a secondary propellant into the vortex combustion chamber containing decomposed monopropellant to create a high thrust level. Related systems, methods, and articles of manufacture are also described.
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公开(公告)号：WO2019224954A1
公开(公告)日：2019-11-28
申请号：PCT/JP2018/019880
申请日：2018-05-23
申请人： 三菱電機株式会社
摘要： 従来の線形計画問題求解システムは、反復を伴う内点法やシンプレックス法を用いるため、最適解が得るまでに必要な時間の見積り、制御サイクル内で最適解を得る保証が困難。制約係数行列および費用ベクトルの情報を入力として、線形計画問題を主問題とする双対問題および双対問題の制約条件の式のうち有効な組合せを表す有効セットを全て求め、有効セットごとに制約条件が有効となる実行可能な双対解候補を求めて有効セットと関連付けて双対解候補を記憶部（４）に記憶する双対解候補探索部（２２）と、制約ベクトルを入力とし、記憶部（４）に記憶された双対解候補と制約ベクトルとの内積から最適となる有効セットを選択し、選択した有効セットに対応する実行可能基底解を最適解として求めて出力する最適解算出装置（３）とを備える。
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公开(公告)号：WO2019176135A1
公开(公告)日：2019-09-19
申请号：PCT/JP2018/032278
申请日：2018-08-24
摘要： A spacecraft including a spacecraft bus and a set of thrusters for changing a pose of the spacecraft. Wherein at least two thrusters are mounted on a gimbaled boom assembly connecting the two thrusters with the spacecraft bus, such that the two thrusters are coupled thrusters sharing the same gimbal angle. A model predictive controller to produce a solution for controlling thrusters of the spacecraft by optimizing a cost function over multiple receding horizons. The cost function is composed of a cost accumulated over the multiple receding horizons, including a cost accumulated over a first horizon using a dynamics governing a north-south position of the spacecraft, and a cost accumulated over a second horizon using a model of dynamics of the spacecraft governing an east-west position. A thruster controller to operate the thrusters according to their corresponding signals.
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公开(公告)号：WO2019021220A1
公开(公告)日：2019-01-31
申请号：PCT/IB2018/055563
申请日：2018-07-25
摘要： The present invention relates to a re-entry module comprising an alpha-dome comprising a petal structures [1-5, 49] positioned on the upper surface [7] of the base for enclosing the payload; Omega hexon positioned parallel to surface [9] and comprising of a base [16], a spike [24] and nozzle [15]; and a plurality of hexon positioned on the periphery of spike [24] wherein hexon is a modified scramjet engine having an outlet velocity vector positioned at an angle θ to the inlet velocity vector, wherein, omega hexon is provided with the inlet vents [26] positioned with spike [24] for the inflow of free stream air, a Delta area where fuel and compressed air interact and flame holders, and wherein, the gases formed will expand and pass through the aerospike nozzle [15], resulting in providing retro thrust to the re-entry module.
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